CN115096319B - Method and device for determining initial orbit of satellite in star chain based on optical angle measurement data - Google Patents
Method and device for determining initial orbit of satellite in star chain based on optical angle measurement data Download PDFInfo
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Abstract
The invention provides a method and a device for determining an initial orbit of a satellite in a star chain based on optical angle measurement data, which relate to the technical field of astronomical measurement and comprise the following steps: acquiring target data corresponding to a satellite chain satellite; determining the geocentric distance of the target track based on the optical angle measurement data at the initial moment, the position information of the measuring station and a preset observation distance rough value; constructing a standard satellite orbit of a satellite chain satellite and a preset orbit of the satellite chain satellite based on the earth-center distance and the target data, and calculating the position information of the off-satellite point of the standard satellite orbit and the position information of the off-satellite point of the preset orbit; correcting the standard satellite orbit based on the position information of the satellite points of the standard satellite orbit and the position information of the satellite points of the preset orbit to obtain a target standard satellite orbit; iterative optimization is carried out on the target standard satellite orbit based on the optical angle measurement data at the final moment to obtain the initial orbit of the satellite link satellite, and the technical problems of low precision and low efficiency of the existing initial orbit determination method are solved.
Description
Technical Field
The invention relates to the technical field of astronomical measurement, in particular to a method and a device for determining an initial orbit of a satellite in a star chain based on optical angle measurement data.
Background
The method is mainly used for determining the initial orbit of the azimuth pitching angle measurement data, the method for determining the initial orbit of the right ascension and declination data is relatively few, and the initial orbit determination precision is related to the observation time;
in the actual application of the initial orbit determination method for the short arc segment optical data of the low orbit satellite (the orbit height is 200 to 600 kilometers), the calculated error ratio is large, even the number of orbits cannot be obtained, and the method for determining the initial orbit according to two points is the phoenix unicorn angle, and the result cannot be determined because the measured data is too little.
In addition, no method for determining initial orbit specially aiming at optical data of a satellite in a star link exists at present.
The space exploration technology company plans to build a 'star chain' network consisting of about 1.2 ten thousand satellites in space between 2019 and 2024 to provide internet services, wherein 1584 satellites are deployed in a near-earth orbit 550 kilometers above the earth and start to work from 2020.
No effective solution has been proposed to the above problems.
Disclosure of Invention
In view of this, the present invention aims to provide a method and an apparatus for determining an initial orbit of a satellite in a satellite chain based on optical goniometric data, so as to alleviate the technical problems of low accuracy and efficiency of the existing initial orbit determination method.
In a first aspect, an embodiment of the present invention provides a method for determining an initial orbit of a satellite in a satellite chain based on optical goniometric data, including: acquiring target data corresponding to a satellite chain satellite, wherein the target data comprises: optical angle measurement data at the initial moment, optical angle measurement data at the final moment and position information of the measuring station; determining the geocentric distance of the target track based on the optical angle measurement data at the initial moment, the position information of the measuring station and a preset observation distance rough value; constructing a standard satellite orbit and a preset orbit of the satellite chain satellite based on the geocentric distance and the target data, and calculating the position information of the off-satellite point of the standard satellite orbit and the position information of the off-satellite point of the preset orbit; correcting the standard satellite orbit based on the position information of the satellite points of the standard satellite orbit and the position information of the satellite points of the preset orbit to obtain a target standard satellite orbit; and performing iterative optimization on the target standard satellite orbit based on the optical angle measurement data at the final moment to obtain the initial orbit of the satellite-link satellite.
Further, the optical goniometric data includes: measuring time, right ascension and declination; the position information of the station comprises: longitude, latitude, and altitude.
Further, determining the earth-center distance of the target track based on the optical angle measurement data at the initial time, the position information of the measuring station and a preset coarse observation distance value, comprises: a first calculation step, calculating initial position information of the satellite chain satellite in a J2000 inertial coordinate system based on the coarse value of the preset observation distance and the right ascension and the declination at the initial moment; a first determination step of determining the position information of the measuring station in a ground-fixed coordinate system based on the position information of the measuring station at the initial moment, and converting the position information of the measuring station in the ground-fixed coordinate system into the position information of the measuring station in a J2000 inertial coordinate system; a second calculation step of calculating an initial earth-center distance of the target orbit based on the initial position information of the satellite-linked satellite in the J2000 inertial coordinate system and the position information of the survey station in the J2000 inertial coordinate system; if the initial earth center distance is not within the preset range, adjusting the preset observation distance coarse value, and repeatedly executing the first calculating step, the first determining step and the second calculating step until the initial earth center distance is within the preset range, and determining the initial earth center distance within the preset range as the earth center distance of the target track.
Further, the orbit parameters of the standard satellite orbit include: the system comprises a semi-long axis, an inclination angle, an eccentricity, a rising intersection declination, an perigee argument, a mean perigee angle and a first initial epoch, wherein the semi-long axis is the geocentric distance of the target track, the inclination angle is 53 degrees, the eccentricity, the rising intersection declination, the perigee argument and the mean perigee angle are all 0, and the first initial epoch is an initial time; the position and speed of the preset track comprises the following steps: the position of the rover in a J2000 inertial coordinate system, the velocity of the satellite chain satellites at an initial time in the standard satellite orbit, and the first initial epoch.
Further, based on the position information of the satellite points in the standard satellite orbit and the position information of the satellite points in the preset orbit, the standard satellite orbit is corrected to obtain a target standard satellite orbit, which includes: a first correction step of calculating a first mean anomaly based on the position information of the satellite points of the standard satellite orbit at the initial time and the position information of the satellite points of the preset orbit at the initial time, and correcting the standard satellite orbit based on the first mean anomaly to obtain a first intermediate standard satellite orbit; and a second correction step of calculating a first rising intersection right ascension based on the longitude of the satellite chain at the initial time in the first intermediate standard satellite orbit and the longitude of the satellite chain at the initial time in the preset orbit, and correcting the first intermediate standard satellite orbit based on the first rising intersection right ascension to obtain the target standard satellite orbit.
