CN107678018A - More star super close distances are with winged Space-based Radar System - Google Patents
More star super close distances are with winged Space-based Radar System Download PDFInfo
- Publication number
- CN107678018A CN107678018A CN201710876153.6A CN201710876153A CN107678018A CN 107678018 A CN107678018 A CN 107678018A CN 201710876153 A CN201710876153 A CN 201710876153A CN 107678018 A CN107678018 A CN 107678018A
- Authority
- CN
- China
- Prior art keywords
- star
- antenna
- based radar
- satellite
- space
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/02—Systems using reflection of radio waves, e.g. primary radar systems; Analogous systems
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/86—Combinations of radar systems with non-radar systems, e.g. sonar, direction finder
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/86—Combinations of radar systems with non-radar systems, e.g. sonar, direction finder
- G01S13/865—Combination of radar systems with lidar systems
Abstract
The invention discloses a kind of more star super close distances with winged Space-based Radar System, it is made up of measuring system, super close distance between satellite health, space based radar antenna, high precision star with flying control system, high precision planeness measuring system, big data quantity Transmission system；Satellite health by satellite structure, attitude control, thermal control, power supply, etc. subsystem form, provided safeguard condition for the work of radar antenna.The present invention ensures the distance between each antenna and flatness by launching more small area radar antenna satellites, in-orbit formation super close distance with flying.
Description
Technical field
The present invention relates to a kind of radar system, more particularly to a kind of more star super close distances with winged Space-based Radar System.
Background technology
In order to realize the detection to middle-size and small-size moving target, according to radar equation, space based radar needs up to a hundred or even thousands of
The antenna of square meter area, antenna bearingt are rice up to a hundred to size, and required power is up to tens to hundreds of kilowatt, it is contemplated that is limited to
The constraint of envelope and weight is delivered, single satellite is difficult to；Therefore more star super close distances are proposed with winged space based radar system
System.
By launching more small area radar antenna satellites, in-orbit formation super close distance ensures between each antenna with flying
Distance and flatness, it is equivalent to up to a hundred or thousands of square metres of radar antennas；The system list star scheme is simply consistent, it is in-orbit application compared with
To be flexible, in the case where single star breaks down, other satellites can still form system work, effectively improve the reliable of system
Property and redundancy, while single star antenna size is smaller, effectively solves the problems, such as the large inertia Flexible Control that long size antenna is brought.
There is the spacebased system being diversion for small yardstick both at home and abroad at present, the more star super close distances for not finding to publish are with flying
Space-based Radar System report, be not collected into similar data yet.
The content of the invention
The technical problems to be solved by the invention are to provide a kind of more star super close distances with winged Space-based Radar System, and it is suitable
For the radar satellite system of space-based overlarge area overlength size, overlarge area overlength chi can not be carried for solving single satellite
The problem of very little radar antenna, reduce system realizes difficulty, improves the reliability and redundancy of system.
The present invention is that solve above-mentioned technical problem by following technical proposals：A kind of more star super close distances are with winged day
Base radar system, it is characterised in that its by measuring system between satellite health, space based radar antenna, high precision star, super close distance with
Fly control system, high precision planeness measuring system, big data quantity Transmission system composition；Satellite health by satellite structure, attitude control,
Thermal control, power supply, etc. subsystem composition, provided safeguard condition for the work of radar antenna；Space based radar antenna is by polylith space-based thunder
Formed up to antenna plate and development mechanism, for launching beam and receive target echo；Measuring system is by high accuracy between high precision star
Laser Cross-Link measurement transmitting and receiving apparatus forms, for measuring the relative position and relative attitude of adjacent two satellites；It is super near
Distance is made up of with flying control system high-precision low thrust equipment, the accurate control of inter-satellite relative position when being worked for radar
Safe distance maintains between system, and star usually；High precision planeness measuring system is by laser scanning measurement equipment and is installed on
The target composition of antenna, measures for antenna plane degree between this star antenna plane degree and star, can be achieved to whole antenna plane degree
Measurement；Big data quantity Transmission system is made up of Space laser communications equipment, for radar data, Cross-Link measurement, antenna plane
Spend the transmission of measurement data；Satellite health connects space based radar antenna below satellite health；Measuring system connects between high precision star
Connect high precision planeness measuring system；Between high precision star measuring system and high precision planeness measuring system all with space based radar day
Line is connected and is located at below space based radar antenna；Big data quantity Transmission system connects satellite health and above satellite health；
Super close distance is located at position on the upper side on the left of satellite health with flying control system connection satellite health, super close distance with flying control system
Put.
