CN112578418B - Heaven and earth joint orbit calculation method for navigation constellation measurement and control management - Google Patents
Heaven and earth joint orbit calculation method for navigation constellation measurement and control management Download PDFInfo
- Publication number
- CN112578418B CN112578418B CN202011329906.XA CN202011329906A CN112578418B CN 112578418 B CN112578418 B CN 112578418B CN 202011329906 A CN202011329906 A CN 202011329906A CN 112578418 B CN112578418 B CN 112578418B
- Authority
- CN
- China
- Prior art keywords
- measurement
- equation
- observation
- satellite
- data
- 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.)
- Active
Links
- 238000005259 measurement Methods 0.000 title claims abstract description 109
- 238000004364 calculation method Methods 0.000 title claims abstract description 22
- 238000000034 method Methods 0.000 claims abstract description 41
- 230000007774 longterm Effects 0.000 claims abstract description 24
- 230000004927 fusion Effects 0.000 claims abstract description 9
- 239000011159 matrix material Substances 0.000 claims description 31
- 238000007781 pre-processing Methods 0.000 claims description 13
- 238000005070 sampling Methods 0.000 claims description 8
- 238000006243 chemical reaction Methods 0.000 claims description 6
- 238000012937 correction Methods 0.000 claims description 6
- 238000012545 processing Methods 0.000 claims description 5
- 239000005433 ionosphere Substances 0.000 claims description 3
- 239000005436 troposphere Substances 0.000 claims description 3
- 230000002457 bidirectional effect Effects 0.000 abstract description 4
- 230000007812 deficiency Effects 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 5
- 230000001502 supplementing effect Effects 0.000 description 2
- 239000013598 vector Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006735 deficit Effects 0.000 description 1
- 238000013213 extrapolation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000004083 survival effect Effects 0.000 description 1
Images
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
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/35—Constructional details or hardware or software details of the signal processing chain
- G01S19/37—Hardware or software details of the signal processing chain
Landscapes
- Engineering & Computer Science (AREA)
- Signal Processing (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Computer Networks & Wireless Communication (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Position Fixing By Use Of Radio Waves (AREA)
Abstract
The invention discloses a space-ground combined orbit calculation method for navigation constellation measurement and control management, which designs a space-ground based whole network orbit calculation process for avoiding rank deficiency of a normal equation, utilizes a long-term prediction ephemeris as a virtual observation for constraint, combines traditional foundation S-band measurement data and a Ka inter-satellite link weighting fusion algorithm, comprehensively processes traditional foundation S-band tracking data and inter-satellite link bidirectional distance measurement, obtains a precise ephemeris product, and is used for supporting navigation satellite measurement and control management and inter-satellite link management.
Description
Technical Field
The invention belongs to the technical field of aerospace measurement and control, and particularly relates to a space-ground combined orbit calculation method for navigation constellation measurement and control management.
Background
The traditional satellite measurement and control system mainly relies on a ground-based S/X waveband measurement and control station to track an in-orbit satellite, collect various measurement data (ranging, speed measuring and angle measuring) and send the measurement data to a measurement and control center to calculate the satellite orbit, thereby supporting the satellite measurement and control management and in-orbit application. Under the support of a foundation system, the satellites lack mutual connection, and the current measurement and control center collects station measurement data by establishing a single-satellite task environment to complete independent orbit calculation of each satellite, including orbit determination and forecast.
The navigation constellation utilizes a Satellite-borne Ka-band phased array antenna to establish an Inter-Satellite Link (ISL), adopts a Time Division Multiple Access (TDMA) mode and a plurality of satellites to carry out Inter-Satellite relative ranging, and can be used for supporting Satellite orbit calculation. Compared with the traditional foundation system, the method has the advantages that: (1) inter-satellite measurement is not restricted by visible arc segments of a ground station, and a longer continuous tracking arc segment is provided; (2) the method is not influenced by atmospheric propagation delay, and the measurement precision is higher; (3) the method depends on the support of a small number of ground measurement and control stations, saves ground measurement and control resources, and improves the autonomous survival capability of the satellite.