Further, performing iterative optimization on the target standard satellite orbit based on the optical angle measurement data at the final time to obtain an initial orbit of the satellite-link satellite, including: a second determination step of determining a target right ascension and a target declination of the satellite chain at the last moment in the target standard satellite orbit; executing a step of calculating a visibility distance of the target standard satellite orbit at the last moment if a difference value between the target right ascension and the target declination corresponding to the last moment in the optical goniometry data and the right ascension and the declination corresponding to the last moment is greater than a threshold value, calculating position information and an under-satellite point of the satellite chain at the last moment based on the visibility distance and the target right ascension and the target declination, and adjusting a semi-major axis of the target standard satellite orbit based on the position information and the under-satellite point of the satellite chain at the last moment to obtain a final standard satellite orbit; a third correction step of calculating a second approximate point angle based on the position information of the sub-satellite point of the final standard satellite orbit at the last moment and the position information of the sub-satellite point of the preset orbit at the last moment, and correcting the final standard satellite orbit based on the second approximate point angle to obtain a second intermediate standard satellite orbit; a fourth correction step of calculating a second ascent point right ascent based on the longitude of the satellite chain at the last time in the second intermediate standard satellite orbit and the longitude of the satellite chain satellite at the initial time in the preset orbit, and correcting the second intermediate standard satellite orbit based on the first ascent point right ascent point to obtain a third intermediate standard satellite orbit; a third determination step of determining a final right ascension and a final declination of the satellite chain at an initial time in the third intermediate standard satellite orbit; if the difference between the final right ascension warp and the final declination corresponding to the initial time in the optical goniometry data and the right ascension weft corresponding to the initial time in the optical goniometry data is greater than a threshold value, calculating a visibility distance of the third intermediate standard satellite orbit at the initial time, determining a target sub-satellite point based on the visibility distance of the initial time and the right ascension warp and the declination corresponding to the initial time, determining the third intermediate standard satellite orbit as the standard satellite orbit, and determining the target sub-satellite point as the sub-satellite point of the preset orbit, repeatedly executing the first correcting step, the second determining step, the executing step, the third correcting step, the fourth correcting step, and the third determining step until the difference between the final right ascension warp and the final declination and the right ascension weft corresponding to the initial time in the optical goniometry data is less than or equal to the threshold value, and determining the difference between the final right ascension warp and the right ascension weft corresponding to the initial time in the optical goniometry data and the right ascension weft corresponding to the intermediate satellite orbit is less than or equal to the standard satellite chain of the initial satellite in the optical goniometry data.
In a second aspect, an embodiment of the present invention further provides an apparatus for determining an initial orbit of a satellite in a star-link satellite based on optical goniometric data, including: the satellite positioning system comprises an acquisition unit, a determination unit, a construction unit, a correction unit and an optimization unit, wherein the acquisition unit is used for acquiring target data corresponding to a satellite chain satellite, and the target data comprises: optical angle measurement data at the initial moment, optical angle measurement data at the final moment and position information of the measuring station; the determining unit is used for determining the earth center distance of the target track based on the optical angle measurement data at the initial moment, the position information of the measuring station and a preset observation distance rough value; the construction unit is used for constructing a standard satellite orbit and a preset orbit of the satellite chain satellite based on the geocentric distance and the target data, and calculating the position information of the off-satellite point of the standard satellite orbit and the position information of the off-satellite point of the preset orbit; the correction unit is used for correcting the standard satellite orbit based on the position information of the satellite points of the standard satellite orbit and the position information of the satellite points of the preset orbit to obtain a target standard satellite orbit; and the optimization unit is used for performing iterative optimization on the target standard satellite orbit based on the optical angle measurement data at the final moment to obtain the initial orbit of the satellite link satellite.
Further, the optical goniometric data includes: measuring time, right ascension and declination; the position information of the station comprises: longitude, latitude, and altitude.
In a third aspect, an embodiment of the present invention further provides an electronic device, which includes a memory and a processor, where the memory is used to store a program that supports the processor to execute the method in the first aspect, and the processor is configured to execute the program stored in the memory.
In a fourth aspect, an embodiment of the present invention further provides a computer-readable storage medium, on which a computer program is stored.
In the embodiment of the present invention, target data corresponding to a satellite in a satellite chain is obtained, where the target data includes: optical angle measurement data at the initial moment, optical angle measurement data at the final moment and position information of the measuring station; determining the geocentric distance of the target track based on the optical angle measurement data at the initial moment, the position information of the measuring station and a preset observation distance rough value; constructing a standard satellite orbit and a preset orbit of the satellite chain satellite based on the geocentric distance and the target data, and calculating the position information of the off-satellite point of the standard satellite orbit and the position information of the off-satellite point of the preset orbit; correcting the standard satellite orbit based on the position information of the satellite points of the standard satellite orbit and the position information of the satellite points of the preset orbit to obtain a target standard satellite orbit; and performing iterative optimization on the target standard satellite orbit based on the optical angle measurement data at the final moment to obtain the initial orbit of the satellite link satellite, so that the purpose of determining the initial orbit of the satellite link satellite by using the optical angle measurement data is achieved, the technical problem that the existing initial orbit determination method is low in precision and efficiency is solved, and the technical effect of improving the precision and efficiency of determining the initial orbit of the satellite link satellite is achieved.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention will be realized and attained by the structure particularly pointed out in the written description and claims hereof as well as the appended drawings.
