阅读说明：本技术 一种折叠式太阳电池阵二次压紧释放机构 (Folding type solar cell array secondary compression releasing mechanism ) 是由 濮海玲 杨淑利 任守志 马静雅 刘颖 于 2021-07-23 设计创作，主要内容包括：本发明提供一种折叠式太阳电池阵二次压紧释放机构,能够在释放后运动并保持固定在设定位置,满足二次压紧释放机构的功能和性能要求。包括：压紧帽、限位机构、压紧杆、压紧座以及火工切割器；压紧座固定安装在航天器侧壁上,压紧杆依次穿过外中太阳板、内中太阳板、内太阳板的压紧衬套后与压紧座固接,通过压紧杆施加预张力；火工切割器用于切断预张紧的压紧杆；在压紧杆切断处上方设置有与限位机构配合的限位段；限位机构固定在外中太阳板的压紧衬套内；当火工切割器切断压紧杆后,切断后的压紧杆向外中太阳板方向滑动；当压紧杆上的限位段移动至限位机构所在位置时,通过限位机构对限位段的限位将压紧杆固定在当前位置。(The invention provides a folding type solar cell array secondary compression release mechanism which can move after being released and keep fixed at a set position, and meets the requirements of the secondary compression release mechanism on function and performance. The method comprises the following steps: the device comprises a pressing cap, a limiting mechanism, a pressing rod, a pressing seat and an initiating explosive cutter; the pressing base is fixedly arranged on the side wall of the spacecraft, the pressing rods sequentially penetrate through the pressing bushings of the outer middle solar panel, the inner middle solar panel and the inner solar panel and then are fixedly connected with the pressing base, and pretension is applied through the pressing rods; the firer cutter is used for cutting off the pre-tensioned pressing rod; a limiting section matched with the limiting mechanism is arranged above the cut-off position of the compression rod; the limiting mechanism is fixed in the pressing bush of the outer and middle solar panels; when the pressing rod is cut off by the firer cutter, the cut pressing rod slides towards the outer middle solar panel; when the limiting section on the pressing rod moves to the position of the limiting mechanism, the pressing rod is fixed at the current position through the limitation of the limiting section by the limiting mechanism.)

1. A folding solar cell array secondary compaction release mechanism is characterized by comprising: the device comprises a pressing cap (3), a limiting mechanism, a pressing rod (15), a pressing seat (17) and a firer cutter (18);

the pressing base (17) is fixedly arranged on the side wall (21) of the spacecraft, the pressing rod (15) sequentially penetrates through the pressing bushings of the outer middle solar panel (10), the inner middle solar panel (12) and the inner solar panel (14) and then is fixedly connected with the pressing base (17), and pretension is applied through the pressing rod (15);

the firer cutter (18) is arranged at one end of the pressing rod (15) close to the pressing seat (17) and is used for cutting off the pre-tensioned pressing rod (15); a limiting section matched with the limiting mechanism is arranged above the cut-off part of the pressing rod (15);

the limiting mechanism is fixed in a pressing bushing of the outer and middle solar panels (10); when the fire cutter (18) cuts off the pressing rod (15), the cut pressing rod (15) slides towards the outer middle solar panel (10); when the limiting section on the pressing rod (15) moves to the position of the limiting mechanism, the pressing rod (15) is fixed at the current position through the limitation of the limiting section by the limiting mechanism.

2. The folding solar cell array secondary compaction release mechanism of claim 1, wherein: the stop gear includes: a buffer block (7) and a barb buffer spring (8); the limiting section arranged on the pressing rod (15) is a wedge-shaped section (16);

the bottom of the barb buffer spring (8) is provided with a barb (22);

the buffer block (7) and the barb buffer spring (8) are sleeved outside the pressing rod (15) after being laminated, wherein the buffer block (7) is positioned above the barb buffer spring (8);

when the cut pressing rod (15) slides towards the outer middle solar plate (10) direction, the wedge-shaped section (16) penetrates through the barb buffer spring (8) and is wedged into the buffer block (7), and then the buffer block (7) deforms and clamps the wedge-shaped section (16); meanwhile, one side, close to the pressing seat (17), of the wedge-shaped section (16) is blocked by a barb (22) of the barb buffer spring (8), so that the cut pressing rod (15) is positioned and stays on the back surface of the outer and middle solar panels (10).

