CN110963090B - Redundant unlocking and time sequence control releasing mechanism for small satellite transmission - Google Patents
Redundant unlocking and time sequence control releasing mechanism for small satellite transmission Download PDFInfo
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- CN110963090B CN110963090B CN201911067305.3A CN201911067305A CN110963090B CN 110963090 B CN110963090 B CN 110963090B CN 201911067305 A CN201911067305 A CN 201911067305A CN 110963090 B CN110963090 B CN 110963090B
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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
Abstract
The invention relates to a release mechanism for redundant unlocking and time sequence control of small satellite launching, belonging to the technical field of rocket launching; the device comprises a cabin door, a frame body, a hinged part, a push plate, a thrust spring, 4 sliding rails, a limiting device, a connecting rod, a pressing plate and an electromagnetic lock; the top end of the frame body is opened; the cabin door is arranged at the opening at the top end of the frame body; the hinged part is arranged at the joint of the cabin door and the frame body; the electromagnetic lock is arranged on the side wall of the frame body; the 4 sliding rails are axially arranged at the corners of 4 side walls in the frame body; the thrust spring is arranged at the bottom end in the frame body; the push plate is horizontally arranged at the top end of the thrust spring; the pressing plate is arranged at the bottom end inside the frame body; the connecting rod is vertically arranged at the top end of the pressing plate; the limiting device is arranged at the top end of the connecting rod; the limiting device drives the pressing plate to act together through the connecting rod; the invention provides an external cubic minisatellite releasing device which takes an electromagnet as a driving power source and has a redundant unlocking function, so that the reliability of the unlocking device is improved, and the launching success rate of an external cubic minisatellite is further improved.
Description
Technical Field
The invention belongs to the technical field of rocket launching, and relates to a release mechanism for redundant unlocking and time sequence control of small satellite launching.
Background
With the development of micro-nano technology and the promotion of application requirements, micro-nano satellites have the advantages of small size, low power consumption, short development period, low cost and the like, and are deeply researched and widely applied to the fields of scientific research, national defense, commercial use and the like. To provide greater opportunity for universities and research institutions to participate in space science practices, external cubic microsatellites refer to a microsatellite manufactured using proprietary design criteria (the first relevant criteria are set forth by professor Jodi Prig Saur, California University of technical State, Cal Poly.) standard external cubic microsatellites are of a "1U" architecture, i.e., 100 x 100mm in volume, and a weight of 1 Kg. based thereon, external cubic microsatellites can be upgraded to "2U" (200 x 100mm) and "3U" (300 x 100mm) architectures.
The external cubic minisatellite is usually launched in a one-rocket multi-satellite launching mode, namely, the external cubic minisatellite is carried and launched by utilizing the surplus carrying capacity of the rocket on the premise of meeting the requirement of a main satellite launching task. In order to launch the external cubic microsatellites into orbit in an efficient, convenient and economical manner, release separation of the external cubic microsatellites in space is usually achieved by means of mechanical launch using dedicated release devices. External cubic minisatellites have standard shape, size and weight requirements, which makes it possible to make standard, unified external cubic minisatellites launching devices.
The traditional moonlet release mechanism mainly separates by the initiating explosive device, has the defects of undetectable and undetectable property and severe impact environment, does not meet the requirement of repeated testing in a ground test, and cannot ensure the reliability of products due to too large load of initiating explosive device impact.
Disclosure of Invention
The technical problem solved by the invention is as follows: the release mechanism overcomes the defects of the prior art, provides a redundant unlocking and time sequence control release mechanism for the small satellite launching, takes an electromagnet as a driving power source, and improves the reliability of the unlocking device and the launching success rate of the external cubic small satellite by using the external cubic small satellite release device with the redundant unlocking function.
The technical scheme of the invention is as follows:
a release mechanism for redundant unlocking and time sequence control of microsatellite transmission comprises a cabin door, a frame body, a hinged part, a push plate, a thrust spring, 4 sliding rails, a limiting device, a connecting rod, a pressing plate and an electromagnetic lock; the frame body is of a hollow cuboid frame structure; the top end of the frame body is opened; the cabin door is arranged at the opening at the top end of the frame body; the hinged part is arranged at the joint of the cabin door and the frame body; the hatch door is turned over, opened and closed relative to the frame body; the electromagnetic lock is arranged on the side wall of the frame body; the electromagnetic lock realizes the locking and unlocking of the cabin door; the 4 sliding rails are axially arranged at the corners of 4 side walls in the frame body; the thrust spring is arranged at the bottom end in the frame body; the push plate is horizontally arranged at the top end of the thrust spring; the pressing plate is arranged at the bottom end inside the frame body; the pressing plate corresponds to the push plate in position; the connecting rod is vertically arranged at the top end of the pressing plate; the limiting device is arranged at the top end of the connecting rod; the position of the limiting device corresponds to the position of the hinge part; the limiting device drives the pressing plate to act together through the connecting rod; an external moonlet is placed in the interior cavity of the frame.
