cruise missile speed. The long arm of the Russian Aerospace Forces is long-range aviation cruise missiles. Productions in different countries
Introduction
1.Preliminary survey
1.1 Prototype analysis
2 Modern requirements to RC design
2.1 Technical requirements
2.2 Operational requirements
2.3 Tactical requirements
3 Choice of aircraft aerodynamic scheme
3.1 Total evaluation of projectiles of various schemes
3.2 Conclusions
4 The choice of geometric parameters of the aircraft
5 Rationale for the choice of start type
6 Propulsion system selection
7 Choice of materials of construction
8 Selecting the control method
9 Selecting the type of control system and aiming the missile at the target
10 Selecting the type of calculated trajectory
11 Steering gear type rationale
12 Warhead type selection
13 Preliminary layout of the rocket
13.1 Power supply scheme
13.2 Missile nose
13.3 Warhead compartment
13.4 Tank compartment
13.5 Flight equipment compartment
13.6 Remote control compartment
1 Basic functions of CAD aircraft
2 Calculation of the parameters of the trajectory and appearance of the aircraft in the CAD 602 program
2.1 Generation task
2.2 Initial data
2.3 Program
2.4 Calculation results
2.5 Calculation of the launch weight of the aircraft
2.6 Graphs
Determination of the loads acting on the aircraft
1 Design mode selection
2 Initial data
2.1 Missile head
2.2 central part rockets
2.3 Rocket bearing surfaces (wings)
2.4 Rocket controls (rudders)
3 Rocket center of pressure coordinate
4 Determination of the drag force of the aircraft
5 Determination of bending moments, shear forces on the body
6 Longitudinal loads
Stability and controllability
4.1 General methodology calculation of stability and balancing
2 Determining the required aerodynamic control force
5. Special part and assembly
1 Analysis of wing layout mechanisms
5.1.1 No. 1 Wing Deployment Mechanism
1.2 Wing layout mechanism No. 2
1.3 Wing layout mechanism No. 3
1.4 Wing layout mechanism No. 4
1.5 Wing layout mechanism No. 5
5.2 All-moving wing with VPPOKr (screw drive for turning and lowering the wing)
2.1 Calculation of the geometrical parameters of the VPPOKr
2.2 Calculation of loads on the wing and VPPOKr when laying out the wing
2.3 Dynamic calculation of wing loads
2.4 Calculation of WFPCR elements
2.4.1 Shearing and bending of screw transducer fingers
2.4.2 Sidewall torsion of screw cylinders
Technological part
1 Justification of the aircraft division scheme
1.1 Technological characteristics of joints
1.2 Choice of method of interchangeability by joints
1.3 Technological characteristics and choice of materials for the manufacture of aircraft
2 Technological process welding
3 Requirements for the overall assembly of the product
4 Assembly guidelines
5 Assembly steps
Occupational Safety and Health
7.1 General requirements for labor protection
2 Requirements for labor protection in the design of aircraft
7.2.1 Permissible noise level
2.2 Requirements for the parameters of the microclimate of the room
2.3 Ergonomic requirements
3 Calculation of the number of lamps in the room
Economic part
1 Calculation method
1.1 OCD costs
1.2 Research costs
1.3 Rocket selling price
1.4 Engine selling price
1.5 Fuel costs
1.6 Operating costs
1.7 Calculation of the number of aircraft required to hit the target
8.2 Initial data
3 Calculation results
9. List of used literature
Introduction
The process of creating modern CR is the most difficult scientific and technical task, which is solved jointly by a number of research, design and production teams. We can single out the following main stages in the formation of the CD: tactical and technical specifications, technical proposals, preliminary design, detailed design, experimental testing, bench and natural tests.
Work on the creation of modern samples of CR is carried out in the following areas:
· increasing the range and speed of flight to supersonic;
· the use of combined multi-channel detection and homing systems for missile guidance;
· reducing the visibility of missiles through the use of stealth technology;
· increasing the stealth of missiles by reducing the flight altitude to the limit and complicating the flight path in its final section;
· equipping the on-board equipment of missiles with a satellite navigation system that determines the location of the missile with an accuracy of 10 ... ..20 m;
· integration of missiles for various purposes into a single missile system maritime, air and ground-based.
The implementation of these areas is achieved mainly through the use of modern high technology.
technological breakthrough in aircraft building and rocket science, microelectronics and computer technology, in the development of on-board automatic control systems and artificial intelligence, propulsion systems and fuels, means electronic protection etc. created real developments of a new generation of CR and their complexes. It became possible to significantly increase the flight range of both subsonic and supersonic CR, increase the selectivity and noise immunity of on-board automatic control systems with a simultaneous decrease (more than twice) in weight and size characteristics.
Cruise missiles are divided into two groups:
· ground-based;
· sea-based.
This group includes strategic and operational-tactical missiles with a flight range from several hundred to several thousand kilometers, which, unlike ballistic missiles fly to the target in dense layers of the atmosphere and for this they have aerodynamic surfaces that create lift. Such missiles are designed to destroy important strategic targets (large administrative and industrial centers, airfields and BR launch sites, naval bases and ports, ships, large railway junctions and stations, etc.).
Cruise missiles capable of being launched from submarines, surface ships, ground complexes, aircraft, provide sea, ground and air force exceptional flexibility.
Their main advantages over BR are:
· almost complete invulnerability in the event of a surprise nuclear missile attack by the enemy due to the mobility of basing, while the locations of launch silos with ballistic missiles are often known to the enemy in advance;
· reduction in comparison with BR of the cost of performing a combat operation to hit a target with a given probability;
· the fundamental possibility of creating an improved guidance system for the KR, functioning autonomously or using a satellite navigation system. This system can provide a 100% probability of hitting the target, i.e. a miss close to zero, which will reduce the required number of missiles and, consequently, operating costs;
· the possibility of creating a weapon system that can solve both strategic and tactical tasks;
· the prospect of creating winged strategic missiles new generation, with even greater range, supersonic and hypersonic speeds, allowing retargeting in flight.
As a rule, nuclear warheads are used on strategic cruise missiles. Conventional warheads are installed on tactical versions of these missiles. For example, penetrating, high-explosive or high-explosive-cumulative type warheads can be installed on anti-ship missiles.
The control system of cruise missiles significantly depends on the flight range, missile trajectory and radar contrast of targets. Long-range missiles usually have combined control systems, for example, autonomous (inertial, astroinertial) plus homing in the final part of the trajectory. Launching from a ground-based installation, a submarine, a ship requires the use of a rocket booster, which is advisable to separate after the fuel burns out, so land-based and sea-based cruise missiles are made two-stage. When launched from a carrier aircraft, an accelerator is not required, since there is a sufficient initial speed. Solid propellant rocket engines are usually used as an accelerator. The choice of a sustainer engine is determined by the requirements of low specific fuel consumption and long flight time (tens of minutes or even several hours). For missiles whose flight speed is relatively low (M<2), целесообразно применять ТРД как наиболее экономичные. Для дозвуковых скоростей () use small thrust turbofan engines (up to 3000 N). At M > 2, the specific fuel consumption of turbojet and ramjet engines become commensurate, and other factors play the main role in choosing an engine: simplicity of design, low weight, and cost. Hydrocarbon fuels are used as fuel for propulsion engines.
1. PRELIMINARY SURVEYS
1 PROTOTYPE ANALYSIS
Country: USA
Type of: tactical missile long range
In the United States, as part of the JASSM (Joint Air to Surface Standoff Missile) program, Lockheed-Martin Corporation continues the full-scale development of the long-range air-to-ground guided missile (UR) AGM-158, which is planned to arm strategic and tactical aircraft of the Air Force and Navy USA. The missile is designed to destroy both stationary and mobile targets (air defense systems, bunkers, large buildings, lightly armored and small heavily protected objects, bridges) in simple and adverse weather conditions, night and day.
The rocket was built according to the normal aerodynamic design: low-wing with folding elevons. Modern composite materials based on carbon fibers are widely used in its design. As power plant the J402 turbojet engine with an improved compressor and fuel system is used. As part of the combined guidance system, along with a thermal imaging seeker (operating at the final guidance site), an inertial control system with correction according to NAVSTAR data and software and hardware for autonomous target recognition are used. Depending on the type of target, a cluster or unitary warhead (warhead) will be used. Currently, a concrete-piercing J-1000 warhead is being installed on the rocket. To equip the cluster warhead, it is possible that BLU-97 GEM (combined action) ammunition will be used.
When launching a rocket over a long range, there is a problem of transmitting information about the current location of the rocket. This information is necessary, in particular, to determine whether the missile hit the target. The existing design includes a BIA (Bomb Impact Assessment) transmitter (power 25 W) that provides data transmission to the RC-135V and W strategic reconnaissance aircraft at a speed of up to 9,600 bps in the frequency range of 391.7-398.3 MHz. The problem will most likely be solved by transmitting data from the rocket to the repeater aircraft via satellite. During the ongoing flight tests of prototype rockets, the engine and guidance system are tested for performance. Based on the results obtained, the power supply system, the wing opening mechanism and software. To reduce aerodynamic drag and improve maneuverability, it is also planned to change the shape of the control surfaces and the location of the air pressure receiver.
The strategic bombers V-52N (12 missiles), V-1V (24), V-2 (16), F-15E (three), as well as tactical fighters F-16 C and D (two ), F/A-18 (two), F-117 (two). In accordance with current plans, it is planned to purchase 4,000 missiles for the Air Force and 700 for the US Navy at a cost of a serial sample of about $400,000. The entry of the new missile into service is expected in 2002-2003.
Weight, kg 1050
Warhead weight, kg 450
Wing, m 2.70
Length, m 4.26
Height, m 0.45
Width, m 0.55
Range, km 350
Accuracy (KVO), m 3
TTRD engine
Thrust, kN 4.2
Carrier aircraft V-52N, V-1V, V-2, F-15E, F-16 C and D, F/A-18, F-117
strategic cruise missile
<#"justify">ОписаниеРазработчикМКБ «Радуга»ОбозначениеХ-101Обозначение NATOAS-?Год1999Тип ГСНоптоэлектронной система коррекции + ТВГеометрические и массовые характеристикиДлина, мЭПР, м20,01Стартовый вес, кг2200-2400Тип боеголовкиобычнаяМасса БЧ, кг400Силовая установкаДвигательДТРДЛетные данныеСкорость, м/сКрейсерская190-200максимальная250-270КВО, м12-20Дальность пуска, km5000-5500ACM
Country: USA
Type: High precision strategic cruise missile
Full-scale work on the ACM (Advanced Cruise Missile) program began in 1983. The goal of the program was to create a strategic precision system aviation weapons, which allows you to destroy enemy targets without the carrier aircraft entering the enemy air defense zone. The first missile was delivered in 1987. Production contracts for the ACM were awarded to General Dynamics and McDonnel-Douglas.
The design of the rocket, designated AGM-129A, makes extensive use of steath technology. The missile has a shape that is less visible to most radars and a special coating. The use of a reverse-swept wing also reduces the radar visibility of the missile. The missile is equipped with a WA80 nuclear warhead weighing 200 kg. Maximum range shooting 3000 km. Circumferential probable deviation less than 30 m. Inertial guidance system, in combination with terrain correlation. The INS uses laser gyroscopes.
In 1993-1994 the AGM-129A missile entered service with the American strategic bombers B-52H (12 KR), B-1B and B-2. Instead of the previously planned 1460 missiles, production was limited to 460.
