CN102323597A - GPS (Global Positioning System)-based inter-satellite baseline measurement method for flight of formed array around satellite - Google Patents
GPS (Global Positioning System)-based inter-satellite baseline measurement method for flight of formed array around satellite Download PDFInfo
- Publication number
- CN102323597A CN102323597A CN201110241765A CN201110241765A CN102323597A CN 102323597 A CN102323597 A CN 102323597A CN 201110241765 A CN201110241765 A CN 201110241765A CN 201110241765 A CN201110241765 A CN 201110241765A CN 102323597 A CN102323597 A CN 102323597A
- Authority
- CN
- China
- Prior art keywords
- star
- satellite
- gps
- antenna
- communication
- 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
Images
Abstract
The invention provides a GPS (Global Positioning System)-based inter-satellite baseline measurement method for flight of a formed array around a satellite. GPS receivers of two satellites (a satellite A and a satellite B) are used for receiving navigation satellite signals and respectively calculating to obtain positioning information. An inter-satellite communication device and an inter-satellite communication antenna array between the two satellites form an inter-satellite communication link for one-way communication, and the two satellites are respectively provided with an isospinning antenna array on the plus X-plane and the minus X-plane. The inter-satellite communication device of the satellite B is used for receiving GPS positioning information of the satellite B through an RS422 interface and modulating and amplifying the GPS positioning information of the satellite B into radio-frequency signals, and the radio-frequency signals are radiated to the whole space through the inter-satellite communication antenna. The inter-satellite communication device of the satellite A is used for receiving signals transmitted by the satellite B, demodulating to restore the original GPS measurement information of the satellite B, and transmitting the information to the GPS receiver of the satellite A through a CAN (Controller Area Network) bus. Relative positioning calculation is carried out in the GPS receiver of the satellite A, results are broadcast through the CAN bus, and thus, one inter-satellite baseline measurement is completed.
Description
Technical field
The present invention relates to base measurement method between a kind of satellite star.
Background technology
The satellite small scale is formed into columns to be diversion and is meant the satellite by two above close together; With certain a bit is that benchmark keeps specific formation configuration; Orbit the earth with the identical orbital period then; Through the inter-satellite link collaborative work, accomplish high-acruracy survey tasks such as specific useful load such as InSAR between two satellites of formation flight.InSAR forms into columns strict to the baseline area requirement, and the yardstick of formation configuration is less, and the measuring accuracy of relative position between two stars has been proposed higher requirement.The line of two satellite barycenter constitutes baseline between star, and actual measurement is the distance between the two star gps antenna phase centers, and needing to convert obtain distance between two star barycenter.
At present; China is based on communication distance measuring sign indicating number between star at rail formation flight satellite constellation and accomplishes that relative distance measures; Precision is lower; All be with flying to carry out under the state base measurement between star at the intersection docked flight devices such as satellite and airship that utilize the GPS receiver to carry out relative positioning that grind at present, precision is not high, and technology does not yet obtain ripe application.Design difficulty mainly contains: (1) GPS receiver should be accomplished absolute fix, regularly absolute, also will accomplish base measurement between the high precision double star, how to design the function and the index of GPS receiver and gps antenna; (2) because there is variation in the relative position between two stars, how to adopt the mode (antenna amount of communication antenna and installation site between star) of rational group of battle array,, reduce interference region and communication disruption zone as far as possible for communication between star provides reliable and stable radio-frequency channel.
Summary of the invention
Technology of the present invention is dealt with problems and is: the deficiency that overcomes prior art; During providing a kind of small scale to form into columns to be diversion based on high precision base measurement method between the star of GPS; Solved before formation flight, be diversion during and high-acruracy survey problem between the star after the formation flight, and realize Autonomous Control, keep structural stability to submit necessary information for the formation satellite through these high precision measuring datas.
