A space station flexible solar wing deployment and retraction and sun-direction integrated drive control device

Abstract

A comprehensive drive control device for the deployment and retraction of large-scale flexible solar wings and solar orientation on a space station. Aiming at the deployment and retraction and solar orientation drive functions of the large-scale flexible solar wings on a space station, the device integrates the driving circuits of the lifting mechanism, the box deployment and retraction mechanism, the constraint release mechanism, the extension mechanism, and the solar orientation drive mechanism for realizing multi-step deployment of the large-scale flexible solar wings within the same comprehensive drive control device, thus realizing a highly integrated design of aerospace products. The device has flexible working modes such as fully automatic deployment of the large-scale flexible solar wings on a space station according to a program or independent deployment and retraction in a time-sharing single step. The device has a highly reliable multi-type command interface design, including 1553B bus communication and redundantly designed OC hard-wired commands. Under high-priority OC hard-wired command execution conditions, the drive control tasks can be isolated and completed in the minimized functional circuit inside a single machine, thus ensuring the high reliability requirements of the drive control device.

Description

Technical Field

[0001] The present invention relates to the field of space technology, and in particular to a comprehensive drive control device for the deployment and retraction of large-scale flexible solar wings and sun-directed drive in space stations. Background Art

[0002] To meet the space station's energy needs, the station's large flexible solar panels utilize a deployable design. Once the station's cabin is in orbit, an articulated extension mechanism supports the deployment of the bilateral flexible arrays. The flexible solar panel primarily consists of a lifting mechanism, a housing deployment locking mechanism, a restraint release mechanism, battery circuitry, cables, and an extension mechanism. Once deployed, to ensure high power generation efficiency, the large flexible solar panels must be driven by a large drive mechanism to capture the solar incident angle and continuously track the sun. To achieve these complex motion mechanisms, a variety of motor driver products are required to cover the motion control requirements of the solar panels and drive mechanisms. Furthermore, due to the strict timing requirements for the multi-step deployment and solar tracking of the solar panels, a unified central processing unit is required to ensure the multi-step, timed deployment and solar tracking of the solar panels. Summary of the Invention

[0003] The problem that the present invention aims to solve is to realize the time-sequential integrated drive control of multi-type, multi-voltage and multi-dimensional motors in large flexible solar wings and solar directional drive mechanisms of space stations, and to design a comprehensive drive control device with highly reliable drive capabilities.

[0004] The technical solution adopted in the present invention is:

[0005] A space station flexible solar wing deployment and retraction and sun-orientation integrated drive control device, comprising: a power supply module, a CPU control module, a stepper and brushed motor drive module, a brushed and brushless motor drive module, and a brushless motor drive module;

[0006] The power module is used to receive the external primary bus power supply and the relay switching OC instruction, and convert the primary bus power supply into a secondary power supply and a motor drive power supply; the relay switching OC instruction is used to switch the working state of the main and standby power supply circuits in the power module;

[0007] The CPU control module is used to receive the 1553B control instructions transmitted by the host computer, generate motion control instructions based on the received 1553B control instructions, and transmit the motion control instructions to the stepper and brushed motor driver module, the brushed and brushless motor driver module, and the brushless motor driver module to complete the timing control of the fully automatic process; receive and feed back the telemetry parameters fed back by the stepper and brushed motor driver module, the brushed and brushless motor driver module, and the brushless motor driver module to the host computer;

[0008] The stepper and brushed motor driver module is used to receive motion control instructions sent by the CPU control module and OC hard-line instructions input by the external host computer; according to the motion control instructions or OC hard-line instructions, it generates the driving current for controlling the brushed motor of the lifting mechanism or generates the driving current for controlling the stepper motor of the driving mechanism;

[0009] The brushed and brushless motor drive modules are used to receive motion control instructions sent by the CPU control module and OC hard-wired instructions input by the external host computer; according to the motion control instructions or OC hard-wired instructions, they generate the driving current of the brushed motor of the box mechanism and the driving current of the brushless DC motor of the extension mechanism.

[0010] The brushless motor drive module is used to receive motion control instructions sent by the CPU control module and OC hard-line instructions input by the external host computer; according to the motion control instructions or OC hard-line instructions, it generates the driving current of the brushless DC motor of the constraint release mechanism.

