CN101823566A - Locking and unlocking device for solar array - Google Patents
Locking and unlocking device for solar array Download PDFInfo
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- CN101823566A CN101823566A CN 201010142090 CN201010142090A CN101823566A CN 101823566 A CN101823566 A CN 101823566A CN 201010142090 CN201010142090 CN 201010142090 CN 201010142090 A CN201010142090 A CN 201010142090A CN 101823566 A CN101823566 A CN 101823566A
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Abstract
The invention provides a locking and unlocking device for a solar array, which is used for locking and unlocking the solar array and a space vehicle body structure, and comprises a first fixed part and a second fixed part, wherein the first fixed part is provided with a first through hole, a first caulking groove and a second caulking groove, the first caulking groove and the second caulking groove are respectively communicated with the first through hole; an electromagnet, a spacing spring assembly and a locking pin are sequentially installed in the first through hole; a cable and a connector which are electrically connected with the electromagnet are installed in the first caulking groove; a second through hole is arranged on one end part of the second fixed part, and the end part can be inserted into the second caulking groove of the first fixed part so that the second through hole and the first through hole are coaxial; and the locking pin can simultaneously penetrate through the first through hole and the second through hole, and realize axial movement under the action of the electromagnet and the spacing spring assembly. The invention can reduce the complex degree of system design, can improve the system reliability and can carry out easy and effective ground tests.
Description
Technical field
The present invention relates to a kind of solar array locking and tripper, be used for body construction locking or release solar array and space vehicle.
Background technology
The locking of solar array and tripper play an important role in the emission of space vehicle and operational process, and blocking device lost efficacy and then causes the abortive launch of aircraft, and tripper lost efficacy and then can have a strong impact on the life-span of aircraft in rail flight.At present, the locking of the solar array of widespread use mainly adopts bolt of rear end plate to lock, adopt the mode of priming system cutting to carry out release with tripper on space vehicle; Before space vehicle is packed vehicle into, by bolt of rear end plate solar array is locked onto on the body construction of space vehicle, make solar array be in the rounding state of locking; After space vehicle enters planned orbit, in the time of solar array need being launched, sending the priming system control command lights a fire priming system, pressure-driven priming system in-to-in cutter by priming system igniting generation, lock(ing) bolt is cut off, solar array is launched under the torsional interaction of development mechanism, realize the release of solar array; Yet this type of locking is all disposed a plurality of firer's devices to guarantee the reliability of releasing process in each latched position usually with tripper, can increase complex degree of system design for this reason; Simultaneously, owing to adopted firer's device, increased the difficulty of ground test process again, carrying out a ground firer tests to unfurl and costs an arm and a leg, and this firer's device can not repeated usage after finishing test, needs firer's device that more renew again, has increased the cost of aircraft development.
Summary of the invention
The object of the present invention is to provide a kind of locking and tripper of solar array, it adopts locking pin, limit spring assembly and electromagnet is the locking and the unlock method of core component, reduce complex degree of system design, improve system reliability, can carry out simple and effective reperformance test, and reduce the cost of aircraft development.
For reaching above-mentioned purpose, a kind of solar array locking of the present invention and tripper are used for body construction locking or release with solar array and space vehicle, and it comprises:
First connecting element, it has one first through hole, one first caulking groove and one second caulking groove, this first caulking groove and this second caulking groove are connected with this first through hole respectively, electromagnet, limit spring assembly and locking pin are installed in this first through hole successively, cable and adaptor union are installed in first caulking groove, and this cable and adaptor union and this electromagnet electrically connect; And
Second connecting element, has one second through hole on one end of this second connecting element, second caulking groove of this first connecting element can be inserted in this end, make this second through hole coaxial with this first through hole, this locking pin can run through this first through hole and this second through hole simultaneously, and this locking pin can be realized axial moving forward and backward in the combined action of this electromagnet and this limit spring assembly.。
Described solar array locking and tripper, wherein, this locking pin detachably and by a lug cap is fixed in this first through hole.
