CN110048760B - Antenna on-orbit autonomous management method for double-antenna non-fixed earth-pointing satellite - Google Patents
Antenna on-orbit autonomous management method for double-antenna non-fixed earth-pointing satellite Download PDFInfo
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- CN110048760B CN110048760B CN201910219160.8A CN201910219160A CN110048760B CN 110048760 B CN110048760 B CN 110048760B CN 201910219160 A CN201910219160 A CN 201910219160A CN 110048760 B CN110048760 B CN 110048760B
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Abstract
The invention relates to an antenna on-orbit autonomous management method of a double-antenna non-fixed earth-pointing satellite, which comprises the following steps: controlling the satellite to stop attitude scanning in advance of the satellite at the moment corresponding to the first preset time period when the satellite enters the orbit through the visible arc segment of the ground receiving station, keeping the attitude of the satellite at the inertial three-axis direction of the scanning stopping moment, and then selecting and recording a quasi-on-duty data transmission antenna channel according to the included angle information of the antenna direction and the satellite centroid-ground receiving station connecting line and the preset quasi-on-duty antenna determining criterion when the on-orbit autonomous real-time estimated time lags behind the moment corresponding to the first preset time period at the current moment; after the satellite enters a visible arc section of a designated ground receiving station, determining an on-duty data transmission antenna channel and a corresponding data transmission arc section and performing earth data transmission according to the record of the quasi-on-duty data transmission antenna channel in a first preset time period in the future until the satellite leaves the visible arc section of the ground receiving station. And then automatically controlling the satellite to recover the attitude scanning.
Description
Technical Field
The invention relates to an in-orbit autonomous optimization and implementation method of a satellite data transmission antenna, which is suitable for the in-orbit data transmission of an unfixed earth pointing satellite in various orbits and various attitude control modes, and is particularly suitable for the in-orbit data transmission of a middle and low orbit space scientific satellite for carrying out inertial observation on any space in the universe.
Background
The satellite earth data transmission mainly aims to modulate load and platform data processed according to requirements by radio frequency when a satellite enters a receiving range (visible arc section) of a ground data station, amplify the load and platform data, and transmit the load and platform data to a traveling wave tube assembly for downloading the ground data station through a data transmission antenna. And stopping transmitting data to the ground after the satellite goes out of the receiving range of the ground data station. Therefore, when the satellite passes through the ground data station, the beam direction of the satellite data transmission antenna is positioned in the tracking receiving range of the ground data receiving antenna.
The earth data transmission of the current orbiting satellite is basically completed by a pair of antennas. The traditional earth-oriented or earth-side-swinging satellite such as remote sensing, communication and the like is fixed to the ground, and the beam orientation of the satellite data transmission antenna in the ground receiving and tracking range can be realized by installing the data transmission antenna on the ground, combining the antenna orientation swinging control, increasing the wave speed angle of the antenna or maneuvering to a special earth-oriented data transmission attitude. While other non-fixed earth-pointing satellites, such as some scientific observation satellites, typically do so by interrupting the main mission and maneuvering to a special earth-pointing attitude.
However, for any directional satellite with continuous observation or monitoring requirements or a satellite with multiple different attitude control and pointing modes, on one hand, a fixed earth direction is difficult to find, on the other hand, special earth data transmission is not allowed to be carried out on the satellite deviating from the observation attitude in the midway, and the satellite needs to jointly use multiple antennas to realize the beam coverage of a data transmission antenna in the full space.
In the aspect of the specific implementation of the ground data transmission, the current on-orbit satellite basically completes the ground data transmission work by the on-off time of the ground data transmission channel. And because only a pair of data transmission antennas can be used for realizing the pointing of the antenna beam to the ground receiving range, the on-off time of the data transmission channel is the time of the satellite entering and exiting the visible arc section of the ground receiving station, and the ground control is easy.
However, in the case of realizing beam coverage by combining multiple data transmission antennas, only one antenna channel can work at the same time, and the ground pointing direction of the antenna beam is directly related to the current attitude of the satellite, so that the ground pointing direction of the antenna beam must be calculated according to the attitude of the satellite and the installation direction of the antenna when the ground data transmission is implemented, and a good ground condition is selected from the multiple antennas to be used as the antenna at work. For a satellite with non-earth-pointing such as inertial pointing, the attitude of the satellite relative to the earth in the arc of one-time transit also changes, so that the beam of the same antenna is not always within the earth receiving and tracking range during one-time transit, and the antenna on duty may be switched. Taking the data transmission antenna combination method covered by two pairs of half spaces as an example, according to theoretical analysis and simulation calculation, the antenna switching is probably performed twice at most during one transit period. In this case, the implementation of the control on the ground data transmission requires not only the optimization of the antenna in operation, but also the accurate calculation of the on-off time (the time when the antenna beam enters and exits the ground receiving and tracking range in the over-arc period) and the time for switching the antenna. For the implementation of ground control, at least one track is required to complete accurate prediction and instruction injection, and the long-term operation difficulty and workload are large.
