A satellite-borne integrated antenna mechanism driver

Abstract

The present invention discloses a satellite-borne integrated antenna mechanism driver for controlling and driving an external antenna, including a communication module for receiving serial communication instructions from an external intersatellite communication integrated terminal and inputting them into a control module and returning a data message; an angle acquisition module for real-time acquisition of the angular position information of the external antenna and inputting them into the control module; a control module for generating a drive signal output according to the serial communication instruction and driving the external antenna, and transmitting the angular position information of the external antenna; and a drive module for amplifying the drive signal. The present invention is lightweight and integrated, and reduces the power consumption of the motor load; it can simultaneously realize the tracking and pointing of a two-dimensional high and low orbit antenna mechanism and two one-dimensional medium and low orbit antenna mechanisms, and the driving of the two-dimensional high and low orbit pointing mechanism and the two one-dimensional medium and low orbit pointing mechanisms have a software limit protection function, and can simultaneously provide two-way data communication between high and low orbit optical warning satellites and medium and low orbit optical warning satellites.

Description

Technical Field

[0001] The invention belongs to the field of satellite-borne antenna control, and in particular relates to a satellite-borne integrated antenna mechanism driver. Background Art

[0002] At present, the antenna mechanism drivers widely used in orbit generally adopt the CPU+FPGA control solution, which has a high hardware cost; the product structure mostly adopts a bracket or box-type structure, which has many disadvantages such as bulky products, poor mechanical response ability, complex processes and constant maintenance; the product shell material is generally made of aluminum alloy, which has weak impact load resistance; the controlled objects are mostly two-dimensional pointing mechanisms, and there is a technical problem of insufficient scalability. Summary of the invention

[0003] The technical purpose of the present invention is to provide a satellite-borne integrated antenna mechanism driver to solve the deficiencies of the prior art.

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

[0005] A satellite-borne integrated antenna mechanism driver, used to control and drive an external antenna, comprising: a communication module, a control module, a drive module and an angle acquisition module;

[0006] The communication module is connected to the control module by signal, and is used to receive serial communication instructions from the external intersatellite communication integrated terminal and input them into the control module and return data messages;

[0007] The angle acquisition module is connected to the control module signal, and is used to collect the angle position information of the external antenna in real time and input it to the control module;

[0008] The control module is used to generate a driving signal output and drive the external antenna according to the serial communication instruction, and transmit the angle position information of the external antenna to the ground terminal through the communication module and the external inter-satellite communication integrated terminal for calculation and processing to obtain the tracking angle calculation value;

[0009] The driving module is used to amplify the driving signal and then input it to the driving mechanism of the external antenna.

[0010] Further preferably, it also includes a power module for receiving the primary bus power of the entire satellite, and obtaining a secondary power supply through a DCDC conversion circuit arranged in the power module to input to the control module to provide power support.

[0011] Among them, the communication module, control module, drive module, angle acquisition module and power module are all connected by high-density printed circuit board connectors. The material is magnesium-aluminum alloy ZK61 M, and the surface is coated with thermal control paint.

[0012] Among them, the communication module, control module, drive module, angle acquisition module and power module all adopt cold backup dual redundancy measures.

[0013] Specifically, the power module uses J36A-9ZJB as the external connector, which is used to receive the primary bus power and return line of the entire satellite.

[0014] Among them, the communication module adopts a one-transmit-two-receive communication mechanism with a baud rate of 115.2kbaud and a response communication mode. The external intersatellite communication integrated terminal is the host, the antenna mechanism driver is the slave, and the serial port communication instruction is a loop control speed instruction. The returned data message includes the acquisition angle, angular velocity information, motor current and working status quantity of the antenna mechanism driver.

[0015] Among them, the driving mechanism includes a two-dimensional high and low orbit antenna mechanism. The control module sends a driving pulse to the two-dimensional high and low orbit intersatellite antenna mechanism to drive the two-dimensional high and low orbit rotation axis for mechanical scanning according to the tracking angle calculation value or the two-dimensional high and low orbit rotation axis fixed-point pointing information recorded on the ground, drives the beam tracking of the high and low orbit parabolic antenna to point to the GEO satellite, and reports the real-time angle of the rotation position of the two-dimensional high and low orbit pointing mechanism to the external intersatellite communication integrated terminal.