Technical solution of the present invention is: form into columns and be diversion satellite based on base measurement method between the star of GPS, step is following:
(1) establish two satellites of participating in base measurement and be respectively A star and B star, the A star+the X face and-communication antenna between a star is installed on the X face respectively, the electric axis line of communication antenna is parallel with the X axle between star, the communication antenna position is higher than the propelling storehouse between the star the on-X face; The A star-gps antenna is installed on the Z face, the electric axis line of gps antenna points to zenith direction, 0 ° of position angle of gps antenna point to the A star+X-direction, the gps antenna altitude range is 300～310mm, communication equipment between A star body set inside GPS receiver and star; Described each face of A star confirms that according to A star body coordinate system wherein the body coordinate system initial point of A star is the satellite barycenter, and the X axle points to the satellite flight direction, points to the earth's core during the flight of Z axle, and the Y axle becomes right-handed system with X axle, Z axle;
(2) the B star+the X face and-communication antenna between a star is installed on the X face respectively, the electric axis line of communication antenna is parallel with the X axle between star, the communication antenna position is higher than and advances the storehouse between the star the on-X face; The B star-gps antenna is installed on the Z face, the electric axis line of gps antenna points to zenith direction, 0 ° of position angle of gps antenna point to the B star+X-direction, the gps antenna altitude range is 215mm～225mm, communication equipment between B star body set inside GPS receiver and star; Described each face of B star confirms that according to B star body coordinate system wherein the body coordinate system initial point of B star is the satellite barycenter, and the X axle points to the satellite flight direction, points to the earth's core during the flight of Z axle, and the Y axle becomes right-handed system with X axle, Z axle;
(3) the GPS receiver on the A star receives GPS navigation star signal, carries out the absolute fix of A star and resolves, and gather original measurement information in real time; GPS receiver on the B star receives GPS navigation star signal, carries out the absolute fix of B star and resolves, and gather original measurement information in real time;
(4) the GPS receiver on the B star with the original measurement information that collects through communication antenna between communication equipment between the star of B star and two stars to space radiation; When the distance between A star and the B star enters in the setting range; Communication equipment receives the signal that communication equipment is launched between the B star through communication antenna between two stars between the star of A star, and demodulation recovers the original measurement information of B star GPS receiver and it is passed to the GPS receiver of A star;
(5) after the GPS receiver of A star is received the original measurement information of B star GPS receiver; Adopting two difference carrier phase measurements to carry out relative positioning with two difference pseudo range measurement methods measures; And give the Star Service computing machine of A star through the CAN bus transfer with the relative positioning measurement result, accomplish a base measurement.
Communication antenna adopts with the pattern of revolving the group battle array between described star, and communication antenna is connected to two prevention at radio-frequency port of communication equipment between star between configurations match network, two stars through matching network.
Communication equipment and B star GPS receiver are through the RS422 interface communication between described B star;
Communication equipment and A star GPS receiver are through the CAN bus communication between described A star.
The present invention's advantage compared with prior art is:
(1) for guaranteeing that communication is reliable continuously between star, the inventive method has designed antenna installation site and height, and adopts with communication antenna battle array between the star that revolves the group battle array, can guarantee wireless signal to the radiation of full spatial domain, guarantees in each stage loss of formation flight minimum;
(2) in order to guarantee reliability and the influence that reduces the bit error rate; When adopting the inventive method; Can communication control processor, GPS receiver between the A star be adopted the Hot Spare design; Communication equipment is not established slave computer between the B star, passes through RS-422 interface communication, simplified apparatus when satisfying mission requirements with B star GPS receiver;
(3) spaceborne GPS receiver all has the carrier phase measurement ability, can export high-precision raw measurement data, and can be transferred to land station.The GPS receiver of A star adopts two difference carrier phase measurement methods to carry out relative positioning and measures; Set up two difference carrier phase equations through original observed quantity, and eliminate or slacken the same or similar error that is comprised in the double star observed reading through differentiation method and reach and carry out relative positioning and measure.In addition, when satellite passed by, land station can receive the raw measurement data of double star, carried out ground validation.
Description of drawings
Fig. 1 is the schematic diagram of the inventive method;
Fig. 2 for A star gps antenna of the present invention at-Z face scheme of installation;
Fig. 3 for B star gps antenna of the present invention at-Z face scheme of installation;
Fig. 4 for communication antenna between A star of the present invention at+X face scheme of installation;
Fig. 5 for communication antenna between A star of the present invention at-X face scheme of installation.
Embodiment
As shown in Figure 1, be the schematic diagram of the inventive method.Be respectively A star and B star if participate in two satellites of base measurement, then should distinguishing between GP configuring S receiving antenna, GPS receiver, star communication antenna battle array between communication equipment, star on two satellites.Carrying out between star before the base measurement, the GPS receiver on two satellites all receives GPS navigation star signal, carries out absolute fix separately respectively and resolves, and gather original measurement information in real time.Communication equipment between the star of B star passed to the original measurement information that collects by GPS receiver on the B star through the RS-422 interface, by communication equipment between star modulate and through communication antenna battle array between star with original measurement information to space radiation.When the distance between two satellites enters into setting range; Communication equipment is received the signal of B star communication equipment emission between the star of A star through communication antenna battle array between star; Carry out demodulation and recover the original measurement information of B star GPS receiver, and it is passed to the GPS receiver of A star through the CAN bus communication.After the GPS receiver of A star is received packet, carry out base measurement, be engaged in for the A star through the CAN bus transfer result after calculating is accomplished, so far accomplish a base measurement.
