CN114408229A - Anti-floating guide interface device for operating equipment of astronaut - Google Patents
Anti-floating guide interface device for operating equipment of astronaut Download PDFInfo
- Publication number
- CN114408229A CN114408229A CN202210159975.3A CN202210159975A CN114408229A CN 114408229 A CN114408229 A CN 114408229A CN 202210159975 A CN202210159975 A CN 202210159975A CN 114408229 A CN114408229 A CN 114408229A
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- guide
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- positioning pin
- astronaut
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- 238000007667 floating Methods 0.000 title abstract description 18
- 230000001681 protective effect Effects 0.000 claims abstract description 31
- 235000014676 Phragmites communis Nutrition 0.000 claims abstract description 14
- 238000005452 bending Methods 0.000 claims description 10
- 230000000694 effects Effects 0.000 abstract description 4
- 230000002265 prevention Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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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
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Insertion Pins And Rivets (AREA)
Abstract
The invention discloses an anti-floating guide interface device for operating equipment of astronauts, which is used for connecting a space station with the operating equipment and comprises a protective shell, a first guide through hole and a second guide through hole, wherein the protective shell is used for fixedly connecting the operating equipment and is provided with a first guide through hole; the cover plate is connected and arranged on the inner side of the protective shell and is provided with a second guide through hole; the limiting spring is arranged in the side wall of the protective shell, and the opening part is surrounded at the outer edge of the first guide through hole; a locating pin for connecting the space station; the second guide through hole is arranged corresponding to the first guide through hole to form a guide hole for inserting the positioning pin and limiting the degree of freedom of the positioning pin in the first direction; be equipped with the diameter on the locating pin and be less than the guiding hole diameter, and be greater than the spacing boss of spacing reed diameter works as the locating pin inserts in the guiding hole, the spacing reed takes place to warp, the restriction the second direction degree of freedom of locating pin can realize weightlessness and prevent floating the effect, is convenient for astronaut's in-orbit operation.
Description
Technical Field
The invention relates to the technical field of anti-floating guide of on-orbit operation of spacecraft equipment, in particular to an anti-floating guide interface device for operating equipment of astronauts.
Background
With the continuous deepening and development of the aerospace technology, more and more space exploration tasks provide more requirements for the in-orbit operation of an aircraft, the in-orbit operation equipment of a astronaut lacks a guiding and positioning device, and the products are unstable in weightlessness and floating in space, so that the difficulty in-orbit dismounting and mounting of the products is increased. Due to limited operating capability of space shuttle and limitations of arrangement and structure of aircraft equipment, the space shuttle lacks positioning guidance and takes time when dismounting the equipment in orbit. Therefore, there is a need to design an anti-drift guide device for use in an aircraft operator.
Disclosure of Invention
The invention aims to provide an anti-floating guide interface device for operating equipment by astronauts, which solves the problems that the equipment cannot be positioned and is weightless and floating in the process of operating the equipment by the astronauts in orbit.
In order to achieve the above object, the present invention provides an anti-drift guiding interface device for an operating device of an astronaut, for connecting a space station with the operating device, the anti-drift guiding interface device comprising: the protective shell is used for fixedly connecting the operating equipment and is provided with a first guide through hole; the cover plate is connected and arranged on the inner side of the protective shell and is provided with a second guide through hole; the limiting spring leaf is arranged in the side wall of the protective shell and is of a semi-surrounding structure, and the opening part is surrounded at the outer edge of the first guide through hole; a locating pin for connecting the space station; the second guide through hole on the cover plate is arranged corresponding to the first guide through hole on the protective shell to form a guide hole for inserting the positioning pin and limiting the first direction freedom degree of the positioning pin; the locating pin on be equipped with the diameter and be less than the guiding hole diameter, be greater than the spacing boss of spacing reed diameter, work as the locating pin insert in the guiding hole, the spacing reed take place to warp, form to spacing boss's screens, the restriction the second direction degree of freedom of locating pin.
Preferably, the limiting spring plate comprises at least two limiting planes.
Preferably, the limiting plane is further provided with a bending structure, so that the positioning pin can be normally inserted without clamping stagnation.
Preferably, the bending structure is located at an end of the limiting plane and is inwardly convex and tilted.
Preferably, the shape of the limit boss is any one of a triangle, a quadrangle, a pentagon and a hexagon.
Preferably, an upper cone is further arranged on the locating pin.
Preferably, the locating pin is further provided with an external thread.
Preferably, the protective shell and the cover plate are fixedly connected through screws.