[0011] When the stepper and brushed motor drive module, the brushed and brushless motor drive module, and the brushless motor drive module execute the motion control instructions sent by the CPU control module, the stepper and brushed motor drive module, the brushed and brushless motor drive module, and the brushless motor drive module independently feed back the action execution status and the motion process parameters of the corresponding mechanism as telemetry parameters to the CPU control module.

[0012] Preferably, the secondary power supply is used to power the stepper and brushed motor drive module, the brushed and brushless motor drive module, and the chip in the brushless motor drive module, and the secondary power supply is also used to power the CPU control module;

[0013] The secondary power supply includes: ±5V secondary power supply and ±12V secondary power supply.

[0014] Preferably, the motor drive power supply includes: +28V drive power supply and +100V DC power;

[0015] The +28V drive power supply is used to power the stepper and brushed motor drive modules, the brushed and brushless motor drive modules, and the brushless motor drive modules; the +100V DC power is used to drive the extension mechanism movement.

[0016] Preferably, when any one of the stepper and brushed motor drive module, the brushed and brushless motor drive module, and the brushless motor drive module simultaneously receives an OC hard-wired instruction sent externally and a motion control instruction sent by the CPU control module, the OC hard-wired instruction is executed first.

[0017] Preferably, the fully automatic process includes the following steps: unfolding the lifting mechanism, unfolding the box mechanism, unfolding the restraint release mechanism, extending and retracting the stretching mechanism, and orienting the driving mechanism towards the sun, which are completed in sequence.

[0018] Preferably, the sun orientation operation of the driving mechanism is specifically as follows: using a stepping motor of the driving mechanism to drive the fully extended solar wing to perform sun orientation;

[0019] The lifting mechanism unfolds specifically as follows: using the brushed motor of the lifting mechanism to drive the solar wing storage box to rotate relative to the aircraft cabin, so that after the solar wing in the solar wing storage box is fully unfolded, the surface of the solar wing is perpendicular to the cabin.

[0020] Preferably, the box mechanism works specifically as follows: using the brush motors of the box mechanisms on both sides to drive the left solar wing storage box and the right solar wing storage box to move relative to each other and unfold outwards;

[0021] The restraint release mechanism operates as follows: using the brushless DC motors of the restraint release mechanisms on both sides to open the lid of the solar wing storage box;

[0022] The specific extension and retraction work of the extension mechanism is: using the brushless DC motor of the extension mechanism to extend the multiple flexible solar cell sheets in the solar wing storage box one by one and fully unfold them to form a solar wing.

[0023] Preferably, when the CPU control module fails to work, the stepper and brushed motor drive module, the brushed and brushless motor drive module, and the brushless motor drive module independently receive OC hard-wired instructions input by an external host computer, thereby completing the timing control of the fully automatic process.

[0024] Preferably, the CPU control module interacts with the stepper and brushed motor drive module, the brushed and brushless motor drive module, and the brushless motor drive module via a data bus, and an isolation circuit is designed for safety protection.

[0025] Compared with the prior art, the present invention has the following beneficial effects:

[0026] The present invention realizes the function of fully automatic unfolding and folding of large flexible solar panels on a space station in strict time sequence, and integrates the circuit of the sun-directed drive mechanism into the same integrated drive control device, which is beneficial to the high integration and weight reduction design of aerospace products. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 This is the architecture diagram of the integrated drive control device for the expansion and retraction of large-scale flexible solar wings and solar orientation in the space station;

[0028] Figure 2This is a flowchart of the working sequence of the large-scale flexible solar wing deployment and retraction and sun-orientation integrated drive control device of the space station;

[0029] Figure 3 This is a schematic diagram of the multi-redundant command interface of the space station's large-scale flexible solar wing deployment and retraction and sun-orientation integrated drive control device;

[0030] Figure 4 This is a schematic diagram of the minimized working unit of the space station's large-scale flexible solar wing deployment and retraction and sun-orientation integrated drive control device;

[0031] Figure 5 This is a schematic diagram of the internal secondary power supply and power-off safety design of the space station's large-scale flexible solar wing deployment and retraction and sun-direction integrated drive control device. DETAILED DESCRIPTION

