RU2373486C1 - Radio-guided antiaircraft missile with telemetry system for registration of missile main parametres - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: invention relates to rocketry and can be used in various antiaircraft complexes with radio control system. Proposed missile comprises detachable launching stage, sustainer stage with functional units, control hardware, radio signal receiver, antenna and power supply including separation conductor. Sustainer stage tail part incorporates onboard telemetry transmitting module. The latter consists of signal controller ADC and radio transmitter with phase-pulse modulation of carrier frequency connected, via switching device, with strip antenna of sustainer stage and, via matching device, with launching stage antenna. Note here that control input of aforesaid switching device is connected with separation conductor.

EFFECT: multi-channel data transfer, data registration at surface fire control station.

Description

The invention relates to the field of rocketry and can be used in various complexes with a radio command control system.

Known radio-controlled anti-aircraft missile (Russian patent No. 2189003 dated 09/10/2002, Bull. No. 25), containing a starting engine, a marching stage with functional blocks and a radio receiver 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 of the march stage with access to the rear end and connected to one of the inputs of the radio command receiver, the other two branches of the antenna device are diametrically opposed in external tides of the 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 of microstrip tee and a switching microwave diode, while the power source of the receiver of the radio commands is connected to a switching microwave a conductor diode mechanically connected to a detachable starting motor.

This design of a radio-controlled anti-aircraft missile, with all its advantages, namely: reliable control of the rocket at supersonic speeds under conditions of exposure to the control channel of the engine body and its torch, as well as in conditions of radio interference on the marching portion of the rocket’s flight path, has a significant drawback, namely: it does not provide information to the ground control reception point about the state of the functioning parameters of the main functional blocks and components of the rocket in flight.

The objective of the invention is the provision of multichannel information transfer and its registration at the ground receiving point during the launch of military missiles in the process of testing and testing in real time.

This task is achieved by the fact that in the radio-controlled anti-aircraft missile with a telemetric registration system for its main parameters, containing a detachable launch stage with functional units, control equipment, a radio receiver with an antenna device and a power source with a tear-off conductor, according to the invention, an onboard telemetry is installed in the aft part of the march stage transmitting module (BTPM), consisting of a series-connected analog-to-digital Converter, a signal controller and a nogolithic radio transmitter with phase-frequency modulation of the carrier frequency connected through a switching device to a marching stripe antenna and through a matching device to the launch stage antennas, while the control input of the switching device is connected to a tear-off conductor, the inputs of the analog-to-digital converter are connected to the outputs of functional units and equipment control, the control input of a multi-liter radio transmitter with phase-pulse modulation of the carrier frequency is connected to one of the outputs a control equipment, the output of the radio command receiver with the antenna device is connected to the input of the control equipment, the second input of which is connected by a digital communication channel to the ground control equipment.

The essence of the invention lies in the fact that this design of a radio-controlled anti-aircraft missile provides a stable multi-channel transmission of information about the functioning parameters of combat missile units both on the launch and on the march sections of the missile’s flight due to the introduction of the BTMP rocket consisting of a signal controller connected in series with an analog-to-digital converter of the recorded parameters, forming information packets in binary code, and a multi-liter radio transmitter with phase-frequency modulation of the carrier frequency, connected through a switching device with a strip antenna of the marching stage and antennas of the starting stage with the matching device installed on the separation mechanism of the starting engine. At the same time, the switching frequencies of the telemetric transmitting module are switched by a signal from the control equipment, which is generated at the rocket address received through the information channel with the ground receiving control center, and to increase the reliability of the transmitted information and protection from interference and noise caused by the influence of the starting stage, information packets are transmitted in a cyclic error-correcting code with retransmission of important parameters with a time offset and their subsequent comparison and highlighted using ground-based equipment when processing the most reliable data packet both during a single missile launch and in multiple launching by switching the frequency of a monolithic radio transmitter according to the signals of the control equipment.

The invention is illustrated by drawings. Figure 1 shows the design of the rocket, and figure 2 is a functional diagram of a radio-controlled rocket with a telemetric registration system for its main parameters, where:

1 - starting stage with a separation mechanism;

2 - march stage;

3 - functional blocks (FB);

4 - control equipment (AU);

5 - receiver radio commands with an antenna device (PRK);

6 - power source (battery) (B);

7 - tear-off conductor;

8 - aft of the march stage;

9 - on-board telemetry transmitting module (BTPM);

10 - analog-to-digital Converter (ADC);

11 - signal controller (SC);

12 - multi-liter radio transmitter with phase-pulse modulation of the carrier frequency (RP);

13 - switching device (CC);

14 - strip antenna marching stage;

15 - coordination device (CS);

16 - antenna launch stage;

17 - ground receiving point (NPP);

18 - place of joining of steps;

19 - digital communication channel;

20 - ground control equipment (NAU).

