RU2189003C2 - Radio-controlled anti-aircraft missile - Google Patents

Abstract

FIELD: rocketry, applicable in anti-aircraft guided missile systems with a radio control system. SUBSTANCE: the radio-controlled antiaircraft missile has a booster engine, sustainer stage with functional units and a radio sensor with an antenna device and a power source, the booster engine is made separable, and the antenna device - in the form of three branches. One of the branches is installed in the aft part of the sustainer stage with an output to the rear end connected to one of the inputs of the radio sensor. The other two branches of the antenna device are installed diametrically opposite in the outer lugs of the cone positioned between the sustainer stage and the engine and closing the front part of the booster engine, and connected via feeder systems of the same length to the other input of the radio sensor by means of a series- connected microsleeker tee and a switching microwave-diode. The radio sensor power source is connected to the switching microwave-diode-conductor mechanically linked with the separable booster engine. EFFECT: provided reliable control of the missible at hypersonic speeds in the conditions of action on the control channel of the body of the booster engine and its flame, as well as in the conditions of radio interference in the boost phase of the missile flight. 2 dwg

Description

 The invention relates to the field of rocketry and can be used in anti-aircraft systems with a radio command control system.

 Known radio-controlled anti-aircraft missile complex "Crotal" containing a marching stage with an inseparable starting engine with stabilizers and antenna devices on them, while the marching stage contains a non-contact fuse, a converter, a pitch and yaw control unit, a fuse cocking mechanism, an autopilot, a warhead, a transmitter , radio receiver and control mechanism [1].

This design of a radio-controlled anti-aircraft missile, with all its advantages, has a number of significant drawbacks, namely:
- the inability to separate the starting engine after the end of its operation, which significantly impairs the ballistic characteristics of the rocket, limiting its use at hypersonic speeds;
- a high level of signal reception of the side and rear lobes of the antenna pattern due to the lack of special measures to suppress side lobes, due to the small size of the antenna device located on the stabilizer.

 The objective of the invention is the provision of reliable control of the rocket at hypersonic speeds under conditions of exposure to the control channel of the housing of the starting engine and its torch, as well as in conditions of radio interference on the marching portion of the flight path of the rocket.

 This task is achieved by the fact that in a radio-controlled anti-aircraft missile containing a starting engine, a marching stage with functional units and a receiver of radio commands with an antenna device and a power source, the starting engine is detachable, and the antenna device is in the form of three branches, one of which is installed inside the aft part of the march stage with access to the rear end and connected to one of the inputs of the receiver of the radio commands, the other two branches of the antenna device are diametrically opposed to the external tides of a fairing located between the march stage and the engine and covering the front of the starting engine, and are connected by feeder systems of the same length to the other input of the receiver of the radio commands through a series-connected micro-slide tee and a switching microwave diode, while the power source of the receiver of the radio commands is connected to a switching microwave diode a conductor mechanically connected to a detachable starting engine.

 The essence of the invention lies in the fact that this design of a radio-controlled anti-aircraft missile provides stable reception of radio control commands at the launch site of a rocket’s flight under the influence of the engine body and nozzle torch by two antennas mounted diametrically opposite on the outer part of the fairing, which ensures the propagation of radio waves along the longitudinal axis of the rocket due to the same length of feeder systems and micro-skid tee. The radio waves from the ground tracking station arrive at the input of the receiver of the rocket radio commands in phase, which ensures their addition, and when the axis of the rocket is rotated relative to the radio wave propagation line, one of the antennas shades and the radio signals are confidently received by the second antenna.

In the proposed FIG. 1, 2 shows the design of a radio-controlled anti-aircraft missile, where:
1 - detachable starting engine;
2 - march stage;
3 - receiver radio commands;
4 - antenna device;
5 - aft of the march stage;
6 - the rear end of the march stage;
7 - fairing;
8 - feeder system of the same length;
9 - micro skid tee;
10 - switching microwave diode;
11 - conductor;
12 - input receiver radio commands;
13 - branches of the antenna device;
14 - the front of the engine;
15 - diametrical tides of the fairing;
16 - another input of the receiver of radio commands;
17 - power source (battery).