[0032] The present invention is aimed at the large-scale flexible solar wing deployment and retraction and solar orientation drive functions of the space station, and integrates two major types of drive circuits into the same integrated drive control device, thereby achieving high integration and weight reduction design of aerospace products. The present invention provides a large-scale flexible solar wing deployment and retraction and solar orientation integrated drive control device for a space station, comprising: a power supply module, a CPU control module, a solar wing deployment and retraction related drive module, and a solar orientation related drive module. The stepper and brushed motor drive module includes a 28V DC brushed drive circuit for the lifting mechanism required for the solar wing deployment and retraction, and a stepper motor drive circuit for the stepping drive mechanism required for the solar orientation drive; the brushed and brushless motor drive module includes a 28V DC brushed drive circuit for the box mechanism required for the solar wing deployment and retraction, and a 100V DC brushless drive circuit for the extension mechanism; the brushless motor drive module includes a 28V brushless DC motor drive circuit for the constraint release mechanism required for the solar wing deployment and retraction.

[0033] like Figure 1 As shown, the present invention provides a large-scale flexible solar wing deployment and retraction and sun-orientation integrated drive control device for a space station, including: a power supply module, a CPU control module, a stepper and brushed motor drive module, a brushed and brushless motor drive module, and a brushless motor drive module.

[0034] The power module is used to receive an external 100V primary bus power supply and relay switching OC instructions. After passing through the internal fuse protection circuit, power-on and power-off control circuit, soft-start circuit, and secondary power conversion circuit, it converts the primary bus power supply into secondary power supply and motor drive power supply. The relay switching OC instruction is used to switch the working status of the main and standby power supply circuits in the power module.

[0035] The secondary power supply includes: 5V secondary power supply and 12V secondary power supply; the secondary power supply is used to power the stepper and brushed motor drive modules, brushed and brushless motor drive modules, and the chips in the brushless motor drive module. The secondary power supply is also used to power the CPU control module.

[0036] The motor drive power supply includes: 28V drive power supply and 100V DC power; the 28V drive power supply is used to power the stepper and brushed motor drive modules, the brushed and brushless motor drive modules, and the brushless motor drive modules; the 100V DC power is used to drive the extension mechanism to move.

[0037] The CPU control module sends motion control instructions to the stepper and brushed motor drive module, the brushed and brushless motor drive module, and the interface isolation circuit in the brushless motor drive module through the data bus.

[0038] The stepper and brushed motor drive module, the brushed and brushless motor drive module, and the brushless motor drive module receive motion control instructions sent by the CPU control module and receive OC hard-line instructions sent externally;

[0039] When an externally sent OC hard-wire instruction and a motion control instruction transmitted through the data bus are received at the same time, the OC hard-wire instruction is executed first; when the stepper and brushed motor drive module, the brushed and brushless motor drive module, and the brushless motor drive module execute the motion control instruction transmitted through the data bus, the stepper and brushed motor drive module, the brushed and brushless motor drive module, and the brushless motor drive module independently feed back the action execution status and the motion process parameters of the corresponding mechanism as telemetry parameters to the CPU control module;

[0040] The CPU control module includes: a CPU processor circuit, a program memory circuit, an interface isolation circuit and a 1553B interface circuit.

[0041] The CPU control module receives 1553B control commands from the host computer and feeds back telemetry parameters. Based on these 1553B commands, the CPU processor circuit in the CPU control module generates motion control commands, completing the timing control of the fully automated process. This fully automated process sequentially involves the deployment of the lifting mechanism, the expansion of the box mechanism, the deployment of the restraint release mechanism, the extension and retraction of the extension mechanism, and the solar orientation of the drive mechanism.

[0042] The 1553B control instructions are used to control the stepper and brushed motor driver modules, the brushed and brushless motor driver modules, and the brushless motor driver module to drive the corresponding mechanism movement.

[0043] The lifting mechanism deploys by using its brushed motor to rotate the solar wing storage box relative to the aircraft cabin, so that when the solar wings are fully deployed, their surfaces are perpendicular to the cabin. During deployment, the lifting mechanism of this embodiment of the present invention rotates the solar wing storage box 90° relative to the aircraft cabin, aligning their axes perpendicularly.

[0044] The box mechanism works specifically as follows: the brushed motor of the box mechanism is used to drive the left solar wing storage box and the right solar wing storage box to move relative to each other and expand outward.

