CN110015444A - Middle zero dip composition aperture radar satellite configuration of high orbit - Google Patents
Middle zero dip composition aperture radar satellite configuration of high orbit Download PDFInfo
- Publication number
- CN110015444A CN110015444A CN201910251480.1A CN201910251480A CN110015444A CN 110015444 A CN110015444 A CN 110015444A CN 201910251480 A CN201910251480 A CN 201910251480A CN 110015444 A CN110015444 A CN 110015444A
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- satellite
- battle array
- aperture radar
- antenna
- load cabin
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
- B64G1/443—Photovoltaic cell arrays
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
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- General Physics & Mathematics (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Details Of Aerials (AREA)
- Aerials With Secondary Devices (AREA)
Abstract
The present invention provides a kind of middle zero dip composition aperture radar satellite configurations of high orbit, including satellite platform, load cabin truss, feed battle array, reflector antenna, reflecting surface extending arm, solar battery array and expandable type radiator, the satellite platform is positive hexagonal prism body structure, under satellite launch state, side length is that the feed battle array of 3m is vertically installed at the side of load cabin truss；Load cabin truss other side is placed and be pressed on to the tubular structure that it is Φ 1.3m × 4m that the reflector antenna of bore 25m, which collapses, by band banding rear-inclined, and it is 2 sections of antenna insides for being pressed on load cabin truss together with antenna that the reflecting surface extending arm that length of run is 8m, which collapses,.Satellite configuration stable structure provided by the invention can carry large scale and big quality load, have very high adaptability for the demand for using the Synthetic Aperture Radar satellite of middle and high track at zero inclination angle to carry out large area scanning detection at present.
Description
Technical field
The present invention relates to space technology Satellite technical field more particularly to a kind of loading heavy caliber deployable reflecting surface days
The zero dip composition aperture radar satellite configuration of middle high orbit of line.
Background technique
Synthetic Aperture Radar satellite, which has, actively emits reception ability, and microwave has the function of to penetrate cloud and mist etc., therefore synthesizes
Aperture radar satellite is not illuminated by the light the adverse weather conditions such as condition, sexual intercourse mist, has round-the-clock, all weather operations condition, is to answer
To one of the most effective means observed under severe weather conditions.Synthetic Aperture Radar satellite is deployed in the middle and high track of the earth,
Make satellite " stand high, look far ", and use low inclination angle, satellite will be made, which to obtain low orbit Synthetic Aperture Radar satellite, to be reached
Temporal resolution and continue earth observation ability, therefore compared with low orbit Synthetic Aperture Radar satellite, high orbit synthesizes hole
Diameter radar satellite has the advantage that timeliness is high, lasting observation time is long, observation swath is big, is that the following applied satellite is given priority to
One of direction.
But it is limited to toter, the satellites such as earth observation, microwave remote sensing are more and more using storage than high, face
Low density deployable heavy caliber reflector antenna carries out the collection and transmitting of signal.Meanwhile needing the sun using large area
Cell array, to meet the energy demand of satellite.Therefore, the synthesis of heavy caliber reflector antenna and large-area solar cell battle array is loaded
The configuration layouts of aperture radar satellite become problem in the urgent need to address.
Summary of the invention
It needs to load the big of " feed battle array+reflector antenna " system for middle and high zero dip composition aperture radar satellite of track
The deployable parabola antenna of type and large-area solar cell battle array, the present invention provides one kind, and the enveloping space, space to be made full use of to fill
Divide Optimum utilization and rationally general assembly, the Large Deployable parabola antenna of satisfaction " feed battle array+reflector antenna " system and big face
The satellite configuration that the gathering of product solar battery array is required with in-orbit expansion efficiently solves the middle and high track conjunction using zero inclination angle
At the demand of aperture radar satellite transmitting and in-orbit flight.
