Multi-device combined spacecraft measurement and control and information system joint design method

Abstract

The invention discloses a joint design method suitable for a multi-device combined spacecraft measurement and control and information system. The joint design method comprises the following steps: (1) giving a maximum working mode set of a detector; (2) determining the layout of a measurement and control antenna according to the configuration of the detector, and giving the radiation coverage range and influence of a directional diagram in various modes through simulation analysis; (3) determining the working modes of measurement and control and information interaction in the combined body state, and meeting the full-space measurement and control requirements in each mode; (4) inter-device remote control and telemetering information interaction design; and (5) improving flight program setting according to ground measurement and control support conditions and task requirements. (6) traversing the working mode of the spacecraft, verifying whether the joint design of the measurement and control and information system meets the requirements of all stages of full-space measurement and control and information transmission, if so, executing the step (7), otherwise, returning to the step (2); and (7) completing joint design of measurement and control and information systems. According to the invention, the function multiplexing design under the multi-mode state is realized, and the full-space measurement and control communication requirements of the detector under various states are realized at the minimum system design cost.

Description

Technical Field

[0001] The present invention is aimed at multi-device combination spacecraft. Due to the complex configuration of the detector and the obstruction of the measurement and control antenna by the solar wings, landing legs, etc., the traditional single-device measurement and control cannot meet the full-space measurement and control requirements of the detector. A multi-device combination measurement and control and information system joint design method 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 the combination of four devices as an example, the individual devices are called A, B, C and D. According to the configuration layout of the detector, in the combined state, the X-band tracking and control antenna (installed on A and B) is blocked by the solar wing (installed on A and C). At the same time, during the entire flight process, the detector may have four-device combination, two-device combination, four-device single working mode and other modes.

[0004] Before the four devices are separated, in order to ensure the energy supply of the detector, the solar wings of device A and device C must be unfolded, and in order to avoid mutual shading of the solar wings of the two devices, the solar wings of the two devices are installed vertically and cross each other. Under this configuration layout condition, the installation direction of the measurement and control antenna of device A is parallel to the unfolding direction of the solar wing of device C, and is located directly below the unfolding of the solar wing of device C (-X direction). The installation direction of the measurement and control antenna of device B is parallel to the unfolding direction of the solar wing of device A, and is located directly above the unfolding of the solar wing of device A (+X direction). Therefore, in the state of the combination of the four devices, the measurement and control antenna of device A is affected by the shading of the solar wing of device C in the +X direction, and the measurement and control antenna of device B is affected by the shading of the solar wing of device A in the -X direction. Using device A or device B alone 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 prior art and to propose a design method that can realize the full-space measurement and control function in a multi-device (four devices or more) combination state. 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 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 on-orbit working mode of the detector;

[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 of measurement and control and information interaction in the assembly state 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. Based on the design of a single device, realize the remote control and telemetry information interaction between devices at the lowest cost.

[0012] (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;

[0013] (6) According to the probe flight program timing design, traverse the spacecraft working mode to 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) to re-determine 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 measurement and control antenna layout 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.

[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 heterodyne 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 sends only 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 capability of receiving M frequencies simultaneously in downlink, and selects the frequency of receiving one of the M detectors according to the current favorable posture to the ground.

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

[0023] Preferably, in the state of multiple devices being combined, if an abnormal situation occurs in a detector, 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) The present invention proposes a full-space measurement and control solution for detectors in a multi-device combination state. From an engineering perspective, the present 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, a BC two-device combination and an AD two-device combination measurement and control scheme are adopted to achieve full space measurement and control coverage in the four-device combination state, thereby solving the problem of solar wing 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 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 A schematic diagram of the relationship between the detector and the mechanical coordinate system of each device of the present invention;

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

[0031] Figure 4 This is the cross-sectional orientation diagram of a single device;

[0032] Figure 5 It is the total field section direction diagram of the two-device combination;

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

[0034] The present invention is aimed at multi-device combination spacecraft. Due to the complex configuration of the detector and the obstruction of the measurement and control antenna by the solar wing, landing legs, etc., the traditional single-device measurement and control cannot meet the full-space measurement and control requirements of the detector. A multi-device combination measurement and control and information system joint design method 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 devices 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 on-orbit working mode of the detector;

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

[0038] (3) Based on (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 lowest cost based on the design of a single device;

[0040] (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;

[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 requirements of full-space measurement, control and information transmission at 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 and control data transmission capabilities that each device of the measurement and control data transmission subsystem in this embodiment needs to have, 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) C device: There is no need for single device measurement and control. In order to save the weight of the whole device, the C device takes on the measurement and control function of the CD device combination. The C device only has a data transmission function. The telemetry and remote control data on the C device are forwarded through the B device;

[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 states, and to achieve the full-space measurement, control and communication requirements of the detector under various states with the minimum system design cost.