Compared with the traditional ground-based measurement data, the inter-satellite distance measurement comprises the relative position information of two satellites, the traditional single-satellite orbit calculation mode cannot be adopted, and the whole-network orbit determination method needs to be adopted. In addition, under the condition of no ground station support, absolute space position reference is lacked when the whole network orbit determination is carried out by only utilizing inter-satellite distance measurement, and the normal equation deficit rank of the orbit parameter estimation is obtained. Therefore, a multi-source information comprehensive constraint method is provided, which comprises the steps of (1) a priori orbit based on long-term prediction ephemeris; (2) tracking and measuring a small number of conventional foundation measurement and control stations; (3) bidirectional measurement is carried out on a foundation Ka tracking station; and the information is subjected to weighted fusion, so that the observation condition is improved, and the orbit determination precision is improved.
Disclosure of Invention
The invention aims to provide a space-ground combined orbit calculation method for navigation constellation measurement and control management, and provides an orbit determination method based on long-term prediction ephemeris, traditional foundation measurement and control station data and inter-satellite link Ka two-way distance measurement multi-source information fusion, so that observation conditions are improved, orbit determination precision is improved, and various satellite orbit information required by measurement and control management is generated.
The technical scheme adopted by the invention is that a navigation constellation measurement and control management-oriented heaven-earth joint orbit calculation method is implemented according to the following steps:
according to the starting time of orbit determination t 0 ,t f ]Extracting long-term ephemeris (t) in a central database i ,X i ) Wherein t is i ∈[t 0 ,t f ]，
Represents t i A forecast ephemeris of time;
and 4, weighting and fusing the normal equation 1 and the normal equation 2 with the normal equation 3 and the normal equation 4, and generating the whole network precise ephemeris after orbit determination and solution.
The invention is also characterized in that:
in step 1, according to the fixed orbit arc segment [ t ] 0 ,t f ]Extracting the last generated long-term ephemeris, and taking t 0 Ephemeris of time of day
As initial orbit determination values; and sampling the long-term prediction ephemeris with the sampling time interval of 5 minutes and the sampling data of each time of t i The ephemeris at that time is also used as a virtual observation.
The specific process of preprocessing the multi-extraterrestrial data in the step 2 is as follows: and carrying out troposphere correction and ionosphere correction on multi-extraterrestrial measurement data, wherein the multi-extraterrestrial measurement data comprise distance measurement, speed measurement and angle measurement, the distance measurement is the distance between a satellite and a ground measurement station, the speed measurement is the radial speed of the satellite relative to the ground measurement station, and the angle measurement is the azimuth and the pitch angle of the satellite in a station center horizontal coordinate system.
The concrete process of the Ka inter-satellite link data preprocessing in the step 2 is as follows: and establishing link matching for the Ka inter-satellite link data, namely finding two data of a receiving end A-transmitting end B and a receiving end B-transmitting end A to obtain the bi-directional Ka inter-satellite link data in the same ranging frame, wherein the time interval of the ranging frame is 3s.
The specific process of the step 3 is as follows:
step 3.1, according to t i ∈[t 0 ,t f ]Virtual observation of time of day
Establishing a virtual observation equation:
in the formula (1), y X,i For virtual observation X i Theoretical value of (v) X,i Represents the observed noise with a mean of 0; a. The X,i Represents an observation matrix A X,i ＝[1 1 1 0 0 0 0] T ，
Representing the state of the track to be determined and a kinetic parameter q;
is a unit weight variance; w is a X,i Representing an observation weight matrix; and then superposing the virtual observation equations of the epochs to obtain:
the corresponding normal equation 1 is obtained:
step 3.2, analogously, for t i ∈[t 0 ,t f ]Conventional foundation S-band ranging observation rho at moment i Establishing a distance measurement observation equation:
wherein, the state p to be estimated is consistent with the formula (1); observation matrix A s,i Expressed as:
wherein
ρ x 、ρ y 、ρ z Representing three components in a coordinate system of the survey station, wherein M represents a conversion matrix from a ground-fixed coordinate system to the coordinate system of the survey station; HG represents a conversion matrix from an inertial coordinate system to a ground-fixed coordinate system;
