A comprehensive controller with integrated data link and control method thereof

Abstract

The present invention provides a missile integrated controller with an integrated missile-borne data link and a control method thereof. The controller comprises a power board, a baseband control board, and a radio frequency board. The power board and the baseband control board, and the baseband control board and the radio frequency board, are connected via board-to-board connectors. The baseband control board includes a system-on-chip (SoC) chip integrating a dual-core ARM processor and a programmable logic gate array. One core of the dual-core ARM processor is used to process data from each individual unit on the aircraft, calculate aircraft control parameters, and execute instructions from a ground fire control system. The other core of the dual-core ARM processor is used to configure data link parameters and conduct wireless communications. The present invention provides an integrated controller with an integrated data link and a control method thereof to address existing problems such as high hardware design costs, complex software coupling, and delayed information exchange and instruction responses.

Description

Technical Field

[0001] The present invention relates to the field of aircraft guidance and control technology, and in particular to a comprehensive controller with integrated data link and a control method thereof. Background Art

[0002] The aircraft control system is the core of the aircraft's information processing, determining its tactical and technical performance. The integrated controller performs navigation, guidance, attitude control, and logic and timing control functions. The data link enables real-time exchange of images, commands, attitude, and position information between the aircraft and the ground-based fire control system, ensuring agile and precise target engagement. The integrated controller and data link are connected via cables within the aircraft.

[0003] The existing aircraft control systems use two single machines, the integrated controller and the data link, which have problems such as high hardware design cost, complex software coupling, and untimely information interaction and command response. Summary of the Invention

[0004] The present invention provides a comprehensive controller with integrated data link and a control method thereof, which are used to solve the problems existing in the prior art such as high hardware design cost, complex software coupling, and untimely information interaction and instruction response.

[0005] In one aspect, the present invention provides an integrated controller with an integrated data link, comprising a power board, a baseband control board, and a radio frequency board, wherein the power board and the baseband control board, and the baseband control board and the radio frequency board are connected via a board-to-board connector, wherein:

[0006] The power board is used to supply power to the baseband control board and the radio frequency board;

[0007] The baseband control board includes a SoC chip, a power management chip, a synchronous dynamic random access memory, a flash memory, an optical coupler, a reset chip, a phase-locked loop, a radio frequency agile transceiver, a first transceiver, an analog-to-digital converter, a second transceiver, and a third transceiver. The SoC chip integrates a dual-core ARM processor and a programmable logic gate array. The dual-core ARM processor is connected to the synchronous dynamic random access memory and the flash memory. One core of the dual-core ARM processor is used to process data of each single machine on the aircraft, calculate the control parameters of the aircraft, and execute instructions of the ground fire control system. The other core of the dual-core ARM processor is used to configure data link parameters and perform wireless communication. The programmable logic gate array is connected to the optical coupler, the reset chip, the phase-locked loop, the radio frequency agile transceiver, the first transceiver, the analog-to-digital converter, the second transceiver, and the third transceiver.

[0008] The radio frequency board is used to complete the conversion between an intermediate frequency signal and a radio frequency signal. The intermediate frequency signal is output by the radio frequency agile transceiver, and the radio frequency signal is received by an antenna.

[0009] The above scheme adopts a modular design concept and integrates the data link and the integrated controller into an integrated design, which saves the internal space of the aircraft, the cables between single machines and the physical resources of storage chips, makes the software coupling between the data link and the integrated controller more efficient and faster, and effectively reduces the software and hardware design, production and testing costs of the aircraft control system; avoids the information interaction between the data link and the integrated controller when they are not integrated, makes the operation more convenient, and the command response more timely.

[0010] Optionally, the power board converts input power into a DC low-voltage steady-state power supply to supply power to the baseband control board and the radio frequency board, and the input power is input through a first external connector.

[0011] Optionally, the input power supply is a power supply on the aircraft or a DC power supply output by ground test equipment.

[0012] Optionally, the data link parameters include communication system, modulation mode, coding mode, time slot, time frame and anti-interference algorithm.