To achieve the above object, the invention is realized by the following technical scheme:
Middle zero dip composition aperture radar satellite configuration of high orbit, including it is satellite platform, load cabin truss, feed battle array, anti-
Penetrate surface antenna, reflecting surface extending arm, solar battery array and expandable type radiator, the satellite platform is positive hexagonal prism body
Structure, the load cabin truss provide installation foundation and pressure for bearing feed battle array, reflector antenna and reflector antenna extending arm
Tight relieving mechanism mounting surface, wherein under satellite launch state, due to being needed when operation on orbit between feed battle array and reflector antenna
Certain relative positional relationship is kept, to reduce the in-orbit enveloping space that number is unfolded and makes full use of fairing of launch vehicle,
Side length is that the feed battle array of 3m is vertically installed at the side of load cabin truss；The reflector antenna of bore 25m collapse be Φ 1.3m ×
Load cabin truss other side is placed and be pressed on to the tubular structure of 4m by band banding rear-inclined, and length of run is the anti-of 8m
It penetrates face extending arm and collapses the antenna inside for being pressed on load cabin truss together with antenna for 2 sections, meet feedback after guaranteeing satellier injection
The demand that source battle array and the relative positional relationship and antenna of reflector antenna are directed toward over the ground；The solar battery array point 2 arranges
120 ° of " V " font gatherings are pressed on the outside of two blocks of side plates of satellite platform, and the expandable type radiator is collapsed in satellite launch
It is pressed on load cabin truss, and close to feed battle array two sides, along satellite ± X to being expanded to line-styled after in-orbit expansion.
Further, the inside of the load cabin truss can increase structural slab as needed, using the peace as satellite borne equipment
Fill basal plane.
The first step, after satellite enters the middle and high track in zero inclination angle, solar battery array unlocks between satellite platform first,
Then two column solar battery arrays extremely track Direct to the sun after zero-bit for reinflated 180 ° rotating around 30 ° to one planes of middle shaft rotation.
Reflector antenna and reflecting surface extending arm are unlocked with load cabin truss first, and then reflecting surface extending arm is by reflecting surface
After antenna is expanded to designated position, reflector antenna is expanded to working condition by rounding state；Feed battle array by deployed configuration around
Satellite X-axis locks after being unfolded 120 °, establishes specified relative positional relationship with reflector antenna.
Further, the expandable type radiator uses the expandable type radiator of 2 wing, 30 ㎡, for feed battle array
Implement thermal control, ensure that the high-power rapid cooling demand of feed battle array.
Further, the mountable star sensor in feed battle array side.
Further, satellite is in-orbit flies along equator East and West direction, and Large deployable antenna is unfolded along earth direction to the north pole, too
Positive cell array tracks day after 180 ° of the expansion of the south pole of the earth direction and orients.
The invention has the following advantages:
1, the present invention provides a kind of Large Deployable parabola antenna receipts for meeting " feed battle array+reflector antenna " system
Hold together the satellite configuration required with in-orbit expansion.
2, the satellite structure required with in-orbit expansion is collapsed the present invention provides a kind of large-scale solar battery array for meeting 100 ㎡
Type.
3, satellite configuration stable structure provided by the invention, large scale and big quality load can be carried, for using at present
The demand that the Synthetic Aperture Radar satellite of the middle and high track at zero inclination angle carries out large area scanning detection has very high adaptability.
4, the use that the in-orbit flight configuration of satellite of the present invention can satisfy the antennas such as rail control, thermal control, number biography, observing and controlling is wanted
It asks, has and be widely applied very much promotional value.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is satellite launch state configuration schematic diagram of the invention；
Fig. 2 is satellite flight state configuration schematic diagram of the invention.
In figure:
1 is satellite platform；
2 be load cabin truss；
3 be feed battle array；
4 be reflector antenna；
5 be reflecting surface extending arm；
6 be solar battery array；
7 be expandable type radiator.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection scope.
As shown in Figure 1, being satellite configuration emission state schematic diagram of the present invention.It is deployable in conjunction with a kind of above-mentioned loading heavy caliber
The characteristics of zero dip composition aperture radar satellite configuration technology of middle high orbit of reflector antenna, builds first in order to describe conveniently
The layout coordinate system (O-XYZ) of vertical satellite, is defined as follows:
Coordinate origin O: the theoretical center of satellite and the rocket connection ring lower end frame, satellite and the rocket parting surface；
Z axis: feed battle array direction is directed toward along coordinate origin；
X-axis: perpendicular to Z axis and platform side plate direction；
Y-axis: with X, Z axis at right-handed system.
