A flight control machine IMA board

Abstract

The utility model provides an IMA board for a flight control machine, comprising a baseboard and a baseboard bus interface located at one side of the baseboard; a CPU module, an AD / DA module, an aviation plug connector, a serial port module, a DI / DO module, a frequency module and an FPGA module are attached to the baseboard; the baseboard bus interface is a CAN bus architecture; the bottom bus interface comprises an analog input and output interface, a discrete input and output interface, a serial communication input and output interface and a frequency input interface. The application effectively solves the problem that the interface resources of the existing industrial flight control computer cannot be freely configured and the low-cost redundancy solution is difficult to achieve. Compared with the traditional board, the production cost is reduced, the hardware reliability is improved, and the free configuration of the later users is also convenient.

Description

[Technical field]

[0001] The utility model relates to the technical field of IMA boards, and in particular to an IMA board for a flight control machine which has the advantages of high portability, scalability and stability and which realizes a high fault-tolerant redundant solution configuration of a flight control computer through abundant interface resources. [Background Technology]

[0002] The flight control computer is the carrier for the realization of UAV control logic and is also the key link for the successful completion of flight missions. With the advancement of science and technology, the flight control computer is gradually developing in the direction of miniaturization, standardization and high reliability. At the same time, higher requirements are also put forward for the core interface board of the flight control computer.

[0003] The design of single-channel flight control computers abroad is getting rid of the resource limitations brought by a single board. The flight control computer jointly developed by Georgia Institute of Technology and other research institutions consists of a processor board and a sensor board designed and developed independently. The processor board selects the optimal fast floating-point processor, and the sensor board consists of digital logic and sensors. The flight control computer developed by the Indian Institute of Technology includes a processor card and a GPS and INS data acquisition card. The processor uses the low-cost TI floating-point processor TMS320VC33. Against the background of the maturity of single-channel flight control computers, fault-tolerant computers with higher reliability are also in a stage of rapid development.

[0004] At present, the flight control computers of high-end UAVs in the world all use fault-tolerant technology. The United States' high-altitude, long-endurance unmanned reconnaissance aircraft Global Hawk uses a dual-redundant flight control computer, and Europe's latest generation of unmanned reconnaissance aircraft "Barrakuda" and Israel's fourth-generation UAV "Heron" both use triple-redundant flight control computers.

[0005] In China, the development of UAVs started relatively late, only in the late 1960s, and their main uses were concentrated in target drones and tactical reconnaissance aircraft with low reliability requirements. In the early 21st century, domestic UAVs developed rapidly, and advanced multi-purpose UAVs such as "Wing Loong", "Color 3" and "Color 4" appeared. Flight control computers also gradually developed from single-channel to redundancy.

[0006] In order to achieve the standardization, redundancy and high reliability requirements of flight control computers, IMA, which integrates multiple core module resources, is particularly critical. On the one hand, comprehensive interface resources can free the flight control computer from dependence on a single board. On the other hand, redundant module configuration also facilitates the redundancy of the flight control computer. [Contents of the utility model]

[0007] The problems existing in the prior art solved by this application are:

[0008] Traditional boards have problems such as high production costs, low reliability, and are not conducive to users' free configuration in the later stage.

[0009] The solution to the technical problem of the utility model is:

[0010] Provided is an IMA board for a flight control machine, comprising a baseboard and a baseboard bus interface located on one side of the baseboard; a CPU module, an AD / DA module, an aviation plug connector, a serial port module, a DI / DO module, a frequency module and an FPGA module are attached to the baseboard; the baseboard bus interface is a CAN bus architecture; the bottom bus interface comprises an analog input and output interface, a discrete input and output interface, a serial communication input and output interface and a frequency input interface.

[0011] Preferably, the bottom bus interface includes 2 CAN interfaces, 6 A / D interfaces, 4 D / A interfaces, 4 DI interfaces, 4 DO interfaces, 1 frequency input interface, 4 serial ports, 3 RS232 / RS422 interfaces and 1 RS232 / RS422 / RS485 interface.

[0012] Preferably, the size of the bottom plate is 111 mm*118 mm; and the thickness of the bottom plate is 2 mm.

[0013] Preferably, the model of the CPU module is MPC555.

[0014] Preferably, the connector model of the aviation plug connector is J30JA2-66ZKW.

