A joint design method for measurement, control and information systems of multi-device combined spacecraft

Abstract

A joint design method for measurement, control and information systems for multi-device combination spacecraft, comprising the following steps: (1) providing a maximum set of detector working modes; (2) determining the measurement and control antenna layout according to the detector configuration, and performing simulation analysis to provide the radiation coverage and impact of the directional pattern under various modes; (3) determining the working mode of measurement, control and information interaction in the combined state to meet the full-space measurement and control requirements in each mode; (4) designing the remote control and telemetry information interaction between devices; (5) improving the flight program settings according to the ground measurement and control support and mission requirements. (6) traversing the spacecraft working modes to verify whether the joint design of the measurement, control and information systems meets the full-space measurement, control and information transmission requirements in each stage. If so, proceed to (7); otherwise, return to (2); (7) completing the joint design of the measurement, control and information systems. The present invention realizes the function reuse design under multi-mode state, and meets the full-space measurement, control and communication requirements of the detector in various states with the minimum system design cost.

Description

Technical Field

[0001] The present invention aims at multi-device combination spacecraft. Due to the complex configuration of the detector, the measurement and control antenna is likely to be blocked by solar panels, landing legs, etc., and the traditional single-device measurement and control cannot meet the full-space measurement and control requirements of the detector. A joint design method for multi-device combination measurement and control and information system is proposed to realize the full-space measurement and control solution of the detector in various working modes such as multi-device combination, two-device combination and single device. Background Art

[0002] In the state of multiple device combination, due to the limitation of configuration layout, it is impossible to rely on one or more devices to realize the full-space measurement and control function alone. It is necessary to optimize the design from the perspective of the overall design of the detector to realize the omnidirectional measurement and control function in the state of multiple device combination.

[0003] Taking a four-device combination as an example, the individual devices are designated A, B, C, and D. Due to the detector's layout, when combined, the X-band tracking and control antennas (installed on devices A and B) could be blocked by the solar panels (installed on devices A and C). Furthermore, throughout flight, the detector may operate in a combination of four devices, a combination of two devices, or even independently.

[0004] Before the four detectors are separated, to ensure the detector's energy supply, the solar panels of both devices A and C must be deployed. To avoid mutual obstruction, the solar panels of the two devices are installed vertically, with the two panels crossing each other. Under this configuration, the measurement and control antenna of device A is installed in a direction parallel to the direction of deployment of the solar panels of device C, located directly below the deployment of the solar panels of device C (-X direction). The measurement and control antenna of device B is installed in a direction parallel to the direction of deployment of the solar panels of device A, located directly above the deployment of the solar panels of device A (+X direction). Therefore, when the four devices are combined, the measurement and control antenna of device A is affected by the obstruction of the solar panels of device C in the +X direction, and the measurement and control antenna of device B is affected by the obstruction of the solar panels of device A in the -X direction. Using only device A or device B cannot meet the full-space measurement and control requirements of the detector. Summary of the Invention

[0005] The technical problem solved by the present invention is: to overcome the shortcomings of the existing technology and propose a design method that can realize the full-space measurement and control function in a combination of multiple devices (four devices or more). Due to the limited resources on the detector, there are strict restrictions on the weight and power consumption of the equipment. This method can realize the function of omnidirectional measurement and control in various modes at a relatively low cost.

[0006] The technical solution of the present invention is:

[0007] The joint design method of the measurement, control and information system of a multi-device combined spacecraft has the following steps:

[0008] (1) Establish a set of working modes and give the maximum working mode set of the detector based on the actual working mode of the detector on orbit;

[0009] (2) Determine the measurement and control antenna layout based on the detector configuration, and perform simulation analysis to determine the radiation coverage and impact of the directional pattern in various modes;

[0010] (3) According to steps (1) and (2), determine the working mode in which measurement and control and information interaction are required under the state of the assembly to meet the full-space measurement and control requirements in each mode;

[0011] (4) Complete the design of remote control and telemetry information interaction between devices, and realize remote control and telemetry information interaction between devices at the minimum cost based on the design of a single device;

[0012] (5) Determine the ground measurement and control system implementation method and improve the flight program settings based on the ground measurement and control support situation and mission requirements;

[0013] (6) According to the probe flight program timing design, traverse the spacecraft working mode and verify whether the joint design of the measurement, control and information system meets the full-space measurement, control and information transmission requirements of each stage. If so, proceed to step (7); otherwise, return to step (2) and redefine the measurement and control antenna layout and simulation;

[0014] (7) Complete the joint design of measurement, control and information systems.