In order to make the aforementioned and other objects, features and advantages of the present invention comprehensible, preferred embodiments accompanied with figures are described in detail below.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
Fig. 1 is a flowchart of a method for determining an initial orbit of a satellite in a satellite chain based on optical goniometric data according to an embodiment of the present invention;
fig. 2 is a schematic diagram of an initial orbit determination device for a satellite in a satellite chain based on optical goniometric data according to an embodiment of the present invention;
fig. 3 is a schematic diagram of an electronic device according to an embodiment of the present invention.
Detailed Description
To make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The first embodiment is as follows:
according to an embodiment of the present invention, there is provided an embodiment of a method for determining an initial orbit of a satellite in a satellite chain based on optical goniometric data, wherein the steps illustrated in the flowchart of the drawings may be performed in a computer system such as a set of computer executable instructions, and wherein although a logical order is illustrated in the flowchart, in some cases the steps illustrated or described may be performed in an order different than here.
Fig. 1 is a flowchart of a method for determining an initial orbit of a satellite in a satellite chain based on optical goniometric data according to an embodiment of the present invention, as shown in fig. 1, the method includes the following steps:
step S102, acquiring target data corresponding to a satellite, wherein the target data comprises: optical angle measurement data at the initial moment, optical angle measurement data at the final moment and position information of the measuring station;
the optical goniometric data includes: measuring time, right ascension and declination; the position information of the survey station includes: longitude, latitude and altitude, where one measurement time corresponds to one right ascension and one declination.
Step S104, determining the earth center distance of the target track based on the optical angle measurement data at the initial moment, the position information of the measuring station and a preset observation distance rough value;
step S106, constructing a standard satellite orbit and a preset orbit of the satellite chain satellite based on the geocentric distance and the target data, and calculating the position information of the off-satellite point of the standard satellite orbit and the position information of the off-satellite point of the preset orbit;
step S108, based on the position information of the satellite points of the standard satellite orbit and the position information of the satellite points of the preset orbit, correcting the standard satellite orbit to obtain a target standard satellite orbit;
and S110, performing iterative optimization on the target standard satellite orbit based on the optical angle measurement data at the final moment to obtain the initial orbit of the satellite-link satellite.
In the embodiment of the present invention, target data corresponding to a satellite in a star chain is obtained, where the target data includes: optical angle measurement data at the initial moment, optical angle measurement data at the final moment and position information of the measuring station; determining the geocentric distance of the target track based on the optical angle measurement data at the initial moment, the position information of the measuring station and a preset observation distance rough value; constructing a standard satellite orbit and a preset orbit of the satellite chain satellite based on the geocentric distance and the target data, and calculating the position information of the off-satellite point of the standard satellite orbit and the position information of the off-satellite point of the preset orbit; correcting the standard satellite orbit based on the position information of the satellite points of the standard satellite orbit and the position information of the satellite points of the preset orbit to obtain a target standard satellite orbit; and performing iterative optimization on the target standard satellite orbit based on the optical angle measurement data at the final moment to obtain the initial orbit of the satellite chain satellite, so that the purpose of determining the initial orbit of the satellite chain satellite by using the optical angle measurement data is achieved, the technical problem that the existing initial orbit determination method is low in precision and efficiency is solved, and the technical effect of improving the precision and efficiency of determining the initial orbit of the satellite chain satellite is achieved.
In the embodiment of the present invention, step S104 includes the following steps:
a first calculation step of calculating initial position information of the satellite chain satellite in a J2000 inertial coordinate system based on the coarse value of the preset observation distance and the right ascension and the declination at the initial moment;
a first determination step of determining the position information of the measuring station in a ground-fixed coordinate system based on the position information of the measuring station at the initial moment, and converting the position information of the measuring station in the ground-fixed coordinate system into the position information of the measuring station in a J2000 inertial coordinate system;
a second calculation step of calculating an initial earth center distance of the target orbit based on the initial position information of the satellite chain satellite in the J2000 inertial coordinate system and the position information of the survey station in the J2000 inertial coordinate system;
if the initial earth center distance is not within the preset range, adjusting the preset observation distance coarse value, and repeatedly executing the first calculating step, the first determining step and the second calculating step until the initial earth center distance is within the preset range, and determining the initial earth center distance within the preset range as the earth center distance of the target track.
In the embodiment of the present invention, a coarse predicted observation distance value is first given, it should be noted that the observation distance is used to represent the distance between the observation station and the satellite in the satellite chain, and according to the coarse predicted observation distance value, the right ascension (α) and the declination (δ) at the initial time, the initial position information of the satellite in the J2000 inertial coordinate system is specifically calculated as follows:
then, based on the position information of the measuring station at the initial time, the position information of the measuring station in the earth-fixed coordinate system is determined, and the position information of the measuring station in the earth-fixed coordinate system is converted into the position information of the measuring station in the J2000 inertial coordinate system (
)。
Then, based on the initial position information of the satellite chain satellite in the J2000 inertial coordinate system and the position information of the survey station in the J2000 inertial coordinate system, the initial center-to-center distance of the target orbit is calculated, wherein the initial center-to-center distance r =
，(
)= 
+ (
)。
And finally, adjusting the preset observation distance rough value and repeatedly executing the first calculation step, the first determination step and the second calculation step until the initial earth center distance is within the preset range, and determining the initial earth center distance within the preset range as the earth center distance of the target track.
The upper limit of the preset range is the equator radius of the earth + the maximum orbit height, and the lower limit of the preset range is the equator radius of the earth-the minimum orbit height.
In the embodiment of the invention, after the earth-center distance of the survey station is acquired, the standard satellite orbit and the preset orbit are constructed according to the earth-center distance of the survey station and the target data.