Satellite is equipped with the Large Deployable parabola antenna of " feed battle array+reflector antenna " system, wherein primary reflection surface day
Linear diameter reaches 25m, and feed battle array size reaches 3m × 3m, it is desirable that keeps specific several when operation on orbit, between feed battle array and reflecting surface
What position, and the radome fairing requirement satellite envelope for being used to emit the "Long March" series of carrier rockets of the satellite is less than 4500mm, due to
The envelope size of primary reflection surface rounding state reaches Φ 1300mm × 4000mm, to meet delivery envelope requirement, feed battle array is vertical
It is placed on the side+Z of load cabin truss, to guarantee operation on orbit, application start mechanism is needed, feed battle array is entered the orbit in satellite launch
After be expanded to designated position.To guarantee the geometry site after being unfolded between feed battle array and reflecting surface, by the anti-of rounding state
Surface antenna and its extending arm slant setting are penetrated in the side-Z of the load truss opposite with feed battle array, meets delivery radome fairing envelope and wants
It asks.After satellite launch is entered the orbit, reflector antenna is deployed into outside celestial body and after locking by extending arm, and reflector antenna presses program
A secondary parabola antenna is expanded into, the in-orbit specific relative positional relationship of holding between feed battle array and reflecting surface is made.
Due to satellite use 0 ° of inclination angle track, for realize antenna large area scanning performance, by antenna along earth arctic cloth
It sets.Energy demand needed for transmission power in order to realize large aperture antenna need to use the solar battery array of 100 square meters.Consider
Satellite configuration and gesture stability demand, using single-blade biserial solar battery array configuration scheme, under emission state, by solar battery array
V-shaped gathering is pressed on two blocks of side plates of platform, after unlock of entering the orbit, first by the solar battery array under rounding state by
After " V " font forms one piece of plane after rotating 30 ° rotating around axis of dilatation, then after edge+Y-direction is expanded to line-styled, by driving machine
Structure drives solar battery array to track day and orients, and realizes the energy demand of satellite.
The expandable type radiator of 2 pieces of 15 square meters of surface area has been respectively arranged in feed battle array two sides, when satellite launch, two pieces
Expandable type radiator collapses be pressed on the truss of feed battle array two sides respectively, when in-orbit flight respectively edge ± X to being expanded to
Line-styled can effectively solve feed array large power heat dissipation problem.
Installation and the pointing accuracy of star sensor is effectively ensured in the mountable star sensor in feed battle array side.
The present invention is the subsequent middle high orbit Synthetic Aperture Radar satellite for loading heavy caliber deployable reflecting surface antenna in China
Construction techniques create a kind of new design method, are mounted on satellite especially for Large deployable antenna, gathering-expansion
Combined configuration designing method becomes the first choice of radar and communications satellite configuration designer, and invention application in the art will
It is very extensive.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring substantive content of the invention.The content that description in the present invention is not described in detail belongs to the known skill of those skilled in the art
Art.
Claims (6)
- Zero dip composition aperture radar satellite configuration of high orbit in 1., which is characterized in that including satellite platform (1), load cabin purlin Frame (2), feed battle array (3), reflector antenna (4), reflecting surface extending arm (5), solar battery array (6) and expandable type radiator (7), the satellite platform (1) is positive hexagonal prism body structure, and under satellite launch state, side length is the feed battle array (3) of 3m It is vertically installed at load cabin truss side；The tubular structure that it is Φ 1.3m × 4m that the reflector antenna (4) of bore 25m, which collapses, passes through Load cabin truss (2) side is placed and be pressed on to band banding rear-inclined, and the reflecting surface extending arm (5) that length of run is 8m collapses It is pressed on the inside of the antenna of load cabin truss (2) together for 2 sections with antenna；2 column of the solar battery array (6) point are in 120 ° " V " Font gathering is pressed on the outside of two blocks of side plates of satellite platform, and the expandable type radiator (7) is collapsed and compressed in satellite launch On load cabin truss (2), and close to feed battle array (3) two sides, along satellite ± X to being expanded to line-styled after in-orbit expansion.
- 2. zero dip composition aperture radar satellite configuration of high orbit in as described in claim 1, which is characterized in that the load The inside of cabin truss (2) can increase structural slab as needed, using the installation base surface as satellite borne equipment.
- 3. zero dip composition aperture radar satellite configuration of high orbit in as described in claim 1, which is characterized in that satellite enters After the middle and high track in zero inclination angle, solar battery array (6) unlocks between satellite platform (1) first, two column solar battery arrays rotating around Then 30 ° to one planes of middle shaft rotation extremely track Direct to the sun after zero-bit for reinflated 180 °.
- 4. zero dip composition aperture radar satellite configuration of high orbit in as described in claim 1, which is characterized in that satellite enters After the middle and high track in zero inclination angle, reflector antenna (4) and reflecting surface extending arm (5) are unlocked with load cabin truss (2) first, then After reflector antenna (4) is expanded to designated position by reflecting surface extending arm (5), reflector antenna (4) is expanded to by rounding state Working condition；Feed battle array (3) is locked after 120 ° of the expansion of satellite X-axis by deployed configuration, is established with reflector antenna (4) specified Relative positional relationship.