[0016] Among them, the driving mechanism includes two one-dimensional medium and low orbit antenna mechanisms. The control module sends driving pulses to the one-dimensional medium and low orbit intersatellite antenna mechanism to drive the two one-dimensional medium and low orbit rotation axes to perform mechanical scanning based on the tracking angle calculation value or the two one-dimensional medium and low orbit rotation axis fixed-point pointing information recorded on the ground, and synchronously cooperates with the antenna electronic scanning to drive the beam tracking of the medium and low orbit intersatellite antenna to point to the LEO satellite, and reports the real-time angle of the rotation position of the two one-dimensional medium and low orbit pointing mechanisms to the external intersatellite communication integrated terminal.

[0017] Due to the adoption of the above technical solution, the present invention has the following advantages and positive effects compared with the prior art:

[0018] The present invention connects the modules of the driving mechanism with high-density printed circuit board connectors to achieve lightweight and integration. The connectors are made of magnesium-aluminum alloy ZK61M, which has the characteristics of high strength, light weight, good heat dissipation, strong anti-electromagnetic interference performance, etc.

[0019] The control module of the present invention uses FPGA as the control core and adopts a PWM driving scheme to reduce the power consumption of the motor load; it can simultaneously realize the tracking and pointing of a two-dimensional high and low orbit antenna mechanism and two one-dimensional medium and low orbit antenna mechanisms, and the driving of the two-dimensional high and low orbit pointing mechanism and the two one-dimensional medium and low orbit pointing mechanisms all have a software limit protection function; it can simultaneously provide two-way data communication between high and low orbit optical warning satellites and medium and low orbit optical warning satellites. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the following detailed description of the preferred embodiment.The drawings are only for the purpose of illustrating the preferred embodiments and are not to be construed as limiting the invention.

[0021] Figure 1 A schematic diagram of the structure of a satellite-borne integrated antenna mechanism driver provided by an embodiment of the present invention;

[0022] Figure 2 A schematic diagram of the structure principle of a serial communication circuit provided in an embodiment of the present invention. DETAILED DESCRIPTION

[0023] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the specific implementation methods of the present invention will be described below with reference to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings and other implementation methods can be obtained based on these drawings without creative work.

[0024] In order to simplify the drawings, only the parts related to the present invention are schematically shown in each figure, and they do not represent the actual structure of the product. In addition, in order to simplify the drawings and facilitate understanding, in some figures, only one of the parts with the same structure or function is schematically drawn or marked. In this article, "one" not only means "only one", but also means "more than one".

[0025] The advantages and features of the present invention will become more apparent from the following description and claims.

[0026] Example

[0027] See also Figure 1 This embodiment provides a satellite-borne integrated antenna mechanism driver for controlling and driving an external antenna. It can be divided into a communication module, a control module, a drive module, and an angle acquisition module. The above modules adopt an integrated design scheme and are integrated with each other. Each module is connected by a high-density printed circuit board connector. The overall structural parts of the module are made of magnesium-aluminum alloy ZK61 M, and the surface is coated with thermal control paint. It has the characteristics of high strength, light weight, good heat dissipation, and strong anti-electromagnetic interference performance. The control module uses FPGA as the control core and adopts a PWM drive scheme. It can simultaneously realize the tracking and pointing of a two-dimensional high-low orbit antenna mechanism and two one-dimensional medium-low orbit antenna mechanisms, a total of three antenna mechanisms. The drive of the three antenna mechanisms has a software limit protection function. It can also provide two-way data communication between high-low orbit optical warning satellites and medium-low orbit optical warning satellites.

[0028] Specifically, the communication module, control module, drive module, angle acquisition module and power supply module all adopt cold backup dual redundancy measures, which can be divided into primary and backup. Their settings and functions are the same, so the following description will only be given in general terms of each module.