Orbital parameters of standard satellite orbits include: the system comprises a semi-long axis, an inclination angle, an eccentricity, a rising intersection declination, an perigee argument, a mean perigee angle and a first initial epoch, wherein the semi-long axis is the geocentric distance of the target track, the inclination angle is 53 degrees, the eccentricity, the rising intersection declination, the perigee argument and the mean perigee angle are all 0, and the first initial epoch is the initial time.
The track parameters of the preset track comprise: the position of the rover in a J2000 inertial coordinate system, the velocity of the satellite chain satellites at an initial time in the standard satellite orbit, and the first initial epoch.
In the embodiment of the present invention, step S108 includes the following steps:
a first correction step of calculating a first mean anomaly based on the position information of the satellite points of the standard satellite orbit at the initial time and the position information of the satellite points of the preset orbit at the initial time, and correcting the standard satellite orbit based on the first mean anomaly to obtain a first intermediate standard satellite orbit;
and a second correction step of calculating a first rising intersection right ascension based on the longitude of the satellite chain at the initial time in the first intermediate standard satellite orbit and the longitude of the satellite chain at the initial time in the preset orbit, and correcting the first intermediate standard satellite orbit based on the first rising intersection right ascension to obtain the target standard satellite orbit.
In an embodiment of the present invention, the standard satellite orbit and the preset orbit are first converted from the J2000 inertial system to the geostationary coordinate system, and then the positions of the quasi-satellite orbit and the preset orbit in the geostationary coordinate system are converted to the sub-satellite points (i.e., for latitude and longitude representation).
Then, according to the off-satellite points, finding the time when the latitude in the standard satellite orbit is equal to the latitude at the initial time of the preset orbit, calculating the position of J2000, calculating a first mean anomaly according to the position of the J2000 satellite chain satellite at the initial time, and correcting the standard satellite orbit to obtain a first intermediate standard satellite orbit, wherein the calculation process of the first mean anomaly M1 is as follows:
because the original data is too short, the two-body prediction needs to be carried out on the standard satellite orbit to generate the J2000 position speed;
the standard satellite orbit J2000 position velocity is then reconverted to the interstellar point.
Then, searching the moment with the latitude being the same as the initial moment latitude of the preset orbit in the latitude and longitude report of the standard satellite orbit, and calculating the J2000 position speed of the standard orbit at the moment;
and calculating a mean-anomaly angle M according to the position speed.
Wherein the content of the first and second substances,
j2000 position at the initial time for a standard satellite orbit;
is the J2000 position of the standard satellite orbit at the same time as the latitude of the initial moment of the preset orbit.
After the first intermediate standard satellite orbit is obtained, the longitude of the satellite of the star chain at the initial time in the first intermediate standard satellite orbit and the longitude of the satellite of the star chain at the initial time in the preset orbit are used for calculating the right ascension of the first ascending intersection point, and correcting the first intermediate standard satellite orbit based on the first ascension point ascension to obtain a target standard satellite orbit, wherein the first ascension point ascension ran = initial time longitude of the preset orbit-initial time longitude of the first intermediate standard satellite orbit.
The target standard satellite orbit is a satellite orbit obtained after the initial orbit determination of a satellite in a star chain is performed using the right ascension and the declination at the initial time in the optical goniometry data.
In the embodiment of the present invention, step S110 includes the following steps:
a second determination step of determining a target right ascension and a target declination of the satellite chain at the last moment in the target standard satellite orbit;
executing a step of calculating a visibility distance of the target standard satellite orbit at the last moment if a difference value between the target right ascension and the target declination corresponding to the last moment in the optical goniometry data and the right ascension and the declination corresponding to the last moment is greater than a threshold value, calculating position information and an under-satellite point of the satellite chain at the last moment based on the visibility distance and the target right ascension and the target declination, and adjusting a semi-major axis of the target standard satellite orbit based on the position information and the under-satellite point of the satellite chain at the last moment to obtain a final standard satellite orbit;
a third correction step of calculating a second approximate point angle based on the position information of the satellite point of the final standard satellite orbit at the last moment and the position information of the satellite point of the preset orbit at the last moment, and correcting the final standard satellite orbit based on the second approximate point angle to obtain a second intermediate standard satellite orbit;
a fourth correction step of calculating a second ascent point right ascent base on the longitude of the satellite chain satellite at the last time in the second intermediate standard satellite orbit and the longitude of the satellite chain satellite at the initial time in the preset orbit, and correcting the second intermediate standard satellite orbit based on the first ascent point right ascent base to obtain a third intermediate standard satellite orbit;
a third determination step of determining a final right ascension and a final declination of the satellite chain at an initial time in the third intermediate standard satellite orbit;
if the difference value between the final right ascension angle and the final declination corresponding to the initial time in the optical goniometry data is greater than a threshold value, calculating the visibility distance of the third intermediate standard satellite orbit at the initial time, determining a target lower star point based on the visibility distance of the initial time and the right ascension angle and declination corresponding to the initial time, determining the third intermediate standard satellite orbit as the standard satellite orbit, determining the target lower star point as the lower star point of the preset orbit, repeatedly executing the first correction step, the second determination step, the execution step, the third correction step, the fourth correction step and the third determination step until the difference value between the final right ascension angle and the final declination corresponding to the initial time in the optical goniometry data is less than or equal to the threshold value, and determining the difference value between the final right ascension angle and the declination corresponding to the initial time in the optical goniometry data is less than or equal to the initial satellite chain of the intermediate satellite.
In the embodiment of the invention, after a target standard satellite orbit is obtained, the orbit of the target standard satellite orbit is predicted, the target right ascension and the target declination at the last moment of the target standard satellite orbit are calculated, and are compared with the right ascension and the declination at the last moment in optical angle measurement data, if the difference value between the right ascension and the declination corresponding to the target right ascension and the target declination and the last moment in the optical angle measurement data is less than or equal to a threshold value, the initial orbit determination of the satellite is finished, and the target standard satellite orbit is the initial orbit of the satellite.