The invention has the beneficial effects that:
(1) under the condition of space weightlessness, the product has a floating condition, the positioning and mounting operation difficulty is high, the radial freedom degree of the positioning pin can be limited by a guide hole formed by the guide through hole of the protective shell and the guide through hole of the cover plate, the axial freedom degree of the positioning pin can be limited by the clamping action of the limiting reed and the limiting boss, and the weightlessness and floating prevention effect can be achieved when the device is operated on a rail through the floating prevention guide interface device;
(2) the bending structure of the limiting spring leaf can ensure that the positioning pin is normally inserted without clamping stagnation, and the upper cone of the positioning pin can provide guidance for in-orbit product installation, so that the in-orbit operation of astronauts is facilitated;
(3) the anti-floating guide interface device is simple in structure and convenient to operate, can save time and labor for the on-orbit operation of astronauts, and improves the working efficiency.
Drawings
Fig. 1 is an external view schematically showing an anti-drift guide interface device for an operating device of an astronaut.
Fig. 2 is a schematic structural view (first orientation) of an anti-drift guide interface device for an astronaut operating apparatus.
Fig. 3 is a schematic structural view (second orientation) of an anti-drift guide interface device for an astronaut operating apparatus.
Fig. 4 is a schematic illustration of a protective shell of an anti-flutter guiding interface device for an astronaut operating device.
Fig. 5 is a schematic illustration of a cover plate of an anti-flutter guiding interface device for an astronaut operating device.
Fig. 6 is a schematic view of a locating pin of an anti-flutter guide interface device for an astronaut operating device.
Fig. 7 is a schematic view of a limit reed of an anti-flutter guiding interface device for an astronaut operating device.
In the figure, 1-protective shell, 11-protective shell first threaded hole, 12-protective shell second threaded hole, 13-first guiding through hole, 14-mounting hole, 2-cover plate, 21-cover plate first threaded hole, 22-second guiding through hole, 3-positioning pin, 31-upper cone, 32-hexagonal limiting boss, 33-external thread, 4-first screw, 5-limiting reed, 51-limiting reed threaded hole, 52-bending structure, 53-limiting plane and 6-second screw.
Detailed Description
The technical solution of the present invention is further described below with reference to the accompanying drawings and examples.
As shown in fig. 1 to 7, an anti-drift guiding interface device for an operating device of an astronaut provided by the present invention is used for connecting a space station and the operating device, and comprises: positioning pins 3 for connecting the space stations; the protective shell 1 is used for fixedly connecting the operating equipment and is provided with a first guide through hole 13; the cover plate 2 is connected and arranged on the inner side of the protective shell 1 and is provided with a second guide through hole 22; the limiting spring leaf 5 is arranged in the side wall of the protective shell 1 and has a semi-surrounding structure, and the opening part is surrounded at the outer edge of the first guide through hole 13; the second guiding through hole 22 on the cover plate 2 is arranged corresponding to the first guiding through hole 13 on the protective shell 1 to form a guiding hole for inserting the positioning pin 3 and limiting the first direction freedom degree of the positioning pin 3; the positioning pin 3 is provided with a limiting boss with the diameter smaller than that of the guide hole and larger than that of the limiting reed 5; when the positioning pin 3 is inserted into the guide hole, the limiting spring 5 deforms, the limiting spring 5 and the limiting boss are clamped, and the second direction freedom degree of the positioning pin 3 is limited.
In some embodiments, as shown in fig. 4 and 5, in order to limit the first degree of freedom of the positioning pin 3 in the first direction, the second guiding through hole 22 of the cover plate 2 and the first guiding through hole 13 of the protective shell 1 form a guiding hole for axially guiding and matching with the hole of the positioning pin 3, and in this embodiment, when the positioning pin 3 is inserted into the guiding hole, the degree of freedom of the positioning pin 3 in the radial direction can be limited.
In some embodiments, as shown in fig. 3 and 7, in order to limit the second degree of freedom of the positioning pin 3, a limit spring 5 is disposed in the sidewall of the protective shell 1, the limit spring 5 is a semi-closed type high-elasticity thin-wall elastic member, and has a semi-enclosed structure, an opening portion is enclosed at the outer edge of the first guiding through hole 13, and the limit spring 5 includes two limit planes 53 in a symmetrical state.
The cross section of the limiting boss can be triangular, quadrilateral, pentagonal, hexagonal and the like. As shown in fig. 6, in the present embodiment, the limiting boss is a hexagonal limiting boss 32.
