Satellite-borne high-integration synthetic aperture radar antenna deployment system

Abstract

The application discloses a kind of satellite-borne high integration synthetic aperture radar antenna deployment systems, power management module is respectively connected with +X side drive module and-X side drive module, for +X side drive module and-X side drive module power supply;+X side and-X drive module and respective corresponding +X side and-X side synthetic aperture radar antenna deployment mechanism are electrically connected, for driving step motor in synthetic aperture radar antenna deployment mechanism, to realize the on-orbit deployment of synthetic aperture radar antenna deployment mechanism further.This application completes the drive of inner plate motor main and standby winding and outer plate motor main and standby winding of synthetic aperture radar antenna deployment mechanism with FPGA as control core, to realize the on-orbit deployment of antenna deployment mechanism further.4 pieces of synthetic aperture radar antenna can be controlled simultaneously on-orbit deployment, with overtime automatic stop function, effectively protect synthetic aperture radar antenna deployment mechanism.

Description

Technical Field

[0001] This invention relates to the field of space technology, and in particular to a spaceborne highly integrated synthetic aperture radar antenna deployment system. Background Technology

[0002] As a crucial satellite payload, the synthetic aperture radar (SAR) antenna is in a retracted state during satellite launch. After the satellite enters orbit, the SAR antenna deployment mechanism is controlled by a SAR antenna deployment controller to deploy and lock the antenna array. Currently, domestic SAR antenna deployment controllers mainly control single-axis or dual-axis deployment mechanisms, with each side using only a single stepper motor as the drive source. The control strategy generally adopts a CPU+PROM control scheme. Such SAR antenna deployment controllers cannot meet the requirements of satellites with large antenna arrays and are limited by the storage capacity of the PROM, failing to meet the frequency conversion control requirements of high-speed stepper motors. Summary of the Invention

[0003] The technical objective of this invention is to provide a spaceborne highly integrated synthetic aperture radar antenna deployment system to solve the problems in the background technology.

[0004] To solve the above problems, the technical solution of the present invention is as follows:

[0005] A spaceborne highly integrated synthetic aperture radar antenna deployment system includes:

[0006] Power supply management module, +X side drive module, -X side drive module, +X side synthetic aperture radar antenna deployment mechanism and -X side synthetic aperture radar antenna deployment mechanism;

[0007] The power supply management module is electrically connected to the +X side drive module and the -X side drive module respectively, and is used to supply power to the +X side drive module and the -X side drive module;

[0008] The +X side drive module is also electrically connected to the +X side synthetic aperture radar antenna deployment mechanism, and is used to drive the stepper motor in the +X side synthetic aperture radar antenna deployment mechanism, thereby realizing the on-orbit deployment of the +X side synthetic aperture radar antenna deployment mechanism.

[0009] The -X side drive module is also electrically connected to the -X side synthetic aperture radar antenna deployment mechanism, and is used to drive the stepper motor in the -X side synthetic aperture radar antenna deployment mechanism, thereby realizing the on-orbit deployment of the -X side synthetic aperture radar antenna deployment mechanism.

[0010] Specifically, the stepper motor in the +X side synthetic aperture radar antenna deployment mechanism includes a +X side inner plate motor and a +X side outer plate motor;

[0011] The +X side inner plate motor is used to deploy the +X side inner plate antenna in the +X side synthetic aperture radar antenna deployment mechanism in orbit.

[0012] The +X side outer plate motor is used to deploy the +X side outer plate antenna in the +X side synthetic aperture radar antenna deployment mechanism in orbit.

[0013] The stepper motor in the -X side synthetic aperture radar antenna deployment mechanism includes the -X side inner plate motor and the -X side outer plate motor;

[0014] The -X side inner plate motor is used to deploy the -X side inner plate antenna in the -X side synthetic aperture radar antenna deployment mechanism in orbit.

[0015] The -X side outer plate motor is used to deploy the -X side outer plate antenna in the -X side synthetic aperture radar antenna deployment mechanism in orbit.

[0016] Specifically, the operating frequency of the +X side inner plate motor and the -X side inner plate motor is 1533.33Hz, and the corresponding deployment speed of the +X side inner plate antenna and the -X side inner plate antenna is 0.3° / s, with a rotation angle range from 0° to 90°.

[0017] Specifically, the operating frequency of the +X side outer panel motor and the -X side outer panel motor is 3666.67Hz, and the corresponding deployment speed of the +X side outer panel antenna and the -X side outer panel antenna is 0.7174° / s, with a rotation angle range from 0° to 180°.