Developer Length, m Fuselage diameter, m Wingspan, m Warhead Starting weight, kg Warhead weight, kg Number of engines Engine Engine thrust, kgf (kN) Max. speed at height, M Maximum range, km KVO, mGeneral Dynamics 6.35 0.74= 3.12 W-80-1 (nuclear) 1250 200 1 Williams International F112 332 DTRD<1 более 2400 менее 30C/D CALCM
Country: USA
Type: cruise missile
The AGM-86 ALCM (Air-Launched Cruise Missile) cruise missile is the main long-range weapon of the B-52H bombers. With the replacement of nuclear warheads with conventional warheads, the AGM-86 remains a very important weapon for the foreseeable future.
The beginning of the creation of ALCM was laid in January 1968, when the US Air Force drew up requirements for a decoy SCAD (Subsonic Cruise Aircraft Decoy). The carriers of the SCAD were to be the B-52 and B-1A bombers. This LC was supposed to imitate bombers on the radar screens to ensure a breakthrough of enemy air defense. In essence, SCAD was a modification of the ADM-20 Quail LC. During the early concept stage, it became clear that the SCAD could be equipped with a small nuclear warhead, and the name of the LC was changed to Subsonic Cruise Armed Decoy. Full-scale work began in June 1970 and the LC was given the designation AGM-86A. In the early 70s, the expected cost of SCAD electronic systems reached too high values. In June 1973, development was interrupted after it became clear that it was economically more profitable to create a cruise missile without electronic warfare equipment.
Immediately after the cancellation of the SCAD program, the US Air Force began a new long-range cruise missile program with a nuclear warhead, using the developments in SCAD. In September 1974, Boeing received a contract to develop a new rocket, which was left with the designation AGM-86A, because. in fact, the new ALCM was the same SCAD, but with a warhead. The length of the AGM-86A is 4.3 m, which made it possible to use it from the same launchers as the AGM-69 SRAM. The first test launch of the rocket took place on March 5, 1976 at the White Sands missile range in New Mexico. On September 9 of the same year, the first controlled launch was successfully made, the rocket flight lasted 30 minutes. ALCM was equipped with an inertial navigation system that works in conjunction with the TERCOM (Terrain Contour Matching) terrain contour following correlation system.
During the creation of the AGM-86A, the Air Force issued requirements for an extended range missile (up to 2400 km). There were two paths that developers could take to achieve such a range. One of them was the use of external fuel tanks, and the other was an increase in the size of the rocket (this option was designated ERV - extended range vehicle). The ERV variant had one drawback - the existing AGM-69 missile launchers could not be used, and the long missile would not fit in the B-1A bomber's bomb bay. The Air Force decided to first take the AGM-86A into service, and then deal with either the installation of additional external tanks or the ERV variant. In January 1977, full-scale serial production of the AGM-86A was supposed to begin, but this was not destined to happen, because. in 1977 there was a decisive change in the direction of the ALCM program. On June 30, 1977, President Carter announced the cessation of the production of B-1A bombers in favor of the development of the ALCM program.
As part of the JCMP program (Joint Cruise Missile Project - a single cruise missile project), the Air Force and the Navy directed their efforts to create cruise missiles to use a single technological base. At the same time, the Navy just announced the BGM-109 Tomahawk missile as the winner of the SLCM competition. One of the consequences of the JCMP program was the use of the same Williams F107 engines and the TERCOM guidance system. Another consequence was the abandonment of the short-range AGM-86A along with a directive to select the long-range ALCM variant based on the results of the competition between the ERV ALCM missiles (now AGM-86B) and the AGM-109 Tomahawk aviation variant. The first launch of the AGM-86B was made in 1979, and in March 1980 the AGM-86B was declared the winner. After some time, mass production was launched, and in August 1981 ALCM missiles were adopted by the B-52G / H bombers.
The AGM-86B missile is powered by one F107-WR-100 or -101 turbojet engine and a W-80-1 variable power thermonuclear warhead. The wings and rudders fold into the fuselage and are released two seconds after launch.
The inertial navigation system of the Litton P-1000 rocket receives updated information from the on-board INS B-52 until the launch itself, and during the flight it is used in the initial and cruising sections of the flight. INS P-1000 consists of a computer, an inertial platform and a barometric altimeter, the weight is 11 kg. The inertial platform consists of three gyroscopes for measuring the angular deviations of the rocket and three accelerometers for determining the acceleration of these deviations. The R-1000 has a drift of up to 0.8 km. in an hour.
When flying at low altitude on the cruising and final sections of the flight, the AGM-86B uses the AN / DPW-23 TERCOM correlation subsystem, and consists of a computer, a radio altimeter and a set of reference maps of areas along the flight route. The beam width of the radio altimeter is 13-15 °. Frequency range 4-8 GHz. The principle of operation of the TERCOM subsystem is based on a comparison of the terrain of a particular area where the missile is located with reference maps of the terrain along the route of its flight. The determination of the terrain is carried out by comparing the data of radio and barometric altimeters. The first measures the height to the surface of the earth, and the second - relative to sea level. Information about a certain terrain in digital form is entered into the on-board computer, where it is compared with data on the relief of the actual terrain and reference maps of areas. The computer generates correction signals for the inertial control subsystem. The stability of TERCOM operation and the required accuracy in determining the location of a cruise missile are achieved by choosing the optimal number and size of cells, the smaller their size, the more accurately the terrain is tracked, and hence the location of the missile. However, due to the limited memory of the on-board computer and the short time for solving the navigation problem, a normal size of 120x120 m was adopted. The entire flight path of a cruise missile over land is divided into 64 correction areas with a length of 7-8 km and a width of 48-2 km. The accepted quantitative characteristics of the cells and areas of correction, according to the statements of American experts, ensure the launch of a cruise missile to the target even when flying over flat terrain. The permissible error in measuring the height of the terrain for reliable operation of the TERCOM subsystem should be 1 meter.
Based on various sources, the guidance system provides a CEP of 30-90 m. B-52N bombers are equipped with CSRL (Common Strategic Rotary Launcher) rotary launchers and allow you to place up to 20 AGM-86B missiles on board - in the bomb bay 8 missiles on CSRL, and 12 missiles on two pylons under the wings.
In total, before the completion of production in 1986, more than 1715 AGM-86B missiles were produced at the Boeing factories.
In 1986, Boeing began converting some AGM-86B missiles to the AGM-86C standard. The main change is the replacement of a thermonuclear warhead with a 900-kg high-explosive fragmentation warhead. This program has received the designation CALCM (Conventional ALCM). The AGM-86C missiles were equipped with a GPS satellite navigation system receiver and an electronic-optical correlation system DSMAC (Digital Scene Matching Area Correlator), which significantly increased the accuracy of the missile (KVO decreased to 10 m). DSMAC uses digital "pictures" of pre-captured areas of terrain along a flight route. The system starts to work on the final leg of the flight after the last TERCOM correction. With the help of optical sensors, the areas adjacent to the target are inspected. The resulting images are digitally entered into a computer. He compares them with the reference digital "pictures" of the regions stored in his memory and issues corrective commands. When approaching the target, the active radar seeker is activated. It consists of antennas with a scanning device, a transceiver and a signal processing unit, as well as a transponder of the "friend or foe" system. To ensure noise immunity, RSL operation is provided at variable frequencies that change according to a random law.
Due to the fact that CALCM is heavier than ALCM, the flight range has been significantly reduced. During Operation Desert Storm and the war in Yugoslavia, AGM-86C missiles were successfully used.
The original AGM-86C configuration is designated CALCM Block 0. The new Block I version is equipped with improved electronics and a GPS receiver, a heavier 1450-kg HE warhead. The missile was successfully tested in 1996, after which all existing Block 0 missiles were upgraded to Block I. The next option was Block IA, focused on improving accuracy in the final leg of the flight. According to the calculations, the CVO should be 3 m. Block IA work began in 1998, and in January 1991 the first CALCM Block IA was delivered to the Air Force. Currently, about 300 ALCM missiles have been modified to the Block I / 1A variant.
For the training and training of the technical staff, a training version of the DATM-86C was created, equipped with a training warhead and a power plant.
In November 2001, flight tests of the AGM-86D Block II cruise missile were carried out, equipped with a new 540-kg AUP (Advanced Unitary Penetrator) penetrating warhead, designed to destroy heavily fortified or deep underground targets. It is expected to produce about 200 AGM-86D missiles.
Length, m 6.32
Diameter, m 0.62
Wing, m 3.66
AGM-86B 1450C Block I 1950
Speed, km/h 800
Warhead thermonuclear W-80-1, 5-150kT
AGM-86C Block I 1450 kg, OF
AGM-86D 540 kg penetrating
Engine DTRD F107-WR-101
Engine thrust, kN 2.7
Range, kmB 2400C Block I 1200
Anti-ship missile "Tomahawk" BGM-109 B/E
Cruise missile "Tomahawk" was created in two main variants: strategic BGM-109А/С/D - for firing at ground targets, and tactical BGM-109B/E - for destroying surface ships and vessels. All options, due to the modular principle of construction, differ from each other only in the head part, which, with the help of a docking station, is attached to the middle compartment of the rocket.
The Tomahawk BGM-109 B/E anti-ship missile, which has been in service with the US Navy since 1983, is designed to fire at large surface targets at over-the-horizon ranges.
It has a modular design, made according to the aircraft scheme. The cylindrical fuselage with a lively warhead consists of six compartments, which contain an active radar seeker with a fiberglass fairing, an onboard control system, a warhead, a fuel tank, a sustainer engine and rudder drives. The launch solid propellant rocket is docked to the last compartment coaxially with the rocket. All compartments are made of aluminum alloy and equipped with stiffeners. To reduce infrared radiation, the body and aerodynamic surfaces have a special coating.
An active radar homing head, an inertial navigation system, a radio altimeter and a power supply are installed on board the missile. GOS weighing about 34 kg, capable of changing the frequency of radiation according to an arbitrary law to increase noise immunity in conditions of electronic countermeasures. The 11 kg inertial system includes an onboard digital computer (OBCM), an autopilot (AP) consisting of three gyroscopes for measuring the angular deviations of the rocket in the coordinate system and three accelerometers for determining the accelerations of these deviations. An active short-pulse radio altimeter (4-8 GHz range) with a beam width of 13-15° has a vertical resolution of 5-10 cm, and a horizontal resolution of 15 cm.
The high-explosive warhead is equipped with a contact deceleration fuse and allows, in order to achieve the greatest damaging effect, to detonate warheads inside the ship.
Especially for the Tomahawk rocket, a small-sized Williams International F107-WR-402 bypass turbojet engine with a low compression ratio and a two-stage axial fan was developed. Its high performance characteristics make it possible to maintain a transonic cruising speed (0.7M) for a long time.
The starting solid propellant rocket engine develops thrust up to 3700 kgf and 10-13 s after launch from under water or from a ship's launcher (PU) ensures that the rocket enters the controlled flight section. Separation of the booster from the rocket occurs with the help of explosive bolts after the fuel has completely burned out.
The launch of the Tomahawk anti-ship missiles is carried out from deck launchers, standard torpedo tubes (TA) or from vertically located missile containers. The concept of vertical launch of anti-ship missiles from surface ships is the main one in the development of the technology for launching these weapons, therefore the main standard launchers are universal installations of the Mk41 type, capable of launching Tomahawk and Standard guided missiles and Asroc-VLA anti-submarine missiles.