In the above release mechanism for redundant unlocking and time sequence control of the microsatellite transmission, the cabin door comprises a cabin door bolt and a door plate; the door plate is of a square plate-shaped structure; one end side wall of the door plate is rotationally connected with the frame body through a hinge part; the cabin door bolt is arranged on the side wall opposite to the joint of the door plate and the frame body.
In the release mechanism for redundant unlocking and time sequence control of the small satellite transmission, the electromagnetic lock comprises an electromagnetic control device, 2 rotating blocks, an unlocking pressure spring and an unlocking tension spring; the electromagnetic control device is arranged on the side wall of the frame body, and the position of the electromagnetic control device corresponds to the cabin door bolt; the 2 rotating blocks are symmetrically arranged at the top end of the electromagnetic control device; the unlocking pressure spring and the unlocking tension spring are arranged between the 2 rotating blocks in parallel; the unlocking pressure spring is positioned above the unlocking tension spring; the 2 rotating blocks are matched with the cabin door bolt to unlock and lock the cabin door.
In the release mechanism for redundant unlocking and time sequence control of the small satellite transmission, the placing process of the external small satellite is as follows: in the initial state, the cabin door is in a closed state; unlocking the pressure spring to be in a compressed state; unlocking the tension spring to be in a stretching state; under the control of the electromagnetic control device, the unlocking pressure spring is restored to a normal state; the unlocking tension spring is restored to a normal state; under the restoring force of the unlocking pressure spring and the unlocking tension spring, 2 rotating blocks are driven to rotate towards two outer sides, the release of the cabin door bolt is realized, and the cabin door is in an opening state; placing an external small satellite in an internal cavity of the frame body, and pushing the push plate to vertically move downwards under the action of the gravity of the external small satellite; a thrust spring compressed state; after the compression is in place, the pressing plate covers the lower surface of the pushing plate; the limit of the push plate is realized; the external small satellite is installed in place; the cabin door is rotationally closed relative to the frame body through a hinge part; under the control of the electromagnetic control device, the unlocking pressure spring is converted into a compression state; the unlocking tension spring is converted into a stretching state; drive 2 rotatory pieces and rotate to two inboards, realize spacing of cabin keeper, the cabin door is closed and is locked.
In the release mechanism for redundant unlocking and time sequence control of the small satellite transmission, the hinge part comprises a rotating shaft and a double torsion spring; the rotating shaft is arranged at the joint of the cabin door and the frame body; the double torsion springs are sleeved on the side walls of the rotating shafts; driven by a double torsion spring; the cabin door rotates along with the rotating shaft; the hatch door can be opened or closed in rotation relative to the frame body.
In the release mechanism for redundant unlocking and time sequence control of the small satellite transmission, the limiting device comprises a return spring and a limiting block; wherein, the limiting block is fixedly arranged at the top end of the connecting rod; the reset spring is sleeved on the outer wall of the connecting rod; and is arranged at the bottom of the limiting block; the limiting block drives the connecting rod and the pressing plate to vertically move upwards under the action of the reset elasticity of the reset spring.
In the release mechanism for redundant unlocking and time sequence control of the small satellite transmission, a limit groove is formed in the side wall of the rotating shaft; the shape of the limiting groove corresponds to that of the limiting block.
In the above release mechanism for redundant unlocking and timing control of small satellite transmission, the external small satellite release process is as follows:
when the cabin door is in a closed state, the outer wall of the rotating shaft limits the top of the limiting block; the reset spring is in a compressed state, the pressing plate presses the upper surface of the push plate through the connecting rod, and the external small satellite is placed in the inner cavity of the frame body; when the release position is reached, the electromagnetic control device controls the cabin door to be opened; the cabin door rotates along with the rotating shaft; when the cabin door rotates to the position, the position of the limiting groove corresponds to the limiting block; the limiting block vertically moves upwards to extend into the limiting groove under the action of the reset elasticity of the reset spring, so that the rotating shaft is locked; the hatch door is kept in an open state; meanwhile, the limiting block drives the pressing plate to open through the connecting rod, and the push plate is released; under the action of the elastic force of the thrust spring, the push plate is pushed to push the external small satellite out of the frame body, and the release is completed.
