CN108791967B - Controllable step-by-step unlocking device applied to spacecraft - Google Patents
Controllable step-by-step unlocking device applied to spacecraft Download PDFInfo
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- CN108791967B CN108791967B CN201810629957.0A CN201810629957A CN108791967B CN 108791967 B CN108791967 B CN 108791967B CN 201810629957 A CN201810629957 A CN 201810629957A CN 108791967 B CN108791967 B CN 108791967B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/645—Separators
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Abstract
The invention discloses a controllable step-by-step unlocking device applied to a spacecraft, which comprises a special-shaped screw rod, a locked plate A, a locked plate B, a locked plate C, a locked plate D, a guide end cover, an outer cylinder, a guide sleeve, a stepping motor, a bearing and a gland nut, wherein the special-shaped screw rod is fixed on the locked plate A; the guide sleeve passes through bearing movable mounting in the urceolus, and the lower extreme links to each other with step motor's pivot end, upper end and special-shaped screw rod swing joint, and special-shaped screw rod one end activity sets up in the guide sleeve, and the other end passes the direction end cover to link to each other with being locked board D, being locked board C, being locked board B, being locked board A in proper order through gland nut. The invention adopts one stepping motor to realize multiple unlocking operations, has the advantages of light weight, simple control, high reliability and the like, and is an unlocking device with higher application value for multiple ordered unlocking occasions on the spacecraft.
Description
Technical Field
The invention relates to a spacecraft structure, in particular to a controllable step-by-step unlocking device applied to a spacecraft.
Background
The unlocking device on the spacecraft is increasingly widely applied, and more requirements are put forward on the unlocking device according to different application occasions. The traditional on-satellite unlocking generally adopts an initiating explosive device unlocking device, a memory alloy unlocking device, a hot knife cutting device and the like. The initiating explosive device unlocking device is large in consumption and impact response, and belongs to one-time unlocking; memory alloy needs to be heated in an on-orbit mode to cause phase change of functional materials to realize unlocking, but the unlocking time sequence is difficult to control; the manner of unlocking the hot knife cutting cord also faces the problems described above. Therefore, the conventional on-board unlocking device is high in cost, most of the conventional on-board unlocking device is used for a single time, and the conventional on-board unlocking device is difficult to control the unlocking time sequence.
Disclosure of Invention
Aiming at the defects of the prior unlocking device in unlocking time sequence, the invention provides a novel controllable step-by-step unlocking device suitable for a spacecraft, which is considered from the aspects of low cost, low impact, high reusability, light weight, simple control, high reliability and the like.
In order to achieve the purpose, the invention is specifically realized by the following technical scheme:
a controllable step-by-step unlocking device applied to a spacecraft comprises a special-shaped screw rod, a locked plate A, a locked plate B, a locked plate C, a locked plate D, a guide end cover, an outer cylinder, a guide sleeve, a stepping motor, a bearing and a compression nut; the guide sleeve passes through bearing movable mounting in the urceolus, and the lower extreme links to each other with step motor's pivot end, upper end and special-shaped screw rod swing joint, and special-shaped screw rod one end activity sets up in the guide sleeve, and the other end passes the direction end cover to link to each other with being locked board D, being locked board C, being locked board B, being locked board A in proper order through gland nut.
Furthermore, the guide end cover is made of a titanium alloy material and is installed at the upper end of the outer cylinder through a screw, and the special-shaped screw is screwed out from a threaded hole in the center of the special-shaped screw; when step motor rotated, the dysmorphism screw rod can produce concertina movement, and is different according to the flexible length of dysmorphism screw rod, can unblock in order by locking board A, by locking board B, by locking board C, by locking board D.
Furthermore, the inner cavity of the guide sleeve is a square cavity, one end of the special-shaped screw rod is a square sliding block and forms clearance fit with the guide sleeve, and therefore the special-shaped screw rod can freely slide in the inner cavity of the guide sleeve along the axial direction.
Further, all be equipped with the through-hole in the middle of by locking plate A, by locking plate B, by locking plate C, by locking plate D, the aperture of this through-hole is greater than the diameter of special-shaped screw.
Furthermore, the stepping motor is fixedly connected with the outer barrel, and the motor generates rotary motion under the control of a program, so that unlocking operation is realized.
Furthermore, the special-shaped screw rod is made of titanium alloy materials and is integrally processed and formed by a square sliding block and a screw rod.
