CN113156225A - Deep space high-gain antenna on-orbit pointing calibration method - Google Patents
Deep space high-gain antenna on-orbit pointing calibration method Download PDFInfo
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Abstract
The invention discloses an on-orbit pointing calibration method for a deep space high-gain antenna, wherein S1 respectively sends uplink radio frequency signals to the high-gain antenna to be calibrated and a low-gain antenna corresponding to the high-gain antenna to be calibrated; s2, acquiring receiver signal levels corresponding to the two sets of antennas; s3, calculating a gain value corresponding to the current pointing angle of the high-gain antenna; s4, injecting a zero correction instruction to the pointing mechanism, and changing the offset angle of the high-gain antenna; s5 repeats steps S1 to S4 until the calibration is completed. The method effectively overcomes various error source influences of communication time delay, atmospheric attenuation, low elevation angle radio frequency error of the ground station and the like commonly existing in the conventional antenna calibration method, and reduces the influence on normal control and tracking of the detector in orbit. The on-orbit calibration precision and efficiency can be effectively improved.
Description
Technical Field
The invention belongs to the technical field of antennas for deep space detectors, and particularly relates to an in-orbit pointing calibration method for a deep space high-gain antenna.
Background
In a certain deep space exploration model, a high-gain transmitting-receiving shared antenna with a pointing mechanism needs to be developed so as to meet the requirement of the detector for ground pointing communication. The antenna has large caliber, complex system layout and high requirement on-orbit pointing accuracy. The antenna gain is more than 40dB, and the pointing accuracy requirement is better than 0.1 degree. In order to eliminate error influence in the ground assembly test process, pointing calibration work needs to be carried out during the in-orbit period, and in-orbit pointing accuracy and communication efficiency are improved.
At present, the known on-orbit pointing calibration method for the satellite-borne high-gain antenna mainly designs an on-orbit pointing calibration program, drives the high-gain antenna to perform linear scanning or spiral scanning by a program-controlled antenna pointing mechanism, and simultaneously receives radio frequency signals through a downlink channel or an uplink channel to judge the maximum pointing direction. When a downlink channel is adopted for calibration, when the high-gain antenna is programmed to point to a ground station for scanning, the ground station receives corresponding uplink and downlink radio frequency signals of the satellite, and reversely deduces a pointing angle corresponding to the maximum gain value of the high-gain antenna through the received radio frequency signals and the corresponding angle of the pointing mechanism of the satellite to perform calibration and correction; if the uplink channel calibration is adopted, when the high-gain antenna is programmed to point to the ground station for scanning, the satellite receiver receives the radio-frequency signal sent by the ground, and provides the receiving level values of the satellite receiver corresponding to different pointing angles of the high-gain antenna, so as to obtain the pointing angle corresponding to the maximum gain value of the high-gain antenna, and carry out calibration and correction.
The method can theoretically and accurately measure the maximum pointing direction of the high-gain antenna, but has extremely high requirements on the influence factors such as satellite-ground time synchronism, the stability of radio frequency signals, atmospheric attenuation caused by different elevation angles of a ground station and the like. In addition, the adoption of a program-controlled scanning mode can also influence the normal antenna ground closed loop tracking with high gain to a certain extent, so that a certain communication interruption risk is brought.
Disclosure of Invention
The invention aims to provide an in-orbit pointing calibration method for a deep space high-gain antenna, which aims to solve the technical problems of communication time delay, atmospheric attenuation, low elevation angle radio frequency error of a ground station and the like in the conventional antenna calibration method.