It should be noted that the calculation process of the target right ascension and the target declination is as follows:
firstly, calculating the position of the measuring station at the last moment in a J2000 inertial coordinate system;
then, the J2000 position velocity (x, y, z; v) of the target standard satellite orbit relative to the survey station is calculated x ，v y ，v z ) = position of the target standard satellite orbit in the J2000 inertial frame at the last instant-position of the last instant station in the J2000 inertial frame;
calculating the target right ascension and the target declination:
if the difference value between the final right ascension and the final declination corresponding to the initial time in the optical angle measurement data and the final right ascension and the declination is larger than a threshold value, performing iterative optimization on a target standard satellite orbit, wherein the specific process is as follows:
using a survey station to carry out two-body forecast on a satellite chain satellite, and calculating the visibility of a target standard satellite orbit to obtain the visibility distance of the last moment;
according to the visibility distance and the target right ascension
Target declination
And calculating the sub-satellite points (longitude and latitude) of the target standard satellite orbit at the last moment:
1) Firstly, calculating the position of a target standard satellite orbit under J2000 inertial coordinates:
2) And calculating the position of the target standard satellite orbit relative to the J2000 inertial coordinate system of the survey station (
) = position under track J2000 + station J2000 position;
3) Converting the position of the target standard satellite orbit relative to the survey station in the J2000 inertial coordinate system into the position in the earth-fixed coordinate system;
4) And converting subsatellite points (longitude and latitude) according to the position in the earth-fixed coordinate system.
Calculating the position and semimajor axis process according to the right ascension and declination at the last moment in the optical measurement data:
and calculating the subsatellite point (longitude and latitude) by using the calculated visibility distance at the last moment and the right ascension and declination at the last moment in the optical angle measurement data.
1) Firstly, calculating the position of a target standard satellite orbit J2000 in an inertial coordinate system:
2) And calculating the position of the target standard satellite orbit relative to the J2000 inertial coordinate system of the survey station (
) = position of target standard satellite orbit in J2000 inertial frame + position of rover station in J2000 inertial frame;
3) Converting the position of the target standard satellite orbit in the J2000 inertial coordinate system relative to the survey station into the position in the earth-fixed coordinate system;
4) And converting the position into a sub-satellite point (longitude and latitude) according to the position in the earth-fixed coordinate system.
Finally, calculating the adjusted semimajor axis, and adjusting the target standard satellite orbit to obtain the final standard satellite orbit;
then, searching a point with the same latitude at the last moment in the final standard satellite orbit lower point and the latitude at the last moment in the optical angle measurement data, calculating a second ascent point right ascension, and correcting the final standard satellite orbit to obtain a second intermediate standard satellite orbit;
the adjusted second ascension point right ascension calculation process:
second rising point right ascension = first rising point right ascension + (last-minute longitude in optical goniometric data — last-minute longitude of target standard satellite orbit).
And calculating a second approximate point angle according to the position of the last moment of the second intermediate standard satellite orbit in the J2000 inertial coordinate system and the position of the last moment satellite chain satellite in the J2000 inertial coordinate system in the optical angle measurement data, and correcting the second intermediate standard satellite orbit to obtain a third intermediate standard satellite orbit.
A second approximate point angle M calculation process:
the method comprises the following steps: calculating the position included angle corresponding to the last moment of the track and the last moment of the original data, namely cosM = < M0, M1>
Wherein the content of the first and second substances,
j2000 position at the last time instant for the second intermediate standard satellite orbit;
is the J2000 position of the last right ascension and declination transition in the optical goniometry data.
The third intermediate standard satellite orbit is an initial orbit obtained by optimizing optical angle measurement data at the last moment.
And then, converting the third intermediate standard satellite orbit into the orbit number of the initial epoch, calculating the right ascension latitude, comparing the right ascension latitude with the right ascension latitude at the initial moment in the optical angle measurement data, judging whether the right ascension latitude is smaller than a threshold value, and if the right ascension latitude is smaller than the threshold value, determining that the initial orbit is finished, namely, the third intermediate standard satellite orbit is the initial orbit of the satellite chain satellite.
Specifically, a two-body orbit predictor is used for calculating the number of orbits at the initial moment of the three-intermediate standard satellite orbit;
converting six third middle standard satellite orbits at the initial moment into three middle standard satellite orbits J2000 position speed, and calculating the position of the survey station in a J2000 inertial coordinate system;
calculating the position velocity in the J2000 relationship coordinate system of the third intermediate standard satellite orbit relative to the survey station = orbit J2000 position velocity-survey station J2000 position;
calculating the final right ascension and the final declination: finally, the product is processed
(ii) a Finally, the product is processed
(
)。
If the difference value is larger than the threshold value, the third intermediate standard satellite orbit corresponding to the optical angle measurement data is determined as the initial orbit of the satellite chain.
Example two:
the embodiment of the invention also provides a device for determining the initial orbit of the star-linked satellite based on the optical angle measurement data, which is used for executing the method for determining the initial orbit of the star-linked satellite based on the optical angle measurement data provided by the embodiment of the invention.
As shown in fig. 2, fig. 2 is a schematic diagram of the above-mentioned device for determining an initial orbit of a satellite in a satellite chain based on optical goniometric data, and the device for determining an initial orbit of a satellite in a satellite chain based on optical goniometric data includes: an acquisition unit 10, a determination unit 20, a construction unit 30, a modification unit 40 and an optimization unit 50.