[0018] Specifically, the power supply management module, the +X side drive module, the -X side drive module, the +X side synthetic aperture radar antenna deployment mechanism, and the -X side synthetic aperture radar antenna deployment mechanism all adopt a primary-backup redundancy design.

[0019] Specifically, both the +X-side drive module and the -X-side drive module are equipped with an inner plate unfolding angle indication and acquisition circuit and an outer plate unfolding angle indication and acquisition circuit; both the +X-side synthetic aperture radar antenna unfolding mechanism and the -X-side synthetic aperture radar antenna unfolding mechanism are equipped with an inner plate angle displacement sensor and an outer plate angle displacement sensor.

[0020] The inner plate unfolding angle indication and acquisition circuit in the +X side drive module is electrically connected to the inner plate angle displacement sensor in the +X side synthetic aperture radar antenna unfolding mechanism, and is used to measure the unfolding angle of the +X side inner plate antenna.

[0021] The inner plate deployment angle indication and acquisition circuit in the -X side drive module is electrically connected to the inner plate angle displacement sensor in the -X side synthetic aperture radar antenna deployment mechanism, and is used to measure the deployment angle of the -X side inner plate antenna.

[0022] The outer plate deployment angle indication and acquisition circuit in the +X side drive module is electrically connected to the outer plate angle displacement sensor in the +X side synthetic aperture radar antenna deployment mechanism, and is used to measure the deployment angle of the +X side outer plate antenna.

[0023] The outer plate deployment angle indication and acquisition circuit in the -X side drive module is electrically connected to the outer plate angle displacement sensor in the -X side synthetic aperture radar antenna deployment mechanism, and is used to measure the deployment angle of the -X side outer plate antenna.

[0024] Specifically, the inner panel unfolding angle indicator acquisition circuit is configured the same as the outer panel unfolding angle indicator acquisition circuit;

[0025] It includes a first resistor, a second resistor, a third resistor, a fourth resistor, a first capacitor, a second capacitor, an operational amplifier, a first diode, and a second diode;

[0026] The positive terminal of the first diode is electrically connected to an external power supply, the negative terminal of the first diode is electrically connected to one end of the second resistor, and the other end of the second resistor is electrically connected to the outer plate angle displacement sensor or the inner plate angle displacement sensor.

[0027] One end of the first resistor is electrically connected to the outer plate angle displacement sensor or the inner plate angle displacement sensor, and the other end of the first resistor is electrically connected to the non-inverting input terminal of the operational amplifier and one end of the first capacitor, respectively; the other end of the first capacitor is electrically connected to the second capacitor, and the other end of the second capacitor is grounded; the output terminal of the operational amplifier is electrically connected to the inverting input terminal of the operational amplifier and one end of the third resistor, and the other end of the third resistor is the output terminal, and is electrically connected to one end of the fourth resistor and the negative terminal of the second diode, respectively;

[0028] The other end of the fourth resistor is grounded, and the other end of the second diode is grounded.

[0029] Specifically, both the +X-side drive module and the -X-side drive module are equipped with an inner plate deployment position indication acquisition circuit and an outer plate deployment position indication acquisition circuit; both the +X-side synthetic aperture radar antenna deployment mechanism and the -X-side synthetic aperture radar antenna deployment mechanism are equipped with an inner plate micro switch and an outer plate micro switch.

[0030] The inner plate deployment indication acquisition circuit in the +X side drive module is electrically connected to the inner plate micro switch of the +X side synthetic aperture radar antenna deployment mechanism, and is used to determine whether the +X side inner plate antenna has been deployed.

[0031] The inner plate deployment indication acquisition circuit in the -X side drive module is electrically connected to the inner plate micro switch of the -X side synthetic aperture radar antenna deployment mechanism, and is used to determine whether the -X side inner plate antenna has been deployed.

[0032] The outer plate deployment indication acquisition circuit in the +X side drive module is electrically connected to the outer plate micro switch of the +X side synthetic aperture radar antenna deployment mechanism, and is used to determine whether the +X side outer plate antenna has been deployed.

[0033] The outer plate deployment indication acquisition circuit in the -X side drive module is electrically connected to the outer plate micro switch in the -X side synthetic aperture radar antenna deployment mechanism, and is used to determine whether the -X side outer plate antenna has been deployed.

