CN107689480B - On-orbit effective evading method for gain concave area of high-orbit remote sensing satellite measurement and control antenna - Google Patents
On-orbit effective evading method for gain concave area of high-orbit remote sensing satellite measurement and control antenna Download PDFInfo
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- CN107689480B CN107689480B CN201710620208.7A CN201710620208A CN107689480B CN 107689480 B CN107689480 B CN 107689480B CN 201710620208 A CN201710620208 A CN 201710620208A CN 107689480 B CN107689480 B CN 107689480B
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
- H01Q1/288—Satellite antennas
Abstract
The invention relates to an effective evading method of a gain concave area of a measurement and control antenna of a high-orbit remote sensing satellite, which dynamically simulates the position of the gain concave area of the measurement and control antenna in the orbit transfer process, the normal orbit conventional imaging process and the sunlight evading process of the high-orbit remote sensing satellite according to the actual working condition of the satellite so as to determine the gain concave area in the actual flying process of the satellite; judging whether a measurement and control link communicating with a ground station needs to use a gain concave area; according to the on-orbit measurement and control characteristics of the satellite, the ground measurement and control station is reasonably selected, so that the measurement and control task of the ground station cannot be influenced by the gain concave area of the measurement and control antenna, and the measurement and control risk is effectively avoided.
Description
Technical Field
The method for effectively avoiding the gain concave area of the measurement and control antenna when the satellite is in orbit is provided. According to the on-orbit measurement and control characteristics of the satellite, the ground measurement and control station is reasonably selected, and the measurement and control risk is effectively avoided.
Background
The static orbit communication satellite and the navigation satellite have no large-volume camera load on the ground, a special antenna tower can be installed on the ground, and a measurement and control antenna is installed in a measurement and control antenna tower mode. The geostationary orbit communication satellite and the navigation satellite measurement and control antenna are both positioned at the highest position relative to the ground, so that the view field of the measurement and control antenna is not blocked, and the problems of obvious fluctuation of the measurement and control antenna gain and a concave area in a coverage area are solved.
The GF-4 satellite is the first domestic static orbit remote sensing satellite and adopts a high orbit remote sensing satellite platform. The high-precision camera is installed on the ground, wherein the height of a camera lens hood is 2.5 meters, and the caliber is 0.7 meter. The installation position of the measurement and control antenna is limited by the design of the light shield, the satellite must be installed on the camera light shield for the ground measurement and control antenna, the measurement and control antenna cannot be higher than the light shield in position in consideration of the camera imaging quality factor, and therefore the measurement and control antenna is flush with the top end of the camera light shield in position. Under the condition of being limited by the specific installation mode, the view field of the measurement and control antenna is shielded by the camera light shield, and a large fluctuating gain concave area is inevitably generated in the coverage area of the measurement and control antenna. Because the sheltering of camera lens hood can not avoid, consequently gain concave zone also exists objectively, how to judge the spatial position of gain concave zone accurately, selects available ground station to carry out on-orbit regulation and evasion, guarantees satellite safety and observes and controls, is the technological problem that this field awaits a urgent need to solve.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: aiming at the characteristics that the field of view of the antenna is blocked and a gain concave area with large fluctuation is generated in a coverage area due to the installation mode of the measurement and control antenna of the high-orbit remote sensing satellite, the ground station is reasonably selected according to the spatial position of the gain concave area of the measurement and control antenna in the satellite measurement and control process, so that the measurement and control task of the ground station cannot be influenced by the gain concave area of the measurement and control antenna, and the measurement and control risk is effectively avoided.