[0015] Preferably, in step (2), the detector with independent measurement, control and data transmission function must have a measurement and control antenna layout that can meet the requirements of full space coverage of measurement and control.

[0016] Preferably, the antenna of the same detector cannot be installed on the same side panel as the solar wing.

[0017] Preferably, for detectors with single-device measurement and control requirements, the antenna achieves full-space measurement and control coverage through a half-space heterogeneous frequency array.

[0018] Preferably, if the radiator of the detector's measurement and control antenna is lower than the extravehicular equipment, the measurement and control antenna should be raised so that it is higher than the extravehicular equipment.

[0019] Preferably, for detectors with return requirements, the layout of their measurement and control antennas should avoid areas with the highest heat flux density.

[0020] Preferably, the ground station of the ground measurement and control system only sends one frequency uplink signal at the same time, and the ground station has the function of time-sharing transmission of M frequencies, where M is the number of detectors with independent measurement and control and data transmission capabilities.

[0021] Preferably, the ground station has the ability to simultaneously receive M frequency points in the downlink, and selects the frequency point for receiving one of the M detectors based on the current favorable posture to the ground.

[0022] Preferably, when multiple devices are combined, the detector's attitude changes greatly when performing orbital maneuvers and attitude adjustments before separation of multiple devices. At this time, the ground adopts dual-station measurement and control, and the dual stations are visible at the same time.

[0023] Preferably, in the multi-device combination state, if a detector has an abnormal situation, if the ground station can receive the downlink signal of the detector, the corresponding uplink frequency point is selected according to the received downlink signal to send the emergency remote control command.

[0024] Compared with the prior art, the present invention has the following beneficial effects:

[0025] (1) This invention proposes a full-space measurement and control solution for detectors in a multi-device combination state. From an engineering perspective, this invention comprehensively considers factors such as mission requirements, equipment weight and power consumption limitations, and proposes a full-space measurement and control solution for detectors in a multi-device combination state.

[0026] (2) The present invention proposes a multi-device combined measurement and control scheme based on the layout conditions of the X-band measurement and control antenna and the solar wing in the multi-device combination state. Taking four devices as an example, the BC two-device combination and the AD two-device combination measurement and control scheme are adopted to achieve full space measurement and control coverage in the four-device combination state, solving the problem of solar wings blocking the measurement and control antenna.

[0027] (3) The present invention proposes to combine the ground measurement and control system measurement and control implementation with the iterative design idea of ​​the flight program, determine the satisfaction of each working mode from the perspective of actual mission execution, and fully verify the effectiveness of the working mode design. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 This is a flow chart of the joint design method of the multi-device combined spacecraft measurement, control and information system of the present invention;

[0029] Figure 2 Schematic diagram of the relationship between the detector and the mechanical coordinate system of each device of the present invention;

[0030] Figure 3 This is a schematic diagram of the relationship between the four-device combination status measurement and control antenna and the solar wing installation position of the present invention;

[0031] Figure 4 It is the single device cross-sectional direction diagram;

[0032] Figure 5 is the total field cross-sectional pattern of the two-device combination;

[0033] Figure 6 This is the total field cross-sectional pattern of the four-device combination. DETAILED DESCRIPTION

[0034] The present invention aims at multi-device combination spacecraft. Due to the complex configuration of the detector, the measurement and control antenna is blocked by solar panels, landing legs, etc., and the traditional single-device measurement and control cannot meet the full-space measurement and control requirements of the detector. A method for jointly designing multi-device combination measurement and control and information systems is proposed to realize the full-space measurement and control solution of the detector in various working modes such as multi-device combination, two-device combination and single device.

