CN102975848A - Hatch cover opening-closing executing mechanism for spacecraft - Google Patents
Hatch cover opening-closing executing mechanism for spacecraft Download PDFInfo
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- CN102975848A CN102975848A CN2012104550209A CN201210455020A CN102975848A CN 102975848 A CN102975848 A CN 102975848A CN 2012104550209 A CN2012104550209 A CN 2012104550209A CN 201210455020 A CN201210455020 A CN 201210455020A CN 102975848 A CN102975848 A CN 102975848A
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- hatchcover
- guide finger
- sleeve
- axle
- shape groove
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Abstract
The invention discloses a hatch cover opening-closing executing mechanism for a spacecraft, and belongs to the technical field of spacecrafts. The hatch cover opening-closing executing mechanism for the spacecraft is mainly composed of a hatch cover shaft, a sleeve, a lead screw, a nut, a guide pin and the like. Rotational motion of the lead screw is transformed to rotational and displacement motion of a hatch cover, and the rotational and displacement motion is conducted in sequence, so that the hatch cover is closed or opened, appearance integrity of the spacecraft is guaranteed, and load security of a cabin is protected. The hatch cover opening-closing executing mechanism for the spacecraft is compact and reliable in structure and small in influencing by space environment, such as temperature alternating and electromagnetic irradiation.
Description
Technical field
The present invention relates to a kind of spacecraft with switch hatchcover actuating unit, belong to the spacecraft technology field.
Background technology
Spacecraft, especially unmanned probing spacecraft after carrying out the objects outside Earth sample collection, need to shift the sample that gathers in spacecraft.Therefore, hatchcover mechanism need to be set, shift behind spacecraft at sample and close hatchcover, the sample that protection gathers guarantees the complete of spacecraft profile.In addition, have many intermittently used equipment that over cap need to be set on the spacecraft, open at its work-hours, out-of-work-time is closed protection.
The hatchcover mechanism of many spacecrafts adopts the unfolding mode of shell type, although the angle of opening is large, the sports envelope space is also larger, is only applicable to the outside unscreened situation of spacecraft, can't use under the environment of spacecraft mechanism kinematic limited space.
Summary of the invention
Given this, the invention discloses a kind of spacecraft switch hatchcover actuating unit, this mechanism structure is compact reliably, the path of motion enveloping space is less, is subjected to such environmental effects little, can overcome the deficiencies in the prior art.
A kind of spacecraft comprises: hatchcover axle, sleeve, leading screw, front guide finger, rear guide finger I, nut, long jackscrew I, bearing carrier ring, bearing, intermediate washer, adjustment pad, tightening cushion, pre-load nut, short jackscrew, rear guide finger II, long jackscrew II with switch hatchcover actuating unit;
Wherein, have vertically " L " shape groove and " one " shape groove on the cylindrical of sleeve, the horizontal sides of " L " shape groove is positioned at the top of sleeve, and " one " shape groove is centrosymmetric with the vertical edges of " L " shape groove;
There is the plug helix of two symmetries the inside, the lower semisection face of cylinder of hatchcover axle;
Hatchcover axle and sleeve are free-running fit, cooperate section spraying lubricating film; It is secondary that leading screw and nut consist of worm drive; Two centres are installed on the leading screw intermediate washer and back-to-back bearing, and bearing carrier ring is sleeved on the outer ring of bearing, forms interference fit, and sleeve set forms interference fit on the outer ring of bearing carrier ring; Pre-load nut is threaded connection the bottom that is installed in leading screw; By the combined action of intermediate washer, tightening cushion and pre-load nut, with two bearing pre-tighteneds;
Front guide finger is installed on the hatchcover axle by short jackscrew;
The end of rear guide finger I and rear guide finger II radially is installed on the nut by long jackscrew I and long jackscrew II left and right symmetrically respectively, the other end level of rear guide finger I is passed plug helix corresponding on the hatchcover axle and " L " shape groove on the sleeve, and the other end level of rear guide finger II is passed one on plug helix corresponding on the hatchcover axle and the sleeve " the shape groove;
The front end of hatchcover axle is connected with hatchcover.
