CN101850852B - SPORT (Solar Polar Orbit Radio Telescope) clock scanning satellite - Google Patents
SPORT (Solar Polar Orbit Radio Telescope) clock scanning satellite Download PDFInfo
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- CN101850852B CN101850852B CN201010191529.8A CN201010191529A CN101850852B CN 101850852 B CN101850852 B CN 101850852B CN 201010191529 A CN201010191529 A CN 201010191529A CN 101850852 B CN101850852 B CN 101850852B
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Abstract
The invention relates to an SPORT (Solar Polar Orbit Radio Telescope) clock scanning satellite comprising a satellite body, a subsatellite, a stretching arm, a solar cell paddle, a butt-joint ring, a geosynchronous communication antenna and an orbit control engine. The SPORT clock scanning satellite is characterized in that the satellite body is in a cuboid shape and has a three-cabin internal structure; and the subsatellite concretely comprises a subsatellite body, a helical antenna, a reflecting plate, a reflecting plate support frame, a flexible solar paddle, a helical antenna unfolding guide mechanism, a guide unfolding drive motor, a speed reducer, an S wave-band digital antenna, a receiver and a power module. The SPORT clock scanning satellite adopts a main force-bearing structure which is a central force-bearing drum and a radial partition board force-transferring path, has a clear and concise force-transferring link, and is beneficial to the design of structure strength and rigidity through configuration distribution; the SPORT clock scanning satellite is provided with an orbit maneuver motor so as to transfer orbits per se when flying during a cruise phase, thereby reducing the requirements on a carrying upper stage; in addition, the SPORT clock scanning satellite ensures the stability of a better satellite attitude through the distribution position of a propelling module of the satellite body.
Description
Technical field
The invention belongs to the satellite configuration that sun SSO (Sun Synchronous Orbit) radio telescope plan (solar polar orbit radio telescope is called for short SPORT plan) proposes, be specially a kind of SPORT clock scan satellite.
Background technology
SPORT satellite is sun polar-orbiting satellite, main research coronal mass emission event and Propagation and evolution thereof, solar wind will be observed from sun surface to the communication process of the earth in sun SSO (Sun Synchronous Orbit), disclose the propagation law of solar wind at day ground interplanetary space, set up and revise interplanetary space weather physical model and forecasting model.For realizing this scientific goal, SPORT satellite is made up of a female star and 8 components, clock scan principle is used to carry out scientific exploration, 8 components are respectively and are fixed on 4 minute hands and 4 second hands, the requirement that the length of minute hand and second hand detects according to component load is different, and the revolution ratio of minute hand and second hand is: 12/11.Satellite adopts Direct to the sun spin stabilization gesture stability mode, 8 components are uniformly distributed along satellite hand of rotation, due to the demand of detection principle, female star and component will keep certain relative position relation and movement relation, by position that to be delivered to component with shaft-like framework type extension means away from female star.
The object of SPORT satellite configuration topological design and principle, the object of satellite configuration topological design is as the layout of capacity weight on star provides Visualization Platform, determine the position of capacity weight on star and direction, avoid the location conflicts between capacity weight and mutually block, observe the working space of capacity weight, tentatively determine the mode that scientific goal realizes, for the Scheme design of satellite platform provides design considerations.The principle of satellite configuration topological design is: adapt to carrier rocket requirement; Adapt to rail conditions; Meet capacity weight detection demand; Under the prerequisite meeting scientific goal realization, inherit ripe satellite structure platform configuration as far as possible; Meet the designing requirement that each subsystem proposes configuration and total arrangement; Configuration is conducive to the normal performance of equipment serviceability, and make between each equipment mechanical, electrical, heat compatible; Consider the convenience of general assembly; Consider the convenience of satellite test; Be considered as common platform, ensure that satellite has extendible load-carrying capacity and adjustable installation space.
The main technical matters that current SPORT satellite configuration topological design exists has: satellite belongs to long-life satellite, and the time is longer in orbit, and satellite platform is wanted to load a large amount of fuel; Satellite is three axis stabilized satellite, how to ensure period in orbit, along with the minimizing of fuel, keeps the stability of satellite; How to ensure that extending arm rod member and satellite attitude coupling response do not occur, extending arm and extending arm do not collide; How on satellite platform, to realize clock scan principle; When satellite moves in-orbit, the relative position between the earth, the sun, satellite three is at any time in change, and for ensureing the communication link with the earth, how communication antenna fixedly mounts over the ground; And under the restriction of delivery fairing envelope, how female star and component are designed.
