RU2561655C2 - Space vehicle - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: space vehicle contains radar, commands and control unit, solar panels, used also for the special-purpose module power supply. The special-purpose module in its turn has a propulsion plant, chemical current source, appropriate service and special devices, and special system. After the special-purpose module separation the power supply from the solar panels is disconnected, and the special-purpose module switches to the power supply from the chemical current source. In case of the attack the space vehicle splits to the decoy simulating the attack target, and the special-purpose module.

EFFECT: special-purpose module protection against defeat during the attack, and assurance of the set objectives execution.

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Description

The invention relates to the field of mechanics, in particular to devices and methods for protecting aircraft during an attack.

A spacecraft (SC), divided in the event of the discovery of hostile actions in space in relation to the SC from other objects.

There are various methods and devices of protection based on maneuver in space, the use of false targets (LC) and plasma formations.

As a prototype, thermal and other traps are considered, separated from aircraft (helicopters) when attacking them, false targets of space objects and warheads.

Thus, the attacking object is redirected to the trap, which in this case is given the properties, as a rule, of the radiation of the engine, the object (sometimes other elements) that mimic the characteristics of the target of the attack.

In outer space, an attack and defeat of an object are carried out after a preliminary assessment of its radiative-reflective characteristics - weakly or strongly fluctuating body, mass, presence, type and orientation of solar batteries, other characteristic elements.

, где:Detection, identification, exit of the attacking apparatus to the target (capture by means of detection) is determined by the ratio $$\overline{R}=k_{\mathrm{one}}{k}_2{k}_3\overline{R_0}$$

where:

- средняя дальность обнаружения; $$\overline{R}$$

- average detection range;

k_one, k₂, k₃ - coefficients characterizing the devices, the purpose and the environment.

We take a value from statistical data (V. A. Gorbunov. The effectiveness of target detection. - M., 1980):

км. $$\overline{R}=120$$

km

The purpose of the invention is to, by means of a false object, in this case a case simulating an object of attack, remove from target an attack the target module located in the body of the main (false) space object, and in this configuration the space object functions until the fact is recorded detection and approximation for inspection or destruction.

The target module is fixed in the spacecraft body with the help of three or four slides inserted into the space guide rails of the spacecraft and spring-loaded stops. After the engine is turned on, the target block on the slide along the guides leaves the spacecraft body.

The device contains (figure 1, 2, 3):

spacecraft body 1, solar panels 2, radar survey locator 3, target module that performs the functions of communication, reconnaissance or combat unit 4 with appropriate service and special equipment and a chemical power source, control unit and propulsion system 5, slide on the target module 6 body guides on the body of the spacecraft 7, locking stops 8, the block receiving commands and control 9.

The device operates as follows. The object 4 is installed in the housing of the spacecraft 1 on the slide 6 in the guides 7 of the device 1, is fixed by stops (for example, ball) 8.

After registration from the attacked object of the fact of a possible attack and the fact of approaching, the response time is calculated, for example, by the speed of approach of the target with the attacked object V _c

V _c = V _c · cosg _c + V _H cosg _H , where:

g _H - heading angle of the observer (attacked spacecraft);

g _C - heading angle of the attacking KO,

after which, according to signals from the Earth or from the locator 3, a command is sent to the issuing teams for separation 9, the engine 5 of the target module is started and at the same time the electrical connections 4 are separated, and it is separated from the spacecraft body 1.

Thus, according to the accepted (available) attacking object, the parameters of the attacking object can affect the spacecraft (false object) 1, and the target object 4, having onboard a control system, an onboard current source, will continue to fulfill the tasks assigned to it.

The technical result of the invention is the protection of the target module from defeat during the attack and ensuring that it fulfills the target (s) tasks (s).

Information sources

1. Methods of development of scientific and economic missile and space systems. - M.: Mechanical Engineering, 1995.

2. V.A. Hunchbacks. The effectiveness of target detection - M., 1980.

3. S.A. Vakin, A.N. Shustov. Fundamentals of radio countermeasures. - M., 1968.

4. V.G. Nebabin, V.V. Sergeev. Methods and techniques of radar recognition. - M., 1968.

5. V.D. Giants and others. Radio engineering systems in rocket technology. MO, M., 1974.

6. Patent No. 3860927 class 343-48 (US).

7. Patent No. 3283328 CL 343-70 (US).

8. Patent No. 4414339 G21F 1/10.

9. Patent No. 4865328 F41J 9/08 (US).

10. Patent No. 131927 U1, RU.

11. Patents of Great Britain No. 2134740 NKI-N4D.

Claims (1)

A spacecraft containing a housing, solar panels with a power supply system from them, a radar survey locator, receiving and transmitting command units, characterized in that a target module is provided inside the spacecraft housing, equipped with a propulsion system, a chemical current source, a unit for receiving commands for separation from the spacecraft and the propulsion system control unit, the target module housing has a slide located in the guides of the spacecraft housing and fixed in them along springing stops, the chemical current source blocks and receiving control commands and target propulsion module electrically connected to the power supply system of the spacecraft by solar panels and the receiving unit and transmitting spacecraft commands.

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