CN-115951722-B - Method, system, storage medium and apparatus for self-tracking using satellite telemetry

CN115951722BCN 115951722 BCN115951722 BCN 115951722BCN-115951722-B

Abstract

The invention provides a method, a system, a storage medium and equipment for self-tracking by satellite telemetry, which relate to the technical field of spacecraft control and comprise the steps of receiving running orbit point position data of a target spacecraft returned by a baseband; the method comprises the steps of calculating two rows of root numbers of a target spacecraft and running orbit point position data to obtain forecast orbit data of the target spacecraft, calculating by combining the two rows of root numbers of the target spacecraft to obtain a relative azimuth angle and a relative pitch angle of the target spacecraft relative to a current measurement and control station at each time point, adjusting the antenna pointing direction of a radar in the current measurement and control station according to the relative azimuth angle and the relative pitch angle of the target spacecraft at the current time point, obtaining telemetry data of the target spacecraft through radar tracking the target spacecraft, demodulating the telemetry data to obtain the current position of the target spacecraft, and guiding the radar to track the target spacecraft. No flashover or loss of tracking of the target spacecraft occurs.

Inventors

WANG XIAOGUANG
ZHOU HUAN
ZHAO LEI

Assignees

北京航天驭星科技有限公司

Dates

Publication Date: 20260508
Application Date: 20230207

Claims (7)

1. A method for self-tracking using satellite telemetry, comprising: receiving running orbit point position data of a target spacecraft returned by a baseband; Calculating the number of two rows of the target spacecraft and the running orbit point position data to obtain the forecast orbit data of the target spacecraft; Calculating according to the two rows of the number of the target spacecraft and the forecast orbit data to obtain the relative azimuth angle and the relative pitch angle of the target spacecraft relative to the current measurement and control station at each time point; according to the relative azimuth angle and the relative pitch angle of the target spacecraft at the current time point, the antenna pointing direction of a radar in a current measurement control station is adjusted, the target spacecraft is tracked through the radar, and telemetry data of the target spacecraft are obtained; Demodulating the telemetry data to obtain the current position of the target spacecraft, and guiding the radar to track the target spacecraft according to the current position of the target spacecraft obtained by demodulation; storing the relative azimuth angle and the relative pitch angle of the target spacecraft relative to the current measurement and control station at each time point in an orbit position list file of the target spacecraft; According to the relative azimuth angle and the relative pitch angle of the target spacecraft at the current time point, the antenna pointing direction of the radar in the current measurement control station is adjusted, and the method specifically comprises the following steps: according to the track position list file, when the current time point arrives, the relative azimuth angle and the relative pitch angle of the current time point of the target spacecraft are sent to a radar in a current measurement control station, and the radar adjusts the antenna pointing direction according to the relative azimuth angle and the relative pitch angle; Further comprises: after the radar is sent to the relative azimuth angle and the relative pitch angle of the current time point, judging the relation between the next time point in the track position list file and the current real time; if the next time point is not earlier than the current real time, transmitting the corresponding relative azimuth angle and relative pitch angle to the radar at the next time point; If the next time point is earlier than the current real time, a frame-skipping mode is adopted to track the frame so as to update the next time point, and the relative azimuth angle and the relative pitch angle corresponding to the updated next time point are sent to the radar, wherein the frame-skipping mode is adopted to track the frame so as to update the next time point, and the method comprises the following steps: Calculating the quotient of the time difference and the interval between two adjacent frames, and taking the upward rounding result of the quotient as the frame skipping number, wherein each frame corresponds to one time point; and starting from the next time point, backward skipping frames according to the number of the frame skipping frames, and taking the skipped time point as the updated next time point.
2. The method of claim 1, wherein demodulating the telemetry data to obtain the current position of the target spacecraft, comprises: Demodulating GNSS navigation measurement data of the target spacecraft from the telemetry data, And analyzing the GNSS navigation measurement data, and solving the current position of the target spacecraft from the GNSS navigation measurement data, wherein the position of the target spacecraft comprises longitude, latitude and altitude.
3. The method for self-tracking using satellite telemetry according to claim 1, further comprising: Determining a first point of an orbit to be tracked by a radar according to the forecast orbit data of the target spacecraft; After the relative azimuth angle and the relative pitch angle corresponding to the first point of the orbit are calculated, and before the target spacecraft does not run to the first point of the orbit, according to the relative azimuth angle and the relative pitch angle corresponding to the first point of the orbit, the antenna pointing direction of the radar in the current measurement control station is adjusted, and the antenna of the radar is pointed to the first point of the orbit.
4. The method for self-tracking using satellite telemetry according to claim 1, wherein the guiding the radar to track the target spacecraft according to the current position of the target spacecraft obtained by demodulation specifically comprises: After the current position of the target spacecraft is obtained, the antenna is automatically cut into a guiding program for tracking the target spacecraft, and the antenna is guided to point to the current position of the target spacecraft through the guiding program.
5. A system for self-tracking using satellite telemetry, comprising: The system comprises a first calculation unit, a first prediction unit, a second calculation unit and a first prediction unit, wherein the first calculation unit is used for receiving running orbit point position data of a target spacecraft returned by a baseband; the second calculation unit is used for calculating according to the two rows of numbers of the target spacecraft and the forecast orbit data to obtain the relative azimuth angle and the relative pitch angle of the target spacecraft relative to the current measurement and control station at each time point; The initial tracking unit is used for adjusting the antenna pointing direction of a radar in a current measurement control station according to the relative azimuth angle and the relative pitch angle of the target spacecraft at the current time point, and tracking the target spacecraft through the radar to acquire telemetry data of the target spacecraft; the tracking adjustment unit is used for demodulating the telemetry data to obtain the current position of the target spacecraft, and guiding the radar to track the target spacecraft according to the current position of the target spacecraft obtained by demodulation; the system also comprises a track position list file unit and a chase frame unit, wherein: The orbit position list file unit is used for storing the relative azimuth angle and the relative pitch angle of the target spacecraft relative to the current measurement and control station at each time point in the orbit position list file of the target spacecraft; The initial tracking unit is specifically configured to send, according to the track position list file, the relative azimuth angle and the relative pitch angle of a current time point of a target spacecraft to a radar in a current measurement control station when the current time point arrives, where the radar adjusts an antenna pointing direction according to the relative azimuth angle and the relative pitch angle; The frame tracking unit is specifically used for judging the relation between the next time point in the track position list file and the current real time after the relative azimuth angle and the relative pitch angle of the current time point are transmitted to the radar; if the next time point is not earlier than the current real time, transmitting the corresponding relative azimuth angle and relative pitch angle to the radar at the next time point; If the next time point is earlier than the current real time, a frame-skipping mode is adopted to track the frame so as to update the next time point, and the relative azimuth angle and the relative pitch angle corresponding to the updated next time point are sent to the radar, wherein the frame-skipping mode is adopted to track the frame so as to update the next time point, and the method comprises the following steps: Calculating the quotient of the time difference and the interval between two adjacent frames, and taking the upward rounding result of the quotient as the frame skipping number, wherein each frame corresponds to one time point; and starting from the next time point, backward skipping frames according to the number of the frame skipping frames, and taking the skipped time point as the updated next time point.
6. A computer readable storage medium storing one or more programs, which when executed by a computer device, cause the computer device to perform the method of self-tracking using satellite telemetry of any of claims 1-4.
7. A computer device, comprising: And a memory arranged to store computer executable instructions that when executed cause the processor to perform the method of any one of claims 1-4 for self tracking using satellite telemetry.