Particularly, the on-orbit attitude of the satellite is autonomously determined and controlled, the inertial pointing direction of the satellite with the change of the orientation axis or the change of the spin direction of the orientation axis is uncertain satellites under an attitude control mode, and the change process of the attitude to the ground and the transit attitude meeting the requirement of the ground receiving and tracking accuracy of antenna beams is difficult to accurately calculate by satellite attitude telemetering data of a plurality of orbits in advance, so that data transmission data loss can be caused. And the way of stopping attitude scanning several rails ahead of time will lose a lot of observation time.
In the above case, for an unfixed pointing-to-earth satellite, an antenna in-orbit autonomous management method is required to prefer a data transmission antenna for data transmission.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the method overcomes the defects of the prior art, and provides an in-orbit autonomous management method for the double-data-transmission antenna aiming at the satellite without fixed pointing to the ground, so that the satellite autonomously completes data timely and effectively downloading in orbit under the working state of observation/monitoring tasks in any pointing direction.
The technical solution of the invention is that: an on-orbit autonomous management method for an antenna of a double-antenna non-fixed earth-pointing satellite is characterized in that the double-antenna non-fixed earth-pointing satellite realizes full-space beam coverage of a data transmission system through two data transmission antenna time-sharing multiplexing channels, and when the satellite works in an attitude scanning mode with variable directional axes or variable directional axis spin, the on-orbit autonomous management of the data transmission antenna channels is realized through the following steps:
(1.1) taking the entry time of the satellite passing through a visible arc segment of the ground receiving station as a starting point, leading the starting point to the time corresponding to a first preset time period, controlling the satellite to stop attitude scanning, keeping the satellite attitude at the inertial triaxial pointing of the scanning stopping time, and then executing the step (1.2) in each execution cycle;
(1.2) when the time corresponding to the first preset time period lagged behind the current time is automatically estimated in real time in orbit, a certain antenna points to the included angle information of the connection line with the satellite centroid-ground receiving station, and a quasi-on-duty data transmission antenna channel is selected and recorded according to the included angle information and a preset quasi-on-duty antenna criterion;
(1.3) after the satellite enters a visible arc section of a designated ground receiving station, determining a data transmission arc section and an on-duty data transmission antenna channel according to the record of the on-duty data transmission antenna channel in a first preset time period in the future, and performing the earth data transmission:
and (1.4) controlling the autonomous recovery scanning mode of the satellite by the satellite through the exit moment in the visible arc section of the ground receiving station.
And (1.3) determining a data transmission arc section and an on-duty data transmission antenna channel according to the following principle:
(1.3.1) in the data transmission arc section of the selected antenna, the duration of the same quasi-current-shift data transmission antenna is not less than a first preset time period;
(1.3.2) selecting an effective data transmission arc segment, wherein the arc segment with the same quasi-on-duty data transmission antenna duration less than a second preset time period before the satellite exit time and the arc segment with the two continuous quasi-on-duty data transmission antenna channel durations less than the second preset time period in total before the satellite exit time are not included;
(1.3.3) during one-time satellite transit data transmission period, switching the data transmission antenna channel at most once;
the first preset time period is determined according to the following conditions:
(1.1.1) the time interval requirement is greater than the time interval requirement constrained by hardware implementation of the shutdown and restart of the data transmission antenna channel;
(1.1.2) the attitude stabilization time is longer than the attitude stabilization time required by stopping scanning of the satellite;
(1.1.3) and on the premise of meeting the conditions (1.1.1) and (1.1.2), selecting a smaller value as far as possible to shorten the time for stopping scanning.
The second preset time period selection criterion is as follows:
(1.3.2a) 1/3 less than the average visible arc period time for a single ground receiving station available to the satellite;
(1.3.2b) is larger than the time interval requirement constrained by the hardware implementation of the data transmission antenna channel shutdown and restart.
When the satellite works in an inertial directional triaxial stable mode and a celestial body directional slow rotation mode, the in-orbit autonomous management of the data transmission antenna channel is realized through the following steps:
and when the satellite on-orbit autonomously performs on-orbit automatic estimation on the time corresponding to the third preset time period lagging behind the current time, the information of the included angle between the pointing direction of a certain antenna and the connection line of the center of mass of the satellite and the ground receiving station is estimated in real time, only the arc section, which continuously meets the standard of the quasi-on-duty antenna and has the longest duration, of the same data transmission antenna in the visible arc section of the satellite of the selected ground receiving station is selected as the on-duty data transmission arc section, and the corresponding channel of the quasi-on-duty data transmission antenna is selected to perform on-earth data.