The reception of GPS receiving antenna is 22000 kilometers GPS navigation star seat signal from orbit altitude.
The GPS receiver of B star carries out absolute fix, orbit determination is handled, and the GPS receiver of A star adopts two difference carrier phase measurements to carry out relative positioning with two difference pseudo range measurement methods and measures.Set up two difference pseudorange observation equations or two poor carrier phase observation equation through original observed quantity, and eliminate or slacken the same or similar error that is comprised in the double star observed reading through differentiation method and reach and carry out relative positioning and measure.
Can take by stages, classification measurement strategies during measurement, when two astrologies distance surpasses 5km, select to be applicable to two difference pseudo range measurement methods of long base measurement, can obtain base measurement precision less than 2m; Select to be applicable to during in two stars distances and two difference carrier phase measurement methods of short base measurement can obtain base measurement precision less than 10cm less than 5km.
Communication equipment has emission function between the star of B star, adopts the BPSK modulation system.Communication equipment has receiving function between the star of A star, adopts the reception double copies communication system of data check measure.Approach in the process of being diversion at A, B two stars; The GPS receiver of B star carries out framing, adds check bit the data that receive, and the data of output are sent between the B star communication equipment and directly transferred, and communication equipment is given communication antenna between the star of B star between the B star; Signal is propagated in the free space environment; Communication antenna receives wireless signal between the star of A star, and signal is forwarded to communication equipment between the star of A star, and communication equipment carries out demodulation, information checking to two paths of signals between star.
The body coordinate system initial point of A star is the satellite barycenter, and the X axle points to the satellite flight direction, points to the earth's core during the flight of Z axle, and the Y axle becomes right-handed system with X, Z axle.As shown in Figure 2, the gps antenna of A star the A star-near+X side and-Y side center of antenna distance+X side 100mm, distance-Y side 315mm are installed on the Z face.。The electric axis line of gps antenna points to zenith direction; A star+X-direction is pointed at 0 ° of position angle of gps antenna, through test, is installing under the envelope maximum height limit; The gps antenna altitude range is that each is maximum to gain in 300～310mm scope, confirms that therefore antenna height is in this scope.
The body coordinate system initial point of B star is the satellite barycenter, and the X axle points to the satellite flight direction, points to the earth's core during the flight of Z axle, and the Y axle becomes right-handed system with X, Z axle.As shown in Figure 3, the gps antenna of B star be installed in the B star-the Z face on, near-Y side and-X side center of antenna distance-Y side 100mm, distance-X side 170mm are installed.The electric axis line of gps antenna points to zenith direction, 0 ° of position angle sensing B star of gps antenna+X-direction, through test, the gps antenna altitude range is that therefore each confirm that to the gain maximum gps antenna height is in this scope in 215mm～225mm scope.
