CN106428645A - Satellite and rocket separation system - Google Patents
Satellite and rocket separation system Download PDFInfo
- Publication number
- CN106428645A CN106428645A CN201610754292.7A CN201610754292A CN106428645A CN 106428645 A CN106428645 A CN 106428645A CN 201610754292 A CN201610754292 A CN 201610754292A CN 106428645 A CN106428645 A CN 106428645A
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- CN
- China
- Prior art keywords
- flexible rack
- stepper motor
- satellite
- sleeve
- guide rail
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- 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.)
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Classifications
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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)
- Transmission Devices (AREA)
Abstract
A satellite and rocket separation system comprises a satellite pulling-off device, a sleeve, a first stepper motor, a second stepper motor, a first flexible rack and a second flexible rack. A rigid adapter is arranged on the satellite pulling-off device, the axis of the sleeve is arranged in the pulling-off direction of the satellite, one end of the sleeve directly faces the rigid adapter, the first stepper motor and the second stepper motor are the same in specifications and are symmetrically arranged relative to the axis of the sleeve, the first flexible rack and the second flexible rack are the same in specifications, the head ends of the first flexible rack and the second flexible rack are meshed and fixedly connected with the rigid adapter by penetrating the sleeve, the sleeve is used for ensuring that the first flexible rack and the second flexible rack are meshed, the stiffness for supporting the pulling off of a satellite is realized after the head ends of the first flexible rack and the second flexible rack are meshed, the middle section of the first flexible rack is tooth-meshed with the output shaft of the first stepper motor, and the middle section of the second flexible rack is tooth-meshed with the output shaft of the second stepper motor. The size and speed of separation force can effectively adjusted and controlled, the separation control accuracy and stability are greatly enhanced, repeated usage can be realized, and the utilization rate of resources is improved.
Description
Technical field
The present invention relates to space flight and aviation technical field is and in particular to a kind of satellite and the rocket piece-rate system.
Background technology
Development with space technology and all kinds of satellite large-scale application, several satellite in a rocket transmitting and the deployment of many star orbitals road, be
Improve one of effective way of launch vehicle performance and task adaptability.For realizing the reliable separation after the satellite and the rocket are entered the orbit, the satellite and the rocket
Piece-rate system design plays an important role.Traditional satellite and the rocket piece-rate system mostly is particular task and develops, versatility and flexibility
Poor, reuse and have difficulties it is impossible to meet the demands such as all kinds of satellite variation track deployment, low cost transmitting.
Content of the invention
Present invention aim at lifting satellite and the rocket separating property index, a kind of structure of proposition is simple, the satellite and the rocket of multiplexing functions divide
From system, realize separating force and separating rate in satellite and the rocket separation process adjustable controlled, separator repeatedly use with
And the versatility of satellite and the rocket piece-rate system.
The invention provides a kind of satellite and the rocket piece-rate system, including：Satellite stripper, satellite stripper is provided with rigidity
Adaptor；Sleeve, its axis pushes away direction setting along satellite, and sleeve one is rectified to rigid adaptor；First stepper motor, second
Stepper motor, is symmetrical arranged with regard to sleeve axis；First flexible rack, the second flexible rack, the head of first, second flexible rack
End is engaged and is passed through sleeve and be fixedly connected with rigid adaptor, and sleeve is used for ensureing first, second flexible rack engagement, the
First, after the head end engagement of the second flexible rack, there is the rigidity supporting that satellite pushes away；The stage casing of the first flexible rack and the first step
The output shaft tooth engagement of stepper motor, the stage casing of the second flexible rack is engaged with the output shaft tooth of the second stepper motor.
Further, including the first stop part, the second stop part, first, second stop part symmetrically sets with regard to sleeve axis
Put, the first stepper motor is located between the first stop part and sleeve, the second stepper motor is located between the second stop part and sleeve；
The tail end of the first flexible rack is provided with the first limiting section with the first stop part cooperation, and the tail end of the second flexible rack is provided with and the
Second limiting section of two stop part cooperations.
Further, the first limiting section and the second limiting section are hook formation.
Further, it is provided with the first guide rail between sleeve and the first stepper motor, the first guide rail is used for limiting the first flexibility
The motion path of tooth bar；It is provided with the second guide rail, the second guide rail is used for limiting the second flexible tooth between sleeve and the second stepper motor
The motion path of bar.
