An autonomous, multi-redundant spaceborne occultation receiver detection system

Abstract

The present invention provides an autonomous management, multi-redundant satellite-borne occultation receiver detection system, including a detection system, wherein the detection system includes a positioning antenna, a first occultation antenna, a second occultation antenna, a first occultation radio frequency module, a positioning radio frequency component, a second occultation radio frequency module, at least one positioning solution module, at least one interface control module, a power supply gating unit, a power supply component, a clock unit and a satellite service computer. The present invention has the following beneficial effects: using a positioning antenna, two occultation antennas, two positioning solution modules and two control modules, it is possible to process signals of multiple frequency points of GPS and Beidou. The two positioning solution modules can back up each other, and can be cold backup or hot backup. The two control modules can back up each other, and can be cold backup or hot backup. The entire system can form 8 combination modes through control program and circuit design. Different combination modes can be selected according to different task requirements, which greatly improves the reliability of the system.

Description

Technical Field

[0001] The invention belongs to the field of GNSS occultation detection, and in particular relates to an autonomous management and multi-redundant satellite-borne occultation receiver detection system. Background Art

[0002] GNSS occultation detection is a meteorological remote sensing technology that uses the occultation phenomenon between the "GNSS navigation constellation-Earth-LEO occultation constellation" in the Earth's orbit to measure the Earth's atmosphere. At present, GNSS occultation detection technology has been applied to earthquake prediction, weather detection, ionospheric parameter binding and other fields. In the next few years, 7,000 small satellites will be launched globally. Installing GNSS occultation receiver detection systems on small satellites will be conducive to the promotion of future occultation applications. However, there are still problems such as large size, heavy weight, high power consumption, high cost of occultation payloads on traditional large satellites, low reliability, short life, and continuity of detection data on small satellites. Summary of the invention

[0003] In view of this, the present invention aims to propose an autonomously managed, multi-redundant satellite-borne occultation receiver detection system to solve at least one of the problems existing in the above-mentioned prior art. It has the characteristics of low cost while ensuring high reliability of the equipment, and can be better applied to various small satellites.

[0004] To achieve the above object, the technical solution of the present invention is achieved as follows:

[0005] A self-managed, multi-redundant satellite-borne occultation receiver detection system includes a detection system, wherein the detection system includes a positioning antenna, a first occultation antenna, a second occultation antenna, a first occultation radio frequency module, a positioning radio frequency component, a second occultation radio frequency module, at least one positioning solution module, at least one interface control module, a power supply gating unit, a power supply component, a clock unit and a satellite service computer. The positioning antenna is communicatively connected to the positioning solution module via the positioning radio frequency component, the first occultation antenna is communicatively connected to the positioning solution module via the first occultation radio frequency module, the second occultation antenna is communicatively connected to the positioning solution module via the second occultation radio frequency module, the positioning solution module is also bidirectionally communicatively connected to the interface control module, the interface control module is also bidirectionally communicatively connected to the satellite service computer, the interface control module is also communicatively connected to the power supply gating unit, and the power supply gating unit is communicatively connected to the power supply component.

[0006] Furthermore, when the number of positioning and solving modules of the detection system is two, they are A positioning and solving module and B positioning and solving module respectively; when the number of interface control modules of the detection system is two, they are A interface control module and B interface control module respectively; the positioning antenna is communicatively connected with the A positioning and solving module and the B positioning and solving module respectively through the positioning RF component; the first occultation antenna is communicatively connected with the A positioning and solving module and the B positioning and solving module respectively through the first occultation RF module; the second occultation antenna is communicatively connected with the A positioning and solving module and the B positioning and solving module respectively through the second occultation RF module; the A positioning and solving module is bidirectionally communicatively connected with the B positioning and solving module; the A positioning and solving module is also bidirectionally communicatively connected with the A interface control module and the B interface control module respectively; the B positioning and solving module is also bidirectionally communicatively connected with the A interface control module and the B interface control module respectively; the A interface control module and the B interface control module are bidirectionally communicatively connected; the A interface control module and the B interface control module are also bidirectionally communicatively connected with the satellite service computer; the A interface control module and the B interface control module are also communicatively connected with the power supply gating unit.