Preferably, the space based radar antenna size is small sized antenna.
Preferably, the high-precision laser Cross-Link measurement transmitting and receiving apparatus is simultaneously for three axle relative positions between star
Measured with three axle relative attitudes, relative position measurement precision reaches below millimeter.
Preferably, the high-precision low thrust equipment is applied not only to the high-precision relative position control of super close distance between star,
The maintenance of safe distance between star is additionally operable to, control accuracy reaches millimeter magnitude.
Preferably, the laser scanning measurement equipment passes through the day to the whole antenna plane degree of this star and adjacent satellite side
Line flatness measures simultaneously, and by obtaining the flatness of whole antenna after conversion.
Preferably, the Space laser communications equipment is sent data in definition by adjacent satellite relay two-by-two
Pivot satellite, carry out the integrated treatment of data and the distribution of data.
The positive effect of the present invention is：By launching more small area radar antenna satellites, in-orbit formation is super near
Distance ensures the distance between each antenna and flatness with flying；Measuring system and super close distance are with flying control system between high precision star
System ensure that the accurate of position between star, and safe distance maintains between star usually, and in-orbit application is flexible.
Brief description of the drawings
Fig. 1 is the structural representation of space based radar satellite in the present invention.
Fig. 2 is schematic diagram of the more in-orbit super close distances of space based radar satellite of the invention with flying state.
Embodiment
Present pre-ferred embodiments are provided below in conjunction with the accompanying drawings, to describe technical scheme in detail.
As shown in figure 1, the more star super close distances of the present invention with winged Space-based Radar System by satellite health 1, space based radar day
Measuring system 3, super close distance are with flying control system 4, high precision planeness measuring system 5, big data quantity between line 2, high precision star
Transmission system 6 forms；Satellite health 1 by satellite structure, attitude control, thermal control, power supply, etc. subsystem form, be radar antenna work
Provide safeguard condition；Space based radar antenna 2 is made up of polylith space based radar antenna plate and development mechanism, for launching beam and
Receive target echo；Measuring system 3 is made up of high-precision laser Cross-Link measurement transmitting and receiving apparatus between high precision star, for surveying
Measure the relative position and relative attitude of adjacent two satellites；Super close distance is with flying control system 4 by high-precision low thrust equipment group
Into, the accurate control of inter-satellite relative position when being worked for radar, and safe distance maintains between star usually；High-precision flat
Face degree measuring system 5 is made up of laser scanning measurement equipment with the target for being installed on antenna, for this star antenna plane degree and star
Between antenna plane degree measure, measurement to whole antenna plane degree can be achieved；Big data quantity Transmission system 6 is by Space laser communications
Equipment forms, the transmission for radar data, Cross-Link measurement, antenna plane degree measurement data；Satellite health 1 connects space based radar
Antenna 2 is in the lower section of satellite health 1；Measuring system 3 connects high precision planeness measuring system 5 between high precision star；Between high precision star
Measuring system 3 and high precision planeness measuring system 5 are all connected with space based radar antenna 2 and positioned at the lower sections of space based radar antenna 2；
Big data quantity Transmission system 6 connects satellite health 1 and positioned at the top of satellite health 1；Super close distance is defended with flying the connection of control system 4
Star body 1, super close distance are located at the left side of satellite health 1 position on the upper side with flying control system 4.
The size of space based radar antenna 2 is small sized antenna, so meets the constraint of delivery.
The three axle relative positions and three that the high-precision laser Cross-Link measurement transmitting and receiving apparatus can be used between star simultaneously
Axle relative attitude measures, and relative position measurement precision reaches below millimeter, and such system realizes difficulty reduction.
The high-precision low thrust equipment is used not only for the high-precision relative position control of super close distance between star, may be used also
For the maintenance of safe distance between star, control accuracy reaches millimeter magnitude, so ensures the distance between each antenna.
The laser scanning measurement equipment passes through the antenna plane to the whole antenna plane degree of this star and adjacent satellite side
Degree measures simultaneously, and by that can obtain the flatness of whole antenna after conversion, so ensures the flatness between each antenna.
The Space laser communications equipment by adjacent satellite relay two-by-two, defend by the maincenter that data can be transmitted to definition
Star, the integrated treatment of data and the distribution of data are carried out, so improves system reliability.
