CN105659761B - Spacecraft equipment supporting component release stopping means - Google Patents
Spacecraft equipment supporting component release stopping meansInfo
- Publication number
- CN105659761B CN105659761B CN200810077294.2A CN200810077294A CN105659761B CN 105659761 B CN105659761 B CN 105659761B CN 200810077294 A CN200810077294 A CN 200810077294A CN 105659761 B CN105659761 B CN 105659761B
- Authority
- CN
- China
- Prior art keywords
- auricle
- pull bar
- stopping means
- compressor arm
- pad
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Abstract
The invention provides a kind of spacecraft equipment supporting component release stopping means, formed by three-jaw structural member auricle (1), pull bar auricle (2), firer's cutter (3), pressed seat (4), compressor arm (12), compressor arm stopping means, pull bar stopping means. The present invention is applied normal pressure by compressor arm (12) to pull bar auricle (2) and three-jaw structural member auricle (1), can guarantee that pull bar (22) provides certain axial force at transmitter section to spacecraft equipment, the response of transmitter section main equipment can be reduced greatly, avoid payload impaired. After entering the orbit, compressor arm is cut to two-section by firer's cutter (3), relieves the supporting role of pull bar (22) to spacecraft equipment, avoids the inharmonious payload that causes of thermal deformation and loses the harm of pointing accuracy. The pull bar of pull bar stopping means after by release avoids the collision of pull bar and miscellaneous equipment within being limited to less scope. Compressor arm stopping means can guarantee that the two-section compressor arm after cut-off can not freely fly out.<pb pnum="1" />
Description
Technical field
The present invention relates to spacecraft structure mechanism technology, be specifically related to main equipment supporting component device.
Background technology
In the structural design of certain model satellite, in order to reduce the response of main equipment support at transmitter section,To main equipment support, support reinforcing must be carried out with supporting component, and supporting component is primarily of releaseStopping means, pull bar and three-jaw structural member composition. But in orbital environment, if do not remove pull bar and carryThe support and connection in lotus cabin, there will be thermal deformation not between load cabin, main equipment support, supporting componentCoordinate, cause instrument on main equipment support to lose precision. Therefore need set of device, protect at transmitter sectionPull bar and large-scale establishing are removed in the supporting role of card supporting component pull bar to main equipment support after entering the orbitConnection between standby, considers security, and the free scope of activities of the pull bar after removing connection is also wantedBe limited in less regional extent.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of release of spacecraft equipment supporting componentStopping means device. At transmitter section, this device can ensure that pull bar provides support spacecraft equipment, andAfter entering the orbit, remove the supporting role of pull bar to spacecraft equipment, and limit the scope of activities of pull bar.
For solving the problems of the technologies described above, the technical solution used in the present invention is:
The present invention includes three-jaw structural member auricle, pull bar auricle, firer's cutter, pressed seat, compressionBar, compressor arm stopping means, pull bar stopping means.
Compressor arm stopping means is divided into upper and lower two parts, upper part by clamping cap, honeycomb pad, pad,Volute spring composition, honeycomb pad, pad, volute spring are put into clamping cap successively, and clamping cap is connected inOn pull bar auricle and be positioned at compressor arm top; Lower part is by square nut, locating piece, cushion pad, compressionSeat bonnet composition, square nut, locating piece, cushion pad are arranged in the groove of pressed seat lower end successively,And fix with pressed seat bonnet.
Three-jaw structural member auricle has through hole, and it is logical that high friction coatings sleeve-board is glued to three-jaw structural member auricleTop, hole, the pressed seat that is provided with cavity is fixed on three-jaw structural member auricle bottom, its cavity and three-jaw knotMember auricle through hole is relative; The one side of pull bar auricle has the ball-and-socket matching with ball pad, for placingBall pad, ball-and-socket bottom has through hole; Firer's cutter is fixedly mounted on pressed seat, by compressor armAfter stopping means lower part is in place, afterburning nut, ball pad are enclosed within on compressor arm successively, compressBar leads to through pull bar auricle ball-and-socket bottom through-hole, high friction coatings sleeve-board, three-jaw structural member auricle successivelyThe cutting hole of hole, pressed seat cavity and firer's cutter, its precession compressor arm stopping means side, lower end spiral shellIn female screw thread, after afterburning nut completes, compressor arm stopping means upper part is in place;
Pull bar stopping means forms by pushing away spring, spacing shim, limiting buffer pad and gag lever post, limitBit buffering pad is glued on the termination of gag lever post, and gag lever post is successively through the circular hole of pull bar auricle, spacingPad, push away spring, be tightened on three-jaw structural member auricle by screw thread.