[0013] Optionally, the wireless communication includes communication between an aircraft and a ground fire control system and communication between aircraft.

[0014] Optionally, the baseband control board is connected to each of the stand-alone machines via a second external connector.

[0015] Optionally, the RF board includes a first low-pass filter, a first low-noise amplifier, a second low-pass filter, a first mixer, a third low-pass filter, a driver amplifier, an attenuator, a power amplifier, a receive / transmit switch, a dielectric filter, a limiter, a second low-noise amplifier, a fourth low-pass filter, a second mixer, a first intermediate frequency amplifier, an intermediate frequency filter and a second intermediate frequency amplifier.

[0016] Optionally, also include:

[0017] It features slotted fins on both the bottom and top of the housing.

[0018] The above solution increases the surface area of ​​the housing, thereby achieving the purpose of heat dissipation.

[0019] In another aspect, the present invention provides a control method for an integrated controller with an integrated data link, which is applied to any of the above controllers, comprising:

[0020] S101, collect self-test information of each single unit on the aircraft and determine whether the self-test information is qualified. If qualified, execute S102; if unqualified, end;

[0021] S102, analyzing whether the output data of each stand-alone machine is normal. If it is normal, execute S103; if it is not normal, end;

[0022] S103, notifying the UAV platform to launch the aircraft, selectively setting the data link working mode, and executing S104;

[0023] S104, when the aircraft enters the homing flight state, selectively set the working mode and execute S105;

[0024] S105, processing the interactive information of the data link in real time, and adjusting the flight control strategy according to the uplink control command of the ground fire control system or the coordinated command of other aircraft, and executing S106;

[0025] S106, determining whether the aircraft has landed, if so, the process ends, if not, executing S104.

[0026] The above solution avoids the information interaction between the data link and the integrated controller when they are not integrated, making the operation more convenient and the command response more timely.

[0027] Optionally, the working mode includes a silent mode and an output mode. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0029] Figure 1 A schematic diagram of a framework of a comprehensive controller with integrated data link provided by an embodiment of the present invention;

[0030] Figure 2 A schematic structural diagram of a baseband control board provided in an embodiment of the present invention;

[0031] Figure 3 A schematic structural diagram of a radio frequency board provided in an embodiment of the present invention;

[0032] Figure 4 The present invention provides a flowchart of a control method for an integrated controller with an integrated data link. DETAILED DESCRIPTION

[0033] To make the objectives, technical solutions, and advantages of the present invention more apparent, the present invention will be further described in detail below with reference to the accompanying drawings. It is apparent that the embodiments described are only some, not all, of the present invention. All other embodiments derived by persons of ordinary skill in the art based on the embodiments of the present invention without creative effort are intended to fall within the scope of protection of the present invention.

[0034] Figure 1 A framework diagram of an integrated controller with an integrated data link provided by an embodiment of the present invention is shown, which includes a power board, a baseband control board and a radio frequency board. The power board and the baseband control board, and the baseband control board and the radio frequency board are connected through board-to-board connectors.

[0035] The board-to-board connector enables back-to-back plug-in. The board-to-board connector between the power board and baseband control board and the board-to-board connector between the baseband control board and the RF board are structurally identical, but the board-to-board connector between the power board and the baseband control board is used to transmit power signals, while the board-to-board connector between the baseband control board and the RF board is used to transmit power signals and intermediate frequency signals.

[0036] The bottom layer is the power board, which is used to supply power to the baseband control board and the radio frequency board.

[0037] In one example, the power board converts input power into a DC low-voltage steady-state power supply to power the baseband control board and the radio frequency board, and the input power is input through the first external connector.

[0038] Furthermore, the input power is a power supply on the aircraft and a DC power supply output by the ground test equipment. The power supply on the aircraft can be a thermal battery or a lithium battery, and the DC power supply voltage output by the ground test equipment can be 28V.

[0039] The middle layer is the baseband control board, which is the core circuit of the integrated controller.

