CN112373732A - Low-impact small-sized spacecraft separation releasing mechanism - Google Patents
Low-impact small-sized spacecraft separation releasing mechanism Download PDFInfo
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- CN112373732A CN112373732A CN202011185216.1A CN202011185216A CN112373732A CN 112373732 A CN112373732 A CN 112373732A CN 202011185216 A CN202011185216 A CN 202011185216A CN 112373732 A CN112373732 A CN 112373732A
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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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- 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
- B64G1/641—Interstage or payload connectors
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention relates to a low-impact small-sized spacecraft separation release mechanism which comprises a gas generator, a connection separation assembly, a rear end cover, a guide rod and an auxiliary support ring, wherein the connection separation assembly is arranged on the gas generator; the gas generator is a power source for releasing and separating and is arranged at one end of the connecting and separating component; the other end of the connecting and separating component is arranged in the center of one side of the rear end cover and is used for mounting, separating and releasing the aircraft; the other side of the rear end cover is circumferentially provided with a plurality of guide rods, and the rear end cover is arranged on the spacecraft platform; the auxiliary support rings are sleeved on the guide rods and can move along the guide rods; the connection and separation assembly is separated by triggering the gas generator, so that the aircraft is separated and released from the spacecraft platform. The invention is arranged on a carrier or a large-scale spacecraft platform, and meets the requirement of low-impact accurate separation and release of a microminiature spacecraft.
Description
Technical Field
The invention relates to an aircraft separation release mechanism.
Background
In order to complete some specific tasks, the micro spacecraft needs to be delivered out of the atmosphere by a carrying platform and released at a certain speed. The existing spacecraft separation technology has various types, wherein explosive bolts or other similar connecting structures are combined with springs, or thrust motors, or thrust and impact mechanisms for separation and release, the structures are generally used for separation and release of large-sized spacecraft, and the defects that the separation and impact are large, the structure size and the weight are large, and combustion products of the solid thrust motors can become pollutants, so that the optical equipment protection on the spacecraft is greatly challenged. The release mechanism of the other type of spacecraft uses gas or cold air as a release power source, and uses a pin puller or other low-impact connecting structures as a connecting and unlocking mechanism, and the release mechanism generally needs to be matched with a launch tube, and is generally suitable for releasing the miniature spacecraft with smaller size and lighter weight (0-20 kg). In addition, there are some release modes based on the separation of the motor and the transmission mechanism, the release mode based on the shape memory alloy, and the like, and compared with the release mode based on the initiating explosive device, the two release modes have certain disadvantages of environmental adaptability, reliability, long-term storage performance and the like. For many small-sized spacecraft with attitude control or orbit control, the shape is not only irregular, but also strict requirements are imposed on the precision of the release speed, the release impact, the weight of the release mechanism and the like. How to design a device which can meet the space environment condition and the requirement of separating and releasing the load has important practical significance.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the mechanism is arranged on a carrier or a large-scale spacecraft platform, and meets the requirement of low-impact accurate separation and release of the micro spacecraft.
The technical scheme adopted by the invention is as follows: a low-impact small-sized spacecraft separation release mechanism comprises a gas generator, a connection separation assembly, a rear end cover, a guide rod and an auxiliary support ring; the gas generator is a power source for releasing and separating and is arranged at one end of the connecting and separating component; the other end of the connecting and separating component is arranged in the center of one side of the rear end cover and is used for mounting, separating and releasing the aircraft; the other side of the rear end cover is circumferentially provided with a plurality of guide rods, and the rear end cover is arranged on the spacecraft platform; the auxiliary support rings are sleeved on the guide rods and can move along the guide rods; the connection and separation assembly is separated by triggering the gas generator, so that the aircraft is separated and released from the spacecraft platform.
