CN104535100A - Space optical remote sensor installation support on-orbit unlocking device - Google Patents
Space optical remote sensor installation support on-orbit unlocking device Download PDFInfo
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- CN104535100A CN104535100A CN201410839972.XA CN201410839972A CN104535100A CN 104535100 A CN104535100 A CN 104535100A CN 201410839972 A CN201410839972 A CN 201410839972A CN 104535100 A CN104535100 A CN 104535100A
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- erection support
- installation support
- remote sensor
- space optical
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Abstract
The invention provides a space optical remote sensor installation support on-orbit unlocking device and belongs to the technical field of space optics. The problems that the requirements for machining, installation, adjustment and accuracy are high, a development period is long, cost is high, the impulse, the weight and the occupied space are large, pollutants are easily generated, and potential safety hazards exist in the prior art are solved. The device comprises a lower installation support body used for being connected with a satellite, semicircular limiting rings connected with the lower installation support body, an upper installation support body connected with a space optical remote sensor, an extension spring connected with the lower installation support body and the upper installation support body, thermal insulation pads making contact with the upper installation support body, and telescopic rings pressing the thermal insulation pads. The two semicircular limiting rings are connected with the lower installation support body through hexagon socket screws, the eight thermal insulation pads have the telescopic function and are clamped between the two telescopic rings and the upper installation support body, the telescopic rings are made of a memory alloy material, heating pads are arranged on the non-contact faces of the telescopic rings, and the telescopic rings shrink when being heated.
Description
Technical field
The invention belongs to space optics technical field, be specifically related to a kind of space optical remote sensor erection support tripper in-orbit.
Background technology
Space optical remote sensor is as high-accuracy spaceborne optical device, counter stress is responsive especially, and ground is debug and launch environment will inevitably introduce a part of stress, particularly in space optical remote sensor and satellite installation process, introduction erection stress is maximum, so design a set of erection support, tripper is imperative in-orbit.At present, space optical remote sensor in-orbit tripper mainly adopts priming system detonation mode, and this kind of device has following shortcoming:
1) process, debug and require high, accuracy requirement is high, and the lead time is long.Priming system priming device structure is relatively complicated, can depart from smoothly after detonating, and parting plane structure precision requires high, and dimensional tolerence and fit-up gap require strict, so the lead time is just long.
2) cost is high.The cost of priming system own is just high, and corollary apparatus processing is debug and required high, and transhipment, storage environment require harsh, so cost is maximum bottleneck of its development of restriction.
3) momentum is large.The priming system burst time is short, and transient energy is concentrated, and produces momentum large, may cause the flutter of whole star.
4) weight large, take up room large.The weight and volume of the tripper that detonates own is just very large, also needs sufficiently long cable and the retracting device of detonating, so count 2 times that general assembly (TW) is greater than pure bearing weight, and cable is thick, hard, takes up room and has just well imagined.
5) easily produce pollutant, there is potential safety hazard.The priming system that the tripper that detonates adopts produces a lot of flue dust, if protect improper, minute surface may be caused to pollute, and priming system is combustible and explosive articles, the potential safety hazard that existence itself is very large.
Summary of the invention
The object of this invention is to provide a kind of space optical remote sensor erection support tripper in-orbit, solve prior art processing, debug require high, accuracy requirement is high, the lead time is long, cost is high, momentum is large, weight is large, it is large to take up room, and easily produces pollutant, there is the problem of potential safety hazard.
A kind of space optical remote sensor erection support of the present invention in-orbit tripper comprises erection support lower body, extension spring, erection support upper body, expansion ring, heat insulating mattress and heating plate; Erection support lower body is enclosed within erection support upper body, extension spring is between bearing upper body and erection support lower body, one end of extension spring hooks on erection support upper body, the other end hooks on erection support lower body, erection support lower body is connected with satellite, and erection support upper body is connected with space optical remote sensor; Erection support upper body is provided with heat dam, and heat insulating mattress is pasted onto in heat dam, and expansion ring is enclosed within outside heat insulating mattress, and on heat dam, is provided with heating plate in the noncontact plane of 2 expansion rings.
