CN102437404B - Integrated structure of rigidized inflatable deployable truss type planar antenna and solar array - Google Patents
Integrated structure of rigidized inflatable deployable truss type planar antenna and solar array Download PDFInfo
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- CN102437404B CN102437404B CN201110237789.9A CN201110237789A CN102437404B CN 102437404 B CN102437404 B CN 102437404B CN 201110237789 A CN201110237789 A CN 201110237789A CN 102437404 B CN102437404 B CN 102437404B
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- windsurfing
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- 239000000758 substrate Substances 0.000 claims abstract description 13
- 238000005273 aeration Methods 0.000 claims description 36
- 229910000831 Steel Inorganic materials 0.000 claims description 10
- 239000010959 steel Substances 0.000 claims description 10
- 239000002131 composite material Substances 0.000 claims description 6
- 230000015572 biosynthetic process Effects 0.000 claims description 3
- RKTYLMNFRDHKIL-UHFFFAOYSA-N copper;5,10,15,20-tetraphenylporphyrin-22,24-diide Chemical compound [Cu+2].C1=CC(C(=C2C=CC([N-]2)=C(C=2C=CC=CC=2)C=2C=CC(N=2)=C(C=2C=CC=CC=2)C2=CC=C3[N-]2)C=2C=CC=CC=2)=NC1=C3C1=CC=CC=C1 RKTYLMNFRDHKIL-UHFFFAOYSA-N 0.000 claims description 3
- 230000007613 environmental effect Effects 0.000 claims description 3
- 238000010438 heat treatment Methods 0.000 claims description 3
- 229920006254 polymer film Polymers 0.000 claims description 3
- 230000035945 sensitivity Effects 0.000 abstract description 6
- 238000005516 engineering process Methods 0.000 abstract description 4
- 230000009286 beneficial effect Effects 0.000 abstract description 3
- 238000003491 array Methods 0.000 abstract 2
- 239000000203 mixture Substances 0.000 description 10
- 230000015556 catabolic process Effects 0.000 description 4
- 238000010276 construction Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 239000004429 Calibre Substances 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 229920001187 thermosetting polymer Polymers 0.000 description 1
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/50—Photovoltaic [PV] energy
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Abstract
The invention provides an integrated structure of a rigidized inflatable deployable truss type planar antenna and a solar array. A substrate of the solar array provided by the invention is arranged at the upper side of a truss structure; a solar cell slice is fixed on the upper surface of the solar array; a planar antenna module is arranged at the lower side of the truss structure to form the planar antenna; and a satellite or a space station is arranged at the middle part or the end part of the truss structure. In the invention, a rigidized inflatable deployable truss is used as the main body of the integrated structure; the truss can be flexibly folded during launching, is high in folding efficiency, small in launching volume and convenient for the traditional launching technology and launching equipment to launch large-aperture antennae and large-area solar arrays; after the launched large-aperture antennae and large-area solar arrays enter tracks, the integrated structure is unfolded and rigidized, is higher in structural rigidity and fundamental vibrational frequency and is beneficial to the posture control and the stable running on tracks of aircrafts such as the satellite and the like, the remarkable improvement of anti-vibration performance of the planar antenna and the improvement of precision and sensitivity of signals.
Description
Technical field
The present invention relates to a kind of can steel charge expansion truss-like flat plane antenna and solar array integral mechanism.
Background technology
Flat plane antenna and solar array (solar array or the sun wing) application in the aircraft such as satellite, manned spaceship, space station is very extensive, flat plane antenna is used for satellite-borne synthetic aperture radar as signal transmitting and receiving parts, solar array is used for the spacecrafts such as satellite as supply of electric power parts, but aircraft uses at present flat plane antenna or solar array are all mechanical type deployed configuration, and are to be arranged separately on aircraft.
Existing expansion solar array mainly adopts mechanical type to launch supporting construction, this launches supporting construction is to be formed by connecting by bindiny mechanism, control development mechanism and retaining mechanism by a lot of rigid members, in use there is the problems such as complex structure, easy break-down, expansion poor reliability, overall weight weigh, folding efficiency is low, transmitting volume is large, for the solar array that adopts large-area plane framework formula deployed configuration, also have that the rigidity of structure is low, fundamental vibration frequency is low, easily cause with aircraft body resonance and cause attitude of flight vehicle to control more difficult problem.