and (3) superposing the ranging observation equation of each epoch to obtain a normal equation 2:
step 3.3, for t i ∈[t 0 ,t f ]Establishing an inter-Ka-satellite link observation equation according to the inter-Ka-satellite link data at the moment to obtain a normal equation 3:
observation matrix A Ka And S-band distance measurement observation matrix A s,i Are consistent in form; weight matrix w Ka Corresponding to Ka band observation data, consisting of
Determining;
step 3.4, for t i ∈[t 0 ,t f ]And (3) establishing observation equation of constellation whole network estimation by Ka inter-satellite link data (2) at the moment:
wherein，
Represents the state of the constellation to be estimated,
representing the state to be estimated of the kth (k =1, \8230;, n) satellite; for inter-satellite link observations between satellites j, k
The observation matrix is:
where ρ = | x j -x k L represents the geometric distance between two stars; w is a ISL A weight matrix representing Ka inter-satellite link data (2) is formed by
Determining;
and (3) superposing the observation equation of the whole network estimation of each epoch constellation to obtain a method equation 4:
the specific process of the step 4 is as follows: and (3) superposing the normal equation 1 and the normal equation 2, the normal equation 3 and the normal equation 4 to obtain:
aligning the vectors p to be estimated before combination, and supplementing the parts of the corresponding observation matrixes needing to be expanded by 0;
solving the linear equation set to obtain the estimated value of the fusion orbit determination as follows:
to estimate the result
And performing long-term orbit prediction as an initial value to obtain the whole network precise ephemeris.
To estimate the result
The specific process of obtaining the whole network precise ephemeris by performing long-term orbit prediction as an initial value is as follows: the estimation result is
And (3) as an initial value of the long-term orbit, combining a dynamics model to perform parallel integral calculation of multi-satellite dynamics of the constellation satellite to obtain the whole network precise ephemeris.
The invention has the beneficial effects that:
the invention relates to a space-ground combined orbit calculation method for navigation constellation measurement and control management, which designs a space-ground whole network orbit calculation process for avoiding rank deficiency of a normal equation, utilizes a long-term prediction ephemeris as a virtual observation for constraint, combines traditional foundation S-band measurement data and a Ka inter-satellite link weighting fusion algorithm, comprehensively processes traditional foundation S-band tracking data and inter-satellite link bidirectional distance measurement, and obtains a precise ephemeris product for supporting navigation satellite measurement and control management and inter-satellite link management.
Drawings
FIG. 1 is a schematic diagram of a conventional single-star measurement and control management system;
FIG. 2 is a schematic view of measurement and control management oriented to navigation constellation;
FIG. 3 is a schematic diagram of a space-ground-based whole network fusion orbit determination process of prior orbit constraints;
FIG. 4 is a schematic diagram of multi-satellite S-outsourced data/Ka-inter-satellite range compatibility format data;
FIG. 5 is a data residual error diagram of inter-satellite link of the Beidou satellite combined orbit determination;
FIG. 6 is a diagram of the combined orbit determination precision of the inter-satellite/satellite-ground links of the Beidou satellites.
Detailed Description
The invention is described in detail below with reference to the drawings and the detailed description.
The invention provides a full-network precise ephemeris and long-term prediction ephemeris product for navigation constellation measurement and control management. The traditional orbit calculation is oriented to satellite measurement and control management, and mainly comprises a single-satellite orbit determination and prediction process, as shown in figure 1; the invention is oriented to navigation constellation measurement and control management, mainly utilizes inter-satellite relative measurement information, and only needs a small amount of ground measurement and control station support as shown in figure 2; as shown in FIG. 3, the invention designs a space-ground combined orbit calculation scheme, which comprises comprehensive data processing flows of various data preprocessing, observation data processing and normal equation production, normal equation superposition and parameter solving, dynamic extrapolation and ephemeris forecast, and can simultaneously meet the requirements of constellation measurement and control management and inter-satellite link management.
In addition, the multi-satellite oriented S-outsider/Ka-inter-satellite distance measurement, speed measurement and angle measurement are data files with compatible formats, and the data type, the satellite SCID and the station ID are used as key index words, as shown in FIG. 4.