When the positioning pin 3 is inserted into the guide hole, the limiting spring 5 is elastically deformed, the limiting plane 53 is in contact with two symmetrical sides of the hexagonal limiting boss 32, and the hexagonal limiting boss 32 is clamped by the limiting plane 53, so that the limiting purpose is achieved. In this embodiment, after the limit spring 5 generates a clamping force to clamp the positioning pin 3, the axial degree of freedom of the positioning pin 3 is limited, so that the positioning pin 3 cannot float out in the on-rail condition.
As shown in fig. 7, in some embodiments, in order to allow the positioning pin 3 to be normally inserted without being jammed, a bending structure 52 is disposed at an end of the one limiting plane 53, the bending structure 52 has a curved surface structure and is inwardly raised, and the positioning pin 3 can be pulled out from the limiting spring 5 along the curved surface of the bending structure 52, so as to achieve the effect of preventing jamming.
As shown in fig. 6, in some embodiments, in order to insert the positioning pin 3 into the guide hole more accurately, the positioning pin 3 is further provided with an upper cone 31, if the upper cone 31 is not provided, when the positioning pin 3 is inserted into the guide hole, the positioning pin 3 needs to be inserted into the guide hole accurately according to the diameter of the guide hole, and the head of the upper cone 31 is arc-shaped like a cone, so that the positioning pin 3 is more easily inserted into the guide hole, which may make the guiding more convenient and accurate.
In some embodiments, as shown in fig. 6, in order to connect the dowel pin 3 to the space station, the dowel pin 3 is provided with an external thread 33 for cooperating with the space station.
In some embodiments, as shown in fig. 4, in order to connect the operating device to the anti-drift guide interface device, the protective shell 1 is provided with a mounting hole 14 for connecting the operating device to be installed, the protective shell first threaded hole 11 provided on the protective shell 1 is connected with the cover plate first threaded hole 21 provided on the cover plate 2 by using the first screw 4, and the protective shell second threaded hole 12 provided on the protective shell 1 is connected with the limit reed threaded hole 51 provided on the limit reed 5 by using the second screw 6.
The working principle of the anti-floating guide interface device for the operating equipment of the astronaut provided by the invention is as follows: when the positioning pin 3 is arranged on the space station, the protective shell 1, the limiting spring 5 and the cover plate 2 are combined and then arranged on the operating equipment; when the operating equipment needs to be installed on a space station, the upper cone 31 of the positioning pin 3 is inserted into the cover plate 2 and the second guide through hole 22 and penetrates out of the first guide through hole 13 of the protective shell 1 to limit radial relative movement; the two limiting planes 53 are in contact with two symmetrical sides of the hexagonal limiting boss 32, and the limiting spring 5 generates clamping force to clamp the positioning pin 3 and limit axial relative movement, so that the anti-floating guiding design concept of the interface device is realized; when the operating equipment needs to be separated from the space station, the operating equipment is pulled, and the bending structure 52 on the limiting reed 5 deforms, so that the upper cone 31 on the positioning pin 3 can be separated from the space station through the bending structure 52 on the limiting reed 5.
In summary, according to the anti-floating guide interface device for the operating equipment of the astronaut, provided by the invention, when the positioning pin is installed on the space station, the protective shell, the cover plate and the limiting spring leaf are assembled and then installed on the operating equipment, and when the positioning pin is inserted into the guide hole formed by the protective shell and the cover plate, the first direction freedom degree of the positioning pin is limited; the limiting spring plate is elastically deformed to generate clamping force on the positioning pin and limit the degree of freedom of the positioning pin in the second direction, so that the product is prevented from floating in the space, and the anti-floating guide effect is realized.
While the present invention has been described in detail with reference to the preferred embodiments, it should be understood that the above description should not be taken as limiting the invention. Various modifications and alterations to this invention will become apparent to those skilled in the art upon reading the foregoing description. Accordingly, the scope of the invention should be determined from the following claims.
Claims (8)
1. An anti-flutter guide interface device for an operating device of an astronaut, for connecting a space station to the operating device, said anti-flutter guide interface device comprising:
the protective shell is used for fixedly connecting the operating equipment and is provided with a first guide through hole;
the cover plate is connected and arranged on the inner side of the protective shell and is provided with a second guide through hole;
the limiting spring leaf is arranged in the side wall of the protective shell and is of a semi-surrounding structure, and the opening part is surrounded at the outer edge of the first guide through hole;
and a positioning pin for connecting the space station;
the second guide through hole in the cover plate is arranged corresponding to the first guide through hole in the protective shell to form a guide hole for inserting the positioning pin and limiting the degree of freedom of the positioning pin in the first direction;
the positioning pin is provided with a limiting boss with the diameter smaller than that of the guide hole and larger than that of the limiting reed; when the positioning pin is inserted into the guide hole, the limiting spring plate deforms to form a clamping position for the limiting boss, and the second direction freedom degree of the positioning pin is limited.
