CN102518922B - Space remote sensor support frame made of carbon fiber composite - Google Patents
Space remote sensor support frame made of carbon fiber composite Download PDFInfo
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- CN102518922B CN102518922B CN 201110410379 CN201110410379A CN102518922B CN 102518922 B CN102518922 B CN 102518922B CN 201110410379 CN201110410379 CN 201110410379 CN 201110410379 A CN201110410379 A CN 201110410379A CN 102518922 B CN102518922 B CN 102518922B
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Abstract
The invention relates to a space remote sensor support frame made of carbon fiber composite, comprising a horizontal lifting ring, a remote sensor support frame body and a vertical lifting ring. The remote sensor support frame body is formed into a three-dimensional grid-like structure by a closed shell, internally peripherally radiating reinforcing ribs and axially parallel reinforcing ribs. The shape of the inner side wall of the shell corresponds to the shape of a space remote sensor; the outer side wall of the shell comprises an circular-arc shaped plate, a left vertical plate, a right vertical plate, a front plate, a rear plate and a bottom plate; the left vertical plate is connected with the bottom plate through a left horizontal plate and a left inclined plate; the right vertical plate is connected with the bottom plate through a right horizontal plate and a right inclined plate; the space remote sensor is fixedly connected with a round flange of the remote sensor support frame body; and the horizontal lifting ring and the vertical lifting ring are connected with the remote sensor support frame body through pre-buried components. The space remote sensor support frame made of carbon fiber composite has a light weight, high structural strength and high lightweight rate and can be applied to the space remote sensing field and the rocket, aviation and machinery industries.
Description
Technical field
The invention belongs to the space remote sensing applied technical field, relate to the high strength Space Remote Sensors support frame structure that a kind of carbon fiber composite is made.
Background technique
Space Remote Sensors is used for the earth and space resources is generally investigated and detailed survey, has important science and military significance in the application in fields such as observation, deep space probing over the ground.In order to improve the resolution of Space Remote Sensors, need to increase the remote sensor bore to absorb more energy.Yet, be limited to carrying capacity and the launch cost of rocket, require the spacecraft structure spare must be light as far as possible under the situation of proof strength, also must adapt to complicated abominable space environment simultaneously.As present performance one of elite clone the most, carbon fiber composite is more and more adopted on space structure spare with its excellent properties at aspects such as specific strength, specific stiffness, high temperature resistant, anticorrosive, moldabilities.
Compare with other space flight common used materials, carbon fiber composite itself and structure thereof have its unique characteristics.Table 1 has been listed the performance parameter of several space flight common materials.
Table 1 is used the space material performance always
As shown in Table 1, the most typical characteristics of carbon fiber composite are exactly that density is little, intensity and Young's modulus height.The density of carbon fiber composite is 0.23～1 times (pressing carbon fiber T700 calculates) of other four kinds of metallic material density.In general, under the situation of proof strength, adopt carbon fiber composite as the structural member material architecture quality is alleviated about 30%～40%.
Summary of the invention
The technical problem to be solved in the present invention provides a kind of weight reduction rate height, and in light weight, the carbon fiber composite Space Remote Sensors supporting frame that structural strength is high of good stability are installed.
In order to solve the problems of the technologies described above, carbon fiber composite Space Remote Sensors supporting frame of the present invention comprises remote sensor supporting frame main body, horizontal hoisting ring, vertical hoisting ring and embedded part; Described remote sensor supporting frame main body constitutes stereo grid shaped structure by the radial stiffening rib of housing, internal circumferential and the parallel to an axis stiffening rib of sealing; Embedded part is bonding to be embedded in the remote sensor supporting frame body shell in advance, and horizontal hoisting ring is fixed on the remote sensor supporting frame main body by embedded part with vertical hoisting ring.