One of the options for converting surface ships into missile carriers is to equip them with unified Mk143 quad launchers. These launchers are designed to store and launch Tomahawk and Harpoon missiles. At the same time, four Tomahawk or Harpoon missiles or two missiles of each type can be placed in one launcher. Before their launch, the launcher is installed at an angle of 35 ° with respect to the deck using a hydraulic system. The armored casing protects the missiles from fragments and mechanical damage, as well as personnel in case of accidental (emergency) operation of the launch booster.
On submarines, the rocket is in a steel capsule filled with nitrogen. The gaseous medium under slight overpressure ensures the storage of the rocket for 30 months. The capsule is loaded into the TA like a regular torpedo. In preparation for launch, water fills the TA, and through special holes also the capsule. This leads to equalization of the internal and external pressure corresponding to the launch depth of 15-20m. After that, the cover of the TA opens, and the rocket is fired from the capsule with the help of a hydraulic system, which is then removed from the device. When the missile reaches a distance that is safe for the firing submarine with the help of a 12-meter halyard, the accelerator is launched, which ensures the passage of the underwater section of the trajectory in about 5 s. Turning on the starting solid propellant rocket engine under water greatly unmasks the submarine, especially in the acoustic field. Preparation for launch from TA takes about 20 minutes. The design of a capsule made of fiberglass reinforced with graphite fiber has been created, as a result of which its weight has decreased by 180-230 kg.
One of the difficulties in the combat use of anti-ship missiles is the lack of proper technical means for detecting an enemy surface ship and target designation, since firing is carried out at a large (beyond-the-horizon) range. To solve this problem, the United States has developed an automated system "Outlaw Shark" for over-the-horizon target designation of anti-ship missiles using patrol helicopters and carrier-based aircraft. At the same time, data on a target located beyond the horizon are received from various means in real time in the computer of the ship-carrier of the CD. Having processed them, the computer issues target designation, as well as information about other ships located near the missile's flight path, to the counting and decisive device of the missile.
Firing range, km 550
Maximum flight speed, km/h 1200
Average flight speed, km/h 885
Rocket length, m 6.25
Rocket body diameter, m 0.53
Wingspan, m 2.62
Starting weight, kg 1205
Warhead
Type high explosive
Weight, kg 454
sustainer engine
Dry engine weight, kg 58.5
Fuel weight, kg 135
Thrust, kg 300
Engine specific gravity, kg/kgf 0.22
Length, mm 800
Diameter, mm 305
Kh-59MK Ovod-MK
Country Russia
Type: Tactical missile system
One of the sensations of MAKS-2001 was the new controlled X-59MK, developed by the Federal State Unitary Enterprise MKB "Rainbow" (Dubna, Moscow region). It was designed on the basis of the well-known X-59M missile, which is the main front-line aviation weapon for hitting especially important ground targets. Unlike the progenitor, equipped with a television-command guidance system, the Kh-59MK carries an active radar homing head. Replacing the launch booster with a fuel tank made it possible to increase the flight range from 115 to 285 km. The disadvantages of the rocket include subsonic flight speed, the advantages - the sophistication of the basic version, a powerful - 320 kg - warhead (warhead) and a lower cost than that of supersonic systems.
According to Raduga specialists, the probability of hitting a cruiser or destroyer is 0.9-0.96, and 0.7-0.93 hitting a boat. At the same time, one missile is enough to destroy a boat, and the estimated average number of hits to destroy a cruiser or destroyer is 1.8 and 1.3, respectively.
The X-59MK has passed ground tests and will be put into production if foreign customers show interest in it. The latter is highly probable, since the initial system, the Kh-59M, is used to arm Su-27 family fighters supplied to China and India. The Kh-59MK has a relatively small mass - 930 kg, which allows up to 5 such missiles to be suspended on the Su-27 fighter.
Developer of MKB "Rainbow"
Manufacturer Smolensk Aviation Plant
Max. launch range, km 285
Active radar guidance system
Rocket weight, kg 930
Warhead weight, kg 320
Warhead type penetrating
Strategic cruise missile Kh-55 (RKV-500)
The Kh-55 is a subsonic small-sized strategic cruise missile that flies around the terrain at low altitude and is designed to be used against important strategic enemy targets with previously reconnoitered coordinates.
The missile was developed at NPO Raduga under the leadership of General Designer I.S. Seleznev in accordance with the Decree of the Council of Ministers of the USSR of December 8, 1976. The design of the new rocket was accompanied by the solution of a host of problems. A long flight range and stealth required high aerodynamic quality with a minimum weight and a large fuel supply with an economical power plant. With the required number of missiles, their placement on the carrier dictated extremely compact forms and made it necessary to fold almost all protruding units - from the wing and plumage to the engine and fuselage ending. As a result, an original aircraft with a folding wing and empennage, as well as with a bypass turbojet engine, located inside the fuselage and pulled down before the missile was uncoupled from the aircraft, was created.
In 1983, for the creation and development of the X-55 production, a large group of employees of the Raduga Design Bureau and the Dubna Machine-Building Plant were awarded the Lenin and State Prizes.
In March 1978 the deployment of the X-55 production at the Kharkov Aviation Industrial Association (HAPO) began. The first serial rocket manufactured at HAPO was handed over to the customer on December 14, 1980. In 1986, production was transferred to the Kirov Machine-Building Plant. The production of X-55 units was also deployed at the Smolensk aircraft plant. Developing a successful design, the Raduga ICD subsequently developed a number of modifications to the basic Kh-55 (product 120), among which the Kh-55SM with an increased range (adopted in 1987) and the Kh-555 with a non-nuclear warhead and an improved guidance system can be noted .
The carriers of the KR X-55 are strategic aircraft - Tu-95MS and Tu-160.
In the west, the Kh-55 missile received the designation AS-15 "Kent".
X-55 is made according to the normal aerodynamic configuration with a straight wing of relatively high elongation. (see projections from the side, top, bottom) The plumage is all-moving. In the transport position, the wing and engine nacelle are retracted into the fuselage, and the plumage is folded (see layout diagram).
The R-95-300 bypass turbojet engine, developed under the guidance of chief designer O.N. Favorsky, is located on a retractable ventral pylon. R95-300 develops static takeoff thrust of 300..350 kgf, having a transverse dimension of 315mm and a length of 850mm. With its own weight of 95 kg, the weight return of the R-95-300 is 3.68 kgf / kg - at the level of the turbojet engines of modern combat aircraft. The R-95-300 was created taking into account a fairly wide flight range characteristic of cruise missiles, with the ability to maneuver in altitude and speed. The engine is started by a pyrostarter located in the tail spinner of the rotor. In flight, when the engine nacelle is extended, to reduce resistance, the tail spinner of the fuselage is extended (the spinner is extended by means of a spring held in a taut state by a nichrome wire, which is burned out by an electric impulse). To carry out the flight program and control the R-95-300 is equipped with a modern automatic electronic-hydromechanical control system. In addition to the usual grades of fuel (aviation kerosene T-1, TS-1 and others), a special synthetic combat fuel T-10, decilin, was developed for the R-95-300. T-10 is a high-calorie and toxic compound; it was with this fuel that the maximum characteristics of the rocket were achieved. A feature of the T-10 is its high fluidity, which requires particularly careful sealing and sealing of the entire rocket fuel system.
The need to accommodate a significant supply of fuel with limited dimensions led to the organization of the entire X-55 fuselage in the form of a tank, inside which the wing, warhead, armature and a number of other units are placed in sealed openings. The wing planes are folded into the fuselage, placed one above the other. When released, the planes are at different heights relative to the building horizontal of the product, fixing with different installation angles, which is why the X-55 becomes asymmetric in flight configuration. The tail unit is also foldable, all surfaces of which are rudders, and the consoles are hingedly broken twice. The rocket fuselage is made entirely welded from AMG-6 alloy.
The design of the rocket implemented measures to reduce radar and thermal visibility. Due to the small midsection and the cleanliness of the contours, the missile has a minimum RCS, which makes it difficult to detect it by air defense systems. The hull surface does not have contrasting cracks and sharp edges, the engine is covered by the fuselage, structural and radio-absorbing materials are widely used. The skin of the nose of the fuselage, wing and plumage is made of special radio-absorbing materials based on an organosilicon composite.
The missile guidance system is one of the significant differences between this cruise missile and previous aircraft weapon systems. The missile uses an inertial guidance system with location correction based on the terrain. A digital map of the area is entered into the onboard computer before launch. The control system ensures a long autonomous flight of the X-55 rocket, regardless of the length, weather conditions, etc. The conventional autopilot on the X-55 was replaced by the BSU-55 electronic on-board control system, which worked out a given flight program with the missile stabilizing along three axes, maintaining the speed and altitude conditions and the ability to perform specified maneuvers to evade interception. The main mode was the passage of the route at extremely low altitudes (50-100m) with terrain bending, at a speed of the order of M=0.5-0.7, corresponding to the most economical mode.
The Kh-55 is equipped with a newly developed compact thermonuclear warhead with a 200kt charge. With a given accuracy (CVO not more than 100m), the power of the charge ensured the defeat of the main targets - strategic centers of state and military administration, military-industrial facilities, nuclear weapons bases, missile launchers, including protected objects and shelters.
The carriers of the missile are the Tu-95MS and Tu-160 long-range bombers. Each Tu-95MS-6 bomber can carry up to six missiles located on an ejection-type MKU-6-5 drum launcher in the aircraft cargo compartment (see photo). The Tu-95MS-16 variant carries sixteen Kh-55s: six on the MKU-6-5, two each on the AKU-2 internal underwing ejection launchers near the fuselage, and three each on the external AKU-3 launchers located between the engines. Two cargo compartments of the supersonic Tu-160 can accommodate 12 Kh-55SM long-range cruise missiles (with additional tanks) or 24 conventional Kh-55 cruise missiles.
Rocket modifications:
X-55OK (product 121) is distinguished by a guidance system with an optical correlator based on a reference image of the terrain.
Modification Kh-55SM (product 125) is designed to hit targets at a distance of up to 3500 km. The guidance system remained the same, but a significant increase in range required an almost 1.5-fold increase in fuel supply. In order not to change the proven design, conformal tanks for 260 kg of fuel were equipped on the sides of the fuselage from below, which practically did not affect the aerodynamics and balancing of the rocket. This design made it possible to preserve the dimensions and the possibility of placing six missiles on the MKU inside the fuselage. However, the mass increased to 1465kg forced to limit the number of missiles on the TU-95MS underwing hangers (eight Kh-55SM can be suspended instead of ten Kh-55).
The non-nuclear variant of the Kh-55 was designated the Kh-555. The new missile is equipped with an inertial-doppler guidance system that combines terrain correction with an optical-electronic correlator and satellite navigation. As a result, the QUO was about 20m. It is envisaged that the Kh-555 can be equipped with several types of warheads: high-explosive, penetrating - for hitting protected targets, or cluster with fragmentation, high-explosive or cumulative elements for hitting areal and extended targets. In connection with the increase in the mass of warheads, the fuel supply was reduced and, accordingly, the flight range was reduced to 2000 km. Ultimately, a more massive warhead and new control equipment led to an increase in the launch weight of the Kh-555 to 1280 kg. X-555 is equipped with conformal external tanks for 220 kg of fuel.
Kh-65 - tactical anti-ship modification of the Kh-55 with a conventional warhead.