Summary of the invention
The object of the invention is to, for meeting scientific exploration demand, thus providing a kind of SPORT clock scan satellite.
For achieving the above object, a kind of SPORT clock scan satellite provided by the invention, this satellite comprises: satellite body, component, extending arm, the solar cell wing, butt joint ring, over the ground communication antenna and precise tracking, it is characterized in that, described satellite body is cuboid, its inside is three cabin structures, specifically comprises: propulsion module, satellite equipment instrument compartment and payload module;
Described butt joint ring is positioned at bottom satellite, for being connected with carrier rocket by band;
Described communication antenna is over the ground connected with satellite body by a set of servomechanism, draws in and be locked on satellite side plate during transmitting, and after satellite enters transfer orbit, latching device release antenna launches;
Described extending arm comprises four second hand extending arms and four minute hand extending arms, and described second hand extending arm and minute hand extending arm are distributed in two planes vertical with the spin axis of satellite respectively; Described minute hand extending arm and satellite body are fixed, and rotate with satellite spin campaign; Described second hand extending arm carries a set of rotating mechanism, and relative minute hand extending arm can realize the demand of different rotating speeds; Maintain a certain distance between described second hand extending arm and minute hand extending arm into, can prevent second hand extending arm and minute hand extending arm from not colliding in end.
Described component is 8, the outside of the celestial body of this component is connected with described four minute hand extending arms or four second hand extending arms respectively with a face, and described be positioned at the rigid connecting rod that component on second hand extending arm and extending arm junction increase a fixed length, after launching for making each component be positioned on second hand extending arm with the component be positioned on minute hand extending arm at grade;
Described component specifically comprises: celestial body, helical antenna, reflecting plate, reflecting plate support, Flexible solar panel, helical antenna launch guiding mechanism, guiding expansion drive motor and retarder, S-band number passes antenna, receiver and power module; Described reflecting plate and described Flexible solar panel are fixed on described reflecting plate support; Described helical antenna is fixed at top with expansion guiding mechanism, and after helical antenna launches, guiding mechanism can limit rocking of helical antenna head;
Place S-band number outside described component celestial body bottom and pass antenna, top layer and described reflecting plate are by the Flange joint of hollow cylinder, and described guiding launches drive motor and retarder is fixed on this hollow cylinder inside.
Described reflecting plate is circular and with the aluminium foil of hollow out grid.
The diameter of described helical antenna is 0.640 meter, and height 2.5 meters after launching.
Described reflecting plate support outer rim end is provided with limiting stopper, launches to make described helical antenna be fixed on compressive state together with guiding mechanism with antenna.
The non-equipment attachment face of described component outside face is pasted with solar battery sheet, for the energize portions demand of component.
A Flexible solar panel that can fold is set below described reflecting plate, for ensureing the power demands of solar battery sheet to component.
Described second hand extending arm and minute hand extending arm are shaft-like framework type extending arm, and being connected through the hinge by some extending arm single-units forms; Described extending arm single-unit is triangular prism, its cross section is equilateral triangle, the end face of extending arm single-unit forms triangle by the length of side bar that three diameters are identical, the axial direction of extending arm single-unit comprises: the strut bar that three diameters are identical, and is provided with two reinforcement intersection digonal links between two strut bars of each side of extending arm single-unit.
Described second hand extending arm is the shaft-like framework type extending arm of 16 meters long, and diameter is 300 millimeters, component central span more than 35.76 meter after launching of entering the orbit;
Described minute hand extending arm is the shaft-like framework type extending arm of 14 meters long, and diameter is 300 millimeters, component central span more than 31.76 meter after launching.
Described rotating mechanism is set of gears transmission device, comprising: the big gear wheel of engagement and inner gear, and described big gear wheel and four second hand extending arms are connected; The motor of this gear drive exports certain moment of torsion and rotating speed by one speed reducer, drives inner gear to rotate, and the big gear wheel of drive and inner gear engagement then rotates, thus realizes the rotary motion of the relative minute hand extending arm of second hand extending arm.
A sheathed main force support structure in described satellite body, loaded cylinder centered by this main force support structure, satellite body is divided into propulsion module, satellite equipment instrument compartment and payload module three-decker.
