CN114735249A - Locking and unlocking mechanism for satellite launching box - Google Patents
Locking and unlocking mechanism for satellite launching box Download PDFInfo
- Publication number
- CN114735249A CN114735249A CN202210648365.XA CN202210648365A CN114735249A CN 114735249 A CN114735249 A CN 114735249A CN 202210648365 A CN202210648365 A CN 202210648365A CN 114735249 A CN114735249 A CN 114735249A
- Authority
- CN
- China
- Prior art keywords
- lock
- hole
- lock pin
- locking
- pin
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- 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
Abstract
Disclosed is a locking and unlocking mechanism (100) for a satellite launch box, comprising: the lock catch (101) is fixed on the moving side of the mechanism to be locked, and a lock hole is formed in the end part of the lock catch; the support (202) is fixed on the fixing side of the structure to be locked, is provided with a support hole, and is internally provided with a guide hole; the lock pin (201) is positioned in the guide hole of the support (202) and can slide, so that the first end of the lock pin is inserted into the lock hole and pulled out of the lock hole, and the second end of the lock pin is provided with a screw hole; the motor bracket (301) is fixed on a fixing side of the structure to be locked; a motor (302); and the first end of the screw rod (204) is connected with the shaft of the motor (302), and the second end of the screw rod can be in threaded engagement with the screw hole of the lock pin (201), so that when the screw rod rotates, the lock pin (201) is driven to slide in the guide hole, the first end of the lock pin (201) is inserted and pulled in the lock hole, and the locking and unlocking of the satellite launching box are completed. The structure is compact, the reliability is high, no impact exists, the pin pulling/plugging force is large, the stroke is adjustable, and the locking and unlocking device is suitable for locking and unlocking satellite launching boxes of various sizes.
Description
Technical Field
The invention relates to the technical field of spaceflight, in particular to a locking and unlocking mechanism of a satellite launching box.
Background
With the rapid development of aerospace technology, the satellite transmitting frequency in China is higher and higher, and the satellite transmitting quantity is increased continuously. The locking and unlocking mechanism of the satellite launching box is an indispensable device link for satellite launching, and serves as a key component for ensuring reliable locking in the launching process and reliable unlocking after orbit entering. After the satellite is launched by the rocket into space and before the separation of the satellite and the rocket is completed, the locking and unlocking mechanism needs to complete the unlocking of the launching box firstly, so that the satellite is released from the launching box in time when the satellite and the rocket are separated, and the satellite is conveniently launched into space. Therefore, the design of the locking and unlocking mechanism must strictly control the weight of the mechanism and ensure that the system has the characteristics of high reliability, high performance, high operability and the like.
The existing locking and unlocking mechanism comprises: initiating explosive device unlocking and non-initiating explosive unlocking. The initiating explosive device unlocking technology is mature, and the satellite has great vibration during separation and influences the angular speed of satellite separation under the influence of initiating explosive device unlocking separation impact. Compared with initiating explosive device unlocking, non-initiating explosive device unlocking obviously reduces impact during unlocking, and two research directions are mainly provided:
(1) the unlocking is carried out by utilizing the material property of the driving part, and mainly comprises a shape memory alloy mechanism, a low-melting-point material fusing and releasing device, a thermal cutting device and the like.
The unlocking mode of the driving material utilizes current to heat, the unlocking time is long, the power consumption is large, and the fusing mode and the hot cutting mode are used as disposable products, so that the ground is inconvenient for multiple test tests.
(2) The unlocking is carried out by utilizing the structural characteristics of the locking component, and mainly comprises a metal belt winding type locking and releasing device, a motor-driven type belt locking and releasing device and the like. The locking devices are complex in structure and are not suitable for unlocking and separating the micro-nano cubic star.
Accordingly, there is a need in the art for an improved satellite launch box lock release mechanism.
