RU2191985C2 - Method of firing antiaircraft guided rocket and rocket for its realization - Google Patents

Abstract

FIELD: antiaircraft armament. SUBSTANCE: method of firing antiaircraft guided rocket includes acceleration of antiaircraft rocket in two stages: first by primary low-thrust engine with powder charge of low-smoke fuel and then by sustainer engine to design terminal velocity. On termination of operation primary engine is separated from antiaircraft guided rocket with separation speed less or equal to velocity of antiaircraft rocket. Sustainer engine is switched on with delay, after separation of primary engine. Proposed method is realized with the use of antiaircraft rocket placed in transportation and launching matrix and comprising main stage of rocket and separable boost engine docked to it by means of stage separation mechanism. Rocket is fitted with primary low-thrust engine with powder charge of low-smoke fuel. Primary engine is installed in outlet part of nozzle of sustainer engine and is attached to it with the use of breakable elements. Separation chamber with thin- arch powder charge and ray igniter of delayed action is positioned by front bottom of primary low-thrust engine. Sealed electric connectors forming circuit of ignition of primary engine jointly with connecting wires are mounted in front cover and nozzle membrane of sustainer engine. EFFECT: invention ensures antiaircraft rocket firing over large range from combat vehicle in motion and enhances reliability of combat vehicle as whole. 6 cl, 4 dwg

Description

 The invention relates to military equipment, and in particular, to anti-aircraft guided missiles and methods of firing them.

 A known method of firing a guided missile "Medvedka" according to the "mortar" scheme [1], including the operation of vertical ejection of a rocket from a transport and launch container (TPK), turning in the direction of the target and accelerating the rocket with a rocket engine to a final speed [1].

 The disadvantage of this method of firing and the missile system that implements it is the large recoil force acting on the launcher when the missile is ejected from the transport-launch container (TPK). The large recoil force is due to the fact that the back section of the container is closed with a blank bottom to provide the container with the necessary gas pressure from the powder pressure accumulator.

 Due to the high recoil force, this method of firing cannot be applied to SAMs launched from mobile combat vehicles in motion, i.e. in position "on the go".

 Also known is the Tunguska anti-aircraft missile system [2], selected as a prototype in which missiles are launched from transport-launch containers opened at the back without creating significant forces acting on the launcher and the fighting vehicle as a whole.

 But this method can be implemented for firing small-sized SAM with rocket engines with a thrust of 1000-2000 kgf and a small range of destruction (10 km).

 The anti-aircraft guided missile - SAM [3], which implements this method, weighing 42 kg (TPK with a missile 57 kg) is made according to the bicaliber circuit with a detachable engine. This engine informs the rocket of the initial speed of 900 m / s and is separated at the end of work, approximately 2.6 seconds after launch. After the launch of missiles to the line of sight of the target, its marching stage continues to fly by inertia.

 The march stage of the missile launcher includes functional blocks - a non-contact fuse, a steering wheel, an autopilot block, a gyroscopic autopilot device, a power supply, a warhead, radio control equipment and a stage separation device.

 However, for firing missiles at a range of 20-30 km, significantly more powerful rocket engines with a thrust of 5000-7000 kgf are required. At the same time, engines with such a thrust when launching a missile launcher affect their combat vehicle with excessive loads, which are unacceptable in the first place for optoelectronic control devices, antennas, radars and neighboring transport and launch containers with missile launchers (usually 8- 12 missiles weighing up to 100 kg each).

 In addition, when starting a missile launcher with a powerful rocket engine, a dense dust cloud forms around the combat vehicle, which impedes the normal operation of the control system with optical communication lines.

 The problem to which the invention is directed, is to ensure the firing of SAM from combat vehicles in movement over long ranges (20-30 km) while improving the reliability of the combat vehicle as a whole.

 The problem is solved in that in the known method of firing a guided missile, including dispersing a missile launcher with a starting engine and bringing it to the line of sight, dispersing a missile launcher is performed in two steps, first with a primary thruster with a powder charge of low smoke, and then with the main starter engine to estimated final speed. At the same time, upon completion of the operation of the primary thruster, it is separated from the SAM with a separation speed less than or equal to the speed of the SAM. The main starting engine is started with a delay after separation of the primary thruster.