Because SPORT satellite attitude control system is according to current attitude control of satellite member prior art research level and satellite layout, providing satellite gravity anomaly frequency is: 7.8 × 10-4Hz, for avoiding the coupling that attitude and extending arm occur, be greater than control frequency two orders of magnitude to the preliminary requirement of long extending arm deployed condition fundamental frequency.The version profile of extending arm single-unit is triangular prism, and the unit by this version of more piece is connected through the hinge and forms by extending arm.Extending arm cross section is equilateral triangle, and single-unit end face is made up of the bar that three diameters are identical, and unit axial direction is also made up of the bar that three diameters are identical, and each side of unit has two to strengthen intersecting digonal links.Drawn by extending arm Dynamics Simulation Analysis: when unit shaft is set to 20 millimeters to shank diameter, triangular-section length of side shank diameter is set to 10 millimeters, the digonal link diameter that intersects is set to 5 millimeters, when unit shaft is set to 350 millimeters to long unification, bar material is carbon fiber composite material, hinge aluminum alloy materials, can ensure that the long extending arm of 14 meters and 16 meters and satellite attitude coupling can not occur.
The invention has the advantages that, loaded cylinder, radial dividing plate load path centered by satellite main force support structure, power transmission link is succinctly clear, and configuration layout is conducive to the design of structural strength and rigidity; Satellite carries a set of orbit maneuver engine, when cruise section flies, can become rail voluntarily, reduces the requirement to delivery Upper Stage; The placement position of satellite body propulsion module ensure that centroid of satellite change in location is little, can not cause excessive pressure, can keep the stability of satellite attitude preferably to the control of satellite attitude along with fuel reduces; The overall height dimension of satellite meets the requirement that satellite attitude subsystem degree of stability is 2 °, second hand extending arm and minute hand extending arm two-layer between distance be 0.660 meter, and increase by a rigid rod in second hand extending arm end, not only ensure that second hand extending arm and minute hand extending arm can not collide at component, end antenna after launching, but also meet 8 component antenna reflective faces in same plane; Propose 1.5 meters of the configuration layout of communication antenna, installation site and mode of motion over the ground, when ensure that satellite moves in-orbit, the relative position between the earth, the sun, satellite three at any time in change, being communicated with of the communication link of antenna and the earth; According to the requirement of clock scan detection principle, design set of gears transmission device and four second hand extending arms are connected.Motor exports certain moment of torsion and rotating speed by retarder, and drive inner gear to rotate, inner gear makes big gear wheel rotate by engagement, thus realizes the rotary motion of the relative minute hand of second hand.The present invention proposes a kind of configuration dimension plan of long extending arm, can ensure that the extending arm of 14 meters and 16 meters long and satellite attitude coupling do not occur.Under the restriction of delivery fairing envelope size, the design of female star and component, provides a kind of SPORT clock scan satellite, meets requirement and the restriction of delivery, meets capacity weight and realizes the requirement that scientific goal carries out detecting.
Accompanying drawing explanation
Fig. 1 is SPORT satellite launch constitution diagram;
Fig. 2 is SPORT satellite body inner structure;
Fig. 3 is that satellite is in cruise section state of flight;
Fig. 4 is that satellite launches in-orbit;
Fig. 5 is component rounding state;
Fig. 6 is component deployed condition in-orbit;
Fig. 7 is component capacity weight;
Fig. 8 is component deployed condition and minute hand extending arm connection diagram;
Fig. 9 is satellite component and second hand extending arm connection diagram;
Figure 10 is the structural representation of rotating mechanism.
Accompanying drawing identifies
1, orbit maneuver engine 2, second hand extending arm 3, component
4, minute hand extending arm 5, over the ground communication antenna 6, satellite body
7, butt joint ring 8, adapter 9, inner gear
10, big gear wheel 11, equipment compartment 12, propulsion module
13, payload module 14, rigid connecting rod 15, the solar cell wing
16, helical antenna 17, expansion guiding mechanism 18, receiver
19, power module 20, S-band number pass antenna 21, reflecting plate
Detailed description of the invention
Be described in further details for the present invention below in conjunction with accompanying drawing.
