CN104691789A - Front-end-expanded inflatable docking mechanism - Google Patents
Front-end-expanded inflatable docking mechanism Download PDFInfo
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- CN104691789A CN104691789A CN201510139308.9A CN201510139308A CN104691789A CN 104691789 A CN104691789 A CN 104691789A CN 201510139308 A CN201510139308 A CN 201510139308A CN 104691789 A CN104691789 A CN 104691789A
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Abstract
The invention discloses a front-end-expanded inflatable docking mechanism and belongs to the technical field of spaceflight. The front-end-expanded inflatable docking mechanism comprises a support pipe and an expanded end, wherein the expanded end is arranged at the front end of the support pipe, aligned with the center of the support pipe in arrangement and fixedly connected with the support pipe, both the support pipe and the expanded end are of flexible inflatable structures, the outer diameter of the support pipe is smaller than the length of the largest liner distance of a section, parallel to the cross section of the support pipe, of the expanded end, and a longitudinal coil spring is arranged on one side of the support pipe. The front-end-expanded inflatable docking mechanism is used for on-orbit docking of space targets like satellites and solves the problems that an existing mechanical docking mechanism is complex in structure, large in launching size, high in control requirement and control difficulty, prone to damaging a docked object and the like..
Description
Technical field
The invention belongs to space technology field, be specifically related to a kind of front end expand formula inflation docking mechanism.
Background technology
Comprise in space tasks and the extraterrestrial targets such as satellite are docked in-orbit, with the catching of implementation space target, posture adjustment, the operation such as change rail and transfer, existing docking mechanism adopts mechanical type docking mechanism, there is complex structure, launch the shortcomings such as size is large, control overflow is high, control difficulty is large, easy damaged docking target, therefore, need a kind of novel, be easy to the Space Docking Mechanism that manipulates, to reduce docking difficulty and the cost of extraterrestrial target.
Summary of the invention
The object of the invention is to adopt mechanical type docking mechanism to solve existing docking mechanism, there is complex structure, launch the problem of the shortcomings such as size is large, control overflow is high, control difficulty is large, easy damaged docking target, provide a kind of front end expand formula inflation docking mechanism, its technical scheme is as follows:
Formula inflation docking mechanism is expanded in a kind of front end, it comprises support tube and expansion termination, expansion termination is arranged on the front end of support tube, align with support tube center and arrange in expansion termination, expansion termination is fixedly connected with support tube, support tube and expansion termination are all flexible gas-filled structures, expansion termination is spherical, cylindricality, the arbitrary shape such as square, the external diameter of support tube is less than the length of the longest straight line distance on the cross section parallel with the cross-sectional plane of support tube, expansion termination, such as expansion termination is spherical, and the external diameter of support tube is less than the diameter of expansion termination; Such as expansion termination is cylindricality, and expansion termination is identical with the axial direction of support tube when arranging, and the external diameter of support tube is less than the external diameter of expansion termination, and expansion termination is vertical with the axial direction of support tube when arranging, and the external diameter of support tube is less than the length of expansion termination; Such as expansion termination is foursquare, and the external diameter of support tube is less than the surperficial catercorner length of of expansion termination, etc.; The side of support tube is provided with longitudinal wind spring, can folds with wind spring automatic curled after support tube and the venting of expansion termination; Support tube and expansion termination are respectively arranged with tracheae, and the tracheae on support tube is arranged on the rear end of support tube, and the tracheae of expansion termination is arranged on support tube inside; Support tube and expansion termination all adopt flexible composite, and expansion termination comprises air-retaining liner, bearing layer and elastic layer, and support tube comprises air-retaining liner and bearing layer, and air-retaining liner material is the stability of butyl rubber membraneous material, holding structure inflation pressure; Bearing layer is aramid fiber reinforced composite, bears the inflation pressure in structure; Elastic layer material is rubber film material, be used for shrink venting after expansion termination.
Beneficial effect of the present invention is: front end expand formula inflation docking mechanism have structure simple, be easy to docking, docking operation control overflow is low, mode simple, launch that volume is little, lightweight, low cost and other advantages, and expansion termination, front end is flexible gas-filled utricule structure, different docking port Inner structural shapes and size can be adapted to, target strong adaptability, and damage can not be caused to docking target; Docking port can be widely used in there is the docking that opening size is less than the objective body of interior space dimension.
accompanying drawing illustrates:
Fig. 1 is structural representation of the present invention.
