CN103121516B - Replaceable module butt joint device - Google Patents
Replaceable module butt joint device Download PDFInfo
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- CN103121516B CN103121516B CN201110368944.0A CN201110368944A CN103121516B CN 103121516 B CN103121516 B CN 103121516B CN 201110368944 A CN201110368944 A CN 201110368944A CN 103121516 B CN103121516 B CN 103121516B
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- replaceable module
- module
- cone
- butt joint
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Abstract
The invention discloses a replaceable module butt joint device which comprises a containing awl, a butt joint adapter and a general hand grip. The containing awl is connected on an air vehicle in orbit through a mechanical fastener. A guide awl structure matched with an installation guide awl is arranged at the upper end of a structure main body of the butt joint adapter, an installation flange structure matched with a replaceable module is arranged in the middle of the structure main body of the butt joint adapter, an external thread matched with an internal thread of the general hand grip is arranged at the lower middle end of the structure main body of the butt joint adapter, and a guide awl structure matched with a hand grip guide awl on the general hand grip is arranged at the lower end of the structure main body of the butt joint adapter. Due to the fact that the replaceable module butt joint device is utilized, the replaceable module can be separated from the air vehicle in orbit, the replaceable module can be reliably installed on an original module connector part of the air vehicle in orbit in a matched mode, and removing work of a waste module and installing work of a new module of the air vehicle in orbit can be achieved. The replaceable module butt joint device can meet the use requirements of removing of the waste module and installing of the new module of the air vehicle in orbit, has a certain generality and is simple in structure, reliable in movement and light in weight.
Description
Technical field
The present invention relates to space travel apparatus, the device of particularly installation the locking and unlocking separation of space replaceable module.
Background technology
At present, known aerospacecraft is generally disposable product.Space flight safeguards in-orbit with service it is to extend in orbit aerocraft service life, expansion and improve system performance, and to carry out making a reservation for or meeting an urgent need at orbit aerocraft check in-orbit, correct, maintain, the space operation of the service role such as repair and upgrade renewal.For realizing above maintenance in-orbit and service, need in limited space, design replaceable module docking facilities, can meet replaceable module and the installation lock function between orbit aerocraft; And in-orbit period, by the space manipulator end all-purpose tool matched with it, replaceable module and being separated between orbit aerocraft can be realized; And after needing the replaceable module removed to be placed into discard module berthing interface, mechanical arm tail end all-purpose tool can capture the new module with identical replaceable module docking facilities, and it is reliably assembled to the grand master pattern block interface position at orbit aerocraft; Finally, space manipulator end all-purpose tool is removed with new module and is connected.Completing above in the waste and old module removal of orbit aerocraft, new module installation process, namely needing to design a kind of replaceable module docking facilities, requiring that its structure is simple, reliable in action, quality are light, and there is certain commonality.
At present, do not find explanation or the report of technology similar to the present invention, not yet collect similar data both at home and abroad yet.
Summary of the invention
Safeguarding in-orbit with service process to solve space flight, lacking efficient apparatus, can implementation space replaceable module installation locking and is separated replacing problem, the object of the present invention is to provide a kind of replaceable module docking facilities.
In order to reach foregoing invention object, the present invention is to provide a kind of replaceable module docking facilities for the technical scheme that its technical matters of solution adopts, and this device comprises receives cone, docking adapter and general handgrip; Above-mentioned receiving cone is installed on orbit aerocraft; Above-mentioned docking adapter is installed on replaceable module; Above-mentioned general handgrip is installed on mechanical arm tail end, therefore under mechanical arm tail end drives, can do suitable, counter-clockwise rotary motion and up-and-down movement around central axis.
The lower end of above-mentioned receiving cone has installation guide cone, and centre has the dead bolt bayonet socket that can hold dead bolt.
Above-mentioned docking adapter comprises main structure body, dead bolt, stage clip and unblock push rod; The upper end of main structure body is the guiding cone structure of mating with installation guide cone, middle part is the mounting flange structure of mating with replaceable module, middle lower end is the outside thread mated with general handgrip negative thread, and lower end is the guiding cone structure of mating with the handgrip guide cone on general handgrip; Dead bolt and stage clip are installed on the middle epimere of main structure body, are symmetrically arranged; Unlock the symmetrical stage casing being installed on main structure body of push rod, and unblock push rod upper end is on dead bolt unblock inclined-plane, when unlocking the application force that push rod lower end is subject to upwards, unlocks push rod upward movement, thus about promoting, two dead bolts overcome stage clip application force, move to central axis; And when unlocking the application force removed upwards push rod lower end, stage clip promotes two dead bolts to direction motion outside central axis, until dead bolt is subject to the stop of main structure body, meanwhile, dead bolt ramp structure promotion unblock push rod moves downward.