Disclosure of Invention
According to an embodiment of the present invention, there is provided a satellite launch box locking and unlocking mechanism 100, including:
the lock catch 101 is fixed on the moving side of the mechanism to be locked, and a lock hole is formed in the end part of the lock catch;
the support 202 is fixed on the fixing side of the structure to be locked, is provided with a support hole for the lock catch 101 to enter and exit, and is internally provided with a guide hole;
the lock pin 201 is positioned in the guide hole of the support 202 and can slide in the guide hole, so that the first end of the lock pin is inserted into and pulled out of the lock hole of the lock catch 101, and the second end of the lock pin is provided with a screw hole;
a motor bracket 301 fixed to a fixing side of the structure to be locked;
a motor 302 fixed to the motor holder 301; and
and a first end of the screw 204 is connected with the shaft of the motor 302, and a second end of the screw can be in threaded engagement with a screw hole of the lock pin 201, so that when the screw is driven by the shaft of the motor 302 to rotate, the lock pin 201 can be driven to slide in the guide hole of the support 202, the first end of the lock pin 201 is inserted into and pulled out of the lock hole of the lock catch 101, and the locking and unlocking of the satellite launching box are completed.
The locking and unlocking mechanism of the launching box provided by the embodiment of the invention realizes locking and unlocking by a mechanical structure, has the characteristics of simple structure, high reliability, large unlocking pin pulling/inserting force, large or small pin pulling/inserting stroke, stable work, no impact and the like, and is suitable for locking and unlocking various satellite launching boxes with different sizes.
Drawings
FIG. 1 shows a schematic perspective view of a satellite launch box latch and unlock mechanism according to an embodiment of the present invention.
FIG. 2 shows a cross-sectional view of the satellite launch box latch and unlock mechanism in view A and in position B-B in accordance with an embodiment of the present invention.
Detailed Description
Embodiments of the present invention are described in detail below with reference to the accompanying drawings. In the following description, numerous specific details are set forth in order to provide a more thorough understanding of the present invention to those skilled in the art. It will be apparent, however, to one skilled in the art that the present invention may be practiced without some of these specific details. Furthermore, it should be understood that the invention is not limited to the specific embodiments described. Rather, it is contemplated that the invention may be practiced with any combination of the following features and elements, whether or not they relate to different embodiments. Thus, the following aspects, features, embodiments and advantages are merely illustrative and should not be considered elements or limitations of the claims except where explicitly recited in a claim(s).
The meanings of the terms referred to in the specification are generally the meanings commonly understood in the art or the meanings as normally understood by those skilled in the art after reading the specification. The terms "comprising" and "including" in this specification are open-ended, i.e., may include additional elements not already mentioned in addition to the elements already mentioned. The terms "connected," "coupled," and the like in this specification generally include mechanical connections, electrical connections, or combinations thereof, and generally include both direct connections and indirect connections or connections via other components. The terms "first", "second", and the like in this specification are used only for distinguishing between similar different components and do not denote any order in importance, structure, function, or the like.
Referring now to fig. 1-2, wherein fig. 1 shows a schematic perspective view of a satellite launch box locking and unlocking mechanism according to an embodiment of the present invention, and fig. 2 shows an a-direction view and a cross-sectional view of a B-B position of the satellite launch box locking and unlocking mechanism according to an embodiment of the present invention.
As shown in fig. 1-2, a satellite launch box locking and unlocking mechanism 100 according to an embodiment of the present invention includes:
the lock catch 101 is fixed on the moving side of the mechanism to be locked, and a lock hole is formed in the end part of the lock catch;
the support 202 is fixed on the fixing side of the structure to be locked, is provided with a support hole for the lock catch 101 to enter and exit, and is internally provided with a guide hole;
the lock pin 201 is positioned in the guide hole of the support 202 and can slide in the guide hole, so that the first end of the lock pin is inserted into and pulled out of the lock hole of the lock catch 101, and the second end of the lock pin is provided with a screw hole;
a motor bracket 301 fixed to a fixing side of a structure to be locked;
a motor 302 fixed to the motor holder 301; and
and a first end of the screw 204 is connected with the shaft of the motor 302, and a second end of the screw can be in threaded engagement with a screw hole of the lock pin 201, so that when the screw is driven by the shaft of the motor 302 to rotate, the lock pin 201 can be driven to slide in the guide hole of the support 202, the first end of the lock pin 201 is inserted into and pulled out of the lock hole of the lock catch 101, and the locking and unlocking of the satellite launching box are completed.