3. The folding solar cell array secondary compaction release mechanism of claim 2, wherein: barb buffer spring (8) are the claw shape component, and its circumference evenly spaced distributes has three bar incision, makes it possess four spring leaf in circumference, and the lower extreme of every spring leaf has barb (22), and the space that four barb (22) surround is frustum shape, then the inner peripheral face of barb buffer spring (8) then includes cylindricality section and frustum shape section, and the internal diameter of frustum shape tip is less than the internal diameter of cylindricality section.

4. The folding solar cell array secondary compaction release mechanism of claim 2, wherein: a buffer pad assembly (6) and a gasket (5) are sequentially arranged above the buffer block (7), wherein the gasket (5) is pressed on the back surface (9) of the outer and middle solar panels through bolts; spherical pad (4) and compress tightly cap (3) are set gradually to gasket (5) top, spherical pad (4) and gasket (5) sphere contact, it screws up on spherical pad (4) and locks with the nut to compress tightly cap (3) spiral.

5. The folding solar cell array secondary compaction release mechanism of claim 2, wherein: the buffer block (7) is a polytetrafluoroethylene buffer block.

Technical Field

The invention relates to a compression release mechanism, in particular to a folding solar cell array secondary compression release mechanism, and belongs to the field of spacecraft mechanism design.

Background

In order to ensure the safety of satellite attitude control, a Solar cell array and a driving device (SADA-Solar array drive assembly) when an orbital transfer engine works, the Solar cell array is not completely unfolded after the satellite enters the orbit, and only the outermost cell panel is unfolded for 90 degrees to be locked, so that the power requirement of the satellite on the transfer orbit is met; and after the satellite enters the geosynchronous orbit, the solar cell array is completely unfolded, and the solar cell array starts full-power generation and enters an on-orbit normal working state.

Based on this, it is necessary to design a primary compression release mechanism for releasing the outermost battery panel and a secondary compression release mechanism for releasing the remaining battery panels, wherein the functions and performances of the secondary compression release mechanisms need to satisfy:

in the process of first releasing the solar cell array and unfolding and locking the outer plate by 90 degrees, the rest solar panels and the connecting frame are still fixed on the side wall of the satellite, and the solar cell array in the once unfolded and locked state can meet the specified rigidity requirement and bear the load generated when an orbital transfer engine works in the orbital transfer process;

when the quasi-synchronous track is released by secondary spreading ignition, the cut-off pressing rod must be moved away from the front surface of the outer and middle solar panels and transferred to the back surface for fixing so as to prevent the solar cell circuit on the panels from being shielded.

The existing solar cell array cannot move and be fixed at a certain position after being released by a once-time compression release mechanism; and there is no disclosure of secondary compression release mechanism technology.

Disclosure of Invention

In view of this, the present invention provides a foldable solar cell array secondary pressing release mechanism, which can move after being released and remain fixed at a set position, so as to meet the requirements of the secondary pressing release mechanism on functions and performance.

