CN110239747B - Point type microsatellite separation unlocking device - Google Patents
Point type microsatellite separation unlocking device Download PDFInfo
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- CN110239747B CN110239747B CN201910441771.7A CN201910441771A CN110239747B CN 110239747 B CN110239747 B CN 110239747B CN 201910441771 A CN201910441771 A CN 201910441771A CN 110239747 B CN110239747 B CN 110239747B
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- 238000000926 separation method Methods 0.000 title claims abstract description 31
- 108091092878 Microsatellite Proteins 0.000 title claims abstract description 30
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- 238000010494 dissociation reaction Methods 0.000 description 10
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- 239000002360 explosive Substances 0.000 description 9
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- 230000007246 mechanism Effects 0.000 description 6
- 230000000977 initiatory effect Effects 0.000 description 5
- 238000000034 method Methods 0.000 description 4
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- 239000012188 paraffin wax Substances 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 238000005265 energy consumption Methods 0.000 description 2
- 230000005389 magnetism Effects 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 230000004044 response Effects 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 238000001612 separation test Methods 0.000 description 2
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/645—Separators
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Abstract
本发明公开了一种点式微小卫星分离解锁装置，包括摆杆装置和电磁铁装置；所述摆杆装置包括第一摆杆、支架、拉簧、两个轴承和两个销轴，支架固定在适配器上；第一摆杆为7字形杆，其中部设有第一通孔，顶端错位设有第二通孔，第一通孔通过销轴与支架转动连接，第二通孔设有销轴，销轴两端设有轴承，轴承压在卫星结构上可紧锁卫星Z方向，第一摆杆下端外壁铣出一个竖直平面，拉簧一端固定在竖直平面上，另一端连接适配器上。本发明具有结构简单、运行可靠、冲击小、可重复性、成本低的优点。
The invention discloses a point-type micro-satellite separation and unlocking device, comprising a pendulum rod device and an electromagnet device; the pendulum rod device comprises a first pendulum rod, a bracket, a tension spring, two bearings and two pin shafts, and the bracket is fixed On the adapter; the first swing rod is a 7-shaped rod, with a first through hole in the middle, a second through hole at the top dislocation, the first through hole is rotatably connected to the bracket through a pin shaft, and the second through hole is provided with a pin There are bearings at both ends of the shaft and the pin shaft. The bearings are pressed on the satellite structure to lock the Z direction of the satellite. A vertical plane is milled out of the outer wall of the lower end of the first pendulum rod. One end of the tension spring is fixed on the vertical plane, and the other end is connected to the adapter superior. The invention has the advantages of simple structure, reliable operation, small impact, repeatability and low cost.
Description
Technical Field
The invention relates to a satellite and carrier rocket separation unlocking device, in particular to a point type microsatellite separation unlocking device.
Background
Since the 20 th century and the 80 th century, with the rapid development of technologies such as microelectronics, micromachines, precision machining, light materials, high-efficiency energy and the like, the miniaturization of instruments and equipment required on satellites is promoted, the modern satellite technology is developing towards the direction of shorter period, lower cost, smaller volume and stronger flexibility, and the development of microsatellites is rapidly rising worldwide. The unlocking separation technology, which is one of the key technologies of the satellite, is a core technology related to successful launching and normal orbit entering of the satellite, and has an important influence on the overall performance of the satellite. Therefore, the unlocking and separating device with small separating impact and high reliability has important significance.
The satellite separation unlocking device is a mechanism device which can reliably connect a satellite and a rocket and can realize reliable separation of the satellite and the rocket after the satellite and the rocket enter the orbit, and plays an important role in satellite projects. At present, the separation of the traditional satellite and the carrier rocket in the world usually adopts a separation mode of combining straps and explosive bolts. The separation technology is mature and is widely applied to large satellites. However, as the size and the weight of the satellite become smaller and smaller, the traditional belt locking device cannot meet the launching separation requirement of the microsatellite. Moreover, the separation mechanism based on the explosive bolt can generate large uncertain impact force at the moment of explosion of the explosive bolt and some uncontrolled fragments, which can bring certain damage to the satellite to be separated and the adapter of the rocket. Particularly, in the process of launching one rocket multi-satellite, other satellites can be damaged.