Tactical and technical characteristics
Kh-55SM 6.040
X-55 5.880
Hull diameter, m
Kh-55SM 0.77
X-55 0.514
Wingspan, m 3.10
Starting weight, kg
Kh-55SM 1465
Kh-55 1185
X-555 1280
Warhead power, kt 200
Warhead weight, kg 410
Flight range, km
Kh-55SM 3500
X-55 2500
Flight speed, m/s 260
Flight altitude on the cruising section of the trajectory, m 40-110
Launch height, m 20-12000
Carrier aircraft speed range, km/h 540-1050
Tests, operation
The first flight of an experimental carrier aircraft Tu-95M-55 (VM-021) took place on July 31, 1978. Total on this machine by the beginning of 1982. 107 flights were performed and ten Kh-55s were launched. The plane was lost in a crash on January 28, 1982. on takeoff from Zhukovsky due to pilot error.
Tests of the X-55 went very intensively, which was facilitated by a thorough preliminary development of the control system on the NIIAS simulation stands. During the first stage of testing, 12 launches were carried out, only one of which ended in failure due to the failure of the power system generator. In addition to the rocket itself, a weapon control system was brought in, which from the carrier carried out the input of the flight mission and the exhibition of the rocket's gyro-inertial platforms.
The first launch of the serial X-55 was made on February 23, 1981. September 3, 1981 the first test launch was made from the first serial Tu-95MS. The tests of the complex were carried out at the route-measuring complex of the 929th LITs test site. Test launches of the X-55 were carried out in almost the entire range of carrier flight modes from altitudes from 200m to 10km. The engine start was carried out reliably, the speed on the route, regulated depending on the weight reduction during fuel consumption, was maintained in the range of 720-830 km / h. With a given CVO value of not more than 100m, in a number of launches, a deviation of only 20-30m was achieved.
The first to develop the new complex began in the Semipalatinsk 1223rd TBAP, where on December 17, 1982. two new Tu-95MS arrived. Since 1984 retraining on the Tu-95MS was started by the neighboring 1226th TBAP of the same Semipalatinsk 79th TBAD. At the same time, the Tu-95MS of the DA regiments in the European part of the USSR was being equipped - 1006 TBAP in Uzin near Kyiv and the 182nd Guards. TBAP in Mozdok, which was part of the 106th TBAD. More advanced Tu-95MS-16s were concentrated in the division. The first Tu-160s arrived in April 1987. in the 184th Guards TBAP, located in Priluki in Ukraine. Three months later, August 1, 1987. the crew of the regiment commander V. Grebennikov was the first to launch the Kh-55.
After the collapse of the USSR, most of the X-55 missiles and their carrier aircraft remained outside of Russia, in particular, in Kazakhstan and Ukraine, where there were, respectively, 40 Tu-95MS in Semipalatinsk, 25 in Uzin and 21 Tu-160 in Priluki . Together with the aircraft, 1,068 Kh-55 missiles remained at Ukrainian bases. It was possible to reach an agreement with Kazakhstan quite quickly, exchanging heavy bombers for fighters and attack aircraft proposed by the Russian side. By February 19, 1994 all TU-95MS were transferred to the Far Eastern airfields, where they were equipped with the 182nd and 79th TBAPs. Negotiations with Ukraine dragged on for a long time. Ultimately, the Ukrainian side transferred three Tu-95MS and eight Tu-160s, which flew to Engels in February 2000, on account of debts for gas. At the end of 1999, 575 Kh-55 and Kh-55SM air-launched cruise missiles were also delivered from Ukraine to Russia.
In the Russian Air Force, all DA forces are combined into the 37th VA. In its composition by July 2001. there were 63 Tu-95MS aircraft with 504 Kh-55 missiles listed behind them, as well as 15 Tu-160s. The first practical launch of the Kh-55SM from the Tu-160 was carried out by the crew of Colonel A.D. Zhikharev on October 22, 1992. In June 1994 four Tu-95MS and Tu-160 took part in the exercises of the strategic nuclear forces of Russia, having worked out tactical launches over the North Sea and then performing real firing of the Kh-55SM at the training ground. In September 1998 a group of four Tu-95MS of the 184th TBAP launched the X-55 in the area of the Northern Fleet Chizh range, from where the missiles traveled 1500 km to the target.
During the Zapad-99 exercises in June 1999, a pair of Tu-95MS from Engels completed a 15-hour flight, reaching Iceland, and on the way back launched the Kh-55 at a training target in the Caspian region. In October 2002, the crew Tu-160 Colonel Y. Deineko in a night flight passed the route over the polar regions, having performed a practical launch of the X-55SM.On May 14, 2003, four Tu-95MS and six Tu-160s participated in exercises covering the Persian Gulf and the Indian Ocean. -55 from the Tu-95MS were also carried out during the strategic command training of ground, sea and air strategic nuclear forces in February 2004.
Country Russia
Type: Tactical cruise missile
In the mid-1980s in the ICD LRaduga? on the basis of the X-55 ALCM, a cruise missile was created, equipped with a conventional warhead (high-explosive or cluster). She received the designation X-65.
Its flight performance was first presented at the Moscow Air Show in 1992. The X-65 itself was shown for the first time in 1993 (in February - Abu Dhabi, and in September - in Zhukovsky and Nizhny Novgorod).
The X-65 missile can be used both from the Tu-95 and Tu-160 strategic bombers, and from fighter-bombers, respectively, from rotary launchers of the MKU-6-5 type or ordinary beam launchers. The Kh-65 can be launched from a height of up to 12 km at a carrier aircraft speed of 540-1050 km/h. The X-65 control system is inertial with terrain correction. The X-65 missile has been tested since the late 1980s, but there is no data on its adoption into service.
To destroy surface ships with an effective dispersion surface of 300 m2 in conditions of strong electronic countermeasures, the Kh-65SE anti-ship missile was created on the basis of the Kh-55. In terms of its characteristics, it differs from the Kh-65 only in its firing range (250 km when launched at low altitudes and 280 km at high altitudes) and the control system. The warhead of the rocket is a cumulative high-explosive weighing 410 kg.
A carrier aircraft (Tu-22M3 or other) can launch a Kh-65SE missile from a height of 0.1 to 12 km at a speed of 540-1050 km/h against a sea target whose coordinates are known only tentatively. The launch of a rocket is carried out according to the principle of fire and forget. The rocket flies to a given area at low altitude, controlled by an inertial guidance system. At the intended location of the target, the missile increases its flight altitude and begins loitering, turning on the onboard active radar homing head until it locks on to the target.
The Kh-65SE missile was exhibited at the MAKS-97 exhibition. There is no data on its acceptance into service.
Characteristics:
Developer MKB Raduga
Kh-65 mid 80s
X-65CE 1992
Type GSN 115
Kh-65 inertial + terrain correction
X-65SE inertial + active radar
Length, m 6.04
Wingspan, m 3.1
Hull diameter, m 0.514
Starting weight, kg 1250
Warhead type
Kh-65 explosive or cassette
X-65SE high-explosive-cumulative
Warhead mass, kg 410
DTRD engine
Speed, km/h (m/s; M) 840 (260; 0.77)
Launch speed, km/h540 - 1050
Launch height, m 100-12000
Launch range, km-
Kh-65 500-600
X-65CE 250-280
Flight altitude on the cruising section of the trajectory, m40-110
Having considered and analyzed all the missiles presented above, we choose the anti-ship missile "Tomahawk" BGM-109 B / E as a prototype.
1.2 MODERN REQUIREMENTS FOR CRUISE MISSILE DESIGN
The high efficiency of modern air defense systems changes the requirements for CR. Rather, in order to be an effective weapon, the KR should only have good aerodynamic characteristics, a minimum starting weight, and a small specific fuel consumption. However, defense systems pose a number of new requirements. At present, a small effective scattering surface is as important as a high flight performance.
The design of complex new technology, which is CR, is a multi-valued and very indefinite process: this is the path of transition from the achieved knowledge, from which design begins to the creation of an object that does not yet exist on the basis of a design assignment and new technical solutions. It is safe to say that such a process cannot be hard-coded and cannot be described in a very specific way. However, a methodological description of the design is possible, i.e. presentation of the concept, basic principles and features of the process.
When forming general approaches to design, the natural desire of the designer is the desire to fully take into account all the factors that determine the appearance of future technology. This requirement of completeness can be satisfied only within the framework of a hierarchical structure of principles, the upper level of which contains a small number of the most general fundamental principles related to the most diverse types of technical systems. In my opinion, there are three such principles.
The first principle reflects the main source of the new quality of technology, the means and the main direction of achieving the goal. The traditional approach is relatively weakly associated with the introduction of innovations. He tends to design by prototype, i.e. “from what has been achieved” by updating technology on the basis of a consistent slight improvement in design, but according to modern views, a radical increase in the quality of technical systems can be obtained only through the implementation of the results of scientific and technological progress, i.e. when using new ideas and high-performance technologies that implement the criterion of "maximum result at minimum cost".
The history of the development of technology shows that the first sample of a fundamentally new device is usually created under conditions of incomplete knowledge of its properties. Therefore, the parameters of such an object, as a rule, are not optimal and there are significant reserves for improvement. With the start of operation of the facility, the process of eliminating its shortcomings and improving quality indicators begins. Improvement is carried out by optimizing the design parameters, changing the design and technological solutions of individual parts of the object. The growth of the general scientific and technical potential of the industry and the development of production technology contribute to the improvement of quality indicators. The improvement of the object continues until the globally optimal values of the parameters for the given structure of the object are obtained, when further improvement of the quality indicators becomes impossible.
The history of the development of technology shows that a technical object dies off during the period of its highest development, i.e. when its quality indicators are realized to the maximum extent. Thus, the use of jet engines in aviation began when they were still inferior to piston engines. With an increase in flight speed of more than 700-800 km / h, the piston engine has exhausted itself, but by this time jet engines have already been sufficiently worked out, allowing the development of aviation to continue in the direction of increasing flight speed.
So the main source of the new quality of technology is the scientific and technical potential of society. When creating new technical objects, it is necessary to determine at what level of constructive evolution the prototype is and what are the prospects for its development, what changes in science and technology have occurred since the creation of the first samples of the class of products under consideration, what achievements of scientific and technical progress have not been reflected in the creation of existing objects, what can be used from the latest achievements of science and technology to develop new operating principles, design and technological solutions to create a new technical device in order to meet continuously growing needs.
The second principle is a systematic approach to the design of new technology. The main feature and positive side of the practical implementation of the systems approach is that the solution of frequent problems is chosen in the interests of more general problems: in accordance with this, its essence is to identify all the main relationships between variable factors and to establish their influence on the behavior of the entire system as a whole. The system approach assumes the properties of the object under study, which are not inherent in its individual elements or their combination without a systemic association.
The structure of the design object determines the properties that, with a sufficiently high reliability, provide a specific area of the object's functioning "functional niche" and can be given to it during the production process. Usually the structure of an object is considered as the main characteristic of its appearance and in some cases even as a synonym for appearance.
Various structures of technical systems differ from each other in the number of components and the components themselves. Obviously, the more uniformity in these components, the more technologically advanced and cheaper the system. The reverse side of the opposite of uniformity is multi-nomenclature. From the point of view of production and operation, multi-production is the most negative quality, which entails negative consequences at all stages of the system's life cycle, from inception to operation and even disposal.
At the same time, multi- nomenclature is a means of giving flexibility to the system: practically only due to multi- nomenclature, the adaptability of the system to changing target tasks is ensured. Both have a positive effect on the functional efficiency of the system. Uniformity and versatility are two opposite trends in the development of the structures of modern technical systems, resolved through compromise. Ultimately, such a compromise consists in reducing the various components (subsystems) to a small number of selected types that form a parametric series (or type order) of components.
Unification is a way to eliminate diversity in standard sizes of equipment, bringing systems, their subsystems and elements to uniformity, which gives them universal properties in terms of purpose, production and operation. The most common form of unification is the introduction of uniformity in design and technical solutions. For parametric products, in addition to structural unification, as a rule, ordering by application is also provided.