In the above redundant unlocking and timing control release mechanism for a moonlet launch, the external moonlet is in the process of installation and release; the outer wall of outside little satellite and 4 slide rail inner walls cooperate and realize sliding movement.
Compared with the prior art, the invention has the beneficial effects that:
(1) the external cubic minisatellite releasing device is provided with the redundant electromagnetic lock device, and normal opening of the cabin door can be realized by simultaneously opening or normally opening any one of the devices, so that the reliability of the cabin door unlocking device is improved;
(2) the external cubic minisatellite releasing device is also provided with a limiting device matched with the limiting groove, the limiting device can move up and down relative to the frame body, when the cabin door is closed, the limiting device is abutted against the outer side of the rotating shaft seat, when the cabin door is opened, the rotating shaft seat rotates along with the cabin door, and the limiting device slides into the limiting groove along the outer side of the rotating shaft seat to limit the cabin door to continuously rotate;
(3) the external cubic minisatellite releasing device with the redundant unlocking function takes the electromagnet as a driving power source, improves the reliability of the unlocking device, further improves the launching success rate of the external cubic minisatellite, and simultaneously avoids the collision between the excessive rotation of the cabin door and a carrying platform or the collision between the rebound of the cabin door and the external cubic minisatellite in the releasing process of the external cubic minisatellite.
Drawings
FIG. 1 is a general schematic view of a release mechanism of the present invention;
FIG. 2 is a schematic view of the hatch of the present invention in an open position;
FIG. 3 is an enlarged view of the hinge and the stop device of the present invention;
FIG. 4 is a schematic diagram of the push plate and the press plate of the present invention.
Detailed Description
The invention is further illustrated by the following examples.
The invention provides a release mechanism for redundant unlocking and time sequence control of microsatellite launching, which takes an electromagnet as a driving power source and an external cubic microsatellite release device with a redundant unlocking function, improves the reliability of the unlocking device and further improves the launching success rate of the external cubic microsatellite. As shown in fig. 1, the release mechanism mainly includes a cabin door 1, a frame 2, a hinge portion 3, a push plate 4, a thrust spring 5, 4 slide rails 6, a limiting device 7, a connecting rod 8, a pressure plate 9 and an electromagnetic lock 10; the frame body 2 is a hollow cuboid frame structure; the top end of the frame body 2 is opened; the cabin door 1 is arranged at the opening at the top end of the frame body 2; the hinge part 3 is arranged at the joint of the hatch door 1 and the frame body 2; the hatch door 1 is turned over and opened and closed relative to the frame body 2; the electromagnetic lock 10 is arranged on the side wall of the frame body 2; the electromagnetic lock 10 realizes the locking and unlocking of the cabin door 1; the 4 sliding rails 6 are axially arranged at the corners of the 4 side walls in the frame body 2; the thrust spring 5 is arranged at the bottom end inside the frame body 2; the push plate 4 is horizontally arranged at the top end of the thrust spring 5; the pressing plate 9 is arranged at the bottom end inside the frame body 2; and the pressing plate 9 corresponds to the push plate 4 in position; the connecting rod 8 is vertically arranged at the top end of the pressing plate 9; the limiting device 7 is arranged at the top end of the connecting rod 8; the position of the limiting device 7 corresponds to the position of the hinge part 3; the limiting device 7 drives the pressing plate 9 to act together through the connecting rod 8; an external moonlet is placed in the interior cavity of the frame 2. The cabin door 1 comprises a cabin door bolt 11 and a door panel 12; the door panel 12 is a square plate-shaped structure; one end side wall of the door plate 12 is rotatably connected with the frame body 2 through a hinge part 3; the door bolt 11 is provided at a side wall opposite to a joint of the door panel 12 and the frame 2. The electromagnetic lock 10 comprises an electromagnetic control device 101, 2 rotating blocks 102, an unlocking compression spring 104 and an unlocking tension spring 105; wherein, the electromagnetic control device 101 is arranged on the side wall of the frame body 2, and the position of the electromagnetic control device 101 corresponds to the position of the hatch bolt 11; the 2 rotating blocks 102 are symmetrically arranged at the top end of the electromagnetic control device 101; the unlocking pressure spring 104 and the unlocking tension spring 105 are arranged between the 2 rotating blocks 102 in parallel; the unlocking pressure spring 104 is positioned above the unlocking tension spring 105; the 2 rotating blocks 102 are matched with the cabin door bolt 11 to unlock and lock the cabin door 1.