[0040] The baseband control board includes a SoC chip, a power management chip, a synchronous dynamic random access memory, a flash memory, an optical coupler, a reset chip, a phase-locked loop, a radio frequency agile transceiver, a first transceiver, an analog-to-digital converter, a second transceiver and a third transceiver. The SoC chip integrates a dual-core ARM processor and a programmable logic gate array. The dual-core ARM processor is connected to the synchronous dynamic random access memory and the flash memory. One core of the dual-core ARM processor is used to process data of each single machine on the aircraft, calculate the control parameters (navigation, guidance and attitude, etc.) of the aircraft and execute instructions from the ground fire control system. The other core of the dual-core ARM processor is used to configure data link parameters and conduct wireless communication. The programmable logic gate array is connected to the optical coupler, reset chip, phase-locked loop, radio frequency agile transceiver, the first transceiver, the analog-to-digital converter, the second transceiver and the third transceiver.

[0041] Optocouplers are used to isolate the transmitting and receiving circuit boards on the serial communication cable to prevent external interference from affecting communication.

[0042] The phase-locked loop is used to provide a precise clock source for the programmable logic gate array and the first mixer and the second mixer on the radio frequency board.

[0043] The RF agile transceiver is used to convert information such as the aircraft's image, attitude, and position into intermediate frequency signals.

[0044] In one example, the first transceiver is a 1533B transceiver, which is a bus protocol commonly used in military aircraft.

[0045] Analog-to-digital converters are used to convert analog signals sent by acceleration, vibration, temperature sensors, etc. into digital signals.

[0046] In one example, the second transceiver is a CAN transceiver. CAN is a common bus used for multiple devices to communicate with each other on the same communication line.

[0047] In one example, the third transceiver is an RS422 transceiver or an RS485 transceiver. RS422 and RS485 are serial communication protocols at the software layer.

[0048] In one example, the data link parameters include communication system, modulation mode, coding mode, time slot, time frame and anti-interference algorithm.

[0049] A time slot is the smallest basic unit that constitutes a wireless physical channel, and a time frame consists of multiple time slots.

[0050] In one example, wireless communications include communications between an aircraft and a ground fire control system and communications between aircraft.

[0051] In one example, the baseband control board is connected to each stand-alone device via a second external connector.

[0052] The second external connector is used to connect the seeker, inertial measurement unit, servo and other single units in the aircraft, and the connection can be achieved through the cable network in the aircraft.

[0053] Figure 2The structure of the baseband control board is shown, in which the SoC chip uses ZYNQ7045, the power management chip is a DC / DC power supply module, the synchronous dynamic random access memory uses DDR4, the flash memory is FLASH, the optocoupler uses the optocoupler TPL291-4, the reset chip uses the reset TPS3808, the phase-locked loop is PLL, the RF agile transceiver uses AD9364, the first transceiver uses BU64843, the analog-to-digital converter is an A / D acquisition circuit, the second transceiver uses ADM3053, and the third transceiver uses ADM2582. The ZYNQ7045 and AD9364 are connected through an LVDS high-speed signal interface.

[0054] When the existing data link and integrated controller are not integrated, the data link and the integrated controller need to be configured with a synchronous dynamic random access memory and a flash memory respectively. After integration, only one synchronous dynamic random access memory and one flash memory need to be configured, saving chip physical resources.

[0055] The top board is the RF board, which is used to complete the conversion between intermediate frequency signals and radio frequency signals. The intermediate frequency signal is output by the radio frequency agile transceiver, and the radio frequency signal is received by the antenna.

[0056] In one example, the RF board includes a first low-pass filter, a first low-noise amplifier, a second low-pass filter, a first mixer, a third low-pass filter, a driver amplifier, an attenuator, a power amplifier, a transmit / receive switch, a dielectric filter, a limiter, a second low-noise amplifier, a fourth low-pass filter, a second mixer, a first intermediate frequency amplifier, an intermediate frequency filter, and a second intermediate frequency amplifier.

[0057] Figure 3 The structure of a radio frequency board is shown. The radio frequency board is equipped with an antenna output interface. Figure 3 The antenna output interface is connected to the antenna on the aircraft bulkhead via a coaxial transmission line.

