CN110282166B - A can accomodate ejection mechanism for small-size rope system satellite - Google Patents
A can accomodate ejection mechanism for small-size rope system satellite Download PDFInfo
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- CN110282166B CN110282166B CN201910462629.0A CN201910462629A CN110282166B CN 110282166 B CN110282166 B CN 110282166B CN 201910462629 A CN201910462629 A CN 201910462629A CN 110282166 B CN110282166 B CN 110282166B
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- connecting rod
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/002—Launch systems
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
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Abstract
The invention discloses a storable ejection mechanism for a small tethered satellite star, relates to the field of tethered satellite release and recovery, and can store the tethered satellite star in the mechanism. The invention comprises the following steps: the fixed plate, folding rod, motor, guide face, butt joint dish, electromagnetic clutch, torsional spring, connecting axle, mount pad. The fixing plate is provided with a mounting seat, the mounting seat is relatively provided with two folding rods, and joints of the folding rods are provided with connecting shafts. The shaft end of the connecting shaft is provided with an electromagnetic clutch, the electromagnetic clutch is connected with an output shaft of the motor, and a torsion spring is further arranged in the radial direction of the connecting shaft. The other end of the folding rod is connected with the butt joint disk, the butt joint disk and the guide surface are of circular structures and made of soft materials, the edge of the butt joint disk is connected with the edge of the guide surface, and the edge of the guide surface is connected with the mounting seat. When the child star is recovered, the guide surface formed by the soft material helps the posture of the child star to be corrected, is convenient to recover quickly, and is stored after being recovered.
Description
Technical Field
The invention relates to the field of release and recovery of tethered satellites, in particular to a retractable ejection mechanism for small tethered satellite satellites.
Background
With the development of space exploration technology, tethered satellites are widely concerned as a novel space vehicle, wherein the most critical problem is the release and recovery of the tethered satellites, and a complete release and recovery device which can be repeatedly used is needed for ground simulation tests and space tests. An ejection mechanism and method for small tethered satellite satellites is disclosed in Chinese patent 201410120144.0, which has a rigid docking cone and utilizes gear and rack transmission to complete the release and recovery processes, and although the ejection mechanism is simple in structure and can be reused, the structural size of an upper fixing plate is larger, which is not beneficial to carrying in ground tests and practical applications, so that a storable tethered satellite ejection mechanism is necessary to design.
Disclosure of Invention
The invention provides a storable ejection mechanism for a small tethered satellite star, which is used for the ejection and recovery guide of the tethered satellite star and can store the tethered satellite star in the mechanism.
In order to achieve the purpose, the invention adopts the following technical scheme:
a stowable ejection mechanism for a small tethered satellite, comprising: the fixed plate, folding rod, motor, guide face, butt joint dish, electromagnetic clutch, torsional spring, connecting axle, mount pad.
The fixing plate is provided with a mounting seat, the mounting seat is relatively provided with two folding rods, and joints of the folding rods are provided with connecting shafts. The shaft end of the connecting shaft is provided with an electromagnetic clutch, the electromagnetic clutch is connected with an output shaft of the motor, and a torsion spring is further arranged in the radial direction of the connecting shaft.
When the ejection device is ejected, the electromagnetic clutch is disconnected, and the restoring force of the torsion spring is utilized to push the butt joint disk, so that the soft material is unfolded to form a conical guide surface. When the butt joint disc is stored, the connecting shaft is connected with the motor through the electromagnetic clutch, and the motor rotates to withdraw the butt joint disc to complete storage.
The other end of the folding rod is connected with a butt joint disk, the butt joint disk is in a circular ring shape, the guide surface is also in a circular ring structure and is made of soft materials, the edge of an inner ring of the butt joint disk is connected with the edge of an outer ring of the guide surface, and the edge of the inner ring of the guide surface is connected with the mounting seat.
When the folding rod is unfolded, the guide surface is unfolded into a conical space for containing; when the folding rod is folded, the guide surface is folded to lean against the fixed plate.
Further, the folding rod is divided into three sections, namely a first connecting rod, a second connecting rod and a third connecting rod, wherein the second connecting rod is divided into a left connecting rod and a right connecting rod. The first connecting rod is U-shaped, and the inner sides of the U-shaped openings of the left connecting rod, the right connecting rod and the first connecting rod are connected through connecting shafts. The other ends of the left connecting rod and the right connecting rod clamp the third connecting rod and are connected through the connecting shaft.
Further, the guide surface is made of a deformable polymer material.
Further, the guiding surface is a woven radiation-proof material
The invention has the beneficial effects that:
the folding rod capable of controlling unfolding and folding is adopted, the subsatellite can be stored and ejected by matching with the guide surface, the folding rod can be repeatedly used for ground simulation experiments of releasing and recovering tethered satellites, and the conical guide surface is helpful for adjusting the attitude of the subsatellite to finish recovery; the guide surface is made of soft materials, so that the ejection mechanism can be opened or tightened, the size of the ejection mechanism is reduced, and the ejection mechanism is convenient to carry; the torsional spring that the joint department of folding rod set up can also slow down the impact when the child star retrieves.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings required to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic view of the present invention in its expanded configuration;
FIG. 2 is a general schematic view of the present invention after storage;
FIG. 3 is a partial schematic view of the first connecting shaft;
fig. 4 is a top view of a folding bar.
1-fixed plate, 2-folding rod, 21-first connecting rod, 22-second connecting rod, 221-left connecting rod, 222-right connecting rod, 23-third connecting rod, 3-motor, 4-guide surface, 5-butt joint disk, 6-sleeve, 7-electromagnetic clutch, 8-bearing, 9-torsion spring, 10-key, 11-first connecting shaft, 12-second connecting shaft, 13-third connecting shaft and 14-mounting seat.
Detailed Description
In order that those skilled in the art will better understand the technical solutions of the present invention, the present invention will be further described in detail with reference to the following detailed description.
An embodiment of the present invention provides a retractable ejection mechanism for a small tethered satellite, as shown in fig. 1, including: the device comprises a fixed plate 1, a folding rod 2, a motor 3, a guide surface 4, a butt joint disk 5, an electromagnetic clutch 7, a torsion spring 9, a bearing 8, a key 10, a first connecting shaft 11, a second connecting shaft 12, a third connecting shaft 13 and a mounting seat 14.
The fixing plate 1 is provided with a mounting seat 14, and the mounting seat 14 is provided with two folding rods 2 oppositely. The mounting seat 14 is provided with a mounting groove, and the folding rod 2 is mounted at the position of the mounting groove. The folding bar 2 and the mounting seat 14 are connected by a first connecting shaft 11, and the first connecting shaft 11 and the folding bar 2 are connected by a key 10.
The folding bar 2 is divided into three segments, as shown in fig. 4, a first connecting bar 21, a second connecting bar 22, and a third connecting bar 23, wherein the second connecting bar 22 is divided into a left connecting bar 221 and a right connecting bar 222.
The first connecting rod 21 is U-shaped, and the left connecting rod 221, the right connecting rod 222 and the inner side of the U-shaped opening of the first connecting rod 21 are connected by the second connecting shaft 12. The left connecting rod 221, the right connecting rod 222 and the second connecting shaft 12 are fixedly connected. The first connecting shaft 11 is connected to the first connecting rod 21 by a key 10.
The first connecting rod 21, the left connecting rod 221 and the right connecting rod 222 are connected through the second connecting shaft 12, and the second connecting shaft 12 is fixedly connected with the left connecting rod 221 and the right connecting rod 222.
The other ends of the left connecting rod 221 and the right connecting rod 222 clamp the third connecting rod 23 and are connected through a third connecting shaft 13, and the third connecting shaft 13 is fixedly connected with the third connecting rod 23. The other end of the third connecting rod 23 is connected with the butt joint disk 5.
The butt-joint tray 5 is in a circular ring shape, the guide surface 4 is also in a circular ring structure and is made of soft materials, the inner circular ring edge of the butt-joint tray 5 is connected with the outer circular ring edge of the guide surface 4, and the inner circular ring edge of the guide surface 4 is connected with the mounting seat 14.
As shown in fig. 3, bearings 8 and electromagnetic clutches 7 are disposed at shaft ends of the first connecting shaft 11, the second connecting shaft 12 and the third connecting shaft 13. The electromagnetic clutch 7 is connected with an output shaft of the motor 3, and a sleeve 6 is arranged outside the output shaft. The first connecting plate 21 and the fixing plate 1 are matched with each other, the first connecting plate 21 and the second connecting rod 22 are matched with each other, the second connecting rod 22 and the third connecting rod 23 are provided with grooves, torsion springs 9 are placed in the grooves, and the torsion springs 9 are respectively sleeved on the outer sides of the first connecting shaft 11, the second connecting shaft 12 and the third connecting shaft 13.
The working principle of the invention is as follows:
the tethered satellite neutron star is connected with the body by a tether, and the fixing plate 1 is arranged on the body satellite. At the initial time, the electromagnetic clutch 7 is energized, and the output torque of the motor 3 and the restoring force of the torsion spring 9 are balanced to form the ejection mechanism in the storage state as shown in fig. 2. When the subsatellite is released, the electromagnetic clutch 7 is powered off, the torsion spring 9 at the joint of the connecting rod drives the folding rod 2 to move to the balance position of the torsion spring 9 due to restoring force, and therefore the butt joint disk 5 is driven to move to the configuration position which expands the guide surface 4 into the conical guide surface, and subsatellite ejection is completed. During recovery, the unfolded guide surface 4 can adjust the pose of the sub-star, and is beneficial to inserting the tether fixing part pair into the round hole on the upper fixing plate 1. After recovery, the electromagnetic clutch 7 is electrified, torque output by the motor 3 is transmitted to the connecting shafts, restoring force of the torsion spring 9 is overcome, the folding rod 2 is driven to move to the position of the initial closed state, and storage of the ejection mechanism is completed.
The above description is only for the specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (3)
1. A stowable ejection mechanism for a small tethered satellite, comprising: the device comprises a fixed plate (1), a folding rod (2), a motor (3), a guide surface (4), a butt joint disc (5), an electromagnetic clutch (7), a torsion spring (9), a connecting shaft and a mounting seat (14);
the fixing plate (1) is provided with a mounting seat (14), the mounting seat (14) is oppositely provided with two folding rods (2), the folding rods (2) are connected with the mounting seat (14) through connecting shafts, and the joints of the folding rods (2) are provided with the connecting shafts;
an electromagnetic clutch (7) is arranged at the shaft end of the connecting shaft, the electromagnetic clutch (7) is connected with an output shaft of the motor (3), and a torsion spring (9) is further arranged in the radial direction of the connecting shaft;
the other end of the folding rod (2) is connected with the butt joint disc (5), the butt joint disc (5) is in a circular ring shape, the guide surface (4) is also in a circular ring shape structure and is made of soft materials, the edge of an inner ring of the butt joint disc (5) is connected with the edge of an outer ring of the guide surface (4), and the edge of the inner ring of the guide surface (4) is connected with the mounting seat (14);
the folding rod (2) is divided into three sections, namely a first connecting rod (21), a second connecting rod (22) and a third connecting rod (23), wherein the second connecting rod (22) is divided into a left connecting rod (221) and a right connecting rod (222);
the first connecting rod (21) is U-shaped, and the inner sides of the U-shaped openings of the left connecting rod (221), the right connecting rod (222) and the first connecting rod (21) are connected through the connecting shafts;
the other ends of the left connecting rod (221) and the right connecting rod (222) clamp the third connecting rod (23) and are connected through the connecting shaft.
2. The stowable ejection mechanism for a small tethered satellite according to claim 1 wherein the guide surface (4) is a deformable polymeric material.
3. The stowable ejection mechanism for a small tethered satellite according to claim 1 wherein the guide surface (4) is of woven type radiation protective material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910462629.0A CN110282166B (en) | 2019-05-30 | 2019-05-30 | A can accomodate ejection mechanism for small-size rope system satellite |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910462629.0A CN110282166B (en) | 2019-05-30 | 2019-05-30 | A can accomodate ejection mechanism for small-size rope system satellite |
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| CN110282166A CN110282166A (en) | 2019-09-27 |
| CN110282166B true CN110282166B (en) | 2022-08-05 |
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| CN201910462629.0A Active CN110282166B (en) | 2019-05-30 | 2019-05-30 | A can accomodate ejection mechanism for small-size rope system satellite |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114212281B (en) * | 2021-12-10 | 2023-04-18 | 哈尔滨工业大学 | Electromagnetic-triggered repeated connection and separation release device for primary and secondary satellites and working method of electromagnetic-triggered repeated connection and separation release device |
| CN114735250B (en) * | 2022-06-09 | 2022-10-18 | 北京劢亚科技有限公司 | Satellite launching box ejection device |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5725183A (en) * | 1994-08-30 | 1998-03-10 | Aerospatiale Societe Nationale Industrielle | Multicontact spacing control device |
| CN103964001A (en) * | 2014-03-28 | 2014-08-06 | 南京航空航天大学 | Small tethered satellite catapulting mechanism and catapulting method |
| CN107128511A (en) * | 2017-04-13 | 2017-09-05 | 北京航空航天大学 | A kind of reusable spaceborne micro-nano satellite catapult-launching gear |
| CN108415449A (en) * | 2018-05-21 | 2018-08-17 | 北京航空航天大学 | A kind of device applied to the expansion of Aerospace Satellite system tether, recycling and tension force |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AU1411401A (en) * | 2000-02-17 | 2001-08-27 | Indian Space Research Organisation | A shape memory alloy step drive mechanism for providing step motion to a system |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5725183A (en) * | 1994-08-30 | 1998-03-10 | Aerospatiale Societe Nationale Industrielle | Multicontact spacing control device |
| CN103964001A (en) * | 2014-03-28 | 2014-08-06 | 南京航空航天大学 | Small tethered satellite catapulting mechanism and catapulting method |
| CN107128511A (en) * | 2017-04-13 | 2017-09-05 | 北京航空航天大学 | A kind of reusable spaceborne micro-nano satellite catapult-launching gear |
| CN108415449A (en) * | 2018-05-21 | 2018-08-17 | 北京航空航天大学 | A kind of device applied to the expansion of Aerospace Satellite system tether, recycling and tension force |
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| CN110282166A (en) | 2019-09-27 |
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