The invention relates to a space and ground combined orbit calculation method for navigation constellation measurement and control management, which is implemented according to the following steps:
according to the starting time of orbit determination t 0 ,t f ]Extracting long-term ephemeris (t) at a central database i ,X i ) Wherein t is i ∈[t 0 ,t f ]，
Denotes t i A forecast ephemeris of time;
according to fixed orbit arc section [ t ] 0 ,t f ]Extracting the last generated long-term ephemeris, and taking t 0 Ephemeris of time of day
As initial orbit determination values; and for long-term ephemeris forecastSampling with 5 min sampling time interval and t sampling data i The ephemeris at that time is also used as a virtual observation.
the specific process of the Ka inter-satellite link data preprocessing comprises the following steps: and establishing link matching for the Ka inter-satellite link data, namely finding two data of a receiving end A-transmitting end B and a receiving end B-transmitting end A to obtain the bi-directional Ka inter-satellite link data in the same ranging frame, wherein the time interval of the ranging frame is 3s.
The specific process of preprocessing the multi-extraterrestrial data comprises the following steps: and carrying out troposphere correction and ionosphere correction on multi-extraterrestrial measurement data, wherein the multi-extraterrestrial measurement data comprise distance measurement, speed measurement and angle measurement, the distance measurement is the distance between a satellite and a ground measurement station, the speed measurement is the radial speed of the satellite relative to the ground measurement station, and the angle measurement is the azimuth and the pitch angle of the satellite in a station center horizontal coordinate system.
step 3.1, according to t i ∈[t 0 ,t f ]Virtual observation of time of day
Establishing a virtual observation equation:
in the formula (1), y X,i For virtual observation X i Theoretical value of v X,i Represents the observed noise with a mean of 0; a. The X,i Represents an observation matrix A X,i ＝[1 1 1 0 0 0 0] T ，
Representing the state of the orbit to be determined and a kinetic parameter q;
is a unit weight variance; w is a X,i Representing an observation weight matrix; and then superposing the virtual observation equations of the epochs to obtain:
the corresponding normal equation 1 is obtained:
step 3.2, analogously, for t i ∈[t 0 ,t f ]Conventional ground-based S-band range observation rho at time i Establishing a distance measurement observation equation:
wherein, the state p to be estimated is consistent with the formula (1); observation matrix A s,i Expressed as:
wherein
ρ x 、ρ y 、ρ z Representing three components in a coordinate system of the measuring station, wherein M represents a conversion matrix from a ground-fixed coordinate system to the coordinate system of the measuring station; HG represents a conversion matrix from an inertial coordinate system to a ground-fixed coordinate system;
and superposing the ranging observation equations of the epochs to obtain a normal equation 2:
step 3.3,For t i ∈[t 0 ,t f ]Establishing an inter-Ka-satellite link observation equation according to the inter-Ka-satellite link data at the moment to obtain a normal equation 3:
observation matrix A Ka And S-band distance measurement observation matrix A s,i Are consistent in form; weight matrix w Ka Corresponding to Ka band observation data, consisting of
Determining;
step 3.4, for t i ∈[t 0 ,t f ]And (3) establishing observation equation of constellation whole network estimation by Ka inter-satellite link data (2) at the moment:
wherein,
represents the state of the constellation to be estimated,
representing the state to be estimated of the kth (k =1, \8230;, n) satellite; for inter-satellite link observations between satellites j, k
The observation matrix is:
where ρ = | x j -x k L represents the geometric distance between two stars; w is a ISL A weight matrix representing the Ka inter-satellite link data (2) of
Determining;
and (3) superposing the observation equation of the whole network estimation of each epoch constellation to obtain a method equation 4:
and 4, weighting and fusing the normal equation 1 and the normal equation 2 with the normal equation 3 and the normal equation 4, and generating the whole network precise ephemeris after orbit determination and solution. The specific process of the step 4 is as follows: and (3) superposing the normal equation 1 and the normal equation 2, the normal equation 3 and the normal equation 4 to obtain:
aligning the vectors p to be estimated before combination, and supplementing the parts of the corresponding observation matrixes needing to be expanded by 0;
solving the linear equation set to obtain the estimated value of the fusion orbit determination as follows:
to estimate the result
And performing long-term orbit prediction as an initial value to obtain the whole network precise ephemeris.
To estimate the result
The specific process of obtaining the whole network precise ephemeris by performing long-term orbit prediction as an initial value is as follows: will estimate the result
And (3) as an initial value of the long-term orbit, combining the dynamic model to perform parallel integral calculation of the multi-satellite dynamics of the constellation satellite to obtain the whole network precise ephemeris.