Beneficial effect
Single rotatablely moving is converted into the axial translation of sequencing and the motion that rotates in a circumferential direction, goes into the action of opening, closing hatchcover.Lead screw transmission and hatchcover axle center superposition are integrated on the same axis, and structure design is compact, save the space.The motion control process is simple.
Description of drawings
Fig. 1 is the structural representation of the present invention under contraction state; 1: hatchcover axle, 2: sleeve, 3: leading screw, 4: front guide finger, 5: rear guide finger I, 6: nut:, 7: long jackscrew I, 8: bearing carrier ring, 9: angular contact ball bearing, 10: intermediate washer, 11: adjust pad, 12: tightening cushion, 13: pre-load nut, 14: short jackscrew, 15: rear guide finger II, 16: long jackscrew II;
Fig. 2 is that the present invention does the constitution diagram under the axial translation state of kinematic motion;
Fig. 3 is that the present invention does the constitution diagram under the state of kinematic motion that rotates in a circumferential direction.
The specific embodiment
Below in conjunction with Figure of description and specific embodiment the present invention is described in further details.
As shown in Figure 1, the present invention is mainly by hatchcover axle 1, sleeve 2, leading screw 3, front guide finger 4, rear guide finger I5, nut 6, long jackscrew I7, bearing carrier ring 8, angular contact ball bearing 9, intermediate washer 10, adjustment pad 11, tightening cushion 12, pre-load nut 13, short jackscrew 14, rear guide finger II15, long jackscrew II16;
Wherein, have vertically " L " shape groove and " one " shape groove on the cylindrical of sleeve 2, the horizontal sides of " L " shape groove is positioned at the top of sleeve 2, and " one " shape groove is centrosymmetric with the vertical edges of " L " shape groove;
There is the plug helix of two symmetries the inside, the lower semisection face of cylinder of hatchcover axle 1;
Hatchcover axle 1 is free-running fit with sleeve 2, cooperates section spraying molybdenum disulphide lubricating film, reduces friction and prevents the vacuum cold welding phenomenon; Leading screw 3 consists of the worm drive pair with nut 6; Two centres are installed on the leading screw 3 intermediate washer 10 and back-to-back angular contact ball bearing 9, and an end of leading screw 3 stagger angle contact ball bearings 9 is power intake, is connected with propulsion source; Bearing carrier ring 8 is sleeved on the outer ring of angular contact ball bearing 9, forms interference fit, and bearing carrier ring 8 is sleeved on the below, inside of sleeve 2, forms interference fit; Pre-load nut 13 is threaded connection the bottom that is installed in leading screw 3; By the combined action of intermediate washer 10, tightening cushion 12 and pre-load nut 13, with two angular contact ball bearing 9 pretensions, eliminate the gap, improve bearing-transmission precision and service life;
Front guide finger 4 is installed on the hatchcover axle 1 by short jackscrew 14, is constrained in " L " shape groove on the sleeve 2;
The end of rear guide finger I 5 and rear guide finger II 15 radially is installed on the nut 6 by long jackscrew I 7 and long jackscrew II 16 left and right symmetricallies respectively, the other end level of rear guide finger I5 is passed plug helix corresponding on the hatchcover axle 1 and " L " shape groove on the sleeve 2, and the other end level of rear guide finger II15 is passed plug helix corresponding on the hatchcover axle 1 and " one " shape groove on the sleeve 2;
The front end of hatchcover axle 1 can be connected with the hatchcover of various shapes.
As shown in Figure 2, when whole mechanism was started working by contraction state, leading screw 3 rotated under the driving of propulsion source, drive nut 6 and rear guide finger I(5 mounted thereto), rear guide finger II(15) do at first vertically motion of translation along the groove of sleeve 2 both sides.Because guide finger constrains in two plug helixs of hatchcover axle 1 after two, therefore Indirect driven hatchcover axle 1 is done the turning that axial translation moves to groove with front guide finger 4 " L " shape groove on sleeve 2 mounted thereto, reaches axial maximum displacement (external presentation is that the hatchcover axial translation stretches out).