[0007] Furthermore, the working mode of the detection system includes 8 working modes, and the expressions of the 8 working modes are respectively:

[0008] A positioning solution module and A interface control module (1);

[0009] B positioning solution module + B interface control module (2);

[0010] A positioning solution module + B interface control module (3);

[0011] B positioning solution module + A interface control module (4);

[0012] A positioning solution module + B positioning solution module + A interface control module (5);

[0013] A positioning solution module + B positioning solution module + B interface control module (6);

[0014] A positioning solution module + B positioning solution module + A interface control module + B interface control module (7);

[0015] (A positioning solution module + B positioning solution module + A interface control module) + (A positioning solution module + B positioning solution module + B interface control module) (8).

[0016] Furthermore, the A positioning and solving module and the B positioning and solving module implement a joint positioning and solving mutual process, the implementation process of the A positioning and solving module is the same as that of the B positioning and solving module, and the implementation process of the A positioning and solving module includes the following steps:

[0017] A1. When the A positioning solution module is powered on or soft-reset or hard-reset and reloaded;

[0018] A2, A positioning solution module starts to search for satellites and solve positioning through the captured information;

[0019] A3, A positioning and solving module receives the positioning and solving information transmitted by B positioning and solving module;

[0020] A4. When the total number of satellites captured by the A positioning and solving module and the B positioning and solving module is greater than or equal to 4, the A positioning and solving module determines the positioning and solving information of the B positioning and solving module;

[0021] A5: If the judgment is passed, the positioning information of the B positioning module is set to the positioning information of the A positioning module to achieve immediate positioning, and then go to step A8;

[0022] A6. If the judgment fails, the positioning solution information of the B positioning solution module is combined with the information captured by the A positioning solution module to obtain the combined positioning solution information;

[0023] A7, after removing duplicate satellite information from the joint positioning solution information, perform joint capture solution positioning;

[0024] A8, correcting the immediate positioning information and the joint capture and solution positioning information to obtain corrected positioning solution information;

[0025] A9. Transmit the corrected positioning solution information to step A1 through the A interface control module.

[0026] Furthermore, in step A2, the information captured by the A positioning solution module includes the captured satellite number, pseudorange and carrier phase.

[0027] Furthermore, in step A3, the positioning solution information transmitted by the B positioning solution module includes frame check, captured satellite number, pseudorange, carrier phase, satellite position and satellite speed.

[0028] Further, in step A4, when the number of captured stars by the A positioning and solving module and the B positioning and solving module is equal to 4, the capture situations are divided into the following types:

[0029] The A positioning and solving module captured 0 stars, and the B positioning and solving module captured 4 stars;

[0030] The A positioning and solving module captured 1 star, and the B positioning and solving module captured 3 stars;

[0031] The A positioning and solving module captured 2 stars, and the B positioning and solving module captured 2 stars.

[0032] Furthermore, the execution operation of the interface control module includes:

[0033] First, the satellite command is received, the A interface control module communicates with the B interface control module at the same time to transmit their respective working states to each other, reads and identifies the physical telemetry of the B interface control module, determines the initial working state of the A interface control module, and selects the initialization working mode;

[0034] The execution operation of the A interface control module is the same as that of the B interface control module;

[0035] The execution operation of the A interface control module includes the following steps:

[0036] B1, A positioning solution module monitors its positioning solution information;

[0037] B2, data threshold for determining positioning solution information;

[0038] B3. If the data threshold of the positioning solution information is abnormal, first execute the soft reset instruction to perform a soft reset load on the A positioning solution module, and then return to step B1;

[0039] If the data threshold of the positioning solution information is still abnormal, execute a hard reset instruction to load the A positioning solution module, and then return to step B1;

[0040] B4. If the data threshold of the positioning solution information is abnormal again, the eight working modes are switched level by level according to the priority preset by the program until the data threshold of the positioning solution information of one working mode is normal.

