RU2564457C1 - Spacecraft separation system - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to space engineering, particularly, to spacecraft separation devices. Proposed system comprises split retainer arranged between bearing structure with hole and spacecraft with hole with ledges for locking of the thrust. Besides, it has mechanical locks with rod and washer and hole displaced relative to rod axis. Locking link retains the link with recess of pivot pin.

EFFECT: reliable separation of payload.

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Description

The invention relates to space technology, and in particular to a device for separating a spacecraft.

A device for separating a spacecraft according to patent RU No. 2453481 is a prototype, comprising a releasable holding device mounted between the supporting structure and the spacecraft and including mechanical locks, each of which contains a rod, threaded end mounted on the spacecraft, and the other end connected with retaining link of a mechanical lock interacting with the locking link.

The disadvantage of the prototype is its limited operational capabilities due to restrictions on the mass of the output payload, which reduces the reliability of the device.

The objective of the invention is to develop a technical device that provides reliable separation of payloads with wide ranges of mass characteristics without increasing the size and mass of mechanical locks.

The problem is solved by a spacecraft separation device containing a releasable holding device mounted between the supporting structure and the spacecraft and including mechanical locks, each of which contains a rod, threaded end mounted on the spacecraft, and the other end connected to the holding link of the mechanical lock interacting with a locking link, as well as the fact that the end of the shaft of the mechanical lock on the side of the holding link is provided with a stop, while one of the end the stop surfaces interacts with the internal bevel of the opening of the base of the mechanical lock case, and the other with the recess made in the axis of rotation of the retaining link, while the holes of the mechanical lock, supporting structure and spacecraft are offset from the axis of the rod, providing passage of the stop during separation, which in the final position, its end surfaces are fixed by protrusions made in the hole of the spacecraft, preventing the rod from falling out, while cutting The washer and nut are placed at the other end of the rod, interacting movably with their spherical surfaces during separation, in the place of their mating, and the washer is movably supported on the spacecraft body. The invention is illustrated by drawings:

- figure 1 shows a General view of the separation device;

- figure 2 shows the interaction of the core of the mechanical lock with the corresponding structural elements (remote element A from figure 1);

- figure 3 shows the interaction of the locking and holding links (remote element B from figure 1);

- figure 4 shows the rod in the open position of the mechanical lock, where:

1. spacecraft;

2. a detachable holding device;

3. supporting structure;

4. mechanical lock;

5. the rod;

6. holding link;

7. fixing link;

8. emphasis;

9. end surface of the stop;

10. end surface of the stop;

11. the inner bevel of the hole;

12. a hole in the base of the mechanical lock housing;

13. notch;

14. axis of rotation of the holding link;

15. hole of the supporting structure;

16. the opening of the spacecraft;

17. protrusion;

18. washer;

19. nut;

20. pyrochek;

21. pusher;

22. sector with an external cylindrical surface;

23. sector with an inner cylindrical surface;

24. spring;

25. pusher.

In the proposed device, the separation of the spacecraft 1, containing a detachable holding device 2, mounted between the supporting structure 3 and the spacecraft 1 and including mechanical locks 4, each of which contains a rod 5, a threaded end mounted on the spacecraft 1, and connected with the other end with the retaining link 6 of the mechanical lock 4, interacting with the locking link 7 (Fig. 1).

In addition, the end of the shaft 5 of the mechanical lock 4 on the side of the holding link 6 is provided with a stop 8 with end surfaces 9, 10, one of which interacts with the inner bevel 11 of the opening of the base of the housing of the mechanical lock 12, and the other with a recess 13 made in the axis of rotation of the holding link 14.

The opening of the base of the housing of the mechanical lock 12, the hole of the supporting structure 15 and the hole of the spacecraft 16 are offset from the axis of the rod 5, which ensures the passage of the stop 8 during separation, which in the end position is fixed by its end surfaces 9, 10 with protrusions 17 made in the hole of the spacecraft 16, preventing the loss of the rod 5 (Fig. 2).

A washer 18 and a nut 19 are placed on the threaded end of the rod 5, interacting movably with their spherical surfaces during separation, in the place of their mating, and the washer 18 is movably supported on the spacecraft 1 body (Fig. 2, 3).

The separation device of the spacecraft operates as follows.

On command from the control system, pyrochets 20 are simultaneously triggered, the rods are released, and under the action of the pushers 21, the locking links 7 rotate on their axes (Fig. 1).

The sector with the outer cylindrical surface 22 of the locking link 7 disengages on the cylindrical surfaces from the sector with the inner cylindrical surface 23 of the holding link 6, while the stop 8 of the shaft 5 of the mechanical lock 4 slides along the inner bevel of the hole 11 in the base of the housing of the mechanical lock 4, while acting on the recess 13, made in the axis of rotation of the retaining link 14. Together with this, the rod 5 with the nut 19 are rotated on the spherical surface of the washer 18, while the washer 18 is slightly changed is pressed along the body of the spacecraft 1. The spring 24 is unclenched and the rod 5 is pulled to the spacecraft 1. In the final position, the rod 5 is fixed by the protrusions 17 made in the hole of the spacecraft 16, and the spacecraft 1 is separated from the supporting structure 3 by the action of pushers 25 (Fig. . 1, 2, 3, 4).

The claimed device will allow for reliable separation of payloads with wide ranges of mass characteristics without increasing the size and mass of mechanical locks.

Claims (1)

A spacecraft separation device comprising a releasable holding device mounted between the supporting structure and the spacecraft and including mechanical locks, each of which contains a rod, threaded end mounted on the spacecraft, and the other end connected to the holding link of the mechanical lock interacting with the fixing link, characterized in that the end of the shaft of the mechanical lock on the side of the holding link is provided with a stop, while one of the end surfaces the stop interacts with the internal bevel of the opening of the base of the mechanical lock case, and the other with the recess made in the axis of rotation of the retaining link, while the holes of the mechanical lock, supporting structure and spacecraft are offset from the axis of the rod, ensuring passage of the stop during separation, which in the final position, its end surfaces are fixed by protrusions made in the opening of the spacecraft, preventing the rod from falling out, while at the threaded end A rod and a nut are placed on the rod, interacting movably, in the place of their conjugation with their spherical surfaces during separation, and the washer is movably supported on the spacecraft body.

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