[0035] The full-space measurement and control solution of the detector of the present invention in the state of multiple devices (four or more) is as follows:

[0036] (1) Establish a set of working modes and give the maximum working mode set of the detector based on the actual working mode of the detector on orbit;

[0037] (2) Determine the measurement and control antenna layout based on the detector configuration and solar wing installation position, and perform simulation analysis to determine the radiation coverage and impact of the directional pattern in various modes;

[0038] (3) According to (1) and (2), analyze the working mode of the combination that needs to perform inter-device measurement and control and information exchange, and determine the combined measurement and control working mode of two combinations (or two devices), with each combination (or each device) responsible for half-space measurement and control;

[0039] (4) Based on (3), complete the design of remote control and telemetry information interaction between devices, and realize remote control and telemetry information interaction between devices at the minimum cost based on the design of a single device;

[0040] (5) Determine the ground measurement and control system implementation method and improve the flight program settings based on the ground measurement and control support situation and mission requirements;

[0041] (6) According to the probe flight program timing design, traverse the spacecraft working mode and verify whether the joint design of the measurement, control and information system meets the full-space measurement, control and information transmission requirements of each stage. If yes, proceed to step (7); otherwise, start from step (2) to redefine the measurement and control antenna layout and simulation;

[0042] (7) Complete the joint design of measurement, control and information systems and provide a solution report.

[0043] Example:

[0044] First, a brief introduction is given to the measurement, control and data transmission capabilities that each device in the measurement, control and data transmission subsystem in this embodiment must possess, as follows:

[0045] 1) Device A: It must have independent measurement, control, and data transmission capabilities to meet the measurement, control, and data transmission requirements of a single device, a combination of two devices (AD), and a combination of four devices;

[0046] 2) Device B: It must have independent measurement and control capabilities to meet the measurement and control requirements of a single device, a combination of two devices (BC), and a combination of four devices;

[0047] 3) Device C: There is no need for single-device measurement and control. To save weight, the device C assumes the measurement and control functions of the CD device combination. The device C only has a data transmission function, and the telemetry and remote control data on the device C are forwarded through the device B.

[0048] 4) Device D: It must have independent measurement and control functions and provide search and rescue signals. It is only used in single-device working mode after being separated from device A.

[0049] For multi-device combination spacecraft, due to its complex configuration and complex multi-state working mode, it is difficult to meet the full-space measurement, control and communication requirements of the combination state by using each sub-device alone. Therefore, from the perspective of system design, the present invention proposes a joint design method of measurement, control and information systems to realize functional reuse design under multi-mode state, and realize the full-space measurement, control and communication requirements of the detector in various states with the minimum system design cost.

[0050] The following combination Figure 1 The implementation process of the method of the present invention is specifically introduced. The specific steps are as follows:

[0051] (1) Establish a working mode set and give the maximum working mode set of the detector based on the actual on-orbit working mode of the detector.

[0052] After analysis, the detector has three combined working modes and four single-device working modes. The measurement and control, data transmission and beacon requirements of each mode are shown in Table 1.

[0053] Table 1 Maximum working mode set of detectors

[0054]

[0055] As shown in the table above, device A requires both measurement and control and data transmission. Therefore, in the AD two-device combination, device A can be used primarily for measurement, control, and data transmission. Device B only requires measurement and control, while device C only requires data transmission. Therefore, in the BC two-device combination, device B can perform measurement and control, while device C can perform data transmission, thus achieving functional reuse. For a four-device combination, either device A or B can be used for measurement and control, while device A can be used for data transmission. Only device D requires a beacon, so the beacon is configured on device D.

[0056] (2) According to the detector configuration, the measurement and control antenna layout is determined, and simulation analysis is performed to give the radiation coverage and impact of the directional pattern under various modes.

[0057] According to the analysis in step (1), both device A and device B must have independent measurement and control data transmission functions, and the measurement and control antenna layout must be able to meet the requirements of full space coverage of measurement and control.

[0058] In the state of the four-device combination, in order to ensure energy, the solar wing of device C is installed parallel to the Z axis of the detector, and the solar wing of device A is installed parallel to the Y axis of the detector, that is, the solar wing of device C and the solar wing of device A are installed vertically, such as Figure 3 The diagram of the relationship between the detector and the mechanical coordinate system of each device is shown in Figure 2 To avoid obstruction and reduce multipath interference, the antenna of the same device cannot be installed on the same side panel as the solar panel.