detailed description of the invention:
With reference to Fig. 1, formula inflation docking mechanism is expanded in a kind of front end, it comprises support tube 1 and expansion termination 2, expansion termination 2 is arranged on the front end of support tube 1, align with support tube 1 center and arrange in expansion termination 2, expansion termination 2 is fixedly connected with support tube 1, support tube 1 and expansion termination 2 are all flexible gas-filled structures, expansion termination 2 is spherical, cylindricality, square arbitrary shape such as grade, the external diameter of support tube 1 is less than the length of the longest straight line distance on the cross section parallel with the cross-sectional plane of support tube 1, expansion termination 2, such as expansion termination 2 is spherical, the external diameter of support tube 1 is less than the diameter of expansion termination 2, such as expansion termination 2 is cylindricalitys, expansion termination 2 is identical with the axial direction of support tube 1 when arranging, the external diameter of support tube 1 is less than the external diameter of expansion termination 2, and expansion termination 2 is vertical with the axial direction of support tube 1 when arranging, and the external diameter of support tube 1 is less than the length of expansion termination 2, such as expansion termination 2 is foursquare, and the external diameter of support tube 1 is less than the surperficial catercorner length of of expansion termination 2, etc., the side of support tube 1 is provided with longitudinal wind spring 3, can folds with wind spring 3 automatic curled after support tube 1 and expansion termination 2 are exitted, support tube 1 and expansion termination 2 are respectively arranged with tracheae, and the tracheae on support tube 1 is arranged on the rear end of support tube 1, and the tracheae of expansion termination 2 is arranged on support tube 1 inside, support tube 1 and expansion termination 2 all adopt flexible composite, and expansion termination 2 comprises air-retaining liner, bearing layer and elastic layer, and support tube 1 comprises air-retaining liner and bearing layer, and air-retaining liner material is the stability of butyl rubber membraneous material, holding structure inflation pressure, bearing layer is aramid fiber reinforced composite, bears the inflation pressure in structure, elastic layer material is rubber film material, be used for shrink venting after expansion termination 2.
Preferably, the external diameter of support tube 1 is less than 1/2nd of the length of the longest straight line distance on the cross section parallel with the cross-sectional plane of support tube 1, expansion termination 2.
The diameter of the docking port on objective body and support tube 1 corresponding position, slightly larger than the diameter of support tube 1, makes support tube 1 easily insert in docking port.
Principle of work: before inflation, expansion termination 2 is shunk under the effect of elastic layer, and support tube 1 is folded in the effect last volume complications of wind spring 3, and overall volume reduces, convenient delivery; First to support tube 1 inflation, support tube 1 is launched during docking, again support tube 1 front end is inserted in the docking port of objective body, then expansion termination 2 is inflated, under inflation pressure effect, expansion termination 2 and support tube 1 all have certain rigidity and hardness, objective body firmly can be connected, after connection, the operations such as change rail, Powered Propulsion can be carried out to objective body; When being separated with objective body, first exit to expansion termination 2, expansion termination 2 is entered to shrink in the effect of elastic layer, is then shifted out in docking port by support tube 1, finally exits to support tube 1, and support tube 1 is folded in the effect last volume complications of wind spring 3 after exitting.
Claims (4)
1. formula inflation docking mechanism is expanded in a front end, it is characterized in that it comprises support tube (1) and expansion termination (2), expansion termination (2) is arranged on the front end of support tube (1), align with support tube (1) center and arrange in expansion termination (2), expansion termination (2) is fixedly connected with support tube (1), support tube (1) and expansion termination (2) are all flexible gas-filled structures, the external diameter of support tube (1) is less than the length of the longest straight line distance on the cross section parallel with the cross-sectional plane of support tube (1), expansion termination (2), the side of support tube (1) is provided with longitudinal wind spring (3).
2. as claimed in claim a kind of front end expand formula inflation docking mechanism, it is characterized in that being respectively arranged with tracheae on support tube (1) and expansion termination (2), tracheae on support tube (1) is arranged on the rear end of support tube (1), and the tracheae of expansion termination (2) is arranged on support tube (1) inside.
3. as claimed in claim a kind of front end expand formula inflation docking mechanism, it is characterized in that support tube (1) and expansion termination (2) all adopt flexible composite, expansion termination (2) comprises air-retaining liner, bearing layer and elastic layer, support tube (1) comprises air-retaining liner and bearing layer, and air-retaining liner material is butyl rubber membraneous material; Bearing layer is aramid fiber reinforced composite; Elastic layer material is rubber film material.