And the third preset time period is selected as the sum of the time of the single longest visible arc period of the appointed ground receiving station and a preset allowance.
And selecting the balance for 1-3 minutes.
The quasi-current-class antenna selection criterion is as follows:
(a) when the included angle between the pointing direction of a certain data transmission antenna and the connecting line of the satellite centroid and the ground receiving station is at [0, 89 ℃), selecting the data transmission antenna as a quasi-on-duty antenna;
(b) when the included angle between the pointing direction of a certain data transmission antenna and the connecting line of the satellite centroid and the ground receiving station is at (91 degrees, pi ], selecting the other data transmission antenna as a quasi-on-duty antenna;
(c) and when the included angle between the pointing direction of a certain data transmission antenna and the connecting line of the satellite centroid and the ground receiving station is in the range of [89 degrees ] and 91 degrees ], maintaining the original standard on-duty antenna unchanged.
The antenna on-orbit autonomous management method for the double-antenna non-fixed earth-pointing satellite is autonomously realized on the satellite through software.
Compared with the prior art, the invention has the beneficial effects that:
(1) the invention realizes the optimization and implementation use of the on-orbit autonomous on-duty data transmission channel of the non-fixed earth-pointing satellite full-space time-sharing coverage double-antenna data transmission system, can effectively improve the autonomous management capability of the satellite, ensures that the on-satellite data and the time-downloading ground are ensured, and reduces the long-term operation workload of the ground.
(2) The invention provides a method for optimizing a data transmission antenna channel and a data transmission arc at work based on information about prediction of a single antenna pointing direction and a satellite centroid-ground receiving station connection included angle of a satellite in a visible arc of a ground receiving station in a limited time advance amount, provides different optimization and implementation methods based on the attitude control type characteristics of a satellite working mode, and solves the problem of in-orbit autonomous optimization and implementation of the data transmission antenna channel under the long-term continuous observation/monitoring requirements of the satellite without fixed attitude pointing to the ground in various attitude control modes.
(3) Based on the characteristic that the ground attitude of the satellite is relatively easy to accurately predict in an inertial directional triaxial stable mode and a celestial body directional slow rotation mode, the invention provides the optimization and implementation criteria for selecting the longest continuous arc section of a single antenna in the satellite visible arc section of the single ground receiving station to carry out data transmission antenna channel in the working mode, improves the use reliability of a data transmission system, and realizes the effective utilization rate of the satellite ground receiving station visible arc section of not less than 75% in the working mode.
(4) Based on the characteristic that the satellite ground attitude is difficult to accurately predict in the inertial pointing non-directional scanning mode, the invention provides the optimization and use implementation criteria for optimizing the data transmission antenna channel and allowing the antenna to be switched for at most one time by adopting the cross-border stop scanning and estimating information based on the short lead under the working mode, thereby ensuring the on-satellite data and time downloading and ensuring the continuous observation task.
Drawings
FIG. 1 is a schematic diagram of hard X-ray tuning telescope (HXMT) satellite dual data transfer antenna channel switching according to an embodiment of the present invention;
fig. 2 is a flow chart of the in-orbit autonomous management design of the data transmission antenna in the hard X-ray adjustment telescope (HXMT) satellite cell mode according to the embodiment of the present invention.
Fig. 3 is a flow chart of the in-orbit autonomous management design of the data transmission antenna in the hard X-ray adjustment telescope (HXMT) satellite fix mode and the roving mode according to the embodiment of the present invention.
Detailed Description
The invention is described in detail below with reference to the figures and specific examples.
At present, a double-antenna fixed-ground-free pointing satellite comprises two data transmission antennas with the same structure, wherein the two data transmission antennas are arranged on two sides of a satellite body in a 180-degree mode, and each antenna directional diagram is a hemispherical wave beam. The satellite realizes the full-space beam coverage of the data transmission system through two data transmission antenna channels.
In order to accomplish various tasks, the operation modes of the general dual-antenna non-fixed point-to-ground pointing satellite are divided into the following two types:
(1) the first type: an inertial pointing non-directional scanning mode with directional axis change and directional axis spin direction change exists;
(2) and the second type: the system comprises an inertial orientation mode for stably pointing the long-term three axes of an inertial point, and a celestial body orientation slow rotation mode for orienting a non-earth celestial body target and uniformly rotating around a single axis of a celestial body.
The invention determines the on-orbit autonomous management method of the data transmission antenna according to different working modes.
1. In-orbit autonomous management method for data transmission antenna in first-class working mode
When the satellite works in an attitude scanning mode with variable directional axis or variable inertial pointing direction of the spin change of the directional axis, the on-orbit autonomous management of the data transmission antenna channel is realized by the following steps:
(1.1) taking the entry time of the satellite in the visible arc segment of the ground receiving station as a starting point, leading the starting point by the time corresponding to a first preset time period P1, controlling the satellite to stop attitude scanning, keeping the attitude of the satellite at the inertial triaxial pointing of the scanning stopping time, and then executing the step (1.2) in each execution cycle;
(1.2) automatically predicting whether the on-orbit real-time prediction lags behind the current time t in real timekAt the moment of a first preset time period P1, a certain antenna points to included angle information connected with a satellite centroid-ground receiving station, and a quasi-on-duty data transmission antenna channel is selected and recorded according to the included angle information and a preset quasi-on-duty antenna criterion;
(1.3) after the satellite enters a visible arc section of the ground receiving station, determining a data transmission arc section and an on-duty data transmission antenna channel according to a next preset first preset time period P1 according to the following principle and performing the ground data transmission:
(1.3.1) in the data transmission arc section of the selected antenna, the duration of the same quasi-current-shift data transmission antenna is not less than a first preset time period P1;
(1.3.2) selecting an effective data transmission arc segment, wherein the arc segment with the same quasi-on-duty data transmission antenna channel duration less than a second preset time period P2 before the satellite exit time and the arc segment with the two continuous quasi-on-duty data transmission antenna channel durations less than a second preset time period P2 before the satellite exit time are not included;
(1.3.3) during one-time satellite transit data transmission period, switching the data transmission antenna channel at most once;
(1.4) the satellite autonomously recovers the scanning mode at the time of the satellite passing through the exit moment in the visible arc section of the ground receiving station.
The first preset time period P1 is determined according to the following condition:
(1.1.1) the time interval requirement is greater than the time interval requirement constrained by hardware implementation of the shutdown and restart of the data transmission antenna channel;
(1.1.2) the attitude stabilization time is longer than the attitude stabilization time required by stopping scanning of the satellite;
(1.1.3) and on the premise of meeting the conditions (1.1.1) and (1.1.2), selecting a smaller value as far as possible to shorten the time for stopping scanning.
The second preset time period P2 is selected according to the following criteria:
(1.3.2a) 1/3 less than the average visible arc period time for a single ground receiving station used by the satellite;
(1.3.2b) is larger than the time interval requirement constrained by the hardware implementation of the data transmission antenna channel shutdown and restart.
2. In-orbit autonomous management method for data transmission antenna in second-class working mode
When the satellite works in an inertial directional triaxial stable mode and a celestial body directional slow rotation mode (non-earth celestial body target is oriented and rotates around a celestial body directional axis at a constant speed), the on-orbit autonomous management of the data transmission antenna channel is realized through the following steps:
the on-satellite on-orbit autonomous real-time estimation method comprises the steps of automatically estimating the information of an included angle between the pointing direction of a certain antenna and the connection line of the center of mass of the satellite and a ground receiving station at the time lagging behind the current time by a third preset time period P3 on-satellite on-orbit, selecting only the arc section, with the longest duration, of the same data transmission antenna continuously meeting the standard of the quasi-on-duty antenna, of the selected ground receiving station in the visible arc section of the satellite as the on-duty data transmission arc section, and selecting the corresponding quasi-on-duty data transmission antenna channel to carry out on.
The third preset time period P3 is selected as the longest visible arc period time of the satellite selectable single ground receiving station plus a preset allowance; and selecting the balance for 1-3 minutes.
The quasi-on-duty antenna selection criterion in the in-orbit autonomous management method for the data transmission antenna in the first and second working modes is as follows:
(a) when the included angle between the pointing direction of a certain data transmission antenna and the connecting line of the satellite centroid and the ground receiving station is at [0, 89 ℃), selecting the data transmission antenna as a quasi-on-duty antenna;
(b) when the included angle between the pointing direction of a certain data transmission antenna and the connecting line of the satellite centroid and the ground receiving station is at (91 degrees, pi ], selecting the other data transmission antenna as a quasi-on-duty antenna;
(c) and when the included angle between the pointing direction of a certain data transmission antenna and the connecting line of the satellite centroid and the ground receiving station is in the range of [89 degrees ] and 91 degrees ], maintaining the original standard on-duty antenna unchanged.
Example (b):
the present invention is further illustrated by embodiments of hard X-ray modulated telescope (HXMT) satellites, with reference to fig. 1-3.
1. Full-space-coverage ground-to-ground data transmission system
(1) Antenna selection and installation: two directional data transmission antennas with completely same structures are adopted, each antenna directional diagram is a hemispherical beam, the two antennas are arranged on two sides of a star body along the axis outwards in an angle of 180 degrees, and the full-space beam coverage of the data transmission system is realized through the two antenna arrays.