The device and principle of operation of a radio-controlled anti-aircraft missile is as follows:
a radio-controlled rocket consists of a marching stage 2 and a detachable starting engine 1, interconnected by a stage separation mechanism and an installed fairing 7 that covers the separation mechanism and the front part 14 of the starting engine 1. In the marching stage 2, in addition to the warhead and functional units in the aft 5 an on-board receiver of radio commands 3 with two inputs 12, 16 and an antenna device 4 are installed, while the antenna device 4 consists of three branches 13 (three antennas), two of which are installed in diameter tides 15 fairing 7, and the third branch inside the aft 5 march stage 2 with access to the rear end 6 and connected to the first input 12 of the control equipment 3. In this case, the other two branches 13 of the antenna device 4 are connected by feeder systems 8 of the same length with another input 16 receiver radio commands 3 through a series-connected micro skid tee 9 and a switching microwave diode 10.

 In this case, the power source 17 of the receiver of the radio commands 3 is connected to a switching microwave diode 10 by a conductor 11 mechanically connected to a detachable starting engine 1.

 When the Start button is pressed in the rocket, the power source 17 (battery) is turned on, which is installed in the receiver of the radio commands of the rocket march stage, which goes into mode for one second, while the radio receiver, steering gear, gyroscope and microwave switching are powered on (turned on) -diode, which provides zero resistance of two antenna-feeder systems. The missile at the launch site of the flight, receiving radio signals from the ground guidance station, is controlled by two branches of the antenna device located in the tides of the fairing mounted on the rocket.

 When the longitudinal axis of the missile is located along the propagation line of radio waves due to feeder systems of the same length and a micro-skid tee with a series-connected switching microwave diode, the radio waves arrive at the input of the radio command receiver in phase, which ensures their addition, i.e., signal amplification. When rocket maneuvers, i.e. when turning the longitudinal axis of the rocket relative to the propagation line of radio waves, one of the branches of the antenna device is obscured by the body of the rocket engine, but the radio signals are confidently received by the second branch of the antenna device.

 Provided the longitudinal axis of the rocket is located along the propagation line of radio waves with feeder devices of different lengths, the radio waves arrive at the input of the radio command receiver in antiphase, compensating each other, which will lead to loss of control of the rocket. To ensure the broadcast of the radio signal from the micro-skid tee to the input of the radio command receiver, a microwave switch diode is installed, to which the unlocking voltage is supplied from the radio command receiver through an electric circuit in the form of a conductor mechanically connected to a detachable starting engine, while the resistance of the switching diode at a high frequency is minimal.

 With the complete combustion of the powder charge, the starting engine is separated from the sustainer stage together with the antenna device mounted on the fairing, while the electric circuit in the form of a conductor mechanically connected to the starting engine is broken, the voltage is removed from the microwave switching diode. The resistance of the switching microwave diode in this case becomes infinitely high in frequency, which prevents the influence of the remaining part of the feeder systems of the two broken branches on the reception of signals by the antenna installed inside the aft part of the march stage, which continues a controlled flight until the target is hit.

 The location of the antenna device inside the aft part of the marching stage with access to the rear end excludes kinetic heating and destruction of the antenna, while the aerodynamic characteristics of the marching stage of the rocket are improved, in addition, the back and side lobes of the antenna pattern due to its additional screening by the body of the marching stage, which improves the noise immunity of the communication channel of the ground control equipment with the rocket march stage.

Sources of information
1. Journal "Soldat und Technik", 1970, 10, s. 562-563, Bild 5 - prototype.

Claims (1)

 A radio-controlled anti-aircraft missile containing a launch engine, a marching stage with functional units and a radio command receiver with an antenna device and a power source, characterized in that the launch engine is detachable, and the antenna device is in the form of three branches, one of which is installed inside the aft of the marching stage with access to the rear end and connected to one of the inputs of the receiver of the radio commands, the other two branches of the antenna device are diametrically opposed in the outer tides of the streamline A la located between the march stage and the engine and covering the front of the starting engine, and connected by feeder systems of the same length to the other input of the radio command receiver via serially connected micro-slide tee and a microwave switching diode, while the power supply of the radio command receiver is connected to the switching microwave diode by a conductor mechanically coupled to a detachable starting engine.

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