[0045] The specific operation of the restraint release mechanism is to use the brushless DC motor of the restraint release mechanism to open the lid of the solar wing storage box.

[0046] The specific extension and retraction work of the extension mechanism is: using the brushless DC motor of the extension mechanism, the multiple flexible solar cells in the solar wing storage box are extended one by one and fully unfolded to form a solar wing.

[0047] The solar orientation work of the driving mechanism is specifically as follows: using the stepper motor of the driving mechanism to drive the fully unfolded solar wings to orient themselves towards the sun.

[0048] The stepper and brushed DC motor driver module consists of an anti-fuse FPGA control circuit and a power amplifier drive circuit. The anti-fuse FPGA control circuit generates the PWM waveform required for motor drive according to the instructions. This waveform is amplified by the power driver to generate the motor drive current. The anti-fuse FPGA control circuit has built-in stepper and brushed DC motor drive code.

[0049] The stepper and brushed motor drive module is used to receive the motion control instructions output by the CPU control module through the data bus and the OC hard-wired instructions input by the external host computer; according to the motion control instructions or OC hard-wired instructions, it generates the driving current for controlling the brushed motor of the lifting mechanism and generates the driving current required for controlling the stepper motor of the driving mechanism.

[0050] The brushed and brushless motor driver modules consist of an anti-fuse FPGA control circuit and a power amplifier drive circuit. Based on the instructions, the anti-fuse FPGA control circuit generates the PWM waveform required for motor drive. This waveform is amplified by the power driver to generate the motor drive current. The anti-fuse FPGA control circuit contains the brushed DC motor and brushless DC motor drive code.

[0051] The brushed and brushless motor drive modules are used to receive motion control instructions output by the CPU control module through the data bus and OC hard-wired instructions input by the external host computer; according to the motion control instructions or OC hard-wired instructions, they generate the driving current of the brushed motor of the box mechanism and the driving current of the brushless DC motor of the extension mechanism.

[0052] The brushless motor drive module consists of an antifuse FPGA control circuit and a power amplifier drive circuit. Based on the instructions, the antifuse FPGA control circuit generates the PWM waveform required for motor drive. This waveform is amplified by the power driver to generate the motor drive current. The antifuse FPGA control circuit contains the brushless DC motor drive code.

[0053] The brushless motor drive module is used to receive motion control instructions output by the CPU control module through the data bus and OC hard-line instructions input by the external host computer; according to the motion control instructions or OC hard-line instructions, it generates the driving current of the brushless DC motor of the constraint release mechanism.

[0054] The working process of the integrated drive control device for deploying and retracting large-scale flexible solar wings and directing solar energy to a space station according to the present invention includes the following steps:

[0055] The power module receives an external 100V DC power supply, and after passing through the internal fuse protection circuit, soft-start circuit, EMI filter circuit, and DC-DC conversion circuit, it generates the 5V and 12V secondary power supplies required by the CPU control module, stepper and brushed motor drive module, brushed and brushless motor drive module, and brushless motor drive module, as well as the 28V and 100V controlled power supplies that can be independently switched on and off.

[0056] After the CPU control module is powered on, the internal program is automatically loaded and run, and initialized. After the initialization is completed, it waits for external 1553B communication instructions or OC hard line instructions.

[0057] Under normal working conditions, the host computer sends the solar wing deployment instruction to the drive controller device through 1553B communication or OC hard line. After the CPU control module receives the solar wing automatic deployment instruction, it enters the following control process:

[0058] The first step is to collect sensor signals (position switches, travel switches) of all controlled mechanisms for fault diagnosis. If an incorrect position signal is detected by a mechanism sensor, control is interrupted and the fault status is uploaded via telemetry. If the sensor signals of all mechanisms are correct, the next step is entered.