Above-mentioned general handgrip upper end has handgrip guide cone; Interlude inside is and the negative thread docking adapter structure main body outside thread and mate; Hypomere middle part is provided with travel switch, for docking after adapter docks with general handgrip, provide both docking and to put in place signal, and follow-up dead bolt unlocking the signal that puts in place.
Utilize the present invention, by the space manipulator end all-purpose tool matched with it, not only can realize replaceable module and being separated between orbit aerocraft; And after needing the replaceable module removed to be placed into discard module berthing interface, mechanical arm tail end all-purpose tool can capture the new module with identical replaceable module docking facilities, and it is reliably assembled to the grand master pattern block interface position at orbit aerocraft; Finally, space manipulator end all-purpose tool is removed with new module and is connected, and completes and removes and new module erection work in the waste and old module of orbit aerocraft.Can meet the operating needs installed in the waste and old module removal of orbit aerocraft, new module, and its structure is simple, reliable in action, quality are light, and there is certain commonality.
Accompanying drawing explanation
Fig. 1 is the receiving cone of replaceable module docking facilities of the present invention, docking adapter and general handgrip, and at orbit aerocraft, the structural representation of replaceable module and mechanical arm tail end;
In figure: 1-receives cone, 2-to dock adapter, 3-installs guide cone at orbit aerocraft, 4-replaceable module, the general handgrip of 5-, 6-mechanical arm tail end, 7-travel switch, 8-negative thread, 9-handgrip guide cone, 10-main structure body, 11-outside thread, 12-unblock push rod, 13-stage clip, 14-dead bolt, 15-replaceable module electrical connector, 16-aircraft electrical joint, 17-dead bolt bayonet socket, 18-;
Fig. 2 is replaceable module and installs at orbit aerocraft the cutaway view locked;
Fig. 3 is the cutaway view that mechanical arm tail end catches replaceable module;
Fig. 4 is replaceable module and the cutaway view unlocked at orbit aerocraft;
Fig. 5 is the cutaway view that replaceable module is separated with at orbit aerocraft.
Detailed description of the invention
The present invention safeguards and the needs of servicing aircraft and developing according to rail, can realize: replaceable module and the installation between orbit aerocraft lock; And in-orbit period, by what match with it, be arranged on the all-purpose tool on space manipulator end, replaceable module and being separated between orbit aerocraft can be realized; And by follow-up cycling, realize carry-on old module removal and new module installation function in-orbit.
Below in conjunction with accompanying drawing, the preferred embodiments of the present invention are described.
Fig. 1 is the receiving cone of replaceable module docking facilities of the present invention, docking adapter and general handgrip, and at orbit aerocraft, the structural representation of replaceable module and mechanical arm tail end; As shown in the illustrated embodiment of fig. 1, this device comprises: receive cone 1, docking adapter 2 and general handgrip 5; Above-mentioned receiving cone 1 is installed on orbit aerocraft 3; Above-mentioned docking adapter 2 is installed on replaceable module 4; Above-mentioned general handgrip 5 is installed on mechanical arm tail end 6, therefore under mechanical arm tail end 6 drives, can do suitable, counter-clockwise rotary motion and up-and-down movement around central axis.
The lower end of above-mentioned receiving cone 1 has installs guide cone 18, and centre has the dead bolt bayonet socket 17 that can hold dead bolt.
Above-mentioned docking adapter 2 comprises main structure body 10, dead bolt 14, stage clip 13 and unlocks push rod 12; The upper end of main structure body 10 is the guiding cone structure of mating with installation guide cone 18, middle part is the mounting flange structure of mating with replaceable module 4, middle lower end is the outside thread 11 mated with general handgrip 5 negative thread 8, and lower end is the guiding cone structure of mating with general handgrip 5 handgrip guide cone 9; Dead bolt 14 and stage clip 13 are installed on the middle epimere of main structure body 10, are symmetrically arranged; Unlock the symmetrical stage casing being installed on main structure body 10 of push rod 12, and unlock push rod 12 upper end and be in dead bolt 14 and unlock on inclined-plane, when unlocking the application force that push rod 12 lower end is subject to upwards, unlock push rod 12 upward movement, thus about promoting, two dead bolts 14 overcome stage clip 13 application force, move to central axis; And when unlocking the application force removed upwards push rod 12 lower end, stage clip 13 promotes two dead bolts 14 to direction motion outside central axis, until dead bolt 14 is subject to the stop of main structure body 10, meanwhile, dead bolt 14 ramp structure promotion unblock push rod 12 moves downward.