[0059] Based on the above principles, since the A-device solar panels are mounted on the ±Y sides of the probe, the A-device's +X direction needs to be docked with the C-device, and the -X direction houses the engine and tank. Therefore, the tactical tracking and control omnidirectional antennas are installed on the ±Z sides of the probe. The ±Z antennas each handle half-space tactical tracking and control tasks, achieving full-space tactical tracking and control coverage through a half-space, cross-frequency array arrangement. The A-device directional antenna is mounted on the -Z side of the probe. The B-device solar panels are mounted on the ±Z sides of the probe. The B-device tactical tracking and control antenna installation needs to meet the full-space tactical tracking and control requirements for both a single device and a combined BC-device configuration. Therefore, the tactical tracking and control omnidirectional antennas are installed on the ±Y sides of the probe. To ensure tactical tracking and control coverage for the BC-device combination in flight and to prevent obstruction of the tactical tracking and control antenna by the C-device, the X-band tactical tracking and control antenna needs to be elevated. The ±Y antennas each handle half-space tactical tracking and control tasks, achieving full-space tactical tracking and control coverage through a half-space, cross-frequency array arrangement.

[0060] On this basis, the directional pattern simulation of the four-device combination, the two-device combination and the single device was carried out to confirm the layout and height of the antenna. At the same time, according to the simulation results, the directional pattern concave point situation was analyzed. Figure 4 , the total field cross-sectional direction diagram of the two-device combination is shown in Figure 5 , the total field cross-sectional direction diagram of the four-device combination is shown in Figure 6 .

[0061] It can be seen that the directional patterns of the single-device and two-device combination meet the requirements for omnidirectional measurement and control. However, the directional pattern of the four-device combination has a large concave area, as shown by the red circle, which does not meet the requirements of omnidirectional measurement and control. Therefore, the four-device combination needs to use the combined measurement and control mode.

[0062] The D-device was designed for tracking and control as a standalone device, with its S-band antennas located on its sidewalls near the lines of quadrants II and IV. Because the D-device's inertial flight attitude during both the pre-reentry and exit phases is in quadrant I, the tracking and control antennas were positioned to avoid areas with the highest heat flux density. Furthermore, after reviewing the orbit and ground station locations, tracking and control were performed without using interference areas outside the antenna's main beam.

[0063] (3) According to (1) and (2), the working mode of the combination that needs to perform inter-device measurement and control and information exchange is analyzed, and the combined measurement and control working mode of two combinations (or two devices) is determined, and each combination (or each device) is responsible for half-space measurement and control.

[0064] According to the coordinate relationship under the combined state of the four devices, device A and device B are determined to be responsible for the measurement and control tasks of half space respectively, device B is responsible for the +X half space, and device A is responsible for the -X half space; when the earth appears in the +X half space of the detector, the BC two-device combination completes the measurement and control task of the detector; when the earth appears in the -X half space of the detector, the AD two-device combination completes the measurement and control task of the detector.

[0065] (4) According to (3), complete the design of remote control and telemetry information interaction between devices, and realize remote control and telemetry information interaction between devices at the lowest cost based on the design of a single device.

[0066] Based on the above inter-device measurement and control multiplexing design, and according to the remote control and telemetry requirements of each device, the inter-device remote control and telemetry information interaction channels are designed as follows.

[0067] In the four-device combination operating mode, measurement and remote control uplink is performed using either device A or device B. Device B can transmit commands to devices B, C, and A, as well as to the BC combination, devices A, and D. Device A can transmit commands to device A, as well as to the BC combination, devices A, and D. In the four-device combination operating mode, telemetry downlink is performed using either device A or device B. Device A's data transmission channel simultaneously transmits telemetry data, serving as a backup for the measurement and control channel. Both devices B and A can transmit telemetry parameters for devices A, D, and the combination.

[0068] In the BC combination operating mode, device B is used for measurement and control remote uplink. Device B can transmit commands to both devices B and C, as well as to the BC combination. In the upper combination operating mode, device B is used for telemetry downlink, and device C's data transmission channel can also transmit telemetry data downlink, serving as a backup for the measurement and control channel. Device B can also transmit telemetry parameters for the upper combination downlink.

[0069] In the AD combination operating mode, device A is used for measurement and control remote uplink. Device A can be used to transmit commands to device A, as well as to both device A and device D. In the AD combination operating mode, device A is used for telemetry downlink. The data transmission channel of device A can also transmit telemetry data downlink, serving as a backup for the measurement and control channel. Device A can also transmit telemetry parameters for the AD combination.

[0070] (5) Determine the ground measurement and control system measurement and control implementation method, and improve the flight program settings based on the ground measurement and control support situation and mission requirements.