[0059] The second step starts with outputting the lifting mechanism motor drive control signal according to the large solar wing deployment timing preset by the internal software. During the process, the lifting mechanism's in-position switch and limit switch are detected in real time. After determining that the lifting mechanism has been deployed in place, the lifting mechanism motor drive control signal is turned off; the delay timer required to wait for the mechanism to stabilize is started, and the sensor signals (in-position switch, limit switch) of the remaining controlled mechanisms are monitored for fault diagnosis. If an erroneous in-position signal is detected by a sensor of a certain mechanism, the control is interrupted and the fault status is uploaded via telemetry. If the sensor signals of all mechanisms are correct, the next step of the process is entered;

[0060] The third step begins by outputting the motor drive control signal for the box mechanism according to the large solar wing deployment sequence preset by the internal software. During this process, the box mechanism's in-place switch and limit switch are detected in real time. Once the box is fully deployed, the motor drive control signal for the box mechanism is turned off. The delay timer required to wait for the mechanism to stabilize is started, and the sensor signals (in-place switch, limit switch) of the remaining controlled mechanisms are monitored for fault diagnosis. If an incorrect in-place signal is detected by a sensor of a mechanism, control is interrupted and the fault status is uploaded via telemetry. If the sensor signals of all mechanisms are correct, the process proceeds to the next step.

[0061] The fourth step begins by outputting the restraint release mechanism motor drive control signal according to the large solar wing deployment sequence preset by the internal software. During this process, the restraint release mechanism's in-position switch and limit switch are detected in real time. After determining that the restraint release mechanism has been deployed to its full position, the restraint release mechanism motor drive control signal is turned off. The delay timer required to wait for the mechanism to stabilize is started, and the sensor signals (in-position switch, limit switch) of the remaining controlled mechanisms are monitored for fault diagnosis. If an erroneous in-position signal is detected by a sensor of a mechanism, control is interrupted and the fault status is uploaded via telemetry. If the sensor signals of all mechanisms are correct, the process proceeds to the next step.

[0062] The fifth step starts with outputting the extension mechanism motor drive control signal according to the large solar wing deployment timing preset by the internal software. During the process, the extension mechanism position switch and travel switch are detected in real time. After determining that the extension mechanism is deployed in place, the extension mechanism motor drive control signal is turned off, and the solar wing automatic deployment success mark is uploaded through telemetry.

[0063] After the solar wing is successfully deployed, the host computer can send the sun-directed capture and tracking instructions to the CPU control module through 1553B communication. The CPU control module generates the drive mechanism stepper motor control signal according to the instruction, transmits it to the stepping and optimization drive module through the interface isolation circuit, and drives the solar wing drive mechanism to perform the sun-directed action after power amplification.

[0064] Under fault conditions, when the CPU control module cannot work, the stepper and brushed motor drive module, brushed and brushless motor drive module, and brushless motor drive module can independently receive external single-step expansion or retraction OC hard-wired instructions, generate open-loop control signals for various motors through the on-board anti-fuse FPGA control circuit, and output them to the controlled mechanism motor after power amplification, realizing single-step open-loop action of the controlled mechanism.

[0065] To meet the high reliability requirements of a single unit on the space station and prevent damage to the solar array mechanism due to malfunction after power-up, the system incorporates independent solar array deployment circuits and secondary power-on / off circuits for the solar wing orientation drive circuit power busbar to provide redundant protection. Once the spacecraft enters orbit, the "Solar wing drive circuit power on" command (OC) is issued to transmit the +28V and +100V motor-controlled drive power supplies within the power module to the lift motor drive circuits of the stepper and brushless motor drive modules, the housing and extension motor drive circuits of the brushless and brushless motor drive modules, and the constraint release motor drive circuit of the brushless motor drive module. After the solar wing successfully deploys, the "Solar wing drive circuit power off" command is issued to disconnect the solar wing deployment drive circuit power busbar. Then, the "Solar wing orientation drive circuit power on" command is issued to transmit the +28V motor-controlled drive power supplies within the power module to the drive mechanism motor drive circuits of the stepper and brushless motor drive modules (controlling the drive mechanism and lift mechanism). Upon receiving this command, the control unit enters solar wing orientation mode.

[0066] The CPU control module interacts with the stepper and brushed motor drive modules, brushed and brushless motor drive modules, and brushless motor drive modules to control parameters and telemetry data via the data bus (address bus, data bus), and an isolation circuit is designed for safety protection.