Existing flat plane antenna mainly adopts mechanical type deployed configuration, this kind launch supporting construction be by a lot of rigid members by bindiny mechanism, control development mechanism and retaining mechanism is formed by connecting, thereby in use there is equally complex structure, easy break-down, expansion poor reliability, the problem such as overall weight is heavy, folding efficiency is low, transmitting volume is large.Precision and the sensitivity of the aircraft signal receptions such as flat plane antenna bore (or effective area) size is larger on precision and the sensitivity impact of the aircraft signal receptions such as satellite or transmitting, and flat plane antenna bore is larger, satellite or transmitting are just higher.And bigbore mechanical type expansion flat plane antenna also exists the problem that the rigidity of structure is low, fundamental vibration frequency is low, easily cause cause attitude of flight vehicle is controlled to more difficult problem with aircraft body resonance, and cause degradation problem under flat plane antenna signal accuracy.
In sum, the flat plane antenna that existing mechanical type launches, installs separately can not meet the demand of aircraft to heavy-calibre planar antenna, and the solar array that existing mechanical type launches, installs separately can not meet the demand of aircraft to large area solar array.
Summary of the invention
The object of the invention is to launch flat plane antenna and in using separately, have complex structure, easy break-down, expansion poor reliability, overall weight is heavy, folding efficiency is low, transmitting volume is large and cost is high problem for solving existing mechanical type deploying solar windsurfing and existing mechanical type; Solve because adopting large-area planar frame-type deployed configuration to exist the rigidity of structure and fundamental frequency to increase and reduce with physical dimension simultaneously, easily cause resonate with aircraft body and cause attitude of flight vehicle to be controlled more difficult, and the problem that causes flat plane antenna signal accuracy to decline, and then provide a kind of can steel charge expansion truss-like flat plane antenna and solar array integral mechanism.
The present invention includes: solar array support, stay pipe, flat plane antenna support, flat plane antenna module, solar array substrate, solar battery sheet and satellite or space station, between solar array support and flat plane antenna support, being connected with stay pipe formation cross section is tetragonal truss structure, solar array substrate is arranged on the upper side of truss structure, solar battery sheet is fixed on the upper surface of solar array substrate, the downside that flat plane antenna module is arranged on truss structure forms flat plane antenna, and satellite or space station are arranged on middle part or the end of truss structure; Described solar array support comprises: two longitudinal gas-filled tubes of windsurfing and windsurfing horizontal aeration pipe, between two longitudinal gas-filled tubes of windsurfing, be connected with windsurfing horizontal aeration pipe, between the longitudinal gas-filled tube of windsurfing and windsurfing horizontal aeration pipe, be interconnected, in each unit that longitudinal gas-filled tube and windsurfing horizontal aeration pipe form by windsurfing, be provided with a solar array substrate; Described flat plane antenna support comprises: two longitudinal gas-filled tubes of antenna and antenna horizontal aeration pipe, between two longitudinal gas-filled tubes of antenna, be connected with antenna horizontal aeration pipe, between the longitudinal gas-filled tube of antenna and antenna horizontal aeration pipe, be interconnected, in each unit that longitudinal gas-filled tube and antenna horizontal aeration pipe form by antenna, be provided with a flat plane antenna module; One end of described stay pipe is connected with the longitudinal gas-filled tube of windsurfing, and the other end of stay pipe is connected with the longitudinal gas-filled tube of antenna; The tube wall of described stay pipe, the longitudinal gas-filled tube of windsurfing, windsurfing horizontal aeration pipe, the longitudinal gas-filled tube of antenna and antenna horizontal aeration pipe is made by gas-barrier layer, zone of heating, firmization layer, adiabatic overcoat and environmental protection ply respectively from the inside to the outside successively; Described gas-barrier layer is made by thin polymer film, and the thickness of gas-barrier layer is 0.01～0.1mm.
During transmitting, whole truss-like flat plane antenna and solar array integral mechanism FOLD AND PACK are inner at carrying case, after transmitting is entered the orbit, integral mechanism is inflating expanded and just changed into type, thereby be shaped to in-orbit the truss-like integral mechanism of heavy-calibre planar antenna and large area solar array, integral mechanism launches to be molded over the one or both sides of aircraft.