The moving side of the mechanism to be locked can be any component which moves through unlocking, such as an upper cover of a satellite launching box, and the fixing side of the mechanism to be locked can be any corresponding component which is kept fixed relative to the moving component when unlocking, such as a box body of the satellite launching box. That is, in the locked state, the mobile party is locked with the fixed party by the satellite transmission box locking and unlocking mechanism 100, and in the unlocked state, the mobile party is released from the fixed party by the satellite transmission box locking and unlocking mechanism 100.
The lock 101 may be a rod-shaped member, the proximal end of which is fixed to the moving part of the mechanism to be locked by means of screw connection or the like, and the distal end of which may have a shape suitable for being inserted into the holder hole of the holder 202 and is provided with a lock hole.
The support 202 and the motor support 301 are both fixed on a fixing part of the structure to be locked, for example, fixed on a box body of a satellite launching box through bolt connection, and the two are close to each other. The support 202 may be a housing structure, and may have a side surface provided with a support hole for the latch 101 to enter and exit, an end provided with a hole for the screw 204 to pass through, and an inner portion provided with a guide hole, etc. to facilitate engagement of the latch 101 and the lock pin 201, for example, as shown in the sectional views of fig. 1 and 2.
The lock pin 201 is located in the guide hole of the support 202, and the maximum outer diameter of the lock pin may be slightly smaller than the inner diameter of the guide hole, so that the lock pin can slide in the guide hole, so that the distal end of the lock pin can be inserted into and separated from the lock hole of the lock catch 101, and the actions of inserting and pulling the pin can be completed.
The cross-sectional shape of the lock pin 201 may be, for example, as shown in the cross-sectional view of fig. 2, with a distal portion having a diameter slightly smaller than the lock hole of the lock catch 101, thereby facilitating insertion into and removal from the lock hole; the diameter of the middle part is larger than that of the distal end part and is smaller than that of the guide hole of the support 202; the diameter of the proximal part of the bracket is slightly smaller than that of the guide hole of the support 202, so that the bracket can slide in the guide hole; the proximal end of which is provided with an internal bore, the end of which is provided with the threaded hole, thereby allowing the threaded rod 204 to engage with the threaded hole.
Of course, in other embodiments, the locking pin 201 may have other cross-sectional shapes, for example, the threaded hole may be provided directly at the end of its proximal end.
The motor bracket 301 is used to fix the motor 302 to a fixing part of the structure to be locked, for example, to a box body of a satellite launch box. For example, the motor bracket 301 may have an L-shaped structure as shown in fig. 1, that is, it includes a bottom portion and a side portion, the bottom portion may be fixed to a fixing portion of the structure to be locked by, for example, a bolt connection, and the side portion may be fixed to the motor 302 by, for example, a bolt connection.
In some embodiments, the motor holder 301 is integrated with the motor 302, that is, the motor 302 can be provided with the motor holder and can be fixed on the fixing side of the structure to be locked.
The motor 302 may be electrically connected to a control device, receive a locking command and an unlocking command from the control device, and rotate in a first direction and a second direction, respectively.
The screw 204 may have a structure as shown in the cross-sectional view of fig. 2, for example, and the proximal end thereof may be provided with a hole, into which the shaft of the motor 302 may be inserted, and the shaft of the motor 302 and the screw 204 may be fixedly connected by a key connection, a pin connection, an interference fit, or the like, so that the screw 204 may be rotated by the shaft of the motor 302. The distal end of the screw 204 may be of a smaller diameter and provided with a thread capable of engaging the threaded hole of the lock pin 201. Therefore, when the screw 204 is driven by the shaft of the motor 302 to rotate in the first direction, the lock pin 201 can be driven to be inserted into the lock hole of the lock catch 101, so that the bolt action is completed, and the locking of the satellite launching box is realized; when the screw 204 is driven by the shaft of the motor 302 to rotate in the second direction, the lock pin 201 can be driven to exit from the lock hole of the lock catch 101, so that the pin pulling action is completed, and the unlocking of the satellite launching box is realized.
In some embodiments, the threaded bore of the lock pin 201 and the threaded shaft 204 have a stroke equal to the latching and unlatching stroke of the first end of the lock pin 201 in the locking bore of the latch 101, such that when the latching and unlatching stroke is complete, the threaded engagement of the threaded bore of the lock pin 201 and the threaded shaft 204 is also just complete. Therefore, when the bolt and the pin pulling action are completed and the motor continues to rotate, the screw hole of the lock pin 201 and the thread of the screw 204 are meshed and withdrawn, and the screw 204 idles, so that the thread between the screw hole of the lock pin 201 and the screw 204 can be prevented from being locked.