The device and principle of operation of a radio-controlled anti-aircraft missile with a telemetric registration system for its main parameters is (see Fig. 1, 2) that the rocket consists of a detachable launch stage 1, march stage 2 with functional blocks 3, control equipment 4, receiver radio commands with an antenna device 5 and a power source 6. In the aft part of the march stage 8, a BTMP 9 is installed, consisting of a series-connected analog-to-digital converter 10, a signal controller 11, a multi-channel radio transmission a phase-modulated carrier 12 connected through a switching device 13 with a strip antenna 14 of the marching stage 2 and through a matching device 15 with antennas of the starting stage 16. The control input of the switching device 13 is connected to a tear-off conductor 7, and the inputs of the analog-to-digital converter 10 are connected to the outputs of the functional blocks 3 and control equipment 4. In this case, the control input of a multi-liter radio transmitter with phase-pulse modulation of the carrier frequency 12 is connected to one of the outputs of the control antenna 4, the output of the radio command receiver with the antenna device 5 is connected to the input of the control equipment 4, the second input of which is connected by a digital communication channel 19 to the ground control equipment 20. At the time of launch, before the rocket leaves the launch container from the ground control equipment 20 via a digital communication channel 19 to the control equipment 4 receives digital information, including the address of the rocket, while in the control equipment 4 the address of the rocket is stored and an analog signal is generated, which is transmitted to an input input of a multi-liter transmitter with phase-pulse modulation of the carrier frequency 12, in which, depending on the magnitude of the control signal, the carrier frequency of the radio transmitter is switched. When the second missile is launched, the second address of the second missile is received via the digital communication channel 19, while the second missile control equipment 4 remembers the second address and generates an analog signal of the second missile and also transfers it to the input of a multi-liter radio transmitter with phase-pulse modulation of the carrier frequency 12 of the second missile. Thus, one or more missiles in the process of aiming at a target emit information at different letter frequencies. From the outputs of the functional blocks 3 and control equipment 4 of the rocket, the signals in analog form are fed to an analog-to-digital converter 10, where they are converted into binary code supplied to a signal controller 11, forming information packets that are sequentially fed to a multi-liter radio transmitter with phase-modulated carrier frequency 12 connected by a switching device 13 through a matching device 15 with antennas of the starting stage 16 on the separation mechanism of the starting stage 1 and the strip antenna 14 march of the second stage 2 and are emitted in the direction of the ground receiving station 17. The switching device 13 is controlled by removing power from the battery 6 due to the breakaway of the tear-off conductor 7, mechanically connected to the separation mechanism, when the starting stage 1 is separated from the sustainer stage 2 at the junction of the stages 18.

The telemetry system for registering the main parameters of a radio-controlled anti-aircraft missile works as follows: at the moment the rocket is launched and the power supply enters the mode, the missile address code is transmitted to the on-board equipment of the missile, which is also the code for setting the letter frequency of the BTMP . The rocket address number and the letter frequency number of the registration system are synchronously stored on the rocket in the control equipment, while the radio command receiver responds only to “its” address and decodes only “its” message, and the BTMP radio transmitter emits the assigned letter frequency number. Thus, if there is a system of registration of several selective reception channels at the ground receiving station, “own” information is received from each missile, thereby ensuring noise-free reception of information from several missiles simultaneously. At the launch site of the flight of the rocket under the influence of the housing of the launch engine and the torch, reliable reception of signals during rocket maneuvers is ensured by taking the antennas installed on the separation mechanism of the launch engine beyond the marching stage.

When the starting engine is separated, a tear-off conductor is mechanically connected to the starting engine separation mechanism, as a result of which the output voltage is removed from the switching device of the antenna devices and the BTMP switches to the march stripe antenna. During the flight, the BTPM of each missile in the process of guidance at its own letter frequency emits information packets in binary code about each registered parameter. The information codes of each parameter are formed due to the fact that information from each block is transferred from the functional blocks of the rocket to the analog-to-digital converter and the signal controller connected in series, where it is converted into a digital binary code.

Thus, a digital sequence of codes is generated through the BTPM, the antenna system and the ground reception point of the registration system, in which information is received, processed and visualized in real time, which is invaluable for reliable analysis of test results and determination of the causes of ground failures equipment or the rocket itself.

Claims (1)

A radio-controlled anti-aircraft missile with a telemetric registration system for its main parameters, comprising a detachable launch stage, a march stage with functional blocks, control equipment, a radio command receiver with an antenna device and a power source with a tear-off conductor, characterized in that it is equipped with launch stage antennas and a marching strip antenna stages, while in the aft part of the march stage an onboard telemetry transmitting module is installed, consisting of a series connected analog-to-digital converter, signal controller and multi-liter radio transmitter with phase-pulse modulation of the carrier frequency connected through a switching device to a march stripe antenna and through a matching device to the antennas of the starting stage, while the control input of the switching device is connected to a tear-off conductor, the inputs of the analog-to-digital the transducer is connected to the outputs of the functional blocks and control equipment, the control input of the multi-liter radio transmitter with phase ulsnoy frequency modulated carrier is connected to one of the outputs of the control apparatus, the radio control receiver output to an antenna device connected to the input control apparatus, the second input of which is connected to a digital communication channel to the ground control equipment.

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