[0058] The intermediate frequency signal output from the RF agile transceiver of the baseband control board is transmitted to the RF board via the board-to-board connector, amplified by the first low-pass filter and the first low-noise amplifier, filtered by the second low-pass filter, and then up-converted and mixed with the first mixing frequency and the intrinsic signal to generate the RF signal to be transmitted. The power amplifier amplifies the RF signal to be transmitted to sufficient power, and then passes through the receive / transmit switch and the dielectric filter to output the RF signal to the omnidirectional antenna.

[0059] The signal received from the omnidirectional antenna first passes through a dielectric filter to suppress external clutter, then passes through a limiter, a second low-noise amplifier, and a fourth low-pass filter, and is down-converted and mixed with the local oscillator signal through a second mixer to generate an intermediate frequency signal. The signal then passes through a first intermediate frequency amplifier and an intermediate frequency filter to suppress interference signals, and then passes through a second intermediate frequency amplifier and is transmitted to the input interface of the RF agile transceiver of the baseband control board through a board-to-board connector.

[0060] In one example, the radio frequency link of the radio frequency board adopts a TDD communication system and a 1T1R transceiver combination.

[0061] The above scheme adopts a modular design concept and integrates the data link and the integrated controller into an integrated design, which saves the internal space of the aircraft, the cables between single machines and the physical resources of storage chips, makes the software coupling between the data link and the integrated controller more efficient and faster, and effectively reduces the software and hardware design, production and testing costs of the aircraft control system; avoids the information interaction between the data link and the integrated controller when they are not integrated, makes the operation more convenient, and the command response more timely.

[0062] In one example, an embodiment of the present invention provides an integrated controller for an integrated data link, further comprising:

[0063] It features slotted fins on both the bottom and top of the housing.

[0064] The embodiment of the present invention integrates the data link and the integrated controller, which greatly increases power consumption. The slotted fin design increases the surface area of ​​the housing, thereby achieving the purpose of heat dissipation.

[0065] In addition to the slotted fin design, heat dissipation can also be achieved by adding fans or liquid cooling.

[0066] Figure 4 The flow chart of a control method of an integrated controller with an integrated data link provided by an embodiment of the present invention is shown, including:

[0067] S101, collect self-test information of each single unit on the aircraft, and determine whether the self-test information is qualified. If qualified, execute S102; if unqualified, end.

[0068] Each unit on the aircraft includes the seeker, servo, inertial measurement unit, etc. The self-test information includes the operating status of the onboard components and software version numbers of each unit's circuit board.

[0069] S102, analyze whether the output data of each stand-alone machine is normal. If it is normal, execute S103; if it is abnormal, end.

[0070] The output data is the functional output of each stand-alone machine. If the value fluctuates irregularly or the data is interrupted at irregular intervals, it indicates abnormality.

[0071] S103, notifying the UAV platform to launch the aircraft, selectively setting the working mode of the data link, and executing S104.

[0072] In one example, the operating mode includes a silent mode and an output mode.

[0073] In silent mode, the RF agile transceiver is in a low signal gain state, and the aircraft can only receive control commands from the ground fire control system in a one-way manner.

[0074] In output mode, the RF agile transceiver is in a high signal gain state, and the aircraft can conduct two-way communication with the ground fire control system or other aircraft.

[0075] The integrated controller sends information such as the aircraft's position, attitude, and image to the ground in real time, and at the same time receives uplink control instructions and image information from the ground fire control system, realizing capture, control, and guidance based on "man in the loop".

[0076] S104, when the aircraft enters the homing flight state, the working mode is selectively set and S105 is executed.

[0077] It should be noted that the data link operating mode can be set during the aircraft's release phase and homing flight phase.

[0078] S105 , processing the interactive information of the data link in real time, and adjusting the flight control strategy according to the uplink control instructions of the ground fire control system or the coordinated instructions of other aircraft, and executing S106 .

[0079] S106, determine whether the aircraft has landed, if it has landed, then end, if not, execute S104.