The connecting and separating assembly comprises a pre-tightening spring, a front cylinder, a steel ball, a piston, a rear cylinder and a sealing ring; an annular arc-shaped groove is formed in the port of the inner wall of the front barrel; one end of the rear cylinder is provided with a plurality of steel ball mounting holes along the circumferential direction, and the end of the rear cylinder provided with the steel ball mounting holes penetrates through the central hole of the rear end cover and then is inserted into the front cylinder; the piston is arranged in the rear cylinder, one end of the piston is sealed with the inner wall of the rear cylinder through a sealing ring, the other end of the piston is inserted into one end of the rear cylinder, which is provided with the steel ball mounting hole, and is connected with the spring, and the other end of the spring is connected with the bottom of the inner cavity of the front cylinder; the steel ball is placed in the arc groove of the front cylinder and the steel ball mounting hole of the rear cylinder, and the bottom of the steel ball is supported by the piston, so that the front cylinder is connected with the rear cylinder; the other end of the rear cylinder is provided with a gas generator.
A load flange is arranged at the sealing end of the front cylinder, so that a positioning boss is formed at the sealing end, and the load flange is connected with the aircraft; the positioning boss is used for being matched with the aircraft in a positioning mode, and the connection and separation assembly is guaranteed to be installed on the axis of the aircraft.
And a fixing flange is arranged on the outer wall of the rear cylinder and is used for fixing the rear end cover.
A plurality of supporting plate screws are distributed on the rear end cover along the circumferential direction, and the supporting plate screws are used for connecting the rear end cover with the spacecraft platform; the rear end cover is made of hard aluminum alloy, reinforcing ribs are arranged on the rear end cover, and through holes are locally processed.
The igniter is arranged at the rear end of the gas generator and used for triggering the release of gas in the gas generator, pushing the piston to move, releasing the steel ball, realizing the separation of the front cylinder and the rear cylinder and releasing the aircraft.
The guide rod is made of titanium alloy and comprises an external thread section, a cylindrical section and a conical table section; the two ends of the cylindrical section are respectively an external thread section and a conical frustum section; two grooves are symmetrically arranged on the cylindrical section of the guide rod close to the external thread section.
The guide rods are distributed along the circumferential direction of the auxiliary support ring, the auxiliary support ring is matched with each guide rod through the arc-shaped grooves along the longitudinal direction, and the auxiliary support ring is made of hard aluminum alloy.
A slope transition is arranged between the front end and the middle section of the piston, and the included angle between the piston and the central axis ranges from 20 degrees to 45 degrees.
The unlocking distance of the piston movement is 1.5-2 times of the diameter of the steel ball.
Compared with the prior art, the invention has the beneficial effects that:
(1) the invention realizes the purpose of strong connection by designing the steel ball and the bearing of the front and rear cylinders. Meanwhile, the unlocking is carried out through the movement displacement of the piston, the nondestructive unlocking is carried out, and the design of the inclined surface of the piston greatly reduces the separation impact and realizes the purpose of low impact release.
(2) According to the invention, through the integrated design idea of separation and release, an independent unlocking signal is saved, a control system is simplified, and the product reliability is improved. The low impact separation is realized by a strong connection and weak unlocking mode, the lightweight design is realized by adopting a rod type framework structure, the purpose that the release speed precision of a 40 kg-class micro aircraft is better than +/-0.5 m/s is realized, and the mass of the release mechanism is less than 5.5 kg.
(3) According to the invention, through the overall design of the rod-type frame and the structural optimization and material selection optimization design, the overall weight of the release mechanism is reduced, and the mass of the whole machine is not more than 5.5 kg.
(4) The invention prevents the false unlocking condition of the connecting mechanism by a spring pre-tightening mode.
(5) According to the invention, through the form that one end of the spring is fixed, the risk that the spring is separated out independently to form space garbage is avoided.
(6) The invention realizes the purposes of convenient and reliable assembly by the design of the circular and lace-type double-layer flanges.
(7) The positioning cylindrical boss is designed on the mounting surface for connecting the small aircraft, so that concentric assembly of the connecting and separating assembly and the aircraft is realized, and the separating force is ensured to act on the axis of the aircraft, thereby ensuring the separating attitude.