In order to overcome the technical limitations of the initiating explosive device compressing and releasing device and meet the compressing and releasing requirements of the next generation of spacecraft high-precision equipment, the novel non-initiating explosive compressing and releasing device which is low in impact, free of pollution and capable of being repeatedly used is rapidly developed in nearly thirty years. According to the driving source difference, can compress tightly release with non-priming sytem and divide into: fuse wire (fuse wire), hot knife (thermal knife), paraffin (paraffin) and shape memory alloy compression release devices. The fuse device cannot be reset quickly, and can be reused only by replacing components or returning to a factory for reassembly; the paraffin device has large volume, long release time and large energy consumption; the hot knife device has small bearing capacity, long release time and large energy consumption. Compared with the prior art, the compressing and releasing device based on the shape memory alloy has the technical characteristics of large bearing capacity, quick release, low power consumption, low impact, resettability and no pollution, is one of the most technical advantages of the compressing and releasing device for the non-explosive work pieces, and is also a research hotspot internationally in recent years.
The memory alloy is used as an actuating element on the separation release mechanism, and works outwards by utilizing the deformation restoring force and the stroke generated by the phase change of the memory alloy. There are generally 3 forms of memory alloy elements: memory alloy rod, memory alloy silk and memory alloy spring. The successful memory alloy actuators that have been studied are based on these 3 elements to achieve the separation function. The memory alloy actuator has the advantages of safety, low impact, reusability and the like, can replace part of initiating explosive devices used on a spacecraft separation mechanism, is suitable for occasions without strict limitation on separation time, but is not suitable for mechanisms requiring large stress and displacement. At present, the research on the aspect is carried out in China, and some products enter the engineering verification stage, so that the method has wide application prospect on small and micro-satellite spacecrafts and the like in the future.
The electromagnetic lock device has a good prospect in the field of aerospace. The electromagnetic lock device adopts a power-off electromagnet which is equivalent to a permanent magnet before being electrified, the metal block can be attracted by magnetism, after the electromagnet is electrified, a power-on coil generates a magnetic field opposite to the magnetism of the permanent magnet, so that the magnetic field of the permanent magnet is counteracted, the metal block cannot be attracted by the power-off electromagnet, and the power-off electromagnet can be applied to some unlocking devices by matching with some structures.
Disclosure of Invention
The invention aims to provide a point type microsatellite separating and unlocking device, which utilizes the suction force of a power-off electromagnet to be combined with a lever and a bearing, tightly locks the Z direction with larger satellite load, better controls the load transmission direction, and utilizes the tension of a spring to drive the bearing to roll when the electromagnet is powered off so as to realize satellite unlocking.
The technical solution for realizing the purpose of the invention is as follows: a point type microsatellite separating and unlocking device comprises a swing rod device and an electromagnet device; the swing rod device comprises a first swing rod, a bracket, a tension spring, a first pin shaft, a second pin shaft and two bearings, and the bracket is fixed on the adapter; the first swing rod is a 7-shaped rod, a first through hole is formed in the middle of the first swing rod, a second through hole is formed in the top end of the first swing rod in a staggered mode, the first through hole is rotatably connected with the support through a first pin shaft, a second pin shaft is arranged in the second through hole, bearings are arranged at two ends of the second pin shaft, the bearings are pressed on the satellite structure and can lock the Z direction of a satellite, a vertical plane is milled out of the outer wall of the lower end of the first swing rod, one end of a tension spring is fixed on the vertical plane, and the other end of the tension spring is connected with an adapter.
Compared with the prior art, the invention has the remarkable advantages that:
(1) the micro-satellite antenna has the advantages of simple structure, good reliability, low processing cost and strong practicability, and accords with the design concepts of low cost, quick response and short period of the micro-satellite.
(2) The invention is adaptively installed on the adapter, can be used as a separation unlocking device of a satellite and rocket separation mechanism suitable for satellites with various shapes, and has higher universality.
(3) The invention adopts the power-off electromagnet, and the unlocking response time is short.
(4) The invention adopts the power-off electromagnet, and has the advantages of low impact, high safety and the like.
(5) The power-off electromagnet is adopted in the invention, the satellite separation test carried out on the ground can be repeatedly used, and the time and cost for replacing the initiating explosive devices in the separation test of the traditional separation unlocking device are saved.
(6) The separating and unlocking device does not participate in axial (satellite X, Y direction) bearing, and Z-direction load of the satellite is mainly borne by the bearing, the pin shaft, the swing rod and the bracket and is not transmitted to the small bearing, so that the electromagnet is mainly under the tension of the small tension spring and bears little load.
(7) The invention has no initiating explosive device, no debris, no pollution and no interference to the satellite.
Drawings
Fig. 1 is a schematic view of an assembly of a point-type microsatellite separation unlocking device, an adapter and a satellite.
Fig. 2 is an overall schematic view of a point-type microsatellite separation unlocking device according to the invention.
Fig. 3 is a side view of a point-type microsatellite separation unlocking device of the present invention.
FIG. 4 is a schematic view of an electromagnet device of the point type microsatellite partial dissociation locking device according to the present invention.