[0041] Furthermore, the FPGA program loading of the positioning and solving module is redundant, and the switching path process includes the FPGA program process of the A positioning and solving module and the FPGA program process of the B positioning and solving module;

[0042] The FPGA program flow of the A positioning and solving module is the same as that of the B positioning and solving module;

[0043] The FPGA program flow of the A positioning solution module includes the following steps:

[0044] After the FPGA of C1 and A positioning and solving modules is turned on, the program in the control circuit loading program FLASH is loaded according to the program;

[0045] C2, the A interface control module monitors the FPGA solving state of the A positioning and solving module. When a single particle event causes an abnormality, the A interface control module reloads the FPGA of the A positioning and solving module. If the state is abnormal again after loading, the A interface control module switches to the channel of the backup program FLASH through the program loading control circuit, and the FPGA of the A positioning and solving module is reloaded;

[0046] C3. When it is determined that the backup program FLASH is overturned by a single particle, the A interface control module selects the backup program stored in the satellite service computer for program transfer; if the backup program stored in the satellite service computer is abnormal, the A positioning solution module program is read through the interface timing control of the A interface control module.

[0047] Compared with the prior art, the autonomous management and multi-redundant satellite-borne occultation receiver detection system described in the present invention has the following advantages:

[0048] (1) The autonomous management and multi-redundant satellite-borne occultation receiver detection system described in the present invention uses a positioning antenna, two occultation antennas, two positioning solution modules, and two control modules, and can process signals of multiple frequencies of GPS and Beidou. The two positioning solution modules can back up each other, and can be cold backup or hot backup. The two control modules can back up each other, and can be cold backup or hot backup. The entire system can form 8 combination modes through control program and circuit design. Different combination modes can be selected according to different task requirements, which greatly improves the reliability of the system.

[0049] (2) In the autonomous management and multi-redundant satellite-borne occultation receiver detection system described in the present invention, when the two positioning and solving modules and the two control modules of the system are in hot standby operation, the two modules can communicate in real time and transmit information such as positioning and solving and control status to each other, thereby realizing rapid joint solving and control. When a positioning and solving module has a single particle problem and needs to be reset and restarted, the other positioning and solving module can quickly transmit the positioning and solving information to the restarted positioning and solving module, and the restarted positioning and solving module uses the transmitted information to realize instantaneous positioning and solving, thereby minimizing the impact of single particles.

[0050] (3) The autonomous management and multi-redundant satellite-borne occultation receiver detection system described in the present invention realizes on-orbit autonomous management of free switching of various modes through the combination of control program and circuit design, control program and algorithm, and monitoring the working status information of each module, thereby realizing seamless switching, minimizing the impact of the space environment on the output data, and greatly ensuring the continuity of the data.

[0051] (4) The present invention discloses an autonomously managed, multi-redundant satellite-borne occultation receiver detection system. A multi-level control program and circuit are designed for program loading and injection of FPGA devices within the system. The system greatly improves the reliability of the system through multi-level safeguards such as autonomous reloading, autonomous switching of program sources, autonomous onboard program injection, and ground injection. BRIEF DESCRIPTION OF THE DRAWINGS

[0052] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings:

[0053] Figure 1 A schematic diagram of a detection system according to an embodiment of the present invention;

[0054] Figure 2 A schematic diagram of the working principle of the joint positioning solution and mutual placement according to an embodiment of the present invention;

[0055] Figure 3 This is a schematic diagram of the control principle of the interface control module according to an embodiment of the present invention;

[0056] Figure 4 A schematic diagram of program redundancy and switching paths according to an embodiment of the present invention;

