CN103274062B - A kind of attitude erection device of mars excurtion module - Google Patents
A kind of attitude erection device of mars excurtion module Download PDFInfo
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- CN103274062B CN103274062B CN201310145555.0A CN201310145555A CN103274062B CN 103274062 B CN103274062 B CN 103274062B CN 201310145555 A CN201310145555 A CN 201310145555A CN 103274062 B CN103274062 B CN 103274062B
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- centering ring
- lander
- attitude
- torsion spring
- base plate
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Abstract
The invention provides a kind of attitude erection device of mars excurtion module, comprise base plate (1), bearing (2), adapter shaft (3), torsion spring (4), centering ring (5) and compress release gear (6); Can under the condition of volume, weight, the equal very critical of power supply, the torsion spring compressed by priming system start release, thus drive centering ring to realize lander attitude righting function; Have that structure is simple, safe and reliable, volume is little, lightweight feature.As guaranteeing that lander is in the correct effective means of martian surface attitude, this erection device can directly apply to the development of lander in China's Mars landing detection mission first, also can provide reference for the design of the follow-up small ep lander of China simultaneously.
Description
Technical field
The present invention relates to Mars landing system, be specifically related to a kind of attitude erection device of mars excurtion module.
Background technology
China plans to launch Mars global remote sensing detector in December, 2015, realize Mars around, carry out Mars global remote sensing detection; Carry out Mars landing validation task, checking Mars enters deceleration landing correlation technique simultaneously.
Owing to being subject to launch window and existing portative constraint, the weight only 60kg of the whole device of lander in Mars global remote sensing detector, the volume of built-in cylindric lander, weight, the equal very critical of the energy; Meanwhile, because landing point relief feature and descent have uncertainty, the initial landing attitude of lander may be discontented with toe and determine towards upper Gesture, needs the later stage to adjust.Therefore, the lander attitude erection device of a kind of small, light, safe and reliable, low-consumption high-efficiency need be developed.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of attitude erection device for mars excurtion module.As guaranteeing that lander is in the correct effective means of martian surface attitude, this erection device can directly apply to the development of lander in China's Mars landing detection mission first, also can provide reference for the design of the follow-up small ep lander of China simultaneously.
According to an aspect of the present invention, a kind of attitude erection device of mars excurtion module is provided, comprise base plate, bearing, adapter shaft, torsion spring, centering ring and compression release gear, wherein, torsion spring to be placed on adapter shaft and to snap in groove reserved on the connector of centering ring, provides the moment of torsion needed for attitude righting; Be connected to the bearing support adapter shaft of base plate, and revolution space is provided; Compress release gear and comprise priming system, the operating bar of priming system stretches in the circular hole of centering ring one end radial direction and realizes substrate hold-down function.
Preferably, centering ring external diameter is 358mm, and the half cycle sectional dimension near torsion spring side is 4mm × 10mm, symmetrical two connectors with holes in middle part; Half cycle sectional dimension is 2mm × 10mm in addition, and middle part radial direction has circular hole.
According to another aspect of the present invention, a kind of mars excurtion module with the attitude erection device of mars excurtion module described in claim 1 or 2 is provided, comprise lander, base plate, bearing, adapter shaft, torsion spring, centering ring and compression release gear, wherein, torsion spring to be placed on adapter shaft and to snap in groove reserved on the connector of centering ring, provides the moment of torsion needed for attitude righting; Be connected to the bearing support adapter shaft of base plate, and revolution space is provided; Compress release gear and comprise priming system, the operating bar of priming system stretches in the circular hole of centering ring one end radial direction and realizes substrate hold-down function; Base plate carries out bolt with lander housing end face and is connected; Compress release gear to be connected with lander housing end face by bolt; Operating bar and centering ring are all parallel with lander end face.
According to a further aspect of the invention, the installation method of the attitude erection device of the mars excurtion module described in a kind of claim 1 or 2 is provided, comprises the steps:
Step 1: torsion spring, centering ring connector and bearing are successively placed on adapter shaft, and bearing is secured by bolts on base plate, and base plate is secured by bolts in lander housing end face;
Step 2: torsion spring two ends are stretched out pin and embedded in the reserved groove of centering ring connector, and centering ring is depressed into compacted position;
Step 3: the radial circular hole of operating bar through centering ring one end compressing release gear, is guaranteed that operating bar and centering ring are all parallel with lander end face, and is connected with lander housing end face by bolt.