The acquiring unit is configured to acquire target data corresponding to a satellite-linked satellite, where the target data includes: optical angle measurement data at the initial moment, optical angle measurement data at the final moment and position information of the measuring station;
the determining unit is used for determining the earth center distance of the target track based on the optical angle measurement data at the initial moment, the position information of the measuring station and a preset observation distance rough value;
the construction unit is used for constructing a standard satellite orbit and a preset orbit of the satellite chain satellite based on the geocentric distance and the target data, and calculating the position information of the off-satellite point of the standard satellite orbit and the position information of the off-satellite point of the preset orbit;
the correction unit is used for correcting the standard satellite orbit based on the position information of the satellite points of the standard satellite orbit and the position information of the satellite points of the preset orbit to obtain a target standard satellite orbit;
and the optimization unit is used for performing iterative optimization on the target standard satellite orbit based on the optical angle measurement data at the final moment to obtain the initial orbit of the satellite-link satellite.
In the embodiment of the present invention, target data corresponding to a satellite in a satellite chain is obtained, where the target data includes: optical angle measurement data at the initial moment, optical angle measurement data at the final moment and position information of the measuring station; determining the geocentric distance of the target track based on the optical angle measurement data at the initial moment, the position information of the measuring station and a preset observation distance rough value; constructing a standard satellite orbit and a preset orbit of the satellite chain satellite based on the earth-center distance and the target data, and calculating the position information of the off-satellite point of the standard satellite orbit and the position information of the off-satellite point of the preset orbit; correcting the standard satellite orbit based on the position information of the satellite points of the standard satellite orbit and the position information of the satellite points of the preset orbit to obtain a target standard satellite orbit; and performing iterative optimization on the target standard satellite orbit based on the optical angle measurement data at the final moment to obtain the initial orbit of the satellite chain satellite, so that the purpose of determining the initial orbit of the satellite chain satellite by using the optical angle measurement data is achieved, the technical problem that the existing initial orbit determination method is low in precision and efficiency is solved, and the technical effect of improving the precision and efficiency of determining the initial orbit of the satellite chain satellite is achieved.
Preferably, the optical goniometric data includes: measuring time, right ascension and declination; the position information of the station comprises: longitude, latitude, and altitude.
Example three:
an embodiment of the present invention further provides an electronic device, which includes a memory and a processor, where the memory is used to store a program that supports the processor to execute the method in the first embodiment, and the processor is configured to execute the program stored in the memory.
Referring to fig. 3, an embodiment of the present invention further provides an electronic device 100, including: a processor 60, a memory 61, a bus 62 and a communication interface 63, wherein the processor 60, the communication interface 63 and the memory 61 are connected through the bus 62; the processor 60 is arranged to execute executable modules, such as computer programs, stored in the memory 61.
The Memory 61 may include a Random Access Memory (RAM) and a non-volatile Memory (non-volatile Memory), such as at least one disk Memory. The communication connection between the network element of the system and at least one other network element is realized through at least one communication interface 63 (which may be wired or wireless), and the internet, a wide area network, a local network, a metropolitan area network, and the like may be used.
The bus 62 may be an ISA bus, PCI bus, EISA bus, or the like. The bus may be divided into an address bus, a data bus, a control bus, etc. For ease of illustration, only one double-headed arrow is shown in FIG. 3, but this does not indicate only one bus or one type of bus.
The memory 61 is used for storing a program, the processor 60 executes the program after receiving an execution instruction, and the method executed by the apparatus defined by the flow process disclosed in any of the foregoing embodiments of the present invention may be applied to the processor 60, or implemented by the processor 60.
The processor 60 may be an integrated circuit chip having signal processing capabilities. In implementation, the steps of the above method may be performed by integrated logic circuits of hardware or instructions in the form of software in the processor 60. The Processor 60 may be a general-purpose Processor, including a Central Processing Unit (CPU), a Network Processor (NP), and the like; the Integrated Circuit may also be a Digital Signal Processor (DSP), an Application Specific Integrated Circuit (ASIC), a Field-Programmable Gate Array (FPGA) or other Programmable logic device, discrete Gate or transistor logic device, or discrete hardware components. The various methods, steps and logic blocks disclosed in the embodiments of the present invention may be implemented or performed. A general purpose processor may be a microprocessor or the processor may be any conventional processor or the like. The steps of the method disclosed in connection with the embodiments of the present invention may be directly implemented by a hardware decoding processor, or implemented by a combination of hardware and software modules in the decoding processor. The software module may be located in ram, flash memory, rom, prom, or eprom, registers, etc. storage media as is well known in the art. The storage medium is located in a memory 61, and the processor 60 reads the information in the memory 61 and, in combination with its hardware, performs the steps of the above method.
Example four:
the embodiment of the present invention further provides a computer-readable storage medium, where a computer program is stored on the computer-readable storage medium, and when the computer program is executed by a processor, the computer program performs the steps of the method in the first embodiment.
In addition, in the description of the embodiments of the present invention, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as being fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in a specific case to those of ordinary skill in the art.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the several embodiments provided in the present application, it should be understood that the disclosed system, apparatus and method may be implemented in other ways. The above-described apparatus embodiments are merely illustrative, and for example, the division of the units into only one type of logical function may be implemented in other ways, and for example, multiple units or components may be combined or integrated into another system, or some features may be omitted, or not implemented. In addition, the shown or discussed coupling or direct coupling or communication connection between each other may be through some communication interfaces, indirect coupling or communication connection between devices or units, and may be in an electrical, mechanical or other form.
The units described as separate parts may or may not be physically separate, and parts displayed as units may or may not be physical units, may be located in one place, or may be distributed on a plurality of network units. Some or all of the units can be selected according to actual needs to achieve the purpose of the solution of the embodiment.
In addition, functional units in the embodiments of the present invention may be integrated into one processing unit, or each unit may exist alone physically, or two or more units are integrated into one unit.