The folding solar cell array secondary compression release mechanism comprises: the method comprises the following steps: the device comprises a pressing cap, a limiting mechanism, a pressing rod, a pressing seat and an initiating explosive cutter;

the pressing base is fixedly arranged on the side wall of the spacecraft, the pressing rods sequentially penetrate through the pressing bushings of the outer middle solar panel, the inner middle solar panel and the inner solar panel and then are fixedly connected with the pressing base, and pretension is applied through the pressing rods;

the firer cutter is arranged at one end of the pressing rod close to the pressing seat and used for cutting off the pre-tensioned pressing rod; a limiting section matched with the limiting mechanism is arranged above the cut-off position of the compression rod;

the limiting mechanism is fixed in the pressing bushing of the outer and middle solar panels; after the pressing rod is cut off by the firer cutter, the cut pressing rod slides towards the outer middle solar panel; when the limiting section on the pressing rod moves to the position of the limiting mechanism, the pressing rod is fixed at the current position through the limitation of the limiting section by the limiting mechanism.

As a preferred embodiment of the present invention: the stop gear includes: the buffer block and the barb buffer spring; the limiting section arranged on the compressing rod is a wedge-shaped section;

the bottom of the barb buffer spring is provided with a barb;

the buffer block and the barb buffer spring are sleeved outside the compression rod after being stacked, wherein the buffer block is positioned above the barb buffer spring;

when the cut pressing rod slides towards the outer middle solar plate direction, the wedge-shaped section penetrates through the barb buffer spring and is wedged into the buffer block, and then the buffer block deforms and clamps the wedge-shaped section; meanwhile, one side, close to the pressing seat, of the wedge-shaped section is blocked by the barb of the barb buffer spring, so that the cut pressing rod is positioned and stays on the back surface of the outer and middle solar panels.

As a preferred embodiment of the present invention: the barb buffer spring is a claw-shaped component, three strip-shaped notches are uniformly distributed at intervals in the circumferential direction of the barb buffer spring, so that the barb buffer spring is provided with four spring pieces in the circumferential direction, the lower end of each spring piece is provided with a barb, the space surrounded by the four barbs is frustum-shaped, the inner circumferential surface of the barb buffer spring comprises a cylindrical section and a frustum-shaped section, and the inner diameter of the small end of the frustum shape is smaller than that of the cylindrical section.

As a preferred embodiment of the present invention: a buffer pad assembly and a gasket are sequentially arranged above the buffer block, wherein the gasket is pressed on the back of the outer and middle solar panels through bolts; the spherical gasket and the pressing cap are sequentially arranged above the gasket, the spherical gasket is in contact with the spherical surface of the gasket, and the pressing cap is screwed on the spherical gasket and locked by a nut.

As a preferred embodiment of the present invention: the buffer block is a polytetrafluoroethylene buffer block.

Has the advantages that:

(1) in a folded state of the solar cell array, the secondary compression release mechanism compresses other solar panels except the solar panel and the connecting frame on the side wall of the spacecraft, and enables the solar cell array in a primary unfolding and locking state to meet the specified rigidity requirement and bear the load generated when an orbital transfer engine works in an orbital transfer process.

(2) When the solar cell array is unlocked and unfolded secondarily, after the pre-tensioned compressing rod is cut off by the firer cutter, the cut compressing rod is pushed to rapidly slide towards the compressing cap by utilizing the tension released by secondary unfolding, so that the wedge-shaped section of the compressing rod enters the polytetrafluoroethylene buffer block to be clamped, the compressing rod stops sliding and cannot fly away from the solar cell array; meanwhile, the tail part of the wedge-shaped section is blocked by a claw-shaped component formed by a barb buffer spring; the polytetrafluoroethylene buffer block and the claw-shaped component play a double-insurance role together, so that the cut-off pressing rod is kept on the back of the second solar panel and cannot return, and the solar cell is prevented from being shielded.

Drawings

FIG. 1 shows the state of the rest solar panels after the solar cell array is unfolded once;

fig. 2 shows a release state of the secondary pressing release mechanism after the solar cell array is unfolded for the first time (at the moment when the pressing rod is cut off by the firer cutter);

FIG. 3 is a schematic view of the secondary pressing release mechanism of the present invention in a pressing state;

FIG. 4 is a view of FIG. 3, schematic B-B;

FIG. 5 is a view of FIG. 3, schematic A-A;

FIG. 6 is a schematic view of the releasing state of the secondary compression releasing mechanism of the present invention;

fig. 7 is a configuration diagram of a barb buffer spring.