[0034] Specifically, the inner panel unfolding position indication acquisition circuit is configured the same as the outer panel unfolding position indication acquisition circuit;

[0035] This includes the fifth resistor, the sixth resistor, the third capacitor, the fourth capacitor, the third diode, and the fourth diode;

[0036] One end of the fifth resistor is electrically connected to the external power supply, and the other end of the fifth resistor is electrically connected to the positive terminal of the third diode and one end of the sixth resistor. The negative terminal of the third diode is electrically connected to the negative terminal of the fourth diode and one end of the inner plate microswitch or the outer plate microswitch. The inner plate microswitch or the outer plate microswitch is connected in parallel with the fourth diode. The other end of the inner plate microswitch or the outer plate microswitch is grounded, and the positive terminal of the fourth diode is grounded. The other end of the sixth resistor is the output terminal and is electrically connected to one end of the third capacitor. The other end of the third capacitor is electrically connected to the fourth capacitor, and the other end of the fourth capacitor is grounded.

[0037] Specifically, the power supply management module includes a control power supply circuit, a drive power supply circuit, and a primary / backup switching circuit; the control power supply circuit is used to supply power to the signal isolation circuit and the deployment position indication acquisition circuit in the +X side drive module and the -X side drive module; the drive power supply circuit is used to supply power to the drive circuit in the +X side drive module and the -X side drive module; the primary / backup switching circuit is used to realize the switching between the primary circuit and the backup circuit.

[0038] Compared with the prior art, the present invention has at least one of the following technical advantages:

[0039] This invention provides a spaceborne highly integrated synthetic aperture radar (SAR) antenna deployment system. Using an FPGA as the control core, it drives the main and backup windings of the inner and outer plate motors of the +X and -X side SAR antenna deployment mechanisms, thereby achieving on-orbit deployment of the antenna deployment mechanism. It can control the dual-sided four-axis SAR antenna deployment mechanism, simultaneously controlling the on-orbit deployment of four SAR antennas: the +X side inner plate antenna, the +X side outer plate antenna, the -X side inner plate antenna, and the -X side outer plate antenna. The entire deployment process is implemented by FPGA software and features an automatic stop function after timeout, effectively protecting the SAR antenna deployment mechanism. The stepper motors driving the four SAR antennas are started using a sinusoidal acceleration curve for frequency conversion starting. The frequency conversion start time is a programmable parameter that can be adjusted according to actual needs. No frequency conversion speed reduction is performed when the stepper motors stop directly. Attached Figure Description

[0040] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention.

[0041] Figure 1 This is a structural diagram of a spaceborne highly integrated synthetic aperture radar antenna deployment system according to an embodiment of the present invention;

[0042] Figure 2 This is the inner and outer plate unfolding angle indication and acquisition circuit of this invention embodiment;

[0043] Figure 3 This is the inner and outer plate unfolding position indication acquisition circuit of this invention embodiment;

[0044] Figure 4 This is a schematic diagram of the speed curve of the inner plate unfolding process according to an embodiment of the present invention;

[0045] Figure 5 This is a schematic diagram of the speed curve of the outer plate unfolding process according to an embodiment of the present invention;

[0046] Figure 6 This is a flowchart illustrating the operational process of a spaceborne highly integrated synthetic aperture radar antenna deployment system according to an embodiment of the present invention.

[0047] Explanation of reference numerals in the attached figures

[0048] R1: First resistor; R2: Second resistor; R3: Third resistor; R4: Fourth resistor; R5: Fifth resistor; R6: Sixth resistor; V1: First diode; V2: Second diode; V3: Third diode; V4: Fourth diode; C1: First capacitor; C2: Second capacitor; C3: Third capacitor; C4: Fourth capacitor; N1: Operational amplifier. Detailed Implementation

[0049] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the specific implementation methods of the present invention will be described below with reference to the accompanying drawings. Obviously, the drawings described below are merely some embodiments of the present invention. For those skilled in the art, other drawings and other implementation methods can be obtained based on these drawings without any creative effort.

[0050] To keep the drawings concise, only the parts relevant to the invention are shown schematically in each figure, and they do not represent the actual structure of the product. Furthermore, for ease of understanding, in some figures, only one of components with the same structure or function is shown schematically, or only one is labeled. In this document, "one" can mean not only "only one" but also "more than one".

[0051] The following detailed description, in conjunction with the accompanying drawings and specific embodiments, provides a more detailed account of a spaceborne highly integrated synthetic aperture radar antenna deployment system proposed in this invention. The advantages and features of this invention will become clearer from the following description and claims.

[0052] Example

[0053] See Figure 1 This embodiment provides a spaceborne highly integrated synthetic aperture radar antenna deployment system. It fully utilizes the advantages of FPGAs, such as high integration, low power consumption, abundant pin resources, and flexible design, to control the deployment mechanism of a dual-sided four-axis system. Simultaneously, it controls the on-orbit deployment of four synthetic aperture radar antennas: the +X side inner antenna, the +X side outer antenna, the -X side inner antenna, and the -X side outer antenna. The entire deployment process is implemented by FPGA software and features an automatic stop function after timeout, effectively protecting the synthetic aperture radar antenna deployment mechanism. The stepper motors driving the four synthetic aperture radar antennas are started using a sinusoidal acceleration curve for frequency conversion. The frequency conversion start time is a programmable parameter that can be adjusted according to actual needs. No frequency conversion speed reduction is performed when the stepper motors stop directly.