Above-mentioned general handgrip 5 upper end has handgrip guide cone 9; Interlude inside is and the negative thread 8 docking adapter 2 main structure body 10 outside thread 11 and mate; Hypomere middle part is provided with travel switch 7, for docking after adapter 2 docks with general handgrip 5, provide both docking and catch the signal that puts in place, and follow-up docking unlocking the signal that puts in place.
Further mode of operation of the present invention and process are described below.
Realize replaceable module and at orbit aerocraft, the state locked be installed being described to the present invention below.
Fig. 2 is replaceable module and installs at orbit aerocraft the cutaway view locked; As shown for example in fig. 2, replaceable module 4 with at orbit aerocraft 3 by receiving cone 1 and docking the installation that adapter 2 realizes between the two and lock, replaceable module electrical connector 15 completes electrical equipment with aircraft electrical joint 16 and is connected.The radial weight that replaceable module 4 bears is by main structure body 10 and the cylinder contacts face of receiving cone 1, and the mating surfaces transmission of replaceable module electrical connector 15 and aircraft electrical joint 16.The axial separation load that replaceable module 4 bears is by the connection transmission between dead bolt 14 and dead bolt bayonet socket 17.The stage clip 13 of docking adapter 2 inside ensures that dead bolt 14 is in the state of stretching out, and makes to be positioned at the dead bolt bayonet socket 17 receiving cone 1 inner, thus realizes replaceable module 4 and reliable installation the between orbit aerocraft 3 locks.
Realize to the present invention the state that mechanical arm tail end catches replaceable module to be below described.
Fig. 3 is the cutaway view that mechanical arm tail end catches replaceable module; Before mechanical arm tail end 6 catches replaceable module 4, general handgrip 5 with dock the location status of adapter 2 as shown in Figure 2.The handgrip guide cone 9 relying on design on general handgrip 5 and the guiding cone structure of docking on adapter 2, realize the position between mechanical arm tail end 6 and replaceable module 4 and attitude misalignment correction, general handgrip 5 rotates upward movement around central axis under mechanical arm tail end 6 drives afterwards, thus the negative thread 8 realized on general handgrip 5 and being threaded between the outside thread 11 docked on adapter 2, and finally realize mechanical arm tail end 6 and catch replaceable module 4 completely, and by being arranged on the travel switch 7 of general handgrip 5 hypomere middle part, provide docking and catch the signal that puts in place.
Realize replaceable module to the present invention to be below described with the state unlocked at orbit aerocraft.
Fig. 4 is replaceable module and the cutaway view unlocked at orbit aerocraft, replaceable module 4 is caught completely at mechanical arm tail end 6, and by being arranged on the travel switch 7 of general handgrip 5 hypomere middle part, provide after docking catches the signal that puts in place, as shown in Figure 3, general handgrip 5 continues to rotate upward movement around central axis under mechanical arm tail end 6 drives, thus make the handgrip guide cone 9 of general handgrip 5 upper end drive unblock push rod 12 upward movement docked on adapter 2, and then make unblock push rod 12 drive dead bolt 14, overcome stage clip 13 application force, move to central axial direction, and finally realize dead bolt 14 and receive the dead bolt bayonet socket 17 of cone 1 to depart from retraining, namely replaceable module 4 and the mechanical release state between orbit aerocraft 3 is realized.
Realize replaceable module to the present invention to be below described with the state be separated at orbit aerocraft.
Fig. 5 is the cutaway view that replaceable module is separated with at orbit aerocraft; After realizing replaceable module 4 and the mechanical release state between orbit aerocraft 3, general handgrip 5 mechanical arm tail end 6 drive under centrally axis move downward, thus drive docking adapter 2 and replaceable module 4 to move downward, and after replaceable module electrical connector 15 and aircraft electrical joint 16 depart from completely, realize replaceable module 4 and being separated between orbit aerocraft 3.
Realize to the present invention the working process that replaceable module is placed and new module is installed below to be described.
