Simulation test system for aircraft

Abstract

The invention provides a simulation test system for an aircraft, and the system comprises a test bus which is used for being connected with a flight control computer of the aircraft, and the cable length of the test bus is the same as the cable length of a real bus of the aircraft; and at least one node device, each node device corresponding to a real device in the aircraft, the node device communicating with the flight control computer through the test bus. In the embodiment of the invention, the cable length of the test bus is the same as the cable length of the real bus in the aircraft, so that the actual operation condition can be simulated more accurately, and the credibility of the test result is improved.

Description

Technical Field

[0001] The present disclosure relates to the technical field of aircraft, and particularly to a simulation test system for an aircraft. Background Art

[0002] With the continuous development of aerospace technology, the application of unmanned aerial vehicle (UAV) systems is becoming more and more extensive, and the demand for simulation testing of flight systems is also increasing day by day. Traditional flight system simulation platforms often face problems such as high costs, limited number of nodes, and insufficient reliability, making it difficult to meet the growing simulation requirements. Therefore, it is particularly important to develop a flight system simulation platform with low cost, multiple nodes, and high reliability.

[0003] Therefore, it is necessary to propose a new technical solution to solve at least one of the above technical problems. Summary of the Invention

[0004] To overcome at least one aspect of the technical problems in the prior art, the present disclosure is proposed.

[0005] According to one aspect of an embodiment of the present disclosure, a simulation test system for an aircraft is proposed, including: a test bus for connecting to the flight control computer of the aircraft, the cable length of the test bus being the same as that of the real bus of the aircraft; at least one node device, each node device corresponding to a real device in the aircraft, and the node device communicating with the flight control computer through the test bus. Brief Description of the Drawings

[0006] The above and other aspects and features of the present disclosure will be clearly presented from the following description of embodiments in conjunction with the drawings, where:

[0007] Figure 1 is a schematic structural diagram of a simulation test system for an aircraft according to an embodiment of the present disclosure;

[0008] Figure 2 is a schematic diagram of a data processing flow according to an embodiment of the present disclosure. Detailed Embodiments

[0009] The following description of the embodiments of the present disclosure with reference to the drawings is intended to explain the general inventive concept of the present disclosure, and should not be construed as a limitation of the present disclosure. Based on the embodiments in the present disclosure, all other embodiments obtained by those skilled in the art belong to the scope of protection of the present disclosure.

[0010] Embodiments of the present disclosure provide a simulation test system for simulating and testing the operation of on-board equipment of an aircraft, including equipment such as a flight control computer, sensors, and motors. In this simulation test system, the flight control computer communicates with other equipment via a test bus (corresponding to the real bus in the aircraft). The cable length of this test bus is the same as that of the real bus in the aircraft, which can more accurately simulate the actual operating conditions, thereby improving the credibility of the test results.

[0011] Figure 1 is a schematic structural diagram of a simulation test system for an aircraft according to an embodiment of the present disclosure. As Figure 1 shown, this system is used to simulate and test flight control computers in an aircraft, such as flight control computer 1, flight control computer 2,..., flight control computer n. The system includes a test bus. Exemplarily, the test bus is a CAN bus, which includes Figure 1 multiple data transmission channels such as CANFD1, CANFD2, CAN in

[0012] In embodiments of the present disclosure, the length of the test bus is the same as that of the corresponding real bus. In addition, it is easy to understand that the material, model, etc. of the test bus are also consistent with those of the real bus to more accurately simulate the actual operating conditions.

[0013] As Figure 1 shown, the system further includes a plurality of node devices, such as node device 1, node device 2,..., node device 64, etc. Each stage device corresponds to a real device in the aircraft other than the flight control computer. For example, node device 1 corresponds to an accelerometer, node device 2 corresponds to an altitude sensor, and node device 3 corresponds to a motor.

[0014] In existing test schemes, real devices in an aircraft are usually implemented by software simulation, and the simulation authenticity is limited, and the response time of the devices cannot be simulated. In this embodiment, simulation is performed at the hardware level, and node devices are used to simulate the corresponding real devices, which is beneficial to improving the authenticity of the simulation and can also simulate the response time of the devices.