In order to solve the problems, the technical scheme of the invention is as follows:
an in-orbit pointing calibration method for a deep space high gain antenna comprises the following steps:
s1: respectively sending uplink radio frequency signals to a high-gain antenna and a low-gain antenna to be calibrated on a detector from the ground, wherein the low-gain antenna and the high-gain antenna are arranged correspondingly;
s2: respectively obtaining signal receiving levels of a first receiver and a second receiver according to on-board telemetering data of the first receiver connected with the high-gain antenna and on-board telemetering data of the second receiver connected with the low-gain antenna;
s3: obtaining a gain value corresponding to the current pointing angle of the high-gain antenna based on the signal receiving levels of the first receiver and the second receiver;
s4: injecting a zero correction instruction to a pointing mechanism for controlling the pointing direction of the high-gain antenna, and correcting the zero reference of the pointing mechanism so as to change the offset angle of the high-gain antenna;
s5: and repeating the steps S1 to S4, sequentially injecting all zero correction instructions in the correction instruction group, respectively obtaining the gain values of the pointing angles corresponding to the high-gain antenna, judging to obtain the maximum gain value of the high-gain antenna, and injecting the zero correction instruction corresponding to the maximum gain value of the high-gain antenna so as to realize the ground on-track pointing calibration of the high-gain antenna.
In step S3, the gain value of the high gain antenna is obtained by the calculation formula
GH＝AAmp-BAmp+LA-LB+GL
Wherein G isHIs the on-track gain value of the high gain antenna, AAmpIs the signal reception level of the first receiver, BAmpIs the signal reception level, L, of the second receiverAIs the feeder loss, L, between the first receiver and the high gain antennaBFor feeder losses between the second receiver and the low-gain antenna, GLThe gain value corresponding to the low gain antenna pointing to the ground.
In step S5, the correction instruction group includes an X-axis angle correction group and a Y-axis angle correction group;
the correction values of the X-axis angle correction group are equal-interval angles in the X-axis direction, the maximum correction value does not exceed 3dB beam width, and the corresponding Y-axis correction value is 0 degree;
the correction values of the Y-axis angle correction group are equal-interval angles in the Y-axis direction, the maximum correction value does not exceed 3dB of beam width, and the corresponding X-axis correction value is the correction value of the X-axis angle correction group corresponding to the maximum gain value of the high-gain antenna.
Further preferably, the method further comprises step S6:
based on the zero correction command corresponding to the maximum gain of the high-gain antenna in step S6, the interval angle is reduced, a new correction command set is established, and steps S1 to S5 are repeated to perform the on-track pointing calibration of the high-gain antenna again.
Further preferably, before the step S1, a preset preparation step is further included,
a1: installing a high-gain antenna on the deep space probe and configuring a pointing mechanism, installing a low-gain antenna on the deep space probe, wherein the high-gain antenna and the low-gain antenna are installed in the same quadrant, and the main beam points to the same region direction;
a2: simulating a detector boundary condition environment and acquiring radiation pattern parameters of a high-gain antenna and a low-gain antenna;
a3: simulating the detector boundary condition environment and obtaining the gain value G corresponding to the angle of the low-gain antenna pointing to the ground stationL。
Due to the adoption of the technical scheme, compared with the prior art, the invention has the following advantages and positive effects:
the method effectively overcomes various error source influences of communication time delay, atmospheric attenuation, low elevation angle radio frequency error of the ground station and the like commonly existing in the conventional antenna calibration method, and simultaneously reduces the on-orbit normal closed-loop control tracking influence of the high-gain antenna. The on-orbit calibration precision and efficiency of the high-gain antenna can be effectively improved.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention.
Fig. 1 is a schematic flow chart of an in-orbit pointing calibration method for a deep space high gain antenna according to the present invention.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following description will be made with reference to the accompanying drawings. It is obvious that the drawings in the following description are only some examples of the invention, and that for a person skilled in the art, other drawings and embodiments can be derived from them without inventive effort.
For the sake of simplicity, the drawings only schematically show the parts relevant to the present invention, and they do not represent the actual structure as a product. In addition, in order to make the drawings concise and understandable, components having the same structure or function in some of the drawings are only schematically illustrated or only labeled. In this document, "one" means not only "only one" but also a case of "more than one".
The following describes in detail an in-track directional calibration method for a deep space high gain antenna according to the present invention with reference to the accompanying drawings and specific embodiments. Advantages and features of the present invention will become apparent from the following description and from the claims.
Examples
Referring to fig. 1, the present embodiment provides an in-orbit pointing calibration method for a deep space high gain antenna, which is now described in detail with reference to specific deep space probe
Before the embodiment is specifically implemented, preparation needs to be performed, specifically:
the deep space probe is provided with a high-gain antenna with a pointing mechanism and a low-gain antenna without the pointing mechanism, the high-gain antenna and the low-gain antenna are both arranged in the same quadrant, and a main beam points to the direction of the same area. The pointing mechanism can change the pointing direction of the high-gain antenna through the upper injection zero correction instruction. The high-gain antenna and the low-gain antenna obtain accurate radiation pattern parameters in a ground test stage, and the low-gain antenna after installation is subjected to simulation test and obtains a gain value G corresponding to the angle of the low-gain antenna pointing to the ground stationL。
The deep space detector is provided with a first receiver and a second receiver which are mutually backup, wherein the first receiver is connected with the high-gain antenna, and the second receiver is connected with the low-gain antenna. The first receiver and the second receiver are used for receiving uplink radio frequency signals through the high-gain antenna and the low-gain antenna respectively.
During the operation of the deep space probe in the orbit, the directional calibration for the high-gain antenna comprises the following steps:
in step S1, the high gain antenna is pointed to the ground station by the pointing mechanism, and the low gain antenna is fixedly installed on the surface of the deep space probe and pointed to the ground station. The ground station transmits an uplink radio frequency signal to the deep space probe, the first receiver receives the uplink radio frequency signal through the high-gain antenna, and the second receiver receives the uplink radio frequency signal through the low-gain antenna.
Next, in step S2, the ground station obtains the signal receiving levels (or signal-to-noise ratios) of the first receiver and the second receiver by uploading the telemetry data through the downlink channel of the deep space probe.
Then, in step S3, a gain value corresponding to the current pointing angle of the high-gain antenna is obtained based on the signal receiving levels of the first receiver and the second receiver, and the specific calculation formula is
GH＝AAmp-BAmp+LA-LB+GL
Wherein G isHIs a high gain antennaOn-track gain value of AAmpIs the signal reception level of the first receiver, BAmpIs the signal reception level, L, of the second receiverAIs the feeder loss, L, between the first receiver and the high gain antennaBFor feeder losses between the second receiver and the low-gain antenna, GLThe gain value corresponding to the low gain antenna pointing to the ground.
For example, at a certain time on the track, the signal reception level of the first receiver is-64.3 dBm, and the signal reception level of the second receiver is-96.6 dBm, LAIs a fixed value of 2.6dB, LBThe fixed value is 1.5dB, if the pointing angle X axis of the high-gain antenna is positioned at +12 degrees, the pointing angle Y axis is positioned at 0 degrees, and the ground working angle of the low-gain antenna is the same as the pointing angle of the high-gain antenna. And inquiring ground simulation actual measurement data of the low-gain antenna directional pattern to obtain that the state gain test result of the whole device corresponding to the angle is 6.2 dB. The on-track gain of the high-gain antenna can be obtained as follows:
GH＝(-64.3dBm)-(-96.6dBm)+2.6dB-1.5dB+6.2d＝39.6dB。
next, in step S4, the ground station injects a zero correction command to the pointing mechanism, and corrects the zero reference of the pointing mechanism to change the offset angle of the high-gain antenna; then, the ground station sends an uplink radio frequency signal, receives the signal receiving levels of the first receiver and the second receiver, and obtains a gain value corresponding to the corrected pointing angle of the high-gain antenna through the calculation formula of step S3.
In step S5, the above steps S1 to S4 are repeated until all the zero position correction commands in the correction command set are completed, and in this process, every time a command is added, after confirming that the signal reception levels of the first and second receivers are downloaded, a new zero position correction command is added. And (4) sequentially calculating by a formula to obtain the gain of the high-gain antenna, and comparing the gain values of the high-gain antenna under different zero correction instructions to obtain the maximum gain value. And subsequently, injecting a zero correction instruction corresponding to the maximum gain value to the pointing mechanism, thereby realizing the ground on-track pointing calibration of the high-gain antenna.
The correction instruction group comprises an X-axis angle correction group and a Y-axis angle correction group;
the correction values of the X-axis angle correction group are equal-interval angles in the X-axis direction, the maximum correction value does not exceed 3dB beam width, and the corresponding Y-axis correction value is 0 degree.
The correction values of the Y-axis angle correction group are equal-interval angles in the Y-axis direction, the maximum correction value does not exceed 3dB of beam width, and the corresponding X-axis correction value is the correction value of the X-axis angle correction group corresponding to the maximum gain value of the high-gain antenna.
Specifically, for example, the X-axis angle correction groups are respectively arranged at intervals of 0.1 °, and are sequentially-0.1 °, -0.2 °, -0.3 ° - …, -1.0 °, +0.1 °, +0.2 °, +0.3 °, … °, and +1.0 °, and the corresponding Y-axis correction values are all 0 °. And sequentially injecting correction instructions of the X-axis angle correction group, receiving to obtain signal receiving levels of the first receiver and the second receiver, calculating a gain value of the high-gain antenna, and supposing that the zero correction value corresponding to the maximum gain 39.9dB is judged to be X-axis +0.3 degrees and Y-axis 0 degrees. And determining the Y-axis angle correction group based on the maximum gain result of the X-axis angle correction group. The Y-axis angle correction groups are respectively arranged at intervals of 0.1 degrees and are sequentially-0.1 degrees, -0.2 degrees, -0.3 degrees …, -1.0 degrees, +0.1 degrees, +0.2 degrees, +0.3 degrees, + … and +1.0 degrees, and the corresponding X-axis correction value is +0.3 degrees. After all the Y-axis angle correction instructions are injected, receiving to obtain signal receiving levels of the first receiver and the second receiver and calculating a gain value of the high-gain antenna, and supposing that a zero correction value corresponding to the actually measured maximum gain of 40.4dB is judged to be an X axis: and +0.3 degrees and-0.1 degrees on the Y axis, the zero correction value is the finally selected zero correction instruction.
Preferably, the method further includes step S6, based on the null correction command corresponding to the maximum gain of the high-gain antenna in step S5, when the high-gain antenna calibration is performed again, the interval angle may be reduced according to the last calibration result, a new correction command set is re-established, the pointing calibration precision is improved, and steps S1 to S5 are repeated to perform the on-track pointing calibration of the high-gain antenna again.
By adopting the embodiment, the high-gain antenna and the low-gain antenna configured by the detector system, the first receiver and the second receiver are used for receiving the radio frequency data of the same ground station at the same time, and the gain value corresponding to the current pointing angle of the high-gain antenna is calculated and obtained by utilizing the signal receiving level (signal-to-noise ratio) remote measurement value received by the receiver according to the known insertion loss difference value of the two radio frequency channel links and the gain actual measurement result of the corresponding angle of the low-gain antenna; and injecting a high-gain antenna pointing mechanism correction instruction group on the ground, controlling the antenna to bias different angles while ensuring the normal tracking pointing of the high-gain antenna to the ground closed loop, comprehensively evaluating to obtain a zero correction value corresponding to the maximum gain value of the high-gain antenna of the detector, and performing injection number correction to finish the on-orbit pointing calibration work.
The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the above embodiments. Even if various changes are made to the present invention, it is still within the scope of the present invention if they fall within the scope of the claims of the present invention and their equivalents.
Claims (5)
1. An in-orbit pointing calibration method for a deep space high gain antenna is characterized by comprising the following steps:
s1: respectively sending uplink radio frequency signals to a high-gain antenna to be calibrated and a low-gain antenna to be calibrated on a detector from the ground, wherein the low-gain antenna and the high-gain antenna are arranged correspondingly;
s2: respectively obtaining signal receiving levels of a first receiver and a second receiver according to on-board telemetering data of the first receiver connected with the high-gain antenna and on-board telemetering data of the second receiver connected with the low-gain antenna;
s3: obtaining a gain value corresponding to the current pointing angle of the high-gain antenna based on the signal receiving levels of the first receiver and the second receiver;
s4: injecting a zero correction instruction to a pointing mechanism for controlling the pointing direction of the high-gain antenna, and correcting the zero reference of the pointing mechanism to change the offset angle of the high-gain antenna;
s5: repeating the steps S1 to S4, sequentially injecting all the zero correction instructions in the correction instruction group, respectively obtaining the gain values of the pointing angles corresponding to the high-gain antenna, judging to obtain the maximum gain value of the high-gain antenna, and injecting the zero correction instruction corresponding to the maximum gain value of the high-gain antenna so as to realize the ground-to-rail pointing calibration of the high-gain antenna.
2. The in-orbit pointing calibration method for deep space high gain antenna according to claim 1, wherein in the step S3, the calculation formula for obtaining the gain value of the high gain antenna is
GH＝AAmp-BAmp+LA-LB+GL
Wherein G isHIs the on-track gain value of the high gain antenna, AAmpIs the signal reception level of the first receiver, BAmpIs the signal reception level, L, of the second receiverAIs a feeder loss, L, between the first receiver and the high gain antennaBIs the feeder loss, G, between the second receiver and the low gain antennaLAnd the gain value corresponding to the low-gain antenna pointing to the ground.
3. The deep space high gain antenna in-orbit pointing calibration method according to claim 1, wherein in the step S5, the correction instruction set includes an X-axis angle correction set and a Y-axis angle correction set;
the correction values of the X-axis angle correction group are equal-interval angles in the X-axis direction, the maximum correction value does not exceed 3dB beam width, and the corresponding Y-axis correction value is 0 degree;
the correction values of the Y-axis angle correction group are equal-interval angles in the Y-axis direction, the maximum correction value does not exceed 3dB of beam width, and the corresponding X-axis correction value is the correction value of the X-axis angle correction group corresponding to the maximum gain value of the high-gain antenna.
4. The deep space high gain antenna on-track pointing calibration method according to claim 3, further preferably further comprising the step S6:
based on the null correction command corresponding to the maximum gain of the high-gain antenna in the step S6, reducing the interval angle, establishing a new correction command set, and repeating the steps S1 to S5 to perform the on-track pointing calibration of the high-gain antenna again.
5. The deep space high gain antenna in-orbit pointing calibration method according to claim 1,
before the step S1, a preset preparation step is also included,
a1: installing the high-gain antenna on the deep space probe, configuring the pointing mechanism, installing the low-gain antenna on the deep space probe, and installing the high-gain antenna and the low-gain antenna in the same quadrant with the main beam pointing to the same region direction;
a2: simulating a detector boundary condition environment and acquiring radiation pattern parameters of the high-gain antenna and the low-gain antenna;
a3: simulating the detector boundary condition environment and obtaining the gain value G corresponding to the angle of the low-gain antenna pointing to the ground stationL。
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| CN114547527A (en) * | 2022-01-25 | 2022-05-27 | 上海卫星工程研究所 | Method and system for calculating ground gain of deep space exploration gain antenna in real time |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113904709A (en) * | 2021-08-19 | 2022-01-07 | 上海卫星工程研究所 | System and method for judging high-gain antenna pointing direction in deep space detection on-orbit |
| CN113904709B (en) * | 2021-08-19 | 2023-12-12 | 上海卫星工程研究所 | System and method for judging high-gain antenna pointing direction by deep space exploration on-orbit |
| CN114547527A (en) * | 2022-01-25 | 2022-05-27 | 上海卫星工程研究所 | Method and system for calculating ground gain of deep space exploration gain antenna in real time |
| CN114547527B (en) * | 2022-01-25 | 2024-09-10 | 上海卫星工程研究所 | Real-time calculation method and system for gain of deep space exploration gain antenna to ground |
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