RU2284455C1 - Radio-controlled missile - Google Patents

Abstract

FIELD: armament.

SUBSTANCE: the radio-controlled missile has a separating engine, sustainer stage with the control equipment connected to the antenna device in the form of a sustainer antenna positioned on the rear end face of the sustainer stage and two start antennas. The aft part of the sustainer stage with the sustainer antenna is positioned in the cavity made on the front end face of the engine. The start antennas are positioned on the lateral surface of the sustainer stage. The antenna device is provided with a waveguide switch having outgoing arms, one of which is connected to the input of the control equipment, and the others - to the antennas provided with movable dampers.

EFFECT: enhanced reliability of the radio-controlled missile and reduced signal distortion.

2 dwg

Description

The alleged invention relates to the field of armament and can be used in small-sized radio-controlled missile systems.

Known radio-controlled anti-aircraft missile, selected as a prototype, containing a detachable rocket engine, a marching stage with a transmitter and receiver of radio commands, and an antenna device made of two parts: a marching antenna with a waveguide located in the marching stage with access to its rear end, and the launch parts made in the form of two antennas placed on the separation mechanism in front of the engine. Starting antennas are connected via waveguides to a repeater docked with the output of the marching antenna (Patent of the Russian Federation No. 2184343, IPC F 42 V 15/10).

The disadvantage of such a device are:

- the sequential arrangement of the mid-flight stage, the separation mechanism and the engine, which leads to a large length of the launch stage of the rocket and, accordingly, to its low stiffness and the limitation of available lateral overloads;

- the repeater distorts the signal due to its amplification;

- in the event of a marching antenna failure, the rocket becomes uncontrollable.

The objective of the present invention are:

- improving the reliability of a radio-controlled rocket by increasing the rigidity of the rocket;

- improving the reliability of the antenna device.

The solution to this problem lies in the fact that in the known radio-controlled rocket containing a detachable engine, the march stage with control equipment connected to the antenna device in the form of a march antenna located at the rear end of the march stage, and two launch antennas, the aft part of the march stage with march the antenna is placed in a cavity made at the front end of the engine, the starting antennas are placed on the side surface of the march stage, while the antenna device is equipped with a waveguide switch having outgoing shoulders, one of which is connected to the input of the control equipment, and the rest to the antennas, and equipped with movable dampers made of electrically conductive material.

The position of the dampers is determined from the condition of least attenuation of the radio signal in the antenna device. The dampers are moved by a power drive of any known design: electromagnetic, pyrotechnic, mechanical, etc. Switching can be performed by the signal that the engine has finished working, for example, from an inertial contactor, on command from ground equipment, to separate the engine, if any.

The technical result of the invention is that:

- reduced the length of the launch stage of the rocket due to the placement of the aft of the march stage in the engine cavity;

- reduced signal distortion due to the absence of a repeater;

- the waveguide switch provides the output of the starting branches directly through the wall of the march stage housing and thereby allows you to take advantage of the telescopic scheme for missiles with the antenna-waveguide system in the aft part and ensure duplication of the antenna-waveguide tract after engine separation.

Figure 1 and 2 shows the design of a radio-controlled missile, where:

1 - detachable engine;

2 - march stage;

3 - engine cavity;

4 - control equipment;

5 - waveguide switch;

6 - shoulder waveguide switch;

7 - power drive;

8 - shutter start antenna;

9 - damper marching antenna;

10 - starting antenna;

11 - marching antenna;

12 - aft of the march stage.

The device and principle of operation of a radio-controlled rocket are as follows.

The radio-controlled missile consists of a marching stage 2 installed by the aft 12 into the cavity 3 at the front end of the detachable engine 1.

At the launch site, before the engine is separated, the radio signal is received by the rocket control equipment 4 from the ground equipment through the start antennas 10 and shoulders 6 of the waveguide switch 5, and the radio signal is transmitted from the rocket to the ground equipment along the same path. At the same time, in order to avoid energy losses from the radiation of the marching antenna 11, the channel of the marching antenna waveguide is closed by a shutter 9, which is actuated by the power actuator 7. After the engine is separated by the power drive, the shutter 9 opens, closing the channel of the marching antenna waveguide, and the shutters 8 blocking the waveguide channels of the start antennas are closed antenna device, which eliminates the loss of electromagnetic energy by radiation of the starting antennas of the antenna device. Receiving and transmitting a radio signal from a rocket occurs through the marching antenna and the corresponding arm of the switch. In case of violation of the operation mode of any of the antennas of the antenna device, the electromagnetic energy flows can be switched into serviceable antennas by shutters, thereby duplicating the antenna-waveguide path of the device.

Thus, the invention provides:

- improving the reliability of a radio-controlled rocket by reducing the length of the rocket when placing the aft part of the marching stage in the engine cavity, since the rigidity of the rocket increases;

- improving the reliability of the antenna device by eliminating the repeater, which eliminates signal distortion, and the use of a waveguide switch, which allows, if necessary, to duplicate the antenna-waveguide path.

Claims (1)

A radio-controlled rocket containing a detachable engine, a marching stage with control equipment connected to an antenna device in the form of a marching antenna located at the rear end of the marching stage and two launch antennas, characterized in that the aft part of the marching stage with the marching antenna is placed in a cavity made on the front end of the engine, the starting antennas are located on the side surface of the march stage, while the antenna device is equipped with a waveguide switch having outgoing shoulders, one of which s is connected to the input of the control equipment, and the others - to the antennas provided with movable dampers, made of an electrically conductive material.

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