The external small satellite placement process comprises the following steps: in the initial state, the cabin door 1 is in a closed state; unlocking the pressure spring 104 to a compressed state; the unlocking tension spring 105 is in a stretching state; under the control of the electromagnetic control device 101, the unlocking compression spring 104 is restored to a normal state; the unlocking tension spring 105 is restored to a normal state; under the restoring force of the unlocking pressure spring 104 and the unlocking tension spring 105, the 2 rotating blocks 102 are driven to rotate towards two outer sides, the release of the cabin door bolt 11 is realized, and the cabin door 1 is in an opening state; an external small satellite is placed in the inner cavity of the frame body 2, and the push plate 4 vertically moves downwards under the action of the gravity of the external small satellite; the thrust spring 5 is in a compressed state; after the compression is in place, the pressing plate 9 covers the lower surface of the push plate 4; the limit of the push plate 4 is realized; the external small satellite is installed in place; the hatch 1 is rotated closed with respect to the frame 2 by means of a hinge 3; under the control of the electromagnetic control device 101, the unlocking pressure spring 104 is converted into a compression state; the unlocking tension spring 105 is converted into a stretching state; the 2 rotating blocks 102 are driven to rotate towards the two inner sides, so that the position limitation of the cabin door bolt 11 is realized, and the cabin door 1 is closed and locked.
As shown in fig. 2 and 3, the hinge portion 3 includes a rotation shaft 31 and a double torsion spring 33; wherein, the rotating shaft 31 is arranged at the joint of the hatch door 1 and the frame body 2; the double torsion spring 33 is sleeved on the side wall of the rotating shaft 31; driven by the double torsion spring 33; the hatch door 1 rotates along with the rotating shaft 31; a rotary opening or rotary closing of the hatch door 1 relative to the frame 2 is achieved. The limiting device 7 comprises a return spring 71 and a limiting block 72; wherein, the limiting block 72 is fixedly arranged at the top end of the connecting rod 8; the reset spring 71 is sleeved on the outer wall of the connecting rod 8; and is arranged at the bottom of the limiting block 72; the limiting block 72 drives the connecting rod 8 and the pressing plate 9 to move vertically and upwards under the action of the reset elasticity of the reset spring 71. And the side wall of the rotating shaft 31 is provided with a limit groove 311; the shape of the limiting groove 311 corresponds to the limiting block 72.
The external small satellite release process is as follows:
when the cabin door 1 is in a closed state, the outer wall of the rotating shaft 31 limits the top of the limiting block 72; the return spring 71 is in a compressed state, the pressing plate 9 presses the upper surface of the push plate 4 through the connecting rod 8, and the external small satellite is placed in the inner cavity of the frame body 2; when the release position is reached, the electromagnetic control means 101 control the hatch 1 to open; the hatch door 1 rotates along with the rotating shaft 31; when the cabin door 1 rotates to the right position, the position of the limiting groove 311 corresponds to the limiting block 72; the limiting block 72 vertically moves upwards to extend into the limiting groove 311 under the action of the reset elastic force of the reset spring 71, so that the rotating shaft 31 is locked; the hatch door 1 is kept in an open state; meanwhile, the limiting block 72 drives the pressing plate 9 to open through the connecting rod 8, and the push plate 4 is released; as shown in fig. 4. Under the action of the elastic force of the thrust spring 5, the push plate 4 is pushed to push the external small satellite out of the frame body 2, and the release is completed. During the installation and release process of the external small satellite; the outer wall of outside little satellite and the 6 inner walls of 4 slide rails cooperate and realize sliding movement.