(2) The data transmission channel composition and switching principle: the two data transmission antenna channels are composed and switched according to the principle shown in fig. 1. The data transmission antenna channel consists of 2 identical traveling wave tube assemblies (a first traveling wave tube assembly and a second traveling wave tube assembly), a waveguide switch, 2 pairs of identical data transmission antennas (data transmission antennas A, B), a high-frequency cable network and other devices. And 2, performing on-orbit cold backup on the traveling wave tube assemblies, and switching the data transmission antenna channels on duty by using switching or waveguide switch state setting through the first traveling wave tube assembly and the second traveling wave tube assembly.
2. On-orbit autonomous switching path determination of data transmission antenna
Considering that the on-orbit running amplifier is complex to switch, the on-orbit autonomous management is based on the use state of the traveling wave tube assembly detected in real time, and the antenna which is actually needed to be used is set and selected through the through/cross state of the waveguide switch. In fig. 1, the first traveling wave tube assembly and the second traveling wave tube assembly are backup, and normally, 1 traveling wave tube assembly is fixed to be in a working state (usually, the working state of the primary part is the working state of the first traveling wave tube assembly), and the traveling wave tube assembly, the waveguide switch and the data transmission antenna a or the data transmission antenna B form a first data transmission antenna channel and a second data transmission antenna channel.
Taking the working state of the first traveling-wave tube component as an example, the waveguide switch is set to be in a direct-connection state, and the data transmission antenna A, namely a first data transmission antenna channel, is used; the waveguide switch is set to a crossed state, and the data transmission antenna B, i.e., the second data transmission antenna channel, is used.
3. Determining instruction sending sequence used by data transmission channel autonomous management
The instruction sequence comprises three types of instruction sequences of starting, switching and shutdown
(1) And 3 kinds of on-duty antenna start-up instruction sequences, realize the selection and start-up data transmission of the on-duty data transmission antenna channel under different conditions: the method comprises the following steps that a working antenna starting instruction sequence A (a waveguide switch is set to be through), a working antenna starting instruction sequence B (the waveguide switch is set to be crossed) and a working antenna starting instruction sequence C (the waveguide switch is set to be in a state of keeping);
(2) and 2 antenna switching instruction sequences for realizing switching and data transmission of two data transmission antenna channels: an antenna switching instruction sequence A (the waveguide switch is switched from a cross state to a through state) and an antenna switching instruction sequence B (the waveguide switch is switched from the through state to the cross state);
(3) and 1, a data transmission channel shutdown sequence is adopted to stop data transmission.
4. Classifying satellite working modes needing to implement data transmission and determining corresponding in-orbit autonomous management principle of data transmission antenna
(1) The HXMT satellite needs to transmit data in three observation modes, wherein the three observation modes and the attitude control mode are respectively as follows:
(a) a tour mode: a sun-oriented slow-speed spinning attitude control mode;
(b) fixed-point mode: an inertial directional triaxial stable attitude control mode;
(c) cell antenna pattern: and controlling the posture of the reciprocating scanning by small-angle rotation.
The attitude change of the sky patrol mode and the fixed point mode in the three working modes is stable, and the satellite ground attitude is easy to accurately predict. The small antenna area mode needs to rotate around two axes of the satellite respectively, the rotating direction is changed frequently, and the satellite ground attitude is difficult to predict accurately, so the digital transmission antenna optimization principle design is carried out by dividing the small antenna area mode into two types.
(2) Determining the on-orbit autonomous management principle of the data transmission antenna:
(a) the patrolling mode and the fixed point mode keep the original attitude control mode, only the longest continuous available arc section of the same antenna in the visible arc section of the satellite of the selected ground receiving station is used, and a corresponding data transmission antenna channel is selected for carrying out ground data transmission;
(b) in the small-sky-region mode, before the satellite enters a visible arc section of the ground data station, the scanning is stopped in advance for a first preset time period, the inertial directional triaxial is kept stable, and the original scanning state is continued when the visible arc section appears. The method is characterized in that an arc section which is smaller than the entry time and is stopped scanning in advance by a first preset time period, an arc section before the exit which is smaller than a second preset time period and two different antennas are continuously available in the visible arc section of the satellite, the total time of the two different antennas is smaller than the last two different antenna arc sections before the exit of the second preset time period, and the antennas are switched at most once during one transit.
5. Determining a criterion for determining selection of an antenna in quasi-on-duty
The quasi-current-class antenna selection criterion determined according to the on-board attitude prediction precision is as follows, and the judgment threshold can be modified in an on-orbit manner:
(1) when the included angle between the pointing direction of the data transmission antenna A and the connecting line of the satellite centroid and the ground receiving station is at [0, 89 ℃), selecting the data transmission antenna A as a quasi-on-duty antenna;
(2) when the angle between the pointing direction of the data transmission antenna A and the connecting line of the satellite centroid and the ground receiving station is (91 degrees, pi'), selecting the data transmission antenna B as a quasi-on-duty antenna;
(3) when the included angle between the pointing direction of the antenna A and the connecting line of the satellite centroid and the ground receiving station is in the range of [89 degrees ] and 91 degrees ], the original standard on-duty antenna is kept unchanged.
6. On-orbit autonomous management method for data transmission antenna in fixed point and antenna patrol mode
The flow chart is shown in FIG. 2, and the specific process is as follows:
(1) the onboard control system autonomously predicts the included angle between the pointing direction of the data transmission antenna A and the connecting line of the satellite centroid-each ground receiving station in real time when the current time is +15 minutes (a third preset time period).
And selecting a third preset time period value as the longest visible arc period time of the satellite single-ground receiving station plus 1-3 minutes allowance. The longest visible arc segment of the single ground receiving station of the HXMT satellite is 12 minutes, and the third preset time period is determined to be 15 minutes.
(2) The method for uploading data transmission task information before the ground enters a ground receiving station time and before a third preset time period includes the following steps: time T0 of entering the ground receiving station; time T1 of the receiving station on the ground; the ground receiving station used in the circle; playback instruction parameters.
(3) And starting from the time T0-a third preset time period, and switching to an in-orbit autonomous management judgment program of a corresponding data transmission antenna when the satellite number management subsystem autonomously judges that the working mode of the satellite is a fixed point or an antenna patrol mode.
a. Continuously acquiring information of a connection included angle between the pointing direction of the data transmission antenna A and the satellite centroid, namely the ground receiving station used by the local coil, judging and recording a quasi-on-duty antenna channel according to a quasi-on-duty antenna selection judgment criterion, and stopping at the moment of T1-a third preset time period;
b. selecting a continuous longest arc section of the same antenna channel from a complete quasi-on-duty antenna channel change array during the satellite passing through a ground receiving station as a data transmission arc section (assuming a time period of T0+ x 1-T0 + x 2), and selecting a corresponding quasi-on-duty data transmission antenna channel as an actually used on-duty data transmission antenna channel;
c. at the time of T0+ x1, a corresponding on-duty antenna starting command sequence is autonomously sent on the satellite according to the use state of the current traveling wave tube component and the setting state of the waveguide switch;
d. and at the time T0+ x2, the satellite autonomously sends a data transmission channel shutdown sequence.
7. On-orbit autonomous management method for data transmission antenna in cell antenna mode
The flow chart is shown in FIG. 3, and the specific process is as follows:
(1) the onboard control system autonomously predicts the included angle between the pointing direction of the data transmission antenna A and the connecting line of the satellite centroid and each ground receiving station in real time when the current time is +70 seconds (a first preset time period).
The numerical value of the first preset time period is selected to be larger than the 1-minute time interval requirement constrained by hardware implementation of switching off and then switching on the HXMT satellite data transmission antenna channel, and is larger than the maximum attitude stabilization time required by stopping scanning of the satellite by 1 minute, the scanning stopping time is shortened as far as possible, and the first preset time period is determined to be 70 seconds.
(2) The ground annotates data to transmit task information before entering a ground receiving station for-15 minutes (a third preset time period), and the method comprises the following steps: time T0 of entering the ground receiving station; time T1 of the receiving station on the ground; the ground receiving station used in the circle; playback instruction parameters.
In order to match with the on-orbit autonomous management method of the data transmission antenna in the fixed point and patrolling mode, the minimum advance of the on-orbit time of the ground instruction is unified into a third preset time period, and the requirement that the advance of the on-orbit time is greater than the first preset time period is met.
(3) And starting from the time T0-a third preset time period, and switching to a corresponding data transmission antenna on-orbit autonomous management judgment program when the satellite number management subsystem autonomously judges that the working mode of the satellite is the small antenna mode.