[0057] Figure 5 A schematic diagram of a circuit for the program redundancy and path switching principle according to an embodiment of the present invention;

[0058] Figure 6 A second schematic diagram of a circuit for the program redundancy and path switching principle according to an embodiment of the present invention;

[0059] Figure 7 A third schematic diagram of a circuit for the program redundancy and path switching principle according to an embodiment of the present invention;

[0060] Figure 8 A fourth schematic diagram of a circuit for the program redundancy and path switching principle according to an embodiment of the present invention;

[0061] Fig. 9 A schematic diagram of a circuit of the modular redundancy adaptive circuit principle according to an embodiment of the present invention;

[0062] Fig.10 A second schematic diagram of a circuit of the modular redundancy adaptive circuit principle according to an embodiment of the present invention;

[0063] Fig.11 A third schematic diagram of a circuit of the modular redundancy adaptive circuit principle according to an embodiment of the present invention;

[0064] Fig.12A fourth schematic diagram of a circuit of the modular redundancy adaptive circuit principle according to an embodiment of the present invention;

[0065] Fig.13 A fifth schematic diagram of a circuit of the modular redundancy adaptive circuit principle according to an embodiment of the present invention;

[0066] Fig.14 A sixth circuit diagram of the modular redundancy adaptive circuit principle according to an embodiment of the present invention;

[0067] Fig.15 Schematic diagram of circuit 7 of the modular redundancy adaptive circuit principle according to an embodiment of the present invention;

[0068] Fig.16 FIG8 is a circuit diagram of the modular redundant adaptive circuit principle according to an embodiment of the present invention. DETAILED DESCRIPTION

[0069] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other.

[0070] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and the like are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", and the like may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0071] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood by specific circumstances.

[0072] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0073] like Figure 1 As shown, an autonomous management, multi-redundant satellite-borne occultation receiver detection system includes a detection system, the detection system includes a positioning antenna, a first occultation antenna, a second occultation antenna, a first occultation radio frequency module, a positioning radio frequency component, a second occultation radio frequency module, an A positioning solution module, a B positioning solution module, an A interface control module, a B interface control module, a power supply gating unit, a power supply component, a clock unit and a satellite service computer, the positioning antenna is respectively connected to the A positioning solution module and the B positioning solution module through the positioning radio frequency component, the first occultation antenna is respectively connected to the A positioning solution module and the B positioning solution module through the first occultation radio frequency module, the second occultation antenna is respectively connected to the A positioning solution module and the B positioning solution module through the second occultation radio frequency module The star radio frequency module is communicatively connected with the A positioning solution module and the B positioning solution module respectively, and the A positioning solution module and the B positioning solution module are bidirectionally communicatively connected. The A positioning solution module is also bidirectionally communicatively connected with the A interface control module and the B interface control module respectively, and the B positioning solution module is also bidirectionally communicatively connected with the A interface control module and the B interface control module respectively. The A interface control module and the B interface control module are bidirectionally communicatively connected, and the A interface control module and the B interface control module are also bidirectionally communicatively connected with the satellite service computer, and the A interface control module and the B interface control module are also communicatively connected with the power supply gating unit, and the power supply gating unit is communicatively connected with the power supply component.

[0074] In a preferred embodiment of the present invention, the system uses a positioning antenna, two occultation antennas, two positioning solution modules, and two interface control modules, which can process navigation signals of multiple frequencies such as GPS L1 / L2 / L5 and Beidou B1 / B2 / B3. The signals received by the positioning antenna and the occultation antenna are amplified and divided by the radio frequency receiving module and then enter the A positioning solution module and the B positioning solution module respectively. After being processed by the two positioning solution modules, the A positioning solution module and the B positioning solution module, the solved data are transmitted to the A interface control module and the B interface control module respectively. The A interface control module and the B interface control module package the data according to the protocol and transmit it to the satellite star service calculation according to the needs of the whole star. Through the power supply and logic switching circuit design in conjunction with the adaptive control program, the signals received by the positioning antenna and the occultation antenna are all passed through the A positioning solution module and the B positioning solution module and the A interface control module and the B interface control module. The two positioning solution modules can be redundant backups for each other, and can be cold backup or hot backup. The two control modules are redundant backups for each other, and can be cold backup or hot backup. The entire system can gradually switch between eight different combination modes according to the satellite service computer instructions, the pre-designed priorities and the working status of each module of the occultation receiver through the control program and circuit design. Each mode can ensure the normal reception and processing of data from one positioning antenna and two occultation antennas. This greatly improves the reliability of the entire system.