Replaceable module 4 is captured at mechanical arm tail end 6, realize replaceable module 4 with after being separated between orbit aerocraft 3, replaceable module 4 is delivered to waste and old module and to be berthed mouth by mechanical arm tail end 6, bores 1 realize location correction with the berth receiving that mouth is arranged of waste and old module, as shown in Figure 4 similar.Then, general handgrip 5 moves downward around central axis contrarotation under mechanical arm tail end 6 drives, the application force unlocking push rod 12 lower end is removed gradually, stage clip 13 promotes two dead bolts 14 to direction motion outside central axis, until dead bolt 14 is subject to the stop of main structure body 10, meanwhile, dead bolt 14 ramp structure promotion unblock push rod 12 moves downward, dead bolt 14 locks the dead bolt bayonet socket 17 received on cone 1 simultaneously, as shown in Figure 3 similar.Subsequently, general handgrip 5 continues contrarotation around central axis and moves downward under mechanical arm tail end 6 drives, until mechanical arm tail end 6 and replaceable module 4 depart from constraint completely, as shown in Figure 2 similar.By above operation, the replaceable module 4 namely achieved on orbit aerocraft 3 transfers to the operation that waste and old module is berthed on mouth; Adopt similar operations, just can realize the new module being configured with docking adapter 2, to the fitting operation received on cone 1, thus realize new module toward the installation on orbit aerocraft 3.
Although the present invention adopts a preferred embodiment to be described, should be appreciated that this and do not mean that the present invention will be confined to this embodiment.On the contrary, the present invention substitutes to comprise in the spirit and scope of the present invention that can be included in and be limited by appending claims all, changes and equivalent.
Claims (2)
1. a replaceable module docking facilities, it is characterized in that, this device comprises: receive cone [1], docking adapter [2] and general handgrip [5], cone [1] lower end is received to have installation guide cone [18], centre has the dead bolt bayonet socket [17] that can hold the upper latch-up structure of dead bolt [14], cone [1] is received to be connected on orbit aerocraft [3] by machanical fastener, docking adapter [2] primary member is main structure body [10], mounted inside has unblock push rod [12], stage clip [13] and dead bolt [14], the upper end of main structure body [10] is the guiding cone structure of mating with installation guide cone [18], the mounting flange structure of middle part for mating with replaceable module [4], middle lower end is the outside thread [11] mated with general handgrip [5] negative thread [8], the guiding cone structure of lower end for mating with the handgrip guide cone [9] on general handgrip [5], stage clip [13] and dead bolt [14] are installed on the middle epimere of main structure body, are symmetrically arranged, unlock push rod [12] the symmetrical stage casing being installed on main structure body [10], and unblock push rod [12] upper end is on dead bolt [14] unblock inclined-plane.
2. a kind of replaceable module docking facilities according to claim 1, is characterized in that, described general handgrip [5] upper end has handgrip guide cone [9]; Interlude inside for the negative thread [8] docking adapter structure main body outside thread [11] and mate; Hypomere middle part is provided with travel switch [7].
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110368944.0A CN103121516B (en) | 2011-11-18 | 2011-11-18 | Replaceable module butt joint device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110368944.0A CN103121516B (en) | 2011-11-18 | 2011-11-18 | Replaceable module butt joint device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103121516A CN103121516A (en) | 2013-05-29 |
| CN103121516B true CN103121516B (en) | 2015-04-22 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201110368944.0A Active CN103121516B (en) | 2011-11-18 | 2011-11-18 | Replaceable module butt joint device |
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| CN (1) | CN103121516B (en) |
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| CN103662105A (en) * | 2013-11-20 | 2014-03-26 | 上海宇航系统工程研究所 | Connecting and unlocking device for replaceable module |
| CN103662103B (en) * | 2013-11-20 | 2015-09-30 | 上海宇航系统工程研究所 | A kind of replaceable module tension release gear |
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| CN105151329B (en) * | 2015-09-02 | 2017-03-29 | 李新洪 | In-orbit replaceable module carries adaptor interface device, adaptation method and system |
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| CN108019401A (en) * | 2017-12-06 | 2018-05-11 | 沈阳航天新光集团有限公司 | A kind of connection separator of underlying mechanism |
| CN108284964B (en) * | 2017-12-22 | 2021-07-27 | 中国船舶重工集团公司第七0七研究所 | Lower support block of compatible mobile course measuring device |
| CN110416775B (en) * | 2019-06-03 | 2020-12-08 | 中国航天时代电子有限公司 | Electromechanical butt joint interface and on-orbit reconfigurable aircraft unit based on same |
| CN111092328B (en) * | 2019-12-20 | 2021-03-26 | 北京航空航天大学 | Three-level fault-tolerant docking mechanism capable of resisting on-orbit impact |
| CN111252269B (en) * | 2020-01-21 | 2020-12-18 | 上海宇航系统工程研究所 | On-orbit transfer device |
| CN111717424B (en) * | 2020-06-02 | 2022-07-15 | 上海空间推进研究所 | On-orbit installation system |
| CN113285301B (en) * | 2021-05-19 | 2023-06-30 | 菲尼克斯亚太电气（南京）有限公司 | Locking device, unlocking device and locking and unlocking assembly |
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| CN103121516A (en) | 2013-05-29 |
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