Beneficial effect of the present invention:
One, the present invention adopt can steel charge expansion truss as the main structure body of solar array and flat plane antenna, inflating expanded truss adopts can just change flexible composite structure, can fold flexibly, folding efficiency is high, transmitting volume is little, is convenient to utilize existing lift-off technology and launch installation to carry out the transmitting of large aperture antenna and large area solar array.
Two, the present invention is simple in structure, does not contain mechanical joint or hinge, does not need retaining mechanism, with the blowing pressure, drives and launches, and launches reliability high, is conducive to total reliable expansion in-orbit and has just changed into type.
Three, this can steel charge expansion antenna and solar array integrated mechanism have advantages of that folding volume is little, quality is light, than existing mechanical type development mechanism, there is the advantage in a lot of engineerings, can build more bigbore flat plane antenna and more large-area solar array, significantly improve the generated output of sensitivity, precision and the solar array of flat plane antenna.
Four, after integral mechanism launches in-orbit and has just changed, flat plane antenna and solar array link into an integrated entity by the truss structure after firmization, significantly improve the rigidity of structure and the fundamental vibration frequency of total, the attitude that is conducive to the aircraft such as satellite is controlled and stable operation in-orbit, and significantly improve the vibration resistance of flat plane antenna, improve signal accuracy and sensitivity.
Five, seldom, and the flexible composite stay pipe that builds the thin-walled of truss structure has further reduced material usage to the material usage of truss structure own, thereby total weight alleviates greatly, is conducive to the transmitting of whole aircraft.
Six, the present invention is by flat plane antenna and solar array integrative installation technology, simplified aircraft accessory structure, reduced antenna and windsurfing to the taking of aircraft exterior space, be beneficial to the raising of total reliability, and be conducive to aircraft exterior more other annexes or load are installed.
Accompanying drawing explanation
Fig. 1 is the overall structure schematic diagram that the specific embodiment of the present invention provides;
Fig. 2 is the structural representation of solar array;
Fig. 3 is the structural representation of flat plane antenna;
Fig. 4 is that the A of Fig. 1 is to view;
Fig. 5 is the B place enlarged drawing of Fig. 1;
Fig. 6 is the C place enlarged drawing of Fig. 2;
Fig. 7 is the D place enlarged drawing of Fig. 3;
Fig. 8 is perspective view of the present invention.
Embodiment
Embodiment one: see Fig. 1, Fig. 4 and Fig. 8, present embodiment comprises: solar array support 1, stay pipe 2, flat plane antenna support 3, flat plane antenna module 4, solar array substrate 8, solar battery sheet 9 and satellite or space station 10, between solar array support 1 and flat plane antenna support 3, being connected with stay pipe 2 formation cross sections is tetragonal truss structure, solar array substrate 8 be arranged on truss structure above, solar battery sheet 9 be fixed on solar array substrate 8 above, what flat plane antenna module 4 was arranged on truss structure forms below flat plane antenna, satellite or space station 10 are arranged on middle part or the end of truss structure.The present invention is admitted to after space track and inflating expanded firmization, and solar array to day, flat plane antenna over the ground.
Embodiment two: see Fig. 2, solar array support 1 described in present embodiment comprises: two longitudinal gas-filled tube 1-1 of windsurfing and windsurfing horizontal aeration pipe 1-2, between two longitudinal gas-filled tube 1-1 of windsurfing, be connected with windsurfing horizontal aeration pipe 1-2, between the longitudinal gas-filled tube 1-1 of windsurfing and windsurfing horizontal aeration pipe 1-2, be interconnected, in each unit that longitudinal gas-filled tube 1-1 and windsurfing horizontal aeration pipe 1-2 form by windsurfing, be provided with a solar array substrate 8.Other composition and annexation are identical with embodiment one.
Embodiment three: see Fig. 3, flat plane antenna support 3 described in present embodiment comprises: two longitudinal gas-filled tube 3-1 of antenna and antenna horizontal aeration pipe 3-2, between two longitudinal gas-filled tube 3-1 of antenna, be connected with antenna horizontal aeration pipe 3-2, between the longitudinal gas-filled tube 3-1 of antenna and antenna horizontal aeration pipe 3-2, be interconnected, in each unit that longitudinal gas-filled tube 3-1 and antenna horizontal aeration pipe 3-2 form by antenna, be provided with a flat plane antenna module 4.Other composition and annexation are identical with embodiment one.