Described horizontal hoisting ring comprises the first horizontal hoisting ring, the second horizontal hoisting ring, the 3rd horizontal hoisting ring, the 4th horizontal hoisting ring; Vertical hoisting ring comprises the first vertical hoisting ring, the second vertical hoisting ring, the 3rd vertical hoisting ring, the 4th vertical hoisting ring; Embedded part comprises first embedded part, second embedded part, the 3rd embedded part, the 4th embedded part, the 5th embedded part, the 6th embedded part, the 7th embedded part, the 8th embedded part, the 9th embedded part, the tenth embedded part; The madial wall of remote sensor supporting frame body shell is corresponding with the Space Remote Sensors shape, outer side wall is made of circular arc plate, left side vertical plate, right side vertical plate, front side plate, back side panel and base plate, and be connected with the left side swash plate by the left side level board between left side vertical plate and the base plate, be connected with the right side swash plate by the right side level board between right side vertical plate and the base plate; Space Remote Sensors is fixedlyed connected with remote sensor supporting frame main body by the attachment hole on the remote sensor supporting frame main body circular flange; In first embedded part, the bonding side level board of the tenth embedded part difference, second embedded part, the 7th embedded part be bonding being embedded in the level board of left side in advance respectively; The 3rd embedded part, the 4th embedded part is bonding is embedded in advance in the circular arc plate, and the first horizontal hoisting ring, the second horizontal hoisting ring are threaded with the 3rd embedded part, the 4th embedded part respectively; The 5th embedded part, the 6th embedded part be bonding circular arc plate and the front side plate connecting part of being embedded in advance respectively, the 3rd horizontal hoisting ring, first vertical hoisting ring and the 5th embedded part scyewed joint, the 4th horizontal hoisting ring, second vertical hoisting ring and the 6th embedded part scyewed joint; The 8th embedded part, the 9th embedded part is bonding is embedded in the base plate the 3rd vertical hoisting ring and the 8th embedded part scyewed joint, the 4th vertical hoisting ring and the 9th embedded part scyewed joint in advance; Remote sensor supporting frame main body is connected with airship with the tenth embedded part by first embedded part, the 7th embedded part, second embedded part.Be embedded in the right side in advance
Remote sensor supporting frame main body of the present invention is by carbon fiber composite one bonding forming, because arbitrarily moulding before carbon fiber composite solidifies, therefore use corresponding mould, utilize carbon fiber composite can realize the structural type of remote sensor supporting frame complexity.The sealing of remote sensor supporting frame main body outer surface, inside constitutes stereo grid shaped structure by circumferential many radial stiffening ribs with the parallel stiffening rib of axial many rows, can improve the intensity of remote sensor supporting frame, make the remote sensor supporting frame can bear high-intensity impact and oscillating load, can alleviate the weight of remote sensor supporting frame again.At the relatively poor shortcoming of processibility after the moulding of carbon fiber composite structure spare, the joining interface of remote sensor supporting frame main body and hoisting ring and vehicle to vehicle is realized by metal embedded part.Metal embedded part is embedded in the supporting frame when the moulding of remote sensor supporting frame in advance, is cured as one with carbon fiber composite, thereby realizes connecting of remote sensor supporting frame and other members.Described remote sensor supporting frame main body is connected with airship by the left and right sides level board of its underpart, has reduced the center of gravity of Space Remote Sensors, has improved the stability of Space Remote Sensors.The present invention is in light weight, structural strength is high, weight reduction rate is high, except being applied to the space remote sensing field, can also be applied in every profession and trades such as rocket, aviation, machinery.
Description of drawings:
Below in conjunction with the drawings and specific embodiments the present invention is described in further detail.
Fig. 1 is the stereogram of carbon fiber composite Space Remote Sensors supporting frame of the present invention.
Fig. 2 is carbon fiber composite Space Remote Sensors support frame structure plan view of the present invention.
Fig. 3 is carbon fiber composite Space Remote Sensors support frame structure A-A sectional view of the present invention.
Fig. 4 is carbon fiber composite Space Remote Sensors support frame structure B-B sectional view of the present invention.
Embodiment