As shown in Figure 3, when hatchcover axle 1 after " L " shape groove moves to the turning on sleeve 2 with front guide finger 4 mounted thereto, nut 6 and rear guide finger I5 mounted thereto, rear guide finger II15 continue to do motion of translation under the driving of leading screw 3, force front guide finger 4 in " L " shape groove, to continue along the circumferential portion componental movement, driving hatchcover axle 1 does circumferential movement (external presentation is the hatchcover Unscrew to the end of " L " shape groove, expose space in the cabin), simultaneously, guide finger moves along two plug helixs on the hatchcover axle 1 after two.So far, finish the whole hatchcover action of opening.
Close the hatchcover action and be the contrary motion of said sequence motion.
For reducing scantling of structure, angular contact ball bearing 9 can be replaced to plain bearing, also can with front guide finger be connected guide finger and adopt interference fit, be threaded or bonding mode is connected with nut with hatchcover axle 1 respectively and is connected.
Can by the design to two plug helix length on " L " shape groove circumferential lengths and the hatchcover axle 1 on the sleeve 2, realize the angle of control hatchcover Unscrew.By to " L " shape fluted shaft on the sleeve 2 to the design of length and correlated parts axial length, realize the length that the translation of control hatchcover is stretched out.
In sum, more than only be a kind of preferred embodiments of the present invention, be not for limiting protection scope of the present invention.Within the spirit and principles in the present invention all, any modification of doing, be equal to replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (3)
1. a spacecraft is characterized in that comprising: hatchcover axle (1), sleeve (2), leading screw (3), front guide finger (4), rear guide finger I(5 with switch hatchcover actuating unit), nut (6), long jackscrew I(7), bearing carrier ring (8), bearing (9), intermediate washer (10), adjust pad (11), tightening cushion (12), pre-load nut (13), lack jackscrew (14), rear guide finger II(15), long jackscrew II(16);
Wherein, have vertically " L " shape groove and " one " shape groove on the cylindrical of sleeve (2), the horizontal sides of " L " shape groove is positioned at the top of sleeve (2), and " one " shape groove is centrosymmetric with the vertical edges of " L " shape groove;
There is the plug helix of two symmetries the inside, the lower semisection face of cylinder of hatchcover axle (1);
Hatchcover axle (1) is free-running fit with sleeve (2), cooperates section spraying lubricating film; Leading screw (3) consists of the worm drive pair with nut (6); There are intermediate washer (10) and back-to-back bearing (9) in two centres of the upper installation of leading screw (3), and bearing carrier ring (8) is sleeved on the outer ring of bearing (9), forms interference fit, and sleeve (2) is sleeved on the outer ring of bearing carrier ring (8), forms interference fit; Pre-load nut (13) is threaded connection the bottom that is installed in leading screw (3); By the combined action of intermediate washer (10), tightening cushion (12) and pre-load nut (13), with two bearings (9) pretension;
Front guide finger (4) is installed on the hatchcover axle (1) by short jackscrew (14);
Rear guide finger I(5) and rear guide finger II(15) an end respectively by long jackscrew I(7) and long jackscrew II(16) left and right symmetrically radially is installed on the nut (6), rear guide finger I(5) other end level is passed plug helix corresponding to hatchcover axle (1) and " L " shape groove on the sleeve (2), rear guide finger II(15) other end level pass the upper corresponding plug helix of hatchcover axle (1) and " one " shape groove on the sleeve (2);
The front end of hatchcover axle (1) is connected with hatchcover.
2. a kind of spacecraft according to claim 1 is with switch hatchcover actuating unit, it is characterized in that: leading screw (3) rotates under the driving of propulsion source, drive nut (6) and rear guide finger I(5 mounted thereto), rear guide finger II(15) do axial translation motion along the groove of sleeve (2) both sides, Indirect driven hatchcover axle (1) is done axial translation or is rotated in a circumferential direction motion along upper " L " shape groove of sleeve (2) with front guide finger (4) mounted thereto.