According to modern concepts, the unification of technical means is best achieved on the basis of a block-modular construction of technology. The block-modular principle means the transition from the individual design of individual types and modifications of products to the system design of product families. At the same time, previously designed, mastered in production and partially already manufactured (in some cases) unified modular components are widely used.
As a rule, a module is a technologically finished object with a well-defined functional purpose. It can be specialized, i.e. industrial purpose, but can also be suitable for general machine-building applications.
The block-modular design principle provides the ability to quickly create new, modified, and in some cases standard products from used (and therefore reliable) unified component parts-modules with the addition of the necessary new elements.
An important advantage of the block-modular principle of the formation of new technology is the increase in serial production and the simplification of assembly technology. The third principle is design automation. Computer-aided design is a qualitatively new level of design based on modern information technologies and computer technology.
Automation of design in our time is one of the most important principles of design activity.
Computer-aided design is defined by GOST as the process of compiling a description of an object that does not yet exist, in which individual transformations of the descriptions of the object and (or) the algorithm of its functioning or the algorithm of the process, as well as the presentation of descriptions in various languages, are carried out by the interaction of a person and a computer. There are three directions: The first direction is comprehension and informal presentation of the problem.
An objective and comprehensive description of the problem determines the requirements for new technology, the formulation of the problem, the design of the way to implement the project, and, ultimately, the quality of meeting the needs. The scientific and methodological basis of the stage of understanding the problem is systemic thinking using the entire arsenal of the systemic approach, including analysis and synthesis, induction and deduction, abstraction and concretization. In order to make the understanding of the problem better suited for solving practical problems, in many cases, striving to “embrace the immensity” in a structured way, preference should be given to deductive compositional approaches.
The result of the stage of understanding the problem is an ordered (usually hierarchical) structure of factors that determine the functional and cost properties of the newly created system (object). Among the factors, there must be clearly formulated target tasks, interacting parties with their own interests, characteristics of the effect and damage, possible consequences from the use of the system, etc. The information should be sufficient for a critical analysis of the customer's technical specifications and the formation of a list of mathematical models.
The second direction is mathematical modeling of the design problem. Usually, when designing, two types of models are used: evaluation (simplified) and verification (more accurate). Evaluation models focused mainly on linear dependencies are used at the initial design stage in the formation of reference options.
Checking models using numerical methods of implementation make it possible to describe the problem most accurately. The results obtained with the help of verification models have a value comparable to experimental data.
When describing design tasks that require taking into account uncertain and random factors, classical methods turn out to be of little use. Simulation modeling is more suitable. Simulation is a numerical method for conducting experiments on digital computers with mathematical models that describe the behavior of complex systems over long periods of time. A simulation model is a computer analogue of a complex real phenomenon. It allows you to replace an experiment with a real process of experiments with a mathematical model of this process.
The third direction is the user interface. Computer technology, otherwise - the user interface, is a set of methodologies for the analysis, development and maintenance of complex application programs, supported by a set of automation tools. Requirements for CR: - Ensuring the minimum mass of the structure. The most effective design that comprehensively meets the requirements of strength, rigidity and minimum weight is a thin-walled shell, which is a skin reinforced with a power set. In such a shell, the material is located along the periphery, which, as is known, provides the greatest strength and rigidity of the structure. The efficiency of using the advantages of a thin-walled shell depends on how successfully the skin is included in the overall power circuit. In order for the sheathing to perform the power function in the best possible way, it is necessary to exclude the loss of its stability under operational loads. The main feature of thin-walled shells is low local stiffness. For this reason, large concentrated forces and moments cannot be directly applied to thin-walled elements. Under the action of such loads, special elements are used, the task of which is to convert concentrated loads into distributed loads and vice versa.
Ensuring high manufacturability of the design.
The requirement for high manufacturability, as a rule, leads to weighting and, in some cases, to the complexity of the design. Manufacturability is improved by: the division of the structure into units, compartments and panels, - the minimum number of parts, - simple configurations of parts that allow the use of high-performance processes; the correct choice of structural materials, taking into account their technological properties, is the minimum consumption of materials.
Simplification of the design is achieved due to a number of factors: simple configurations of parts, the use of standard and normalized parts, the use of a minimum number of standard sizes and the range of materials and semi-finished products are important. The use of components and parts previously mastered in production and tested in operation also opens up great opportunities for simplifying the design.
The mechanical and physical properties of the material must ensure the minimum mass of the structure, allow the use of high-performance technological processes. Materials must be corrosion-resistant, inexpensive and made from non-scarce raw materials. From the point of view of production technology and operation, it is very important that the structural material does not have a tendency to crack and is well processed. These qualities of the material are the better, the higher its plasticity, which indicates the ability of the material to absorb energy during deformation and, therefore, is the most important characteristic of performance, and, consequently, the resource of the structure. - Ensuring operational excellence. Operational perfection is understood as a set of properties of an aircraft that characterize its adaptability to the operation process at all stages. Modern requirements for the operational properties of the CR are quite stringent and are as follows. After assembly and a comprehensive check of performance at the factory, the missile should not require any restoration work during the scheduled storage period (10 years). This is achieved by careful testing of all rocket systems in the process of comprehensive tests corresponding to real extreme operating conditions (in terms of loads, temperature conditions, humidity and dust content of the air, etc.).
It is very important that the equipment be assembled according to the block principle, and the designs of the block attachment points should be easily removable. This ensures that equipment blocks can be replaced with minimal labor and time.
After the expiration of the scheduled service life, the missiles are subjected to careful control with test launches. If there are failures, the missiles are sent for modifications to the manufacturing plants. Based on the results of checks and launches, a decision is made to extend the service life and reliability level of the missiles during this period, with an orientation that the total service life of the missiles should be approximately 20 years.
The final stage of operation is the disposal of missiles. At present, this stage is very uncertain and very time-consuming, which is a consequence of shortcomings in the creation of the existing fleet of missiles. According to modern requirements, the development of recycling technology should be an integral part of design studies and reflected in project documentation. From the very beginning, it should be foreseen which part of the rocket elements will be used as a reserve fund, which part is planned for use in subsequent modifications of the rocket - technologies for the destruction of fuels and explosives should be worked out with particular care.
1.2.1 Technical requirements
-The dimensions of the product must ensure the possibility of launching from a container.
-Control-guidance systems must ensure an accurate hit on the target.
-The warhead must ensure trouble-free operation and trouble-free storage.
1.2.2 Operational requirements
-CR should be convenient in operation, storage and transportation; faultless and reliable.
Emerged (more precisely, revived) in the late 1970s. Since the second half of the 1980s, in the USSR and the USA, as an independent class of strategic offensive weapons, long-range air and sea cruise missiles (CR) are also considered as high-precision missiles (HTO), designed to destroy especially important small-sized targets with conventional (non-nuclear) warheads. The AGM-86C (CALCM) and AGM-109C "Tomahawk" cruise missiles equipped with high-power (weight - about 450 kg) non-nuclear warheads (warheads) demonstrated high efficiency in combat operations against Iraq (permanently conducted since 1991), as well as in the Balkans (1999) and in other parts of the world. At the same time, tactical (non-nuclear) first-generation missiles had a relatively low flexibility of combat use - the flight mission was entered into the missile guidance system on the ground, before the bomber took off or the ship left the base, and took more than a day (later it was reduced to several hours ).
In addition, the KR had a relatively high cost (more than $ 1 million), low hit accuracy (circular probable deviation - CEP - from tens to hundreds of meters) and several times less than their strategic prototypes, the range of combat use (respectively , 900-1100 and 2400-3000 km), which was due to the use of a heavier non-nuclear warhead, which "displaced" part of the fuel from the rocket body. The carriers of the KR AGM-86C (launch weight 1460 kg, warhead weight 450 kg, range 900-1100 km) are currently only strategic bombers-missile carriers B-52N, and AGM-109C are equipped with surface ships of the "destroyer" and "cruiser" class ", equipped with universal vertical container launchers, as well as multi-purpose nuclear submarines (NPS), using missiles from a submerged position.
Based on the experience of military operations in Iraq (1991), American KR of both types were modernized in the direction of increasing the flexibility of their combat use (now the flight mission can be entered remotely, directly on board the aircraft or carrier ship, in the process of solving a combat mission) . Due to the introduction of an optical correlation system of final homing, as well as equipping with a satellite navigation unit (GPS), the accuracy characteristics of the weapon (KVO -8-10 m) have significantly increased, which made it possible to hit not just a specific target, but its specific area.
In the 1970-1990s, up to 3,400 AGM-109 missiles and more than 1,700 AGM-86 missiles were produced. At present, the AGM-109 missile systems of early modifications (both "strategic" and anti-ship) are massively being finalized into the tactical version of the AGM-109C Block 111С, equipped with an improved guidance system and having an increased combat range from 1100 to 1800 km, as well as reduced KVO (8-10 m). At the same time, the mass (1450 kg) of the rocket and its speed characteristics (M = 0.7) remained practically unchanged.
Since the late 1990s, work has also been carried out in parallel to create a simplified, cheaper version of the Tactical Tomahawk cruise missile, designed exclusively for use from aboard surface ships. This made it possible to reduce the requirements for the strength of the airframe, to abandon a number of other elements that ensure the launch of a missile in a submerged position from nuclear submarine torpedo tubes, and thereby improve the weight return of the aircraft and increase its performance characteristics (first of all, the range, which should increase to 2000 km ).
In the longer term, by reducing the mass of avionics and the use of more economical engines, the maximum range of the upgraded AGM-86C and AGM-109C type missiles will increase to 2000-3000 km (while maintaining the same efficiency of non-nuclear warheads).
cruise missile AGM-86B
However, the process of transforming the AGM-86 aircraft cruise missiles into a non-nuclear version in the early 2000s slowed down significantly due to the lack of "extra" missiles of this type in the US Air Force (unlike the Tomahawk missiles in the nuclear version, which, in accordance with the Russian-American agreements, withdrawn from the ammunition of ships and transferred to coastal storage, the AGM-86 continues to be included in the nuclear classification, being the basis of the strategic weapons of the US Air Force B-52 bombers). For the same reason, the transformation into a non-nuclear variant of the AGM-129A strategic stealth missile system, which is also equipped exclusively with B-52H aircraft, has not begun. In this regard, the issue of resuming mass production of an improved version of the AGM-86 KR has been repeatedly raised, but a decision on this has not been made.
For the foreseeable future, the US Air Force considers the subsonic (M = 0.7) Lockheed Martin AGM-158 JASSM missile, the flight tests of which began in 1999, as the main tactical missile launcher of the US Air Force. The missile, which has dimensions and weight (1100 kg), approximately corresponding to the AGM- 86, is capable of hitting targets with high accuracy (KVO - several meters) at a distance of up to 350 km. Unlike the AGM-86, it is equipped with a more powerful warhead and has less radar visibility.
Another important advantage of the AGM-158 is its versatility in terms of carriers: it can be equipped with almost all types of combat aircraft of the US Air Force, Navy and Marine Corps (B-52H, B-1B, B-2A, F-15E, F-16C, F / A-18, F-35).
KR JASSM is equipped with a combined autonomous guidance system - inertial-satellite on the marching leg of the flight and thermal imaging (with target self-recognition mode) - on the final one. It can be assumed that a number of improvements implemented (or planned for implementation) on the AGM-86C and AGM-109C cruise missiles will also be used on the rocket, in particular, the transmission of a "receipt" of hitting the target to the ground command post and the retargeting mode in flight.