[0015] The technical effects of solving the technical problem in this application are as follows:

[0016] Compared with the prior art, the utility model provides an IMA board for flight control machines, which solves the problem that the interface resources of existing industrial flight control computers cannot be freely configured and low-cost redundancy solutions are difficult to implement. Compared with traditional boards, it reduces production costs, improves hardware reliability, and facilitates free configuration by later users. [Drawings]

[0017] Figure 1 The utility model is a three-dimensional structural diagram of an IMA board of a flight control machine.

[0018] Figure 2 The utility model is a schematic diagram of the framework structure of an IMA board of a flight control machine. [Specific implementation method]

[0019] In order to make the purpose, technical solution and advantages of the utility model more clear, the utility model is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the utility model and are not used to limit this utility model.

[0020] See also Figure 1 and Figure 2 The utility model discloses a flight control machine IMA board 1, comprising a baseboard 11 and a baseboard bus interface 12 located on one side of the baseboard 11; a CPU module 19, an AD / DA module 17, an aviation plug connector 13, a serial port module 15, a DI / DO module 14, a frequency module 16 and an FPGA module 18 are attached to the baseboard 11; the baseboard bus interface 12 is a CAN bus architecture; the baseboard bus interface 12 comprises an analog input and output interface, a discrete input and output interface, a serial communication input and output interface and a frequency input interface.

[0021] In some other embodiments, the bottom bus interface 12 includes 2 CAN interfaces, 6 A / D interfaces, 4 D / A interfaces, 4 DI interfaces, 4 DO interfaces, 1 frequency input interface, 4 serial ports, 3 RS232 / RS422 interfaces and 1 RS232 / RS422 / RS485 interface.

[0022] The size of the bottom plate 11 is 111 mm*118 mm; and the thickness of the bottom plate is 2 mm.

[0023] The model of the CPU module 19 is MPC555.

[0024] The connector model of the aviation plug connector 13 is J30JA2-66ZKW.

[0025] This patent proposes a new type of IMA board for standard flight control computers, which solves the problem that the interface resources of existing industrial flight control computers cannot be freely configured and low-cost redundancy solutions are difficult to implement. Compared with traditional boards, it reduces production costs, improves hardware reliability, and facilitates free configuration by later users.

[0026] At the same time, the IMA board supports CAN bus communication. Compared with the traditional PC / 104, MIL-STD-1553B and ARINC429 bus protocols, it has a higher transmission rate, a safer multi-master peer-to-peer structure, a single node failure does not affect the normal communication of other nodes, a more complete bus arbitration mechanism, and higher efficiency. At the same time, only three ordinary wires are needed for direct connection, which is simpler, more reliable, and cheaper;

[0027] The IMA board adopts CAN bus architecture, and integrates the CPU minimum system and a complete range of interface resources. The interface resources mainly include analog input and output, discrete input and output, serial communication input and output, and frequency input.

[0028] (1) 2-way CAN bus (FPGA uses CAN core to expand 2-way CAN interface);

[0029] (2) 6-channel A / D, 4-channel D / A, 4-channel DI, 4-channel DO, 1-channel frequency input;

[0030] (3) 4 serial ports, 3 RS232 / RS422, 1 RS232 / RS422 / RS485 (isolated);

[0031] (4) The minimum CPU system includes: CPU, FLASH, SRAM, BootLoader, watchdog (WDT), status light (LED), real-time clock (RTC), and NVRAM (512K per chip).

[0032] In the IMA plug-in board, the logic operation is realized by the CPU minimum system, and the interface resource management function is realized by the FPGA expansion of various controllers. The CPU manages the interface input and output by controlling the FPGA, so that the CPU with limited computing power can focus on controlling the logic operation, simplifying the complexity of interface driver programming, reducing CPU load, and improving system real-time performance;

[0033] Compared with other boards on the market, it has more abundant module interface resources;

[0034] The communication design based on CAN bus has higher communication efficiency and stronger reliability;

[0035] The redundancy configuration of the flight controller can be achieved by configuring multiple IMA boards;

[0036] Except for the CAN bus interface, the performance indicators of each sub-module of the IMA plug-in board are the same as those of the ISA core plug-in board. The details are as follows.

[0037] (1) CPU minimum system: The CPU uses the MPC555 processing chip with stable and reliable performance, an operating frequency of 40MHz, and an external 1M SRAM and 2M FLASH. At the same time, a 512K NVRAM is connected through the FPGA to quickly access important data during work.