[0067] Example

[0068] The power module receives a 100V primary power bus and converts it into the +5V, ±12V, and +28V secondary power supplies required by the single-unit internal circuitry. It also includes a soft-start circuit, a fuse-holding circuit, and a secondary power-up / down circuit for the motor power bus power supply. The motor drive module is divided into three types: a stepper and brushed motor drive module, a brushed and brushless drive module, and a brushless motor drive module. Table 1 summarizes the motor types controlled by the integrated drive controller. In a single-unit design, the stepper and brushed motor drive module drives the +28V brushed DC motors of the solar panel lift mechanism and the +28V stepper motors of the solar panel orientation mechanism. The brushed and brushless drive module drives the +100V brushless DC motors of the solar panel extension mechanism and the +28V brushed DC motors of the solar panel housing mechanism. The brushless motor drive module drives the +28V brushless DC motors of the solar panel restraint release mechanism and the solar panel housing mechanism.

[0069] Table 1 List of motor types of the controlled mechanism of the integrated drive control device for the expansion and retraction of large flexible solar wings and solar orientation in space stations

[0070]

[0071] Figure 1This is the hardware architecture diagram of the integrated drive controller of the present invention. The whole machine consists of a power supply module, a CPU control module, a stepper and brushed motor drive module, a brushed and brushless drive module, a brushless motor drive module, etc., to realize the multi-step sequential deployment of the large-scale flexible solar wing of the space station and the subsequent sun-directed drive function (the action sequence is as follows Figure 2 The CPU control module and other driver modules transmit control parameters and telemetry data via a custom data bus. The data buses of each module are interconnected via a bus isolation chip to achieve a fault isolation safety design. Figure 3 It is the command interface of the integrated drive controller, including: 1553B communication interface, fully automatic timed deployment OC command interface, and each mechanism single-step action OC command interface (lifting mechanism deployment / retraction OC command, box mechanism deployment / retraction OC command, restraint release mechanism deployment / retraction OC hard-wired command, extension mechanism deployment / retraction OC hard-wired command, sun-directed capture / tracking OC command, etc.). Under normal working conditions, the integrated drive controller receives control commands through the 1553B communication interface and uploads telemetry data; under fault conditions, when the 1553B communication function is lost, the integrated drive controller can receive the fully automatic timed deployment OC command received on the CPU control module, and perform fully automatic deployment according to the planned timed deployment steps of the solar wing; when a larger fault occurs, the integrated drive controller can also directly receive single-step action OC commands on each drive module (at this time, the single machine is working at Figure 4 The minimized working unit state shown in the figure) realizes the open-loop motion of each independent mechanism, and ensures that each mechanism is deployed in place under the premise of reducing some servo performance to meet the high reliability design requirements of the space station. Figure 5 This is a schematic diagram of the safety design for the secondary power supply on / off within the integrated drive control device. To enhance the power supply safety of individual space station units, independent secondary on / off circuits for the solar wing deployment and solar-orientation drive line power busbars are designed within the device to provide redundant protection. Once the spacecraft enters orbit, the "Solar Wing Drive Line Power On" OC command is first used to power on the solar wing deployment-related drive line power busbars. After the solar wing is successfully deployed, the "Solar Wing Drive Line Power Off" command is used to disconnect the solar wing deployment-related drive line power busbars. This further reduces the risk of short-circuit failures within the unit and the risk of single-particle burnout of a large number of power MOSFET chips within the unit due to the space radiation environment. Prior to the solar wing's solar-orientation tracking, the "Solar-orientation Drive Line Power On" OC command is used to power on the solar-orientation drive mechanism motor power busbars, and the unit enters its solar-orientation operating mode.

[0072] Although the present invention has been disclosed as above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention are within the scope of protection of the technical solutions of the present invention. In the absence of conflict, the embodiments of the present application and the technical features in the embodiments can be combined with each other.