2. A flutter preventing guide interface device for an astronaut operating device according to claim 1, wherein said limit spring comprises not less than two limit planes.
3. A flutter preventing guide interface device for spacecraft operator equipment as claimed in claim 2, wherein said limiting plane is further provided with a bending structure to enable said positioning pin to be normally inserted without being stuck.
4. A flutter preventing guide interface device for an astronaut operating device according to claim 3, wherein the bent structure is located at an end of the limit plane and is inwardly convex.
5. A float resistant guide interface assembly for use with an astronaut's operating equipment as claimed in claim 1, wherein said limit boss is in the shape of any one of a triangle, quadrilateral, pentagon, hexagon.
6. A flutter preventing guide interface device for an astronaut operating device according to claim 1, wherein an upper cone is further provided on the dowel pin.
7. A flutter preventing guide interface device for an astronaut operating device according to claim 1, wherein the dowel pin is further provided with an external thread.
8. A float resistant guide interface assembly for an astronaut's operating equipment according to claim 1, wherein said protective housing is fixedly attached to said cover plate by screws.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210159975.3A CN114408229B (en) | 2022-02-22 | 2022-02-22 | Anti-drifting guide interface device for astronaut operation equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210159975.3A CN114408229B (en) | 2022-02-22 | 2022-02-22 | Anti-drifting guide interface device for astronaut operation equipment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114408229A true CN114408229A (en) | 2022-04-29 |
| CN114408229B CN114408229B (en) | 2023-11-17 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210159975.3A Active CN114408229B (en) | 2022-02-22 | 2022-02-22 | Anti-drifting guide interface device for astronaut operation equipment |
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| Country | Link |
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| CN (1) | CN114408229B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0268824A1 (en) * | 1986-10-29 | 1988-06-01 | Leonhardy GmbH | Spring contact strip |
| EP0847222A2 (en) * | 1996-12-05 | 1998-06-10 | NOKIA TECHNOLOGY GmbH | Retaining grid |
| JP2005510849A (en) * | 2001-11-21 | 2005-04-21 | バル・シール・エンジニアリング・カンパニー・インコーポレーテッド | A detachable and conductive connector that can be connected and disconnected without the use of tools. |
| CN2724253Y (en) * | 2004-08-03 | 2005-09-07 | 聂玉霞 | Swing shock-proof and anti-slip safety socket |
| CN104266041A (en) * | 2014-09-25 | 2015-01-07 | 江南工业集团有限公司 | Underwater bottom fixing device |
| CN105443535A (en) * | 2014-09-27 | 2016-03-30 | 东风(十堰)有色铸件有限公司 | Elastic positioning pin |
| CN207683800U (en) * | 2018-01-05 | 2018-08-03 | 宏佳实业有限公司 | Space articulation spacecraft group |
| CN212637903U (en) * | 2020-07-01 | 2021-03-02 | 亿航智能设备（广州）有限公司 | Connector and flying device |
-
2022
- 2022-02-22 CN CN202210159975.3A patent/CN114408229B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0268824A1 (en) * | 1986-10-29 | 1988-06-01 | Leonhardy GmbH | Spring contact strip |
| EP0847222A2 (en) * | 1996-12-05 | 1998-06-10 | NOKIA TECHNOLOGY GmbH | Retaining grid |
| JP2005510849A (en) * | 2001-11-21 | 2005-04-21 | バル・シール・エンジニアリング・カンパニー・インコーポレーテッド | A detachable and conductive connector that can be connected and disconnected without the use of tools. |
| CN2724253Y (en) * | 2004-08-03 | 2005-09-07 | 聂玉霞 | Swing shock-proof and anti-slip safety socket |
| CN104266041A (en) * | 2014-09-25 | 2015-01-07 | 江南工业集团有限公司 | Underwater bottom fixing device |
| CN105443535A (en) * | 2014-09-27 | 2016-03-30 | 东风(十堰)有色铸件有限公司 | Elastic positioning pin |
| CN207683800U (en) * | 2018-01-05 | 2018-08-03 | 宏佳实业有限公司 | Space articulation spacecraft group |
| CN212637903U (en) * | 2020-07-01 | 2021-03-02 | 亿航智能设备（广州）有限公司 | Connector and flying device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114408229B (en) | 2023-11-17 |
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