Examples
The method provided by the invention is applied to the engineering in the measurement and control process of the Beidou satellite, the orbit determination precision is obviously higher than that of the traditional S frequency band measurement and control orbit determination mode, and the high-precision characteristic of the inter-satellite link is effectively utilized. By adopting the combined orbit determination method provided by the invention, the data residual rms of the inter-satellite link is about 0.3m, as shown in FIG. 5, the radial precision of the Beidou satellite orbit is better than 0.2 m, and the three-dimensional position precision is better than 3m, as shown in FIG. 6, an effective means is provided for realizing the refined measurement and control of the Beidou satellite.
Through the mode, the invention relates to a space-ground combined orbit calculation method for navigation constellation measurement and control management, which designs a space-ground whole network orbit calculation process for avoiding rank deficiency of a normal equation, utilizes a long-term prediction ephemeris as a virtual observation for constraint, combines traditional foundation S-band measurement data and a Ka inter-satellite link weighting fusion algorithm, comprehensively processes traditional foundation S-band tracking data and inter-satellite link bidirectional distance measurement, and obtains a precise ephemeris product for supporting navigation satellite measurement and control management and inter-satellite link management.
Claims (6)
1. A space and ground combined orbit calculation method for navigation constellation measurement and control management is characterized by being implemented according to the following steps:
step 1, collecting and collecting original external measurement data packets and telemetering data packets, and decoding to obtain multi-satellite external measurement data and Ka inter-satellite link data;
according to the starting time of orbit determination t 0 ,t f ]Extracting long-term ephemeris (t) at a central database i ,X i ) Wherein t is i ∈[t 0 ,t f ]，
Denotes t i A forecast ephemeris of time;
step 2, preprocessing multi-extraterrestrial measurement data and preprocessing Ka inter-satellite link data to obtain orbit determination observation data with a compatible format;
step 3, taking the forecast ephemeris at different moments as virtual observation, and calculating an equation 1 according to orbit determination observation data in a compatible format of each epoch; obtaining a normal equation 2 according to the multi-satellite external measurement data; processing Ka intersatellite link data to obtain a normal equation 3 and a normal equation 4, wherein the specific process is as follows:
step 3.1, according to t i ∈[t 0 ,t f ]And (3) virtual observation of the moment, establishing a virtual observation equation:
in the formula (1), y X,i For theoretical values of virtual observations, v X,i Represents the observed noise with a mean of 0; a. The X,i A representation of an observation matrix is shown,
the method comprises the steps of representing the state to be estimated and the dynamic parameter q of n satellites, wherein k =1, \8230;
is a unit weight variance; w is a X,i Representing an observation weight matrix; and then superposing the virtual observation equations of the epochs to obtain:
the corresponding normal equation 1 is obtained:
step 3.2, analogously, for t i ∈[t 0 ,t f ]Conventional foundation S-band ranging observation rho at moment i Establishing a distance measurement observation equation:
wherein, the k, k =1, \8230, the states p to be estimated of n satellites k Is the same as the formula (1); observation matrix A s,i Expressed as:
wherein
ρ x 、ρ y 、ρ z Representing three components in a coordinate system of the measuring station, wherein M represents a conversion matrix from a ground-fixed coordinate system to the coordinate system of the measuring station; HG represents a conversion matrix from an inertial coordinate system to a ground-fixed coordinate system;
and superposing the ranging observation equations of the epochs to obtain a normal equation 2:
step 3.3, for t i ∈[t 0 ,t f ]Establishing an inter-Ka-satellite link observation equation according to the inter-Ka-satellite link data at the moment to obtain a normal equation 3:
observation matrix A Ka And S-band distance measurement observation matrix A s,i Are consistent in form; weight matrix w Ka Corresponding to Ka band observation data, consisting of
Determining;
step 3.4, for t i ∈[t 0 ,t f ]Establishing an observation equation of the constellation whole network estimation by Ka inter-satellite link data at the moment:
wherein,
represents the state of the constellation to be estimated,
representing the state to be estimated of n satellites, wherein k =1, \8230; for inter-satellite link observations between satellites j, k
The observation matrix is:
where ρ = | x j -x k L represents the geometric distance between two stars; w is a ISL A weight matrix representing Ka inter-satellite link data, consisting of
Determining;
and (3) superposing the observation equation of the whole network estimation of each epoch constellation to obtain a method equation 4:
and 4, weighting and fusing the normal equation 1 and the normal equation 2 with the normal equation 3 and the normal equation 4, and generating the whole network precise ephemeris after orbit determination and solution.