[0075] In a preferred embodiment of the present invention, Figure 2 The two positioning and solving modules of the satellite-borne occultation receiver detection system shown in the figure can communicate in real time, transmit information such as positioning and solving and control status to each other, and realize fast joint solving and control. Taking the A positioning and solving module as an example (the B positioning and solving module program is completely consistent with A, and the A / B module is determined according to the hardware circuit pin), when the A positioning and solving module is turned on or soft reset or hard reset and reloaded, the A positioning and solving module starts to run the positioning and solving program to search for stars and solve the positioning, and the A positioning and solving module simultaneously receives the positioning and solving information transmitted by the B positioning and solving module. When the total number of captured stars of the A positioning solution module and the B positioning solution module is 4, such as (0 stars in the A positioning solution module and 4 stars in the B positioning solution module, or 1 star in the A positioning solution module and 3 stars in the B positioning solution module, or 2 stars in the A positioning solution module and 2 stars in the B positioning solution module, etc., the total number of captured stars of the two positioning solution modules is greater than or equal to 4), due to the rapid exchange of positioning solution information, the A positioning solution module and the B positioning solution module can achieve instant positioning solution after screening by evaluating the captured stars, pseudorange, carrier phase, satellite position and speed information in the transmitted positioning solution information and judging the relevant thresholds. Specifically, the positioning solution information of the B positioning solution module is judged in the A positioning solution module; if the judgment fails, the positioning solution information of the B positioning solution module and the information captured by the A positioning solution module are combined to obtain the joint positioning solution information; and the duplicate satellite information is eliminated from the joint positioning solution information, and the better satellite information (the better satellite information is the satellite information with small positioning clock error, clock drift, and carrier phase) is selected for joint capture and solution positioning. The above function can shorten the capture and positioning solution time to 1 / 3 of the positioning solution time of the single A positioning solution module or the single B positioning solution module on average when the machine is turned on. When the B positioning solution module is in the positioning state, through the mutual placement and selection of information, the A positioning solution module can achieve instantaneous positioning of less than 2s after reloading.

[0076] In a preferred embodiment of the present invention, Figure 3The control principle of the interface control module is shown as follows. Taking the A interface control module as an example, it first receives satellite instructions, and at the same time communicates with the B interface control module to transmit their respective working states to each other, reads and determines some physical telemetry of the B interface control module, determines the initial working state of the A interface control module, and selects the initialization working mode. The B interface control module performs the same operation. The A interface control module receives the positioning and solution information of the A / B positioning and solution module, monitors the positioning and solution information of the positioning and solution module, and determines the threshold of the data of the positioning and solution information. If the threshold exceeds the tolerance, the soft instruction is first executed to soft reset and load the corresponding positioning and solution module. The A / B positioning and solution module performs positioning and solution by searching for satellites, using part of the information of the last positioning and solution, and receiving the information of the B / A positioning and solution module. Then the positioning solution information of the positioning solution module is monitored, and the data threshold of the positioning solution information is determined. If the data threshold of the positioning solution information is still abnormal, the A / B positioning solution module is hard reset, and the positioning solution information of the positioning solution module is monitored again, and the data threshold monitoring and determination are performed. If it is abnormal again, the 8 working modes are switched on the satellite in an adaptive and autonomous manner level by level according to the priority set in advance by the program until a stable working mode is reached.