Described erection support lower body is provided with elongated slot under spring, under spring, elongated slot both sides respectively arrange a spring through hole.
The center of the upper surface of described erection support upper body is provided with elongated slot on spring, on spring, the both sides of elongated slot respectively arrange a spring unthreaded hole, at centre position circumference uniform distribution 4 screw unthreaded holes of upper surface, at uniform 4 mounting holes of the outer circumference of upper surface, the lower end of erection support upper body is cylinder, cylinder is divided into pintongs by four elongated slots, and cylinder distributes two circle stopper slots, cylinder is also distributed with 8 threading holes.
The present invention also comprises spacing semicircular ring, and the spacing semicircular ring of two panels is fixedly connected with erection support lower body respectively by socket head cap screw.
Principle of work of the present invention: before space optical remote sensor is entered the orbit, because expansion ring is fixedly connected with erection support lower body by screw, expansion ring and the erection support lower body of erection support upper body were win to coordinate, erection support upper body and erection support lower body as a whole; After space optical remote sensor is entered the orbit, the heating plate of heating expansion ring two noncontact planes, by the memory function of expansion ring material, expansion ring shrinks, expansion ring inwall is made to be pressed on erection support upper body, expansion ring outer wall is separated with erection support lower body, and then realizes erection support upper body and be separated with erection support lower body, realizes unlocking; The spacing of erection support upper body and erection support lower body leans on the natural length of extension spring to maintain; If extension spring lost efficacy, then spacing semicircular ring was second insurance, thus guaranteed that erection support thoroughly unlocks, and stress obtains maximum release, and interval, space optical remote sensor present position is controlled.In order to make space optical remote sensor not introduce heat, erection support upper body and expansion ring surface of contact are evenly equipped with heat insulating mattress.
Advantageous Effects of the present invention: expansion ring of the present invention is memorial alloy ring structure, the difficulty reducing tripper processing and debug, reduce weight and the space of device, eliminate and unlock the large equivalent risk of momentum, cost and lead time are saved, and this tripper structure is simple in-orbit, strong operability, implements convenient, safety.
Accompanying drawing explanation
Fig. 1 is the main pseudosection of a kind of space optical remote sensor erection support of the present invention tripper locking state in-orbit;
Fig. 2 is a kind of space optical remote sensor erection support of the present invention vertical view of Fig. 1 in tripper in-orbit;
Fig. 3 is the main pseudosection of a kind of space optical remote sensor erection support of the present invention tripper released state in-orbit;
Fig. 4 is the erection support upper body structure three-dimensional figure of a kind of space optical remote sensor erection support of the present invention in-orbit in tripper;
Wherein: 1, erection support lower body, 2, extension spring, 3, spacing semicircular ring, 4, erection support upper body, 4001, elongated slot, 4002, stopper slot, 4003, threading hole, 5, expansion ring, 6, heat insulating mattress, 7, socket head cap screw.
Embodiment
Below in conjunction with accompanying drawing, the present invention is further elaborated.
See accompanying drawing 1, accompanying drawing 2, accompanying drawing 3 and accompanying drawing 4, a kind of space optical remote sensor erection support of the present invention in-orbit tripper comprises erection support lower body 1, extension spring 2, erection support upper body 4, expansion ring 5, heat insulating mattress 6 and heating plate; Erection support lower body 1 is enclosed within erection support upper body 4, extension spring 2 is between bearing upper body and erection support lower body 1, one end of extension spring 2 hooks on erection support upper body 4, the other end hooks on erection support lower body, erection support lower body 1 is connected with satellite, and erection support upper body 4 is connected with space optical remote sensor; Erection support upper body 4 is provided with two circle heat dams, and heat insulating mattress 6 is pasted onto in heat dam, and 2 expansion rings 5 are enclosed within outside the heat insulating mattress 6 of the heat insulation grass of two circles respectively, are provided with heating plate in the noncontact plane of 2 expansion rings 5.
Described erection support lower body 1 is provided with elongated slot under spring, under spring, elongated slot both sides respectively arrange a lower spring through hole.