[0038] (2) Serial port: The extended 4-channel serial port is managed by FPGA, and only the basic signals required for data transmission and reception are brought out. Among them, the first channel adopts isolation mode, and the communication mode can be selected as RS232 / RS422 / RS485; the second to fourth channels can choose RS232 / RS422 mode. Each serial port reception and transmission is configured with a 255-byte FIFO, and data transmission and reception adopts an efficient and simple queue buffering method.

[0039] (3) Analog interface: The AD sampling channel has a 16-bit resolution and can be calibrated by software. The analog input front end uses a second-order low-pass filter with a cutoff frequency of 10 Hz. Channels 1-3 are large voltage channels with an input range of ±15 V, and channels 4-6 are small voltage channels with an input range of ±10 V. The DA output channel has a 16-bit resolution, a maximum refresh rate of 100 kS / s, an output voltage range of ±10 V, and a drive capability of 10 mA.

[0040] (4) Discrete quantity interface: Discrete quantity input adopts photoelectric isolation technology to ensure the safety of core circuits. Input / output can flexibly select 27VDC / open or ground / open format through jumpers.

[0041] (5) Frequency measurement: The measurement range of the frequency measurement interface is 1Hz-1kHz, the accuracy is better than 0.1%, the high level range is 10-36V, and the low level range is 0-2V.

[0042] Different interface units have different mounted devices and specific functions, so the software logic they execute is not the same. In order to improve development efficiency and ensure good maintainability, the software reuse strategy of the interface unit is studied to achieve higher maintainability of the interface unit software.

[0043] By reading the configuration status of the hardware jumper, the IMA board ID can be obtained, which is represented by a 6-bit binary number ranging from 0 to 63, where 0-9 is defined as the control unit ID range and 10-19 is the interface unit ID range, thereby achieving the role distinction of each unit. The ID identification of the IMA board becomes the hardware basis of the interface unit software management strategy. The real-time operating system in the CPU becomes the software basis of the interface unit software management strategy by creating different tasks, activating different functions, and scheduling the kernel.

[0044] At the same time, the CAN bus abandons the traditional station address encoding and encodes the data instead. The devices are completely distinguished by the Label identification of the message frame. The data interaction between the plug-ins is no longer a master-slave architecture, but a peer-to-peer architecture with equal status. The plug-in board responsible for interface management first obtains the data of the attached device, and then converts it into usable information such as physical quantities through processing, and then actively encodes and packages the information and sends it to the bus. After the plug-in board responsible for logical solution obtains the information, it can interpret the Label to parse the data packet into the corresponding physical quantity and use it as the input for the solution. Throughout the process, each plug-in board is autonomously managed and sends and receives data autonomously to achieve information interaction;

[0045] The technical effects of solving the technical problem in this application are as follows:

[0046] Compared with the prior art, the utility model of a flight control machine IMA board 1 solves the problem that the existing industrial flight control computer interface resources cannot be freely configured and the low-cost redundancy solution is difficult to achieve. Compared with traditional boards, it reduces production costs, improves hardware reliability, and is convenient for later users to freely configure.

[0047] The above-described implementation methods of the utility model do not constitute a limitation on the protection scope of the utility model. Any modification, equivalent replacement and improvement made within the spirit and principle of the utility model shall be included in the protection scope of the claims of the utility model.

Claims

1. A flight control machine IMA board, characterized by: It includes a baseboard and a baseboard bus interface located on one side of the baseboard; the baseboard is attached with a CPU module, an AD / DA module, an aviation plug connector, a serial port module, a DI / DO module, a frequency module and an FPGA module; the baseboard bus interface is a CAN bus architecture; the baseboard bus interface includes an analog input and output interface, a discrete input and output interface, a serial communication input and output interface and a frequency input interface.

2. A flight control machine I MA board as claimed in claim 1, characterized in that: The backplane bus interface includes 2 CAN interfaces, 6 A / D interfaces, 4 D / A interfaces, 4 DI interfaces, 4 DO interfaces, 1 frequency input interface, 4 serial ports, 3 RS232 / RS422 interfaces and 1 RS232 / RS422 / RS485 interface.

3. A flight control machine I MA board as claimed in claim 1, characterized in that: The size of the bottom plate is 111mm*118mm; and the thickness of the bottom plate is 2mm.

4. The flight control machine IMA board as claimed in claim 1, characterized in that: The model of the CPU module is MPC555.

5. A flight control machine I MA board as claimed in any one of claims 1 to 4, characterized in that: The connector model of the aviation plug connector is J30JA2-66ZKW.

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