(8) According to the invention, the positioning cylindrical hole is designed between the rear end cover and the guide rod, so that the assembly form and position accuracy of the guide rod is ensured.
(9) The invention not only ensures the guiding precision during separation, but also is convenient for assembly through reasonable guiding fit tolerance and the angle of the guiding fit arc surface of the aircraft, and can play a certain auxiliary supporting role when experiencing mechanical environment.
(10) The invention not only ensures that the auxiliary support ring and the guide rod can be assembled in a sliding way, but also ensures that the auxiliary support ring and the guide rod are reliably matched through reasonable matching tolerance of the auxiliary support ring and the guide rod and the angle of the matched arc surface.
(11) According to the invention, through reasonable envelope size of the aircraft and inner diameter size of the auxiliary support ring, the release process can still not be interfered even if the guiding arc surface of the aircraft is discontinuous.
Drawings
FIG. 1 is a schematic structural diagram of the present invention.
FIG. 2 is a schematic view of the coupling of the separator assembly to the gas generator.
FIG. 3 is a schematic view of a rear endcap assembly.
Fig. 4 is a schematic view of the guide bar.
Fig. 5 is a schematic view of an auxiliary support ring.
Detailed Description
The invention is further illustrated by the following examples.
Example 1
As shown in FIG. 1, the low-impact small-sized spacecraft separation and release mechanism comprises a gas generator 1, a connection and separation assembly 2, a rear end cover assembly 3, a guide rod 4 and an auxiliary support ring 5. The gas generator 1 serves as a power source for releasing separation by generating or storing high-pressure gas. The coupling and decoupling assembly 2 enables the connection of the small aircraft with the release mechanism and acts as an actuator for the decoupling release. The rear end cover assembly 3 realizes the connection of the connecting and separating assembly 2 and the guide rod 4 and the connection of the separating and releasing mechanism and the upper stage platform. The guide rod 4 plays a guiding role for the separation process and also plays an auxiliary supporting role after the small aircraft is installed. The auxiliary support ring 5 provides auxiliary rigidity for auxiliary support of the small aircraft and for the guide bar 4.
As shown in fig. 2, the connection and disconnection assembly 2 comprises a pre-tightening spring 6, a front cylinder 7, a steel ball 8, a piston 9, a rear cylinder 10 and a sealing ring 11. An annular arc-shaped groove is formed in the end opening of the inner wall of the front barrel 7, wherein the arc section is slightly smaller than a semicircle; one end of the rear cylinder 10 is circumferentially provided with 3-6 steel ball mounting holes, the steel ball mounting holes are round through holes or long round through holes, and one end of the rear cylinder 10 provided with the steel ball mounting holes penetrates through a central hole of the rear end cover assembly 3 and then is inserted into the front cylinder 7; the piston 9 is arranged in the rear cylinder 10, one end of the piston is sealed with the inner wall of the rear cylinder 10 through a sealing ring 11, the other end of the piston is inserted into one end of the rear cylinder 10, which is provided with a steel ball mounting hole, and is connected with the spring 6, and the other end of the spring 6 is connected with the bottom of the inner cavity of the front cylinder 7; the steel ball 8 is placed in the arc groove of the front cylinder 7 and the steel ball mounting hole of the rear cylinder 10, and the bottom of the steel ball 8 is supported by the front end of the piston 9, so that the front cylinder 7 is connected with the rear cylinder 10. The other end of the rear cylinder 10 is provided with a gas generator 1, the rear end of the gas generator 1 is provided with an igniter 12 for triggering the release of high-pressure gas, pushing the piston 9 to move, releasing the steel ball 8, realizing the separation of the front cylinder 7 and the rear cylinder 10, and releasing the small aircraft. A load flange 14 is arranged at the sealing end of the front barrel 7, so that the sealing end forms a positioning boss 13; and a fixing flange 15 is arranged on the outer wall of the joint of the rear barrel 10 and the front barrel 7, and the fixing flange 15 is used for fixing with a rear end cover 16.