[0080] The above solution avoids the information interaction between the data link and the integrated controller when they are not integrated, making the operation more convenient and the command response more timely.

[0081] Although the preferred embodiments of the present invention have been described, those skilled in the art may make additional changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the present invention.

[0082] Obviously, those skilled in the art may make various changes and modifications to this application without departing from the spirit and scope of this application. Thus, if these modifications and variations of this application fall within the scope of the claims of this application and their equivalents, this application is intended to include these modifications and variations.

Claims

1. A comprehensive controller with integrated data link, characterized in that: It includes a power board, a baseband control board, and a radio frequency board. The power board and the baseband control board, as well as the baseband control board and the radio frequency board, are connected via board-to-board connectors. The power board is used to supply power to the baseband control board and the radio frequency board; The baseband control board includes a SoC chip, a power management chip, a synchronous dynamic random access memory, a flash memory, an optical coupler, a reset chip, a phase-locked loop, a radio frequency agile transceiver, a first transceiver, an analog-to-digital converter, a second transceiver, and a third transceiver. The SoC chip integrates a dual-core ARM processor and a programmable logic gate array. The dual-core ARM processor is connected to the synchronous dynamic random access memory and the flash memory. One core of the dual-core ARM processor is used to process data of each single machine on the aircraft, calculate the control parameters of the aircraft, and execute instructions of the ground fire control system. The other core of the dual-core ARM processor is used to configure data link parameters and perform wireless communication. The programmable logic gate array is connected to the optical coupler, the reset chip, the phase-locked loop, the radio frequency agile transceiver, the first transceiver, the analog-to-digital converter, the second transceiver, and the third transceiver. The radio frequency board is used to complete the conversion between an intermediate frequency signal and a radio frequency signal. The intermediate frequency signal is output by the radio frequency agile transceiver, and the radio frequency signal is received by an antenna.

2. The controller according to claim 1, characterized in that: The power board converts input power into a DC low-voltage steady-state power supply to supply power to the baseband control board and the radio frequency board, and the input power is input through a first external connector.

3. The controller according to claim 2, characterized in that: The input power source is a power source on the aircraft or a DC power source output by ground test equipment.

4. The controller according to claim 1, characterized in that: The data link parameters include communication system, modulation mode, coding mode, time slot, time frame and anti-interference algorithm.

5. The controller according to claim 1, characterized in that: The wireless communication includes communication between an aircraft and a ground fire control system and communication between aircraft.

6. The controller according to claim 1, characterized in that: The baseband control board is connected to each of the single machines via a second external connector.

7. The controller according to claim 1, characterized in that: The radio frequency board includes a first low-pass filter, a first low-noise amplifier, a second low-pass filter, a first mixer, a third low-pass filter, a driver amplifier, an attenuator, a power amplifier, a receive / transmit switch, a dielectric filter, a limiter, a second low-noise amplifier, a fourth low-pass filter, a second mixer, a first intermediate frequency amplifier, an intermediate frequency filter, and a second intermediate frequency amplifier.

8. The controller according to claim 1, characterized in that: Also includes: It features slotted fins on both the bottom and top of the housing.

9. A control method for an integrated controller with an integrated data link, applied to the controller according to any one of claims 1 to 8, characterized in that: include: S101, collect self-test information of each single unit on the aircraft and determine whether the self-test information is qualified. If qualified, execute S102; if unqualified, end; S102, analyzing whether the output data of each stand-alone machine is normal. If it is normal, execute S103; if it is not normal, end; S103, notifying the UAV platform to launch the aircraft, selectively setting the data link working mode, and executing S104; S104, when the aircraft enters the homing flight state, selectively set the working mode and execute S105; S105, processing the interactive information of the data link in real time, and adjusting the flight control strategy according to the uplink control command of the ground fire control system or the coordinated command of other aircraft, and executing S106; S106, determining whether the aircraft has landed, if so, the process ends, if not, executing S104.

10. The method according to claim 9, characterized in that: The working modes include a silent mode and an output mode.

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