2. The method for computing the heaven-earth combined orbit for navigation constellation measurement and control management according to claim 1, wherein in the step 1, the orbit determination arc segment [ t ] is used 0 ,t f ]Extracting the last generated long-term ephemeris and taking t 0 Ephemeris of time of day
As initial orbit determination values; and sampling the long-term prediction ephemeris with the sampling time interval of 5 minutes and the sampling data of each time of t i The ephemeris at that time is also used as a virtual observation.
3. The method for computing the space-ground combined orbit for the measurement and control management of the navigation constellation according to claim 1, wherein the specific process of preprocessing the multi-satellite external measurement data in the step 2 is as follows: and carrying out troposphere correction and ionosphere correction on multi-extraterrestrial measurement data, wherein the multi-extraterrestrial measurement data comprise distance measurement, speed measurement and angle measurement, the distance measurement is the distance between a satellite and a ground measurement station, the speed measurement is the radial speed of the satellite relative to the ground measurement station, and the angle measurement is the azimuth and the pitch angle of the satellite in a station center horizontal coordinate system.
4. The method for computing the space-ground combined orbit for the measurement and control management of the navigation constellation according to claim 1, wherein the specific process of the Ka inter-satellite link data preprocessing in the step 2 is as follows: and establishing link matching for the Ka inter-satellite link data, namely finding two pieces of data of a receiving end A-transmitting end B and a receiving end B-transmitting end A to obtain the double-unidirectional Ka inter-satellite link data in the same ranging frame, wherein the time interval of the ranging frame is 3s.
5. The method for computing the heaven-earth combined orbit for the measurement and control management of the navigation constellation according to claim 1, wherein the specific process in the step 4 is as follows: and (3) superposing the normal equation 1 and the normal equation 2, the normal equation 3 and the normal equation 4 to obtain:
n in equation 1
In equation 2
In equation 3
In equation 4
Are combined to obtain b from equation 1
In equation 2
In equation 3
In equation 4
Combining to obtain;
the track state p to be determined before combination needs to be aligned, and the part of the corresponding observation matrix needing to be expanded is supplemented by 0;
solving the linear equation set to obtain the estimated value of the fusion orbit determination as follows:
to estimate the result
And performing long-term orbit prediction as an initial value to obtain the whole network precise ephemeris.
6. The method of claim 5, wherein the estimation result is used as a space-ground joint orbit calculation method for measurement and control management of navigation constellation
The specific process of obtaining the whole network precise ephemeris by long-term orbit prediction as an initial value is as follows: the estimation result is
And (3) as an initial value of the long-term orbit, combining a dynamics model to perform parallel integral calculation of multi-satellite dynamics of the constellation satellite to obtain the whole network precise ephemeris.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011329906.XA CN112578418B (en) | 2020-11-24 | 2020-11-24 | Heaven and earth joint orbit calculation method for navigation constellation measurement and control management |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011329906.XA CN112578418B (en) | 2020-11-24 | 2020-11-24 | Heaven and earth joint orbit calculation method for navigation constellation measurement and control management |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112578418A CN112578418A (en) | 2021-03-30 |
| CN112578418B true CN112578418B (en) | 2022-12-27 |
Family
ID=75124199
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011329906.XA Active CN112578418B (en) | 2020-11-24 | 2020-11-24 | Heaven and earth joint orbit calculation method for navigation constellation measurement and control management |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112578418B (en) |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2010117303A1 (en) * | 2009-04-06 | 2010-10-14 | Strelnikov Sergey Vasilevich | Method for providing ephemeris support to the process of controlling the spacecraft of the global navigation satellite system |