[0029] See also Figure 1 , one end of the communication module is connected to the control module signal, and the other end of the communication module is connected to the external intersatellite communication integrated terminal signal. The communication module adopts a one-transmit-two-receive communication mechanism, the baud rate is 115.2kbaud, and the communication mode is response type. The signal transmission of the communication module is bidirectional. On the one hand, it receives the serial communication command from the intersatellite communication integrated terminal and inputs it into the control module. The serial communication command is a loop control speed command. On the other hand, the data message is fed back to the intersatellite communication integrated terminal. The intersatellite communication integrated terminal can communicate with the ground control terminal and can transmit the data message on the satellite to the ground. The data message includes the acquisition angle, angular velocity information, motor current and working status quantity of this embodiment.

[0030] The power module is electrically connected to the control module and the drive module respectively. The external connector is J36A-9ZJB, which is used to receive the primary bus power and return line of the entire satellite. The primary bus power passes through the DCDC conversion circuit in the power module to obtain the secondary power input to the control module and the drive module to provide power support.

[0031] The control module is also connected to one end of the drive module and one end of the angle acquisition module. The control module uses FPGA as the control core to modulate the stepper motor drive direction signal and the subdivided PWM drive pulse to send to the drive module, and collects the angle information fed back by the angle acquisition module in real time.

[0032] The control module can generate a driving signal output and drive the motor of the external antenna according to the serial communication instruction, and transmit the angular position information of the external antenna to the ground end through the communication module and the external intersatellite communication integrated terminal for calculation and processing to obtain the tracking angle calculation value.

[0033] When the driving mechanism is a two-dimensional high-orbit antenna mechanism, the control module sends a driving pulse to the two-dimensional high-orbit intersatellite antenna mechanism to drive the two-dimensional high-orbit rotation axis for mechanical scanning based on the tracking angle calculation value or the two-dimensional high-orbit rotation axis fixed-point pointing information recorded on the ground, drives the beam tracking of the high-orbit parabolic antenna to point to the GEO satellite (high-orbit satellite), and reports the real-time angle of the rotation position of the two-dimensional high-orbit pointing mechanism to the external intersatellite communication integrated terminal.

[0034] When the driving mechanism is two one-dimensional low-orbit antenna mechanisms, the control module sends a driving pulse to the one-dimensional low-orbit intersatellite antenna mechanism to drive the two one-dimensional low-orbit rotation axes to perform mechanical scanning based on the tracking angle calculation value or the two one-dimensional low-orbit rotation axis fixed-point pointing information recorded on the ground, and synchronously cooperates with the antenna electronic scanning to drive the beam tracking of the low-orbit intersatellite antenna to point to the LEO satellite (low-orbit satellite), and reports the real-time angle of the rotation position of the two one-dimensional low-orbit pointing mechanisms to the external intersatellite communication integrated terminal.

[0035] The other end of the driving module is connected to the driving mechanism signal of the external antenna, receives the driving direction signal and PWM driving pulse of the control module, amplifies the power of both, and drives the X-axis motor winding and Y-axis motor winding of the high and low orbit antenna mechanism, the motor winding of the medium and low orbit antenna A mechanism, and the motor winding of the medium and low orbit antenna B mechanism respectively.

[0036] The other end of the angle acquisition module is connected to the signal of the drive mechanism of the external antenna. With the dual-channel rotary transformer AD2S80 as the core, the angle position information of the antenna mechanism motor is obtained through demodulation, and the angle information is transmitted to the control module to realize closed-loop control of the position.

[0037] Figure 2 Schematic diagram of the structure principle of the serial communication interface circuit between the communication module and the inter-satellite communication integrated terminal in this embodiment. Figure 2 The communication module is used as the slave, and the intersatellite communication integrated terminal is used as the host. The communication line interface is a balanced asynchronous serial port, a standard RS-422 interface, a half-duplex I / O, and the transmission medium is a twisted pair. Both the master communication module and the backup communication module have a 26C31 chip. The two sets of redundant data outputs of each 26C31 chip are connected to the host and backup of the intersatellite communication integrated terminal at the same time, which enhances the reliability of communication.