4. as claimed in claim a kind of front end expand formula inflation docking mechanism, it is characterized in that the external diameter of support tube (1) is less than 1/2nd of the length of the longest straight line distance on the cross section parallel with the cross-sectional plane of support tube (1), expansion termination (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510139308.9A CN104691789B (en) | 2015-03-28 | 2015-03-28 | Formula inflation docking mechanism is expanded in a kind of front end |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510139308.9A CN104691789B (en) | 2015-03-28 | 2015-03-28 | Formula inflation docking mechanism is expanded in a kind of front end |
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| CN104691789A true CN104691789A (en) | 2015-06-10 |
| CN104691789B CN104691789B (en) | 2016-08-24 |
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| CN201510139308.9A Active CN104691789B (en) | 2015-03-28 | 2015-03-28 | Formula inflation docking mechanism is expanded in a kind of front end |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105270651A (en) * | 2015-11-20 | 2016-01-27 | 成都尔珏科技有限公司 | Internal shrink gradual change inflatable docking apparatus for space |
| CN105292524A (en) * | 2015-11-20 | 2016-02-03 | 成都尔珏科技有限公司 | Externally-expanding gradual-change inflatable docking unit used for outer space |
| CN108639390A (en) * | 2018-05-02 | 2018-10-12 | 中国人民解放军国防科技大学 | Pneumatic control type auxiliary butt joint device and pneumatic control type auxiliary butt joint method of satellite |
| CN109131952A (en) * | 2018-09-07 | 2019-01-04 | 哈尔滨工业大学 | Spacecraft capture systems based on jet pipe capture and the locking of satellite-rocket docking ring |
| CN109178358A (en) * | 2018-09-07 | 2019-01-11 | 哈尔滨工业大学 | A kind of spacecraft flexibility capture systems based on jet pipe |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4860975A (en) * | 1988-12-30 | 1989-08-29 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Smart tunnel - docking mechanism |
| CN2534388Y (en) * | 2002-03-27 | 2003-02-05 | 万金玉 | Fixing clip for inflator head |
| CN101323067A (en) * | 2008-07-22 | 2008-12-17 | 广州广船国际股份有限公司 | Pipe fitting butt welding protecting method and apparatus |
| US7669804B2 (en) * | 2005-06-09 | 2010-03-02 | Odyssey Space Research, LLC | Spacecraft interface module for enabling versatile space platform logistics support |
| CN102294690A (en) * | 2011-05-12 | 2011-12-28 | 哈尔滨工业大学 | Large-tolerance docking acquisition device focused on space large mechanical arm and rendezvous and docking |
| CN103086079A (en) * | 2011-10-27 | 2013-05-08 | 廖耀鑫 | Buffer air bag with automatic clamping pressure adjusting function |
-
2015
- 2015-03-28 CN CN201510139308.9A patent/CN104691789B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4860975A (en) * | 1988-12-30 | 1989-08-29 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Smart tunnel - docking mechanism |
| CN2534388Y (en) * | 2002-03-27 | 2003-02-05 | 万金玉 | Fixing clip for inflator head |
| US7669804B2 (en) * | 2005-06-09 | 2010-03-02 | Odyssey Space Research, LLC | Spacecraft interface module for enabling versatile space platform logistics support |
| CN101323067A (en) * | 2008-07-22 | 2008-12-17 | 广州广船国际股份有限公司 | Pipe fitting butt welding protecting method and apparatus |
| CN102294690A (en) * | 2011-05-12 | 2011-12-28 | 哈尔滨工业大学 | Large-tolerance docking acquisition device focused on space large mechanical arm and rendezvous and docking |
| CN103086079A (en) * | 2011-10-27 | 2013-05-08 | 廖耀鑫 | Buffer air bag with automatic clamping pressure adjusting function |
Non-Patent Citations (1)
| Title |
|---|
| 卫剑征: "空间充气管展开动力学研究进展", 《力学进展》 * |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105270651A (en) * | 2015-11-20 | 2016-01-27 | 成都尔珏科技有限公司 | Internal shrink gradual change inflatable docking apparatus for space |
| CN105292524A (en) * | 2015-11-20 | 2016-02-03 | 成都尔珏科技有限公司 | Externally-expanding gradual-change inflatable docking unit used for outer space |
| CN105270651B (en) * | 2015-11-20 | 2017-04-19 | 成都尔珏科技有限公司 | Internal shrink gradual change inflatable docking apparatus for space |
| CN108639390A (en) * | 2018-05-02 | 2018-10-12 | 中国人民解放军国防科技大学 | Pneumatic control type auxiliary butt joint device and pneumatic control type auxiliary butt joint method of satellite |
| CN109131952A (en) * | 2018-09-07 | 2019-01-04 | 哈尔滨工业大学 | Spacecraft capture systems based on jet pipe capture and the locking of satellite-rocket docking ring |
| CN109178358A (en) * | 2018-09-07 | 2019-01-11 | 哈尔滨工业大学 | A kind of spacecraft flexibility capture systems based on jet pipe |
| CN109178358B (en) * | 2018-09-07 | 2022-03-04 | 哈尔滨工业大学 | Spacecraft flexible capturing system based on spray pipe |
| CN109131952B (en) * | 2018-09-07 | 2022-03-04 | 哈尔滨工业大学 | Spacecraft capturing system capturing method based on nozzle capturing and satellite-rocket docking ring locking |
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|---|---|
| CN104691789B (en) | 2016-08-24 |
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Effective date of registration: 20230919 Address after: 100000 302, Floor 3, No. 8, Anningzhuang East Road, Haidian District, Beijing Patentee after: Beijing Qihe Jingwei Innovation Technology Co.,Ltd. Address before: 150000 No. 92, West Da Zhi street, Nangang District, Harbin, Heilongjiang. Patentee before: HARBIN INSTITUTE OF TECHNOLOGY |