[0054] Specifically, this embodiment includes a power management module, a +X side drive module, a -X side drive module, a +X side synthetic aperture radar antenna deployment mechanism, and a -X side synthetic aperture radar antenna deployment mechanism. All three modules—the power management module, the +X side drive module, the -X side drive module, the +X side synthetic aperture radar antenna deployment mechanism, and the -X side synthetic aperture radar antenna deployment mechanism—adopt a primary / backup redundancy design.

[0055] See Figure 1 The power management module is electrically connected to the +X-side drive module, the -X-side drive module, the +X-side synthetic aperture radar antenna deployment mechanism, and the -X-side synthetic aperture radar antenna deployment mechanism, providing primary and secondary power to each module and mechanism. The power management module includes a control power supply circuit, a drive power supply circuit, and a primary / backup switching circuit. The control power supply circuit supplies power to the signal isolation circuits and deployment position indication acquisition circuits within the +X-side and -X-side drive modules. The drive power supply circuit supplies power to the drive circuits within the +X-side and -X-side drive modules. The primary / backup switching circuit enables switching between the primary and backup circuits.

[0056] Specifically, see Figure 1 The +X-side drive module is also electrically connected to the +X-side synthetic aperture radar antenna deployment mechanism, driving the stepper motor within the mechanism to rotate the inner and outer motor windings, thereby enabling the on-orbit deployment of the +X-side synthetic aperture radar antenna deployment mechanism. Similarly, the -X-side drive module is also electrically connected to the -X-side synthetic aperture radar antenna deployment mechanism, driving the stepper motor within this mechanism to achieve on-orbit deployment of the -X-side synthetic aperture radar antenna deployment mechanism.

[0057] Specifically, the stepper motor in the +X side synthetic aperture radar antenna deployment mechanism includes an +X side inner plate motor and a +X side outer plate motor; the +X side inner plate motor is used to deploy the +X side inner plate antenna in the +X side synthetic aperture radar antenna deployment mechanism in orbit; the +X side outer plate motor is used to deploy the +X side outer plate antenna in the +X side synthetic aperture radar antenna deployment mechanism in orbit.

[0058] The stepper motors in the -X side synthetic aperture radar antenna deployment mechanism include an -X side inner plate motor and an -X side outer plate motor; the -X side inner plate motor is used to deploy the -X side inner plate antenna in the -X side synthetic aperture radar antenna deployment mechanism in orbit; the -X side outer plate motor is used to deploy the -X side outer plate antenna in the -X side synthetic aperture radar antenna deployment mechanism in orbit.

[0059] Specifically, the operating frequency of the +X side inner panel motor and the -X side inner panel motor is 1533.33Hz, and the corresponding deployment speed of the +X side inner panel antenna and the -X side inner panel antenna is 0.3° / s, with a rotation angle range from 0° to 90°.

[0060] Specifically, the operating frequency of the +X side outer panel motor and the -X side outer panel motor is 3666.67Hz, and the corresponding deployment speed of the +X side outer panel antenna and the -X side outer panel antenna is 0.7174° / s, with a rotation angle range from 0° to 180°.

[0061] Specifically, see Figure 1 , Figure 2 and Figure 3 In the +X side synthetic aperture radar antenna deployment mechanism, internal microswitches and +X side inner and outer plate angle displacement sensors are used to collect real-time information on the deployment position indication and deployment angle indication of the inner and outer plates. The collected deployment position indications are sent to the satellite attitude control system and FPGA for processing, while the collected deployment angle indications are sent to the satellite integrated electronic system for further processing. Similarly, the -X side synthetic aperture radar antenna deployment mechanism is configured in the same way, and will not be elaborated upon here.

[0062] Specifically, see Figure 2 In this embodiment, in order to obtain the inner and outer plate unfolding angle indication, i.e., the unfolding angle value, both the +X side drive module and the -X side drive module are equipped with an inner plate unfolding angle indication acquisition circuit and an outer plate unfolding angle indication acquisition circuit, which are electrically connected to the inner plate angle displacement sensor and the outer plate angle displacement sensor provided in the +X side synthetic aperture radar antenna unfolding mechanism and the -X side synthetic aperture radar antenna unfolding mechanism, so as to obtain specific measurement values.