Described solar array locking and tripper, wherein, this locking pin is a ferromagnetic material.
Described solar array locking and tripper, wherein, this electromagnet is fixedly installed in this first through hole.
Described solar array locking and tripper, wherein, this first connecting element is installed on by tightening screw on the body construction of space vehicle, and this second connecting element is installed on the solar array by tightening screw.
Described solar array locking and tripper, wherein, the length of this locking pin is greater than the size of this second caulking groove along the first through-bore axis direction.
Beneficial effect of the present invention is: it adopts locking pin, limit spring assembly and electromagnet is the locking and the unlock method of core component, reduced complex degree of system design, improved system reliability, can carry out simple and effective reperformance test, and reduce the cost of aircraft development.
Description of drawings
Fig. 1 is the structural representation of space vehicle;
Fig. 2 is the section-drawing of first connecting element of locking of the present invention and tripper;
Fig. 3 is the section-drawing of second connecting element of locking of the present invention and tripper;
Fig. 4 is locking of the present invention and tripper single-piece section-drawing.
Description of reference numerals: 1-space vehicle body construction; 2-solar array development mechanism; The 3-solar array; 4-locking and tripper; 41-first connecting element; 411-first through hole; 412-first caulking groove; 413-second caulking groove; 42-second connecting element; The 421-end; 422-second through hole; The 5-tightening screw; 6-cable and adaptor union; The 7-electromagnet; 8-limit spring assembly; 9-locks pin; The 10-lug cap.
The specific embodiment
Below in conjunction with the description of drawings specific embodiment.
Fig. 1 is the structural representation of space vehicle, space vehicle body construction 1 is connected by development mechanism 2 with solar array 3, the jump ring that is used for fixing after required moment of torsion and solar array 3 launched to put in place when development mechanism 2 was used to provide solar array 3 to launch, locking can be locked in the fixed position with tripper 4 with solar array 3 before space vehicle enters planned orbit, then solar array 3 is discharged when needing to unfurl after aircraft is entered the orbit.
As Fig. 2, Fig. 3 and Figure 4 shows that first connecting element, second connecting element and the single-piece section-drawing of locking of the present invention and tripper, wherein, locking mainly comprises first connecting element 41 and second connecting element 42 with tripper 4, have one first through hole 411, one first caulking groove 412 and one second caulking groove 413 on this first connecting element 41, this first caulking groove 412 and this second caulking groove 413 are connected with this first through hole 411 respectively.Have one second through hole 422 on one end 421 of this second connecting element 6, insert after this second caulking groove 413 this end 421, and this second through hole 422 is coaxial with this first through hole 411.
First connecting element 41 is installed on the space vehicle body construction 1 by tightening screw 5, second connecting element 42 is installed on the solar array 3 by tightening screw 5, when locking pin 9 is installed, pin 9 be should lock and first through hole 411 and second through hole 422 run through simultaneously, finish locking and release by 9 axial the moving forward and backward of locking pin, thereby realize the locking and unlocking function of solar array 3.
After locking pin 9 is installed, limit spring assembly 8 is in impaction state, locking pin 9 is in stabilized conditions under the combined action of lug cap 10 and limit spring assembly 8, first connecting element 41 and second connecting element 42 are limited within the specific limits, thereby realized the locking of solar array 3.
When the release of needs solar array, produce electromagnetic force by cable and adaptor union 6 control electromagnet 7, locking pin 9 is to the direction motion of electromagnet 7 under the effect of electromagnetic force, after going out of lock the restriction of pin 9, second connecting element 42 under the torsional interaction of development mechanism 2, moves with solar array 3, finish separating of first connecting element 5 and second connecting element 6, thereby realize the release of solar array 3; Fix by the jump ring in the development mechanism 2 after putting in place when solar array 3 reverses, and after providing the signal indication that launches to put in place, can stop control, make locking pin 9 under the effect of limit spring assembly 8, reset to stabilized conditions electromagnet 7.Wherein, the length of this locking pin 9 discharges from this second caulking groove 413 to prevent this locking pin 9 greater than the size of this second caulking groove 413 along first through hole, 411 axis directions.