As shown in fig. 3, the rear cover assembly 3 includes a rear cover 16, and support plate screws 17, wherein the support plate screws 17 are circumferentially distributed on the rear cover 16.
As shown in fig. 4, two grooves 18 are symmetrically formed at one end of the guide bar 4. The guide rod 4 is circumferentially arranged on the rear end cover 16; the auxiliary support rings 5 are mounted on the guide bars 4, the guide bars 4 are distributed along the circumferential direction of the auxiliary support rings 5, and the auxiliary support rings 5 are engaged with the guide bars 4 through arc-shaped grooves along the longitudinal direction.
Preferably, the separation release mechanism adopts a skeleton structure formed by four rods, a rear end cover and an auxiliary support ring to realize light design.
Preferably, the front end of the piston 9 is used for supporting the steel ball 8 to realize connection; a slope transition is arranged between the front end and the middle section of the piston 9, and the included angle between the slope transition and the central axis is 20-45 degrees for reducing unlocking impact; the rear end of the piston 9 is provided with a radial seal for ensuring the sealing performance in the movement process and preventing gas leakage. The pre-tightening spring 6 at the front end of the piston 9 is used for pre-tightening the piston 9, so that the situation that the piston 9 moves forwards to cause mistaken unlocking of the connecting mechanism before unlocking is avoided.
Preferably, the unlocking distance of the piston movement is generally 1.5-2 times the diameter of the steel ball.
Preferably, the coupling and decoupling assembly 2 has two layers of flanges, a load flange 14 on the front barrel 7 and a fixing flange 15 on the rear barrel 10. The load flange 14 is connected with the small aircraft, and the fixed flange 15 is fixedly connected with the rear end cover assembly 3 of the release mechanism. The assembly sequence is that the connection and separation component 2 is connected with the small aircraft, then the small aircraft (or the connection and separation component 2) is pushed to enable the fixing flange 15 to the corresponding mounting surface of the rear end cover 16, and the screws are screwed from the other side of the rear end cover 16.
Preferably, the mounting holes of the load flange 14 are through holes, the flanges are complete circles, the fixing flange 15 is a lace shape, the mounting holes are threaded holes, and the threaded holes and the through holes of the two layers of flanges are staggered in angle on the distribution circle. The design of the lace flange and the staggered distribution angle of the two layers of flanges are used for ensuring the operation space of screws of the flange when the load flange is installed. The threaded holes in the mounting flange 15 are provided to facilitate assembly with the rear end cap.
Preferably, one end of the pre-tightening spring 6 is fixed on the front barrel 7, so that the spring is prevented from being randomly separated into a space environment in an unconstrained state after the small aircraft is separated and released, and space garbage is formed.
Preferably, the gas generator 1 is screwed on the rear cylinder 10 of the connection and separation assembly 2 through a large thread, and the piston 9 is limited to move backwards through the end face of the gas generator 1, so that the connection and separation mechanism is prevented from being unlocked mistakenly. The rear end of the gas generator 1 is provided with an igniter, when the igniter receives an instruction, the gas generator 1 generates high-pressure gas and releases the high-pressure gas to form a power source to push the piston 9 to move, the connection is firstly unlocked, then the piston 9 is continuously pushed to move, and the small aircraft is separated.
Preferably, the front end of the front barrel 7 is provided with a cylindrical table protruding 3mm high, namely a positioning boss 13, which is used for positioning and matching with a small aircraft to ensure that the connection and separation assembly 2 is installed on an aircraft axis, so that the force borne by the aircraft in the release process is ensured to be on the axis, and the separation force is prevented from being pushed to deviate.
Preferably, the rear end cover assembly 3 is made of hard aluminum alloy, adopts a structural form of a reinforcing rib, and is locally provided with a through hole to achieve the purpose of light weight. Meanwhile, the local through hole can facilitate the small aircraft to pass through the upper-level communication cable.
Preferably, four holes of the rear end cover assembly 3 connected with the guide rod 4 are designed as stepped holes, one section is an M12 threaded hole, the length is about 12mm, the four holes are used for fixing the guide rod 4, one section is a high-precision unthreaded hole, the length is about 12mm, the four holes are used for positioning the guide rod 4 and the rear end cover 16, and the shape and position precision of the installation of the guide rod and the rear end cover is ensured.