Microswitch is welded with a resistance, and is connected on three-jaw structural member auricle. Adjust screwBe arranged on pull bar auricle, after afterburning nut pretension puts in place, head of screw withstands on the triggering of microswitchOn arm.
The present invention is applied normal pressure by compressor arm to pull bar auricle and three-jaw structural member auricle, can guaranteePull bar provides certain axial force (frictional force) at transmitter section to spacecraft equipment, and transmitter section can be reduced greatlyThe response of main equipment, avoids payload impaired. After entering the orbit, by remote control or program control command to cuttingCutter is powered, and pull bar supporting role to spacecraft equipment just can be removed, thus avoid thermal deformation notCoordinate to cause payload to lose the harm of part pointing accuracy. The drawing after by release by stopping meansBar avoids the collision of pull bar and celestial body and miscellaneous equipment within being limited to a less scope.
Accompanying drawing explanation
Fig. 1 is the profilograph of release stopping means of the present invention.
Fig. 2 is the front view of release stopping means of the present invention.
Fig. 3 is the partial sectional view of release stopping means of the present invention.
Fig. 4 is the scheme of installation of release stopping means of the present invention on satellite.
Detailed description of the invention
Fig. 1, Fig. 2 are release position limiting structure schematic diagrames of the present invention. The present invention by three-jaw structural member auricle 1,Pull bar auricle 2, firer's cutter 3, pressed seat 4, compressor arm 12, compressor arm stopping means, pull barStopping means composition. Compressor arm stopping means is divided into upper and lower two parts, and upper part is by honeycomb pad 6, pad7, volute spring 8, clamping cap 5 form, and honeycomb pad 6, pad 7, volute spring 8 are put into clamping cap successivelyIn 5, clamping cap 5 is fixed by screws on pull bar auricle 2, and is positioned at compressor arm 12 top.Lower part is made up of square nut 13, locating piece 14, cushion pad 15, pressed seat bonnet 16, square nut13, locating piece 14, cushion pad 15 are arranged in the groove of pressed seat 4 lower end successively, and use pressed seatBonnet 16 is fixing. The lower end of compressor arm 12 screws in square nut 13 screw thread. Compressor arm 12 is being separatedAfter lock, be cut to two sections by firer's cutter 3, compressor arm stopping means upper part is pressed for after releaseTight bar 12 epimere spacing, compressor arm stopping means lower part is for compressor arm 12 hypomere after releaseSpacing, in case compressor arm 12 freely flies out.
As shown in Figure 3, three-jaw structural member auricle 1 has through hole, and high friction coatings sleeve-board 11 is glued toThree-jaw structural member auricle 1 through hole top, the pressed seat 4 that inside is provided with cavity is fixed on three-jaw structural memberAuricle 1 bottom, its cavity is relative with three-jaw structural member auricle 1 through hole. The one side of pull bar auricle 2 hasWith the ball-and-socket that ball pad 10 matches, for placing ball pad 10, ball-and-socket bottom has through hole. FirerCutter 3 is arranged on pressed seat 4. After compressor arm stopping means lower part is in place, will addPower nut 9, ball pad 10 are enclosed within on compressor arm 12 successively, and compressor arm 12 is successively through pull bar auricle2 ball-and-socket bottom through-holes, sleeve-board 11, three-jaw structural member auricle 1 through hole, pressed seat 4 cavity and firerThe cutting hole of cutter 3, by the screw thread of compressor arm 12 lower end precession square nut 13. Screw reinforcingNut 9, by ball pad 10, pull bar auricle 2 is pressed together with three-jaw structural member auricle 1, makesPull bar auricle 2 is fitted face-to-face with high friction coatings sleeve-board 11. By adjusting the pretension of afterburning nut 9The anglec of rotation can provide the axial force of different sizes. After axial force has applied, by spacing compressor arm dressBe set up part to be in place.