[0038] The principle of this embodiment is as follows: After the satellite is launched into orbit, the antenna mechanism driver is powered on and works according to the working mode required by the entire satellite. The working modes include: (1) pointing and tracking mode, receiving the serial communication instructions of the intersatellite communication integrated terminal, using FPGA as the control core to modulate the stepper motor drive direction signal and the subdivided PWM drive pulse, driving the motor windings of a two-dimensional high and low orbit antenna mechanism and two one-dimensional medium and low orbit antenna mechanisms, a total of three antenna mechanisms, to rotate at a specified speed, so as to complete the preset mode, program tracking mode, program control mode and automatic tracking mode of the three antenna mechanisms; (2) power-off holding mode, the antenna mechanism driver is only powered on and does not work, and the motor windings of the three antenna mechanisms are not powered; (3) power-on holding mode, the antenna mechanism driver is only powered on, and the motor windings of the three antenna mechanisms are only powered on and do not rotate.

[0039] The embodiments of the present invention are described in detail above in conjunction with 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 still fall within the protection scope of the present invention.

Claims

1. A satellite-borne integrated antenna mechanism driver, used to control and drive an external antenna, characterized in that: include: Communication module, control module, drive module and angle acquisition module; The communication module is connected to the control module by signal, and is used to receive serial communication instructions from an external intersatellite communication integrated terminal and input them into the control module and return data messages; The angle acquisition module is connected to the control module signal, and is used to collect the angle position information of the external antenna in real time and input it to the control module; The control module is used to generate a driving signal output and drive the external antenna according to the serial communication instruction, and transmit the angular position information of the external antenna to the ground terminal through the communication module and the external inter-satellite communication integrated terminal for calculation and processing to obtain a tracking angle calculation value; The driving module is used to amplify the driving signal and then input it to the driving mechanism of the external antenna; The driving mechanism includes a two-dimensional high-low orbit antenna mechanism, and the control module sends a driving pulse to the two-dimensional high-low orbit intersatellite antenna mechanism to drive the two-dimensional high-low orbit rotation axis to perform mechanical scanning according to the tracking angle calculation value or the two-dimensional high-low orbit rotation axis fixed-point pointing information recorded on the ground, drives the beam tracking of the high-low orbit parabolic antenna to point to the GEO satellite, and reports the real-time angle of the rotation position of the two-dimensional high-low orbit pointing mechanism to the external intersatellite communication integrated terminal; The driving mechanism includes two one-dimensional low- and medium-orbit antenna mechanisms. The control module sends a driving pulse to the one-dimensional low- and medium-orbit intersatellite antenna mechanism to drive the two one-dimensional low- and medium-orbit rotation axes to perform mechanical scanning according to the tracking angle calculation value or the two one-dimensional low- and medium-orbit rotation axis fixed-point pointing information recorded on the ground, and synchronously cooperates with the antenna electric scanning to drive the beam tracking of the low- and medium-orbit intersatellite antenna to point to the LEO satellite, and reports the real-time angle of the rotation position of the two one-dimensional low- and medium-orbit pointing mechanisms to the external intersatellite communication integrated terminal.

2. The onboard integrated antenna mechanism driver according to claim 1, characterized in that: It also includes a power module for receiving the primary bus power of the entire satellite, and obtaining a secondary power supply through a DCDC conversion circuit arranged in the power module to input to the control module to provide power support.

3. The onboard integrated antenna mechanism driver according to claim 2, characterized in that: The communication module, the control module, the drive module, the angle acquisition module and the power supply module are all connected by high-density printed circuit board connectors.

4. The satellite-borne integrated antenna mechanism driver according to claim 3, characterized in that The structural parts of the communication module, the control module, the drive module, the angle acquisition module and the power module are made of magnesium-aluminum alloy ZK61M, and the surface is coated with thermal control paint.

5. The onboard integrated antenna mechanism driver according to claim 2, characterized in that: The communication module, the control module, the drive module, the angle acquisition module and the power supply module all adopt cold backup dual redundancy measures.

6. The onboard integrated antenna mechanism driver according to claim 2, characterized in that: The power module uses J36A-9ZJB as the external connector, which is used to receive the primary bus power and return line of the entire satellite.

7. The onboard integrated antenna mechanism driver according to claim 1, characterized in that: The communication module adopts a one-transmit-two-receive communication mechanism with a baud rate of 115.2 kbaud and a response communication mode. The external intersatellite communication integrated terminal is the host, the antenna mechanism driver is the slave, the serial port communication instruction is a loop control speed instruction, and the returned data message includes the acquisition angle, angular velocity information, motor current and working status quantity of the antenna mechanism driver.

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