When the locking of solar array 3 and release test are carried out in ground, can realize that first connecting element 41 and second connecting element 42 lock again by the crank motion of drive controlling electromagnet 7 repeatedly, also can realize that first connecting element 41 and second connecting element 42 lock again by unloading lug cap 10.
Only the above, only be preferred embodiment of the present invention, when can not limiting scope of the invention process, so the displacement of the change of numerical value or equivalent elements such as with this, or, all should still belong to the category that patent of the present invention contains according to equalization variation and modification that the present patent application claim is done.
Claims (6)
1. a solar array locks and tripper, is used for the locking or the release of solar array and space vehicle body construction, it is characterized in that, comprises:
First connecting element, it has one first through hole, one first caulking groove and one second caulking groove, this first caulking groove and this second caulking groove are connected with this first through hole respectively, electromagnet, limit spring assembly and locking pin are installed in this first through hole successively, cable and adaptor union are installed in first caulking groove, and this cable and adaptor union and this electromagnet electrically connect; And
Second connecting element, has one second through hole on one end of this second connecting element, second caulking groove of this first connecting element can be inserted in this end, makes this second through hole coaxial with this first through hole, and this locking pin can run through this first through hole and this second through hole simultaneously.
2. solar array locking according to claim 1 and tripper is characterized in that this locking pin detachably and by a lug cap is fixed in this first through hole.
3. solar array locking according to claim 1 and tripper is characterized in that this locking pin is a ferromagnetic material.
4. solar array locking according to claim 1 and tripper is characterized in that this electromagnet is fixedly installed in this first through hole.
5. solar array locking according to claim 1 and tripper is characterized in that this first connecting element is installed on by tightening screw on the body construction of space vehicle, and this second connecting element is installed on the solar array by tightening screw.
6. solar array locking according to claim 1 and tripper is characterized in that the length of this locking pin is greater than the size of this second caulking groove along the first through-bore axis direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010142090 CN101823566A (en) | 2010-03-30 | 2010-03-30 | Locking and unlocking device for solar array |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010142090 CN101823566A (en) | 2010-03-30 | 2010-03-30 | Locking and unlocking device for solar array |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101823566A true CN101823566A (en) | 2010-09-08 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201010142090 Pending CN101823566A (en) | 2010-03-30 | 2010-03-30 | Locking and unlocking device for solar array |
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| CN (1) | CN101823566A (en) |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102578953A (en) * | 2011-11-25 | 2012-07-18 | 李飞宇 | Magnetic lock connecting device of cover board component and fast dismantling method employing magnetic lock |
| CN104579145A (en) * | 2015-01-09 | 2015-04-29 | 浙江宏阳新能源科技有限公司 | Solar energy collection device easy to disassemble and wash |
| CN107143161A (en) * | 2017-06-22 | 2017-09-08 | 周存慧 | Combined type stage |
| CN107323699A (en) * | 2017-07-06 | 2017-11-07 | 北京吾天科技有限公司 | One kind repeats locking with stopping feedback complex device |