[0015] In an alternative embodiment, each of the above node devices may be an embedded device to improve the processing efficiency of the node device and achieve better real-time performance.

[0016] Generally speaking, in CAN communication, a CAN board is needed for signal conversion. CAN boards can be divided into ordinary CAN boards and real-time CAN boards. Compared with ordinary CAN boards, real-time CAN boards have high real-time performance, high processing performance, high time accuracy, and complex processing capabilities, but at the same time, they have higher costs.

[0017] In the above embodiment, using an embedded device to implement the node device has good real-time performance and processing capabilities, and can achieve high simulation real-time performance and simulation accuracy based on an ordinary CAN board, which is beneficial to saving hardware costs.

[0018] In this embodiment, each node device is connected to the test bus through a corresponding test branch line (see the double-arrow straight line between the node device and the test bus in Figure 1 . Optionally, the length of each test branch line is the same as that of the corresponding real branch line in the aircraft (the test branch line between the node device and the test bus corresponds to the real branch line between the corresponding real device and the real bus) to achieve higher authenticity. It is easy to understand that the parameters such as the material and model of the test branch line are also the same as those of the real branch line to more accurately simulate the actual operating conditions.

[0019] As Figure 1 shown, the simulation test system in this embodiment further includes a simulation computer. The simulation computer is used to run the data model of the aircraft. The simulation computer is connected to the test bus.

[0020] In an alternative embodiment, the simulation computer runs the data model of the aircraft at a high frequency (≥200 Hz), and can accurately simulate the dynamic behavior of the aircraft, providing accurate test data for the flight control computer.

[0021] In an alternative embodiment, the simulation computer can be implemented using an embedded device.

[0022] In an alternative embodiment, the simulation computer receives the actuator control instruction sent by the flight control computer through the bus, performs model calculation, and obtains the attitude, position, altitude, etc. of the aircraft, and sends them as sensor simulation data.

[0023] In the embodiment of the present disclosure, the data protocol between the flight control computer and the node device is the same as the real data protocol of the aircraft. Thus, this embodiment can simulate and test the real data protocol in the aircraft.

[0024] In an alternative embodiment, the node device can be replaced by a corresponding real device. Thus, as the R & D process progresses, after the real device is in place, it can be conveniently connected to the simulation test system to perform tests with higher authenticity on the real device and the overall system.

[0025] As Figure 1 described, the simulation test system in this embodiment further includes a bus test device. The bus test device is used to monitor the signals on the test bus to obtain test results and can also inject hardware faults (such as simulating short circuits, current increases, etc.).

[0026] Figure 2 is a schematic diagram of the data processing flow according to an embodiment of the present disclosure. As Figure 2 shown, first, the simulation computer loads the aircraft data model and performs data preprocessing, and then processes the data and distributes it to each node. After receiving the data, each node performs further processing.

[0027] In the embodiments of the present disclosure, a high - efficiency, reliable, and low - cost semi - physical simulation platform is provided for the flight system of an aircraft, especially an unmanned aerial vehicle. This platform not only has high real - time performance and accuracy but also has the advantages of being easy to develop and maintain, providing strong support for the R & D and application of the flight system of an aircraft, especially an unmanned aerial vehicle.