As Fig. 1,2,3, shown in 4, carbon fiber composite Space Remote Sensors supporting frame of the present invention comprises first embedded part 1, second embedded part 2, the first horizontal hoisting ring 3, the 3rd embedded part 4, the 4th embedded part 5, the second horizontal hoisting ring 6, remote sensor supporting frame main body 7, the 3rd horizontal hoisting ring 8, the 5th embedded part 9, the first vertical hoisting ring 10, the second vertical hoisting ring 11, the 6th embedded part 12, the 4th horizontal hoisting ring 13, the 7th embedded part 14, the 8th embedded part 15, the 3rd vertical hoisting ring 16, the 4th vertical hoisting ring 17, the 9th embedded part 18, the tenth embedded part 19; Described remote sensor supporting frame main body 7 is that the epoxy resin-base material of TDE-85 and carbon fiber that model is T700 are made by model, and boundary dimension is long 900mm, wide 900mm, and thick 400mm, inner diameter of steel flue are Φ 750mm.Remote sensor supporting frame main body 7 constitutes stereo grid shaped structure by 16 radial stiffening ribs 23 of housing, internal circumferential and the parallel stiffening rib 24 of axial 2 rows of sealing.The madial wall 22 of housing is corresponding with the Space Remote Sensors shape, outer side wall is made of circular arc plate 31, left side vertical plate 32, right side vertical plate 33, front side plate 39, back side panel 40 and base plate 34, and be connected with left side swash plate 36 by left side level board 35 between left side vertical plate 32 and the base plate 34, be connected with right side swash plate 38 by right side level board 37 between right side vertical plate 33 and the base plate 34; Space Remote Sensors is fixedlyed connected with remote sensor supporting frame main body 7 by the attachment hole 25 on remote sensor supporting frame main body 7 circular flanges; First embedded part 1, the tenth embedded part 19 bonding being embedded in advance in the right side level board 37, second embedded part 2, the 7th embedded part 14 bonding being embedded in advance in the level board 35 of difference left side, described remote sensor supporting frame main body 7 is connected with airship with the tenth embedded part 19 by first embedded part 1, the 7th embedded part 14, second embedded part 2, reduce distance between tie point and the Space Remote Sensors center of gravity, reduced the center of gravity of Space Remote Sensors.The 3rd embedded part 4, the 4th embedded part 5 bonding being embedded in advance in the circular arc plate 31, the first horizontal hoisting ring 3, the second horizontal hoisting ring 6 are threaded with the 3rd embedded part 4, the 4th embedded part 5 respectively; The 5th embedded part 9, the 6th embedded part 12 be bonding circular arc plate 31 and front side plate 39 connecting parts of being embedded in advance respectively, the 3rd horizontal hoisting ring 8, the first vertical hoisting ring 10 and the 5th embedded part 9 are by scyewed joint, and the 4th horizontal hoisting ring 13, the second vertical hoisting ring 11 and the 6th embedded part 12 pass through scyewed joint; The 8th embedded part 15, the 9th embedded part 18 bonding being embedded in advance in the base plate 34, the 3rd vertical hoisting ring 16 and the 8th embedded part 15 are by scyewed joint, and the 4th vertical hoisting ring 17 and the 9th embedded part 18 pass through scyewed joint.First embedded part 1, second embedded part 2, the 7th embedded part 14 and the tenth embedded part 19 employing trades mark are that the titanium alloy material of TC4 is made, and boundary dimension is long 90mm, wide 80mm, high 60mm.The 3rd embedded part 4 and the 4th embedded part 5 employing trades mark are that the titanium alloy material of TC4 is made, and boundary dimension is long 50mm, wide 35mm, high 15mm.The 5th embedded part 9 and the 6th embedded part 12 employing trades mark are that the titanium alloy material of TC4 is made, and boundary dimension is long 50mm, wide 40mm, high 40mm.The 8th embedded part 15 and the 9th embedded part 18 employing trades mark are that the titanium alloy material of TC4 is made, and boundary dimension is long 40mm, wide 40mm, high 40mm.The first horizontal hoisting ring 3, the second horizontal hoisting ring 6, the 3rd horizontal hoisting ring 8, the 4th horizontal hoisting ring 13, the first vertical hoisting ring 10, the second vertical hoisting ring 11, the vertical hoisting ring 17 with the 4th of the 3rd vertical hoisting ring 16 are standard piece, the NBS code name is GB/T825-2000, and specification is M12 * 30mm.Can realize the level of remote sensor supporting frame and Space Remote Sensors is lifted by crane by the first horizontal hoisting ring 3, the second horizontal hoisting ring 6, the 3rd horizontal hoisting ring 8 and the 4th horizontal hoisting ring 13; Can realize the vertical lifting to remote sensor supporting frame and Space Remote Sensors by the first vertical hoisting ring 10, the second vertical hoisting ring 11, the vertical hoisting ring 17 with the 4th of the 3rd vertical hoisting ring 16.
Claims (1)
1. a carbon fiber composite Space Remote Sensors supporting frame is characterized in that comprising remote sensor supporting frame main body (7), horizontal hoisting ring, vertical hoisting ring and embedded part; Described remote sensor supporting frame main body (7) constitutes stereo grid shaped structure by the radial stiffening rib of housing, internal circumferential (23) and the parallel to an axis stiffening rib (24) of sealing; Embedded part is bonding to be embedded in remote sensor supporting frame main body (7) housing in advance, and horizontal hoisting ring is fixed on the remote sensor supporting frame main body (7) by embedded part with vertical hoisting ring; Described horizontal hoisting ring comprises the first horizontal hoisting ring (3), the second horizontal hoisting ring (6), the 3rd horizontal hoisting ring (8), the 4th horizontal hoisting