The first small-scale batch of JASSM missiles includes 95 missiles (its production began in mid-2000), two subsequent batches will amount to 100 items each (deliveries begin in 2002). The maximum production rate will reach 360 missiles per year. Serial production of cruise missiles is expected to continue at least until 2010. Within seven years, it is planned to manufacture at least 2,400 cruise missiles at a unit cost of each product of at least $0.3 million.
Lockheed Martin, together with the Air Force, are considering the possibility of creating a variant of the JASSM missile with an extended body and a more economical engine, which will increase the range to 2800 km.
At the same time, the US Navy, in parallel with a rather "formal" participation in the JASSM program, in the 1990s continued work to further improve the AGM-84E SLAM tactical aviation missile, which, in turn, is a modification of the Boeing Harpoon AGM anti-ship missile -84, created in the 1970s. In 1999, the US Navy carrier-based aviation received the Boeing AGM-84H SLAM-ER tactical cruise missile with a range of about 280 km - the first American weapon system with the ability to automatically recognize targets (ATR mode - Automatic Target Recognition). Giving the SLAM-ER KR guidance system the ability to autonomously identify targets is a major step in improving the WTO. Compared to the Automatic Target Acquisition (ATA) mode, already implemented in a number of aircraft weapons, in the ATR mode, the "picture" of a potential target obtained by onboard sensors is compared with its digital image stored in the on-board computer memory, which makes it possible to carry out autonomous search for the object of strike, its identification and targeting of the missile in the presence of only approximate data on the location of the target.
The SLAM-ER missile is equipped with F/A-18B/C, F/A-18E/F and, in the future, F-35A carrier-based multirole fighters. SLAM-ER is the "domestic" competitor of the KR JASSM (purchases of the latter by the US fleet still seem problematic).
Thus, until the beginning of the 2010s, in the arsenal of the US Air Force and Navy in the class of non-nuclear cruise missiles with a range of 300-3000 km, there will be only low-altitude subsonic (M = 0.7-0.8) missile launchers with marching turbofan engines, which have a small and ultra-low radar signature (EPR = 0.1-0.01 sq.m) and high accuracy (KVO - less than 10 m).
In the longer term (2010-2030s), it is planned to create a new generation of long-range missiles in the United States, designed to fly at high supersonic and hypersonic (M = 4 or more) speeds, which should significantly reduce the reaction time of the weapon, as well as , in combination with low radar visibility, the degree of its vulnerability to existing and prospective enemy missile defense systems.
The US Navy is considering the development of a high-speed universal cruise missile JSCM (Joint Supersonic Cruise Missile), designed to combat advanced air defense systems. KR should have a range of about 900 km and a maximum speed corresponding to M = 4.5-5.0. It is assumed that it will carry a unitary armor-piercing part or a cluster warhead equipped with several submunitions. Deployment of KPJSMC, according to the most optimistic forecasts, can be started in 2012. The cost of the missile development program is estimated at $1 billion.
It is assumed that the JSMC KR will be able to be launched from surface ships equipped with Mk 41 universal vertical launchers. replacement of subsonic KR SLAM-ER). It is planned that the first decisions on the JSCM program will be made in 2003, and in the 2006-2007 financial year, full-scale financing of the work may begin.
According to the director of naval programs at Lockheed, Martin E. Carney (AI Carney), although state funding for the JSCM program has not yet been carried out, in 2002 it is planned to finance work on the ACTD (Advanced Concept Technology Demonstrator) research program. In the event that the groundwork for the ACTD program will form the basis of the JSMC rocket concept, Lockheed Martin is likely to become the main contractor for the creation of a new CD.
The development of an experimental ACTD rocket is carried out jointly by Orbital Science and the US Naval Weapons Center (China Lake Air Force Base, California). The rocket is supposed to be equipped with a liquid air-ramjet engine, research on which has been underway in China Lake for the past 10 years.
The main "sponsor" of the JSMC program is the US Pacific Fleet, which is primarily interested in effective means of combating the rapidly improving Chinese air defense systems.
In the 1990s, the US Navy launched a program to create advanced ALAM missile weapons designed for use by surface ships against coastal targets. A further development of this program in 2002 was the project of the FLAM (Future Land Attack Missile) complex, which should fill the "niche range" between the corrected active-reactive artillery 155-mm ERGM guided projectile (capable of hitting targets with high accuracy at a distance of more than 100 km) and the Tomahawk missile launcher. The missile must have increased accuracy. Funding for its creation will begin in 2004. It is planned that the FLAM missile will be equipped with a new generation of destroyers of the DD (X) type, which will begin to be put into operation in 2010.
The final appearance of the FLAM rocket has not yet been determined. According to one of the options, it is possible to create a hypersonic aircraft with a liquid ramjet engine based on the JSCM rocket.
Lockheed Martin, together with the French center ONR, is working on the creation of a solid-propellant air-jet engine SERJ (Solid-Fuelled RamJet), which can also be used on the ALAM / FLAM rocket (although it seems more likely to install such an engine on rockets of a later design, which may appear after 2012, or on the ALAM / FLAM KR in the process of its modernization), since the ramjet is less economical than the turbofan engine, a supersonic (hypersonic) missile with a SERJ type engine is estimated to have a shorter (about 500 km) range, than subsonic missiles of the same mass and dimensions.
Boeing, together with the US Air Force, is considering the concept of a hypersonic missile launcher with a lattice wing, designed to deliver two to four subminiature autonomous subsonic missile launchers of the LOCAADS type to the target area. The main task of the system should be to defeat modern mobile ballistic missiles, which have a pre-launch preparation time (the beginning of which can be fixed by reconnaissance means after the missile is raised to a vertical position) of the order of 10 minutes. Based on this, a hypersonic cruise missile should reach the target area within 6-7 minutes. after receiving the target designation. No more than 3 minutes can be allotted for searching and hitting a target with submunitions (mini-KR LOCAADS or BAT-type gliding munitions).
As part of this program, the possibility of creating a demonstration hypersonic missile ARRMD (Advanced Rapid Response Missile Demonstrator) is being investigated. UR must carry out cruising flight at a speed corresponding to M=6. At M=4, submunitions must be ejected. The ARRMD hypersonic missile with a launch weight of 1045 kg and a maximum range of 1200 km will carry a payload of 114 kg.
In the 1990s work on the creation of missiles of the operational-tactical class (with a range of about 250-350 km) unfolded in Western Europe. France and Great Britain, on the basis of the French tactical missile launcher "Apache" with a range of 140 km, designed to destroy railway rolling stock (the entry of this missile into service with the French Air Force began in 2001), created a family of cruise missiles with a range of about 250-300 km SCALP-EG / "CTOpM Shadow", designed to equip the Mirage 20000, Mirage 2000-5, Harier GR.7 and Tornado GR.4 strike aircraft (and in the future - Rafal and EF2000 Lancer) . The features of rockets equipped with turbofan engines and retractable aerodynamic surfaces include subsonic (M = 0.8) speed, low-altitude flight profile and low radar visibility (achieved, in particular, by finned surfaces of the airframe).
The rocket flies along a pre-selected "corridor" in the mode of following the terrain. It has high maneuverability, which makes it possible to implement a number of programmed anti-aircraft fire evasion maneuvers. There is a GPS receiver (American NAVSTAR system). In the final section, a combined (thermal imaging / microwave) homing system with a target self-recognition mode should be used. Before approaching the target, the rocket performs a slide, followed by a dive on the target. In this case, the dive angle can be set depending on the characteristics of the target. A BROACH tandem warhead on approach "fires" a head submunition at the target, which pierces a hole in the protective structure, into which the main ammunition flies, exploding inside the object with some slowdown (the degree of slowdown is set depending on the specific features of the target assigned to hit).
It is assumed that the Storm Shadow and SCALP-EG missiles will go into service with the aviation of Great Britain, France, Italy and the United Arab Emirates. It is estimated that the cost of one serial KR (with a total order volume of 2000 missiles) will be approximately $ 1.4 million. (however, the order volume of 2000 CR seems to be very optimistic, so one can expect that the real cost of one missile will be much higher).
In the future, on the basis of the Storm Shadow missile, it is planned to create a reduced export version of the Black Shahin, which can be equipped with Mirage 2000-5/9 aircraft.
The international Franco-English concern MBD (Matra/BAe Dynamics) is studying new modifications of the Storm Shadow/SCALP-EG rocket. One of the promising options is an all-weather and all-day ship-based missile launcher designed to destroy coastal targets. According to the developers, the new European missile with a range of more than 400 km can be considered as an alternative to the American Tomahawk naval missile equipped with a non-nuclear warhead, in comparison with which it will have higher accuracy.
The CR should be equipped with an inertial satellite guidance system with an extreme correlation correction system along the earth's surface (TERPROM). At the final stage of the flight, it is supposed to use a thermal imaging system for autonomous homing to a contrast target. The European GNSS space navigation system, which is under development and is similar in its characteristics to the American NAVSTAR system and Russian GLONASS, will be used to guide the CR.
The EADS concern is working on the creation of another subsonic aviation KR KEPD 350 Taurus with a launch weight of 1400 kg, very close to the SCALP-EG / Storm Shadow KR. The missile with a maximum combat range of about 300-350 km is designed for low-altitude flight at a speed corresponding to M=0.8. It should enter service with the German Tornado fighter-bombers after 2002. In the future, it is also planned to equip the EF2000 Typhoon aircraft with it. In addition, it is planned to deliver the new CD for export, where it will seriously compete with the Franco-British tactical cruise missile Matra / BAe Dynamics "Storm Shadow" and, probably, the American AGM-158.
On the basis of the KEPD 350 missile, a project is being developed for the KEPD 150SL anti-ship missile with a range of 270 km, designed to replace the Harpoon missile. Anti-ship missiles of this type are supposed to be equipped with promising German frigates and destroyers. The missile should be placed in deck containers of rectangular section, grouped into four-container blocks.
The airborne version of the KEPD 150 (having a launch weight of 1060 kg and a range of 150 km) has been selected by the Swedish Air Force to equip the JAS39 Gripen multirole fighter. In addition, this SD is offered to the Air Force of Australia, Spain and Italy.
Thus, in terms of speed characteristics (M = 0.8), European cruise missiles approximately correspond to their American counterparts, they also fly along a low-altitude profile and have a range that is much shorter than the range of the tactical variants of the AGM-86 and AGM-109 and approximately equal to the range of the AGM -158 (JASSM). Just like the American KR, they have a low (RSR of the order of 0.1 sq.m) radar visibility and high accuracy.
The scale of production of European CRs is much smaller than that of American ones (the volume of their purchases is estimated at several hundred units). At the same time, the cost characteristics of American and European subsonic CDs are approximately comparable.
It can be expected that until the beginning of the 2010s, the Western European aviation and missile industry in the class of tactical (non-nuclear) KR will produce only products of the SCALP / Storm Shadow and KEPD 350 types, as well as their modifications. With a view to a more distant future (2010s and later) in Western Europe (primarily in France), as well as in the United States, research is being conducted in the field of long-range hypersonic strike missiles. During 2002-2003, flight tests of a new hypersonic experimental cruise missile with a ramjet "Vestra", created by EADS and the French arms agency DGA, should begin.
The implementation of the Vestra program was launched by the DGA in September 1996. At the same time, the goal was to "promote the definition of the appearance of a multi-purpose long-range high-altitude (combat) missile." The program made it possible to work out the aerodynamics, power plant and elements of the control system of a promising CR. Studies conducted by DGA specialists led to the conclusion that a promising high-speed rocket should perform the final stage of flight at low altitude (originally it was assumed that the entire flight would take place only at high altitude).