| CN108506287A (en) * | 2018-04-19 | 2018-09-07 | 南京邮电大学 | A kind of electromagnetic type solar energy pole plate locking device |
| CN108528739A (en) * | 2018-03-09 | 2018-09-14 | 芜湖翼讯飞行智能装备有限公司 | A kind of quick-disassembly structure for unmanned machine head |
| CN109394152A (en) * | 2018-09-30 | 2019-03-01 | 杭州行开科技有限公司 | A kind of medical endoscope sealing structure |
| CN110030236A (en) * | 2019-04-30 | 2019-07-19 | 上海利正卫星应用技术有限公司 | Reciprocating locking device and its application method |
| CN111301724A (en) * | 2019-12-12 | 2020-06-19 | 哈尔滨工业大学 | Novel connection unlocking mechanism based on electromagnetic drive |
| CN112288067A (en) * | 2020-10-20 | 2021-01-29 | 张黎 | Intelligent gun management system based on Internet of things technology |
| CN112431355A (en) * | 2020-11-23 | 2021-03-02 | 上海绿地建设(集团)有限公司 | Concrete column capable of preventing displacement and shearing |
| CN112918704A (en) * | 2021-01-22 | 2021-06-08 | 中国科学院沈阳自动化研究所 | Mechanism for optimizing spacecraft solar sailboard to overcome rocket launching mechanical environment |
| CN114572417A (en) * | 2022-03-23 | 2022-06-03 | 沃飞长空科技(成都)有限公司 | Quick locking device and aircraft comprising same |
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| FR2707250A1 (en) * | 1993-04-26 | 1995-01-13 | Hughes Aircraft Co | Variable-angle locking mechanism for spacecraft |
| JP2000351398A (en) * | 1999-06-10 | 2000-12-19 | Toshiba Corp | Unfolding mechanism latch device |
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| US6896441B1 (en) * | 2002-08-14 | 2005-05-24 | Lockheed Martin Corporation | Automated latching device with active damping |
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Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102578953A (en) * | 2011-11-25 | 2012-07-18 | 李飞宇 | Magnetic lock connecting device of cover board component and fast dismantling method employing magnetic lock |
| CN104579145A (en) * | 2015-01-09 | 2015-04-29 | 浙江宏阳新能源科技有限公司 | Solar energy collection device easy to disassemble and wash |
| CN107143161A (en) * | 2017-06-22 | 2017-09-08 | 周存慧 | Combined type stage |
| CN107323699B (en) * | 2017-07-06 | 2020-01-14 | 北京吾天科技有限公司 | Repeated locking and stopping feedback composite device |
| CN107323699A (en) * | 2017-07-06 | 2017-11-07 | 北京吾天科技有限公司 | One kind repeats locking with stopping feedback complex device |
| CN108528739A (en) * | 2018-03-09 | 2018-09-14 | 芜湖翼讯飞行智能装备有限公司 | A kind of quick-disassembly structure for unmanned machine head |
| CN108506287A (en) * | 2018-04-19 | 2018-09-07 | 南京邮电大学 | A kind of electromagnetic type solar energy pole plate locking device |
| CN109394152A (en) * | 2018-09-30 | 2019-03-01 | 杭州行开科技有限公司 | A kind of medical endoscope sealing structure |
| CN110030236A (en) * | 2019-04-30 | 2019-07-19 | 上海利正卫星应用技术有限公司 | Reciprocating locking device and its application method |
| CN111301724A (en) * | 2019-12-12 | 2020-06-19 | 哈尔滨工业大学 | Novel connection unlocking mechanism based on electromagnetic drive |
| CN111301724B (en) * | 2019-12-12 | 2021-06-15 | 哈尔滨工业大学 | Connection unlocking mechanism based on electromagnetic drive |
| CN112288067A (en) * | 2020-10-20 | 2021-01-29 | 张黎 | Intelligent gun management system based on Internet of things technology |
| CN112431355A (en) * | 2020-11-23 | 2021-03-02 | 上海绿地建设(集团)有限公司 | Concrete column capable of preventing displacement and shearing |
| CN112431355B (en) * | 2020-11-23 | 2022-04-12 | 上海绿地建设(集团)有限公司 | Concrete column capable of preventing displacement and shearing |
| CN112918704A (en) * | 2021-01-22 | 2021-06-08 | 中国科学院沈阳自动化研究所 | Mechanism for optimizing spacecraft solar sailboard to overcome rocket launching mechanical environment |
| CN114572417A (en) * | 2022-03-23 | 2022-06-03 | 沃飞长空科技(成都)有限公司 | Quick locking device and aircraft comprising same |
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Application publication date: 20100908 |