[0063] Specifically, the inner plate deployment angle indication and acquisition circuit in the +X side drive module is electrically connected to the inner plate angle displacement sensor in the +X side synthetic aperture radar antenna deployment mechanism, and is used to measure the deployment angle of the +X side inner plate antenna; the inner plate deployment angle indication and acquisition circuit in the -X side drive module is electrically connected to the inner plate angle displacement sensor in the -X side synthetic aperture radar antenna deployment mechanism, and is used to measure the deployment angle of the -X side inner plate antenna; the outer plate deployment angle indication and acquisition circuit in the +X side drive module is electrically connected to the outer plate angle displacement sensor in the +X side synthetic aperture radar antenna deployment mechanism, and is used to measure the deployment angle of the +X side outer plate antenna; the outer plate deployment angle indication and acquisition circuit in the -X side drive module is electrically connected to the outer plate angle displacement sensor in the -X side synthetic aperture radar antenna deployment mechanism, and is used to measure the deployment angle of the -X side outer plate antenna.

[0064] See Figure 2The inner and outer panel unfolding angle indicator acquisition circuits on the ±X sides are responsible for powering four WD22E precision angle displacement sensors on the 90° and 180° hinges on the ±X sides, and providing a telemetry acquisition channel. The WD22E precision angle displacement sensor is powered by +12V and has a theoretical electrical travel of 320°±5°. The inner and outer panel unfolding angle indicator acquisition circuits on the ±X sides do not control the angle sensor information themselves; this angle sensor information is only used for ground monitoring.

[0065] Specifically, the inner panel unfolding angle indicator acquisition circuit and the outer panel unfolding angle indicator acquisition circuit are configured identically, including a first resistor R1, a second resistor R2, a third resistor R3, a fourth resistor R4, a first capacitor C1, a second capacitor C2, an operational amplifier N1, a first diode V1, and a second diode V2.

[0066] Explaining along the current direction, the 12V external power supply is input from the positive terminal of the first diode V1, and after being divided by the second resistor R2, it enters the angle displacement sensor. The first diode V1 and the second resistor R2 work together to improve the reliability of the power supply circuit. The angle displacement sensor is then grounded to ensure its normal operation. The angle displacement sensor also has an output port. Its output signal passes through an RC filter circuit composed of the first resistor R1, the first capacitor C1, and the second capacitor C2 before entering the non-inverting input of operational amplifier N1. The use of the RC filter circuit enhances the signal's anti-interference capability. The output terminal of operational amplifier N1 is connected to its own inverting input terminal. Its output signal passes through the third resistor R3 and is then sent to the satellite integrated electronic system for acquisition. The fourth resistor R4 is connected in parallel with the second diode V2, with one end connected between the third resistor R3 and the output terminal, and the other end of the fourth resistor and the other end of the second diode also grounded.

[0067] Specifically, see Figure 1 and Figure 3Both the +X-side drive module and the -X-side drive module are equipped with an inner plate deployment indication acquisition circuit and an outer plate deployment indication acquisition circuit; both the +X-side synthetic aperture radar antenna deployment mechanism and the -X-side synthetic aperture radar antenna deployment mechanism are equipped with an inner plate micro switch and an outer plate micro switch; the inner plate deployment indication acquisition circuit in the +X-side drive module is electrically connected to the inner plate micro switch of the +X-side synthetic aperture radar antenna deployment mechanism, and is used to determine whether the +X-side inner plate antenna has been deployed; the inner plate deployment indication acquisition circuit in the -X-side drive module is electrically connected to the outer plate micro switch of the -X-side synthetic aperture radar antenna deployment mechanism. The inner plate microswitch of the X-side synthetic aperture radar antenna deployment mechanism is electrically connected to determine whether the -X-side inner plate antenna has been deployed. The outer plate deployment position indication acquisition circuit in the +X-side drive module is electrically connected to the outer plate microswitch of the +X-side synthetic aperture radar antenna deployment mechanism to determine whether the +X-side outer plate antenna has been deployed. The outer plate deployment position indication acquisition circuit in the -X-side drive module is electrically connected to the outer plate microswitch of the -X-side synthetic aperture radar antenna deployment mechanism to determine whether the -X-side outer plate antenna has been deployed.

[0068] Specifically, the inner panel unfolding position indication acquisition circuit on the ±X side is configured the same as the outer panel unfolding position indication acquisition circuit, which includes a fifth resistor R5, a sixth resistor R6, a third capacitor C3, a fourth capacitor C4, a third diode V3, and a fourth diode V4.

