Integrated controller of integrated data chain and control method thereof

Abstract

The invention provides a missile comprehensive controller integrated with a missile-borne data chain and a control method thereof, the missile comprehensive controller comprises a power panel, a baseband control panel and a radio frequency board, the power panel and the baseband control panel are connected through a board-to-board connector, the baseband control panel and the radio frequency board are connected through a board-to-board connector, the baseband control panel comprises an SoC chip, and the SoC chip is connected with the radio frequency board through a board-to-board connector. The SoC chip is integrated with a dual-core ARM processor and a programmable logic gate array, one core of the dual-core ARM processor is used for processing data of each single machine on the aircraft, calculating control parameters of the aircraft and executing instructions of a ground fire control system, and the other core of the dual-core ARM processor is used for configuring data link parameters and performing wireless communication. The invention provides an integrated controller of an integrated data link and a control method thereof, which are used for solving the problems of high hardware design cost, complex software coupling, untimely information interaction and instruction response and the like in the prior art.

Description

Technical Field

[0001] The 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 part of aircraft information processing, which determines the tactical and technical performance of the aircraft. Among them, the integrated controller has functions such as navigation, guidance, attitude control, and logic timing control. The data link realizes the real-time interaction of images, instructions, attitudes, and positions between the aircraft and the ground fire control command system to achieve the requirements of agile and accurate target hitting. The integrated controller and the data link are connected through cables inside 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, so as 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. Another 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 the storage chip, 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, and is more convenient to operate and the command response is more timely.

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

[0011] Optionally, the input power source is a power source on the aircraft or a DC power source 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 single 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 fin design on both the bottom and top of the housing.

[0018] The above solution increases the surface area of ​​the housing and can achieve the purpose of heat dissipation.

[0019] On the other hand, the present invention provides a control method of an integrated controller with an integrated data link, which is applied to any of the above controllers, comprising:

[0020] S101, collecting self-test information of each single machine on the aircraft, and judging whether the self-test information is qualified, if qualified, executing S102, if unqualified, then ending;

[0021] S102, analyzing whether the output data of each stand-alone machine is normal, if normal, executing S103, if abnormal, then ending;

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

[0023] S104, when the aircraft enters the homing flight state, selectively setting the working mode, and executing 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, which makes 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 drawings required for use in the description of the embodiments will be briefly introduced below. 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 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 diagram of the structure of a baseband control board provided in an embodiment of the present invention;

[0031] Figure 3 A schematic diagram of the structure 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 of an integrated controller with an integrated data link according to an embodiment of the present invention. DETAILED DESCRIPTION

[0033] In order to make the purpose, technical scheme and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are 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 in an embodiment of the present invention is shown, including 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 a board-to-board connector.

[0035] The board-to-board connector realizes back-to-back plug-in. The board-to-board connector between the power board and the baseband control board and the board-to-board connector between the baseband control board and the RF board are the same in structure, but the board-to-board connector between the power board and the baseband control board is used to transmit the power supply signal, and the board-to-board connector between the baseband control board and the RF board is used to transmit the power supply signal and the intermediate frequency signal.

[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 powers the baseband control board and the radio frequency board by converting input power into a DC low-voltage steady-state power supply, and the input power is input through the first external connector.

[0038] Furthermore, the input power source is a power source on the aircraft and a DC power source output by the ground test equipment. The power source on the aircraft may be a thermal battery or a lithium battery, and the DC power source voltage output by the ground test equipment may 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 the data of each single machine on the aircraft, calculate the control parameters (navigation, guidance and attitude, etc.) of the aircraft and execute the 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.

[0041] Optocouplers are used to isolate the receiving and transmitting 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 image, attitude and position of the aircraft 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, the wireless communication includes communication between an aircraft and a ground fire control system and communication 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 adopts ZYNQ7045, the power management chip is a DC / DC power supply module, the synchronous dynamic random access memory adopts DDR4, the flash memory is FLASH, the optical coupler adopts the optical coupler TPL291-4, the reset chip adopts the reset TPS3808, the phase-locked loop is PLL, the RF agile transceiver adopts AD9364, the first transceiver adopts BU64843, the analog-to-digital converter is an A / D acquisition circuit, the second transceiver adopts ADM3053, and the third transceiver adopts ADM2582. ZYNQ7045 and AD9364 are connected through an LVDS high-speed signal interface.

[0054] In the case where 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 the intermediate frequency signal and the radio frequency signal. 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 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.

[0057] Figure 3 The structure of a radio frequency board is shown, and an antenna output interface is installed on the radio frequency board, that is, Figure 3 The antenna output interface is connected to the antenna on the aircraft cabin wall through 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 by the first mixing frequency and the intrinsic signal to generate a RF signal to be transmitted. The power amplifier amplifies the RF signal to be transmitted to sufficient power, and then outputs the RF signal to the omnidirectional antenna through the receive / transmit switch and the dielectric filter.

[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 the storage chip, 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, and is more convenient to operate and the command response is more timely.

[0062] In one example, an integrated controller with an integrated data link provided by an embodiment of the present invention further includes:

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

[0064] The embodiment of the present invention integrates the data link and the integrated controller together, which greatly increases the 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 a comprehensive controller with integrated data link provided by an embodiment of the present invention is shown, including:

[0067] S101, collect self-test information of each single machine 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 a seeker, a servo, an inertial measurement unit, etc. The self-test information includes the operating status of the onboard components and the software version number of each unit circuit board.

[0069] S102, analyzing whether the output data of each stand-alone machine is normal, if normal, executing S103, if abnormal, then ending.

[0070] The output data is the output of the functional items of each single machine. If the value fluctuates irregularly or the data is interrupted at irregular intervals, it means it is abnormal.

[0071] S103, notify the UAV platform to launch the aircraft, selectively set the working mode of the data link, and execute 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 unidirectional manner.

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

[0075] The integrated controller sends the aircraft's position, attitude, image and other information to the ground in real time, while receiving uplink control commands 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 operating mode of the data link can be set during the aircraft's release phase and homing flight phase.

[0078] S105, process the interactive information of the data link in real time, and adjust the flight control strategy according to the uplink control instructions of the ground fire control system or the coordinated instructions of other aircraft, and execute 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, which makes 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 can make various changes and modifications to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is also intended to include these modifications and variations.

Claims

1. An integrated 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, and the baseband control board and the radio frequency board are connected through a board-to-board connector, wherein: 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. Another 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 powers the baseband control board and the radio frequency board by converting input power into a DC low-voltage steady-state power supply, 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 driving 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 fin design 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 described in any one of claims 1 to 8, characterized in that: include: S101, collecting self-test information of each single machine on the aircraft, and judging whether the self-test information is qualified, if qualified, executing S102, if unqualified, then ending; S102, analyzing whether the output data of each stand-alone machine is normal, if normal, executing S103, if abnormal, then ending; S103, notifying the UAV platform to launch the aircraft, selectively setting the working mode of the data link, and executing S104; S104, when the aircraft enters the homing flight state, selectively setting the working mode, and executing 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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