Pull bar stopping means is by pushing away spring 17, spacing shim 18, limiting buffer pad 20 and gag lever post19 compositions. Limiting buffer pad 20 is glued on the termination of gag lever post 19. By compressor arm 12 screw intoAfter square nut 13 and before screwing afterburning nut 9, pull bar stopping means must be installed: gag lever post 19Successively through circular hole, the spacing shim 18 of pull bar auricle 2, push away spring 17, revolve eventually through screw threadTightly on three-jaw structural member auricle 1. When pull bar auricle 2 and high friction coatings sleeve-board 11 are fitted face-to-faceTime, push away spring 17 pressurized.
Microswitch 25 is arranged on three-jaw structural member auricle 1 by screw, weldering on microswitch 25Be connected to a resistance, resistance is used to indicate compression, release instruction; Adjust screw 21 and be arranged on pull bar auricleOn 2. Install and after afterburning nut 9 pretension puts in place, to adjusting screw 12 at pull bar stopping meansAdjust on the trigger arm that makes its head of screw withstand on microswitch 25.
Pull bar 22 glueds joint be integrated with pull bar auricle 2, pull bar 22 and main equipment Support joint 24 itBetween connected by bearing pin 23, thus pull bar 22 can rotate around bearing pin 23. Three-jaw structural member auricle 1 is logicalCross screw to be fixed on pressed seat 4.
Fig. 4 is the scheme of installation of release stopping means of the present invention on satellite, wherein 26-load cabin,27-release stopping means, 28-main equipment support, 29-three-jaw structural member.
After spacecraft is entered the orbit, star power source is powered to firer's cutter 3, the cutting of firer's cutter 3Compressor arm 12 is cut to two-section by cutter. Wherein one section drives square nut 13, locating piece 14 outwards to move,Cushion pad 15 can be absorbed by distortion the energy of this process, and pressed seat bonnet 16 can be guaranteed to fly without partGo out; Another section of compressor arm 12 drives volute spring 8, pad 7 outwards to move, and honeycomb pad 6 is by becomingShape absorbs the energy of this process, and clamping cap 5 can be guaranteed to fly out without part. Because compressor arm 12 is cutDisconnected, the normal pressure between three-jaw structural member auricle 1 and pull bar auricle 2 disappears, and pushes away spring 17 and becomesFree state, under the effect that pushes away spring 17, pull bar 22 rotates around bearing pin 23, due to gag lever post19 are through in the circular hole of three-jaw structural member auricle 1, thus the motion of pull bar 22 only can one among a small circle inFreely-movable. Meanwhile, under the effect that pushes away spring 17, can ensure after release, adjust screw 21Head of screw no longer contact with the trigger arm of microswitch 25, thus guarantee that microswitch provides correct solutionLock signal.
Claims (2)
1. a spacecraft equipment supporting component release stopping means, is characterized in that: comprise three-jaw knotMember auricle (1), pull bar auricle (2), firer's cutter (3), pressed seat (4), compressor arm (12),Compressor arm stopping means, pull bar stopping means;
Compressor arm stopping means is divided into upper and lower two parts, upper part by clamping cap (5), honeycomb pad (6),Pad (7), volute spring (8) composition, honeycomb pad (6), pad (7), volute spring (8) are successivelyPut into clamping cap (5), clamping cap (5) is connected in pull bar auricle (2) and goes up and be positioned at compressor arm(12) top; Lower part is by square nut (13), locating piece (14), cushion pad (15), pressed seatBonnet (16) composition, square nut (13), locating piece (14), cushion pad (15) are arranged on successivelyIn the groove of pressed seat (4) lower end, and fixing with pressed seat bonnet (16);
Three-jaw structural member auricle (1) has through hole, and high friction coatings sleeve-board (11) is glued to three-jaw knotMember auricle (1) through hole top, the pressed seat (4) that is provided with cavity is fixed on three-jaw structural member auricle(1) bottom, its cavity is relative with three-jaw structural member auricle (1) through hole; One of pull bar auricle (2)There is the ball-and-socket matching with ball pad (10) in face, and for placing ball pad (10), ball-and-socket bottom hasThrough hole; It is upper that firer's cutter (3) is fixedly mounted on pressed seat (4), by under compressor arm stopping meansAfter part is in place, it is upper that afterburning nut (9), ball pad (10) are enclosed within compressor arm (12) successively,Compressor arm (12) successively through pull bar auricle (2) ball-and-socket bottom through-hole, high friction coatings sleeve-board (11),The cutting hole of three-jaw structural member auricle (1) through hole, pressed seat (4) cavity and firer's cutter (3),In the screw thread of its lower end precession compressor arm stopping means square nut (13), afterburning nut (9) has screwedAfter one-tenth, compressor arm stopping means upper part is in place;
Pull bar stopping means is by pushing away spring (17), spacing shim (18), limiting buffer pad (20)And gag lever post (19) composition, limiting buffer pad (20) is glued on the termination of gag lever post (19),Gag lever post (19) successively through circular hole, the spacing shim (18) of pull bar auricle (2), push away spring(17), be tightened on three-jaw structural member auricle (1) by screw thread.