[0069] Following the direction of current flow, the 5V external power supply first passes through the fifth resistor R5, then splits into two paths. One path passes through the RC filter circuit consisting of the sixth resistor R6, the third capacitor C3, and the fourth capacitor C4 before being sent to the FPGA. The other end of the fourth capacitor is grounded. The other path is input from the positive terminal of the third diode V3 and output to the entire satellite attitude control system. The negative terminal of the third diode is electrically connected to the negative terminal of the fourth diode and one end of the inner or outer microswitch. The inner or outer microswitch is connected in parallel with the fourth diode V4, and the other end of the inner or outer microswitch is grounded. The positive terminal of the fourth diode V4 is grounded.

[0070] Specifically, in this embodiment, the synthetic aperture radar antenna deployment controller can realize 13-channel control command detection function, and can detect 13-channel control commands in real time and latch valid commands. Valid commands are low level. The FPGA's processing modules for each microswitch are independent and uncoupled. The FPGA can perform filtering and anti-jitter processing on the control commands. The method is to determine whether the low-level pulse width is (80±20)ms after acquiring the control command. If it is, the signal is locked and the corresponding function is executed. If the low-level pulse width does not meet the requirement, the command signal is discarded and the current state is maintained.

[0071] Specifically, the 13 control commands include the "deploy according to program" command, forward, reverse, and stop commands for the inner and outer panel motors of the +X side synthetic aperture radar antenna, and forward, reverse, and stop commands for the inner and outer panel motors of the -X side synthetic aperture radar antenna. When the synthetic aperture radar antenna deployment controller receives the "deploy according to program" command, all motors execute the on-orbit deployment of a total of 4 synthetic aperture radar antennas on the ±X side according to the prescribed program.

[0072] Specifically, see Figure 4 After receiving the "deploy according to program" command, the synthetic aperture radar antenna deployment controller controls the ±X side inner plate to start at a frequency conversion speed of 0.3° / s. The frequency conversion start is achieved by controlling the micro-interval period. Different speeds correspond to different micro-interval periods. The 3s startup time is divided into 250 startup time points according to the sinusoidal acceleration speed curve, with each speed value corresponding to 0.012s. If a valid inner plate deployment indication signal is acquired at time T1, the system stops directly after a 2s delay. If the cumulative rotation time of the inner plate reaches 315s, the FPGA sets the inner plate timeout processing register and stops the corresponding motor directly.

[0073] Specifically, see Figure 5 Upon receiving the "deploy according to program" command, the synthetic aperture radar antenna deployment controller controls the ±X side outer panel to start at a frequency conversion speed of 0.7174° / s. Frequency conversion startup is achieved by controlling the micro-interval period; different speeds correspond to different micro-interval periods. The 3-second startup time is divided into 500 startup time points according to the sinusoidal acceleration curve, with each 0.006s corresponding to a speed value. If a valid outer panel deployment indication signal is acquired at time T2, the system stops immediately after a 2-second delay. If the cumulative rotation time of the outer panel reaches 270s, the FPGA sets the outer panel timeout processing register and stops the corresponding motor.

[0074] Specifically, refer to Figure 6 In this embodiment, motor 1 refers to the inner plate motor of the +X or -X side synthetic aperture radar antenna; motor 2 refers to the outer plate motor of the +X or -X side synthetic aperture radar antenna. The control program for the deployment mechanism of the +X and -X side synthetic aperture radar antennas is the same. In this embodiment, after power-on, when the "deploy according to program" command is received from the entire satellite, the +X and -X side synthetic aperture radar antennas will deploy according to the program. Figure 6The flowchart shown is in operation. Under normal circumstances, the motor can be stopped in the following three situations: (1) Stop command, that is, the motor of the inner and outer plates is stopped when the command is received on the +X side or -X side; (2) Receive unfolding position indication signal, that is, after receiving the inner plate unfolding position indication, the motor 1 (inner plate motor) is stopped, and after receiving the outer plate unfolding position indication, the motor 2 (outer plate motor) is stopped; (3) No unfolding position indication signal is received after timeout, that is, the outer plate unfolding exceeds 270s, the outer plate motors on the +X side and -X side stop simultaneously, and the inner plate unfolding exceeds 315s, the inner plate motors on the +X side and -X side stop simultaneously.