In order to receive nautical star signal as much as possible, gps antenna must have bigger directional diagram overlay area, and works in a good electromagnetism environment, avoids being blocked and disturbing as far as possible.The installation principle of gps antenna is following:
(1) gps antenna is loaded on satellite-Z face, and electrical boresight of antenna line points to zenith direction, around antenna, reduces to block in 0～85 ° of scope as far as possible, works in a good electromagnetism environment;
(2) in order to reduce the influence of multipath effect, the antenna frame height of trying one's best, the too high scattering problem that has again of antenna also will be taken all factors into consideration the problem of satellite envelope; Therefore, through test, as the high 304mm of gps antenna of A star, the high 220mm of the gps antenna of B star, this moment, the gain of gps antenna all directions was maximum;
(3) satellite body coordinate system+X-direction is pointed at 0 of antenna ° of position angle, and with this as the starting point of demarcating phase center;
(4) alignment error of gps antenna on celestial body guarantees less than ± 0.5mm (1 σ, three) at the dress asterisk surely;
When flying over the ground, realize on two satellites being diversion; Relative position between two satellites exists and changes, radiation pattern need cover with the X axle be axis ± 66 degree scopes because satellite posture adjustment and orbit maneuver; Antenna is preferably the total space and covers, and guarantees good intersatellite communication link.The design of communication antenna battle array is as follows between star:
(1) between star the communication antenna battle array by between star between communication antenna, star communication network, cable form; Communication antenna adopts with the pattern of revolving the group battle array between the star of A, B two stars; Configurations match network, each antenna are connected to two prevention at radio-frequency port of communication equipment between star through matching network;
(2) the communication antenna battle array is formed with the antenna that revolves the group battle array by two between the star of every star, and when two satellites one in front and one in back flew, two satellite antenna forward radiation districts were relative, and the link requirement is satisfied in gain.When satellite line and heading when vertical, with limit nearer antenna work apart, still satisfy the link requirement.When the attitude of satellite changes, form nearly circular radiation directional diagram with revolving antenna, all radiationless blind area of any direction, and the antenna work that backups each other, reliability is high;
(3) between the star of A star communication antenna be installed in the A star+X face and-X face on, antenna axis is parallel with the X face.Communication antenna 1 is installed in A star+X face between star, and through test, total space gain was maximum when setting height(from bottom) was 354mm ± 5mm.Communication antenna 2 is installed at A star-X face between star, and through test, total space gain was maximum when setting height(from bottom) was 404mm ± 5mm.Therefore confirm that the communication antenna height is in this scope between two stars.
(4) B luck row track is projected as the oblique dotted line of Fig. 4 on A star+X face, and B luck row track is projected as the oblique dotted line of Fig. 5 on A star-X face.Relative for fear of interference region, between 2 stars will try one's best far in A star+X face and the projection the on-X face apart from B luck row track in the installation site of communication antenna on celestial body+X face and-X face.As shown in Figure 4, communication antenna 1 is installed near+Z side at A star+X face between star, center of antenna distance+Y side 590mm, distance+Z side 130mm.As shown in Figure 5, between star communication antenna 2 A star-X face near+Y ,+the Z side installs center of antenna distance+Y side 360mm, distance+Z side 310mm.
(5) installation site is suitably away from the equipment that electromagnetic interference is arranged, suitably away from electrical propulsion arrangement;
(6) to consider the occlusion effect of miscellaneous equipment in the installation process, can not be blocked in the communication antenna communication zone between star, and have the good gain characteristic;
(7) the character of surface more complicated-the X face, the communication antenna position is higher than and advances the storehouse between star.
Communication antenna installation principle and A satellite-based are originally identical between the star of B star, and difference is, requires the design and installation height according to satellite installation envelope requirement and gain.In the envelope claimed range, through test, antenna height antenna total space gain when 234 ± 2mm is maximum, confirms that therefore setting height(from bottom) is 234mm.
In addition, the original measurement information of A star and B star all can reach land station through under the satellite-ground link, resolves on ground with checking and resolves the result at rail.
The content of not doing to describe in detail in the instructions of the present invention belongs to those skilled in the art's known technology.
Claims (4)
1. form into columns and be diversion satellite, it is characterized in that step is following based on base measurement method between the star of GPS:
(1) establish two satellites of participating in base measurement and be respectively A star and B star, the A star+the X face and-communication antenna between a star is installed on the X face respectively, the electric axis line of communication antenna is parallel with the X axle between star, the communication antenna position is higher than the propelling storehouse between the star the on-X face; The A star-gps antenna is installed on the Z face, the electric axis line of gps antenna points to zenith direction, 0 ° of position angle of gps antenna point to the A star+X-direction, the gps antenna altitude range is 300～310mm, communication equipment between A star body set inside GPS receiver and star; Described each face of A star confirms that according to A star body coordinate system wherein the body coordinate system initial point of A star is the satellite barycenter, and the X axle points to the satellite flight direction, points to the earth's core during the flight of Z axle, and the Y axle becomes right-handed system with X axle, Z axle;
(2) the B star+the X face and-communication antenna between a star is installed on the X face respectively, the electric axis line of communication antenna is parallel with the X axle between star, the communication antenna position is higher than and advances the storehouse between the star the on-X face; The B star-gps antenna is installed on the Z face, the electric axis line of gps antenna points to zenith direction, 0 ° of position angle of gps antenna point to the B star+X-direction, the gps antenna altitude range is 215mm～225mm, communication equipment between B star body set inside GPS receiver and star; Described each face of B star confirms that according to B star body coordinate system wherein the body coordinate system initial point of B star is the satellite barycenter, and the X axle points to the satellite flight direction, points to the earth's core during the flight of Z axle, and the Y axle becomes right-handed system with X axle, Z axle;
(3) the GPS receiver on the A star receives GPS navigation star signal, carries out the absolute fix of A star and resolves, and gather original measurement information in real time; GPS receiver on the B star receives GPS navigation star signal, carries out the absolute fix of B star and resolves, and gather original measurement information in real time;
(4) the GPS receiver on the B star with the original measurement information that collects through communication antenna between communication equipment between the star of B star and two stars to space radiation; When the distance between A star and the B star enters in the setting range; Communication equipment receives the signal that communication equipment is launched between the B star through communication antenna between two stars between the star of A star, and demodulation recovers the original measurement information of B star GPS receiver and it is passed to the GPS receiver of A star;
(5) after the GPS receiver of A star is received the original measurement information of B star GPS receiver; Adopting two difference carrier phase measurements to carry out relative positioning with two difference pseudo range measurement methods measures; And give the Star Service computing machine of A star through the CAN bus transfer with the relative positioning measurement result, accomplish a base measurement.