[0077] In a preferred embodiment of the present invention, Figure 4 Schematic diagram of program loading and uploading redundancy and switching path. This system has designed five layers of safeguard measures for loading and uploading the FPGA program of the positioning and solving module. Taking the A positioning and solving module as an example, after the FPGA is turned on, the program in the program FLASH is loaded according to the normal process. The A / B interface control module monitors the solving status of the A positioning and solving module. When a single particle event causes an abnormality, the interface control module reloads the FPGA. If the status is abnormal again after loading, the interface control module switches to the backup FLASH channel through the program loading control circuit, and the FPGA reloads it. When it is determined that the backup program FLASH program is overturned by a single particle, the interface control module selects the backup program stored on the satellite for program transfer. If the program stored on the satellite is abnormal, the A / B positioning and solving module program can be read through the A interface timing control and the B interface timing control. Because the circuit design is adaptive to various modes, the A interface control module completely autonomously monitors the status and negotiates the real-time information of the B interface control module to achieve multiple redundancy of program uploading and completely autonomous management on orbit. When all the above measures fail, the program can still be uploaded through the ground.

[0078] In a preferred embodiment of the present invention, Figure 5-Figure 8Program redundancy, switching path schematics, and the design of the adaptive circuit utilize the characteristics of the AVC4T245 driver chip and the ALVC12 and MT25QL158 chip select pins that are in high impedance when they are not selected, which does not affect the reading and writing of other chips on the circuit line. Combined with the multiple enable control pins of the chip, the interface control module controls the switching of multiple enable pins according to the predetermined program, and then selects different paths to switch the path loaded by the FPGA and the source of the program. With the control of the program, it can fully achieve autonomous management of on-orbit adaptation and minimize the impact of single particles in space.

[0079] In a preferred embodiment of the present invention, Figure 9-Figure 16 Schematic diagram of module redundancy adaptive circuit. The signal of A positioning and solving module is connected to the two pins of A and B of SN7LVTH162245 respectively. The signal of B positioning and solving module is connected to the two pins of A and B of SN7LVTH162245 respectively. The signal of SN74LVTH162245 is selected through two different control enable signals. The signal of A positioning and solving module is transmitted to A and B interface control modules respectively. The signal of B positioning and solving module is transmitted to A and B interface control modules respectively. The output of A and B interface control modules is added to A and B positioning and solving modules, and the reset signal is merged together through OC gate circuit. The output signals of A and B interface control modules are transmitted to A and B positioning and solving modules. The above circuit is suitable for 8 different module redundancy settings, and can cooperate with the program to achieve real-time switching of various working modes.

[0080] Aiming at the problems of large volume, heavy weight, high power consumption and high cost of occultation payloads on traditional large satellites and low reliability, short life and continuity of detection data on small satellites, the present invention proposes an autonomous management and multi-redundant satellite-borne occultation receiver detection system, which adopts a control algorithm and circuit combination method to achieve low cost of equipment while ensuring high reliability.

[0081] Advantages of the present invention:

[0082] 1. It uses one positioning antenna, two occultation antennas, two positioning and solving modules, and two control modules, which can process signals of multiple frequency points of GPS and Beidou. The two positioning and solving modules can back up each other, and can be cold backup or hot backup. The two control modules can back up each other, and can be cold backup or hot backup. Through the control program and circuit design, the whole system can form 8 combination modes, including A positioning and solving module + A interface control module, B positioning and solving module + B interface control module, A positioning and solving module + B interface control module, B positioning and solving module + A interface control module, A positioning and solving module + B positioning and solving module + A interface control module, A positioning and solving module + B positioning and solving module + B interface control module, A positioning and solving module + B positioning and solving module + A interface control module + B interface control module, (A positioning and solving module + B positioning and solving module + A interface control module) + (A positioning and solving module + B positioning and solving module + B interface control module). According to different task requirements, different combination modes can be selected, which greatly improves the reliability of the system.