Wherein: 1-outer solar panel, 2-secondary compaction release mechanism, 3-compaction cap, 4-spherical pad, 5-pad, 6-buffer pad assembly, 7-buffer block, 8-barb buffer spring, 9-outer middle solar panel back, 10-outer middle solar panel, 11-outer middle solar panel battery face, 12-inner middle solar panel, 13-compaction bush, 14-inner solar panel, 15-compaction rod, 16-wedge-shaped section, 17-compaction seat, 18-firer cutter, 19-square nut, 20-transition pad, 21-spacecraft sidewall, 22-barb

Detailed Description

The invention is described in detail below by way of example with reference to the accompanying drawings.

The embodiment provides a folding rigid or semi-rigid solar cell array secondary compression release mechanism.

As shown in fig. 1, in the satellite launching state, the folding rigid or semi-rigid solar cell array secondary pressing release mechanism 2 presses other solar panels and connecting frames except the solar panel 1 on the side wall of the satellite. Namely: after the satellite and the satellite are separated, the primary pressing release mechanism cuts off the pressing rods of the outer solar panel 1 through the firer cutter in sequence to remove the constraint on the outer solar panel 1, and at the moment, other solar panels and the connecting frame except the outer solar panel 1 are pressed on the side wall of the satellite through the secondary pressing release mechanism 2. When the satellite flies in the transfer orbit (for a plurality of days), the secondary compression release mechanism not only has the capacity of compressing other solar panels and connecting frames, but also has the capacity of overcoming the load generated when the orbital transfer engine works in the orbital transfer process.

As shown in fig. 2, after the satellite is positioned, the secondary pressing release mechanism 2 cuts off the pressing rod 15 by using the fire cutter 18, the pressing rod 15 is ejected, the pressing on other solar panels and the connecting rack is released, and the pressing rod 15 is left on the side of the back surface 9 of the middle solar panel at this time, so that the solar rays are not blocked.

As shown in fig. 3 to 5, the folding solar cell array secondary pressing and releasing mechanism 2 includes: the pressing cap 3, the spherical pad 4, the gasket 5, the cushion pad assembly 6, the buffer block 7, the barb buffer spring 8, the pressing rod 15, the pressing seat 17 and the firer cutter 18;

wherein the buffer block 7 is a polytetrafluoroethylene buffer block;

barb buffer spring 8 is the claw shape component as shown in fig. 7, and its circumference evenly spaced distributes has three bar incision, makes it possess four spring leaf in circumference, and the lower extreme of every spring leaf has barb 22, and the lower extreme of every spring leaf is the inclined plane that increases progressively from bottom to top thickness promptly, makes the space that four barb 22 surround for the frustum shape from this, then barb buffer spring 8's inner circumferential surface then includes cylindricality section and frustum shape section, and the internal diameter of frustum shape tip is less than the internal diameter of cylindricality section, forms the step from this between cylindricality section and frustum shape section.

The installation relationship of the secondary compression release mechanism 2 is as follows: the pressing base 17 is fixedly arranged on the side wall 21 of the spacecraft, and the pressing rod 15 sequentially penetrates through the pressing bushings 13 of the outer middle solar panel 10, the inner middle solar panel 12 and the inner solar panel 14 and the pressing base 17 and then is screwed on the pressing base 17 through the square nut 19 and the transition pad 20; the barb buffer spring 8 and the buffer block 7 are fixed in the pressing bush 13 of the outer and middle solar panels 10 and are sleeved outside the pressing rod 15; wherein the buffer block 7 is positioned above the barb 22 of the barb buffer spring 8; a buffer pad component 6 and a gasket 5 are sequentially arranged above the buffer block 7, and the gasket 5 is pressed on the back 9 of the outer and middle solar panels through bolts (the front of the outer and middle solar panels is the battery surface 11 of the outer and middle solar panels); a spherical pad 4 and a pressing cap 3 are sequentially arranged above the gasket 5, the spherical pad 4 is in spherical contact with the gasket 5, and the top of the pressing rod 15 extends out of the spherical pad 4 and then is screwed and pre-tightened with a pressing nut to apply pre-tension; the pressing cap 3 is sleeved outside the pressing nut, and the pressing cap 3 is screwed on the spherical pad 4 and is tightly taken by the nut, so that the flying of excess materials is prevented.