In some embodiments, the satellite launch box locking and unlocking mechanism 100 further comprises:
a first compression spring 203 which abuts between a shoulder of the lock pin 201 and an inner end wall of the support 202; and
a second pressure spring 205 which is abutted between the end of the second end of the lock pin 201 and the motor bracket 301, thereby
When the first end of the lock pin 201 is inserted into the lock hole of the lock catch 101, the first compression spring 203 causes the screw hole of the second end of the lock pin 201 to press against the head of the thread of the second end of the screw 204, the second compression spring 205 causes the first end of the lock pin 201 to be held in the lock hole of the lock catch 101, and
when the first end of the lock pin 201 is completely pulled out of the lock hole of the lock catch 101, the second compression spring 205 causes the screw hole at the second end of the lock pin 201 to be pressed against the root of the thread at the second end of the screw 204, and the first compression spring 203 causes the first end of the lock pin 201 to be kept out of the lock hole of the lock catch 101.
The shoulder of the lock pin 201 is formed between the middle part with a smaller diameter and the proximal part with a larger diameter of the lock pin 201, for example, the first pressure spring 203 can be sleeved on the middle part and is in a compression state under the locking and unlocking states of the mechanism, so that when the latch action of the lock pin 201 is completed, the screw hole of the lock pin 201 can be abutted against the end part of the screw 204, the screw hole of the lock pin 201 and the end part of the screw 204 are always contacted and pressed mutually, and therefore when the motor 302 rotates reversely, the screw hole of the lock pin 201 and the thread at the end part of the screw 204 can be rapidly engaged; when the pin pulling action of the lock pin 201 is completed, the lock pin 201 can be abutted to the direction of the screw 204 and the motor 302, so that the first end of the lock pin 201 is kept outside the lock hole of the lock catch 101, and the mechanism is kept in an unlocking state.
The second pressure spring 205 may be, for example, sleeved on a circumference of the screw 204 near the first end, and abuts between an end of the second end of the lock pin 201 and the motor holder 301, and is in a compressed state in both the locked and unlocked states of the mechanism, so that when the latch action of the lock pin 201 is completed, the lock pin 201 may be abutted to the direction of the latch 101, so that the first end of the lock pin 201 is held in the lock hole of the latch 101, thereby holding the mechanism in the locked state, and further, the mechanical strength of the lock pin 201 and the support 202 may ensure that the latch 101 is locked at the locked position and cannot move, thereby ensuring that the mechanism is in the locked state; when the pin pulling action of the lock pin 201 is completed, the screw hole of the lock pin 201 can be abutted against the root of the thread of the screw 204, so that the screw hole of the lock pin 201 and the root of the thread of the screw 204 are always contacted and mutually pressed, and therefore when the motor 302 rotates reversely, the screw hole of the lock pin 201 and the thread of the root of the screw 204 can be quickly engaged.
Thus, under the combined action of the first compression spring 203 and the second compression spring 205, the lock pin 201 and the screw 204 are always contacted and pressed against each other, so that when the motor 302 rotates reversely, the lock pin 201 and the screw 204 can be rapidly engaged to realize pin pulling or pin plugging. At the same time, the cooperation of the first pressure spring 203 and the second pressure spring 205 also ensures that the first end of the lock pin 201 is kept inserted into or separated from the lock hole of the lock catch 101, so that the mechanism is kept in the locking or unlocking position.
According to the locking and unlocking mechanism 100 for the satellite launching box, the motor 302 is used for driving the screw 204 to realize pin pulling/bolt insertion through threads, and the threads are labor-saving structures, so that the pin pulling/bolt insertion force range is wide and can be large, and the pin pulling/bolt insertion stroke can be adjusted at will according to needs, so that the locking and unlocking requirements of various different occasions can be met. In addition, the whole mechanism has simple and compact structure, small size, stable operation, no impact and no vibration.