| CN104048664A (en) * | 2014-07-01 | 2014-09-17 | 南京航空航天大学 | Autonomous orbit determination method of navigation satellite constellation |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109917431B (en) * | 2019-04-02 | 2021-03-23 | 中国科学院空间应用工程与技术中心 | Method for realizing GNSS satellite autonomous navigation by utilizing DRO orbit and inter-satellite measurement |
-
2020
- 2020-11-24 CN CN202011329906.XA patent/CN112578418B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2010117303A1 (en) * | 2009-04-06 | 2010-10-14 | Strelnikov Sergey Vasilevich | Method for providing ephemeris support to the process of controlling the spacecraft of the global navigation satellite system |
| CN104048664A (en) * | 2014-07-01 | 2014-09-17 | 南京航空航天大学 | Autonomous orbit determination method of navigation satellite constellation |
Non-Patent Citations (2)
| Title |
|---|
| 历史轨道约束信息下的区域站GPS卫星轨道确定;赵齐乐等;《大地测量与地球动力学》;20091031;第28卷(第5期);第81-82页 * |
| 联合星地与星间Ka伪距的北斗三号卫星一体化定轨和时间同步;阮仁桂等;《测绘学报》;20200331;第49卷(第3期);第292-294页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112578418A (en) | 2021-03-30 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| van den IJssel et al. | Precise science orbits for the Swarm satellite constellation | |
| CN111522037B (en) | Autonomous navigation method and navigation system for constellation co-orbital plane satellite | |
| CN110426720B (en) | Method for realizing rapid recovery of GEO satellite after maneuvering through inter-satellite measurement | |
| CN109495156B (en) | Low-orbit broadband satellite communication terminal antenna direction obtaining method based on ephemeris | |
| CN102679985B (en) | A kind of apply between star follow the tracks of the decentralized autonomous navigation method of spacecraft constellation | |
| CN103033188B (en) | The autonomous method for synchronizing time of Navsat based on synthetic aperture observation | |
| Jiang et al. | LEO Doppler-aided GNSS position estimation | |
| CN111522036B (en) | Satellite-usable Beidou satellite centralized constellation autonomous navigation system and navigation method | |
| Hwang et al. | GPS‐Based Orbit Determination for KOMPSAT‐5 Satellite | |
| CN112013834B (en) | Astronomical navigation-based inter-satellite link autonomous recovery method and system | |
| CN116338742A (en) | Real-time high-precision PNT service method based on combined space and earth observation resources | |
| CN112014869A (en) | Astronomical navigation-based inter-satellite link autonomous navigation method and system | |
| Schonfeldt et al. | A system study about a lunar navigation satellite transmitter system | |
| Hwang et al. | Orbit determination accuracy improvement for geostationary satellite with single station antenna tracking data | |
| CN113581501A (en) | System and method suitable for networking low-orbit satellite combined orbit determination | |
| CN117890936B (en) | Low-orbit satellite in-orbit real-time inter-satellite time transfer method and system | |
| CN111487660A (en) | High-precision real-time micro-nano satellite cluster navigation algorithm | |
| CN110554443A (en) | Method for determining earth gravity field based on carrier phase observed value and point acceleration method | |
| El-Mowafy et al. | The impact of orbital and clock errors on positioning from LEO constellations and proposed orbital solutions | |
| CN112578418B (en) | Heaven and earth joint orbit calculation method for navigation constellation measurement and control management | |
| CN114740541B (en) | Asteroid gravitational field inversion method and system based on master-slave star velocity measurement mode | |
| CN115455343A (en) | Multi-station local sensing joint orbit determination method for low-orbit large-scale constellation | |
| Ádám | Estimability of geodetic parameters from space VLBI observables | |
| CN114280915A (en) | Space-based measurement and control time service integrated system | |
| CN114839592B (en) | Non-navigation GEO satellite forwarding type orbit determination method based on low orbit satellite assistance |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP02 | Change in the address of a patent holder |
Address after: No.462, East Xianning Road, Xi'an, Shaanxi 710043 Patentee after: CHINA XI'AN SATELLITE CONTROL CENTER Address before: No.462, East Xianning Road, Xincheng District, Xi'an, Shaanxi 710043 Patentee before: CHINA XI'AN SATELLITE CONTROL CENTER |
|
| CP02 | Change in the address of a patent holder |