The center of the upper surface of described erection support upper body 4 is provided with elongated slot on spring, on spring, the both sides of elongated slot respectively arrange spring unthreaded hole on, at centre position circumference uniform distribution 4 screw unthreaded holes of upper surface, at uniform 4 mounting holes of the outer circumference of upper surface, the lower end of erection support upper body 4 is cylinder, cylinder is divided into pintongs by four elongated slots 4001, cylinder distributes two circle stopper slots 4002, cylinder is also distributed with 8 threading holes, 4003,8 threading holes 4003 for heating plate cabling.
The present invention also comprises spacing semicircular ring 3, and the spacing semicircular ring 3 of two panels is fixedly connected with erection support lower body 1 respectively by socket head cap screw 7.
Assembling process of the present invention is: 8 heat insulating mattress 6 are one-sided smears heat insulation fat, is all pasted onto in 8 place's stopper slots of erection support upper body 4 by 8 heat insulating mattress 6 fat liquoring sides; 2 expansion rings 5 are enclosed within the stopper slot of erection support upper body 4 respectively; Extension spring 2 is placed between erection support lower body 1 and erection support upper body 4, on the spring on top, erection support upper body 4, elongated slot is consistent with elongated slot direction under the spring of erection support lower body 1 bottom, the drag hook at extension spring 2 two ends is made to pass through elongated slot smoothly, elongate extension spring 2 until drag hook all exposes erection support upper body 4 top end face and erection support lower body 1 bottom face, by extension spring about 2 synchronous axial system 90 degree, hang in the spring unthreaded hole of erection support upper body 4 and erection support lower body 1; By the gap between erection support upper body 4 and erection support lower body 1,2 spacing semicircular ring 3 are put into correct position, by the screw unthreaded hole on top, erection support upper body 4, with 4 socket head cap screws 7,2 spacing semicircular ring 3 are fixed with erection support lower body 1 respectively.
After space optical remote sensor is entered the orbit, when needing to unlock to eliminate erection stress, by the heating plate heating on 2 expansion ring 5 noncontact faces, due to the memory function of expansion ring 5 material, expansion ring 5 shrinks, and makes expansion ring 5 inwall be pressed on erection support upper body 4, and expansion ring 5 outer wall is separated with erection support lower body 1, and then realize erection support lower body 1 and be separated with erection support upper body 4, the two spacing maintains by the natural length of extension spring 2.
The setting of described spacing semicircular ring 3 is in case spring failure, and because expansion ring 5 shrinks the internal diameter that rear external diameter is greater than semicircular ring, erection support upper body 4 can not skid off in erection support lower body 1, thus guarantees that erection support thoroughly unlocks, and stress obtains maximum release.
In order to improve the stability of space optical remote sensor, many groups tripper in-orbit of the present invention can be adopted.
Claims (4)
1. space optical remote sensor erection support tripper in-orbit, it is characterized in that, comprise erection support lower body (1), extension spring (2), erection support upper body (4), expansion ring (5), heat insulating mattress (6) and heating plate; Erection support lower body (1) is enclosed within erection support upper body (4), extension spring (2) is between bearing upper body and erection support lower body (1), one end of extension spring (2) hooks on erection support upper body (4), the other end hooks on erection support lower body (1), erection support lower body (1) is connected with satellite, and erection support upper body (4) are connected with space optical remote sensor; Erection support upper body (4) is provided with two circle heat dams, heat insulating mattress (6) is pasted onto in heat dam, 2 expansion rings (5) are enclosed within the heat insulating mattress (6) of the heat insulation grass of two circles outward respectively, are provided with heating plate in the noncontact plane of 2 expansion rings (5).
2. a kind of space optical remote sensor erection support according to claim 1 tripper in-orbit, is characterized in that, described erection support lower body (1) is provided with elongated slot under spring, under spring, elongated slot both sides respectively arrange a lower spring through hole.
