RU2167793C2 - Spacecraft solar battery - Google Patents

Abstract

FIELD: space engineering; spacecraft of various purposes. SUBSTANCE: solar battery includes frame, beam and upper and lower doors. Doors are secured on frame, beam and spacecraft case by means of pyro locks with pawls and are interconnected by means of retainers. Body of each pyro lock is additionally provided with pyro element independently engageable with pawl provided with second hole for additional axle. Articulated on lower door is latch whose one end is engageable with bracket rigidly secured on upper door and other end is engageable with end face of respective retainer. Pyro units are provided for securing the door stack to frame and beam, as well as for securing the frame and beam to spacecraft case. EFFECT: increased reliability of opening the solar battery doors, by approximately 100 times. 11 dwg

Description

 The invention relates to space technology and can be used on spacecraft (SC) for various purposes.

 The solar battery (SB) of the spacecraft developed by TsSKB in Samara is known, drawings 11f624 8700-0, a general view of which is shown in FIG. 1 prototype.

 In FIG. 2 is a cross-sectional view of a battery (section AA).

 In FIG. 3 shows a pyromedic tool in a section (BB).

 In FIG. 4 depicts a sash fixation element, and in FIG. 5 of the prototype depicts a solar battery in working (open position).

 A drive 2 is rigidly fixed on the spacecraft body 1 (Fig. 1), and a power frame 3 is attached to the output shaft 3. The spacecraft 4 is installed on the spacecraft body (Fig. 2), which, together with the area under the cowl, determines the configuration of the battery in the laid position.

 On the frame 3 and the beam 5 (Fig. 1) with the help of a hinged parallelogram 6 (Fig. 2), the lower flaps 7 and the upper flaps 8 are mounted, chased on one side by the latch 9 (Fig. 4 of the prototype), and on the other hand are connected by a hinge 10 , Frame 3 and beam 5 with pyro means 11 of FIG. 1 are fixed on the spacecraft body. Pyromedium 11 is a body 12, a dog 13, a torsion spring 14, a pyroelement 15 (for example, a pyro bolt), which presses frame 3 and beam 5 (Fig. 1) with a dog 13 to the spacecraft body 1. In the pyromedium case 12 (Fig. 3) and the dog 13 has a hole 16 under the main axis 17.

 By means of 11 (Fig. 2) of a similar design using the same pyroelements 15 (Fig. 3), the lower flaps 7 (Fig. 2) are attached to the frame 3 and beam 5 (Fig. 1) at six power points. A cam 18 (Fig. 4) is rigidly mounted on one of the hinges of the parallelogram 6 (Fig. 2), which abuts against a spring-loaded latch 9, which holds the shutters 7 and 8 in the locked position. Along the perimeter of each leaf 7 and 8, a net-sheet is tensioned, on which the photoelectric converters 19 are fixed (Fig. 5).

 Disclosure of SB occurs in the following sequence.

 After resetting the head fairing, a command is issued to activate the pyroelements 15 (Fig. 3) of the pyroelectric device 11. The pyroelement 15 is broken along the separation plane. The dog 13 torsion spring 14 is rotated in the hole 16 relative to the main axis 17.

 The connection between the frame 3, the beam 5 (Fig. 3) and the body of the spacecraft 1 (Fig. 1) is broken. Drive 2 diverts the SB panel from the spacecraft body 1 and stops. A command is issued to trigger the pyroelement 15 (FIG. 3) of the pyro means 11 (FIG. 2). The connection between the lower leaf 7, the frame 3 and the beam 5 (Fig. 1) is broken. Under the action of torsion springs installed in the axes Г (Fig. 2) of the articulated parallelogram 6, the shutters 7 and 8 begin plane-parallel movement in the axes of the articulated parallelogram 6. The cam 18 (Fig. 4) rigidly fixed on the hinge at a certain angle of rotation of the shutters 7 and 8 releases the spring-loaded latch 9, which, moving in the axial direction, strikes the sash 8 relative to the sash 7.

 The leaf 8 is rotated relative to the hinge 10, and the leaf 7 continues plane-parallel movement until it is fixed on the frame 3 (Fig. 1) and the beam 5. The leaf 8 (Fig. 4) is fixed in the hinge 10 with the leaf 7.

 Thus, all four wings open and lock, forming a single flat panel. Drive 2 (Fig. 1) rotates the panel to the optimal position relative to the Sun.

 The disadvantage of this design is the low reliability of the opening of the wings. The presence of a large number of pyroelements reduces the likelihood of a failure-free operation of the disclosure system.

To open one SB panel, it is necessary to operate 12 pyroelements (pyro-bolts). In accordance with the technical conditions for them
P _bolt = 0.99996, and for 12 P _systems = 0.99996 ¹² = 0.99952
This means approximately 1 failure per 1000 products.

 In addition, the axial displacement of the latch when the base holes are displaced in different flaps during their temperature deformations is prone to “biting”, which leads to non-opening of the flaps. The objective of the present invention is to increase the reliability of the opening of the valves of the SB through the introduction of duplication elements.

 The problem is solved in that in the case of each pyromedicine (lock) an additional pyroelement is installed, which interacts with the dog, with a swinging latch pivotally attached to the lower casement, abutting against the bracket with one end rigidly fixed to the upper casement, and the other interacting with the end of the latch.