The present invention adopts above method, be developed into a kind of attitude erection device being applicable to China's detection of Mars soft landing first lander, can when lander arbitrary end towards on adjust attitude, make device attachment face upwards, have that structure is simple, safe and reliable, volume is little, lightweight feature.
Accompanying drawing explanation
By reading the detailed description done non-limiting example with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious:
Fig. 1 is attitude erection device principle of work schematic diagram, and wherein, subgraph (1) to (5) represents that initial attitude, the start of compression release gear, torsion spring drive centering ring expansion, lander barycenter negotiate terrain fulcrum, final carriage respectively.
Fig. 2 is attitude erection device appearance schematic diagram.
Fig. 3 is attitude erection device composition schematic diagram.
Fig. 4 is centering ring structural representation.
Fig. 5 is each unit construction schematic diagram of torsion spring hinge, and wherein, subgraph (1) to (4) represents base arrangement figure, connecting axle structure figure, seat structure figure, torsion spring constructional drawing respectively.
Fig. 6 compresses release gear structural representation.
In figure:
1 is base plate;
2 is bearing;
3 is adapter shaft;
4 is torsion spring;
5 is centering ring;
6 for compressing release gear.
Detailed description of the invention
Below in conjunction with specific embodiment, the present invention is described in detail.Following examples will contribute to those skilled in the art and understand the present invention further, but not limit the present invention in any form.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, some distortion and improvement can also be made.These all belong to protection scope of the present invention.
The present invention proposes a kind of attitude erection device being applicable to China's detection of Mars soft landing first lander.This attitude erection device forms primarily of base plate 1, bearing 2, adapter shaft 3, torsion spring 4, centering ring 5 and compression release gear 6; Compress the torsion spring that release gear is compressed by priming system start release, thus drive centering ring to realize lander attitude righting function, guarantee lander given side upwards.
The major part of this erection device adopts light alloy material to make, and compress release gear 6 and configure small-sized priming system, envelope is of a size of 383mm × 358mm × 49mm, and be installed on lander end face, centering ring 5 is parallel with end face.
Centering ring 5 external diameter is 358mm, and the half cycle sectional dimension near torsion spring 4 side is 4mm × 10mm, stretches out two symmetrical connectors with holes and is connected with adapter shaft 3; Half cycle sectional dimension is 2mm × 10mm in addition, and middle part radial direction has circular hole and is connected with the priming system compressing release gear 6.
Base plate 1, bearing 2, adapter shaft 3 and torsion spring 4 be composition torsion spring hinge component jointly, envelope size 123mm × 32mm × 22mm; Base plate 1 is connected with lander housing, provides installation and supporting plane; Torsion spring 4 to be placed on adapter shaft 3 and to snap in groove reserved on centering ring 5 connector, provides the moment of torsion needed for attitude righting; Bearing 2 is in order to support adapter shaft 3 and to provide revolution space.
Compress release gear 6 to be made up of small-sized priming system (pin drift) and adapter, envelope is of a size of 50mm × 30mm × 49mm, be connected with lander housing by bolt, and priming system operating bar is stretched in the circular hole of centering ring 5 one end and realize substrate hold-down function, draw back operating bar by priming system start when needing and realize release function.
As shown in Figure 3, attitude erection device is made up of base plate 1, bearing 2, adapter shaft 3, torsion spring 4, centering ring 5 and compression release gear 6.
As shown in Figure 3, torsion spring hinge component carries out bolt by base plate 1 with lander housing end face and is connected, and by the connector nested encryptions of adapter shaft 3 with centering ring 5, outside torsion spring 4 two ends, pin embeds in the draw-in groove of centering ring 5 connector simultaneously; Centering ring 5 is connected with the operating bar compressing release gear 6 by radial circular hole; Compress release gear 6 to be connected with lander housing end face by bolt.
The installation process of this attitude erection device is as follows:
Step one: torsion spring 4, centering ring 5 connector and bearing 2 are successively placed on adapter shaft 3, and bearing 2 is secured by bolts on base plate 1, and base plate 1 is secured by bolts in lander housing end face;
Step 2: torsion spring 4 two ends are stretched out pin and embedded in the reserved groove of centering ring 5 connector, and centering ring 5 is depressed into compacted position;
Step 3: compress the radial circular hole of release gear 6 operating bar through centering ring 5 one end, guarantee that operating bar and centering ring 5 are all parallel with lander end face, and be connected with lander housing end face by bolt.