In the present embodiment, by taking 400mx3m antennas as an example, each antenna is 25mx3m, is divided into 16 antennas, transmitting
16 small area space based radar satellites, it is in-orbit formation super close distance precision with fly, adjacent radar antenna front and back end interval 5~
10m, ensure the distance between each antenna and flatness, using distributed radar system, pass through MIMO digital beam froming
Realization is equivalent to 1200m2Radar antenna.
As shown in Fig. 2 it is in-orbit along in one line before and after heading to share 16 small area space based radar satellites, in thunder
Up to during work, adjacent radar antenna front and back end interval need to stablize some fixed value in 5~10m, when radar does not work, control
Make adjacent radar antenna front and back end to be spaced in the range of 5~10m, adjacent satellite can enter interplanetary communication, Cross-Link measurement, antenna are put down
Face degree measurement；16 small area space based radar satellite operations launch radar beam in middle low orbit, work, and together
When receive radar beam.
Advantages of the present invention：Satellite health provides safeguard condition for the work of radar antenna；Measuring system between high precision star
And super close distance ensure that the accurate of position between star with flying control system, and safe distance maintains between star usually, it is in-orbit should
With flexible；Big data quantity Transmission system is used for data transfer, improves the reliability of system.
Particular embodiments described above, technical problem, technical scheme and the beneficial effect of the solution to the present invention are carried out
It is further described, should be understood that the specific embodiment that the foregoing is only of the invention, be not limited to
The present invention, within the spirit and principles of the invention, any modification, equivalent substitution and improvements done etc., it should be included in this
Within the protection domain of invention.
Claims (6)
1. a kind of more star super close distances are with winged Space-based Radar System, it is characterised in that it is by satellite health, space based radar day
Measuring system, super close distance are with flying control system, high precision planeness measuring system, big data quantity transmission between line, high precision star
System forms；Satellite health by satellite structure, attitude control, thermal control, power supply, etc. subsystem form, provided for the work of radar antenna
Guarantee condition；Space based radar antenna is made up of polylith space based radar antenna plate and development mechanism, for launching beam and receives mesh
Mark echo；Measuring system is made up of high-precision laser Cross-Link measurement transmitting and receiving apparatus between high precision star, adjacent for measuring
The relative position and relative attitude of two satellites；Super close distance is made up of with flying control system high-precision low thrust equipment, is used for
Safe distance maintains between the accurate control of inter-satellite relative position, and star usually when radar works；High precision planeness is surveyed
Amount system is made up of laser scanning measurement equipment with the target for being installed on antenna, is put down for antenna between this star antenna plane degree and star
Face degree measurement, can be achieved the measurement to whole antenna plane degree；Big data quantity Transmission system is made up of Space laser communications equipment,
Transmission for radar data, Cross-Link measurement, antenna plane degree measurement data；Satellite health connects space based radar antenna in satellite
Below celestial body；Measuring system connects high precision planeness measuring system between high precision star；Measuring system and high-precision between high precision star
Degree measurement of planeness system is all connected with space based radar antenna and is located at below space based radar antenna；Big data quantity Transmission system connects
Connect satellite health and above satellite health；Super close distance is with flying control system connection satellite health, and super close distance is with flying control
System processed is located at position on the upper side on the left of satellite health.
2. more star super close distances as claimed in claim 1 are with winged Space-based Radar System, it is characterised in that the space based radar
Antenna size is small sized antenna.
3. more star super close distances as claimed in claim 1 are with winged Space-based Radar System, it is characterised in that the high accuracy swashs
Light Cross-Link measurement transmitting and receiving apparatus is simultaneously for three axle relative positions between star and the measurement of three axle relative attitudes, relative position
Measurement accuracy reaches below millimeter.
4. more star super close distances as claimed in claim 1 are with winged Space-based Radar System, it is characterised in that the high accuracy is small
Thrust devices are applied not only to the high-precision relative position control of super close distance between star, are additionally operable to the maintenance of safe distance between star, control
Precision processed reaches millimeter magnitude.
5. more star super close distances as claimed in claim 1 are with winged Space-based Radar System, it is characterised in that the laser scanning
Measuring apparatus passes through conversion by measuring the antenna plane degree of the whole antenna plane degree of this star and adjacent satellite side simultaneously
The flatness of whole antenna is obtained afterwards.