Description

Method, system, storage medium and apparatus for self-tracking using satellite telemetry Technical Field The present invention relates to the field of spacecraft control technology, and in particular, to a method, system, storage medium, and apparatus for performing self-tracking using satellite telemetry. Background The task of the measurement and control station is to receive measurement and telemetry information of the spacecraft, and the tracking process is to accurately obtain the actual real direction by generating azimuth axis angles and pitching axis angles through two rows of numbers, which is theoretical data. However, in actual tracking, after the target spacecraft is tracked, telemetry signals are received, and target tracking may be locked or lost due to some uncertainty factors such as some deviation of the satellite's orbit and actual position, time azimuth and atmospheric effects. Or because the orbit height of the user satellite is low, signals can pass through the top layer of the atmosphere when the acquisition is started at the edge of the earth, and signal fading generated by the signal fading can have adverse effect on the acquisition tracking function, and in the tracking process, under the condition of determining the position coordinates of a local portable station, file data of a calculated orbit are fixed orbit data, and in the tracking process, a target can be locked or lost. Disclosure of Invention The invention discloses a method, a system, a storage medium and equipment for self-tracking by satellite telemetry, which can solve the problems in the prior art. To achieve the above object, a first aspect of the present invention provides a method for self-tracking using satellite telemetry, comprising: receiving running orbit point position data of a target spacecraft returned by a baseband; Calculating the number of two rows of the target spacecraft and the running orbit point position data to obtain the forecast orbit data of the target spacecraft; Calculating according to the two rows of the number of the target spacecraft and the forecast orbit data to obtain the relative azimuth angle and the relative pitch angle of the target spacecraft relative to the current measurement and control station at each time point; according to the relative azimuth angle and the relative pitch angle of the target spacecraft at the current time point, the antenna pointing direction of a radar in a current measurement control station is adjusted, the target spacecraft is tracked through the radar, and telemetry data of the target spacecraft are obtained; demodulating the telemetry data to obtain the current position of the target spacecraft, and guiding the radar to track the target spacecraft according to the current position of the target spacecraft obtained by demodulation. As a second aspect of the present invention, the present invention provides a system for self-tracking using satellite telemetry, comprising: The system comprises a first calculation unit, a first prediction unit, a second calculation unit and a first prediction unit, wherein the first calculation unit is used for receiving running orbit point position data of a target spacecraft returned by a baseband; the second calculation unit is used for calculating according to the two rows of numbers of the target spacecraft and the forecast orbit data to obtain the relative azimuth angle and the relative pitch angle of the target spacecraft relative to the current measurement and control station at each time point; The initial tracking unit is used for adjusting the antenna pointing direction of a radar in a current measurement control station according to the relative azimuth angle and the relative pitch angle of the target spacecraft at the current time point, and tracking the target spacecraft through the radar to acquire telemetry data of the target spacecraft; The tracking adjustment unit is used for demodulating the telemetry data to obtain the current position of the target spacecraft, and guiding the radar to track the target spacecraft according to the current position of the target spacecraft obtained by demodulation. As a third aspect of the invention, the invention provides a computer readable storage medium storing one or more programs which, when executed by a computer device, cause the computer device to perform the method of self-tracking using satellite telemetry. As a fourth aspect of the present invention, the present invention provides a computer apparatus comprising: And a memory arranged to store computer executable instructions that, when executed, cause the processor to perform the method of self-tracking using satellite telemetry. The method has the advantages that running orbit point position data of the target spacecraft returned by the baseband are received, prediction orbit data of the target spacecraft are obtained by calculating the two rows of the target spacecraft and the running orbit point position