[0075] Specifically, the working principle of this embodiment is as follows: After the satellite is launched into orbit, the synthetic aperture radar antenna deployment controller is powered on and receives the "deploy according to program" command from the entire satellite. It controls the ±X side synthetic aperture radar antenna deployment mechanisms to simultaneously deploy the antenna wings. Each side deployment mechanism drives the inner and outer antenna arrays to deploy. The ±X side inner plate motor is located at the 90° hinge and connected to the satellite. From retraction to deployment, this motor drives the inner plate deployment mechanism to deploy from 0° to 90°. The ±X side outer plate motor is located at the 180° hinge position. From retraction to deployment, this motor drives the outer plate deployment mechanism to deploy from 0° to 180°. During the on-orbit deployment of the four ±X side synthetic aperture radar antennas, the synthetic aperture radar antenna deployment controller monitors the deployment completion indicator and deployment angle indicator in real time. After deployment, the hinge locks, a microswitch sends a deployment completion indicator signal, the deployment mechanism is powered off, and the deployment movement is complete.

[0076] The embodiments of the present invention have been described in detail above with reference to the accompanying drawings, but the present invention is not limited to the above embodiments. Even if various changes are made to the present invention, if these changes fall within the scope of the claims of the present invention and their equivalents, they shall still fall within the protection scope of the present invention.

Claims

1. A spaceborne highly integrated synthetic aperture radar antenna deployment system, characterized in that, include: The system includes a power management module, a +X side drive module, a -X side drive module, a +X side synthetic aperture radar antenna deployment mechanism, and a -X side synthetic aperture radar antenna deployment mechanism. All of these components adopt a primary / backup redundancy design. The power supply management module is electrically connected to the +X side drive module and the -X side drive module respectively, and is used to supply power to the +X side drive module and the -X side drive module; The +X-side drive module is electrically connected to the +X-side synthetic aperture radar antenna deployment mechanism and is used to drive the stepper motor in the +X-side synthetic aperture radar antenna deployment mechanism, thereby realizing the on-orbit deployment of the +X-side synthetic aperture radar antenna deployment mechanism; wherein, the stepper motor in the +X-side synthetic aperture radar antenna deployment mechanism includes a +X-side inner plate motor and a +X-side outer plate motor; the +X-side inner plate motor is used to deploy the +X-side inner plate antenna in the +X-side synthetic aperture radar antenna deployment mechanism on-orbit; the +X-side outer plate motor is used to deploy the +X-side outer plate antenna in the +X-side synthetic aperture radar antenna deployment mechanism on-orbit. The -X-side drive module is electrically connected to the -X-side synthetic aperture radar antenna deployment mechanism and is used to drive the stepper motor in the -X-side synthetic aperture radar antenna deployment mechanism, thereby realizing the on-orbit deployment of the -X-side synthetic aperture radar antenna deployment mechanism. The stepper motor in the -X-side synthetic aperture radar antenna deployment mechanism includes an -X-side inner plate motor and an -X-side outer plate motor. The -X-side inner plate motor is used to deploy the -X-side inner plate antenna in the -X-side synthetic aperture radar antenna deployment mechanism in orbit; the -X-side outer plate motor is used to deploy the -X-side outer plate antenna in the -X-side synthetic aperture radar antenna deployment mechanism in orbit.

2. The spaceborne highly integrated synthetic aperture radar antenna deployment system according to claim 1, characterized in that, The operating frequency of the +X side inner plate motor and the -X side inner plate motor is 1533.33Hz, and the corresponding deployment speed of the +X side inner plate antenna and the -X side inner plate antenna is 0.3° / s, with a rotation angle range from 0° to 90°.

3. The spaceborne highly integrated synthetic aperture radar antenna deployment system according to claim 1, characterized in that, The operating frequency of the +X side outer panel motor and the -X side outer panel motor is 3666.67Hz, and the corresponding deployment speed of the +X side outer panel antenna and the -X side outer panel antenna is 0.7174° / s, with a rotation angle range from 0° to 180°.

4. The spaceborne highly integrated synthetic aperture radar antenna deployment system according to claim 1, characterized in that, Both the +X-side drive module and the -X-side drive module are equipped with an inner plate unfolding angle indication and acquisition circuit and an outer plate unfolding angle indication and acquisition circuit; both the +X-side synthetic aperture radar antenna unfolding mechanism and the -X-side synthetic aperture radar antenna unfolding mechanism are equipped with an inner plate angle displacement sensor and an outer plate angle displacement sensor. The inner plate unfolding angle indication and acquisition circuit in the +X side drive module is electrically connected to the inner plate angle displacement sensor in the +X side synthetic aperture radar antenna unfolding mechanism, and is used to measure the unfolding angle of the +X side inner plate antenna. The inner plate deployment angle indication and acquisition circuit in the -X side drive module is electrically connected to the inner plate angle displacement sensor in the -X side synthetic aperture radar antenna deployment mechanism, and is used to measure the deployment angle of the -X side inner plate antenna. The outer plate deployment angle indication and acquisition circuit in the +X side drive module is electrically connected to the outer plate angle displacement sensor in the +X side synthetic aperture radar antenna deployment mechanism, and is used to measure the deployment angle of the +X side outer plate antenna. The outer plate deployment angle indication and acquisition circuit in the -X side drive module is electrically connected to the outer plate angle displacement sensor in the -X side synthetic aperture radar antenna deployment mechanism, and is used to measure the deployment angle of the -X side outer plate antenna.