SPORT satellite outside and inner structure layout are as shown in Figure 1,2 and 3.Satellite is primarily of satellite body 6, component 3, extending arm 2/4, the solar cell wing 15, butt joint ring 7, the over the ground parts such as communication antenna 5, precise tracking 1 composition.Satellite body 5 is cuboid, is of a size of 2520mm × 2520mm × 2270mm, and body side is that 2 wings can open up solar array 15, and every wing forms by 5 pieces.Second hand extending arm 2 is the shaft-like framework type extending arm of 16 meters long, and diameter is 0.3 meter, and component central span after launching of entering the orbit is 35.76 meters.Minute hand extending arm 4 is the shaft-like framework type extending arm of 14 meters long, and diameter is 0.3 meter, and after launching, component central span is 31.76 meters.Second hand extending arm, minute hand extending arm respectively have four, uniform along satellite spin axle.Minute hand extending arm 4 and satellite body are fixed, and rotate with satellite spin campaign.Second hand extending arm 2 carries a set of rotating mechanism, and relative minute hand extending arm 4 can realize the demand of different rotating speeds.The TT&C antenna 5 of 1.5 rice diameters is connected with satellite body 6 by a set of servomechanism, draws in and be locked on satellite side plate during transmitting, and after satellite enters transfer orbit, latching device release antenna launches.When satellite moves in-orbit, the relative position between the earth, the sun, satellite three, at any time in change, is ensure and the communication link of the earth, and servomechanism can realize day wire-wound satellite spin axle and to rotate and around the rotation with spin axis vertical direction axle.Component has 8, respectively on minute hand extending arm 4 and second hand extending arm 2 fixes 4.The outer profile size of satellite launch state is 4515mm × 4515mm × 5226mm (not comprising adapter), and part dimension can adjust according to the inner space of novel delivery fairing.
As shown in Figure 10, described rotating mechanism is set of gears transmission device, comprising: the big gear wheel 10 of engagement and inner gear 9, and described big gear wheel 10 and four second hand extending arms 2 are connected; The motor of this gear drive exports certain moment of torsion and rotating speed by one speed reducer, drives inner gear 9 to rotate, and the big gear wheel 10 that drive and inner gear 9 engage then rotates, thus realizes the rotary motion of the relative minute hand extending arm 4 of second hand extending arm 2.And described be positioned at the rigid connecting rod 14 that component on second hand extending arm 2 and extending arm junction increase a fixed length, after launching for making each component be positioned on second hand extending arm 2 with the component be positioned on minute hand extending arm 4 at grade.
In the design of satellite overall height dimension, mainly consider the requirement of satellite attitude subsystem, for preventing second hand extending arm 2 and minute hand extending arm 4 from not colliding in end, the distance between two-layer extending arm is greater than 0.6516 meter, and the distance in this programme between two-layer bar is 0.660 meter.Satellite in cruise section state of flight as shown in Figure 3, satellite in-orbit deployed condition as Fig. 4.
SPORT satellite has 8 components, 4 minute hand components, 4 second hand components, and its formation is substantially identical.Component gathering and deployed condition are as shown in Figure 5, Figure 6.Component 3 is launched guiding mechanism 17, guiding expansion drive motor and retarder, S-band number biography antenna 20, receiver 18 and power module 19 etc. formed by celestial body, helical antenna 16, reflecting plate 21, reflecting plate support, Flexible solar panel, helical antenna.Reflecting plate and Flexible solar panel are fixed on reflecting plate support.Helical antenna 16 is fixed at top with expansion guiding mechanism 17, and after helical antenna 16 launches, guiding mechanism 17 can limit rocking of helical antenna 16 head.Helical antenna 16 diameter is 0.640 meter, height 2.5 meters after launching.Reflecting plate 21 is diameters is 2 meters, aluminium foil with 100mm × 100mm hollow out grid.
During satellite launch, helical antenna 16, reflecting plate 21, reflecting plate support, Flexible solar panel, helical antenna launch guiding mechanism 17 and are in rounding state, be locked by component band, reflecting plate support outer rim end is provided with limiting stopper, and helical antenna 16 can be made to be in compressive state.After satellite enters sun SSO (Sun Synchronous Orbit), after female star 8 extending arms launch, component is drawn band in and is unlocked, and reflecting plate support is under the effect of torsion spring, launch with reflecting plate and Flexible solar panel, guiding mechanism 17 together launches with helical antenna 16 under motor drives subsequently.Component rounding state outer profile size is 768mm × 768mm × 1087mm, and component deployed condition outer profile size is 2000mm × 2000mm × 2933mm.