[0083] 2. When the two positioning and solving modules and two control modules of the system are in hot backup, the two modules can communicate in real time and transmit information such as positioning and solving and control status to each other to achieve rapid joint solving and control. When a positioning and solving module has a single particle problem and needs to be reset and restarted, the other positioning and solving module can quickly transmit the positioning and solving information to the restarted positioning and solving module. The restarted positioning and solving module uses the transmitted information to achieve instant positioning and solving, minimizing the impact of single particles.

[0084] 3. The system combines control programs and circuit designs, and through control programs and algorithms, and by monitoring the working status information of each module, it realizes on-orbit autonomous management of free switching of various modes, achieves seamless switching, minimizes the impact of the space environment on output data, and greatly ensures data continuity.

[0085] 4. A multi-level control program and circuit are designed for program loading and injection of FPGA devices within the system. The reliability of the system is greatly improved through multi-level security measures such as autonomous reloading, autonomous switching of program sources, autonomous on-board program injection, and ground injection.

[0086] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. An autonomous, multi-redundant satellite-borne occultation receiver detection system, characterized in that: The invention comprises a detection system, which comprises a positioning antenna, a first occultation antenna, a second occultation antenna, a first occultation radio frequency module, a positioning radio frequency component, a second occultation radio frequency module, at least one positioning solution module, at least one interface control module, a power supply gating unit, a power supply component, a clock unit and a satellite service computer. The positioning antenna is communicatively connected to the positioning solution module through the positioning radio frequency component, the first occultation antenna is communicatively connected to the positioning solution module through the first occultation radio frequency module, the second occultation antenna is communicatively connected to the positioning solution module through the second occultation radio frequency module, the positioning solution module is also bidirectionally communicatively connected to the interface control module, the interface control module is also bidirectionally communicatively connected to the satellite service computer, the interface control module is also communicatively connected to the power supply gating unit, and the power supply gating unit is communicatively connected to the power supply component; When the number of the positioning and solving modules of the detection system is two, they are respectively A positioning and solving module and B positioning and solving module; when the number of the interface control modules of the detection system is two, they are respectively A interface control module and B interface control module; the positioning antenna is respectively connected to the A positioning and solving module and the B positioning and solving module in communication through the positioning radio frequency component; the first occultation antenna is respectively connected to the A positioning and solving module and the B positioning and solving module in communication through the first occultation radio frequency module; the second occultation antenna is respectively connected to the A positioning and solving module and the B positioning and solving module in communication through the second occultation radio frequency module; the A positioning and solving module is bidirectionally connected to the B positioning and solving module; the A positioning and solving module is also bidirectionally connected to the A interface control module and the B interface control module; the B positioning and solving module is also bidirectionally connected to the A interface control module and the B interface control module; the A interface control module and the B interface control module are bidirectionally connected; the A interface control module and the B interface control module are also bidirectionally connected to the satellite service computer; the A interface control module and the B interface control module are also bidirectionally connected to the power supply gating unit; The working modes of the detection system include 8 working modes, and the expressions of the 8 working modes are respectively: A positioning solution module and A interface control module (1); B positioning solution module + B interface control module (2); A positioning solution module + B interface control module (3); B positioning solution module + A interface control module (4); A positioning and solving module + B positioning and solving module + A interface control module (5); A positioning and solving module + B positioning and solving module + B interface control module (6); A positioning and solving module + B positioning and solving module + A interface control module + B interface control module formula (7); (A positioning and solving module + B positioning and solving module + A interface control module) + (A positioning and solving module + B positioning and solving module + B interface control module) (8); The A positioning and solving module and the B positioning and solving module implement a joint positioning and solving mutual process. The implementation process of the A positioning and solving module is the same as that of the B positioning and solving module. The implementation process of the A positioning and solving