Further, the distance between the first stop part and the first guide rail are less than the first flexible rack and the first limiting section exists
Overall size on this range direction；The distance between second stop part and second guide rail are spacing with second less than the second flexible rack
Overall size on this range direction for the portion.
Further, the motion path between the first stepper motor and sleeve is whole to the first flexible rack for the first guide rail
Spacing；The motion path whole process between the second stepper motor and sleeve is spacing to the second flexible rack for second guide rail.
Further, sleeve is to be converged by the first guide rail and the second guide rail to be formed.
Beneficial effects of the present invention：The present invention is directed to traditional rocket satellite and the rocket piece-rate system and mostly is particular task and develops, and leads to
With the problem that property and flexibility are poor, from stepper motor as separating power, can effectively adjust control separating force size and speed
Degree, greatly improves and separates control accuracy and stability, and can be repeated several times use, improve resource utilization；From flexibility
Tooth bar, as thrust transferring element, effectively save space, is suitable for various radome fairing envelopes；Two flexible racks are after engagement
There is the rigidity supporting that satellite pushes away, the direction guiding in conjunction with sleeve is it is ensured that turn the rotary motion of stepper motor output shaft
It is changed to validity and the accuracy of the linear motion of satellite stripper.
Brief description
Fig. 1 is the total arrangement schematic diagram of first embodiment of the invention；
Fig. 2 pushes away the schematic diagram of satellite for first embodiment of the invention；
Fig. 3 is second embodiment of the invention the first guide rail schematic diagram.
In all of the figs, identical reference is used for representing identical element or structure, wherein：
1- satellite stripper, 2- first guide rail, 3- first stepper motor, 4- first flexible rack, 5- first stop part,
6- first limiting section, 7- second limiting section, 8- second stop part, 9- second flexible rack, 10- second stepper motor, 11- second
Rail in guide rail, 12- sleeve, 13- rigidity adaptor, 21- first outer rail, 22- first.
Specific embodiment
In order that the objects, technical solutions and advantages of the present invention become more apparent, below in conjunction with drawings and Examples, right
The present invention is further elaborated.It should be appreciated that specific embodiment described herein is only in order to explain the present invention, and
It is not used in the restriction present invention.
Refer to Fig. 1,2, be first embodiment of the invention.The satellite and the rocket piece-rate system of first embodiment includes satellite and pushes away dress
Put the 1, first guide rail 2, the first stepper motor 3, the first flexible rack 4, the first stop part 5, the first limiting section 6, the second limiting section
7th, the second stop part 8, the second flexible rack 9, the second stepper motor 10, the second guide rail 11, sleeve 12, rigid adaptor 13 etc..
Satellite stripper 1 is provided with rigid adaptor 13, and in the present embodiment, rigid adaptor 13 is located at satellite and pushes away
Device 1 center；The axis of sleeve 12 pushes away direction setting along satellite, and sleeve 12 1 is rectified to rigid adaptor 13；First stepping
Motor 3, the second stepper motor 10 specification are identical, with regard to the setting of sleeve 12 axisymmetrical；First flexible rack 4, the second flexible tooth
Bar 9 specification is identical, and the head end of first, second flexible rack 9 is engaged and passes through sleeve 12 and be fixedly connected with rigid adaptor 13,
Sleeve 12 is used for ensureing first, second flexible rack 4,9 engagement, has and prop up after the head end engagement of first, second flexible rack 4,9
Hold the rigidity that satellite pushes away；The stage casing of the first flexible rack 4 is engaged with the output shaft tooth of the first stepper motor 3, the second flexible tooth
The stage casing of bar 9 is engaged with the output shaft tooth of the second stepper motor 10.
First, second stop part 5,8 is arranged with regard to sleeve 12 axisymmetrical, and the first stepper motor 3 is located at the first stop part 5
And sleeve 12 between, the second stepper motor 10 is located between the second stop part 8 and sleeve 12；The tail end of the first flexible rack 4 sets
There is the first limiting section 6 with the first stop part 5 cooperation, the tail end of the second flexible rack 9 is provided with the with the second stop part 8 cooperation
Two limiting sections 7, in the present embodiment, the first limiting section 6 and the second limiting section 7 are hook formation.First stop part 5 and first
The distance between guide rail 2 is less than the first flexible rack 4 and the first limiting section 6 overall size on this range direction；Second backstop
The distance between part 8 and the second guide rail 11 are less than the second flexible rack 9 and the second limiting section 7 total chi on this range direction
Very little.Above-mentioned size setting can avoid limiting section to deviate between stop part and guide rail, when repeating to push away satellite, can be more preferable
Ensure the stable of transmission with effectively.Even if certainly not possessing stop part and limiting section, as long as tooth bar is engaged with stepper motor, that is,
Can ensure that tooth bar normally moves back and forth with the rotating of stepper motor.In the case of non-overload, the rotating speed of stepper motor, stopping
Position be solely dependent upon frequency and the umber of pulse of pulse signal, and do not affected by loading to change, therefore be can ensure that the satellite and the rocket divide
From precision and stability, the many stars of unequally loaded launch application and recycling on, advantage becomes apparent from.