Component receiver 18 and power module 19 are placed on component stellar interior, as shown in Figure 7.Be connected with female star extending arm 2/4 with a face outside component, place S-band number outside the bottom of component and pass antenna 20, top layer is connected by hollow cylinder butt flange with reflecting plate, and the drive motor and the retarder that control the expansion of helical antenna guiding mechanism are just fixed on this cylinder inside.The energy demand of component is ensured by self, at the attachment face of the non-equipment of component outside face, be pasted with solar battery sheet, but block often due to reflecting plate antithetical phrase star body, a Flexible solar panel that can fold is increased, to ensure the power demands of component below reflecting plate.
Clock scan detection principle requires that minute hand and second hand component reflecting plate in same plane, to avoid mutual blocking, and should point to the sun after launching simultaneously.Therefore increase the rigid connecting rod of a measured length in second hand component and extending arm junction, make each second hand component launch after and minute hand component at grade, as shown in Figure 8, Figure 9.
It should be noted last that, above embodiment is only in order to illustrate technical scheme of the present invention and unrestricted.Although with reference to embodiment to invention has been detailed description, those of ordinary skill in the art is to be understood that, modify to technical scheme of the present invention or equivalent replacement, do not depart from the spirit and scope of technical solution of the present invention, it all should be encompassed in the middle of right of the present invention.
Claims (10)
1. a SPORT clock scan satellite, this satellite comprises: satellite body, component, extending arm, the solar cell wing, butt joint ring, over the ground communication antenna and precise tracking, is characterized in that,
Described satellite body is cuboid, and its inside is three cabin structures, specifically comprises: propulsion module, satellite equipment instrument compartment and payload module;
Described butt joint ring is positioned at bottom satellite, for being connected with carrier rocket by band;
Described communication antenna is over the ground connected with satellite body by a set of servomechanism, draws in and be locked on satellite side plate during transmitting, and after satellite enters transfer orbit, latching device release antenna launches;
Described extending arm comprises four second hand extending arms and four minute hand extending arms, and described second hand extending arm and minute hand extending arm are distributed in two planes vertical with the spin axis of satellite respectively; Described minute hand extending arm and satellite body are fixed, and rotate with satellite spin campaign; Described second hand extending arm carries a set of rotating mechanism, and relative minute hand extending arm can realize the demand of different rotating speeds;
Described component is 8, the outside of this component celestial body is connected with described four minute hand extending arms or four second hand extending arms respectively with a face, and described be positioned at the rigid connecting rod that component on second hand extending arm and extending arm junction increase a fixed length, after launching for making each component be positioned on second hand extending arm with the component be positioned on minute hand extending arm at grade;
Described component specifically comprises: celestial body, helical antenna, reflecting plate, reflecting plate support, Flexible solar panel, helical antenna launch guiding mechanism, guiding expansion drive motor and retarder, S-band number passes antenna, receiver and power module; Described reflecting plate and described Flexible solar panel are fixed on described reflecting plate support; Described helical antenna is fixed at top with expansion guiding mechanism, and after helical antenna launches, guiding mechanism can limit rocking of helical antenna head;
Place S-band number outside described component celestial body bottom and pass antenna, top layer and described reflecting plate are by the Flange joint of hollow cylinder, and described guiding launches drive motor and retarder is fixed on this hollow cylinder inside.
2. SPORT clock scan satellite according to claim 1, is characterized in that, described reflecting plate is rounded and with the aluminium foil of hollow out grid.
3. SPORT clock scan satellite according to claim 1, is characterized in that, the diameter of described helical antenna is 0.640 meter, and height 2.5 meters after launching.
4. SPORT clock scan satellite according to claim 1, is characterized in that, described reflecting plate support outer rim end is provided with limiting stopper, launches to make described helical antenna be fixed on compressive state together with guiding mechanism with antenna.
5. SPORT clock scan satellite according to claim 1, is characterized in that, the non-equipment attachment face of described component outside face is pasted with solar battery sheet, for the energize portions demand of component.
6. SPORT clock scan satellite according to claim 1 or 5, is characterized in that, arrange a Flexible solar panel that can fold below described reflecting plate, for ensureing the power demands of solar battery sheet to component.
7. SPORT clock scan satellite according to claim 1, is characterized in that, described second hand extending arm and minute hand extending arm are shaft-like framework type extending arm, and being connected through the hinge by some extending arm single-units forms; Described extending arm single-unit is triangular prism, its cross section is equilateral triangle, the end face of extending arm single-unit forms triangle by the length of side bar that three diameters are identical, the axial direction of extending arm single-unit comprises: the strut bar that three diameters are identical, and is provided with two reinforcement intersection digonal links between two strut bars of each side of extending arm single-unit.