[0050] Combine the following 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 set of working modes 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 Detector maximum working mode set

[0054]

[0055] As can be seen from the table above, device A has both measurement and control requirements and data transmission requirements, so the AD two-device combination can use device A as the main body for measurement, control and data transmission. Device B only has measurement and control requirements, and device C only has data transmission requirements, so the BC two-device combination can use device B for measurement and control and device C for data transmission to achieve functional reuse. For the four-device combination, device A or device B can be used for measurement and control according to the situation, and device A can be used for data transmission. Only device D has a beacon requirement, so the beacon is configured on device D.

[0056] (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 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 the C device is installed parallel to the Z axis of the detector, and the solar wing of the A device is installed parallel to the Y axis of the detector, that is, the solar wing of the C device and the solar wing of the A device are installed vertically, such as Figure 3 The schematic 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 wing.

[0059] According to the above principles, since the A-device solar wing is installed on the ±Y side of the detector, the A-device +X direction needs to be docked with the C-device, and the -X direction is equipped with an engine and a tank, the measurement and control omnidirectional antenna is installed on the ±Z side of the detector. The ±Z antennas are responsible for half-space measurement and control tasks, and full-space measurement and control coverage is achieved through half-space heterogeneous array formation. The A-device directional antenna is installed on the -Z side of the detector. The B-device solar wing is installed on the ±Z side of the detector. The installation of the B-device measurement and control antenna needs to meet the full-space measurement and control requirements of a single device and a BC combination. Therefore, the measurement and control omnidirectional antenna is installed on the ±Y side of the detector. In order to ensure the measurement and control coverage of the BC combination in flight and avoid the C-device blocking the measurement and control antenna, the X-band measurement and control antenna needs to be elevated. The ±Y antennas are responsible for half-space measurement and control tasks, and full-space measurement and control coverage is achieved through half-space heterogeneous array formation.

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

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

[0062] The D device was designed as an independent single device for measurement and control, and the S-band antenna of the D device was arranged on the side wall of the D device near the II and IV quadrant lines. Since the inertial flight attitude of the D device before reentry and in the jump-out phase is both in the I quadrant to the ground, the layout of the measurement and control antenna avoids the area with the highest heat flux density, and after reviewing the orbit and the position of the ground station, the interference area outside the main beam of the antenna is not used for measurement and control.

[0063] (3) Based on (1) and (2), analyze the working mode of the combination that requires 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) being responsible for half-space measurement and control.

[0064] According to the coordinate relationship under the combined state of the four devices, it is determined that device A and device B are respectively responsible for the measurement and control tasks of half space, 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, and 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) Based on (3), complete the design of remote control and telemetry information interaction between devices. On the basis of single device design, realize remote control and telemetry information interaction between devices at the lowest cost.

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

[0067] In the four-device combination working mode, device A or device B is used for measurement and control remote uplink. Device B can be used to send commands to device B, device C, and device A, and can also send commands to the BC combination, device A, and device D; device A can be used to send commands to device A, and can also send commands to the BC combination, device A, and device D. In the four-device combination working mode, device A or device B is used for telemetry downlink, and device A's data transmission channel simultaneously transmits telemetry data, which can serve as a backup for the measurement and control channel. Both device B and device A can be used to transmit telemetry parameters of device A, device D, and the combination.

[0068] In the BC combination working mode, the B device is used for remote control uplink. The B device can be used to send commands to the B and C devices, and can also send commands to the BC combination uplink. In the upper combination working mode, the B device is used for telemetry downlink, and the C device data transmission channel can also transmit telemetry data downlink, which can be used as a backup for the measurement and control channel. The telemetry parameters of the upper combination can be transmitted downlink through the B device.

[0069] In the AD two-device combination working mode, the A device is used for remote control uplink. The A device can be used to send instructions to the A device, and can also send instructions to the A and D devices. In the AD two-device combination working mode, the A device is used for telemetry downlink, and the A device data transmission channel can also transmit telemetry data downlink, which can be used as a backup for the measurement and control channel. The telemetry parameters of the AD two-device combination can be transmitted downlink through the A device.

[0070] (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.

[0071] 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 four frequencies (two frequencies for A device and two frequencies for B device). The ground station has the ability to receive dual frequencies simultaneously, and can receive dual frequencies of A device or dual frequencies of B device simultaneously. It selects the frequency of A device or B device according to the current favorable posture to the ground.

[0072] When the four devices are in the combined state, the attitude of the detector changes greatly when performing orbital maneuvers and attitude adjustments before the separation of the four devices. At this time, the ground adopts dual-station measurement and control, and the two 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, which is used to send 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 the emergency remote control command (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 timing design of the probe flight program, traverse the spacecraft working mode and verify whether the joint design of the measurement, control and information system meets the requirements of full-space measurement, control and information transmission in 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 is directly sent into the Earth-Moon transfer orbit by the carrier rocket, and the probe measurement and control adopts a four-device combined measurement and control method. The measurement and control is realized by the X-band measurement and control equipment of the A device and the B device. The A device is the main measurement and control body.