The satellite launch box locking and unlocking mechanism according to embodiments of the present invention is described above with reference to the accompanying drawings, it being noted that the above description and illustrations are only examples and are not limiting of the present invention. In other embodiments of the invention, the apparatus may have more, fewer, or different components, and the connections, inclusion, and functional relationships between the components may differ from those described and illustrated. For example, the shape and structure of each component may be different from those described and illustrated, and the position and connection relationship between the components may also be different from those described and illustrated, and so on. All such variations are within the spirit and scope of the present invention.
Although the present invention has been disclosed above by way of examples, the present invention is not limited thereto. Various changes and modifications within the spirit and scope of the invention may be effected by those skilled in the art without departing from the spirit and scope of the invention, which is to be limited only by the language of the claims and the equivalents thereof.
Claims (4)
1. A satellite launch box locking and unlocking mechanism (100), comprising:
the lock catch (101) is fixed on the moving side of the mechanism to be locked, and a lock hole is formed in the end part of the lock catch;
the support (202) is fixed on the fixing side of the structure to be locked, is provided with a support hole for the lock catch (101) to enter and exit, and is internally provided with a guide hole;
the lock pin (201) is positioned in the guide hole of the support (202) and can slide in the guide hole, so that the first end of the lock pin is inserted into the lock hole of the lock catch (101) and pulled out, and the second end of the lock pin is provided with a screw hole;
the motor bracket (301) is fixed on a fixing side of the structure to be locked;
a motor (302) fixed to the motor holder (301); and
and a first end of the screw rod (204) is connected with a shaft of the motor (302), and a second end of the screw rod can be in threaded engagement with a screw hole of the lock pin (201), so that when the screw rod is driven by the shaft of the motor (302) to rotate, the lock pin (201) can be driven to slide in a guide hole of the support (202), the first end of the lock pin (201) is inserted into and pulled out of a lock hole of the lock catch (101), and the locking and unlocking of the satellite launching box are completed.
2. The satellite launch box lock release mechanism (100) of claim 1, wherein the threaded bore of the locking pin (201) and the threaded rod (204) have a threaded stroke equal to the latching and unlatching stroke of the first end of the locking pin (201) in the locking bore of the shackle (101), such that when the latching and unlatching stroke is complete, the threaded engagement of the threaded bore of the locking pin (201) and the threaded rod (204) is also just complete.
3. The satellite launch box lock release mechanism (100) of claim 2, further comprising:
a first pressure spring (203) which is abutted between the shoulder of the lock pin (201) and the inner end wall of the support (202); and
a second pressure spring (205) which is abutted between the end part of the second end of the lock pin (201) and the motor bracket (301) so as to
When the first end of the lock pin (201) completes the latch in the lock hole of the lock catch (101), the first compression spring (203) enables the screw hole of the second end of the lock pin (201) to be pressed against the head of the thread of the second end of the screw rod (204), the second compression spring (205) enables the first end of the lock pin (201) to be kept in the lock hole of the lock catch (101), and
when the first end of the lock pin (201) is pulled out of the lock hole of the lock catch (101), the second pressure spring (205) enables the screw hole of the second end of the lock pin (201) to be pressed at the root of the thread of the second end of the screw rod (204), and the first pressure spring (203) enables the first end of the lock pin (201) to be kept out of the lock hole of the lock catch (101).