8. the SPORT clock scan satellite according to claim 1 or 7, is characterized in that, described second hand extending arm is the shaft-like framework type extending arm of 16 meters long, and diameter is 300 millimeters, component central span more than 35.76 meter after launching of entering the orbit;
Described minute hand extending arm is the shaft-like framework type extending arm of 14 meters long, and diameter is 300 millimeters, component central span more than 31.76 meter after launching.
9. SPORT clock scan satellite according to claim 1, it is characterized in that, described rotating mechanism is set of gears transmission device, comprising: the big gear wheel of engagement and inner gear, and described big gear wheel and four second hand extending arms are connected; The motor of this gear drive exports certain moment of torsion and rotating speed by one speed reducer, drives inner gear to rotate, and the big gear wheel of drive and inner gear engagement then rotates, thus realizes the rotary motion of the relative minute hand extending arm of second hand extending arm.
10. SPORT clock scan satellite according to claim 1, it is characterized in that, a sheathed main force support structure in described satellite body, loaded cylinder centered by this main force support structure, satellite body is divided into propulsion module, satellite equipment instrument compartment and payload module three-decker.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010191529.8A CN101850852B (en) | 2010-05-26 | 2010-05-26 | SPORT (Solar Polar Orbit Radio Telescope) clock scanning satellite |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201010191529.8A CN101850852B (en) | 2010-05-26 | 2010-05-26 | SPORT (Solar Polar Orbit Radio Telescope) clock scanning satellite |
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| CN101850852A CN101850852A (en) | 2010-10-06 |
| CN101850852B true CN101850852B (en) | 2015-03-18 |
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| CN201010191529.8A Expired - Fee Related CN101850852B (en) | 2010-05-26 | 2010-05-26 | SPORT (Solar Polar Orbit Radio Telescope) clock scanning satellite |
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| CN102009746B (en) * | 2010-11-08 | 2012-11-14 | 航天东方红卫星有限公司 | Octagonal battery-equipped array upright post micro satellite configuration |
| RU2457157C1 (en) * | 2010-12-07 | 2012-07-27 | Федеральное государственное унитарное предприятие "Государственный космический научно-производственный центр имени М.В. Хруничева (ФГУП "ГКНПЦ им. М.В. Хруничева") | Micro-satellite for earth surface remote sensing |
| CN102267573A (en) * | 2011-05-11 | 2011-12-07 | 哈尔滨工业大学 | On-track inflatable rigidizable aerated satellite |
| CN103482084B (en) * | 2013-08-29 | 2016-01-13 | 中国科学院长春光学精密机械与物理研究所 | A kind of novel Stretching of solar wings based on banded spring and supporting mechanism |
| CN103593505B (en) * | 2013-10-16 | 2016-06-01 | 中国空间技术研究院 | A kind of satellite precise tracking installation parameter defining method |
| CN108172968B (en) * | 2017-12-08 | 2019-12-20 | 中国空间技术研究院 | Antenna unfolding support capable of being overlapped |
| CN113173271A (en) * | 2021-05-28 | 2021-07-27 | 重庆协点通讯技术有限公司 | Star chain receiving arrangement convenient to adjust |
| CN114678676B (en) * | 2022-04-22 | 2023-02-14 | 西安电子科技大学 | Satellite-borne spiral antenna unfolding structure based on opening circular tube |
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| US6229501B1 (en) * | 1998-04-23 | 2001-05-08 | Astrium Gmbh | Reflector and reflector element for antennas for use in outer space and a method for deploying the reflectors |
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| EP0666612A2 (en) * | 1994-02-04 | 1995-08-09 | Orbital Sciences Corporation | Self-deploying helical structure |
| US6229501B1 (en) * | 1998-04-23 | 2001-05-08 | Astrium Gmbh | Reflector and reflector element for antennas for use in outer space and a method for deploying the reflectors |
| CN1782734A (en) * | 2004-11-25 | 2006-06-07 | 中国科学院空间科学与应用研究中心 | Rotary scanning passive microwave imaging primary and secondary satellite system |
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Address after: 100084 No. 1, No. 2, South of Zhongguancun, Haidian District, Beijing Patentee after: NATIONAL SPACE SCIENCE CENTER, CAS Address before: 100084 No. 1, No. 2, South of Zhongguancun, Haidian District, Beijing Patentee before: Space Science & Applied Research Centre, Chinese Academy of Sciences |
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Granted publication date: 20150318 Termination date: 20200526 |