FIG. 5 is a schematic view of an electromagnet device in the point type microsatellite partial dissociation locking device of the present invention.
FIG. 6 is a schematic view of a swing link structure in the point microsatellite partial dissociation locking apparatus of the present invention.
FIG. 7 is a schematic view of a bracket structure of a point-type microsatellite dissociation locking apparatus according to the present invention.
FIG. 8 is a schematic view of a mounting frame of the point-type microsatellite dissociation locking apparatus of the present invention.
Fig. 9 is a schematic view of the inner frame structure of a point type microsatellite dissociation locking apparatus of the present invention, wherein (a) is a first side view and (b) is a second side view.
FIG. 10 is a schematic view of a small swing link in the point microsatellite partial dissociation locking apparatus of the present invention.
FIG. 11 is a schematic view of a suction block structure of a point-type microsatellite dissociation locking apparatus according to the present invention.
FIG. 12 is a schematic view of an electromagnet device in a point-type microsatellite dissociation lock apparatus according to the present invention, wherein (a) is before unlocking and (b) is after unlocking.
Fig. 13 is a schematic view of a swing link device in the point-type microsatellite separation and dissociation locking device of the invention, wherein (a) is before unlocking and (b) is after unlocking.
Detailed Description
The present invention is described in further detail below with reference to the attached drawing figures.
Referring to fig. 1 to 13, the invention relates to a point type microsatellite separation unlocking device, which comprises a swing rod device 2 and an electromagnet device 1. With reference to fig. 2 and 3, the swing link device 2 includes a first swing link 201, a bracket 202, a tension spring 205, a first pin, a second pin, and two bearings 203. Referring to fig. 7, the bracket 202 is fixed to the adapter 3. The reference numerals for both pins are 204.
With reference to fig. 6, 2 and 3, the first swing rod 201 is a 7-shaped rod, a first through hole is formed in the middle of the first swing rod, a second through hole is formed in the top of the first swing rod in a staggered mode, the first through hole is rotatably connected with the support 202 through a first pin shaft, a second pin shaft is arranged in the second through hole, bearings 203 are arranged at two ends of the second pin shaft, the bearings 203 are pressed on the satellite 4 structure and can tightly lock the satellite 4Z direction, a vertical plane is milled on the outer wall of the lower end of the first swing rod 201, one end of a tension spring 205 is fixed on the vertical plane, and the other end of the tension spring is connected to the adapter 3. The round hole of the swing rod 201 connected with the support 202 is located at the upper part of the rod body, the arm of force of the swing rod 201 rotating around the pin 204 fixed on the support 202 is longer, and the tension spring 205 saves labor. The bearing 203 is used for pressing on the satellite 4 structure, but the swing rod 201 is not directly pressed on the satellite 4 structure, the rolling friction of the bearing 203 is small, labor is saved, and the tension spring 205 can be unlocked easily. When the type of the tension spring 205 is selected, the requirement on tension is not high.
The pin shaft 204 is small in size and large in stress, and is made of titanium alloy.
The first swing link 201 is provided with a weight reduction groove.
With reference to fig. 2, 4 and 5, the electromagnet device 1 includes a mounting frame 101, an electromagnet 102, a suction block 103, a long shaft 104, a second swing link 105, a second bearing 107, an inner frame 108, a second tension spring 109, a first short shaft, and a second short shaft, where reference numerals of the two short shafts are denoted by 106.
Referring to fig. 8, the mounting frame 101 is a rectangular frame, the middle portions of the frame are connected by a block 110, and the block 110 is provided with a threaded hole for mounting the inner frame 108.
Referring to fig. 9 and 12, the inner frame 108 is a block, and one side of the inner frame is provided with an arc opening matched with the arc outer wall surface of the lower portion of the first swing link 201, and the other side of the inner frame is provided with an inclined surface for controlling the rotation angle of the second swing link 105.
Referring to fig. 10, 4 and 5, the second swing link 105 is a 7-shaped rod, the middle portion of the second swing link is provided with a first round hole which is rotatably connected with the inner frame 108 through a long shaft 104, one end of the second swing link is provided with a second round hole coaxial with the first round hole and rotatably connected with the suction block 103 through a first short shaft, the other end of the second swing link is provided with a third round hole in a staggered manner, a second short shaft is arranged in the third round hole, the second short shaft is provided with a second bearing 107, one end of a second tension spring 109 is connected with the end portion of the second swing link 105 connected with the suction block 103, and the other end of the second tension spring 109 is fixed on the mounting frame 101.