Above specific embodiments of the invention are described.It is to be appreciated that the present invention is not limited to above-mentioned particular implementation, those skilled in the art can make various distortion or amendment within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (3)
1. the attitude erection device of a mars excurtion module, it is characterized in that, comprise base plate (1), bearing (2), adapter shaft (3), torsion spring (4), centering ring (5) and compress release gear (6), wherein, torsion spring (4) is placed on adapter shaft (3) and goes up and snap in groove reserved on the connector of centering ring (5), provides the moment of torsion needed for attitude righting; Be connected to the bearing (2) supporting adapter shaft (3) of base plate (1), and revolution space is provided; Compress release gear (6) and comprise priming system, the operating bar of priming system stretches in the circular hole of centering ring (5) one end radial direction and realizes substrate hold-down function;
Centering ring (5) external diameter is 358mm, and the half cycle sectional dimension near torsion spring (4) side is 4mm × 10mm, symmetrical two connectors with holes in middle part; Half cycle sectional dimension is 2mm × 10mm in addition, and middle part radial direction has circular hole.
2. one kind has the mars excurtion module of the attitude erection device of mars excurtion module according to claim 1, it is characterized in that, comprise lander, base plate (1), bearing (2), adapter shaft (3), torsion spring (4), centering ring (5) and compress release gear (6), wherein, torsion spring (4) is placed on adapter shaft (3) and goes up and snap in groove reserved on the connector of centering ring (5), provides the moment of torsion needed for attitude righting; Be connected to the bearing (2) supporting adapter shaft (3) of base plate (1), and revolution space is provided; Compress release gear (6) and comprise priming system, the operating bar of priming system stretches in the circular hole of centering ring (5) one end radial direction and realizes substrate hold-down function; Base plate (1) carries out bolt with lander housing end face and is connected; Compress release gear (6) to be connected with lander housing end face by bolt; Operating bar is all parallel with lander end face with centering ring (5).
3. an installation method for the attitude erection device of mars excurtion module according to claim 1, is characterized in that, comprise the steps:
Step 1: torsion spring (4), centering ring (5) connector and bearing (2) are successively placed on adapter shaft (3), bearing (2) is secured by bolts on base plate (1), and base plate (1) is secured by bolts in lander housing end face;
Step 2: torsion spring (4) two ends are stretched out pin and embedded in the reserved groove of centering ring (5) connector, and centering ring (5) is depressed into compacted position;
Step 3: the radial circular hole of operating bar through centering ring (5) one end compressing release gear (6), is guaranteed that operating bar is all parallel with lander end face with centering ring (5), and is connected with lander housing end face by bolt.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310145555.0A CN103274062B (en) | 2013-04-24 | 2013-04-24 | A kind of attitude erection device of mars excurtion module |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310145555.0A CN103274062B (en) | 2013-04-24 | 2013-04-24 | A kind of attitude erection device of mars excurtion module |
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| CN103274062A CN103274062A (en) | 2013-09-04 |
| CN103274062B true CN103274062B (en) | 2016-04-20 |
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Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1663885A (en) * | 2005-04-15 | 2005-09-07 | 大连轻工业学院 | Loading method of star landing vehicle and equipment for landing |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7913953B2 (en) * | 2005-12-28 | 2011-03-29 | Frank Werner Ellinghaus | Solar sail launch system and solar sail attitude control system |
| FR2943318B1 (en) * | 2009-03-17 | 2011-05-20 | Astrium Sas | SPATIAL SENSOR INTERLASTING DEVICE AND METHOD OF LANDING A PROBE PROVIDED WITH SUCH A DEVICE |
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2013
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Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1663885A (en) * | 2005-04-15 | 2005-09-07 | 大连轻工业学院 | Loading method of star landing vehicle and equipment for landing |
Non-Patent Citations (3)
| Title |
|---|
| 气囊式火星软着陆探测器结构机构技术初探;恽卫东等;《中国宇航学会深空探测技术专业委员会第七届学术年会论文集》;20101231;对比文件全文，特别是第266-267页，3.1-3.3节部分,图6-7 * |
| 火星着陆器扶正展开策略研究;王永滨;《中国宇航学会深空探测技术专业委员会第七届学术年会》;20101231;全文 * |
| 火星着陆舱扶正展开技术方案研究;丁弘等;《中国宇航学会深空探测技术专业委员会第六届学术年会暨863计划"深空探测与空间实验技术"重大项目学术研讨会论文集》;20091231;全文 * |
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| CN103274062A (en) | 2013-09-04 |
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