6. more star super close distances as claimed in claim 1 are with winged Space-based Radar System, it is characterised in that laser between the star
Communication equipment sends data to the maincenter satellite of definition by adjacent satellite relay two-by-two, carry out data integrated treatment and
The distribution of data.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710876153.6A CN107678018B (en) | 2017-09-25 | 2017-09-25 | Multi-satellite ultra-close-range following flying space-based radar system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710876153.6A CN107678018B (en) | 2017-09-25 | 2017-09-25 | Multi-satellite ultra-close-range following flying space-based radar system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107678018A true CN107678018A (en) | 2018-02-09 |
| CN107678018B CN107678018B (en) | 2021-04-27 |
Family
ID=61138112
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710876153.6A Active CN107678018B (en) | 2017-09-25 | 2017-09-25 | Multi-satellite ultra-close-range following flying space-based radar system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107678018B (en) |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| IT1205769B (en) * | 1987-03-26 | 1989-03-31 | Selenia Spazio Spa | RADAR SYSTEM CONSTITUTED BY A SERIES OF INTERCONNECTED ELEMENTARY SATELLITES |
| CN101520511A (en) * | 2009-03-13 | 2009-09-02 | 北京航空航天大学 | Method for formation configuration of distributed satellites with synthetic aperture radars |
| CN101915911A (en) * | 2010-08-26 | 2010-12-15 | 哈尔滨工业大学 | Space arbitrary configuration distributed SAR moving target parameter estimation method based on cancellation accumulation space-time spectrum |
| CN102147967A (en) * | 2010-02-10 | 2011-08-10 | 上海卫星工程研究所 | Satellite data acquisition and transmission method |
| CN102323571A (en) * | 2011-05-31 | 2012-01-18 | 北京航空航天大学 | Distribution method of satellite-borne dual-antenna SAR (Synthetic Aperture Radar) interferometric calibrator with comprehensive overall parameter |
| CN102736118A (en) * | 2012-06-18 | 2012-10-17 | 航天东方红卫星有限公司 | Integrated satellite system for measuring global gravity field |
| CN104089594A (en) * | 2014-07-25 | 2014-10-08 | 北京卫星环境工程研究所 | Automatic accurate measurement method for satellite large-size planar array SAR antenna |
| CN104359374A (en) * | 2014-11-11 | 2015-02-18 | 上海无线电设备研究所 | Device and method for manually measuring normal thickness of large cavity deep radome |
| CN105207703A (en) * | 2015-09-06 | 2015-12-30 | 哈尔滨工业大学深圳研究生院 | Communication array parameter optimization method based on low-earth-orbit satellite formation satellite-earth MIMO |
| US20160116582A1 (en) * | 2011-04-29 | 2016-04-28 | Spatial Digital Systems, Inc. | Radar imaging via spatial spectrum measurement and MIMO waveforms |
| CN106229605A (en) * | 2016-06-30 | 2016-12-14 | 北京空间飞行器总体设计部 | A kind of massive phased array accurate installation method of antenna based on mathematical modeling |
| CN106970388A (en) * | 2017-05-23 | 2017-07-21 | 王辉 | Double star Ka FMCW PANEL SAR imaging systems |
-
2017
- 2017-09-25 CN CN201710876153.6A patent/CN107678018B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| IT1205769B (en) * | 1987-03-26 | 1989-03-31 | Selenia Spazio Spa | RADAR SYSTEM CONSTITUTED BY A SERIES OF INTERCONNECTED ELEMENTARY SATELLITES |
| CN101520511A (en) * | 2009-03-13 | 2009-09-02 | 北京航空航天大学 | Method for formation configuration of distributed satellites with synthetic aperture radars |
| CN102147967A (en) * | 2010-02-10 | 2011-08-10 | 上海卫星工程研究所 | Satellite data acquisition and transmission method |
| CN101915911A (en) * | 2010-08-26 | 2010-12-15 | 哈尔滨工业大学 | Space arbitrary configuration distributed SAR moving target parameter estimation method based on cancellation accumulation space-time spectrum |
| US20160116582A1 (en) * | 2011-04-29 | 2016-04-28 | Spatial Digital Systems, Inc. | Radar imaging via spatial spectrum measurement and MIMO waveforms |
| CN102323571A (en) * | 2011-05-31 | 2012-01-18 | 北京航空航天大学 | Distribution method of satellite-borne dual-antenna SAR (Synthetic Aperture Radar) interferometric calibrator with comprehensive overall parameter |
| CN102736118A (en) * | 2012-06-18 | 2012-10-17 | 航天东方红卫星有限公司 | Integrated satellite system for measuring global gravity field |