module includes the following steps: A1. When the A positioning solution module is powered on or soft-reset or hard-reset and reloaded; A2, A positioning solution module starts to search for satellites and solve positioning through the captured information; A3, A positioning and solving module receives the positioning and solving information transmitted by B positioning and solving module; A4. When the total number of satellites captured by the A positioning and solving module and the B positioning and solving module is greater than or equal to 4, the A positioning and solving module determines the positioning and solving information of the B positioning and solving module; A5: If the judgment is passed, the positioning information of the B positioning module is set to the positioning information of the A positioning module to achieve immediate positioning, and then go to step A8; A6. If the judgment fails, the positioning solution information of the B positioning solution module is combined with the information captured by the A positioning solution module to obtain the combined positioning solution information; A7, after removing duplicate satellite information from the joint positioning solution information, perform joint capture solution positioning; A8, correcting the immediate positioning information and the joint capture and solution positioning information to obtain corrected positioning solution information; A9, transmitting the corrected positioning solution information to step A1 through the A interface control module; The interface control module performs the following operations: First, the satellite command is received, the A interface control module communicates with the B interface control module at the same time to transmit their respective working states to each other, reads and identifies the physical telemetry of the B interface control module, determines the initial working state of the A interface control module, and selects the initialization working mode; The execution operation of the A interface control module is the same as that of the B interface control module; The execution operation of the A interface control module includes the following steps: B1, A positioning solution module monitors its positioning solution information; B2, data threshold for determining positioning solution information; B3. If the data threshold of the positioning solution information is abnormal, first execute the soft reset instruction to perform a soft reset load on the A positioning solution module, and then return to step B1; If the data threshold of the positioning solution information is still abnormal, execute a hard reset instruction to load the A positioning solution module, and then return to step B1; B4. If the data threshold of the positioning solution information is abnormal again, the eight working modes are switched level by level according to the priority preset by the program until the data threshold of the positioning solution information of one working mode is normal; The FPGA program loading redundancy and switching path flow of the positioning and solving module include the FPGA program flow of the A positioning and solving module and the FPGA program flow of the B positioning and solving module; The FPGA program flow of the A positioning and solving module is the same as that of the B positioning and solving module; the FPGA program flow of the A positioning and solving module includes the following steps: After the FPGA of C1 and A positioning and solving modules is turned on, the program in the control circuit loading program FLASH is loaded according to the program; C2, the A interface control module monitors the FPGA solving state of the A positioning and solving module. When a single particle event causes an abnormality, the A interface control module reloads the FPGA of the A positioning and solving module. If the state is abnormal again after loading, the A interface control module switches to the channel of the backup program FLASH through the program loading control circuit, and the FPGA of the A positioning and solving module is reloaded; C3. When it is determined that the backup program FLASH is overturned by a single particle, the A interface control module selects the backup program stored in the satellite service computer for program transfer; if the backup program stored in the satellite service computer is abnormal, the A positioning solution module program is read through the interface timing control of the A interface control module.

2. The autonomously managed, multi-redundant spaceborne occultation receiver detection system according to claim 1, characterized in that: In step A2, the information captured by the A positioning solution module includes the captured satellite number, pseudorange and carrier phase.

3. The autonomous, multi-redundant satellite-borne occultation receiver detection system according to claim 1, characterized in that: In step A3, the positioning solution information transmitted by the B positioning solution module includes frame check, captured satellite number, pseudorange, carrier phase, satellite position and satellite speed.

4. The autonomously managed, multi-redundant spaceborne occultation receiver detection system according to claim 1, characterized in that: In step A4, when the number of captured stars by the A positioning and solving module and the B positioning and solving module is equal to 4, the capture situations are as follows: The A positioning and solving module captured 0 stars, and the B positioning and solving module captured 4 stars; The A positioning and solving module captured 1 star, and the B positioning and solving module captured 3 stars; The A positioning and solving module captured 2 stars, and the B positioning and solving module captured 2 stars.

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