Finally, it should be noted that: the above-mentioned embodiments are only specific embodiments of the present invention, which are used for illustrating the technical solutions of the present invention and not for limiting the same, and the protection scope of the present invention is not limited thereto, although the present invention is described in detail with reference to the foregoing embodiments, those skilled in the art should understand that: those skilled in the art can still make modifications or changes to the embodiments described in the foregoing embodiments, or make equivalent substitutions for some features, within the scope of the disclosure; such modifications, changes or substitutions do not depart from the spirit and scope of the embodiments of the present invention, and they should be construed as being included therein. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (7)
1. A satellite chain satellite initial orbit determination method based on optical angle measurement data is characterized by comprising the following steps:
acquiring target data corresponding to a satellite chain satellite, wherein the target data comprises: optical angle measurement data at the initial moment, optical angle measurement data at the final moment and position information of the measuring station;
determining the geocentric distance of a target track based on the optical angle measurement data at the initial moment, the position information of the measuring station and a preset observation distance rough value;
constructing a standard satellite orbit and a preset orbit of the satellite chain satellite based on the earth-center distance and the target data, and calculating the position information of the off-satellite point of the standard satellite orbit and the position information of the off-satellite point of the preset orbit;
correcting the standard satellite orbit based on the position information of the satellite points of the standard satellite orbit and the position information of the satellite points of the preset orbit to obtain a target standard satellite orbit;
performing iterative optimization on the target standard satellite orbit based on the optical angle measurement data at the final moment to obtain an initial orbit of the satellite-link satellite;
wherein the orbit parameters of the standard satellite orbit comprise: the system comprises a semi-long axis, an inclination angle, an eccentricity, a rising intersection declination, an perigee argument, a mean perigee angle and a first initial epoch, wherein the semi-long axis is the geocentric distance of the target track, the inclination angle is 53 degrees, the eccentricity, the rising intersection declination, the perigee argument and the mean perigee angle are all 0, and the first initial epoch is the initial time;
the position and speed of the preset track comprises the following steps: a position of the target orbit in a J2000 inertial coordinate system, a velocity of the satellite in the standard satellite orbit at an initial time, and the first initial epoch;
wherein, based on the position information of the point under the satellite of the standard satellite orbit and the position information of the point under the satellite of the preset orbit, the standard satellite orbit is corrected to obtain a target standard satellite orbit, which comprises:
a first correction step of calculating a first mean anomaly based on the position information of the satellite points of the standard satellite orbit at the initial time and the position information of the satellite points of the preset orbit at the initial time, and correcting the standard satellite orbit based on the first mean anomaly to obtain a first intermediate standard satellite orbit;
a second correction step of calculating a first rising intersection red longitude based on the longitude of the satellite chain satellite at the initial time in the first intermediate standard satellite orbit and the longitude of the satellite chain satellite at the initial time in the preset orbit, and correcting the first intermediate standard satellite orbit based on the first rising intersection red longitude to obtain the target standard satellite orbit;
the iterative optimization of the target standard satellite orbit based on the optical angle measurement data at the final time to obtain the initial orbit of the satellite chain satellite comprises the following steps:
a second determination step of determining a target right ascension and a target declination of the satellite chain at the last moment in the target standard satellite orbit;
executing a step of calculating a visibility distance of the target standard satellite orbit at the last moment if a difference value between the target right ascension and the target declination corresponding to the last moment in the optical goniometry data and the right ascension and the declination corresponding to the last moment is greater than a threshold value, calculating position information and an under-satellite point of the satellite chain at the last moment based on the visibility distance and the target right ascension and the target declination, and adjusting a semi-major axis of the target standard satellite orbit based on the position information and the under-satellite point of the satellite chain at the last moment to obtain a final standard satellite orbit;
a third correction step of calculating a second approximate point angle based on the position information of the sub-satellite point of the final standard satellite orbit at the last moment and the position information of the sub-satellite point of the preset orbit at the last moment, and correcting the final standard satellite orbit based on the second approximate point angle to obtain a second intermediate standard satellite orbit;
a fourth correction step of calculating a second ascent point right ascent base on the longitude of the satellite chain satellite at the last time in the second intermediate standard satellite orbit and the longitude of the satellite chain satellite at the initial time in the preset orbit, and correcting the second intermediate standard satellite orbit based on the first ascent point right ascent base to obtain a third intermediate standard satellite orbit;
a third determination step of determining a final right ascension and a final declination of the satellite in the star chain at an initial time in the third intermediate standard satellite orbit;
if the difference value between the final right ascension angle and the final declination corresponding to the initial time in the optical goniometry data is greater than a threshold value, calculating the visibility distance of the third intermediate standard satellite orbit at the initial time, determining a target lower star point based on the visibility distance of the initial time and the right ascension angle and declination corresponding to the initial time, determining the third intermediate standard satellite orbit as the standard satellite orbit, determining the target lower star point as the lower star point of the preset orbit, repeatedly executing the first correction step, the second determination step, the execution step, the third correction step, the fourth correction step and the third determination step until the difference value between the final right ascension angle and the final declination corresponding to the initial time in the optical goniometry data is less than or equal to the threshold value, and determining the difference value between the final right ascension angle and the declination corresponding to the initial time in the optical goniometry data is less than or equal to the initial satellite chain of the intermediate satellite.
2. The method of claim 1,
the optical goniometric data includes: measuring time, right ascension and declination;
the position information of the station comprises: longitude, latitude, and altitude.