A firer cutter 18 is arranged at one end of the pressing rod 15 close to the pressing seat 17 and is used for cutting off the pre-tensioned pressing rod 15; the connecting position of the firer cutter 18 and the pressing rod 15 is a cutting position of the pressing rod 15, and a wedge-shaped section 16 is arranged above the pressing rod 15 and close to the cutting position.

Compared with a primary compression release mechanism, the secondary compression release mechanism adopts the following design measures:

(1) designing a wedge-shaped section 16 at the position, close to the cutting position, of the pressing rod 15;

(2) a polytetrafluoroethylene buffer block 7 and a barb buffer spring 8 are arranged in a compression bush 13 of the outer and middle solar panels 10.

The working process of the secondary compression release mechanism of the folding solar cell array is as follows:

when the solar cell array is unfolded and released secondarily, the pre-tensioned compressing rod 15 is cut off by the initiating explosive cutter 18, and the cut compressing rod 15 is pushed to slide towards the compressing cap 3 by the aid of reaction force released by the compressing rod 15 and explosive force of the initiating explosive cutter 18; when the wedge-shaped section 16 above the cut-off part of the pressing rod 15 approaches to the pressing bush 13 of the outer and middle solar panels 10, the wedge-shaped section passes through the barb buffer spring 8 and is wedged into the round hole of the polytetrafluoroethylene buffer block 7, so that the polytetrafluoroethylene buffer block 7 deforms and clamps the wedge-shaped section 16 of the pressing rod 15, and the wedge-shaped section 16 cannot completely pass through the hole due to the small aperture of the round hole of the polytetrafluoroethylene buffer block 7, so that the pressing rod 15 is prevented from flying out of the solar cell array and dissociating from the spacecraft. Meanwhile, the side of the wedge-shaped section 16 close to the pressing seat 17 is blocked by the barb 22 of the barb buffer spring 8, so that the cut pressing rod 15 is positioned and stays on the back side of the outer and middle solar panels 10, and the ejected secondary pressing release mechanism 2 is shown in fig. 6.

The buffer block 7 and the barb buffer spring 8 of the claw-shaped component play a double protection role, and ensure that the cut pressing rod 15 is left on the back surface 9 of the solar panel in the outside and can not return, so that the solar cell is not shielded. The secondary pressing releases the pressing rod 15 which is cut off and clamped on the back of the outer and middle solar panels as shown in fig. 2.

In the secondary compression release mechanism, through the design of a wedge-shaped section at the position, close to the cut-off part, of the compression rod and the design of a polytetrafluoroethylene buffer block and a claw-shaped component which are arranged in the compression bush of the outer and middle solar panels, when secondary expansion ignition release is carried out, the cut-off compression rod needs to be moved from the front surface of the outer and middle solar panels and fixed to the back surface of the outer and middle solar panels so as to prevent a solar cell circuit on the panels from being blocked;

the other solar panels and the connecting frame are fixed on the side wall of the spacecraft by using the single secondary compression release mechanism, and after a certain pretightening force is applied, the solar cell array can bear the load generated by the operation of the orbital transfer engine in the satellite orbital transfer process without damage.

Therefore, the secondary compression release mechanism can meet the requirements of functions and performances of the secondary compression release mechanism.

The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.