The invention adopts the special-shaped screw rod as the locking part and the unlocking part, and the special-shaped screw rod and the guide sleeve can generate one-dimensional axial sliding in the inner cavity of the sleeve by certain matching without relative rotation. The threaded rod part of the special-shaped screw rod can penetrate through the threaded hole of the guide end cover to achieve the functions of guiding and locking. After the special-shaped screw rod part penetrates through the guide end cover, the extending part is used as a screw rod which actually participates in locking.
Due to the adoption of the technical scheme, the invention has the following advantages:
1. according to the size and the number of the locked components, the length of the special-shaped screw can be flexibly designed to adapt to different locking requirements;
2. the stepping motor is simple to control, sequential unlocking can be realized only by rotating towards one direction, and the reliability is high;
3. the unlocking device has no impact, high reusability and basically no consumable material. If necessary, repeated unlocking and locking actions can be realized.
Drawings
Fig. 1 is a schematic structural diagram of a controllable step-by-step unlocking device applied to a spacecraft according to an embodiment of the present invention.
FIG. 2 is a schematic view of a profile screw in the example.
Fig. 3 is a schematic view of a guide sleeve in an embodiment of the invention.
Detailed Description
The present invention will be described in detail with reference to specific examples.
As shown in fig. 1, the embodiment of the invention provides a controllable step-by-step unlocking device applied to a spacecraft, which comprises a special-shaped screw rod 1, a locked plate a2, a locked plate B3, a locked plate C4, a locked plate D5, a guide end cover 6, an outer cylinder 7, a guide sleeve 8, a stepping motor 9, a bearing 10 and a compression nut 11; the guide sleeve 8 is movably arranged in the outer cylinder 7 through a bearing 10, the lower end of the guide sleeve is connected with the rotating shaft end of the stepping motor 9, the upper end of the guide sleeve is movably connected with the special-shaped screw rod 1, one end of the special-shaped screw rod 1 is movably arranged in the guide sleeve 8, the other end of the special-shaped screw rod passes through the guide end cover 6, and the guide sleeve is sequentially connected with the locked plate D5, the locked plate C4, the locked plate B3 and the locked plate A2 through the compression nut 11.
The guide end cover 6 is made of titanium alloy materials and is installed at the upper end of the outer cylinder 7 through a screw, and the special-shaped screw rod 1 is screwed out from a threaded hole in the center of the special-shaped screw rod; when the stepping motor 9 rotates, the special-shaped screw 1 can make telescopic motion, and the locked plate a2, the locked plate B3, the locked plate C4 and the locked plate D5 can be sequentially unlocked according to the telescopic length of the special-shaped screw 1.
The inner cavity of the guide sleeve 8 is a square cavity, one end of the special-shaped screw rod 1 is also a square head and forms clearance fit with the guide sleeve 8, so that the special-shaped screw rod 1 can freely slide in the inner cavity of the guide sleeve 8 along the axial direction.
The inner cavity of the guide sleeve 8 is a square cavity, one end of the special-shaped screw rod 1 is a square sliding block and forms clearance fit with the guide sleeve 8, and therefore the special-shaped screw rod 1 can freely slide in the inner cavity of the guide sleeve 8 along the axial direction.
The step motor 9 is fixed with the outer cylinder 7, the two parts are fixed on the star body at the same time, and when the step motor 9 rotates under the program control, the output shaft of the motor drives the guide sleeve 8 to rotate under the support of the bearings 10 at the two ends.
The special-shaped screw 1 is made of titanium alloy material and is integrally processed and formed by a square sliding block and a screw
By locking board A2, by locking board B3, by locking board C4, by all being equipped with the through-hole in the middle of the locking board D5, the aperture of this through-hole and gland nut 11's external diameter cooperation, gland nut 11's center is the screw hole, with the screw-thread fit of dysmorphism screw rod 1.
The unlocking device of this embodiment drives special-shaped screw rod at the uide bushing internal rotation through step motor's clearance rotation under the program control of on-board computer, and special-shaped screw rod passes the screw hole of direction end cover and passes through the screw thread fastening with the locking part to realize that special-shaped screw rod is flexible along the axial rotation, accomplish the release action simultaneously. Specifically, in the pressing operation, the to-be-locked plate 5 passes through the special-shaped screw 1, then the compression nut 11 is screwed in from the top end of the special-shaped screw 1 and finally screwed into the to-be-pressed plate 5, and the compression nut 11 and the to-be-pressed plate 5 are fastened through a screw, so that the locking operation is realized. The locking operation of the locking plate a2, the locked plate B3, the locked plate C4, and the locked plate D5 is sequentially performed in this order. When the on-orbit unlocking is needed, the special-shaped screw rod 1 can be drawn out only by rotating the stepping motor 9, so that the special-shaped screw rod retracts into the inner cavity of the guide sleeve 8. The locking plate a2, the locked plate B3, the locked plate C4, the locked plate D5, and the like can be unlocked in sequence.