2. formation according to claim 1 is diversion satellite based on base measurement method between the star of GPS; It is characterized in that: communication antenna adopts with the pattern of revolving the group battle array between described star; Communication antenna is connected to two prevention at radio-frequency port of communication equipment between star between configurations match network, two stars through matching network.
3. formation according to claim 1 is diversion satellite based on base measurement method between the star of GPS, it is characterized in that: communication equipment and B star GPS receiver are through the RS422 interface communication between described B star.
4. formation according to claim 1 is diversion satellite based on base measurement method between the star of GPS, it is characterized in that: communication equipment and A star GPS receiver are through the CAN bus communication between described A star.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110241765 CN102323597B (en) | 2011-08-19 | 2011-08-19 | GPS (Global Positioning System)-based inter-satellite baseline measurement method for flight of formed array around satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110241765 CN102323597B (en) | 2011-08-19 | 2011-08-19 | GPS (Global Positioning System)-based inter-satellite baseline measurement method for flight of formed array around satellite |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102323597A true CN102323597A (en) | 2012-01-18 |
| CN102323597B CN102323597B (en) | 2013-06-19 |
Family
ID=45451376
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201110241765 Active CN102323597B (en) | 2011-08-19 | 2011-08-19 | GPS (Global Positioning System)-based inter-satellite baseline measurement method for flight of formed array around satellite |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102323597B (en) |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103217691A (en) * | 2012-01-19 | 2013-07-24 | 中国电力工程顾问集团华北电力设计院工程有限公司 | High-precision baseline measuring and phase correcting method |
| CN104135322A (en) * | 2014-08-01 | 2014-11-05 | 中国人民解放军国防科学技术大学 | Femto satellite and distributed space detection system |
| CN104333408A (en) * | 2014-09-26 | 2015-02-04 | 航天东方红卫星有限公司 | Inter-satellite communication system used for realizing high-dynamic and low-delay space teleoperation |
| CN104536026A (en) * | 2015-01-08 | 2015-04-22 | 中国航空无线电电子研究所 | Dynamic-to-dynamic real-time measurement system |
| CN107193290A (en) * | 2017-08-03 | 2017-09-22 | 上海航天控制技术研究所 | The satellites formation payload relative position control method exchanged based on linear momentum |
| CN107846245A (en) * | 2017-11-20 | 2018-03-27 | 航天东方红卫星有限公司 | A kind of design method of synchronous double star GPS raw measurement datas |
| CN108438255A (en) * | 2018-03-14 | 2018-08-24 | 上海航天控制技术研究所 | Satellite is diversion Formation Configuration initial method under a kind of engineering constraints |
| CN108919312A (en) * | 2018-05-03 | 2018-11-30 | 武汉大学 | Independent navigation signal enhancing method based on low orbit satellite |
| CN109597108A (en) * | 2018-12-20 | 2019-04-09 | 上海微小卫星工程中心 | Global navigation satellite system receiver and its operating method |
| CN109885087A (en) * | 2019-03-12 | 2019-06-14 | 中国人民解放军军事科学院国防科技创新研究院 | The double star short distance formation method of micro-nano satellite |
| CN111175797A (en) * | 2020-02-02 | 2020-05-19 | 上海交通大学 | Multi-GNSS receiver collaborative navigation method based on virtual centroid |
| CN111786087A (en) * | 2020-08-07 | 2020-10-16 | 上海卫星工程研究所 | Earth data transmission antenna layout method suitable for inter-satellite transmission |
| CN112924999A (en) * | 2021-01-14 | 2021-06-08 | 华南理工大学 | Unmanned aerial vehicle positioning method, system, device and medium |
| CN114562991A (en) * | 2021-12-27 | 2022-05-31 | 北京控制工程研究所 | Relativistic astronomical effect navigator based on star sensor assistance and navigation method thereof |