5. The spaceborne highly integrated synthetic aperture radar antenna deployment system according to claim 4, characterized in that, The inner plate unfolding angle indicator acquisition circuit is configured the same as the outer plate unfolding angle indicator acquisition circuit. It includes a first resistor, a second resistor, a third resistor, a fourth resistor, a first capacitor, a second capacitor, an operational amplifier, a first diode, and a second diode; The positive terminal of the first diode is electrically connected to an external power supply, the negative terminal of the first diode is electrically connected to one end of the second resistor, and the other end of the second resistor is electrically connected to the outer plate angle displacement sensor or the inner plate angle displacement sensor. One end of the first resistor is electrically connected to the outer plate angle displacement sensor or the inner plate angle displacement sensor, and the other end of the first resistor is electrically connected to the non-inverting input terminal of the operational amplifier and one end of the first capacitor, respectively; the other end of the first capacitor is electrically connected to the second capacitor, and the other end of the second capacitor is grounded; the output terminal of the operational amplifier is electrically connected to the inverting input terminal of the operational amplifier and one end of the third resistor, and the other end of the third resistor is the output terminal, and is electrically connected to one end of the fourth resistor and the negative terminal of the second diode, respectively; The other end of the fourth resistor is grounded, and the other end of the second diode is grounded.

6. The spaceborne highly integrated synthetic aperture radar antenna deployment system according to claim 5, characterized in that, Both the +X-side drive module and the -X-side drive module are equipped with an inner plate deployment position indication acquisition circuit and an outer plate deployment position indication acquisition circuit; both the +X-side synthetic aperture radar antenna deployment mechanism and the -X-side synthetic aperture radar antenna deployment mechanism are equipped with an inner plate micro switch and an outer plate micro switch; The inner plate deployment indication acquisition circuit in the +X side drive module is electrically connected to the inner plate micro switch of the +X side synthetic aperture radar antenna deployment mechanism, and is used to determine whether the +X side inner plate antenna has been deployed. The inner plate deployment indication acquisition circuit in the -X side drive module is electrically connected to the inner plate micro switch of the -X side synthetic aperture radar antenna deployment mechanism, and is used to determine whether the -X side inner plate antenna has been deployed. The outer plate deployment indication acquisition circuit in the +X side drive module is electrically connected to the outer plate micro switch of the +X side synthetic aperture radar antenna deployment mechanism, and is used to determine whether the +X side outer plate antenna has been deployed. The outer plate deployment indication acquisition circuit in the -X side drive module is electrically connected to the outer plate micro switch in the -X side synthetic aperture radar antenna deployment mechanism, and is used to determine whether the -X side outer plate antenna has been deployed.

7. The spaceborne highly integrated synthetic aperture radar antenna deployment system according to claim 6, characterized in that, The inner panel unfolding position indication acquisition circuit is configured the same as the outer panel unfolding position indication acquisition circuit. This includes the fifth resistor, the sixth resistor, the third capacitor, the fourth capacitor, the third diode, and the fourth diode; One end of the fifth resistor is electrically connected to the external power supply, and the other end of the fifth resistor is electrically connected to the positive terminal of the third diode and one end of the sixth resistor. The negative terminal of the third diode is electrically connected to the negative terminal of the fourth diode and one end of the inner plate microswitch or the outer plate microswitch. The inner plate microswitch or the outer plate microswitch is connected in parallel with the fourth diode. The other end of the inner plate microswitch or the outer plate microswitch is grounded, and the positive terminal of the fourth diode is grounded. The other end of the sixth resistor is the output terminal and is electrically connected to one end of the third capacitor. The other end of the third capacitor is electrically connected to the fourth capacitor, and the other end of the fourth capacitor is grounded.

8. The spaceborne highly integrated synthetic aperture radar antenna deployment system according to claim 7, characterized in that, The power management module includes a control power supply circuit, a drive power supply circuit, and a main / standby switching circuit. The control power supply circuit is used to supply power to the signal isolation circuits in the +X side drive module and the -X side drive module, as well as the unfolding position indication acquisition circuit; The drive power supply circuit is used to supply power to the drive circuits in the +X side drive module and the -X side drive module; The primary / backup switching circuit is used to switch between the primary circuit and the backup circuit.

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