- 5. zero dip composition aperture radar satellite configuration of high orbit in as described in claim 1, which is characterized in that described can Expansion radiator (7) uses the expandable type radiator of 2 wing, 30 ㎡, for implementing thermal control to feed battle array, ensure that feed battle array (3) high-power rapid cooling demand.
- 6. zero dip composition aperture radar satellite configuration of high orbit in as described in claim 1, which is characterized in that the feed The mountable star sensor in battle array (3) side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910251480.1A CN110015444A (en) | 2019-03-29 | 2019-03-29 | Middle zero dip composition aperture radar satellite configuration of high orbit |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910251480.1A CN110015444A (en) | 2019-03-29 | 2019-03-29 | Middle zero dip composition aperture radar satellite configuration of high orbit |
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| CN110015444A true CN110015444A (en) | 2019-07-16 |
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Cited By (7)
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| CN110994192A (en) * | 2019-10-30 | 2020-04-10 | 西安空间无线电技术研究所 | Satellite-borne long-focus large-aperture antenna whole-satellite layout and expansion design method |
| CN111505614A (en) * | 2020-04-21 | 2020-08-07 | 西安电子科技大学 | Photoelectric integrated satellite-borne deployable detection device |
| CN111661366A (en) * | 2020-05-27 | 2020-09-15 | 上海卫星工程研究所 | Radome wave-transmitting port arrangement method suitable for satellite wave-transmitting requirements |
| CN112093081A (en) * | 2020-09-27 | 2020-12-18 | 中国科学院微小卫星创新研究院 | Solar wing microwave remote sensing integrated load and control method thereof |
| CN112993536A (en) * | 2021-02-07 | 2021-06-18 | 中国科学院微小卫星创新研究院 | Antenna load compartment configuration |
| CN113258249A (en) * | 2021-05-18 | 2021-08-13 | 上海宇航系统工程研究所 | On-orbit ultra-large deployable space structure system |
| CN113471661A (en) * | 2021-07-02 | 2021-10-01 | 上海航天测控通信研究所 | Large-caliber reflecting surface antenna star mounting with pointing mechanism and testing method |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110994192A (en) * | 2019-10-30 | 2020-04-10 | 西安空间无线电技术研究所 | Satellite-borne long-focus large-aperture antenna whole-satellite layout and expansion design method |
| CN111505614A (en) * | 2020-04-21 | 2020-08-07 | 西安电子科技大学 | Photoelectric integrated satellite-borne deployable detection device |
| CN111505614B (en) * | 2020-04-21 | 2023-03-24 | 西安电子科技大学 | Photoelectric integrated satellite-borne deployable detection device |
| CN111661366A (en) * | 2020-05-27 | 2020-09-15 | 上海卫星工程研究所 | Radome wave-transmitting port arrangement method suitable for satellite wave-transmitting requirements |
| CN111661366B (en) * | 2020-05-27 | 2021-07-20 | 上海卫星工程研究所 | Radome wave-transmitting port arrangement method suitable for satellite wave-transmitting requirements |
| CN112093081A (en) * | 2020-09-27 | 2020-12-18 | 中国科学院微小卫星创新研究院 | Solar wing microwave remote sensing integrated load and control method thereof |
| CN112093081B (en) * | 2020-09-27 | 2021-11-09 | 中国科学院微小卫星创新研究院 | Solar wing microwave remote sensing integrated load and control method thereof |
| CN112993536A (en) * | 2021-02-07 | 2021-06-18 | 中国科学院微小卫星创新研究院 | Antenna load compartment configuration |
| CN112993536B (en) * | 2021-02-07 | 2022-12-09 | 中国科学院微小卫星创新研究院 | Antenna load compartment configuration |
| CN113258249A (en) * | 2021-05-18 | 2021-08-13 | 上海宇航系统工程研究所 | On-orbit ultra-large deployable space structure system |
| CN113471661A (en) * | 2021-07-02 | 2021-10-01 | 上海航天测控通信研究所 | Large-caliber reflecting surface antenna star mounting with pointing mechanism and testing method |
| CN113471661B (en) * | 2021-07-02 | 2022-07-22 | 上海航天测控通信研究所 | Large-caliber reflecting surface antenna star-assembling with pointing mechanism and testing method |
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Application publication date: 20190716 |