On the basis of the Vestra missile launcher, an air-launched combat hypersonic missile FASMP-A, designed to replace the KPASMP, should be created. Its entry into service is expected at the end of 2006. The carriers of the FASMP-A missile, equipped with a thermonuclear warhead, should be Dassault Mirage N fighter-bombers and Rafal multifunctional fighters. In addition to the strategic version of the KR, it is also possible to create an anti-ship version with a conventional warhead and a final homing system.
France is currently the only foreign country armed with a long-range cruise missile with a nuclear warhead. As early as the 1970s, work began on the creation of a new generation of aviation nuclear weapons - the Aerospasial ASMP supersonic cruise missile. On July 17, 1974, the TN-80 nuclear warhead with a capacity of 300 kt was tested, designed to equip this missile. Testing was completed in 1980 and the first TN-80 ASMP missiles entered service with the French Air Force in September 1985.
The ASMP missile (which is part of the armament of the Mirage 2000M fighter-bombers and the Super Etandar carrier-based attack aircraft) is equipped with a ramjet engine (kerosene is used as fuel) and a starting solid fuel booster. The maximum speed at high altitude corresponds to M=3, near the ground - M=2. Launch range - 90-350 km. The launch weight of the KR is 840 kg. A total of 90 ASMP missiles and 80 nuclear warheads for them were manufactured.
Since 1977, China has been implementing national programs to create its own long-range cruise missiles. The first Chinese KR, known as the X-600 or Hong Nyao-1 (XN-1), was adopted by the ground forces in 1992. It has a maximum range of 600 km and carries a 90 kT nuclear warhead. A small-sized turbofan engine was developed for the KR, flight tests of which began in 1985. The X-600 is equipped with an inertial correlation guidance system, probably supplemented by a satellite correction unit. The final homing system is believed to have used a television camera. According to one source, the CEP of the X-600 missile is 5 m. However, this information seems to be too optimistic. The radio altimeter installed on board the CD ensures flight at an altitude of about 20 m (obviously above the sea surface).
In 1992, a new, more economical engine was tested for the Chinese KR. This made it possible to increase the maximum launch range to 1500-2000 km. The modernized version of the cruise missile under the designation XN-2 was put into service in 1996. The developed modification XN-Z should have a range of about 2500 m.
KhN-1, KhN-2 and KhN-Z missiles are ground-based weapons. They are placed on "ground-mobile" wheeled launchers. However, variants of the KR are also under development for placement on board surface ships, submarines or aircraft.
In particular, new Chinese multi-purpose nuclear submarines of project 093 are considered as potential carriers of the missile launcher. The missiles should be launched from a submerged position through 533-mm torpedo tubes. The new JH-7A tactical bombers, as well as the J-8-IIM and J-11 (Su-27SK) multipurpose fighters, can be carriers of the aviation version of the KR.
In 1995, it was reported that the PRC had begun flight tests of a supersonic unmanned aircraft, which could be considered a prototype of a promising cruise missile.
Initially, work on the creation of cruise missiles was carried out in China by the Hain Electromechanical Academy and led to the creation of tactical anti-ship missiles Hain-1 (a variant of the Soviet anti-ship missiles P-15) and Hain-2. Later, the supersonic anti-ship missile "Khain-Z" with a ramjet engine and "Khain-4" with a turbojet engine were developed.
In the mid-1980s, NII 8359, as well as the "Chinese Institute of Cruise Missiles" (however, the latter may be the renamed Hain Electromechanical Academy), were formed to work in the field of creating cruise missiles in the PRC.
We should also stop at work on improving the warheads of cruise missiles. In addition to combat units of the traditional type, American KR began to be equipped with fundamentally new types of warheads. In the course of Operation Desert Storm in 1991, for the first time, KR were used, carrying fibers of thin copper wire, scattered over the target. Such a weapon, which later received the unofficial name "I-bomb", served to disable power lines, power plants , substations and other energy facilities: hanging on the wires, the wire caused a short circuit, depriving military, industrial and communication centers of the enemy of electricity.
During the fighting against Yugoslavia, a new generation of these weapons was used, where thinner carbon fibers were used instead of copper wire. At the same time, not only missile launchers, but also free-falling aerial bombs are used to deliver new "anti-energy" warheads to targets.
Another promising type of American missile combat units is an explosive magnetic warhead, which, when triggered, generates a powerful electromagnetic pulse (EMP) that "burns out" the enemy's radio-electronic equipment. At the same time, the radius of the damaging effect of EMP generated by an explosive magnetic warhead is several times greater than the radius of destruction of a conventional high-explosive fragmentation warhead of the same mass. According to a number of media reports, explosive magnetic warheads have already been used by the United States in real combat conditions.
Undoubtedly, the role and importance of long-range cruise missiles in non-nuclear equipment will increase in the foreseeable future. However, the effective use of these weapons is possible only if there is a global space navigation system (currently the United States and Russia have such systems, and the United Europe will soon join them), a high-precision geographic information system of combat areas, as well as a multi-level system of aviation and space reconnaissance, which provides data on the position of targets with their exact (on the order of several meters) georeferencing. Therefore, the creation of modern high-precision long-range weapons is the lot of only relatively technologically advanced countries that are capable of developing and maintaining the entire information and intelligence infrastructure that ensures the use of such weapons.
"Harpoon", "Tomahawk", "Caliber", "Onyx" or "Brahmos": who can compete with them for the title of the best cruise missile in the world?
Recently, it is the cruise missile that has become one of the most deadly and sought-after types of weapons. To get the enemy with a scalpel-point strike, eliminate his command bunker, sink the flagship, or conduct a massive attack on enemy positions - only cruise missiles are capable of performing all these tasks at once. Cheap, angry, effective, and, most importantly, without any participation of the pilot. It is for these reasons that all the leading world powers and countries of a lower rank are trying to effectively develop their technologies aimed at building new models of this formidable weapon. But who among them went the farthest? Whose gunsmiths created the most advanced cruise missile in the world?
Answers to this question in a special review of the ten best cruise missiles in the world.
10th place: RGM-84 Harpoon Block II (USA).
Opens our top "American old man", the development of the middle of the last century, one of the most common cruise missiles in the world, a kind of anti-ship "harpoon" - RGM-84 of the latest Block II modification. A reliable, proven system is truly universal and can be based both on land and in the air, on water and under water. But only naval targets are capable of hitting, and even then at a very short distance, only 130 kilometers and with a not very high maximum speed of 860 km / h, and it carries only a little more than 200 kilograms of combat load. Agree, very, very modestly.
With such parameters, all kinds of target approach modes and the small dimensions of the missile will not help to break through the modern enemy missile defense system and sink a serious ship like an aircraft carrier. Yes, and the rocket carrier will have to approach a dangerous distance. Therefore, Harpoon takes an honorable tenth place, for the sake of respect for the former glory of the "old man".
9th place: RBS-15 Mk. III (Sweden).
Another "old man" from our review, the Swedish arms concern Saab began to develop at the same time as the RGM-84, but the development, alas, dragged on and the first modification of the rocket was put into service only in 1985. But it turned out better than the American competitor. Launch versatility from all possible carriers, twice the flight range, almost the same warhead mass and higher flight speed: the RBS-15, the third modification, is more deadly than the Harpoon, but also cannot be used against ground targets. Therefore, the Swedish development and confidently pushes the American "harpoon" in our rating.
8th place: SOM (Turkey)
The Turkish armed forces, up to the present moment, did not have a cruise missile of their own production, but in 2012 they nevertheless adopted the latest development - the SOM missile. Created in Turkish design bureaus, SOM is a fairly compact universal cruise missile capable of hitting not only sea, but also ground targets. The latest electronics, various target engagement modes, firing range and maximum flight speed above the level of the legendary RGM-84 - all this was realized by the Turks in metal. But still, Turkey still lacks experience in the development of such weapons systems. Therefore, it was possible to surpass the Swedish and American analogues of SOM, but nothing more. Diagnosis: study and study again, development experience comes with time.
7th place: Naval Strike Missile (Norway)
The Norwegians, first of all, care about the protection of the maritime borders of their own state and, with their development in 2007, do not lag behind the world's leading manufacturers of cruise missiles. Naval Strike Missile puts Harpoon, RBS-15, and SOM in the belt. The missile flies further, almost reaches the speed of sound, is assembled from composite materials, destroys all targets and itself can actively interfere with the enemy. Therefore, such a “gift” is extremely difficult to intercept by the missile defense system.
But for now, the Naval Strike Missile can only be based on ships, and it carries only 125 kilograms of combat load. Not enough - the lowest indicator from our rating, therefore only 7th place.
6th place: BGM-109 Tomahawk Block IV (USA)
So, meet the legendary Tomahawk. Where would we be without it ... An ageless veteran and one of the most famous cruise missiles in the world opens the list of heavyweights in our ranking.
The longest range of destruction, the richest history of combat use, a very serious warhead mass of 450 kilograms - the American "tomahawk" is the most serious threat to the enemy. For an adversary who does not have the same modern air defense system, for example, third world countries. Subsonic speed, coupled with the inability to maneuver with large overloads, make the American “miracle weapon” an easy target for the latest enemy anti-aircraft missiles.
But still, the flight range of 1600 kilometers plays a significant role, so place number 6.
5th place: Storm Shadow/SCALP EG (France-Italy-Great Britain).
The joint development of the leading arms concerns of the European Union should have led to something, at least grandiose. Thus was born the unique, electronically crammed, stealth-based cruise missile Storm Shadow. Its tandem-type warhead, weighing almost half a ton, can penetrate the most serious armor, and the combined guidance system with target recognition mode can hit the most hard-to-reach targets.
It would seem that Storm Shadow should be the leader of this rating, if not for one "but" ... maximum speed. The missile cannot overcome the supersonic barrier, which means that for the latest missile defense systems it remains a fairly easy victim.
4th place: R-800 Onyx/Yakhont (Russia)
The old man "of the Soviet development of the late 70s earned its place on the list thanks to one advantage - a supersonic flight speed of 3000 km / h. None of the above cruise missiles developed in the West has such a characteristic, which means that there are practically no equals in the breakthrough of modern Onyx missile defense systems. And the complete unification of the main types of carriers (surface, underwater, ground) and the possibility of using against targets of any base confidently put the Russian missile in 4th place.
3rd place: 3M-54 Caliber (Russia)
The latest Russian weapons system, developed at the turn of the century, recently shocked the whole world with its combat capabilities during the autumn missile launches at the positions of Daesh militants *. An amazing possibility of basing on all types of media, including in specially disguised containers. Amazing maximum flight speed, almost three times the speed of sound. Incredible targeting and hitting accuracy. One of the highest firing ranges and the largest mass of the warhead. "Caliber" certainly deserved the highest place in our rating!
But, alas, most of the data on the Russian cruise missile is classified and we can only be guided by approximate parameters. Therefore, bronze.
2nd place: YJ-18 (China)
In any rating there will always be a "dark horse", in ours - Chinese-made. Very little is known about the YJ-18 cruise missile: the Celestial Empire has always been able to keep its secrets, but, apparently, it is a serious modification of the Russian analogue 3M-54 Caliber, the technology of which went to the Chinese along with Project 636 submarines.
Well, what could be better and more lethal than the improved Caliber? That's right, practically nothing, which means - silver.
1st place: BRAHMOS (Russia-India).
Only mountains can be better than mountains, and only BRAHMOS is better than Caliber and the Chinese-modified Caliber. The latest Russian-Indian cruise missile, based on the R-800 Oniks, leads the ranking.