2. a kind of spacecraft equipment supporting component release stopping means as claimed in claim 1, its spyLevy and be: on microswitch (25), be welded with a resistance, microswitch (25) is connected in three-jawStructural member auricle (1) is upper, adjusts screw (21) and is arranged on pull bar auricle (2) above, at afterburning spiral shellAfter female (9) pretension puts in place, head of screw withstands on the trigger arm of microswitch (25).
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105659761B true CN105659761B (en) | 2013-02-27 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043744A (en) * | 2016-07-11 | 2016-10-26 | 上海宇航系统工程研究所 | Point type satellite and rocket connection unlocking mechanism |
| CN108860660A (en) * | 2018-06-26 | 2018-11-23 | 上海卫星工程研究所 | Soft type compresses the tension compensating mechanism of relieving mechanism |
| CN109305391A (en) * | 2018-08-08 | 2019-02-05 | 上海宇航系统工程研究所 | Compress relieving mechanism and its method |
| CN110203402A (en) * | 2019-05-27 | 2019-09-06 | 上海宇航系统工程研究所 | A kind of tank load support with explosion-proof buffering function |
| CN109606744B (en) * | 2018-12-17 | 2020-09-18 | 北京卫星制造厂有限公司 | Device for automatically pre-tightening solar wing compression rod |
| CN113753270A (en) * | 2021-09-13 | 2021-12-07 | 北京空间飞行器总体设计部 | Wide-temperature-range high-rigidity statically determinate type pressing system |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043744A (en) * | 2016-07-11 | 2016-10-26 | 上海宇航系统工程研究所 | Point type satellite and rocket connection unlocking mechanism |
| CN108860660A (en) * | 2018-06-26 | 2018-11-23 | 上海卫星工程研究所 | Soft type compresses the tension compensating mechanism of relieving mechanism |
| CN108860660B (en) * | 2018-06-26 | 2020-05-29 | 上海卫星工程研究所 | Tension compensation device of flexible compression release mechanism |
| CN109305391A (en) * | 2018-08-08 | 2019-02-05 | 上海宇航系统工程研究所 | Compress relieving mechanism and its method |
| CN109305391B (en) * | 2018-08-08 | 2021-12-21 | 上海宇航系统工程研究所 | Compression release mechanism and method thereof |
| CN109606744B (en) * | 2018-12-17 | 2020-09-18 | 北京卫星制造厂有限公司 | Device for automatically pre-tightening solar wing compression rod |
| CN110203402A (en) * | 2019-05-27 | 2019-09-06 | 上海宇航系统工程研究所 | A kind of tank load support with explosion-proof buffering function |
| CN113753270A (en) * | 2021-09-13 | 2021-12-07 | 北京空间飞行器总体设计部 | Wide-temperature-range high-rigidity statically determinate type pressing system |
| CN113753270B (en) * | 2021-09-13 | 2023-08-29 | 北京空间飞行器总体设计部 | Wide-temperature-range high-rigidity statically-determined compression system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR03 | Grant of secret patent right | ||
| DC01 | Secret patent status has been lifted | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130227 Termination date: 20181112 |