Preferably, the guide rod 4 is made of titanium alloy, and the guide rod 4 is in the shape of an external thread section, a cylindrical section or a frustum of a cone. M12 has a thread length of 12mm, a cylindrical section length of about 460mm, a cylindrical section diameter of phi 16mm (nominal size), a truncated cone length of about 180mm, and a small end diameter of phi 10 mm. The frustum design is convenient for the direction when small aircraft assembles to reduce the separation release in-process contact length, thereby reduce the friction, improve the release precision. In addition, the guide rod is provided with two grooves 18 at the cylindrical section close to the thread, so that the guide rod 4 can be screwed down by using a tool when the guide rod 4 is assembled with the rear end cover 16.
Preferably, the outer cylindrical surface of the guide rod 4 is guided when the separation and release of the arc surface of the small aircraft are carried out. The angle of the circular arc surface of the small aircraft matched with the guide rod 4 is about 117 degrees.
Preferably, the guide bar4 the matching sizes of the outer cylindrical surface and the circular arc surface of the small aircraft are respectively as follows: outer cylindrical surface phi 16 of guide rod 4-0.1 -0.15mm, and the size of the arc surface matched with the small aircraft is R8+0.16 +0.08mm。
Preferably, as shown in fig. 5, the material of the auxiliary support ring 5 is hard aluminum alloy, and the arc diameter where the auxiliary support ring 5 is matched with the guide rod 4 is phi 16+0.1 +0.04mm, the angle of the circular arc surface which is matched with the guide rod 4 is about 227 degrees. The auxiliary support ring 5 has an inner diameter of 282+0.5 +0.1mm, and the maximum envelope size of the small aircraft is 279.5 mm. The outside of the auxiliary support ring 5 is provided with two ears for mounting with the upper stage platform.
Preferably, the auxiliary support ring 5 and the guide rod 4 adopt a sliding structure, so that the over-positioning installation is avoided, and the assembly is convenient.
The working principle of the invention is as follows:
the igniter 12 receives a release trigger signal given by the upper stage platform, the igniter 12 works to trigger the release of high-pressure gas, the high-pressure gas pushes the piston 9 to move, the steel ball slides out of the front cylinder 7 after moving for a certain distance (the diameter of the steel ball is 1.5-2 times), namely, the unlocking of the front cylinder 7 and the rear cylinder 10 is realized, the piston 9 continues to move under the pushing of the high-pressure gas to push the small aircraft to move forwards, and finally, the piston 9 moves in place, at the moment, the separation speed of the small aircraft reaches the maximum, and the subsequent small aircraft continues to move along the guide rail under the inertia action until the small aircraft is completely separated from the guide.
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 (10)
1. A low-impact small-sized spacecraft separation and release mechanism is characterized by comprising a gas generator (1), a connection and separation assembly (2), a rear end cover (16), a guide rod (4) and an auxiliary support ring (5); the gas generator (1) is a power source for releasing and separating and is arranged at one end of the connecting and separating component (2); the other end of the connecting and separating component (2) is arranged at the center of one side of the rear end cover (16) and is used for installation and separation release of the aircraft; the other side of the rear end cover (16) is provided with a plurality of guide rods (4) along the circumferential direction, and the rear end cover (3) is arranged on a spacecraft platform; the auxiliary support rings (5) are sleeved on the guide rods (4), and the auxiliary support rings (5) can move along the guide rods (4); the separation and release of the aircraft from the spacecraft platform are realized by triggering the gas generator (1) to separate the connection and separation assembly (2).