[0077] During the Earth-Moon transfer to the circumlunar flight phase, the four devices are separated. According to the layout relationship between the solar wing and the X-band measurement and control antenna, the X-band measurement and control antenna of device A is blocked by the solar wing of device C in the +X direction, and the X-band measurement and control antenna of device B is blocked by the solar wing of device A in the -X direction. When the +X direction of the detector is favorable to the ground, measurement and control are completed through the combination of the BC devices. When the +Y direction of the detector is favorable to the ground, the X-band measurement and control signal operates at the f4 frequency point. When the -X direction of the detector is favorable to the ground, the measurement and control function is completed by device A. During the Earth-Moon transfer phase, when downlink data transmission is required, device C will fold the -Z side solar wing and transmit downlink data through the directional antenna of device A.

[0078] During the lunar circumnavigation phase, after the BC combination is separated from the AD combination, until the powered descent phase, the BC combination is measured and controlled by the ground station in cooperation with the B combination's measurement and control subsystem; the AD combination is measured and controlled by the ground station in cooperation with the A combination's measurement and control digital transmission subsystem.

[0079] During the powered descent phase, lunar surface operation phase and lunar surface ascent phase, the X-band measurement and control uplink and downlink of the BC two-device combination are completed by the B device, and the C device digital transmission channel completes the detection data transmission. The AD two-device combination realizes measurement and control through the ground station in cooperation with the A device measurement and control digital transmission subsystem.

[0080] During the rendezvous and approach phase to the lunar circling waiting phase, device B uses the ground station for measurement and control, 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, it transmits the downlink data through a directional antenna.

[0081] During the lunar-earth transfer phase, the AD combination uses station measurement and control. When downlink data transmission is required before and after the orbit-return separation point, downlink data transmission is carried out through the directional antenna. Before the orbit-return separation, the S-band transponder of the D device is turned on to perform S-band measurement and control.

[0082] During the reentry recovery phase, the D device only has the measurement and control function. After the D device opens the parachute, the recovery beacon starts working and the search helicopter tracks the recovery beacon signal. After the D device lands, the international rescue position indicator starts working.

[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, the measurement and control and information systems of the BC two-device combination and the AD two-device combination are jointly designed, and the two-device combination measurement and control mode is adopted to realize the full-space measurement and control function of the detector in the four-device combination state. Under this design mode, the ground measurement and control system has the measurement and control implementation means, and can realize the interaction of remote control and telemetry data of the BC two-device combination and the AD two-device combination, and realize the function of omnidirectional measurement and control in various modes at a relatively low cost.

[0086] Under the condition of complex structure layout of detector, the present invention realizes the full-space measurement and control function of detector multi-device combination state by jointly designing two combined measurement and control and information systems and adopting combined measurement and control mode. By adopting combined measurement and control mode, the ground measurement and control system has measurement and control implementation means, and can realize the interaction of remote control and telemetry data of two combined bodies, and the system cost is relatively low.

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

Claims

1. A joint design method for measurement, control and information systems of 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 on-orbit working mode of the detector; (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 of measurement and control and information interaction in the assembly state 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. Based on the design of a single device, realize the remote control and telemetry information interaction between devices at the lowest cost. (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; (6) According to the probe flight program timing design, traverse the spacecraft working mode to 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) to re-determine 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 measurement, control and information systems for multi-device combined spacecraft according to claim 1, characterized in that: In step (2), the measurement and control antenna layout 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 multi-device combined spacecraft measurement, control and information systems according to claim 1, characterized in that: The antenna of the same probe cannot be installed on the same side panel as the solar wing.

4. The method for joint design of multi-device combined spacecraft measurement, control and information systems 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 heterodyne array.

5. The method for joint design of measurement, control and information systems for multi-device combined spacecraft 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 multi-device combined spacecraft measurement, control and information systems according to claim 1, characterized in that: For probes that need to return, the layout of their measurement and control antennas should avoid areas with the highest heat flux density.

7. The method for joint design of measurement, control and information systems for multi-device combined spacecraft 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 and control and data transmission capabilities.

8. The method for joint design of measurement, control and information systems for multi-device combined spacecraft according to claim 7 is characterized by: The ground station has the ability to simultaneously receive M frequencies in downlink, and selects the frequency of receiving one of the M detectors based on the current favorable attitude toward the ground.

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

10. The method for joint design of measurement, control and information systems for multi-device combined spacecraft 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 point according to the received downlink signal to send the emergency remote control command.

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