It is provided with the first guide rail 2, the first guide rail 2 is used for limiting the first flexible rack 4 between sleeve 12 and the first stepper motor 3
Motion path；It is provided with the second guide rail 11, the second guide rail 11 is soft for limiting second between sleeve 12 and the second stepper motor 10
The motion path of property tooth bar 9.In the present embodiment, the first guide rail 2 to the first flexible rack 4 in the first stepper motor 3 and sleeve
Motion path whole process between 12 is spacing；Second guide rail 11 to the second flexible rack 9 the second stepper motor 10 and sleeve 12 it
Between motion path whole process spacing.
The material of the strip part of flexible rack can be vulcanie, steel disc, or can also adopt chain structure, both
There is flexibility, be easy to the conversion of transmission direction, it may have enough intensity is it is ensured that the efficiency of driving force.Using vulcanie or
During steel disc, because both materials itself have enough elasticity, even if there is no guide supporting, also be enough to complete stepper motor and
The transmission of motion between satellite stripper 1, has the support of guide rail more preferable with guiding auxiliaring effect.And the structure of chain-type then exists
Whole process between first stepper motor 3 and sleeve 12 needs support and the guiding of guide rail.
Sleeve 12 in the present embodiment is and guide rail split setting to be easy to be changed or adjusting sleeve according to different mission needs
Cylinder 12.
The present invention is applied to single star and separates or many stars networking separation scheme, to introduce this with reference to two application examples
Bright operation principle and process.
【Application example one】Single star separation scheme
Satellite and the rocket attachment means are connected with satellite stripper 1, after rocket enters the track of predetermined release satellite, the satellite and the rocket
Attachment means unlock, and the first stepper motor 3 and the second stepper motor 10 start simultaneously, now with reference to Fig. 2, the first stepper motor 3
Driving the first flexible rack 4 that turns clockwise moves, and the synchronous rotate counterclockwise of the second stepper motor 10 drives the second flexible rack 9
Motion, according to pre-set constant power, under the restriction of sleeve 12, the first flexible rack 4 and the second flexible rack 9 promote satellite jointly
Stripper 1 moves (direction as shown is not necessarily actual direction) upwards, provides for satellite and separates initial velocity, away from rocket end
Level, realizes the satellite and the rocket and separates.
【Application example two】Multi satellite separation scheme
Taking double star series arrangement as a example, satellite and the rocket attachment means two satellites of independent connection.During first satellite unblock, second
Satellite is still within lock-out state.After first satellite separation release finishes, rocket continues to second with second satellite
The predetermined launching trajectory of satellite advances, and during this period, the first stepper motor 3 and the second stepper motor 10 invert simultaneously, drives
First flexible rack 4 and the second flexible rack 9 reset, and pull satellite stripper 1 counter motion playback (as Fig. 1).Enter the
After the predetermined launching trajectory of two satellites, second satellite unlocks, and the first stepper motor 3 and the second stepper motor 10 rotate forward again
Start, the first stepper motor 3 turns clockwise and drives the first flexible rack 4 to move, the second stepper motor 10 is synchronous to be revolved counterclockwise
Turn and drive the second flexible rack 9 to move, according to pre-set constant power, under the restriction of sleeve 12, the first flexible rack 4 and second is soft
Property tooth bar 9 promotes satellite stripper 1 to move (direction as shown is not necessarily actual direction) upwards jointly, is that second satellite carries
For separating initial velocity, away from final vehicle, realize the satellite and the rocket and separate, finally realize double star transmitting.Many star transmittings are with this in the same manner.