[0028] In some embodiments of the present disclosure, the simulation test system can achieve the following technical effects: (1) Highly realistic test environment: By using the actual cable length, branch length, and data protocol for testing, it is possible to more accurately simulate the actual operating conditions, thereby improving the credibility of the test results; (2) Real-time performance verification: The fast response time (≤200 μs) of the slave node device ensures that the system can meet the real-time requirements, which is crucial for the flight control system; (3) Redundant design: The design of multiple flight control computers as the master nodes increases the redundancy of the system, improving the overall reliability and fault tolerance; (4) Flexibility and scalability: Using node simulation devices allows testing to be carried out before the actual devices are in place, which not only saves costs but also improves the flexibility of testing. In addition, once the actual devices are ready, they can be easily integrated into the system; (5) Comprehensive fault simulation: With the node and bus fault injection and simulation functions, it is possible to test the system's response to various potential faults in a controlled environment, thereby evaluating its robustness and fault recovery mechanism; (6) High-precision model calculation: The simulation computer runs the aircraft data model at a high frequency (≥200 Hz), which can accurately simulate the dynamic behavior of the aircraft and provide accurate test data for the flight control system; (7) 7. Comprehensive test platform: This system can not only test the performance of the flight control computer but also verify the effectiveness and stability of the entire network communication, including the accuracy and real-time performance of data transmission; (8) Facilitate early problem discovery: By conducting comprehensive testing and verification in the early development stage, it can help identify potential design and implementation problems, thereby reducing the costs and risks of later modifications; (9) Support multiple test scenarios: Due to the high configurability of the system, it can be used to simulate a variety of different flight conditions and operation scenarios, thus more comprehensively evaluating the performance of the flight control system.

[0029] Based on the above, the present disclosure proposes the following technical solutions:

[0030] 1. A simulation test system for an aircraft, comprising:

[0031] A test bus for connecting to the flight control computer of the aircraft, the cable length of the test bus being the same as the cable length of the actual bus of the aircraft;

[0032] At least one node device, each node device corresponding to an actual device in the aircraft, and the node device communicates with the flight control computer through the test bus.

[0033] 2. The simulation test system according to 1, further comprising:

[0034] A test branch line provided between the node device and the test bus, the cable length of the test branch line being the same as the cable length of the corresponding actual branch line.

[0035] 3. The simulation test system according to 1, wherein:

[0036] The node device is an embedded device.

[0037] 4. The simulation test system according to 1, further comprising:

[0038] A simulation computer for running the data model of the aircraft and connected to the test bus.

[0039] 5. The simulation test system according to 4, wherein:

[0040] The solution frequency of the simulation computer is greater than or equal to 200 Hz.

[0041] 6. The simulation test system according to 4, wherein:

[0042] The simulation computer is an embedded device.

[0043] 7. The simulation test system according to 1, wherein:

[0044] The test bus is a CAN bus.

[0045] 8. The simulation test system according to 1, wherein:

[0046] The CAN board of the CAN bus is a common CAN board.

[0047] 9. The simulation test system according to 1, wherein:

[0048] The data protocol between the flight control computer and the node device is consistent with the real data protocol of the aircraft.

[0049] 10. The simulation test system according to 1, wherein:

[0050] The at least one node device is adapted to be replaced by a corresponding real device.

[0051] Although the embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that various changes may be made therein without departing from the principles and spirit of the invention, and the scope of the invention is defined by the appended claims and their equivalents.

Claims

1. A simulation test system for an aircraft, comprising: A test bus for connecting to the flight control computer of the aircraft, the cable length of the test bus being the same as that of the real bus of the aircraft; At least one node device, each node device corresponding to a real device in the aircraft, and the node device communicates with the flight control computer through the test bus.

2. The simulation test system according to claim 1, further comprising: A test branch line provided between the node device and the test bus, the cable length of the test branch line being the same as that of the corresponding real branch line.

3. The simulation test system according to claim 1, wherein: The node device is an embedded device.

4. The simulation test system according to claim 1, further comprising: A simulation computer for running the data model of the aircraft and connected to the test bus.

5. The simulation test system according to claim 4, wherein: The solution frequency of the simulation computer is greater than or equal to 200 Hz.

6. The simulation test system according to claim 4, wherein: The simulation computer is an embedded device.

7. The simulation test system according to claim 1, wherein: The test bus is a CAN bus.

8. The simulation test system according to claim 1, wherein: The CAN board of the CAN bus is a common CAN board.

9. The simulation test system according to claim 1, wherein: The data protocol between the flight control computer and the node device is consistent with the real data protocol of the aircraft.

10. The simulation test system according to claim 1, wherein: The at least one node device is adapted to be replaced by the corresponding real device.

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