Embodiment four: see Fig. 2 and Fig. 6, present embodiment also comprises windsurfing connector 6, described windsurfing connector 6 is arranged on the junction between the longitudinal gas-filled tube 1-1 of windsurfing and windsurfing horizontal aeration pipe 1-2.Windsurfing connector 6 can be used for increasing the bonding strength between the longitudinal gas-filled tube 1-1 of windsurfing and windsurfing horizontal aeration pipe 1-2.Other composition and annexation are identical with embodiment two.
Embodiment five: see Fig. 3 and Fig. 7, present embodiment also comprises antenna connection 7, described antenna connection 7 is arranged on the junction between the longitudinal gas-filled tube 3-1 of antenna and antenna horizontal aeration pipe 3-2.Antenna connection 7 can be used for increasing the bonding strength between the longitudinal gas-filled tube 3-1 of antenna and antenna horizontal aeration pipe 3-2.Other composition and annexation are identical with embodiment three.
Embodiment six: see Fig. 1 and Fig. 5, one end of stay pipe 2 is connected with the longitudinal gas-filled tube 1-1 of windsurfing described in present embodiment, and the other end of stay pipe 2 is connected with the longitudinal gas-filled tube 3-1 of antenna.Other composition and annexation are identical with embodiment one, two or three.
Embodiment seven: see Fig. 1 and Fig. 5, present embodiment also comprises stay pipe connector 5, and described stay pipe connector 5 is arranged on junction between stay pipe 2 and the longitudinal gas-filled tube 1-1 of windsurfing and the junction between stay pipe 2 and the longitudinal gas-filled tube 3-1 of antenna.The effect of stay pipe connector 5 is the bonding strengths in order to increase between the longitudinal gas-filled tube 1-1 of stay pipe 2 and windsurfing, between stay pipe 2 and the longitudinal gas-filled tube 3-1 of antenna.Other composition and annexation are identical with embodiment six.
Embodiment eight: the tube wall of the stay pipe 2 described in present embodiment, the longitudinal gas-filled tube 1-1 of windsurfing, windsurfing horizontal aeration pipe 1-2, the longitudinal gas-filled tube 3-1 of antenna and antenna horizontal aeration pipe 3-2 is made by gas-barrier layer, zone of heating, thermoset layer, adiabatic overcoat and environmental protection ply respectively from the inside to the outside successively.Because stay pipe, gas-filled tube are to consist of plural layers composite material, the performance index such as stay pipe bending rigidity, intensity can design by changing the methods such as diameter, length, pipe thickness and material property of stay pipe.Other composition and annexation are identical with embodiment one, two or three.
Embodiment nine: the gas-barrier layer described in present embodiment is made by thin polymer film, the thickness of gas-barrier layer is 0.01～0.1mm, when tube wall requirement is thinner, adopts this parameter.Other composition and annexation are identical with embodiment eight.
Embodiment ten: the firmization layer described in present embodiment is made by can just changing flexible composite, can guarantee stay pipe, the needed strength and stiffness of gas-filled tube after firmization.Other composition and annexation are identical with embodiment eight.
Embodiment 11: the firmization layer described in present embodiment is made by can just changing flexible composite.Before being characterized in firmization, pliability is good, has very high strength and stiffness after firmization.Other composition and annexation are identical with embodiment eight.
Embodiment 12: present embodiment is provided with control valve on gas ducting, can control gas flow and flow velocity that gas ducting is filled into stay pipe, gas-filled tube inside, makes the inflating expanded process of framework comparatively stable.
Because precision and the sensitivity of the aircraft signals such as the size of flat plane antenna is larger, satellite reception or transmitting are just higher; And the effect of solar array is to provide electric power safeguard for aircraft such as satellites, so the size of solar array is larger, and the electric power providing for aircraft such as satellites is just more sufficient.Volume after flat plane antenna of the present invention and solar array are inflating expanded can reach launch tens times of front volume, more than tens times or hundred times.