3. The method of claim 2, wherein determining the geocentric distance of the target track based on the optical angle measurement data at the initial time and a preset coarse observation distance value comprises:
a first calculation step of calculating initial position information of the satellite chain satellite in a J2000 inertial coordinate system based on the coarse value of the preset observation distance and the right ascension and the declination at the initial moment;
a first determination step of determining the position information of the survey station in a ground-fixed coordinate system based on the position information of the survey station at the initial time, and converting the position information of the survey station in the ground-fixed coordinate system into the position information of the survey station in a J2000 inertial coordinate system;
a second calculation step of calculating an initial earth center distance of the target orbit based on the initial position information of the satellite chain satellite in the J2000 inertial coordinate system and the position information of the survey station in the J2000 inertial coordinate system;
if the initial earth center distance is not within the preset range, adjusting the preset observation distance coarse value, and repeatedly executing the first calculating step, the first determining step and the second calculating step until the initial earth center distance is within the preset range, and determining the initial earth center distance within the preset range as the earth center distance of the target track.
4. An initial orbit determination device for a satellite in a star chain based on optical angle measurement data, comprising: an acquisition unit, a determination unit, a construction unit, a modification unit and an optimization unit, wherein,
the acquiring unit is configured to acquire target data corresponding to a satellite, where the target data includes: optical angle measurement data at the initial moment, optical angle measurement data at the final moment and position information of the measuring station;
the determining unit is used for determining the earth center distance of the target track based on the optical angle measurement data at the initial moment, the position information of the measuring station and a preset observation distance rough value;
the construction unit is used for constructing a standard satellite orbit and a preset orbit of the satellite chain satellite based on the geocentric distance and the target data, and calculating the position information of the off-satellite point of the standard satellite orbit and the position information of the off-satellite point of the preset orbit;
the correction unit is used for correcting the standard satellite orbit based on the position information of the satellite points of the standard satellite orbit and the position information of the satellite points of the preset orbit to obtain a target standard satellite orbit;
the optimization unit is used for performing iterative optimization on the target standard satellite orbit based on the optical angle measurement data at the final moment to obtain an initial orbit of the satellite chain satellite;
wherein the orbit parameters of the standard satellite orbit include: the system comprises a semimajor axis, an inclination angle, an eccentricity, a rising intersection akaarasia, an apogee argument, a mean apogee angle and a first initial epoch, wherein the semimajor axis is the geocentric distance of the target track, the inclination angle is 53 degrees, the eccentricity, the rising intersection akaarasia, the apogee argument and the mean apogee angle are all 0, and the first initial epoch is the initial time;
the position speed of the preset track comprises: a position of the target orbit in a J2000 inertial coordinate system, a velocity of the satellite in the standard satellite orbit at an initial time, and the first initial epoch;
wherein the correction unit is configured to:
a first correction step of calculating a first mean anomaly based on the position information of the satellite points of the standard satellite orbit at the initial time and the position information of the satellite points of the preset orbit at the initial time, and correcting the standard satellite orbit based on the first mean anomaly to obtain a first intermediate standard satellite orbit;
a second correction step of calculating a first rising intersection right ascension based on the longitude of the satellite chain at the initial time in the first intermediate standard satellite orbit and the longitude of the satellite chain at the initial time in the preset orbit, and correcting the first intermediate standard satellite orbit based on the first rising intersection right ascension to obtain the target standard satellite orbit;
wherein the optimization unit is configured to:
a second determination step, determining the target right ascension and the target declination of the satellite chain at the last moment in the target standard satellite orbit;
an executing step, if a difference value between the target right ascension and the target declination and the right ascension and the declination corresponding to the last moment in the optical goniometry data is greater than a threshold value, calculating a visibility distance of the target standard satellite orbit at the last moment, calculating position information and a sub-satellite point of the satellite chain satellite at the last moment based on the visibility distance, the target right ascension and the target declination, and adjusting a semi-major axis of the target standard satellite orbit based on the position information and the sub-satellite point of the satellite chain satellite at the last moment to obtain a final standard satellite orbit;
a third correction step of calculating a second approximate point angle based on the position information of the satellite point of the final standard satellite orbit at the last moment and the position information of the satellite point of the preset orbit at the last moment, and correcting the final standard satellite orbit based on the second approximate point angle to obtain a second intermediate standard satellite orbit;
a fourth correction step of calculating a second ascent point right ascent base on the longitude of the satellite chain satellite at the last time in the second intermediate standard satellite orbit and the longitude of the satellite chain satellite at the initial time in the preset orbit, and correcting the second intermediate standard satellite orbit based on the first ascent point right ascent base to obtain a third intermediate standard satellite orbit;
a third determination step of determining a final right ascension and a final declination of the satellite chain at an initial time in the third intermediate standard satellite orbit;
if the difference value between the final right ascension angle and the final declination corresponding to the initial time in the optical goniometry data is greater than a threshold value, calculating the visibility distance of the third intermediate standard satellite orbit at the initial time, determining a target lower star point based on the visibility distance of the initial time and the right ascension angle and declination corresponding to the initial time, determining the third intermediate standard satellite orbit as the standard satellite orbit, determining the target lower star point as the lower star point of the preset orbit, repeatedly executing the first correction step, the second determination step, the execution step, the third correction step, the fourth correction step and the third determination step until the difference value between the final right ascension angle and the final declination corresponding to the initial time in the optical goniometry data is less than or equal to the threshold value, and determining the difference value between the final right ascension angle and the declination corresponding to the initial time in the optical goniometry data is less than or equal to the initial satellite chain of the intermediate satellite.
5. The apparatus of claim 4,
the optical goniometric data includes: measuring time, right ascension and declination;
the position information of the station comprises: longitude, latitude, and altitude.
6. An electronic device comprising a memory for storing a program that enables a processor to perform the method of any of claims 1 to 3 and a processor configured to execute the program stored in the memory.
7. A computer-readable storage medium, on which a computer program is stored, which, when being executed by a processor, carries out the steps of the method according to any one of the claims 1 to 3.
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