| CN116743241A (en) * | 2023-08-16 | 2023-09-12 | 天津讯联科技有限公司 | Inter-satellite link system implementation method suitable for satellite-surrounding flying formation |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101833080A (en) * | 2009-03-12 | 2010-09-15 | 周迅 | Method for measuring attitude of carrier by using additional constraint condition of GPS system |
-
2011
- 2011-08-19 CN CN 201110241765 patent/CN102323597B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101833080A (en) * | 2009-03-12 | 2010-09-15 | 周迅 | Method for measuring attitude of carrier by using additional constraint condition of GPS system |
Non-Patent Citations (1)
| Title |
|---|
| 梁志国等: "GPS相对定位在星间测量中的应用", 《航天器工程》 * |
Cited By (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103217691A (en) * | 2012-01-19 | 2013-07-24 | 中国电力工程顾问集团华北电力设计院工程有限公司 | High-precision baseline measuring and phase correcting method |
| CN104135322A (en) * | 2014-08-01 | 2014-11-05 | 中国人民解放军国防科学技术大学 | Femto satellite and distributed space detection system |
| CN104135322B (en) * | 2014-08-01 | 2017-02-15 | 中国人民解放军国防科学技术大学 | Femto satellite and distributed space detection system |
| CN104333408A (en) * | 2014-09-26 | 2015-02-04 | 航天东方红卫星有限公司 | Inter-satellite communication system used for realizing high-dynamic and low-delay space teleoperation |
| CN104333408B (en) * | 2014-09-26 | 2017-09-29 | 航天东方红卫星有限公司 | A kind of Inter-satellite Communication System for being used to realize high dynamic and low time delay Space teleoperation |
| CN104536026A (en) * | 2015-01-08 | 2015-04-22 | 中国航空无线电电子研究所 | Dynamic-to-dynamic real-time measurement system |
| CN107193290B (en) * | 2017-08-03 | 2019-12-03 | 上海航天控制技术研究所 | Satellites formation payload relative position control method based on linear momentum exchange |
| CN107193290A (en) * | 2017-08-03 | 2017-09-22 | 上海航天控制技术研究所 | The satellites formation payload relative position control method exchanged based on linear momentum |
| CN107846245A (en) * | 2017-11-20 | 2018-03-27 | 航天东方红卫星有限公司 | A kind of design method of synchronous double star GPS raw measurement datas |
| CN108438255A (en) * | 2018-03-14 | 2018-08-24 | 上海航天控制技术研究所 | Satellite is diversion Formation Configuration initial method under a kind of engineering constraints |
| CN108919312A (en) * | 2018-05-03 | 2018-11-30 | 武汉大学 | Independent navigation signal enhancing method based on low orbit satellite |
| CN109597108A (en) * | 2018-12-20 | 2019-04-09 | 上海微小卫星工程中心 | Global navigation satellite system receiver and its operating method |
| CN109885087B (en) * | 2019-03-12 | 2019-10-29 | 中国人民解放军军事科学院国防科技创新研究院 | The double star short distance formation method of micro-nano satellite |
| CN109885087A (en) * | 2019-03-12 | 2019-06-14 | 中国人民解放军军事科学院国防科技创新研究院 | The double star short distance formation method of micro-nano satellite |
| CN111175797A (en) * | 2020-02-02 | 2020-05-19 | 上海交通大学 | Multi-GNSS receiver collaborative navigation method based on virtual centroid |
| CN111175797B (en) * | 2020-02-02 | 2023-11-03 | 上海交通大学 | Virtual centroid-based multi-GNSS receiver collaborative navigation method |
| CN111786087A (en) * | 2020-08-07 | 2020-10-16 | 上海卫星工程研究所 | Earth data transmission antenna layout method suitable for inter-satellite transmission |
| CN112924999A (en) * | 2021-01-14 | 2021-06-08 | 华南理工大学 | Unmanned aerial vehicle positioning method, system, device and medium |
| CN112924999B (en) * | 2021-01-14 | 2023-08-22 | 华南理工大学 | Unmanned aerial vehicle positioning method, system, device and medium |
| CN114562991A (en) * | 2021-12-27 | 2022-05-31 | 北京控制工程研究所 | Relativistic astronomical effect navigator based on star sensor assistance and navigation method thereof |
| CN114562991B (en) * | 2021-12-27 | 2024-02-09 | 北京控制工程研究所 | Relativistic astronomical effect navigator based on star sensor assistance and navigation method thereof |