Claims (5)
- One kind can steel charge expansion truss-like flat plane antenna and solar array integral mechanism, it is characterized in that, comprise: solar array support (1), stay pipe (2), flat plane antenna support (3), flat plane antenna module (4), solar array substrate (8), solar battery sheet (9) and satellite or space station (10), between solar array support (1) and flat plane antenna support (3), being connected with stay pipe (2) formation cross section is tetragonal truss structure, solar array substrate (8) is arranged on the upper side of truss structure, solar battery sheet (9) is fixed on the upper surface of solar array substrate (8), the downside that flat plane antenna module (4) is arranged on truss structure forms flat plane antenna, satellite or space station (10) are arranged on middle part or the end of truss structure, described solar array support (1) comprising: two longitudinal gas-filled tubes of windsurfing (1-1) and windsurfing horizontal aeration pipe (1-2), between two longitudinal gas-filled tubes of windsurfing (1-1), be connected with windsurfing horizontal aeration pipe (1-2), between the longitudinal gas-filled tube of windsurfing (1-1) and windsurfing horizontal aeration pipe (1-2), be interconnected, in each unit that longitudinal gas-filled tube (1-1) and windsurfing horizontal aeration pipe (1-2) form by windsurfing, be provided with a solar array substrate (8), described flat plane antenna support (3) comprising: two longitudinal gas-filled tubes of antenna (3-1) and antenna horizontal aeration pipe (3-2), between two longitudinal gas-filled tubes of antenna (3-1), be connected with antenna horizontal aeration pipe (3-2), between the longitudinal gas-filled tube of antenna (3-1) and antenna horizontal aeration pipe (3-2), be interconnected, in each unit that longitudinal gas-filled tube (3-1) and antenna horizontal aeration pipe (3-2) form by antenna, be provided with a flat plane antenna module (4), one end of described stay pipe (2) is connected with the longitudinal gas-filled tube of windsurfing (1-1), and the other end of stay pipe (2) is connected with the longitudinal gas-filled tube of antenna (3-1), the tube wall of described stay pipe (2), the longitudinal gas-filled tube of windsurfing (1-1), windsurfing horizontal aeration pipe (1-2), the longitudinal gas-filled tube of antenna (3-1) and antenna horizontal aeration pipe (3-2) is made by gas-barrier layer, zone of heating, firmization layer, adiabatic overcoat and environmental protection ply respectively from the inside to the outside successively, described gas-barrier layer is made by thin polymer film, and the thickness of gas-barrier layer is 0.01～0.1mm.
- 2. according to claim 1 can steel charge expansion truss-like flat plane antenna and solar array integral mechanism, it is characterized in that, also comprise windsurfing connector (6), described windsurfing connector (6) is arranged on the junction between the longitudinal gas-filled tube of windsurfing (1-1) and windsurfing horizontal aeration pipe (1-2).
- 3. according to claim 2 can steel charge expansion truss-like flat plane antenna and solar array integral mechanism, it is characterized in that, also comprise antenna connection (7), described antenna connection (7) is arranged on the junction between the longitudinal gas-filled tube of antenna (3-1) and antenna horizontal aeration pipe (3-2).
- 4. according to claim 3 can steel charge expansion truss-like flat plane antenna and solar array integral mechanism, it is characterized in that, also comprise stay pipe connector (5), described stay pipe connector (5) is arranged on junction between stay pipe (2) and the longitudinal gas-filled tube of windsurfing (1-1) and the junction between stay pipe (2) and the longitudinal gas-filled tube of antenna (3-1).