| CN104089594A (en) * | 2014-07-25 | 2014-10-08 | 北京卫星环境工程研究所 | Automatic accurate measurement method for satellite large-size planar array SAR antenna |
| CN104359374A (en) * | 2014-11-11 | 2015-02-18 | 上海无线电设备研究所 | Device and method for manually measuring normal thickness of large cavity deep radome |
| CN105207703A (en) * | 2015-09-06 | 2015-12-30 | 哈尔滨工业大学深圳研究生院 | Communication array parameter optimization method based on low-earth-orbit satellite formation satellite-earth MIMO |
| CN106229605A (en) * | 2016-06-30 | 2016-12-14 | 北京空间飞行器总体设计部 | A kind of massive phased array accurate installation method of antenna based on mathematical modeling |
| CN106970388A (en) * | 2017-05-23 | 2017-07-21 | 王辉 | Double star Ka FMCW PANEL SAR imaging systems |
Non-Patent Citations (6)
| Title |
|---|
| M.A. HASAN: "Impact of tracking requirements on space-based radar (SBR) design", 《IEEE INTERNATIONAL CONFERENCE ON RADAR》 * |
| 宋南海: "大型相控阵雷达阵面平面度测量方法研究", 《电子机械工程》 * |
| 李志: "分布式天基雷达卫星编队与波束形成技术研究", 《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》 * |
| 苏力争等: "大型相控阵雷达天线阵面结构精度分析及控制", 《火控雷达技术》 * |
| 郝继刚: "分布式卫星编队构形控制研究", 《中国博士学位论文全文数据库 工程科技Ⅱ辑》 * |
| 陈荣: "美国天基预警雷达系统发展", 《国防科技》 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107678018B (en) | 2021-04-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105928467B (en) | Large Spacecraft malformation measures pilot system under vacuum low-temperature environment | |
| Zuber et al. | The lunar reconnaissance orbiter laser ranging investigation | |
| CN102323597B (en) | GPS (Global Positioning System)-based inter-satellite baseline measurement method for flight of formed array around satellite | |
| CN107808997A (en) | Space array antenna | |
| Murphy et al. | LLCD operations using the lunar lasercom ground terminal | |
| CN105790812B (en) | It is a kind of to receive system and method using the ground station signals enhancing of spaced antenna battle array | |
| CN110146860B (en) | Remote radar calibration satellite system and calibration method thereof | |
| CN103178895A (en) | Inter-satellite measuring and controlling system and inter-satellite measuring and controlling method for mobile satellite communication satellites | |
| CN103412308A (en) | High-precision interferometric synthetic aperture radar system | |
| CN107544469A (en) | A kind of automatic winged control closed loop test system with configuration | |
| CN110940310B (en) | Calculation method for phased array antenna beam pointing angle of missile-borne relay measurement and control terminal | |
| CN108583934A (en) | Survey of deep space large aperture antenna based on erecting by overhang calibrates ground system test | |
| CN202421491U (en) | Multilateral positioning system based on distributed clocks | |
| CN204925385U (en) | Mountain landslide's MIMO radar monitoring system | |
| CN109760852A (en) | A kind of extensive aircraft and application method of the in-orbit autonomous assembling of microsatellite cluster | |
| CN103954945B (en) | A kind of tellurometer survey radar gamut scaling method based on fibre delay line | |
| CN105571597A (en) | Ultra-deep-field X-ray active navigation system | |
| CN107678018A (en) | More star super close distances are with winged Space-based Radar System | |
| CN102590786A (en) | Multilateral positioning system based on distributed clock | |
| CN115877415B (en) | Ultra-high precision space spacecraft clock error estimation method and system | |
| CN113483699B (en) | Ground laser terminal multi-optical-axis parallel calibration method based on star sensor | |
| CN106628254B (en) | A kind of micro-nano satellite for ionospheric probing | |
| Peng et al. | Preparatory study for constructing FAST, the world's largest single dish | |
| Geldzahler | Coherent uplink arraying techniques for next generation space communications and planetary radar systems | |
| Cantafio et al. | Photovoltaic, gravitationally stabilized, solid-state satellite solar power station |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB03 | Change of inventor or designer information |
Inventor after: Lu Qing Inventor after: Su Yuezeng Inventor after: Sun Yongyan Inventor after: Wan Xiangcheng Inventor after: Chen Junli Inventor before: Lu Qing Inventor before: Sun Yongyan Inventor before: Wan Xiangcheng Inventor before: Chen Junli |
|
| CB03 | Change of inventor or designer information | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |