RU2380648C1 - Multistaged air-defense missile - Google Patents

Abstract

FIELD: defense technology.

SUBSTANCE: multistaged air-defense missile comprises at least two stages with at least one solid propellant rocket engine at lower stage. Controlled aerodynamic rudders and wings are installed on upper stage and at least one solid propellant rocket engine. Solid propellant boosters with solid propellant rocket engines are connected to lower stage parallel to its axis. Number of aerodynamic rudders complies with number of solid propellant boosters, and they are installed each opposite according solid propellant booster. Solid propellant boosters are arranged with the possibility of undocking in process of flight, for instance due to their connection to lower stage with the help of pyrobolts.

EFFECT: increased speed, distance and altitude of missile flight.

3 cl, 2 dwg

Description

The invention relates to rocket technology, specifically anti-aircraft missiles with solid propellant rocket engines solid propellant rocket engines.

Liquid propellant rocket engines are often used as propulsion engines for rockets; they are easier to regulate than solid propellants. But solid propellant rocket engines have several advantages: they take less time to start, they are simpler in design and cheaper.

Known cruise missile according to the patent of the Russian Federation for invention No. 2225975, the combat stage of which is located in the cavity of the marching stage, which contains its own nose cone, flight control and guidance system for the target, warhead and additional solid fuel engine. The marching stage can be docked with a turbojet engine by means of a docking and separation device. According to the method of using the rocket before the separation of the march and combat stages include a flight control system and guidance on the target march stage. After the separation of the stages, the solid propellant engine of the march stage is started.

Known anti-aircraft missile according to the patent of the Russian Federation No. 2235281, a prototype that contains a marching degree and a combat stage with solid-fuel engines. Disadvantage: such missiles are applicable as short-range anti-aircraft guided missiles due to the insufficient power supply of the march (lower stage).

Disadvantages: short range, low flight speed. In addition, the control of the missile and its guidance on the target is very difficult, because the warhead contains only a solid fuel engine, the regulation of which is difficult. The control system is included before the separation of the march and combat stages. Maneuvering at supersonic speeds is technically difficult.

The task of creating the invention: improving the technical characteristics of the rocket, flight speed and increasing range and altitude.

The solution of these problems was achieved in a multi-stage anti-aircraft missile containing at least two rocket stages with at least one rocket engine of solid fuel at the lower stage, so that controlled aerodynamic rudders and wings and at least one rocket are installed on the upper stage solid fuel engine, solid fuel accelerators with solid fuel rocket engines are connected to the lower rocket stage parallel to its axis. The number of aerodynamic rudders corresponds to the number of solid fuel boosters, and they are each placed against the corresponding solid fuel accelerator.

Solid fuel boosters are capable of undocking in flight, for example, are connected to the lower rocket stage using pyro-bolts.

The invention is illustrated in figure 1 ... 2, where:

figure 1 shows a diagram of an anti-aircraft missile,

figure 2 shows a section along aa.

Multistage anti-aircraft missile (figure 1) may contain at least two missile stages. In the following, the description is made on the example of a two-stage rocket, but three or four rocket stages can be used, for example, to shoot down targets in space.

A multi-stage anti-aircraft missile (FIGS. 1 and 2) contains two missile stages: the lower (first) 1 and upper (second) 2, connected by a connecting farm 3, the head of the rocket 4, in which an explosive device 5 with a fuse 6. is installed. stage 1 parallel to its axis are attached solid fuel boosters 7 with solid propellant rocket engines 8, rotary aerodynamic rudders 9 with actuators 10 (figure 2) and two or four wings 11 are mounted on the upper rocket stage 2. It is preferable to use four rotary aerodynamic their booster 9 and place them on solid boosters 7. It will increase the efficiency of management in the initial part of the flight path of antiaircraft missiles and reduce its aerodynamic drag in the dense layers of the atmosphere. At least one solid fuel rocket engine 12 comprising a combustion chamber 13 with a fuel charge and a jet nozzle 14 is installed inside the lower rocket stage 1. Inside the upper rocket stage 2 there is a solid fuel rocket engine 15 containing a combustion chamber 16 and a jet nozzle 17 The solid propellant rocket engines 8 also include combustion chambers 18 and a jet nozzle 19.

Solid fuel boosters 7 are connected to the rocket block of the lower stage 1 with the possibility of undocking in flight, for example, using pyro-bolts 20. On the upper rocket stage 2 there are four control nozzles 21, to which gas ducts 22 with flow controllers 23, installed in them.

The rocket has a control unit 24 and heading sensors: a magnetometer 25 and an accelerometer 26 installed in the upper stage 2. The control unit 21 is connected by electrical connections 24 to the drives 10, rocket engines of solid fuel 12, 8 and 17, flow controllers 23, and also with a fuse 7 and with course sensors 22 and 23.

When starting the propulsion system from the control unit 21, the signal is simultaneously supplied to the solid fuel rocket engines 8 and 12. The solid fuel in the solid fuel rocket engines 8 and 12 ignites, and the anti-aircraft missile starts almost instantly.

After the development of solid fuel, a signal is applied to pyro-bolts 20, and solid fuel accelerators 7 are discarded. In addition to the fact that the flight weight of the rocket is reduced, there are four false targets that mislead the attacked enemy.

Then the solid fuel rocket engine (engines) 15 of the second rocket stage 2 is launched. Control during flight in the initial section of the trajectory and at the final is carried out by the control unit 24, depending on the readings of the sensors: magnetometer 26 and accelerometer 27 with rotary aerodynamic rudders 9 using drives 10. Wings 11 provide stabilization of the flight of an anti-aircraft missile in the atmosphere at an altitude of up to 10,000 m. When flying at a higher altitude, it is used to control the missile in the following way: open the corresponding regulator 23, and part of the combustion products from the combustion chamber 15 is supplied to the corresponding nozzle 21 or two nozzles 21 at the same time. Anti-aircraft missile deviates in the direction opposite to the location of the involved nozzles 21.

Placing control unit 24 in the upper rocket stage 2 made it possible to control all rocket stages, including solid fuel boosters, with the help of a single control block of solid fuel rocket engines.

The application of the invention allowed:

1. Significantly increase the flight range of an anti-aircraft missile with its identical launch weight due to the use of solid fuel rocket engines for all rocket stages and for solid fuel boosters.

2. To optimize the launch weight of the rocket through the use of a control system installed only on the upper rocket stage.

3. To ensure good controllability of the rocket both in the initial part of the trajectory and in the final one by installing rotary aerodynamic rudders on the upper stage of the anti-aircraft missile and control nozzles on the upper missile stage.

Claims (3)

1. A multi-stage anti-aircraft missile containing at least two missile stages with at least one solid fuel rocket engine at the lower stage, characterized in that the upper stage is equipped with controlled aerodynamic rudders and wings and at least one solid rocket engine fuel, and solid fuel boosters with rocket engines of solid fuel are attached to the lower rocket stage parallel to its axis. 2. A multi-stage anti-aircraft missile according to claim 1, characterized in that the aerodynamic rudders are each placed against the corresponding solid fuel accelerator and their number corresponds to the number of solid fuel accelerators. 3. A multi-stage anti-aircraft missile according to claim 1 or 2, characterized in that the solid fuel boosters are capable of undocking in flight, for example, by connecting them to the lower missile stage using pyro-bolts.

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