The external cubic minisatellite releasing device is provided with a redundant electromagnetic lock 10, and normal opening of the cabin door can be realized by simultaneously opening or normally opening any one of the redundant electromagnetic locks, so that the reliability of the unlocking device of the cabin door 1 is improved; the external cube microsatellite releasing device is further provided with a limiting block 72 matched with the limiting groove 311, the limiting block 72 can move up and down relative to the frame body 2, when the hatch door 1 is closed, the limiting block 72 abuts against the outer side of the seat of the rotating shaft 31, when the hatch door 1 is opened, the rotating shaft 31 rotates along with the hatch door, the limiting block 72 slides into the limiting groove 311 along the outer side of the rotating shaft 31, and the hatch door 1 is limited to continue rotating. The collision between the cabin door 1 which rotates excessively and the carrying platform or the collision between the cabin door 1 which rebounds and the external cubic minisatellite is avoided in the releasing process of the external cubic minisatellite.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (3)
1. A redundant unblock of little satellite transmission and release mechanism of time sequence control which characterized in that: comprises a cabin door (1), a frame body (2), a hinged part (3), a push plate (4), a thrust spring (5), 4 sliding rails (6), a limiting device (7), a connecting rod (8), a pressing plate (9) and an electromagnetic lock (10); wherein, the frame body (2) is a hollow cuboid frame structure; the top end of the frame body (2) is opened; the cabin door (1) is arranged at the opening at the top end of the frame body (2); the hinged part (3) is arranged at the joint of the cabin door (1) and the frame body (2); the hatch (1) is turned over, opened and closed relative to the frame body (2); the electromagnetic lock (10) is arranged on the side wall of the frame body (2); the electromagnetic lock (10) realizes the locking and unlocking of the cabin door (1); the 4 sliding rails (6) are axially arranged at the corners of 4 side walls in the frame body (2); the thrust spring (5) is arranged at the bottom end inside the frame body (2); the push plate (4) is horizontally arranged at the top end of the thrust spring (5); the pressing plate (9) is arranged at the bottom end inside the frame body (2); the pressing plate (9) corresponds to the push plate (4); the connecting rod (8) is vertically arranged at the top end of the pressing plate (9); the limiting device (7) is arranged at the top end of the connecting rod (8); the position of the limiting device (7) corresponds to the position of the hinge part (3); the limiting device (7) drives the pressing plate (9) to act together through the connecting rod (8); the external small satellite is placed in the inner cavity of the frame body (2);
the cabin door (1) comprises a cabin door bolt (11) and a door panel (12); the door panel (12) is of a square plate-shaped structure; one end side wall of the door panel (12) is rotationally connected with the frame body (2) through a hinge part (3); the cabin door bolt (11) is arranged on the side wall opposite to the joint of the door panel (12) and the frame body (2);
the electromagnetic lock (10) comprises an electromagnetic control device (101), 2 rotating blocks (102), an unlocking pressure spring (104) and an unlocking tension spring (105); the electromagnetic control device (101) is arranged on the side wall of the frame body (2), and the position of the electromagnetic control device (101) corresponds to the cabin door bolt (11); the 2 rotating blocks (102) are symmetrically arranged at the top end of the electromagnetic control device (101); the unlocking pressure spring (104) and the unlocking tension spring (105) are arranged between the 2 rotating blocks (102) in parallel; the unlocking pressure spring (104) is positioned above the unlocking tension spring (105); 2 rotating blocks (102) are matched with the cabin door bolt (11) to unlock and lock the cabin door (1);
the limiting device (7) comprises a return spring (71) and a limiting block (72); wherein, the limiting block (72) is fixedly arranged at the top end of the connecting rod (8); the reset spring (71) is sleeved on the outer wall of the connecting rod (8); and is arranged at the bottom of the limiting block (72); the limiting block (72) drives the connecting rod (8) and the pressing plate (9) to vertically move upwards under the action of the reset elasticity of the reset spring (71);
the external minisatellite is in the process of installation and release; the outer wall of the external small satellite is matched with the inner walls of the 4 sliding rails (6) to realize sliding movement;
the external small satellite placement process comprises the following steps: in the initial state, the cabin door (1) is in a closed state; unlocking the pressure spring (104) to a compressed state; the unlocking tension spring (105) is in a stretching state; under the control of the electromagnetic control device (101), the unlocking pressure spring (104) is restored to a normal state; the unlocking tension spring (105) is restored to a normal state; under the restoring force of an unlocking pressure spring (104) and an unlocking tension spring (105), 2 rotating blocks (102) are driven to rotate towards two outer sides, the release of a cabin door bolt (11) is realized, and a cabin door (1) is in an opening state; an external small satellite is placed in an internal cavity of the frame body (2), and the push plate (4) vertically moves downwards under the action of the gravity of the external small satellite; the thrust spring (5) is in a compressed state; after the compression is in place, the pressing plate (9) covers the upper surface of the push plate (4); the limit of the push plate (4) is realized; the external small satellite is installed in place; the cabin door (1) is rotationally closed relative to the frame body (2) through the hinge part (3); under the control of an electromagnetic control device (101), an unlocking pressure spring (104) is converted into a compression state; the unlocking tension spring (105) is converted into a stretching state; the 2 rotating blocks (102) are driven to rotate towards the two inner sides, so that the position limitation of the cabin door bolt (11) is realized, and the cabin door (1) is closed and locked;
the hinge part (3) comprises a rotating shaft (31) and a double torsion spring (33); wherein, the rotating shaft (31) is arranged at the joint of the hatch (1) and the frame body (2); the double torsion spring (33) is sleeved on the side wall of the rotating shaft (31); driven by a double torsion spring (33); the cabin door (1) rotates along with the rotating shaft (31); the hatch (1) is opened or closed in a rotating way relative to the frame body (2);
a limiting groove (311) is formed in the side wall of the rotating shaft (31); the shape of the limiting groove (311) corresponds to the limiting block (72).