Referring to fig. 5 and 12, the second bearing 107 presses the first swing link 201 to limit the rotation of the first swing link 201. The second bearing 107 is used for pressing the first swing link 201 instead of directly pressing the second swing link 105 on the first swing link 201, the rolling friction of the second bearing 107 is small, labor is saved, and the second tension spring 109 can be unlocked easily. And when the second tension spring 109 is selected, the requirement on tension is not high.
The second swing link 105 is provided with a weight reduction groove.
The electromagnet 102 is cylindrical, and one end thereof is fixed in the mounting frame 101 by a screw.
Referring to fig. 11, the suction block 103 is a disc shape, one smooth surface of which can be tightly sucked by the electromagnet 102, and the other surface of which is provided with a through hole, and can be rotatably connected with the end of the second swing link 105 through a short shaft 106.
The force pressing the first swing link 201 in the electromagnet device 1 is the tension of the tension spring 205, and is mainly applied by the second swing link 105, the second bearing 107, the inner frame 108 and the two short shafts 106. The suction block 103 is mainly pulled by the second tension spring 109, and the electromagnetic force of the electromagnet 102 needs to be greater than the tension of the second tension spring 109.
The working process of the invention is as follows: and (3) locking state: as shown in fig. 12 (a), the electromagnet 102 attracts the attraction block 103, the attraction block 103 is rotatably connected to the second swing link 105 to limit the rotation of the second swing link 105, the second bearing 107 fixed to the top of the second swing link 105 can press the first swing link 201 to limit the rotation of the first swing link 201 around the bracket 202, and the first swing link 201 can be locked to the satellite 4Z direction, as shown in fig. 13 (a). In the carrier rocket, loads in all directions generated by the carrier rocket are applied to the connection of the satellite 4 and the separation unlocking device, the load in the Z direction is transmitted to the bearing 203 from the structure of the satellite 4, then transmitted to the pin shaft 204 and the swing rod 201, and then transmitted to the pin shaft 204 and the bracket 202, and the electromagnet device 1 only pulls the tension spring 205, which is far smaller than the load of the carrier rocket.
An unlocking process: after an unlocking signal is obtained, as shown in fig. 12 (b), the electromagnet 102 is electrified and demagnetized, and does not attract the attraction block 103 any more, the second swing link 105 rotates around the long shaft 104 fixed to the inner frame 108 under the tension of the second tension spring 109, and rotates to contact with the inclined plane arranged on the inner frame 108, the second bearing 107 at the top of the second swing link 105 rolls away from the first swing link 201, as shown in fig. 13 (b), the first swing link 201 loses the locking of the second bearing 107, rotates around the bracket 202 under the tension of the tension spring 205, the bearing 203 fixed at the top of the first swing link 201 rolls away from the satellite 4 structure, and the satellite 4 is unlocked.
Claims (5)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910441771.7A CN110239747B (en) | 2019-05-24 | 2019-05-24 | Point type microsatellite separation unlocking device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910441771.7A CN110239747B (en) | 2019-05-24 | 2019-05-24 | Point type microsatellite separation unlocking device |
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| CN110239747A CN110239747A (en) | 2019-09-17 |
| CN110239747B true CN110239747B (en) | 2022-04-01 |
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| CN201910441771.7A Active CN110239747B (en) | 2019-05-24 | 2019-05-24 | Point type microsatellite separation unlocking device |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112319864B (en) * | 2020-09-29 | 2022-10-21 | 上海航天控制技术研究所 | Space protection cover device adopting synchronous unlocking double pin pulling devices |
| CN113086254B (en) * | 2021-04-14 | 2022-09-02 | 电子科技大学 | Simple unlocking device for aviation environment |
| CN115196054B (en) * | 2022-09-16 | 2023-03-10 | 北京宇航系统工程研究所 | Electricity separation mechanism that drives |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5145227A (en) * | 1990-12-31 | 1992-09-08 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Electromagnetic attachment mechanism |
| US7104505B2 (en) * | 2001-11-01 | 2006-09-12 | Michigan Aerospace Corporation | Autonomous satellite docking system |
| CN106742081B (en) * | 2016-11-29 | 2021-02-05 | 航天东方红卫星有限公司 | Separating mechanism based on unlocking of rotary pressure ring |
| CN107054700A (en) * | 2017-03-30 | 2017-08-18 | 哈尔滨工业大学（威海） | A kind of satellite and the rocket separation locking releasing device |
| CN107215485B (en) * | 2017-05-31 | 2019-07-12 | 北京空间飞行器总体设计部 | A passive trigger locking device |
| CN107839905B (en) * | 2017-09-30 | 2019-10-29 | 北京空间飞行器总体设计部 | The low impact of one kind compresses release device from separation rod-type |
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