[0073] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. A space station flexible solar wing deployment and retraction and sun-orientation integrated drive control device, characterized in that: include: Power supply module, CPU control module, stepper and brushed motor driver module, brushed and brushless motor driver module, and brushless motor driver module; The power module is used to receive the external primary bus power supply and the relay switching OC instruction, and convert the primary bus power supply into a secondary power supply and a motor drive power supply; the relay switching OC instruction is used to switch the working state of the main and standby power supply circuits in the power module; The CPU control module is used to receive the 1553B control instructions transmitted by the host computer, generate motion control instructions based on the received 1553B control instructions, and transmit the motion control instructions to the stepper and brushed motor driver module, the brushed and brushless motor driver module, and the brushless motor driver module to complete the timing control of the fully automatic process; receive and feed back the telemetry parameters fed back by the stepper and brushed motor driver module, the brushed and brushless motor driver module, and the brushless motor driver module to the host computer; The stepper and brushed motor driver module is used to receive motion control instructions sent by the CPU control module and OC hard-line instructions input by the external host computer; according to the motion control instructions or OC hard-line instructions, it generates the driving current for controlling the brushed motor of the lifting mechanism or generates the driving current for controlling the stepper motor of the driving mechanism; The brushed and brushless motor drive modules are used to receive motion control instructions from the CPU control module and OC hard-wired instructions from the external host computer; based on the motion control instructions or OC hard-wired instructions, they generate the drive current for the brushed motor of the box mechanism and the drive current for the brushless DC motor of the extension mechanism; The brushless motor drive module is used to receive motion control instructions sent by the CPU control module and OC hard-wired instructions input by the external host computer; according to the motion control instructions or OC hard-wired instructions, it generates the driving current of the brushless DC motor of the constraint release mechanism; When the stepper and brushed motor drive module, the brushed and brushless motor drive module, and the brushless motor drive module execute the motion control instructions sent by the CPU control module, the stepper and brushed motor drive module, the brushed and brushless motor drive module, and the brushless motor drive module independently feed back the action execution status and the motion process parameters of the corresponding mechanism as telemetry parameters to the CPU control module; The fully automatic process includes the following steps: unfolding the lifting mechanism, unfolding the box mechanism, unfolding the restraint release mechanism, unfolding and retracting the extension mechanism, and directing the driving mechanism to the sun. The sun orientation work of the driving mechanism is specifically as follows: using the stepping motor of the driving mechanism to drive the fully extended solar wing to perform sun orientation; The lifting mechanism operates as follows: a brushed motor of the lifting mechanism is used to drive the solar wing storage box to rotate relative to the aircraft cabin, so that when the solar wing in the solar wing storage box is fully deployed, the surface of the solar wing is perpendicular to the cabin; The box mechanism works specifically as follows: using the brush motors of the box mechanism on both sides to drive the left solar wing storage box and the right solar wing storage box to move relative to each other and unfold outward; The restraint release mechanism operates as follows: using the brushless DC motors of the restraint release mechanisms on both sides to open the lid of the solar wing storage box; The specific extension and retraction work of the extension mechanism is: using the brushless DC motor of the extension mechanism to extend the multiple flexible solar cell sheets in the solar wing storage box one by one and fully unfold them to form a solar wing.

2. A space station flexible solar wing deployment and sun-orientation integrated drive control device according to claim 1, characterized in that: The secondary power supply is used to power the stepper and brushed motor drive modules, the brushed and brushless motor drive modules, and the chips in the brushless motor drive module. The secondary power supply is also used to power the CPU control module. The secondary power supply includes: ±5V secondary power supply and ±12V secondary power supply.

3. The space station flexible solar wing deployment and sun-orientation integrated drive control device according to claim 1, characterized in that: The motor drive power supply includes: +28V drive power supply and +100V DC power; The +28V drive power supply is used to power the stepper and brushed motor drive modules, the brushed and brushless motor drive modules, and the brushless motor drive modules; the +100V DC power is used to drive the extension mechanism movement.

4. The space station flexible solar wing deployment and sun-orientation integrated drive control device according to claim 1, characterized in that: When any one of the stepper and brushed motor drive module, the brushed and brushless motor drive module, and the brushless motor drive module simultaneously receives an OC hard-wired instruction sent externally and a motion control instruction sent by the CPU control module, the OC hard-wired instruction is preferentially executed.

5. A space station flexible solar wing deployment and sun-orientation integrated drive control device according to any one of claims 1 to 4, characterized in that: When the CPU control module fails to work, the stepper and brushed motor drive module, the brushed and brushless motor drive module, and the brushless motor drive module independently receive OC hard-wired instructions input by the external host computer, thereby completing the timing control of the fully automatic process.

6. A space station flexible solar wing deployment and sun-orientation integrated drive control device according to any one of claims 1 to 4, characterized in that: The CPU control module interacts with the stepper and brushed motor drive module, the brushed and brushless motor drive module, and the brushless motor drive module through a data bus, and an isolation circuit is designed for safety protection.

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