- 5. according to claim 1 can steel charge expansion truss-like flat plane antenna and solar array integral mechanism, it is characterized in that, described firmization layer is made by can just changing flexible composite.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110237789.9A CN102437404B (en) | 2011-08-18 | 2011-08-18 | Integrated structure of rigidized inflatable deployable truss type planar antenna and solar array |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110237789.9A CN102437404B (en) | 2011-08-18 | 2011-08-18 | Integrated structure of rigidized inflatable deployable truss type planar antenna and solar array |
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| CN102437404A CN102437404A (en) | 2012-05-02 |
| CN102437404B true CN102437404B (en) | 2014-02-12 |
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| CN201110237789.9A Expired - Fee Related CN102437404B (en) | 2011-08-18 | 2011-08-18 | Integrated structure of rigidized inflatable deployable truss type planar antenna and solar array |
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| CN103786903A (en) * | 2012-10-26 | 2014-05-14 | 中国科学院物理研究所 | Solar sail for spacecraft |
| CN103236804B (en) * | 2013-04-27 | 2015-04-22 | 中国空间技术研究院 | Spherical inflatable space solar power station |
| CN103682668B (en) * | 2013-12-18 | 2015-06-17 | 哈尔滨工业大学 | Bending-forming-based parabolic cylinder antenna reflector and method for reflector to achieve parabolic cylinder |
| CN104410349B (en) * | 2014-12-15 | 2017-05-24 | 辽宁矽钛照临能源有限公司 | Intelligent sail type over-water floating solar power station |
| CN106025488B (en) * | 2016-05-28 | 2019-02-22 | 上海大学 | A kind of two-dimensional flat plate antenna expanding unit |
| CN106654505B (en) * | 2016-12-24 | 2019-02-12 | 哈尔滨工业大学 | Inflatable drives the modularization flat plane antenna being orderly unfolded |
| CN106654504B (en) * | 2016-12-24 | 2019-04-09 | 哈尔滨工业大学 | A kind of modularization flat plane antenna |
| CN107134656A (en) * | 2017-05-11 | 2017-09-05 | 哈尔滨工业大学 | A kind of foldable expansion putamina antenna reflective face and its design method based on the hard and soft conversion of configuration |
| CN107416231B (en) * | 2017-06-28 | 2019-11-08 | 合肥凯石投资咨询有限公司 | Pneumatic-control type thin film solar windsurfing and its accommodation method |
| CN107618679B (en) * | 2017-08-07 | 2019-07-12 | 中国空间技术研究院 | A kind of high storage ratio expansion supporting mechanism |
| CN111056047B (en) * | 2018-10-17 | 2021-07-30 | 哈尔滨工业大学 | Truss type foldable and unfoldable space capsule based on shape memory polymer composite material |
| CN109210285B (en) * | 2018-10-24 | 2023-06-30 | 上海海事大学 | Novel bionic expandable structure and expansion method |
| CN109515753A (en) * | 2018-12-07 | 2019-03-26 | 上海宇航系统工程研究所 | A kind of load plate expansion module of spacecraft |
| CN109713420B (en) * | 2018-12-29 | 2020-07-17 | 长沙天仪空间科技研究院有限公司 | Inflatable antenna with expandable space |
| CN110112533B (en) * | 2019-06-05 | 2021-08-03 | 哈尔滨工业大学 | Rigid-flexible combined supported inflatable unfolding type Z-shaped folding array antenna |
| CN111509358B (en) * | 2020-04-30 | 2021-05-18 | 燕山大学 | Single-degree-of-freedom panel antenna folding and unfolding unit and panel antenna folding and unfolding mechanism |
| CN112849436B (en) * | 2021-02-25 | 2023-02-03 | 北京卫星制造厂有限公司 | Carbon fiber composite material truss rib and preparation method thereof |
| CN113914474B (en) * | 2021-09-26 | 2023-11-10 | 国核电力规划设计研究院有限公司 | Suspension cable truss structure system |
| CN114348300A (en) * | 2022-01-11 | 2022-04-15 | 沈阳航天新光集团有限公司 | Automatic retractable sun wing unfolding device |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6394395B1 (en) * | 2000-03-15 | 2002-05-28 | Lockheed Martin Corporation | Combination solar array assembly and antenna for a satellite |
| AU2000263338A1 (en) * | 2000-03-23 | 2001-10-03 | Ilc Dover, Inc. | Deployable space frame and method of deployment therefor |
| CN100362693C (en) * | 2005-09-26 | 2008-01-16 | 哈尔滨工业大学 | Plane framework supporting structure capable of steel charge expansion |
| CN100345728C (en) * | 2005-10-21 | 2007-10-31 | 哈尔滨工业大学 | Truss type rigidifying solar energy cell array of inflatable expansion |
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- 2011-08-18 CN CN201110237789.9A patent/CN102437404B/en not_active Expired - Fee Related
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Effective date of registration: 20221114 Address after: 100000 302, Floor 3, No. 8, Anningzhuang East Road, Haidian District, Beijing Patentee after: Beijing Qihe Jingwei Innovation Technology Co.,Ltd. Address before: 150001 No. 92 West straight street, Nangang District, Heilongjiang, Harbin Patentee before: HARBIN INSTITUTE OF TECHNOLOGY |
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