| CN116743241A (en) * | 2023-08-16 | 2023-09-12 | 天津讯联科技有限公司 | Inter-satellite link system implementation method suitable for satellite-surrounding flying formation |
| CN116743241B (en) * | 2023-08-16 | 2023-10-13 | 天津讯联科技有限公司 | Inter-satellite link system implementation method suitable for satellite-surrounding flying formation |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102323597B (en) | 2013-06-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102323597B (en) | GPS (Global Positioning System)-based inter-satellite baseline measurement method for flight of formed array around satellite | |
| CA2965312C (en) | Systems, methods and computer-readable media for improving platform guidance or navigation using uniquely coded signals | |
| EP2843441B1 (en) | System and method for detecting false global navigation satellite system satellite signals | |
| US20200225359A1 (en) | System and method for detecting false global navigation satellite system satellite signals | |
| US10234564B2 (en) | System and method for determining the direction of a false GNSS satellite signal transmitter | |
| JP6080851B2 (en) | High-performance time synchronization and time transfer of satellite constellations using cross-link ranging and accurate time sources | |
| CN108196272A (en) | A kind of satellite navigation positioning device and method based on real-time accurate One-Point Location | |
| CN107395309A (en) | High accuracy relative ranging and method for synchronizing time based on inter-satellite link | |
| WO1995008778A1 (en) | Navigation system using re-transmitted gps | |
| CN104536026A (en) | Dynamic-to-dynamic real-time measurement system | |
| CN109061701B (en) | Phase difference component measurement method suitable for satellite-borne multi-antenna fusion carrier | |
| US20240025564A1 (en) | Monitoring system, monitoring satellite, and communication satellite | |
| CN107782317B (en) | A kind of unidirectional navigation locating method of deep space that falls VLBI | |
| WO2015142985A1 (en) | Gnss satellite signal spoofer direction determination | |
| US8952847B2 (en) | System of geographical location of a radio signal transmitter located on the earth's surface, and associated method of distributed interferometry | |
| WO2017066750A1 (en) | Triple difference formulation for formation flight | |
| KR101129255B1 (en) | Active gimbal for gps antenna using attitude sensor | |
| CN105371854A (en) | Spacecraft attitude determination method utilizing same-beam interferometric measurement of ground measurement station | |
| Thevenet et al. | Formation Flying Radio-Frequency metrology validation and performance: The PRISMA case | |
| Kube et al. | GNSS-based curved landing approaches with a virtual receiver | |
| Dianetti et al. | Spacecraft Proximity Operations Using Ultra-Wideband Communication Devices | |
| KR101513100B1 (en) | Apparatus and method for spoofing detection with single antenna gnss receiver and inertial measurement unit | |
| Shim et al. | Single Frequency RTK Relative Navigation for Autonomous Formation Flying Mission of SNUGLITE-III CubeSat | |
| KR20120071238A (en) | System for global earth navigation using inclined geosynchronous orbit satellite | |
| Hartrampf et al. | LION navigator for transfer to GEO using electric propulsion |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C53 | Correction of patent of invention or patent application | ||
| CB03 | Change of inventor or designer information |
Inventor after: Zhang Lei Inventor after: Cang Rongchun Inventor after: Lu Bo Inventor after: Zhao Zhiming Inventor after: Liu Yiwei Inventor after: Gao Xiaoyan Inventor after: Yang Xiaojiang Inventor after: Li Dongjun Inventor after: Liu Xiaorong Inventor before: Zhang Lei Inventor before: Cang Rongchun Inventor before: Lu Bo Inventor before: Zhao Zhiming Inventor before: Liu Yiwei Inventor before: Gao Xiaoyan Inventor before: Yang Xiaojiang Inventor before: Li Dongjun Inventor before: Liu Xiaorong |