CN108438258A - One kind being used for the in-orbit separation release device of satellite - Google Patents
One kind being used for the in-orbit separation release device of satellite Download PDFInfo
- Publication number
- CN108438258A CN108438258A CN201810136652.6A CN201810136652A CN108438258A CN 108438258 A CN108438258 A CN 108438258A CN 201810136652 A CN201810136652 A CN 201810136652A CN 108438258 A CN108438258 A CN 108438258A
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- Prior art keywords
- zone center
- separation
- satellite
- release device
- plate
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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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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Details Of Aerials (AREA)
Abstract
The invention discloses one kind being used for the in-orbit separation release device of satellite,Including zone center,Separating table and separation track,Zone center is internally provided with placed cavity,It places cavity wall and is connected with several support columns,Separation track is uniformly connected to zone center exterior lateral sides respectively,Separating table one end is connected with pressure-bearing frame,Separating table bottom surface is provided with sliding slot,Sliding slot and the mutually identical separation track of separation track and zone center are connected together through a hinge by hinge,Separation track bottom end is connected with several electric telescopic rods,Electric telescopic rod both ends pass through hinged seat and separation track,Zone center is connected together through a hinge,Separating table one end is connected with release spring,Release spring bottom end is cased with positioning tube,Positioning tube is connected with magnetic plate at port,Zone center sidewall surfaces are provided with several raised plates,Raised plate is internally provided with electromagnetic coil,Convenient for freely adjusting release angle and direction,Be conducive to the quick separating of satellite,It is simple in structure,Control is accurate,It is worthy to be popularized.
Description
Technical field
The present invention relates to satellite technology fields, specially a kind of to be used for the in-orbit separation release device of satellite.
Background technology
Satellite refers in the natural celestial body for doing cycling service around a planetary orbit and by closed orbit, artificial satellite
Generally it is also referred to as satellite.Artificial satellite is built by the mankind, is emitted to too with space flight carrier such as rocket, space shuttle etc.
In the air, around the earth or the device of other planets as natural satellite.Often the satellite of gas planet is all very much, separation release
Device detaches more separation load for master control discharge, is mechanical interface between the two, and separation release device is emitting
Separation load can safely and reliably be locked with the initial flying stage stage, controlled can release separation load, separating rate energy at any time
Reach certain size；
General separation release device cannot rationally adjust release angle and direction, be unfavorable for when satellite orbit works
The On-orbit release of satellite.
Invention content
In order to overcome the shortcomings of that prior art, the present invention provide one kind and being used for the in-orbit separation release device of satellite, no
The quick separating of multiple components only may be implemented, and convenient for freely adjusting release angle and direction, be conducive to the quick of satellite
Separation, simple in structure, control is accurate, is worthy to be popularized.
The technical solution adopted by the present invention to solve the technical problems is：One kind being used for the in-orbit separation release device of satellite,
Including zone center, separating table and separation track, the zone center is internally provided with placed cavity, if the placement cavity wall is connected with
Dry support column, the support column includes fixed section and spiral section, and described spiral section one end passes through electric screw and fixed section spiral shell
Rotation connection carries out length adjustment, and the fixed section and placed cavity link together, and the spiral section other end is connected with positioning plate,
The separation track is uniformly connected to zone center exterior lateral sides respectively, and described separating table one end is connected with pressure-bearing frame, the separation
Platform bottom surface is provided with sliding slot, and the sliding slot and separation track mutually coincide, and the separation track and zone center are hinged by hinge
It is connected together, the separation track bottom end is connected with several electric telescopic rods, and the electric telescopic rod both ends are by hinged
Seat and separation track, zone center are connected together through a hinge, and described separating table one end is connected with release spring, the release spring bottom end
It is cased with positioning tube, magnetic plate is connected at the positioning tube port, the zone center sidewall surfaces are provided with several raised plates,
The raised plate is internally provided with electromagnetic coil, and the position of all raised plates and the position of magnetic plate correspond, protrusion
Plate is attracted each other by electromagnetic coil and magnetic plate.
As a kind of preferred technical solution of the present invention, the zone center inner wall surface is provided with several tripods, phase
It is linked together by metallic rod between the adjacent tripod.
As a kind of preferred technical solution of the present invention, the positioning plate is formed by connecting by two blocks of hang plates, and hang plate
Between linked together and adjustment length by adjusting screw.
As a kind of preferred technical solution of the present invention, the zone center top and bottom end are respectively connected with butt joint ring, described
Butt joint ring side is provided with through-hole.
As a kind of preferred technical solution of the present invention, the support column and placement cavity wall annular link together, and
The distance between the adjacent support column is equal.
As a kind of preferred technical solution of the present invention, the raised plate and magnetic panel surface are using the knot being mutually clamped
Structure, and be hollow-core construction inside the raised plate and magnetic plate.
As a kind of preferred technical solution of the present invention, the release spring is made of multiple cylindrical springs, the cylindricality
Both ends of the spring is linked together by fixed disk.
As a kind of preferred technical solution of the present invention, the electric telescopic rod is controlled by telescope motor, institute
It states telescope motor and is mounted on zone center side.
Compared with prior art, the beneficial effects of the invention are as follows：
(1) primary is fixed using support column and positioning plate by the way that placed cavity is arranged, ensure that entirety is steady by the present invention
While qualitative, facilitate and discharge the shell of primary, mitigates weight, ensure the normal operation of satellite；
(2) present invention adjusts the angle of separation track using electric telescopic rod by the way that electric telescopic rod is arranged so that separation
Platform can be popped up along the direction of separation track, you can releasing for different requirements is completed in release angle and the direction for adjusting separating table
It puts；
(3) magnetic plate and raised plate are fixed together by the present invention using electromagnetic coil, can not only be fixed, but also can be with
Pop-up coordinates release spring, accelerates rate of release, be conveniently adjusted rate of release.
Description of the drawings
Fig. 1 is the whole schematic top plan view of the present invention；
Fig. 2 is the global sections flow diagram of the present invention；
Fig. 3 is the release spring structural schematic diagram of the present invention.
In figure：1- zone centers；101- tripods；102- metallic rods；103- butt joint rings；104- through-holes；2- separating tables；201-
Pressure-bearing frame；202- sliding slots；203- release springs；204- positioning tubes；205- magnetic plates；206- raised plates；207- electromagnetic coils；
208- cylindrical springs；209- fixes disk；3- detaches track；4- placed cavities；401- support columns；402- fixed sections；403- spiral sections；
404- electric screws；405- positioning plates；406- hang plates；407- adjusting screws；5- hinges；6- electric telescopic rods；7- hinged seats；
8- telescope motors.
Specific implementation mode
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation describes, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
The explanation of following embodiment is refer to the attached drawing, can be to the specific embodiment implemented to the example present invention.
The direction and position term that the present invention is previously mentioned, for example, "upper", " in ", "lower", "front", "rear", "left", "right", "inner", "
Outside ", " side " etc. is only direction and position with reference to annexed drawings.Therefore, the direction and position term used is to illustrate
And understand the present invention, rather than to limit the present invention.
Embodiment：
As shown in Figure 1 to Figure 3, the present invention provides one kind be used for the in-orbit separation release device of satellite, including zone center 1,
Separating table 2 and separation track 3, the zone center 1 are internally provided with placed cavity 4, and 4 inner wall of the placed cavity is connected with several branch
Dagger 401, the support column 401 include fixed section 402 and spiral section 403, and 403 one end of the spiral section passes through electric screw
404 connect progress length adjustment with 402 spiral of fixed section, and the fixed section 402 and placed cavity 4 link together, the spiral
403 other ends of section are connected with positioning plate 405, and positioning plate 405 is fixed on primary side using electric screw 404, you can realize
The fixation of primary, while primary can be discharged by packing up electric screw 404, and all separating tables 2 are with zone center 1
Center centered on dot center be symmetrical arranged.
The separation track 3 is uniformly connected to 1 exterior lateral sides of zone center respectively, and 2 one end of the separating table is connected with pressure-bearing
Frame 201,2 bottom surface of the separating table are provided with sliding slot 202, and the sliding slot 202 and separation track 3 mutually coincide, the separation rail
Road 3 and zone center 1 are connected together through a hinge by hinge 5, and 3 bottom end of separation track is connected with several electric telescopic rods 6, institute
It states 6 both ends of electric telescopic rod to be connected together through a hinge by hinged seat 7 and separation track 3, zone center 1, by adjusting electronic stretch
The length of contracting bar 6, since separation track 3 and zone center are hinged so that the angle of separation track 3 changes, and detaches track 3
Guiding role is primarily served, to realize the angle adjustment of release；
2 one end of the separating table is connected with release spring 203, and 203 bottom end of the release spring is cased with positioning tube 204, institute
It states and is connected with magnetic plate 205 at 204 port of positioning tube, 1 sidewall surfaces of the zone center are provided with several raised plates 206, institute
It states raised plate 206 and is internally provided with electromagnetic coil 207, the position of all raised plates 206 and the position of magnetic plate 205 are mutual
Corresponding, raised plate 206 is attracted each other by electromagnetic coil 207 and magnetic plate 205, by giving electromagnetic coil 207 to lead to forward current,
So that raised plate 206 and magnetic plate 205 attract each other so that release spring 203 is compressed, when reversed to electromagnetic coil 207
When electric current, raised plate 206 and magnetic plate 205 coordinate the bullet of release spring 203 because the effect to repel each other in the same direction mutually pushes away
Property effect so that separating table 2 quickly pop up, change the size of electric current, you can change electromagnetic coil 207 generate magnetic intensity, from
And change repulsion size, you can adjust rate of release.
Preferably, the positioning plate 405 is formed by connecting by two blocks of hang plates 406, and passes through adjusting between hang plate 406
Leading screw 407 links together and adjustment length, according to the difference of primary surface texture so that positioning plate 405 and primary link are more
Step up close, 1 inner wall surface of the zone center is provided with several tripods 101, passes through gold between the adjacent tripod 101
Belong to bar 102 to link together, pressure-bearing is carried out using tripod 101, reduces the pressure that zone center 1 itself is born.
1 top of the zone center and bottom end are respectively connected with butt joint ring 103, and 103 side of the butt joint ring is provided with through-hole
104, it is convenient for assembling, while through-hole reduces weight, reduces resistance.
Wall circular links together in the support column 401 and placed cavity 4, and between the adjacent support column 401
Apart from equal, the guarantee each position uniform force of satellite primary, guarantee balance.
The raised plate 206 and 205 surface of magnetic plate use the structure being mutually clamped, and the raised plate 206 and magnetism
It is hollow-core construction inside disk 205, mitigates weight.
The release spring 203 is made of multiple cylindrical springs 208, and 208 both ends of the cylindrical spring pass through fixed disk
209 link together, and the electric telescopic rod 6 is controlled by telescope motor 8, and the telescope motor 8 is mounted on center
1 side of platform.
In conclusion the main characteristic of the invention lies in that：
(1) primary is fixed using support column and positioning plate by the way that placed cavity is arranged, ensure that entirety is steady by the present invention
While qualitative, facilitate and discharge the shell of primary, mitigates weight, ensure the normal operation of satellite；
(2) present invention adjusts the angle of separation track using electric telescopic rod by the way that electric telescopic rod is arranged so that separation
Platform can be popped up along the direction of separation track, you can releasing for different requirements is completed in release angle and the direction for adjusting separating table
It puts；
(3) magnetic plate and raised plate are fixed together by the present invention using electromagnetic coil, can not only be fixed, but also can be with
Pop-up coordinates release spring, accelerates rate of release, be conveniently adjusted rate of release.
It is obvious to a person skilled in the art that invention is not limited to the details of the above exemplary embodiments, Er Qie
In the case of without departing substantially from spirit or essential attributes of the invention, the present invention can be realized in other specific forms.Therefore, no matter
From the point of view of which point, the present embodiments are to be considered as illustrative and not restrictive, and the scope of the present invention is by appended power
Profit requires rather than above description limits, it is intended that all by what is fallen within the meaning and scope of the equivalent requirements of the claims
Variation is included within the present invention.Any reference signs in the claims should not be construed as limiting the involved claims.
Claims (8)
1. one kind being used for the in-orbit separation release device of satellite, it is characterised in that：Including zone center (1), separating table (2) and separation rail
Road (3), the zone center (1) are internally provided with placed cavity (4), and placed cavity (4) inner wall is connected with several support columns
(401), the support column (401) includes fixed section (402) and spiral section (403), and described spiral section (403) one end passes through electronic
Screw rod (404) is connected with fixed section (402) spiral carries out length adjustment, and the fixed section (402) and placed cavity (4) are connected to one
It rises, spiral section (403) other end is connected with positioning plate (405), and the separation track (3) is uniformly connected to zone center respectively
(1) exterior lateral sides, described separating table (2) one end are connected with pressure-bearing frame (201), and separating table (2) bottom surface is provided with sliding slot
(202), the sliding slot (202) and separation track (3) mutually coincide, and the separation track (3) and zone center (1) pass through hinge
(5) it is connected together through a hinge, separation track (3) bottom end is connected with several electric telescopic rods (6), the electric telescopic rod
(6) both ends are connected together through a hinge by hinged seat (7) and separation track (3), zone center (1), and described separating table (2) one end connects
It is connected to release spring (203), release spring (203) bottom end is cased with positioning tube (204), at positioning tube (204) port
It is connected with magnetic plate (205), zone center (1) sidewall surfaces are provided with several raised plates (206), the raised plate
(206) it is internally provided with electromagnetic coil (207), the position of all raised plates (206) and the position of magnetic plate (205) are mutual
Corresponding, raised plate (206) is attracted each other by electromagnetic coil (207) and magnetic plate (205).
2. according to claim 1 a kind of for the in-orbit separation release device of satellite, it is characterised in that：The zone center
(1) inner wall surface is provided with several tripods (101), is connected by metallic rod (102) between the adjacent tripod (101)
It is connected together.
3. according to claim 1 a kind of for the in-orbit separation release device of satellite, it is characterised in that：The positioning plate
(405) it is formed by connecting by two pieces of hang plates (406), and is linked together simultaneously by adjusting screw (407) between hang plate (406)
Adjustment length.
4. according to claim 1 a kind of for the in-orbit separation release device of satellite, it is characterised in that：The zone center
(1) top and bottom end are respectively connected with butt joint ring (103), and butt joint ring (103) side is provided with through-hole (104).
5. according to claim 1 a kind of for the in-orbit separation release device of satellite, it is characterised in that：The support column
(401) it links together with placed cavity (4) interior wall circular, and the distance between adjacent described support column (401) is equal.
6. according to claim 1 a kind of for the in-orbit separation release device of satellite, it is characterised in that：The raised plate
(206) and magnetic plate (205) surface is using the structure being mutually clamped, and the raised plate (206) and magnetic plate (205) are internal
For hollow-core construction.
7. according to claim 1 a kind of for the in-orbit separation release device of satellite, it is characterised in that：The release spring
(203) it is made of multiple cylindrical springs (208), cylindrical spring (208) both ends are connected to one by fixed disk (209)
It rises.
8. according to claim 1 a kind of for the in-orbit separation release device of satellite, it is characterised in that：The electric expansion
Bar (6) is controlled by telescope motor (8), and the telescope motor (8) is mounted on zone center (1) side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810136652.6A CN108438258A (en) | 2018-02-09 | 2018-02-09 | One kind being used for the in-orbit separation release device of satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810136652.6A CN108438258A (en) | 2018-02-09 | 2018-02-09 | One kind being used for the in-orbit separation release device of satellite |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108438258A true CN108438258A (en) | 2018-08-24 |
Family
ID=63192252
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810136652.6A Withdrawn CN108438258A (en) | 2018-02-09 | 2018-02-09 | One kind being used for the in-orbit separation release device of satellite |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108438258A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109625339A (en) * | 2018-12-29 | 2019-04-16 | 西北工业大学 | A kind of micro-nano satellite separator of controllable rotating angular speed |
| CN113443176A (en) * | 2021-07-02 | 2021-09-28 | 哈尔滨工业大学 | Electromagnetic actuator for nano satellite deployer |
| CN113998156A (en) * | 2021-12-15 | 2022-02-01 | 北华航天工业学院 | Pneumatic satellite-rocket separation system |
| CN115837991A (en) * | 2023-01-10 | 2023-03-24 | 中国科学院微小卫星创新研究院 | Satellite storage and release mechanism and method |
-
2018
- 2018-02-09 CN CN201810136652.6A patent/CN108438258A/en not_active Withdrawn
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109625339A (en) * | 2018-12-29 | 2019-04-16 | 西北工业大学 | A kind of micro-nano satellite separator of controllable rotating angular speed |
| CN109625339B (en) * | 2018-12-29 | 2022-04-15 | 西北工业大学 | Micro-nano satellite separation device capable of controlling rotation angular velocity |
| CN113443176A (en) * | 2021-07-02 | 2021-09-28 | 哈尔滨工业大学 | Electromagnetic actuator for nano satellite deployer |
| CN113998156A (en) * | 2021-12-15 | 2022-02-01 | 北华航天工业学院 | Pneumatic satellite-rocket separation system |
| CN113998156B (en) * | 2021-12-15 | 2023-11-14 | 北华航天工业学院 | Pneumatic type satellite and rocket separation system |
| CN115837991A (en) * | 2023-01-10 | 2023-03-24 | 中国科学院微小卫星创新研究院 | Satellite storage and release mechanism and method |
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| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20180824 |
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| WW01 | Invention patent application withdrawn after publication |