In FIG. 6 shows a general view of the SB;
in FIG. 7 - cross section of the SB;
in FIG. 8 - fixation element of the upper and lower cusps;
in FIG. 9 depicts a pyro agent (lock) securing the lower shutter of the SB with a frame and beam on the spacecraft body;
in FIG. 10 shows the position of the working link after the operation of the main pyroelement (squib);
in FIG. 11 - the position of the working link after the operation of the additional pyroelement (pyro cartridge).

 The solar battery is installed on the housing 20 (Fig. 6) of the spacecraft. The drive frame 21 is rigidly attached to the drive 21.

 The equipment, for example, an antenna 23 is placed between the frame 22 and the beam 24. On the frame 22 and the beam 24 using the hinged parallelogram 25 (Fig. 7) are installed lower 26 and upper 27 wings.

 The lower leaf 26, connected with the leaf 27 by a spring-loaded hinge 28, is pressed against the body 20 (Fig. 6) by means of a pyro means 29 (Fig. 9).

 Thus, the pyromedicine 29 is pressed against the body of the spacecraft 20 (Fig. 6) of the sash 26 (Fig. 7), the frame 22 (Fig. 6) and the beam 24.

 In the case 30 (Fig. 9) of each pyromedicine 29, a hole 31 is made under the main axis 32 and a pyroelectric element 33 (squib) is installed, which, interacting with the axis 32, fixes the lever 34 relative to the body 30. An additional pyroelectric 35 (Fig. 11) is installed in the body 30, interacts with an additional axis 36 (Fig. 10) and fixes the lever 34 with the housing 30 (Fig. 9) and the dog 37.

 Own axis 38 fixes the lever 34 relative to the dog 37 and ensures their joint rotation relative to the additional axis 36 (Fig. 10) in the housing 30 (Fig. 9), in which a shaped groove 39 is made.

 The spring pusher 40 abuts against the lever 34, and the dog 37 interacts with the cocked torsion spring 41.

 On the shutter 26 (Fig. 8), a latch 43 spring-loaded in the axis 42 is installed, one end of which abuts against the end face 44 of the spring-loaded latch 45 held in position by the cam 46.

 The other end of the latch 43 holds the sash 27 from opening.

 The operation of the spacecraft is carried out in the following sequence.

 After resetting the head fairing, based on the functional tasks of the spacecraft, the antenna 23 (Fig. 7) is driven by its drive from the body of the spacecraft 20 (Fig. 6) from the SB opening area and is fixed in the working position.

Thus, the antenna 23 (Fig. 7) frees up a zone for opening the wings 26 and 27 on board the spacecraft. There was an opportunity to use pyromedicine for:
- fastening the sash package to the frame and beam and for their subsequent opening;
- fixing the frame and beam to the spacecraft body and their subsequent separation.

 The use of one pyromedicine for solving two problems can reduce their number, which increases the reliability of the system.

 A command is issued to trigger the main pyroelement 33 (Fig. 9) pyromedium 29.

 The main axis 32, moving in the axial direction, is "buried" in the housing 30.

 The lever 34 under the action of the compressed spring of the pusher 40 together with the dog 37 (Fig. 10) and its own axis 38 is rotated relative to the additional axis 36.

 In this case, the axis 38 moves in the cavity of the figured groove 39.

 Without analysis of the operation of the pyromedicine from the main pyroelement 33, a command for the duplicating pyroelement 35 is given in 0.5-2 s (Fig. 11). Under the action of its powder gases, the additional axis 36 is "buried" (Fig. 10), the dog 37 is rotated relative to the main axis 32 by a torsion spring 41.

 The flaps 26 and 27 (Fig. 7), the frame 22 (Fig. 6) and the beam 24 are released from the body of the spacecraft 20, open under the action of torsion springs installed in the axes of the articulated parallelogram 25 (Fig. 7). The panel is retracted by the actuator 21 to the operating position.

 Dog 37 (Fig. 10) does not protrude beyond the plane "u" and does not prevent the withdrawal of SB elements from the spacecraft.

 The cam 46 (Fig. 8), rigidly hinged at a certain angle of rotation, releases the latch 45, which, moving in the axial direction, releases the shank of the latch 43. Turning the torsion spring, the latch 43 releases the sash 57, which is opened and fixed.

 With mutual movements of the valves from overloads and temperature extremes, the end face 44 of the latch 45 is able to move along the square. "I", which excludes the failure to open the wings.

Due to the fact that two independent mechanisms are installed in the housing of the pyromedicine 30 (Fig. 9), which are triggered by pyroelements (pyro-cartridges) 33 and 35 (Fig. 11), the reliability of the pyromedicine increases and is
P _o = 0.999999
And since it was possible to solve the problem of fastening and opening the shutters with 6 pyromedics (instead of 12), the reliability of the opening of the shutters is
P _system = 0.999999 ⁶ = 0.99999
This is approximately 1 failure per 100,000 products.

 The introduction of a latch pivotally fixed to the leaflet eliminates jamming of the latch (even with temperature movements of the leaflets relative to each other).

 The proposed technical solution allows to increase the reliability of the system of opening the shutter SB approximately 100 times.

Claims (1)

 The spacecraft’s solar battery, consisting of a frame, a beam, upper and lower shutters, pairwise interconnected by clamps and mounted on a frame and a beam, which are mounted on the spacecraft’s body with a pyro-weapon with a dog rotating about an axis in an opening made in the pyro-medium case characterized in that the pyroelectric element additionally has a pyroelement interacting with the dog, and a spring-loaded latch is pivotally mounted on the lower sash, with one end of the stop schayasya a bracket fixedly secured to the upper leaf, and cooperating with the other end clamp.

Images