4. The locking and unlocking mechanism (100) for the satellite launching box as claimed in claim 1, wherein the moving side of the mechanism to be locked is an upper cover of the satellite launching box, and the fixing side of the mechanism to be locked is a box body of the satellite launching box.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210648365.XA CN114735249B (en) | 2022-06-09 | 2022-06-09 | Locking and unlocking mechanism for satellite launching box |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210648365.XA CN114735249B (en) | 2022-06-09 | 2022-06-09 | Locking and unlocking mechanism for satellite launching box |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114735249A true CN114735249A (en) | 2022-07-12 |
| CN114735249B CN114735249B (en) | 2022-08-16 |
Family
ID=82287793
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210648365.XA Active CN114735249B (en) | 2022-06-09 | 2022-06-09 | Locking and unlocking mechanism for satellite launching box |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114735249B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115057012A (en) * | 2022-08-03 | 2022-09-16 | 北京劢亚科技有限公司 | Multi-satellite chain type launching, locking, unlocking and ejecting mechanism |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0628478A1 (en) * | 1993-06-04 | 1994-12-14 | AEROSPATIALE Société Nationale Industrielle | Device for ejecting removable object attached to a structure |
| US20150314893A1 (en) * | 2014-05-02 | 2015-11-05 | Macdonald Dettwiler & Associates Inc. | Spacecraft capture mechanism |
| CN107628269A (en) * | 2017-07-31 | 2018-01-26 | 上海宇航系统工程研究所 | A kind of linkage of unlocking declines satellite On-orbit release device |
| 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 |
| CN112498751A (en) * | 2020-12-15 | 2021-03-16 | 航天科工火箭技术有限公司 | Connecting and unlocking device |
| CN113879569A (en) * | 2021-10-09 | 2022-01-04 | 航天科工火箭技术有限公司 | Low-impact unlocking satellite-arrow separation device and satellite-arrow separation system |
-
2022
- 2022-06-09 CN CN202210648365.XA patent/CN114735249B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0628478A1 (en) * | 1993-06-04 | 1994-12-14 | AEROSPATIALE Société Nationale Industrielle | Device for ejecting removable object attached to a structure |
| US20150314893A1 (en) * | 2014-05-02 | 2015-11-05 | Macdonald Dettwiler & Associates Inc. | Spacecraft capture mechanism |
| CN107628269A (en) * | 2017-07-31 | 2018-01-26 | 上海宇航系统工程研究所 | A kind of linkage of unlocking declines satellite On-orbit release device |
| 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 |
| CN112498751A (en) * | 2020-12-15 | 2021-03-16 | 航天科工火箭技术有限公司 | Connecting and unlocking device |
| CN113879569A (en) * | 2021-10-09 | 2022-01-04 | 航天科工火箭技术有限公司 | Low-impact unlocking satellite-arrow separation device and satellite-arrow separation system |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115057012A (en) * | 2022-08-03 | 2022-09-16 | 北京劢亚科技有限公司 | Multi-satellite chain type launching, locking, unlocking and ejecting mechanism |
| CN115057012B (en) * | 2022-08-03 | 2022-10-25 | 北京劢亚科技有限公司 | Multi-satellite chain type launching, locking, unlocking and ejecting mechanism |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114735249B (en) | 2022-08-16 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN114735249B (en) | Locking and unlocking mechanism for satellite launching box | |
| US6530718B2 (en) | Connector assembly | |
| US5129753A (en) | Shape memory wire latch mechanism | |
| US6769830B1 (en) | Connector assembly | |
| CN110104161B (en) | Folding tail unfolding mechanism and unfolding method thereof | |
| EP3558822B1 (en) | Actuated resettable shockless hold down and release mechanism (ares hdrm) | |
| CN112389684B (en) | Connecting and unlocking structure driven by shape memory alloy | |
| CN111114754B (en) | Locking mechanism and folding airfoil with same | |
| CN109515751B (en) | Compressing and releasing mechanism based on hot knife | |
| CN102363444B (en) | Transverse folding mechanism for empennage | |
| CN113148244B (en) | On-orbit assembling and butting mechanism and method for spacecraft group | |
| US6186442B1 (en) | Wing deployer and locker | |
| CN111717420B (en) | Accurate limiting and unfolding device and unfolding limiting method for pressing mechanism | |
| CN111332503A (en) | Passive in-orbit docking device for space antenna module | |
| KR100692237B1 (en) | Folding type tail boom | |
| CN114802821B (en) | Unfolding in-place locking device and spacecraft | |
| US6568950B2 (en) | Umbilical disconnect connector | |
| US6203237B1 (en) | Apparatus for releasably connecting first and second structures together | |
| CN113753269A (en) | Satellite release device | |
| CN220176023U (en) | Gyro handle | |
| CN214824053U (en) | Wing folding and unfolding device and unmanned aerial vehicle | |
| CN220187557U (en) | Missile wing folding mechanism | |
| CN116294844A (en) | Multi-degree-of-freedom separation spring mechanism, fairing separation and interstage separation device | |
| CN218703982U (en) | Star and arrow locking and releasing device | |
| CN212271843U (en) | Intelligent improved controller for lock |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |