CN113904709B - System and method for judging high-gain antenna pointing direction by deep space exploration on-orbit - Google Patents
System and method for judging high-gain antenna pointing direction by deep space exploration on-orbit Download PDFInfo
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Abstract
The application provides a system and a method for judging the orientation of a high-gain antenna in on-orbit deep space exploration, which relate to the technical field of radio communication of deep space exploration spacecraft, and comprise the following steps: satellite receiving module: the system comprises a low-gain antenna, a high-gain antenna with a two-dimensional driving mechanism, a first deep space transponder and a second deep space transponder; deep space station module: the antenna comprises a large-caliber antenna, baseband equipment and a forwarding device; ground data processing center: including telemetry monitoring devices, databases, and data processing tools. The application can greatly improve the judgment accuracy; and in the cruising state, no additional ground operation and on-satellite attitude adjustment are needed, and real-time monitoring can be realized.
Description
Technical Field
The application relates to the technical field of deep space exploration spacecraft radio communication, in particular to a system and a method for judging high-gain antenna pointing in-orbit by deep space exploration.
Background
In order to realize ultra-long-distance measurement and control communication, a spacecraft for executing a deep space exploration task is generally provided with a parabolic high-gain antenna with a large caliber and a narrow beam, and in a cruising state, the high-gain antenna and a low-gain receiving antenna are simultaneously grounded. Due to the problem of pointing accuracy of two-dimensional mechanisms, it is often necessary to perform on-orbit calibration of high gain antennas. Under the remote situation, the earth radius can be ignored, the earth is used as a particle to carry out mathematical modeling, and a common method for antenna calibration is to judge whether the high-gain antenna is accurate or not through the ground station through downlink received signal strength in a cross scanning or spiral scanning mode. According to the method, the pointing direction of the antenna is controlled by means of the ground interference on-board gestures, the operation flow is complex, and the risk on the satellite is greatly increased.
The application patent with publication number of CN111755824A discloses an antenna control method for compensating the coverage area of a small-inclination GEO satellite antenna, firstly, the satellite starts antenna pointing calculation under the condition of no ground intervention by calculating on-orbit autonomous real-time pointing time, and autonomously outputs an antenna beam pointing planning angle to drive an antenna rotating mechanism, so that the fine adjustment of the beam pointing of a typical position is realized, and then the adjustment of the coverage area is realized. The method mainly calculates the pointing time in real time by satellite in orbit and performs driving angle planning autonomously, thereby realizing regional coverage. Unlike the determination by manual processing based on in-orbit telemetry values set forth herein.
The application patent with publication number of CN111891402A discloses a method for recovering the direction of a ground antenna based on autonomous mars detection, which comprises the following steps: s1, under a long-term steady-state flight reference, if the high-gain antenna is abnormally driven, the GNC calculates the attitude of the high-gain antenna to the ground pointing target according to the last beat of high-gain antenna driving angle, and autonomously plans the maneuvering path maneuver to the attitude of the high-gain antenna to the ground pointing target; s2, calculating according to the target gesture in the S1, automatically planning a path by the GNC according to the flywheel moment and the angular momentum constraint on the machine, and calculating a control quaternion and a control angular speed in the process of maneuvering the path; and S3, if no communication is established, entering a slow rotation state around a sun axis. The method mainly comprises the step of performing autonomous path planning driving through remote measurement of a driving angle of an on-orbit last beat of a high-gain antenna recorded by GNC after high-gain pointing is abnormal. Unlike the normal on-track determination high gain pointing proposed herein.
The application patent with publication number of CN110441758B discloses an on-orbit geometric calibration method of a satellite-borne linear array multi-beam altimeter laser radar, which comprises the following steps: inputting initial calibration parameters to a satellite-borne linear array multi-beam height measurement laser radar geometric model, and calculating initial coordinates of the laser footprints corresponding to the laser detection units; estimating the plane deviation and direction of the laser footprint; determining the laser footprint control point coordinates corresponding to the laser footprint initial coordinates according to the laser footprint initial coordinates and the plane deviation size and direction of the laser footprint; calculating a ranging correction parameter of each laser detection unit by using the difference value between the laser footprint initial coordinate corresponding to each laser detection unit and the laser footprint control point coordinate; and solving the overall position deviation of the laser footprint according to the coordinates of the control points of the laser footprint, and obtaining the overall attitude correction parameters of the satellite-borne linear array multi-beam height measurement laser radar according to the overall position deviation. The method realizes parameter correction through laser detection, and does not relate to the on-orbit parabolic antenna pointing judgment.
The application patent with publication number of CN112362080A discloses a method for determining the synchronous deviation of ground data of on-orbit pointing calibration of a spacecraft antenna, which comprises the following steps: acquiring a scanning angle of a spacecraft high-gain antenna during directional scanning and power data measured by ground measurement and control equipment during directional scanning of the high-gain antenna; wherein, the scanning angle adopts a spacecraft time scale, and the power data adopts a ground time scale; performing coarse search on the synchronous deviation of the scanning angle and the power data to obtain a first deviation result; and according to the first deviation result, performing fine search on the synchronous deviation of the scanning angle and the power data to obtain the synchronous deviation of the data of the machine.
Disclosure of Invention
Aiming at the defects in the prior art, the application provides a system and a method for judging the high-gain antenna pointing in an on-orbit manner by deep space exploration.
According to the system and the method for judging the high-gain antenna pointing in the on-orbit detection of the deep space, provided by the application, the scheme is as follows:
in a first aspect, a system for determining a high gain antenna pointing direction in on-orbit deep space exploration is provided, the system comprising:
satellite receiving module: the system comprises a low-gain receiving antenna, a high-gain antenna with a two-dimensional driving mechanism, a first deep space transponder and a second deep space transponder;
deep space station module: the antenna comprises a large-caliber antenna, baseband equipment and a forwarding device;
ground data processing center: including telemetry monitoring devices, databases, and data processing tools;
the deep space station module sends an uplink remote control signal, the satellite receiving module receives the uplink remote control signal through the antenna and the transponder, the intensity of the received signal level is measured in the transponder, the deep space station module receives and processes the remote measurement of the detector, and the remote measurement data of the signal level received on the characterizer is sent to the ground data processing center.
Preferably, the high-gain antenna is connected with the first deep space transponder, the low-gain antenna is connected with the second deep space transponder, the low-gain antenna is fixedly installed on a cabin board on the surface where the high-gain antenna is located, and the high-gain antenna controls the two-dimensional driving mechanism to rotate along an X axis, a Y axis and an unfolding axis through the whole device.
Preferably, the whole device collects the entry level telemetry of the deep space transponder and transmits to the ground.
Preferably, the tracking sensitivity of the deep space transponder is above-150 dBm.
In a second aspect, a method for determining a high gain antenna pointing direction by deep space exploration on-orbit is provided, the method comprising:
step S1: the detector keeps high-gain antenna closed-loop control pointing to the earth, the deep space station transmits uplink remote control signals, and meanwhile, the receiver uploads downlink telemetry signals to the ground;
step S2: the ground station forwards the processed downlink telemetry signal to a data processing center;
step S3: the ground data processing center extracts the inlet signal level telemetry data of the first deep space transponder and the second deep space transponder in the database, and performs difference processing on two groups of inlet level data in the same time period to obtain a difference A;
step S4: calculating channel gains of a first deep space transponder receiving channel and a second deep space transponder receiving channel, and performing difference processing to obtain a difference B;
step S5: and comparing the difference A in the step S3 with the difference B in the step S4 to judge the pointing precision of the high-gain antenna.
Preferably, the step S1 includes adjusting the transmit power of the deep space station module to make the signal strength meet the tracking threshold of the first deep space transponder connected to the low gain antenna.
Preferably, in the step S1, the low-gain antenna is in a fixed direction, and the high-gain antenna is in the same direction as the low-gain antenna through the driving mechanism.
Preferably, the entry signal level telemetry in step S3 is capable of linearly reflecting the signal strength at the entry end of the transponder.
Preferably, the receiving channels in step S4 include a first deep space transponder to low gain antenna channel and a second deep space transponder to high gain antenna channel.
Preferably, the channel gain in step S4 includes the gain of the antenna itself and the radio frequency link insertion loss from the antenna exit end to the deep space transponder entrance end.
Compared with the prior art, the application has the following beneficial effects:
1. the application eliminates other interference factors of signals reaching the receiving front end of the high-gain antenna by utilizing the low-gain antenna channels on the satellite, thereby greatly improving the judgment accuracy;
2. the method can be used in most of the flight time of the spacecraft, does not need extra ground operation and on-board attitude adjustment under the cruising state, and can realize real-time monitoring.
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Other features, objects and advantages of the present application will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
fig. 1 is a flow of world information transmission;
FIG. 2 is a data processing flow diagram;
Detailed Description
The present application will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the present application, but are not intended to limit the application in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present application.
The embodiment of the application provides a system for determining the orientation of a high-gain antenna in-orbit by deep space exploration, which is shown by referring to fig. 1 and comprises a satellite receiving module, a deep space station module and a ground data processing center, wherein the satellite receiving module is used for: including a low gain antenna, a high gain antenna with a two-dimensional driving mechanism (i.e. a high gain narrow beam parabolic antenna with a two-dimensional driving mechanism), a first deep space transponder and a second deep space transponder. Deep space station module: the antenna comprises a large-caliber antenna, baseband equipment and a forwarding device; ground data processing center: including telemetry monitoring devices, databases, and data processing tools. The deep space transponder has extremely high sensitivity, and the tracking sensitivity is more than-150 dBm.
The high-gain antenna is connected with the first deep space transponder, the low-gain antenna is connected with the second deep space transponder, the low-gain antenna is fixedly arranged on a cabin board on the surface where the high-gain antenna is located, and the high-gain antenna controls the two-dimensional driving mechanism to rotate along the X axis, the Y axis and the unfolding axis through the whole device. The whole device collects the entrance level telemetry of the deep space transponder and packetizes and forwards the information.
The application also provides a method for judging the high-gain antenna orientation in the deep space exploration on-orbit, which is shown by referring to fig. 2 and comprises the following steps:
step S1: the detector keeps high-gain antenna closed-loop control pointing to the earth; and adjusting the transmitting power of the deep space station module to ensure that the signal strength meets the tracking threshold of a first deep space transponder connected with the low-gain antenna. The middle-low gain antenna is in fixed direction, and the high-gain antenna is in the same direction as the low-gain antenna through the driving mechanism. The first deep space transponder and the second deep space transponder have extremely high capture sensitivity and still have carrier capture capability beyond billions of meters.
Step S2: the ground station transmits the processed downlink telemetry signal, namely satellite telemetry received by the ground, to a data processing center;
step S3: monitoring the inlet signal level telemetry of the first deep space transponder and the second deep space transponder, extracting telemetry data in a database, and performing difference processing on two groups of inlet level data in the same time period to obtain a difference A; the ingress signal level telemetry can reflect the signal strength of the ingress port of the transponder in a linear and true manner.
Step S4: calculating channel gains of a first deep space transponder receiving channel and a second deep space transponder receiving channel, and performing difference processing to obtain a difference B; the receive channel includes a first deep space transponder to low gain antenna channel and a second deep space transponder to high gain antenna channel. The channel gain includes the gain of the antenna itself and the radio frequency link insertion loss from the antenna exit end to the deep space transponder entrance end.
Step S5: and comparing the difference A in the step S3 with the difference B in the step S4 to judge the pointing precision of the high-gain antenna.
Next, the present application will be described in more detail.
As shown in fig. 1, the present application relates to a satellite receiving module, a deep space station module and a ground data processing center. The satellite receiving module receives the ground station remote control signal, and the remote measurement is acquired by the whole device to generate the remote measurement information of the entrance level of the deep space responder; and the deep space station module forwards the processed downlink telemetry signal to a ground data processing center.
The deep space station system receives the telemetry information downloaded by the satellite, and transmits the telemetry information to the ground data processing center to be cached in the database through the ground optical fiber cable network after demodulation.
And extracting telemetry information of the entrance level of the deep space transponder in the same deep space measurement and control station in the same time period from the database, generating a data table, wherein the data content of the table is divided into three columns, the first column is on-board time, the second column is a telemetry value of the entrance level of the first deep space transponder, and the third column is a telemetry value of the entrance level of the second deep space transponder. All contents are arranged in ascending time sequence on the first column device, and the continuity of time is checked. And screening the remote measurement value of the entrance level of the deep space responder, and removing bad points. And carrying out difference and averaging on the level values of the two groups of preprocessed data at the same moment to obtain a difference absolute value A.
Inquiring that the channel gain from the first deep space transponder to the low-gain antenna is X, the channel gain from the second deep space transponder to the high-gain antenna is Y, and performing difference on the insertion loss of the two channels to obtain a difference absolute value B. Comparing the absolute value A of the difference with the absolute value B of the difference, and considering that the high-gain antenna basically points to the earth under the condition that the absolute value is smaller than 1; if the difference is greater than or equal to 1, the high gain antenna is considered to have a deviation in pointing direction.
The embodiment of the application provides a system and a method for judging the orientation of a high-gain antenna in a deep space exploration in-orbit, which are used for carrying out difference processing on the signal intensity of two satellite receiving channels, eliminating the channel influence from a ground station to an antenna inlet, comparing with the actually measured gain of the antenna ground, achieving the purpose of judging the orientation precision of the high-gain antenna in-orbit, being applicable to a deep space aircraft in a long distance, having simple and effective criterion and having a certain engineering value. The satellite low-gain antenna channel is utilized to eliminate other interference factors of signals reaching the receiving front end of the high-gain antenna, so that the judgment accuracy is greatly improved; the method can be used in most of the flight time of the spacecraft, does not need extra ground operation and on-board attitude adjustment under the cruising state, and can realize real-time monitoring.
Those skilled in the art will appreciate that the application provides a system and its individual devices, modules, units, etc. that can be implemented entirely by logic programming of method steps, in addition to being implemented as pure computer readable program code, in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers, etc. Therefore, the system and various devices, modules and units thereof provided by the application can be regarded as a hardware component, and the devices, modules and units for realizing various functions included in the system can also be regarded as structures in the hardware component; means, modules, and units for implementing the various functions may also be considered as either software modules for implementing the methods or structures within hardware components.
The foregoing describes specific embodiments of the present application. It is to be understood that the application is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the application. The embodiments of the application and the features of the embodiments may be combined with each other arbitrarily without conflict.
Claims (6)
1. The system for determining the high-gain antenna pointing direction by deep space exploration on-orbit is characterized by comprising the following components:
satellite receiving module: the system comprises a low-gain antenna, a high-gain antenna with a two-dimensional driving mechanism, a first deep space transponder and a second deep space transponder;
deep space station module: the antenna comprises a large-caliber antenna, baseband equipment and a forwarding device;
ground data processing center: including telemetry monitoring devices, databases, and data processing tools;
the deep space station module sends an uplink remote control signal, the satellite receiving module receives the uplink remote control signal through the antenna and the transponder, the intensity of the received signal level is measured in the transponder, the deep space station module receives and processes the remote measurement of the detector, and the remote measurement data of the signal level received on the characterizer is sent to the ground data processing center;
the high-gain antenna is connected with the first deep space transponder, the low-gain antenna is connected with the second deep space transponder, the low-gain antenna is fixedly arranged on a cabin board on the surface of the high-gain antenna, and the high-gain antenna controls the two-dimensional driving mechanism to rotate along an X axis, a Y axis and an unfolding axis through the whole device;
the whole device collects the entrance level telemetry of the deep space transponder and transmits the entrance level telemetry to the ground station in a subpackage mode.
2. The system for determining the orientation of a high gain antenna on-orbit for deep space exploration according to claim 1, wherein the tracking sensitivity of the deep space transponder is above-150 dBm.
3. A method for determining the high gain antenna pointing direction by deep space exploration on-orbit, based on the system for determining the high gain antenna pointing direction by deep space exploration on-orbit according to any one of claims 1-2, comprising:
step S1: the detector keeps high-gain antenna closed-loop control pointing to the earth, the deep space station transmits uplink remote control signals, and meanwhile, the receiver uploads downlink telemetry signals to the ground;
step S2: the ground station forwards the processed downlink telemetry signal to a data processing center;
step S3: the ground data processing center extracts the inlet signal level telemetry data of the first deep space transponder and the second deep space transponder in the database, and performs difference processing on two groups of inlet level data in the same time period to obtain a difference A;
step S4: calculating channel gains of a first deep space transponder receiving channel and a second deep space transponder receiving channel, and performing difference processing to obtain a difference B;
step S5: comparing the difference A in the step S3 with the difference B in the step S4, and judging the pointing precision of the high-gain antenna;
the step S1 comprises the steps of adjusting the transmitting power of a deep space station module to enable the signal strength to meet the tracking threshold of a first deep space transponder connected with a low-gain antenna;
in the step S1, the low-gain antenna is in a fixed direction, and the high-gain antenna is in the same direction as the low-gain antenna through the driving mechanism.
4. A method for determining the orientation of a high gain antenna in-orbit detection according to claim 3, wherein the entry signal level telemetry in step S3 is capable of linearly reflecting the signal strength at the entry end of the transponder.
5. The method according to claim 3, wherein the receiving channel in step S4 includes a first deep space transponder to low gain antenna channel and a second deep space transponder to high gain antenna channel.
6. The method for determining the orientation of a high gain antenna according to claim 3, wherein the channel gain in step S4 includes the gain of the antenna itself and the radio frequency link insertion loss from the antenna exit end to the deep space transponder entrance end.
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| CN108173589A (en) * | 2017-12-25 | 2018-06-15 | 航天东方红卫星有限公司 | A kind of moonlet TT＆C system and method suitable for survey of deep space |
| CN108583934A (en) * | 2018-03-12 | 2018-09-28 | 上海卫星工程研究所 | Survey of deep space large aperture antenna based on erecting by overhang calibrates ground system test |
| CN109039422A (en) * | 2018-06-28 | 2018-12-18 | 上海卫星工程研究所 | Deep space exploration high-gain aerial In-flight calibration system and method |
| CN113156225A (en) * | 2021-04-25 | 2021-07-23 | 上海航天测控通信研究所 | Deep space high-gain antenna on-orbit pointing calibration method |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108173589A (en) * | 2017-12-25 | 2018-06-15 | 航天东方红卫星有限公司 | A kind of moonlet TT＆C system and method suitable for survey of deep space |
| CN108583934A (en) * | 2018-03-12 | 2018-09-28 | 上海卫星工程研究所 | Survey of deep space large aperture antenna based on erecting by overhang calibrates ground system test |
| CN109039422A (en) * | 2018-06-28 | 2018-12-18 | 上海卫星工程研究所 | Deep space exploration high-gain aerial In-flight calibration system and method |
| CN113156225A (en) * | 2021-04-25 | 2021-07-23 | 上海航天测控通信研究所 | Deep space high-gain antenna on-orbit pointing calibration method |
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