Refer to Fig. 3, be the schematic diagram of second embodiment of the invention first guide rail, the second guide rail and the first guide rail structure pair
Claim therefore omit.Second embodiment and the form of the composition differring primarily in that guide rail and stop part of first embodiment.In this enforcement
In example, the first guide rail 2 includes rail 22 in the first outer rail 21 and first, and the first stop part 5 is to bypass the first stepper motor 3 by outer rail
Output shaft after back extend formed, the first flexible rack 4 is between the output shaft of the first outer rail 21 and the first stepper motor 3
Engage with the output shaft tooth of the first stepper motor 3；Second guide rail 11 includes rail in the second outer rail (not shown) and second (does not scheme
Show), the second stop part 8 is back to extend after the output shaft being bypassed the second stepper motor 10 by the second outer rail to be formed, and second is soft
Property tooth bar 9 is engaged with the output shaft tooth of the second stepper motor 10 between the output shaft of the second outer rail and the second stepper motor 10.
It is arranged such and can ensure that tooth bar is more reliable and more stable with the cooperation of the output shaft tooth of stepper motor.
In the present embodiment, in the first stop part 5 and first, the distance between rail 22 is less than the first flexible rack 4 and first
Overall size on this range direction for the limiting section 6；In second stop part 8 and second, the distance between rail is less than the second flexible rack
9 and second overall size on this range direction for the limiting section 7.It is arranged such and can avoid limiting section between stop part and interior rail
Abjection, when repeating to push away satellite, can preferably ensure that be driven stablizes and effective.
In other embodiments (not shown), sleeve 12 can also be to be converged by the first guide rail 2 and the second guide rail 11 to be formed,
I.e. sleeve 12 and guide rail are integrally formed, and with reference to the arrangement form of second embodiment middle guide, sleeve 12 can also be by outside first
The head end of rail and the second outer rail cooperatively forms.It is arranged such and be conducive to integration processing.
The present invention is not only limited to above-mentioned specific embodiment, and persons skilled in the art are according to disclosed by the invention interior
Hold, the present invention can be implemented using other multiple specific embodiments, therefore, the design structure of every employing present invention and think of
Road, does some simple designs changing or changing, both falls within the scope of protection of the invention.
Claims (9)
1. a kind of satellite and the rocket piece-rate system is it is characterised in that include：
Satellite stripper, satellite stripper is provided with rigid adaptor；
Sleeve, its axis pushes away direction setting along satellite, and sleeve one is rectified to rigid adaptor；
First stepper motor, the second stepper motor, are symmetrical arranged with regard to sleeve axis；
First flexible rack, the second flexible rack, the head end of first, second flexible rack is engaged and passes through sleeve and turned with rigidity
Fitting is fixedly connected, and sleeve is used for ensureing first, second flexible rack engagement, after the head end engagement of first, second flexible rack
There is the rigidity supporting that satellite pushes away；The stage casing of the first flexible rack is engaged with the output shaft tooth of the first stepper motor, and second is soft
The property stage casing of tooth bar is engaged with the output shaft tooth of the second stepper motor.
2. a kind of satellite and the rocket piece-rate system according to claim 1 is it is characterised in that include the first stop part, the second backstop
Part, first, second stop part is symmetrical arranged with regard to sleeve axis, and the first stepper motor is located between the first stop part and sleeve,
Second stepper motor is located between the second stop part and sleeve；The tail end of the first flexible rack is provided with and the first stop part cooperation
First limiting section, the tail end of the second flexible rack is provided with the second limiting section with the second stop part cooperation.
3. a kind of satellite and the rocket piece-rate system according to claim 2 is it is characterised in that the first limiting section and the second limiting section are equal
For hook formation.
4. a kind of satellite and the rocket piece-rate system according to claim 1 and 2 it is characterised in that sleeve and the first stepper motor it
Between be provided with the first guide rail, the first guide rail is used for limiting the motion path of the first flexible rack；Between sleeve and the second stepper motor
It is provided with the second guide rail, the second guide rail is used for limiting the motion path of the second flexible rack.
5. a kind of satellite and the rocket piece-rate system according to claim 4 is it is characterised in that between the first stop part and the first guide rail
Distance be less than the first flexible rack and the first limiting section overall size on this range direction；Second stop part and the second guide rail
The distance between be less than the second flexible rack and the second limiting section overall size on this range direction.
6. a kind of satellite and the rocket piece-rate system according to claim 4 is it is characterised in that the first guide rail exists to the first flexible rack
Motion path whole process between first stepper motor and sleeve is spacing；Second guide rail is to the second flexible rack in the second stepper motor
Motion path whole process and sleeve between is spacing.