Therefore, the invention can adaptively improve the special-shaped screw rod 1 according to the number and the size of the parts needing to be locked, can realize sequential unlocking, and has the advantages of high reliability, mature working principle and simple control scheme.
The preferred embodiments of the present invention are provided only to help illustrate the present invention. The preferred embodiments are not intended to be exhaustive or to limit the invention to the precise embodiments disclosed. Many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the invention and the practical application, to thereby enable others skilled in the art to best utilize the invention. The invention is limited only by the claims and their full scope and equivalents.
Claims (4)
1. A controllable step-by-step unlocking device applied to a spacecraft is characterized by comprising a special-shaped screw rod (1), a locked plate A (2), a locked plate B (3), a locked plate C (4), a locked plate D (5), a guide end cover (6), an outer cylinder (7), a guide sleeve (8), a stepping motor (9), a bearing (10) and a compression nut (11);
the guide sleeve (8) is movably arranged in the outer barrel (7) through a bearing (10), the lower end of the guide sleeve is connected with the rotating shaft end of the stepping motor (9), the upper end of the guide sleeve is movably connected with the special-shaped screw (1), one end of the special-shaped screw (1) is movably arranged in the guide sleeve (8), the other end of the special-shaped screw penetrates through the guide end cover (6), and the special-shaped screw is sequentially connected with the locked plate D (5), the locked plate C (4), the locked plate B (3) and the locked plate A (2) through a compression nut (11);
the guide end cover (6) is made of a titanium alloy material and is arranged at the upper end of the outer cylinder (7) through a screw, and the special-shaped screw rod (1) is screwed out from a threaded hole in the center of the special-shaped screw rod; when the stepping motor (9) rotates, the special-shaped screw rod (1) can generate telescopic motion, and the locked plate A (2), the locked plate B (3), the locked plate C (4) and the locked plate D (5) can be unlocked in sequence according to different telescopic lengths of the special-shaped screw rod (1);
the inner cavity of the guide sleeve (8) is a square cavity, one end of the special-shaped screw rod (1) is a square sliding block and forms clearance fit with the guide sleeve (8), and therefore the special-shaped screw rod (1) can freely slide in the inner cavity of the guide sleeve (8) along the axial direction.
2. The controllable stepped unlocking device applied to spacecraft of claim 1, wherein the locked plate A (2), the locked plate B (3), the locked plate C (4) and the locked plate D (5) are all provided with through holes in the middle, and the diameter of each through hole is larger than that of the special-shaped screw (1).
3. A controlled step-by-step release mechanism for spacecraft as claimed in claim 1, wherein said stepper motor (9) is fixedly attached to said outer barrel (7).
4. The controllable step-by-step unlocking device applied to the spacecraft of claim 1, wherein the special-shaped screw (1) is made of titanium alloy materials and is integrally formed by a square sliding block and a screw.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810629957.0A CN108791967B (en) | 2018-06-19 | 2018-06-19 | Controllable step-by-step unlocking device applied to spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810629957.0A CN108791967B (en) | 2018-06-19 | 2018-06-19 | Controllable step-by-step unlocking device applied to spacecraft |
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| Publication Number | Publication Date |
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| CN108791967A CN108791967A (en) | 2018-11-13 |
| CN108791967B true CN108791967B (en) | 2020-07-14 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201810629957.0A Active CN108791967B (en) | 2018-06-19 | 2018-06-19 | Controllable step-by-step unlocking device applied to spacecraft |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113148226B (en) * | 2021-03-26 | 2022-10-25 | 上海卫星工程研究所 | One-rocket multi-satellite launching system with separation device and separation method |
| CN113636112A (en) * | 2021-08-25 | 2021-11-12 | 翎客航天科技(江阴)有限公司 | Energy storage type satellite-rocket separation device |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101875404B (en) * | 2009-12-17 | 2012-10-24 | 北京理工大学 | Sealed small low-impact release screw bolt |
| CN103321993B (en) * | 2013-06-25 | 2015-03-25 | 上海宇航系统工程研究所 | Device and method utilizing separation nut for connecting and releasing |
| US11111034B2 (en) * | 2016-04-25 | 2021-09-07 | Ruag Space Ab | Separable roller screw assembly for a space craft release mechanism system |
| CN107352049A (en) * | 2017-06-06 | 2017-11-17 | 上海卫星工程研究所 | Spacecraft memorial alloy driving rope holds repeatable tripper tightly |
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