ring (13); Vertical hoisting ring comprises the first vertical hoisting ring (10), the second vertical hoisting ring (11), the 3rd vertical hoisting ring (16), the 4th vertical hoisting ring (17); Embedded part comprises first embedded part (1), second embedded part (2), the 3rd embedded part (4), the 4th embedded part (5), the 5th embedded part (9), the 6th embedded part (12), the 7th embedded part (14), the 8th embedded part (15), the 9th embedded part (18), the tenth embedded part (19); The madial wall (22) of remote sensor supporting frame main body (7) housing is corresponding with the Space Remote Sensors shape, outer side wall is made of circular arc plate (31), left side vertical plate (32), right side vertical plate (33), front side plate (39), back side panel (40) and base plate (34), and be connected with left side swash plate (36) by left side level board (35) between left side vertical plate (32) and the base plate (34), be connected with right side swash plate (38) by right side level board (37) between right side vertical plate (33) and the base plate (34); Space Remote Sensors is fixedlyed connected with remote sensor supporting frame main body (7) by the attachment hole (25) on remote sensor supporting frame main body (7) circular flange; First embedded part (1), the tenth embedded part (19) be bonding being embedded in the right side level board (37) in advance respectively, and second embedded part (2), the 7th embedded part (14) be bonding being embedded in the left side level board (35) in advance respectively; The 3rd embedded part (4), the 4th embedded part (5) is bonding is embedded in advance in the circular arc plate (31), and the first horizontal hoisting ring (3), the second horizontal hoisting ring (6) are threaded with the 3rd embedded part (4), the 4th embedded part (5) respectively; The 5th embedded part (9), the 6th embedded part (12) be bonding circular arc plate (31) and front side plate (39) connecting part of being embedded in advance respectively, the 3rd horizontal hoisting ring (8), the first vertical hoisting ring (10) and the 5th embedded part (9) scyewed joint, the 4th horizontal hoisting ring (13), the second vertical hoisting ring (11) and the 6th embedded part (12) scyewed joint; The 8th embedded part (15), the 9th embedded part (18) is bonding is embedded in advance in the base plate (34), the 3rd vertical hoisting ring (16) and the 8th embedded part (15) scyewed joint, the 4th vertical hoisting ring (17) and the 9th embedded part (18) scyewed joint; Remote sensor supporting frame main body (7) is connected with airship with the tenth embedded part (19) by first embedded part (1), the 7th embedded part (14), second embedded part (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110410379 CN102518922B (en) | 2011-12-12 | 2011-12-12 | Space remote sensor support frame made of carbon fiber composite |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110410379 CN102518922B (en) | 2011-12-12 | 2011-12-12 | Space remote sensor support frame made of carbon fiber composite |
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| Publication Number | Publication Date |
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| CN102518922A CN102518922A (en) | 2012-06-27 |
| CN102518922B true CN102518922B (en) | 2013-07-03 |
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| CN 201110410379 Expired - Fee Related CN102518922B (en) | 2011-12-12 | 2011-12-12 | Space remote sensor support frame made of carbon fiber composite |
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Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103672320B (en) * | 2013-11-18 | 2015-10-21 | 北京空间机电研究所 | A kind of space flight optical remote sensor auxiliary support mechanism |
| CN104329783A (en) * | 2014-11-19 | 2015-02-04 | 重庆市金泽鑫科技有限公司 | Enhanced diversion fan cover |
| CN104536113B (en) * | 2014-12-30 | 2017-02-01 | 中国科学院长春光学精密机械与物理研究所 | High-specific stiffness supporting structure of space optical remote sensor |
| CN105805172B (en) * | 2014-12-31 | 2019-03-12 | 同方威视技术股份有限公司 | A kind of support frame for CT slip ring bearing |
| CN105203640A (en) * | 2015-09-18 | 2015-12-30 | 天津大学 | Embedded type acoustic emission sensing system |
| CN105181810A (en) * | 2015-09-18 | 2015-12-23 | 天津大学 | CFRP fixing support of acoustic emission sensor |
| CN111029965A (en) * | 2019-12-14 | 2020-04-17 | 武汉大云物移智科技有限公司 | Clamp for replacing insulator |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JPH08159381A (en) * | 1994-12-05 | 1996-06-21 | Minolta Co Ltd | Indicating direction turning device |
| CN2743875Y (en) * | 2004-10-28 | 2005-11-30 | 中国科学院长春光学精密机械与物理研究所 | Strucure of optical remote sensing camera frame |
| DE202007009966U1 (en) * | 2007-07-17 | 2007-09-20 | Leuze Lumiflex Gmbh + Co. Kg | Optical sensor |
| AT508562B1 (en) * | 2009-09-02 | 2011-02-15 | Riegl Laser Measurement Sys | 3-D MEASUREMENT DEVICE |
| KR20110131789A (en) * | 2010-05-31 | 2011-12-07 | 엘지이노텍 주식회사 | 3d laser range finder sensor |
| DE102010032723B3 (en) * | 2010-07-26 | 2011-11-24 | Faro Technologies, Inc. | Device for optically scanning and measuring an environment |
| CN102062637B (en) * | 2010-12-22 | 2013-08-21 | 中国科学院长春光学精密机械与物理研究所 | Support mechanism for multi-side cylindrical achromatic prism |
| CN102096172B (en) * | 2011-01-18 | 2012-07-25 | 中国科学院长春光学精密机械与物理研究所 | Back flexible supporting structure for reflecting mirror of space remote sensor |
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