 The main starting engine SAMs include at a distance of 15-30 m from the combat vehicle (depending on the shooting conditions).

 Acceleration of missiles by the primary starting thruster is carried out to a speed of 25-50 m / s.

 The method is implemented by a missile located in a transport and launch container (TPK) and consisting of a marching stage with functional blocks and docked with it using a device for separating the steps of a detachable starting engine. The missile is equipped with a primary thruster with a powder charge of low-smoke fuel. The primary thruster starting engine is installed in the output part of the nozzle of the main starting engine and is fastened with discontinuous elements. At the same time, at the front bottom of the primary engine there is a separation chamber with a fine-composite powder charge and a delayed-action beam igniter. Sealed electrical connectors are installed in the front cover and nozzle membrane of the main starting engine, forming the ignition circuit of the primary starting engine with the wires connecting them.

 The discontinuous elements are made in the form of trapezoidal discontinuous keys installed symmetrically with respect to the longitudinal axis of the SAM.

 The outer surface of the primary engine at the place of docking with the output part of the nozzle of the main starting engine is made equidistant to the inner surface of the output part of the nozzle.

 Preliminary acceleration of missiles by the primary thruster with a powder charge of low-smoke fuel to a speed of 25-50 m / s and the inclusion of the main starting engine at a distance from the combat vehicle of 15-30 m ensure the absence of dust interference for the control system and exclude the force of the jet combat vehicle and its instrumentation.

The invention is illustrated by graphic materials, where:
figure 1 shows a diagram explaining the method of firing, figure 2, figure 3, figure 4 is a schematic design of a missile system that implements the specified method of firing and explosive structural elements.

Designations:
1 - combat vehicle;
2 - radar antenna;
3 - control devices;
4 - transport and launch containers;
5 - jet stream of the primary thruster;
6 - primary thruster;
7 - SAM with the main discharge; starting engine;
8 - the housing of the separated primary starting engine;
9 - jet stream of the main starting engine;
10 - march stage missiles;
11 - line of sight;
12 - trajectory of the fall of the separated housing of the primary starting engine;
13 - place of the fall of the primary starting engine;
14 - low smoke powder charge;
15 - the output of the nozzle of the main starting engine;
16 - trapezoidal discontinuous keys;
17 - camera compartment with a fine powder charge;
18 - radiation igniter delayed action;
19 - fine powder charge;
20 - front cover of the main starting engine with a sealed electrical connector;
21 - nozzle membrane of the main starting engine with a sealed electrical connector;
22 - electrical wires,
23 - functional blocks.

 The parameters indicated in the proposed method of firing in terms of the speed of SAM missiles of 25-50 m / s reported by the primary launch engine, and in terms of the starting range of the main launch engine of 15-30 m from the combat vehicle are justified as follows.

 At a speed of less than 25 m / s, the SAM has an increased sensitivity to wind speed and, as a result, large angular spreads in the position of the rocket in space by the time the main starting engine is turned on. As a result of a large initial dispersion, a miss is possible, that is, a decrease in firing efficiency.

 At a speed of missiles more than 50 m / s, it is necessary to use primary starting engines with a thrust of more than 2000 kgf. However, with such a thrust, the jet stream adversely affects the combat vehicle and can damage its control devices, radar antennas, etc., which ultimately will lead to a decrease in the reliability of the combat vehicle and failure to fulfill the combat mission. This problem is especially aggravated with the simultaneous launch of 2-3 missiles simultaneously to hit multiple targets.

 Thus, the range of speed SAM 25-50 m / s from the primary starting engine is optimal from the point of view of ensuring maximum efficiency of the missile system.

The minimum starting range of the starting engine of 15 m from the combat vehicle was selected based on the requirement to prevent a large excess pressure and high temperature of the jet stream on the elements of the combat vehicle when launching a missile launcher. At such a distance, the braking pressure in the stream usually does not exceed 0.2-0.3 kgf / cm, and the temperature of the gases is 200-400 ^o C, which is quite acceptable for short-term exposure.

 The limitation on the maximum starting range of the starting engine of 30 m is imposed for reasons of ensuring minimum dispersion and accurate shooting of SAM. Before the start engine is turned on, the missile launcher flies at a low speed, reported by the primary thruster, is controlled "sluggishly", sensitive to wind. When the main starting engine is turned on at ranges greater than 30 m from the combat vehicle, there is a significant dispersion of missiles, the effectiveness of the missile system decreases (to destroy one target, instead of one missile, two or three are required). Thus, the range of the starting range of the main starting engine of 15-30 m ensures maximum efficiency of the missile system.