Maximum speed of 3700 km / h, a mixed flight profile that provides a completely unpredictable trajectory of approach to the target at ultra-low altitudes at supersonic speed, 300 kilograms of a warhead (penetrating, high-explosive fragmentation, cluster) and a launch range of 300 kilometers - save from BRAHMOS is unlikely to be able to any PRO. Well, if we add here the possibility of being based on any type of carriers and the possibility of hitting absolutely any targets, then it becomes clear why gold is behind the missile of Russian-Indian development.
Well, and finally - a short video with colorful launches of all the presented missiles.
* – The activity of the organization is prohibited on the territory of the Russian Federation by decision of the Supreme Court.
CRUISE ROCKET (CR), an atmospheric unmanned aerial vehicle equipped with wings, an engine (jet or rocket), and a targeting system; designed for high-precision destruction of land and sea targets. KR can be placed both on stationary and mobile launchers (land, air and sea-based). The main distinguishing features of the CD: high aerodynamic characteristics; maneuverability; the ability to set an arbitrary course and movement at low altitude along the bends in the terrain, which makes it difficult to detect them by enemy air defense systems; high-precision target destruction [circular probable deviation (CEP) of modern CR does not exceed 10 m]; the ability, if necessary, to correct the programmed flight trajectory using the on-board computer and automatic control system (BSAU). Depending on the relative position of the bearing and control surfaces, the CR can have an aircraft or rocket aerodynamic configuration. Therefore, in a broad sense, almost all types of guided missiles (aircraft, anti-aircraft, anti-ship and anti-tank) are referred to as missiles. In a narrow sense, CR is understood as missiles made according to an aircraft scheme (Fig. 1). KR are subdivided: according to the firing range and the nature of the tasks being solved - into tactical (up to 150 km), operational-tactical (150-1500 km) and strategic (over 1500 km); by flight speed - into sonic and supersonic; by type of basing - ground, air, sea (surface and underwater); by type of warhead (warhead) - nuclear and conventional (high-explosive, cluster, etc.); for combat purposes - classes "air - surface" (Fig. 2) and "surface - surface".
The CR consists of a body (fuselage) with bearing and control surfaces (wing, rudders, stabilizers, etc.), an engine, installation, onboard control equipment and warheads. The CR has a welded metal or composite housing, most of the internal volume of which is a fuel tank. Prior to the launch of the rocket, the wings are in the folded state and open after the ejection launcher is triggered. The propulsion system of the land- and sea-based cruise missile consists of a launch booster and a propulsion engine. As the latter, both a rocket (liquid or solid propellant) and an air-jet engine can be used. The launch booster is, as a rule, a solid-propellant jet engine (there is no air-based missile launcher). The engine has an automatic electronic-hydraulic control system that provides a change in its modes and thrust adjustment during the rocket flight. The basic composition of the equipment of a modern CR includes: an inertial navigation system; altimeters; route correction systems (including with the help of the global satellite navigation system); homing head; automatic self-destruction system; a system for exchanging information between salvo missiles; on-board computer; in addition to the autopilot function, the BSAU also has the ability to perform missile maneuvers to counter interception. A typical RC scheme is shown in Figure 3.
The prospects of this weapon drew the attention of S. P. Korolev, who developed in 1932-38 a series of experimental KR (217 / I, 217 / II, etc.); ground and flight tests were carried out, which confirmed the design characteristics, but the autopilot was unable to provide proper flight stabilization. The first KR (they were called unmanned projectiles) V-1 were developed and used by Germany at the end of World War II (the prototype was tested in December 1942, the first combat use was in June 1944). In the USSR, since 1943, the KR 10X was tested on Pe-8 bombers, and then Tu-2, but it did not receive combat use in the war. In the 1950s and 1960s, the USSR (the term "KR" was introduced in the USSR in 1959) and the United States created a number of KRs. Among them: in the USSR - KS-1 "Kometa" (the first guided missile in the USSR; launched in 1952), P-15, Kh-20, KSR-11, Kh-66, etc.; in the USA - "Matador", "Regulus-1", "Hound-Dog" and others. KR of this generation were not widely used, as they were heavy and bulky (starting weight 5.5-27 tons, length 10-20 m , hull diameter 1.3-1.5 m), in addition, there was no effective guidance system. The first KR with an underwater launch was the Soviet homing KR "Amethyst" (1968). The revival of interest in CR in the 1970s and the creation of a new generation of CR is due to technical advances that have made it possible to significantly increase the guidance accuracy, reduce overall dimensions and place them on mobile launch platforms. One of the most massive foreign CDs is the Tomahawk (USA). This missile began to enter service in 1981 in several versions: strategic ground (BGM-109 G) and sea (BGM-109 A) based with a nuclear warhead (there is a similar aviation KR AGM-86 B); operational-tactical sea-based BGM-109 C and BGM-109 D, respectively, with semi-armor-piercing and cluster warheads; tactical sea-based BGM-109 V with a high-explosive warhead. Modern domestic strategic missile launchers include the X-55 (air-based) and Granit (sea-based).
The main flight performance characteristics of some CRs of the Russian Federation and the USA are presented in the table.
When developing a new generation CR, much attention is paid to the creation of long-range CR control systems that provide CEP of 3-10 m with equipment mass up to 100 kg. Reducing the visibility of the RR is provided by the choice of low-reflective geometric shapes, the use of radar-absorbing materials and coatings, special devices for reducing the effective scattering surface, antenna devices and air intakes. Of the conventional warheads that are used on high-precision missiles to hit various targets, multifactorial warheads (high-explosive-cumulative with a penetrating effect) with a mass of 250-350 kg are widely used. The latest achievements in the field of microelectronics, propulsion systems, high-performance fuels and structural materials ensure the development of supersonic high-precision, low-profile missiles with a range of up to 3,500 km and a mass of no more than 1,500 kg.
Lit .: The creative heritage of Academician S.P. Korolev. Selected Works and Documents / Edited by M. V. Keldysh. M., 1980; Prospects and ways to improve weapons systems with sea-based cruise missiles. SPb., 1999; Salunin V., Burenok V. High-precision long-range weapons: military and technical aspects of creation // Military Parade. 2003. No. 1.
TOP 10 FASTEST ROCKETS IN THE WORLD
R-12U
The fastest medium-range ballistic missile with a maximum speed of 3.8 km per second opens the ranking of the fastest missiles in the world. The R-12U was a modified version of the R-12. The rocket differed from the prototype in the absence of an intermediate bottom in the oxidizer tank and some minor design changes - there are no wind loads in the mine, which made it possible to lighten the tanks and dry compartments of the rocket and abandon the stabilizers. Since 1976, the R-12 and R-12U missiles began to be withdrawn from service and replaced by Pioneer mobile ground systems. They were decommissioned in June 1989, and between May 21, 1990, 149 missiles were destroyed at the Lesnaya base in Belarus.
53Т6 "Amur"
The fastest anti-missile in the world, designed to destroy highly maneuverable targets and high-altitude hypersonic missiles. Tests of the 53T6 series of the Amur complex began in 1989. Its speed is 5 km per second. The rocket is a 12-meter pointed cone with no protruding parts. Its body is made of high-strength steels using composite windings. The design of the rocket allows it to withstand large overloads. The interceptor starts at 100x acceleration and is capable of intercepting targets flying at speeds up to 7 km per second.
SM-65-"Atlas"
One of the fastest American launch vehicles with a maximum speed of 5.8 km per second. It is the first developed intercontinental ballistic missile adopted by the United States. Developed under the MX-1593 program since 1951. It formed the basis of the US Air Force nuclear arsenal in 1959-1964, but then was quickly withdrawn from service in connection with the advent of the more advanced Minuteman missile. It served as the basis for the creation of the Atlas family of space launch vehicles, which has been in operation since 1959 to the present day.
UGM-133A Trident II
American three-stage ballistic missile, one of the fastest in the world. Its maximum speed is 6 km per second. Trident-2 has been developed since 1977 in parallel with the lighter Trident-1. Adopted in 1990. Starting weight - 59 tons. Max. throw weight - 2.8 tons with a launch range of 7800 km. The maximum flight range with a reduced number of warheads is 11,300 km.
PCM 56 Mace
One of the fastest solid-propellant ballistic missiles in the world, which is in service with Russia. It has a minimum radius of destruction of 8000 km, an approximate speed of 6 km / s. The development of the rocket has been carried out since 1998 by the Moscow Institute of Thermal Engineering, which developed in 1989-1997. ground-based missile "Topol-M". To date, 24 test launches of the Bulava have been carried out, fifteen of them were recognized as successful (during the first launch, a mass-size model of the rocket was launched), two (the seventh and eighth) were partially successful. The last test launch of the rocket took place on September 27, 2016.
Minuteman LGM-30G
One of the fastest land-based intercontinental ballistic missiles in the world. Its speed is 6.7 km per second. The LGM-30G Minuteman III has an estimated range of 6,000 kilometers to 10,000 kilometers, depending on the type of warhead. The Minuteman 3 has been in service with the US since 1970. It is the only silo-based missile in the United States. The first rocket launch took place in February 1961, modifications II and III were launched in 1964 and 1968, respectively. The rocket weighs about 34,473 kilograms and is equipped with three solid propellant engines. It is planned that the missile will be in service until 2020.
"Satan" SS-18 (P-36M)
The most powerful and fastest nuclear missile in the world with a speed of 7.3 km per second. It is intended, first of all, to destroy the most fortified command posts, ballistic missile silos and air bases. A nuclear explosive from a single missile can destroy a large city, quite a large part of the US. Hit accuracy is about 200-250 meters. The missile is housed in the world's most durable mines. The SS-18 carries 16 platforms, one of which is loaded with decoys. Entering a high orbit, all the heads of the "Satan" go "in a cloud" of decoys and are practically not identified by radars.
DongFeng 5A
An intercontinental ballistic missile with a maximum speed of 7.9 km per second opens the top three fastest in the world. The Chinese DF-5 ICBM entered service in 1981. It can carry a huge 5 mt warhead and has a range of over 12,000 km. The DF-5 has a deviation of approximately 1 km, which means that the missile has one goal - to destroy cities. The size of the warhead, the deflection, and the fact that it only takes an hour to fully prepare for launch all mean that the DF-5 is a punitive weapon designed to punish any would-be attackers. The 5A version has increased range, improved 300m deflection, and the ability to carry multiple warheads.
R-7
Soviet, the first intercontinental ballistic missile, one of the fastest in the world. Its top speed is 7.9 km per second. The development and production of the first copies of the rocket was carried out in 1956-1957 by the OKB-1 enterprise near Moscow. After successful launches, it was used in 1957 to launch the world's first artificial earth satellites. Since then, launch vehicles of the R-7 family have been actively used to launch spacecraft for various purposes, and since 1961 these launch vehicles have been widely used in manned cosmonautics. Based on the R-7, a whole family of launch vehicles was created. From 1957 to 2000, more than 1,800 launch vehicles based on the R-7 were launched, of which more than 97% were successful.
RT-2PM2 "Topol-M"
The fastest intercontinental ballistic missile in the world with a maximum speed of 7.9 km per second. The maximum range is 11,000 km. Carries one thermonuclear warhead with a capacity of 550 kt. In the mine-based variant, it was put into service in 2000. The launch method is mortar. The rocket's solid propellant main engine allows it to pick up speed much faster than previous types of rockets of a similar class, created in Russia and the Soviet Union. This greatly complicates its interception by missile defense systems in the active phase of the flight.