2. The low-impact small-sized spacecraft separation and release mechanism according to claim 1, wherein the connection and release assembly (2) comprises a pre-tightening spring (6), a front cylinder (7), a steel ball (8), a piston (9), a rear cylinder (10) and a sealing ring (11); an annular arc-shaped groove is formed in the port of the inner wall of the front barrel (7); one end of the rear cylinder (10) is circumferentially provided with a plurality of steel ball mounting holes, and the end of the rear cylinder (10) provided with the steel ball mounting holes penetrates through the central hole of the rear end cover (16) and then is inserted into the front cylinder (7); the piston (9) is arranged in the rear cylinder (10), one end of the piston is sealed with the inner wall of the rear cylinder (10) through a sealing ring (11), the other end of the piston is inserted into one end, provided with a steel ball mounting hole, of the rear cylinder (10) and is connected with the spring (6), and the other end of the spring (6) is connected with the bottom of the inner cavity of the front cylinder (7); the steel ball (8) is placed in the arc groove of the front cylinder (7) and the steel ball mounting hole of the rear cylinder (10), and the bottom of the steel ball (8) is supported by the piston (9) to realize the connection of the front cylinder (7) and the rear cylinder (10); the other end of the rear cylinder (10) is provided with a gas generator (1).
3. A low-impact mini-spacecraft separation and release mechanism according to claim 2, wherein the load flange (14) is provided at the closed end of the front barrel (7) so that the closed end forms the positioning boss (13), and the load flange (14) is connected with the spacecraft; the positioning boss (13) is used for being matched with the aircraft in a positioning mode, and the connection and separation assembly (2) is guaranteed to be installed on the axis of the aircraft.
4. A low-impact mini-space vehicle decoupling release mechanism as claimed in claim 3, wherein the rear barrel (10) is provided with a fixing flange (15) on the outer wall, the fixing flange (15) being used for fixing with the rear end cap (16).
5. A low-impact mini-spacecraft separation and release mechanism according to claim 4, wherein the rear end cap (16) is circumferentially distributed with a plurality of pallet screws (17), the pallet screws (17) are used for connecting the rear end cap (16) with the spacecraft platform; the rear end cover (16) is made of hard aluminum alloy, reinforcing ribs are arranged on the rear end cover (16), and through holes are formed in part of the rear end cover.
6. A low impact mini-spacecraft separation and release mechanism according to claim 5, wherein the igniter (12) is arranged at the rear end of the gas generator (1) and is used for triggering the gas release in the gas generator (1) to push the piston (9) to move and release the steel ball (8) to realize the separation of the front cylinder (7) and the rear cylinder (10) so as to release the spacecraft.
7. A low impact mini-spacecraft separation and release mechanism according to claim 6, wherein the material of the guide rod (4) is titanium alloy, the guide rod (4) comprises an external thread section, a cylindrical section, a frustum of a cone section; the two ends of the cylindrical section are respectively an external thread section and a conical frustum section; two grooves (18) are symmetrically arranged on the cylindrical section of the guide rod (4) close to the external thread section.
8. A low impact mini-spacecraft separation and release mechanism according to claim 7, wherein the guide rods (4) are distributed along the circumference of the auxiliary support ring (5), the auxiliary support ring (5) is engaged with each guide rod (4) by means of an arc-shaped groove along the longitudinal direction, and the material of the auxiliary support ring (5) is duralumin.
9. A low-impact spacecraft release mechanism according to claim 8, wherein a ramp transition is provided between the front end and the middle section of the piston (9) at an angle in the range of 20 ° to 45 ° to the central axis.
10. A low impact spacecraft separation release mechanism according to claim 9, wherein the piston (9) moves an unlocking distance of 1.5 to 2 times the diameter of the steel ball (8).
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| CN202011185216.1A CN112373732B (en) | 2020-10-29 | 2020-10-29 | Low-impact small-sized spacecraft separation releasing mechanism |
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| CN202011185216.1A CN112373732B (en) | 2020-10-29 | 2020-10-29 | Low-impact small-sized spacecraft separation releasing mechanism |
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| CN112373732B CN112373732B (en) | 2022-07-05 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114543601A (en) * | 2022-03-28 | 2022-05-27 | 北京中科宇航技术有限公司 | Low-impact explosive bolt unlocking and capturing device |
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