2. The redundant unlock and timing control release mechanism for a moonlet launch of claim 1 wherein: the external small satellite release process is as follows:
when the cabin door (1) is in a closed state, the outer wall of the rotating shaft (31) limits the top of the limiting block (72); the reset spring (71) is in a compressed state, the pressing plate (9) presses the upper surface of the push plate (4) through the connecting rod (8), and the external small satellite is placed in the inner cavity of the frame body (2); when the release position is reached, the electromagnetic control device (101) controls the hatch (1) to be opened; the cabin door (1) rotates along with the rotating shaft (31); when the cabin door (1) rotates to the position, the position of the limiting groove (311) corresponds to the limiting block (72); the limiting block (72) vertically moves upwards to extend into the limiting groove (311) under the action of the reset elastic force of the reset spring (71) to lock the rotating shaft (31); the cabin door (1) is kept in an open state; meanwhile, the limiting block (72) drives the pressing plate (9) to open through the connecting rod (8) to release the push plate (4); under the action of the elastic force of the thrust spring (5), the push plate (4) is pushed to push the external small satellite out of the frame body (2) to complete release.
3. The redundant unlock and timing control release mechanism for a moonlet launch of claim 2, wherein: the external small satellite is of a cubic star structure.
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| CN201911067305.3A CN110963090B (en) | 2019-11-04 | 2019-11-04 | Redundant unlocking and time sequence control releasing mechanism for small satellite transmission |
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| CN201911067305.3A CN110963090B (en) | 2019-11-04 | 2019-11-04 | Redundant unlocking and time sequence control releasing mechanism for small satellite transmission |
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| CN112124630B (en) * | 2020-08-20 | 2024-03-19 | 山东航天电子技术研究所 | Cube star connection and separation device and connection and separation method thereof |
| CN112278333B (en) * | 2020-09-30 | 2022-03-25 | 北京空间飞行器总体设计部 | Automatic opening and closing cabin door of extraterrestrial celestial body sampling returning cabin |
| CN113697133A (en) * | 2021-09-01 | 2021-11-26 | 长光卫星技术有限公司 | Orbit deploying device for cubic micro-nano satellite |
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| CN107933976A (en) * | 2017-12-21 | 2018-04-20 | 星际漫步（北京）航天科技有限公司 | Cube star ejector and its catapult technique |
| CN207809821U (en) * | 2017-12-21 | 2018-09-04 | 星际漫步（北京）航天科技有限公司 | Cube star ejector |
| CN110155376A (en) * | 2019-05-23 | 2019-08-23 | 南京理工大学 | A kind of cube star unlocking separation mechanism and its separation method |
| CN110282162A (en) * | 2019-06-26 | 2019-09-27 | 北京宇航系统工程研究所 | A kind of cube satellite release device |
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| US9567115B2 (en) * | 2014-07-29 | 2017-02-14 | Victor Dube | Door mechanism for satellite deployer system |
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| CN107933976A (en) * | 2017-12-21 | 2018-04-20 | 星际漫步（北京）航天科技有限公司 | Cube star ejector and its catapult technique |
| CN207809821U (en) * | 2017-12-21 | 2018-09-04 | 星际漫步（北京）航天科技有限公司 | Cube star ejector |
| CN110155376A (en) * | 2019-05-23 | 2019-08-23 | 南京理工大学 | A kind of cube star unlocking separation mechanism and its separation method |
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