a. Autonomously sending a 'stop scanning' instruction on the satellite at the moment of T0-a first preset time period, continuously collecting the information of the included angle between the pointing direction of the data transmission antenna A and the center of mass of the satellite-the ground receiving station used by the circle, and simultaneously judging and recording the channel of the quasi-on-duty antenna according to the selection judgment criterion of the quasi-on-duty antenna;
b. at time T0, determining whether the stored 70-second (first preset time period) quasi-on-duty antenna channel array record is the same antenna, if so, selecting the antenna channel on duty, and directly transmitting the on-duty antenna start instruction sequence at time T0, and proceeding to step f; otherwise, recording the change time (assuming to be T0+ y1a time) and continuing to execute the step c;
c. judging whether the quasi-on-duty antennas recorded in the period of T0+ y1 a-T0 + y1a +69 are the same at the time of T0+ y1a, if the quasi-on-duty antennas are different, recording the time (assumed to be T0+ y2a) when the quasi-on-duty antennas change for the second time, using the third quasi-on-duty antenna arc section as the on-duty antenna arc section, sending an on-duty antenna startup sequence at the time of T0+ y2a, then sending a data transmission channel shutdown sequence at the time of T1, ending the data transmission, and turning to the step k; otherwise, using the second quasi-current-class antenna arc segment as the current-class antenna arc segment, sending a current-class antenna starting sequence at the moment of T0+ y1a, and continuing to execute the step d;
d. judging whether the currently recorded quasi-current-class antenna is the same as the antenna at the previous moment, if so, continuing to judge until T1 moment, automatically sending a data transmission channel shutdown sequence on the satellite, ending the data transmission, and turning to the step k; otherwise, recording the time when the quasi-current-shift antenna change occurs for the second time (assumed to be T0+ y2b), and continuing to execute the step e;
e. judging whether the time (T0+ y2b) from the time of the antenna change of the quasi-current class for the second time to the time of the exit (T1) has 3 minutes (a second preset time period), if the time is less than 3 minutes, sending a data transmission channel shutdown sequence at the time of T0+ y2b, ending the data transmission, and turning to the step k; otherwise, using the third quasi-current-class antenna arc segment as the current-class antenna arc segment, sending a current-class antenna cutting sequence at the moment of T0+ y2b, sending a data transmission channel shutdown sequence at the moment of T1, ending the data transmission, and turning to the step k;
the second preset time period is selected to be greater than the 1 minute time interval required by the hardware implementation of the HXMT satellite data transmission antenna channel for power-off and power-on, and is less than 1/3 of 10 minutes of the average visible arc of the usable single ground receiving station of the satellite, and the time interval is determined to be 3 minutes.
f. Judging whether the currently recorded quasi-current-class antenna is the same as the antenna at the previous moment, if so, continuing to judge until T1 moment, automatically sending a data transmission channel shutdown sequence on the satellite, ending the data transmission, and turning to the step k; otherwise, recording the change time (assuming to be T0+ y1b time) and continuing to execute the step g;
g. judging whether the time (T0+ y1b) from the first antenna change of the quasi-current class to the departure (T1) has 3 minutes, if the time is less than 3 minutes, sending a data transmission channel shutdown sequence at the time of T0+ y1b, ending the data transmission, and turning to the step k; otherwise, continuing to execute the step h;
h. judging whether the quasi-on-duty antennas recorded in the periods of T0+ y1 b-T0 + y1b +69 are the same at the time of T0+ y1b, if so, using the second quasi-on-duty antenna arc segment as the on-duty antenna arc segment, sending a data transmission antenna switching instruction sequence at the time of T0+ y1b, and continuing to execute the step i; otherwise, sending a data transmission channel shutdown sequence at the time T0+ y1b, recording the time T0+ y2d when the quasi-current-class antenna changes for the second time, and turning to the step j;
i. judging whether the currently recorded quasi-current-class antenna is the same as the antenna at the previous moment, if so, continuing to judge until T1 moment, automatically sending a data transmission channel shutdown sequence on the satellite, ending the data transmission, and turning to the step k; otherwise, judging the time (T0+ y2c) when the quasi-current-class antenna changes for the second time, sending a data transmission channel shutdown sequence at the time of T0+ y2c, ending the data transmission, and turning to the step k;
j. judging whether the time (T0+ y2d) from the second antenna change of the quasi-current class to the departure (T1) has 3 minutes, if the time is less than 3 minutes, turning to the step k; otherwise, the third quasi-current-class antenna arc segment is used as the current-class antenna arc segment, a current-class antenna startup command sequence is sent at the time of T0+ y2d, a data transmission channel shutdown sequence is sent at the time of T1, the data transmission is finished, and the step k is carried out;
k. and (3) autonomously sending a scanning starting command on the satellite at the time of T1, finishing the data transmission and recovering the original scanning observation posture.
In conclusion, the method can save the time of satellite-ground interaction by using the on-satellite data transmission antenna on-orbit autonomous management mode, pre-estimate the direction of the data transmission antenna to the ground by taking the on-satellite real-time attitude as the reference, complete the optimization and implementation control of the on-duty antenna channel in a short time, ensure the data transmission time control precision, reduce the observation time loss to the maximum extent, and greatly reduce the difficulty and workload of ground long-term operation.
The invention has not been described in detail, in part, to enable those skilled in the art to practice the invention.