The technical solution of the invention is as follows:
the method for effectively avoiding the gain concave area of the high-orbit remote sensing satellite measurement and control antenna comprises the following steps:
(1) a plurality of satellite measurement and control antennas are arranged at the top end of the light shield;
(2) determining the calibration position of the gain concave area according to the actually measured directional diagram of the satellite measurement and control antenna;
(3) according to the satellite orbit and the attitude of the satellite in the process of transferring the orbit and changing the orbit, dynamically simulating the space position of the satellite; obtaining a position area alpha 1 of the gain concave area of the measurement and control antenna in the track transfer process according to the calibration position of the gain concave area determined in the step (2);
(4) according to the satellite orbit and the attitude of the normal orbit conventional imaging process of the satellite, carrying out dynamic simulation on the space position of the satellite; obtaining a position area alpha 2 of the gain concave area of the measurement and control antenna in the normal imaging process of the satellite orbit according to the calibration position of the gain concave area determined in the step (2);
(5) dynamically simulating the space position of the satellite according to the satellite orbit and attitude change in the sunlight evasion process of the satellite; obtaining a position area alpha 3 of the gain concave area of the measurement and control antenna in the sunlight evasion process of the satellite according to the determined calibration position of the gain concave area in the step (2);
(6) detecting the actual in-orbit position of a satellite in real time, acquiring the position of a ground measurement and control station, determining the relative position of an antenna of the ground measurement and control station and the satellite measurement and control antenna, and determining whether the actual position of a gain concave area of the satellite measurement and control antenna is an area alpha 1, an area alpha 2 or an area alpha 3; determining the direction of a satellite measurement and control antenna and the direction Z of a ground measurement and control station antenna;
(7) judging the relation between the actual gain concave space position of the measurement and control antenna of the in-orbit satellite and the measurement and control space position of the ground station on the satellite measurement and control antenna at the same moment; if the two spatial positions are coincident, the ground station is replaced and the step (6) is returned;
if the two positions do not coincide, the ground station is used for communication.
Preferably, the specific method for determining the calibration position of the gain notch area according to the actually measured directional diagram of the satellite measurement and control antenna in the step (2) is as follows: the antenna gain is obtained from an actually measured directional diagram of the satellite measurement and control antenna, when the gain of a certain position Z (theta, phi) of the antenna is smaller than an index threshold value, the point is judged to be a gain concave point, an area formed by a plurality of gain concave points is a gain concave area, and the calibration position of the gain concave area under the antenna body coordinate system is determined.
Compared with the prior art, the invention has the beneficial effects that:
(1) according to the invention, the dynamic simulation is carried out on the gain concave area position of the measurement and control antenna in the orbit transfer process, the normal orbit conventional imaging process and the sunlight avoidance process of the high-orbit remote sensing satellite according to the actual working condition of the satellite, various working states of the satellite are comprehensively considered, the gain concave area of the measurement and control antenna is pre-judged in advance, and a basis is provided for the accurate calculation of the gain concave area under the actual flight condition of the follow-up satellite.
(2) In the actual satellite flight process, the ground station is reasonably selected according to the spatial position of the measurement and control antenna gain concave area, so that the measurement and control antenna gain concave area cannot influence the measurement and control task of the ground station, and the measurement and control risk is effectively avoided.
Drawings
FIG. 1 is a schematic structural view of a measurement and control antenna mounted on a light shield;
fig. 2 is a schematic diagram of an antenna body coordinate system.
Detailed Description
The invention discloses a gain concave rule avoiding method of a high-orbit remote sensing satellite measurement and control antenna, which comprises the following steps:
(1) install a plurality of observing and controling antennas on the lens hood top, keep suitable position interval between a plurality of observing and controlling antennas, guarantee that the distance between a plurality of observing and controlling antennas satisfies the isolation requirement.
(2) And obtaining a measured directional diagram of the measurement and control antenna through satellite testing of a satellite Radiation Model (RM), obtaining antenna gain from the directional diagram, judging that a certain position Z (theta, phi) of the antenna is a gain concave point when the gain is smaller than an index threshold value, and determining a calibration position of the gain concave point under a coordinate system of the antenna body, wherein the area formed by a plurality of gain concave points is a gain concave area. The antenna body coordinate system is defined as shown in fig. 2, the axial direction of the antenna is taken as the Z axis, the center of the antenna is taken as the origin O, and the XOY plane is perpendicular to the Z axis. Wherein θ: and forms an included angle with the central axis of the antenna. Phi: in the XOY plane, subtend an angle with the X-axis.
(3) According to the satellite orbit and the attitude of the satellite in the orbit transferring and changing process, dynamically simulating the space position of the satellite in the geocentric inertial coordinate system; combining the installation position and the direction of the measurement and control antenna to obtain dynamic simulation of the spatial position of the measurement and control antenna and the axial direction of the antenna; combining the calibration position of the gain concave area under the antenna body coordinate system, carrying out coordinate conversion, converting the coordinate into the position under the geocentric inertial coordinate system, and obtaining a position area alpha 1 of the measurement and control antenna gain concave area in the track transfer process;
(4) according to the satellite orbit and the attitude of the satellite in the normal orbit conventional imaging process, dynamically simulating the space position of the satellite in the geocentric inertial coordinate system; combining the installation position and the direction of the measurement and control antenna to obtain dynamic simulation of the spatial position of the measurement and control antenna and the axial direction of the antenna; combining the calibration position of the antenna body coordinate system of the gain concave area, carrying out coordinate conversion, converting the coordinate into the position of the earth center inertial coordinate system, and obtaining a position area alpha 2 of the measurement and control antenna gain concave area in the conventional imaging process of the satellite normal orbit;
(5) according to the satellite orbit and attitude change in the sunlight evasion process of the satellite, dynamically simulating the space position of the satellite in the geocentric inertial coordinate system; combining the installation position and the direction of the measurement and control antenna to obtain dynamic simulation of the spatial position of the measurement and control antenna and the axial direction of the antenna; combining the calibration position of the gain concave area under the antenna body coordinate system, carrying out coordinate conversion, converting the coordinate into the position under the geocentric inertial coordinate system, and obtaining a position area alpha 3 of the measurement and control antenna gain concave area under the satellite sunlight avoidance process;
(6) obtaining the positions of all available ground measurement and control stations under the geocentric inertial coordinate system;
(7) comprehensively judging the relation between the actual gain concave space position of the measurement and control antenna of the orbit satellite and the space position of the ground measurement and control station in all measurement and control periods in the three processes according to the three processes of the satellite orbit transfer process, the normal orbit conventional imaging process and the sunlight evasion process and the position information of the ground station available in the three processes;
if the actual gain concave space position of the measurement and control antenna of the on-orbit satellite is independent from the space position of the ground measurement and control station in the measurement and control time period, the gain concave space of the measurement and control antenna does not influence the normal measurement and control use of the satellite and can be disregarded.
If the actual gain concave space position of the measurement and control antenna coincides with the spatial position of a certain ground measurement and control station in a certain measurement and control time period, the ground measurement and control station is located at the actual gain concave space position of the measurement and control antenna in the actual measurement and control process, and if the ground measurement and control station is used, the satellite measurement and control application can be influenced. Taking advance evasion measures in response to the situation, replacing other unaffected satellite measurement and control stations to carry out satellite measurement and control, and not using a ground measurement and control station in an actual gain concave area of a measurement and control antenna to carry out satellite measurement and control in a measurement and control time period;
in the actual satellite measurement and control process, the ground station is reasonably selected, so that the measurement and control task of the ground station cannot be influenced by the measurement and control antenna gain concave area, and the measurement and control risk is effectively avoided.
The invention is not described in detail and is within the knowledge of a person skilled in the art.
Claims (1)
1. A method for effectively avoiding a gain concave area of a measurement and control antenna of a high-orbit remote sensing satellite is characterized by comprising the following steps:
(1) a plurality of satellite measurement and control antennas are arranged at the top end of the light shield;
(2) determining the calibration position of the gain concave area according to the actually measured directional diagram of the satellite measurement and control antenna; obtaining antenna gain from an actually measured directional diagram of a satellite measurement and control antenna, judging that a certain position Z (theta, phi) of the antenna is a gain concave point when the gain is smaller than an index threshold value, and determining a calibration position of the gain concave point under an antenna body coordinate system, wherein an area formed by a plurality of gain concave points is a gain concave area;
(3) according to the satellite orbit and the attitude of the satellite in the process of transferring the orbit and changing the orbit, dynamically simulating the space position of the satellite; obtaining a position area alpha 1 of the gain concave area of the measurement and control antenna in the track transfer process according to the calibration position of the gain concave area determined in the step (2), specifically: combining the calibration position of the gain concave area under the antenna body coordinate system, carrying out coordinate conversion, converting the coordinate into the position under the geocentric inertial coordinate system, and obtaining a position area alpha 1 of the measurement and control antenna gain concave area in the track transfer process;
(4) according to the satellite orbit and the attitude of the normal orbit conventional imaging process of the satellite, carrying out dynamic simulation on the space position of the satellite; obtaining a position area alpha 2 of the gain concave area of the measurement and control antenna in the normal orbit imaging process of the satellite according to the calibration position of the gain concave area determined in the step (2), specifically: combining the calibration position of the antenna body coordinate system of the gain concave area, carrying out coordinate conversion, converting the coordinate into the position of the earth center inertial coordinate system, and obtaining a position area alpha 2 of the measurement and control antenna gain concave area in the conventional imaging process of the satellite normal orbit;
(5) dynamically simulating the space position of the satellite according to the satellite orbit and attitude change in the sunlight evasion process of the satellite; obtaining a position area alpha 3 of the measurement and control antenna gain concave area under the sunlight avoidance process of the satellite according to the calibration position of the gain concave area determined in the step (2), specifically: combining the calibration position of the gain concave area under the antenna body coordinate system, carrying out coordinate conversion, converting the coordinate into the position under the geocentric inertial coordinate system, and obtaining a position area alpha 3 of the measurement and control antenna gain concave area under the satellite sunlight avoidance process;
(6) detecting the actual in-orbit position of a satellite in real time, acquiring the position of a ground measurement and control station, determining the relative position of an antenna of the ground measurement and control station and the satellite measurement and control antenna, and determining whether the actual position of a gain concave area of the satellite measurement and control antenna is an area alpha 1, an area alpha 2 or an area alpha 3; determining the direction of a satellite measurement and control antenna and the direction Z of a ground measurement and control station antenna;
(7) judging the relation between the actual gain concave space position of the measurement and control antenna of the in-orbit satellite and the measurement and control space position of the ground station on the satellite measurement and control antenna at the same moment; if the two spatial positions are coincident, the ground station is replaced and the step (6) is returned;
if the two positions do not coincide, the ground station is used for communication.
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| CN201710620208.7A CN107689480B (en) | 2017-07-26 | 2017-07-26 | On-orbit effective evading method for gain concave area of high-orbit remote sensing satellite measurement and control antenna |
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| CN201710620208.7A CN107689480B (en) | 2017-07-26 | 2017-07-26 | On-orbit effective evading method for gain concave area of high-orbit remote sensing satellite measurement and control antenna |
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| CN107689480B true CN107689480B (en) | 2020-09-18 |
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| CN113791430B (en) * | 2021-09-10 | 2023-05-05 | 上海卫星工程研究所 | Method for expanding combined measurement and control coverage area |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104332707A (en) * | 2014-10-27 | 2015-02-04 | 西安空间无线电技术研究所 | Method for tracking ground station through low earth orbit space-borne antenna |
| WO2015084464A2 (en) * | 2013-10-04 | 2015-06-11 | Qualcomm Incorporated | Low cost cableless ground station antenna for medium earth orbit satellite communication systems |
| CN106558761A (en) * | 2015-09-28 | 2017-04-05 | 中国移动通信集团公司 | A kind of method of adjustment of antenna, device, earth station and low-orbit satellite |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9979082B2 (en) * | 2015-08-10 | 2018-05-22 | Viasat, Inc. | Method and apparatus for beam-steerable antenna with single-drive mechanism |
| CN106229680B (en) * | 2016-08-31 | 2023-05-12 | 四川灵通电讯有限公司 | Application method of device for carrying out real-time satellite alignment on satellite antenna in motion |
| CN106602261A (en) * | 2016-12-21 | 2017-04-26 | 中云卫星通信有限公司 | Shipborne satellite communication system and method for shipborne antenna to track satellite |
-
2017
- 2017-07-26 CN CN201710620208.7A patent/CN107689480B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015084464A2 (en) * | 2013-10-04 | 2015-06-11 | Qualcomm Incorporated | Low cost cableless ground station antenna for medium earth orbit satellite communication systems |
| CN104332707A (en) * | 2014-10-27 | 2015-02-04 | 西安空间无线电技术研究所 | Method for tracking ground station through low earth orbit space-borne antenna |
| CN106558761A (en) * | 2015-09-28 | 2017-04-05 | 中国移动通信集团公司 | A kind of method of adjustment of antenna, device, earth station and low-orbit satellite |
Non-Patent Citations (2)
| Title |
|---|
| A High-Gain Multibeam Bifocal Reflector Antenna With 40° Field of View for Satellite Ground Station Applications;Andrey N. Plastikov;《IEEE Transactions on Antennas and Propagation》;20160429;第64卷(第7期);3251-3254 * |
| 卫星测控通信地面站多天线布局的分析与设计方法;张远帆，赵军祥，陈爱平;《遥测遥控》;20140115;第35卷(第1期);23-35 * |
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