3. a kind of spacecraft according to claim 1 is with switch hatchcover actuating unit, and it is characterized in that: described lubricating film is the molybdenum disulphide lubricating film.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012104550209A CN102975848A (en) | 2012-11-13 | 2012-11-13 | Hatch cover opening-closing executing mechanism for spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012104550209A CN102975848A (en) | 2012-11-13 | 2012-11-13 | Hatch cover opening-closing executing mechanism for spacecraft |
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| Publication Number | Publication Date |
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| CN102975848A true CN102975848A (en) | 2013-03-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012104550209A Pending CN102975848A (en) | 2012-11-13 | 2012-11-13 | Hatch cover opening-closing executing mechanism for spacecraft |
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| Country | Link |
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| CN (1) | CN102975848A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104832033A (en) * | 2013-12-16 | 2015-08-12 | 拉蒂尔菲雅克公司 | Motorized device for opening and/or closing an aircraft door |
| CN108002277A (en) * | 2017-12-29 | 2018-05-08 | 贵州大学 | A kind of directional solidification conticaster furnace cover lifting device |
| CN108320385A (en) * | 2018-02-15 | 2018-07-24 | 河南智售宝智能科技有限公司 | A kind of automatic vending machine stretches shipment device and rotating mechanism |
| CN111102233A (en) * | 2020-01-07 | 2020-05-05 | 北京中科科仪股份有限公司 | Bearing mounting structure and heat-conducting grease filling method |
| CN113374370A (en) * | 2021-06-25 | 2021-09-10 | 庆安集团有限公司 | Time sequence actuating mechanism |
| CN113650809A (en) * | 2018-08-13 | 2021-11-16 | 蓝箭航天空间科技股份有限公司 | Spacecraft cabin segment blanking cover, cabin segment structure and spacecraft |
| CN115076264A (en) * | 2021-03-16 | 2022-09-20 | 陕西国力信息技术有限公司 | Variable-lead motion conversion mechanism and electronic mechanical brake |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN1114984A (en) * | 1994-07-14 | 1996-01-17 | 中国科学院兰州化学物理研究所 | Common-sputtering solid lubricating film |
| CN2575257Y (en) * | 2002-09-23 | 2003-09-24 | 帅伟金 | Vehicle door lock |
| CN202012238U (en) * | 2011-03-21 | 2011-10-19 | 苏州德仕耐五金技术有限公司 | Rotary tension lock |
| CN102965707A (en) * | 2012-07-23 | 2013-03-13 | 贵州航天精工制造有限公司 | Method for electrodeposition of solid lubricating film by molybdenum disulfide liquid lubricant |
-
2012
- 2012-11-13 CN CN2012104550209A patent/CN102975848A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1114984A (en) * | 1994-07-14 | 1996-01-17 | 中国科学院兰州化学物理研究所 | Common-sputtering solid lubricating film |
| CN2575257Y (en) * | 2002-09-23 | 2003-09-24 | 帅伟金 | Vehicle door lock |
| CN202012238U (en) * | 2011-03-21 | 2011-10-19 | 苏州德仕耐五金技术有限公司 | Rotary tension lock |
| CN102965707A (en) * | 2012-07-23 | 2013-03-13 | 贵州航天精工制造有限公司 | Method for electrodeposition of solid lubricating film by molybdenum disulfide liquid lubricant |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104832033A (en) * | 2013-12-16 | 2015-08-12 | 拉蒂尔菲雅克公司 | Motorized device for opening and/or closing an aircraft door |
| CN108002277A (en) * | 2017-12-29 | 2018-05-08 | 贵州大学 | A kind of directional solidification conticaster furnace cover lifting device |
| CN108320385A (en) * | 2018-02-15 | 2018-07-24 | 河南智售宝智能科技有限公司 | A kind of automatic vending machine stretches shipment device and rotating mechanism |
| CN113650809A (en) * | 2018-08-13 | 2021-11-16 | 蓝箭航天空间科技股份有限公司 | Spacecraft cabin segment blanking cover, cabin segment structure and spacecraft |
| CN111102233A (en) * | 2020-01-07 | 2020-05-05 | 北京中科科仪股份有限公司 | Bearing mounting structure and heat-conducting grease filling method |
| CN115076264A (en) * | 2021-03-16 | 2022-09-20 | 陕西国力信息技术有限公司 | Variable-lead motion conversion mechanism and electronic mechanical brake |
| CN113374370A (en) * | 2021-06-25 | 2021-09-10 | 庆安集团有限公司 | Time sequence actuating mechanism |
| CN113374370B (en) * | 2021-06-25 | 2022-08-23 | 庆安集团有限公司 | Time sequence actuating mechanism |
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20130320 |