3. a kind of space optical remote sensor erection support according to claim 1 tripper in-orbit, it is characterized in that, the center of the upper surface of described erection support upper body (4) is provided with elongated slot on spring, on spring, the both sides of elongated slot respectively arrange spring unthreaded hole on, at centre position circumference uniform distribution 4 screw unthreaded holes of upper surface, at uniform 4 mounting holes of the outer circumference of upper surface, the lower end of erection support upper body (4) is cylinder, cylinder is divided into pintongs by four elongated slots (4001), cylinder distributes two circles stopper slot (4002), cylinder is also distributed with 8 threading holes (4003).
4. a kind of space optical remote sensor erection support according to claim 1 tripper in-orbit, it is characterized in that, also comprise spacing semicircular ring (3), the spacing semicircular ring of two panels (3) is fixedly connected with erection support lower body (1) respectively by socket head cap screw (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410839972.XA CN104535100B (en) | 2014-12-30 | 2014-12-30 | A kind of in-orbit tripper of space optical remote sensor erection support |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410839972.XA CN104535100B (en) | 2014-12-30 | 2014-12-30 | A kind of in-orbit tripper of space optical remote sensor erection support |
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| CN104535100A true CN104535100A (en) | 2015-04-22 |
| CN104535100B CN104535100B (en) | 2017-06-09 |
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| CN201410839972.XA Active CN104535100B (en) | 2014-12-30 | 2014-12-30 | A kind of in-orbit tripper of space optical remote sensor erection support |
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Citations (8)
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|---|---|---|---|---|
| EP1115615A1 (en) * | 1998-09-24 | 2001-07-18 | EADS Deutschland Gmbh | Holding and releasing mechanism with a shape memory actuator |
| CN1827475A (en) * | 2006-04-10 | 2006-09-06 | 北京航空航天大学 | Mini-sized large-load SMA space synchronous unlocking mechanism |
| CN101157388A (en) * | 2007-11-21 | 2008-04-09 | 航天东方红卫星有限公司 | Mechanism for separating stars or star-arrow |
| CN201142300Y (en) * | 2008-01-07 | 2008-10-29 | 北京有色金属研究总院 | Shape memory alloy load fast releasing device |
| CN102975872A (en) * | 2012-12-25 | 2013-03-20 | 中国科学院长春光学精密机械与物理研究所 | Shock-free wrapping tape type unlocking separation mechanism |
| CN203381788U (en) * | 2013-04-19 | 2014-01-08 | 南京航空航天大学 | Controlled unlocking device based on shape memory alloy spring |
| CN103895879A (en) * | 2014-02-26 | 2014-07-02 | 郑钢铁 | Low-impact locking and unlocking device |
| CN104085540A (en) * | 2014-07-07 | 2014-10-08 | 中国科学院长春光学精密机械与物理研究所 | Unlocking device made of shape memory material |
-
2014
- 2014-12-30 CN CN201410839972.XA patent/CN104535100B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1115615A1 (en) * | 1998-09-24 | 2001-07-18 | EADS Deutschland Gmbh | Holding and releasing mechanism with a shape memory actuator |
| CN1827475A (en) * | 2006-04-10 | 2006-09-06 | 北京航空航天大学 | Mini-sized large-load SMA space synchronous unlocking mechanism |
| CN101157388A (en) * | 2007-11-21 | 2008-04-09 | 航天东方红卫星有限公司 | Mechanism for separating stars or star-arrow |
| CN201142300Y (en) * | 2008-01-07 | 2008-10-29 | 北京有色金属研究总院 | Shape memory alloy load fast releasing device |
| CN102975872A (en) * | 2012-12-25 | 2013-03-20 | 中国科学院长春光学精密机械与物理研究所 | Shock-free wrapping tape type unlocking separation mechanism |
| CN203381788U (en) * | 2013-04-19 | 2014-01-08 | 南京航空航天大学 | Controlled unlocking device based on shape memory alloy spring |
| CN103895879A (en) * | 2014-02-26 | 2014-07-02 | 郑钢铁 | Low-impact locking and unlocking device |
| CN104085540A (en) * | 2014-07-07 | 2014-10-08 | 中国科学院长春光学精密机械与物理研究所 | Unlocking device made of shape memory material |
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| CN104535100B (en) | 2017-06-09 |
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