 Shooting SAM in accordance with the invention is carried out as follows.

 Starting a missile launcher starts by supplying voltage to the electric igniter of the primary starting thruster 6. The charge 14 of the primary thruster made of low-smoke fuel is ignited, enters the mode, accelerates the missile 7 with its low thrust and pushes it out of the TPK 4. After exiting the container the primary thruster starting engine continues to work and by the end of it the missile speed reports 25-50 m / s. After a certain time, but always only after the end of the charge 14, the delayed-action beam igniter 18 is triggered and turns on the compartment chamber 17 with a fine powder charge 19.

 As a result of the operation of the separation chamber, the housing 8 (empty) of the primary thruster starting engine is separated from the SAM with a speed less than or equal to the speed of the SAM and along the path 12 falls to the ground at point 13, i.e. at a safe distance from the combat vehicle.

 During this period, missiles fly by inertia at a speed gained from the prime mover in the direction of the target. At a distance of SAM from the fighting vehicle 1 at a distance of 15-30 m, the main thrust starting engine is turned on, which accelerates the rocket to the final supersonic or hypersonic speed on trajectory 11. In this case, the jet stream 9 of the main starting engine at the indicated distance does not affect the vehicle her missiles and devices of unacceptable power, smoke and temperature effects. The operability of such a missile system is also ensured by simultaneous firing of two or three missiles to destroy several targets.

 Since with this method of firing the recoil force is negligible and the dust interference is small, reliable operation of the control system is ensured when firing immediately, i.e. when moving a combat vehicle, which is very important to increase the combat effectiveness of the complex and its invulnerability.

 Thus, the proposed method for firing SAMs and a missile for its implementation makes it possible to create highly effective mobile missile systems for the air defense forces, which, when performing a combat mission, change their location on the ground and for this reason are well protected from the opposing side.

Sources of information
1 Magazine "Military Parade", 1999, 3, p. 28-29.

 2. The magazine "Aviopanorama", September - October, 1999, pp. 56-57.

 3. The journal "Equipment and armaments yesterday, today, tomorrow" May - June 1999, p. 66.67.

Claims (6)

 1. A method of firing an anti-aircraft guided missile (SAM), including dispersing a missile launcher with a starting engine and bringing it to the line of sight, characterized in that the dispersal of a missile launcher is performed in two steps, first with a primary thruster with a powder charge of low-smoke fuel, and then with the main the starting engine to the calculated final speed, and at the end of the operation of the primary starting thruster, it is separated from the SAM with a separation speed less than or equal to the speed of the SAM, and I turn on the main starting engine t with a delay after separation of the primary thruster.  2. A method of firing a missile launcher according to claim 1, characterized in that the acceleration of the missile launcher by the primary starting thruster is carried out to a speed of 25-50 m / s.  3. The method of firing missiles according to claim 1 or 2, characterized in that the main starting engine of the missiles is switched on at a distance of 15-30 m from the combat vehicle.  4. Anti-aircraft guided missile located in the transport and launch container and consisting of a marching stage with functional blocks and docked with it using a stage separation device of a detachable starting engine, including a nozzle membrane and a front cover, characterized in that the rocket is additionally equipped with a primary a small thrust starting engine with a powder charge of low-smoke fuel, installed in the output part of the nozzle of the main starting engine and fastened with explosive elements and, at the same time, a separation chamber with a fine-powder powder charge and a delayed-action beam igniter is located at the front bottom of the primary engine, and sealed electrical connectors are installed in the front cover and the nozzle membrane of the main starting engine, which form the primary engine ignition circuit with the wires connecting them.  5. Anti-aircraft guided missile according to claim 4, characterized in that the explosive elements are made in the form of trapezoidal dowels installed symmetrically to the longitudinal axis of the SAM.  6. Anti-aircraft guided missile according to claim 4 or 5, characterized in that the outer surface of the primary starting engine at the place of docking with the output part of the nozzle of the main starting engine is made equidistant to the inner surface of the output part of the nozzle.

Images