Claims (9)
1. An on-orbit autonomous management method for an antenna of a double-antenna non-fixed earth-pointing satellite is characterized in that when the satellite works in an attitude scanning mode with variable directional axis or variable inertial pointing of directional axis spin, the on-orbit autonomous management of the data transmission antenna channel is realized through the following steps:
(1.1) taking the entry time of the satellite passing through a visible arc segment of the ground receiving station as a starting point, leading the starting point to the time corresponding to a first preset time period, controlling the satellite to stop attitude scanning, keeping the satellite attitude at the inertial triaxial pointing of the scanning stopping time, and then executing the step (1.2) in each execution cycle;
(1.2) when the time corresponding to the first preset time period lagged behind the current time is automatically estimated in real time in orbit, a certain antenna points to the included angle information of the connection line with the satellite centroid-ground receiving station, and a quasi-on-duty data transmission antenna channel is selected and recorded according to the included angle information and a preset quasi-on-duty antenna criterion;
(1.3) after the satellite enters a visible arc section of a designated ground receiving station, determining a data transmission arc section and an on-duty data transmission antenna channel according to the record of the on-duty data transmission antenna channel in a first preset time period in the future, and performing the earth data transmission:
and (1.4) controlling the autonomous recovery scanning mode of the satellite by the satellite through the exit moment in the visible arc section of the ground receiving station.
2. The method for the antenna on-orbit autonomous management of a dual-antenna non-fixed point-to-ground pointing satellite according to claim 1, wherein the step (1.3) determines the data transmission arc segment and the on-duty data transmission antenna channel according to the following principles:
(1.3.1) in the data transmission arc section of the selected antenna, the duration of the same quasi-current-shift data transmission antenna is not less than a first preset time period;
(1.3.2) selecting an effective data transmission arc segment, wherein the arc segment with the same quasi-on-duty data transmission antenna duration less than a second preset time period before the satellite exit time and the arc segment with the two continuous quasi-on-duty data transmission antenna channel durations less than the second preset time period in total before the satellite exit time are not included;
(1.3.3) and during one satellite transit data transmission period, switching the data transmission antenna channel at most once.
3. The method of claim 1, wherein the first predetermined time period is determined according to the following condition:
(1.1.1) the time interval requirement is greater than the time interval requirement constrained by hardware implementation of the shutdown and restart of the data transmission antenna channel;
(1.1.2) the attitude stabilization time is longer than the attitude stabilization time required by stopping scanning of the satellite;
(1.1.3) and on the premise of meeting the conditions (1.1.1) and (1.1.2), selecting a smaller value as far as possible to shorten the time for stopping scanning.
4. The method of claim 2, wherein the second predetermined time period is selected according to the following criteria:
(1.3.2a) 1/3 less than the average visible arc period time for a single ground receiving station available to the satellite;
(1.3.2b) is larger than the time interval requirement constrained by the hardware implementation of the data transmission antenna channel shutdown and restart.
5. An on-orbit autonomous management method for an antenna of a double-antenna fixed-free earth-pointing satellite is characterized in that when the satellite works in an inertial directional triaxial stable mode and a celestial body directional slow rotation mode, the on-orbit autonomous management of a data transmission antenna channel is realized through the following steps:
and when the satellite on-orbit autonomously performs on-orbit automatic estimation on the time corresponding to the third preset time period lagging behind the current time, the information of the included angle of the connection of the pointing direction of a certain antenna and the center of mass of the satellite-ground receiving station is estimated in real time, and only the arc section, which continuously meets the standard of the quasi-on-duty antenna and has the longest duration, of the same data transmission antenna in the visible arc section of the satellite of the selected ground receiving station is selected as the on-duty data transmission arc section according to the information of the included angle of the pointing direction of the data transmission antenna and the connection of the center of mass of the satellite-ground receiving station, and the corresponding channel of the quasi-on.
6. The method of claim 5, wherein the third predetermined time period is selected from a time of a single longest arc of sight of a specific ground receiving station plus a predetermined margin.
7. The method of claim 6, wherein the margin is selected from 1-3 minutes.
8. The method as claimed in claim 1 or 5, wherein the selection criteria of the quasi-current-class antenna is:
(a) when the included angle between the pointing direction of a certain data transmission antenna and the connecting line of the satellite centroid and the ground receiving station is at [0, 89 ℃), selecting the data transmission antenna as a quasi-on-duty antenna;
(b) when the included angle between the pointing direction of a certain data transmission antenna and the connecting line of the satellite centroid and the ground receiving station is at (91 degrees, pi ], selecting the other data transmission antenna as a quasi-on-duty antenna;
(c) and when the included angle between the pointing direction of a certain data transmission antenna and the connecting line of the satellite centroid and the ground receiving station is in the range of [89 degrees ] and 91 degrees ], maintaining the original standard on-duty antenna unchanged.
9. The method for antenna on-orbit autonomous management of a dual-antenna non-fixed-point-to-ground satellite according to claim 1 or 5, wherein the method is implemented autonomously on the satellite through software.
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