7. as claimed in claim 4 a kind of satellite and the rocket piece-rate system it is characterised in that sleeve is by the first guide rail and the second guide rail
Converge and formed.
8. as claimed in claim 4 a kind of satellite and the rocket piece-rate system it is characterised in that the first guide rail includes the first outer rail and first
Interior rail, the first stop part is back to extend after the output shaft being bypassed the first stepper motor by outer rail to be formed, the first flexible rack
Engage with the output shaft tooth of the first stepper motor between the output shaft of the first outer rail and the first stepper motor；Second guide rail includes
Rail in second outer rail and second, the second stop part is back to extend after the output shaft being bypassed the second stepper motor by the second outer rail
Formed, the second flexible rack output shaft tooth with the second stepper motor between the output shaft of the second outer rail and the second stepper motor
Engagement.
9. a kind of satellite and the rocket piece-rate system according to claim 8 is it is characterised in that in the first stop part and first between rail
Distance be less than the first flexible rack and the first limiting section overall size on this range direction；Rail in second stop part and second
The distance between be less than the second flexible rack and the second limiting section overall size on this range direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610754292.7A CN106428645B (en) | 2016-08-29 | 2016-08-29 | A kind of satellite and the rocket separation system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610754292.7A CN106428645B (en) | 2016-08-29 | 2016-08-29 | A kind of satellite and the rocket separation system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106428645A true CN106428645A (en) | 2017-02-22 |
| CN106428645B CN106428645B (en) | 2019-03-22 |
Family
ID=58090044
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610754292.7A Active CN106428645B (en) | 2016-08-29 | 2016-08-29 | A kind of satellite and the rocket separation system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106428645B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5173248A (en) * | 1990-02-14 | 1992-12-22 | Kabushiki Kaisha Toshiba | Remote control apparatus for maintaining in-vessel components in a structure having an inner torus space |
| JPH08164900A (en) * | 1994-12-13 | 1996-06-25 | Mitsubishi Heavy Ind Ltd | Artificial satellite separating part structural body |
| JP2003081198A (en) * | 2001-09-12 | 2003-03-19 | Mitsubishi Heavy Ind Ltd | Clamping band constraining device |
| CN101691139A (en) * | 2009-10-19 | 2010-04-07 | 航天东方红卫星有限公司 | Separation mechanism of on-board equipment |
| CN201842261U (en) * | 2010-09-17 | 2011-05-25 | 湖北航天技术研究院总体设计所 | Pneumatic executive device used for separating two objects |
| CN102803071A (en) * | 2010-02-19 | 2012-11-28 | 三菱重工业株式会社 | Connecting and separating device, connecting and separating system, and connecting and separating method |
| CN103022774A (en) * | 2012-12-28 | 2013-04-03 | 中国人民解放军国防科学技术大学 | Satellite-rocket separation connector |
| CN105173123A (en) * | 2015-08-14 | 2015-12-23 | 西北工业大学 | Electromagnetic self-locking plane connection device |
-
2016
- 2016-08-29 CN CN201610754292.7A patent/CN106428645B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5173248A (en) * | 1990-02-14 | 1992-12-22 | Kabushiki Kaisha Toshiba | Remote control apparatus for maintaining in-vessel components in a structure having an inner torus space |
| JPH08164900A (en) * | 1994-12-13 | 1996-06-25 | Mitsubishi Heavy Ind Ltd | Artificial satellite separating part structural body |
| JP2003081198A (en) * | 2001-09-12 | 2003-03-19 | Mitsubishi Heavy Ind Ltd | Clamping band constraining device |
| CN101691139A (en) * | 2009-10-19 | 2010-04-07 | 航天东方红卫星有限公司 | Separation mechanism of on-board equipment |
| CN102803071A (en) * | 2010-02-19 | 2012-11-28 | 三菱重工业株式会社 | Connecting and separating device, connecting and separating system, and connecting and separating method |
| CN201842261U (en) * | 2010-09-17 | 2011-05-25 | 湖北航天技术研究院总体设计所 | Pneumatic executive device used for separating two objects |
| CN103022774A (en) * | 2012-12-28 | 2013-04-03 | 中国人民解放军国防科学技术大学 | Satellite-rocket separation connector |
| CN105173123A (en) * | 2015-08-14 | 2015-12-23 | 西北工业大学 | Electromagnetic self-locking plane connection device |
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| Publication number | Publication date |
|---|---|
| CN106428645B (en) | 2019-03-22 |
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