[0071] The ground station of the ground measurement and control system transmits only one uplink frequency at a time. It has the ability to time-share transmission across four frequencies (two for device A and two for device B). The ground station also has the ability to simultaneously receive signals on both frequencies, either for device A or for device B. The frequency of either device A or B is selected based on the system's current favorable attitude relative to the ground.

[0072] When the four devices are in a combined state, the attitude of the detector changes greatly when performing orbital maneuvers and attitude adjustments before separation of the four devices. At this time, the ground adopts dual-station measurement and control, and both stations are visible at the same time. For downlink telemetry, one ground station receives the downlink dual-frequency points of device A, and the other receives the downlink dual-frequency points of device B to ensure normal reception of downlink telemetry; for uplink remote control, one ground station works at frequency 1 or frequency 2 of device B, and the other ground station works at frequency 1 or frequency 2 of device A, for sending uplink remote control commands.

[0073] When the four devices are in the combined state, if the detector has an abnormal situation, if the ground station can receive the downlink signal, it will select the corresponding uplink frequency according to the received downlink signal to send emergency remote control commands (operate according to the fault mode, such as restoring the attitude control of the detector, resetting the faulty unit, etc.).

[0074] To sum up, under the four-device combination mode, the ground measurement and control system has the ability to implement measurement and control of the detector.

[0075] (6) According to the probe flight program timing design, traverse the spacecraft working mode and verify whether the joint design of the measurement, control and information system meets the full-space measurement, control and information transmission requirements of each stage. If yes, proceed to step (7); otherwise, start from step (2) to redefine the measurement and control antenna layout and simulation.

[0076] During the launch-to-orbit insertion phase, the probe was sent directly into the Earth-Moon transfer orbit by a carrier rocket. Tracking and control of the probe was achieved using a four-device combination. Tracking and control were performed by X-band tracking and control equipment, including devices A and B. Device A was the primary tracking and control component.

[0077] During the Earth-Moon transfer phase and the lunar circumlunar flight phase, the four detectors separated. Due to the layout of the solar arrays and the X-band tracking and control antennas, the X-band tracking and control antenna of detector A was shielded by the solar array of detector C in the +X direction, and the X-band tracking and control antenna of detector B was shielded by the solar array of detector A in the -X direction. When the +X direction of the detector was favorable for Earth observation, tracking and control were performed by the combined detectors BC. When the +Y direction of the detector was favorable for Earth observation, the X-band tracking and control signals operated at the f4 frequency. When the -X direction of the detector was favorable for Earth observation, tracking and control were performed by detector A. During the Earth-Moon transfer phase, when downlink data transmission was required, detector C retracted the -Z side solar array, and downlink data transmission was carried out by the directional antenna of detector A.

[0078] During the lunar circumnavigation phase, after the BC and AD devices separate and reach the powered descent phase, the BC device is measured and controlled by the ground station in cooperation with the B device's measurement and control subsystem; the AD device is measured and controlled by the ground station in cooperation with the A device's measurement and control data transmission subsystem.

[0079] During the powered descent, lunar surface operation, and lunar ascent phases, the BC dual-device complex's X-band tracking and control uplink and downlink are handled by the B device, while the C device's data transmission channel handles detection data transmission. The AD dual-device complex achieves tracking and control through the ground station in conjunction with the A device's tracking and control data transmission subsystem.

[0080] During the rendezvous and approach phase to the lunar circumlunar waiting phase, device B uses the ground station for measurement and control, and the AD combination uses the ground station for measurement and control or uses the ground station for measurement and control in the dual-station common view arc phase. When device A needs to transmit downlink data, the downlink data is transmitted through a directional antenna.

[0081] During the lunar-Earth transfer phase, the AD device uses station tracking and control. Downlink data transmission is performed via directional antennas before and after the separation point. Prior to separation, the D device's S-band transponder is activated for S-band tracking and control.

[0082] During the reentry phase, the D-device only performs tracking and control functions. After the D-device deploys its parachute, the recovery beacon operates, and the search helicopter tracks the recovery beacon signal. After the D-device lands, the international rescue beacon begins operating.

[0083] By traversing the spacecraft's operating modes, it was verified that the joint design of the measurement, control and information systems meets the full-space measurement, control and information transmission requirements at all stages of the flight program.

[0084] (7) Complete the joint design of measurement, control and information systems.

[0085] Combining the above steps and design methods, through the joint design of the measurement, control, and information systems for the BC and AD devices, and employing a combined measurement and control mode for the two devices, full-space measurement and control capabilities are achieved for the detector's four-device combination. Under this design model, the ground-based measurement and control system possesses the means to implement measurement and control, and can exchange remote control and telemetry data between the BC and AD devices, achieving omnidirectional measurement and control capabilities in various modes at a minimal cost.

[0086] This invention, while addressing the complex structural layout of detectors, achieves full-space measurement and control capabilities for multiple detectors by integrating two combined measurement and control systems with information systems. This combined measurement and control mode provides the ground-based measurement and control system with the necessary means to implement measurement and control, enabling remote control and telemetry data exchange between the two combined units, while minimizing system costs.

[0087] Parts of the present invention that are not described in detail belong to common knowledge among those skilled in the art.

Claims

1. Joint design method of measurement, control and information system for multi-device combined spacecraft, characterized by Here are the steps: (1) Establish a set of working modes and give the maximum working mode set of the detector based on the actual working mode of the detector on orbit; (2) Determine the measurement and control antenna layout based on the detector configuration, and perform simulation analysis to determine the radiation coverage and impact of the directional pattern in various modes; (3) According to steps (1) and (2), determine the working mode in which measurement and control and information interaction are required under the state of the assembly to meet the full-space measurement and control requirements in each mode; (4) Complete the design of remote control and telemetry information interaction between devices, and realize remote control and telemetry information interaction between devices at the minimum cost based on the design of a single device; (5) Determine the ground measurement and control system implementation method and improve the flight program settings based on the ground measurement and control support situation and mission requirements; (6) According to the probe flight program timing design, traverse the spacecraft working mode and verify whether the joint design of the measurement, control and information system meets the full-space measurement, control and information transmission requirements of each stage. If so, proceed to step (7); otherwise, return to step (2) and redefine the measurement and control antenna layout and simulation; (7) Complete the joint design of measurement, control and information systems.

2. The method for joint design of a multi-device combined spacecraft measurement, control, and information system according to claim 1, characterized in that: In step (2), the layout of the measurement and control antenna of the detector with independent measurement and control data transmission function must be able to meet the requirements of full space coverage of measurement and control.

3. The method for joint design of a multi-device combined spacecraft measurement, control, and information system according to claim 1, characterized in that: The antenna of the same probe cannot be installed on the same side panel as the solar panel.

4. The method for joint design of a multi-device combined spacecraft measurement, control, and information system according to claim 1, characterized in that: For detectors with single-device measurement and control requirements, their antennas achieve full-space measurement and control coverage through a half-space heterogeneous frequency array.

5. The method for joint design of a multi-device combined spacecraft measurement, control, and information system according to claim 1, characterized in that: If the radiator of the detector's tracking and control antenna is lower than the extravehicular equipment, the tracking and control antenna should be raised so that it is higher than the extravehicular equipment.

6. The method for joint design of a multi-device combined spacecraft measurement, control, and information system according to claim 1, characterized in that: For detectors with return requirements, the layout of their tracking and control antennas should avoid areas with the highest heat flux density.

7. The method for joint design of a multi-device combined spacecraft measurement, control, and information system according to claim 1, characterized in that: The ground station of the ground measurement and control system only sends one frequency uplink signal at the same time. The ground station has the function of time-sharing transmission of M frequencies, where M is the number of detectors with independent measurement, control and data transmission capabilities.

8. The method for joint design of a multi-device combined spacecraft measurement, control, and information system according to claim 7, characterized in that: The ground station has the ability to simultaneously receive M frequency points for downlink, and selects the frequency point to receive one of the M detectors based on the current favorable attitude towards the ground.

9. The method for joint design of a multi-device combined spacecraft measurement, control, and information system according to claim 1, characterized in that: When multiple devices are combined, the attitude of the detector changes greatly when performing orbital maneuvers and attitude adjustments before separation of multiple devices. At this time, the ground adopts dual-station measurement and control, and the two stations are visible at the same time.

10. The method for joint design of a multi-device combined spacecraft measurement, control, and information system according to claim 1, characterized in that: In the multi-device combination state, if a detector has an abnormal situation, if the ground station can receive the downlink signal of the detector, it will select the corresponding uplink frequency according to the received downlink signal to send the emergency remote control command.

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