Distributed dynamic excitation test system and method

Abstract

The invention provides a distributed dynamic excitation test system and method, and the system comprises an excitation data source system which generates dynamic flight parameters, and transmits the dynamic flight parameters to the distributed excitation test system according to a preset period; the distributed excitation test system converts the dynamic flight parameters into excitation signals and sends the excitation signals to the tested avionics system; the tested avionics system responds to the excitation signal; and the bus monitoring system is used for acquiring response data of the tested avionics system through a bus, comparing the response data with preset data and judging whether the working state of the tested avionics system meets requirements or not. The distributed design is adopted, flexible deployment can be carried out according to the laboratory environment, a multi-point excitation mode is adopted, dynamic system-level testing can be carried out, and the economical efficiency and reliability of the system are extremely high.

Description

Technical Field

[0001] This invention belongs to the field of helicopter avionics system testing technology, and particularly relates to a distributed dynamic excitation testing system and method. Background Technology

[0002] The avionics system, or avionics system for short, is a crucial component of modern helicopters. As the aircraft's "network hub," it handles most of the mission functions, including communication, navigation, and control. Functional testing of the system is an essential part of the avionics system development process. This involves not only checking hardware connections such as equipment interfaces and wiring relationships, but more importantly, verifying the functionality of each device within the system, as well as the data exchange and communication logic between these devices. Currently, static verification methods using key discrete points are often employed, resulting in a small detection coverage area, making dynamic simulation difficult and hindering the achievement of detection over a wider range. Summary of the Invention

[0003] The technical problem that this invention aims to solve is that the static verification method using key discrete points has a small detection area coverage, making it difficult to perform dynamic simulation and unable to achieve detection over a wider range.

[0004] The technical solution of this invention is: Firstly, a distributed dynamic stimulus testing system is provided, the system comprising: The stimulus data source system generates dynamic flight parameters and sends these parameters to the distributed stimulus test system according to a preset cycle. The distributed excitation test system converts dynamic flight parameters into excitation signals and sends them to the avionics system under test. The tested avionics system responds to the excitation signal; The bus monitoring system collects response data from the avionics system under test via the bus, compares the response data with preset data, and determines whether the working status of the avionics system under test meets the requirements.

[0005] The distributed stimulus testing system consists of multiple programmable discrete devices.

[0006] Optionally, the excitation data source system uses human-in-the-loop FlightGear flight simulation software or a custom automatic flight envelope model to generate dynamic flight parameters.

[0007] Optionally, multiple programmable discrete devices are distributed according to the location of their respective test objects in the avionics system under test.

[0008] Optionally, the avionics system under test includes integrated navigation.

[0009] Optionally, dynamic flight parameters include: relative pressure altitude data, flight vacuum speed, flight indicated airspeed, flight latitude and longitude, flight pitch angle, flight roll angle, flight true heading, flight magnetic heading, and flight yaw angle.

[0010] Optionally, the preset period is determined based on the maximum excitation delay of the discrete device in the excitation test system.

[0011] In a second aspect, a distributed dynamic stimulus testing method is provided for use in any of the distributed dynamic stimulus testing systems described in the first aspect, the method comprising: The excitation data source system generates dynamic flight parameters and sends these parameters to the distributed excitation test system according to a preset cycle. The distributed excitation test system converts dynamic flight parameters into excitation signals and sends them to the avionics system under test. The tested avionics system responds to the excitation signal; The bus monitoring system collects response data from the avionics system under test via the bus, compares the response data with preset data, and determines whether the working status of the avionics system under test meets the requirements.

[0012] The beneficial effects of this application are as follows: 1) Systematic dynamic functional testing can be carried out. The system adopts a distributed design, which can be flexibly deployed according to the laboratory environment. It uses a multi-point excitation method to carry out dynamic system-level testing, and the system is highly economical and reliable.

[0013] 2) Beat-based testing This system, based on beat-based testing, has lower requirements for the real-time driving capability of the excitation equipment, thus reducing the environmental requirements for system testing. Furthermore, this method can utilize data from flight simulation software such as FlightGear as the real-time driver, as well as flight parameter records from actual aircraft. Therefore, it can not only verify the solution during the project design phase but also assist in analyzing and reconstructing on-board faults during the flight test support phase. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of a distributed dynamic stimulus testing system; Figure 2 This is a test diagram of an integrated navigation system; Figure 3 This is a test diagram of the atmospheric data system; Figure 4 This is a schematic diagram of a test for a radio navigation system. Detailed Implementation

[0015] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0016] The features and illustrative embodiments of various aspects of the present invention will now be described in detail. Numerous specific details are set forth in the following detailed description to provide a thorough understanding of the invention. However, it will be apparent to those skilled in the art that the invention may be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. The invention is by no means limited to any specific setups and methods set forth below, but covers any improvements, substitutions, and modifications to structures, methods, and devices without departing from the spirit of the invention. Well-known structures and techniques are not shown in the drawings and the following description to avoid unnecessarily obscuring the invention.

[0017] It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other, and the various embodiments can be referenced and cited from each other.

[0018] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments.

[0019] See Figure 1 This application provides a distributed dynamic stimulus testing system, the system comprising: The excitation data source system 3 generates dynamic flight parameters and sends the dynamic flight parameters to the distributed excitation test system 1 according to a preset cycle; Distributed excitation test system 1 converts dynamic flight parameters into excitation signals and sends them to the avionics system under test; The tested avionics system responds to the excitation signal; Bus monitoring system 2 collects response data from the avionics system under test via the bus, compares this response data with preset data, and determines whether the operating status of the avionics system under test meets the requirements. Specifically, if the error between the response data and the preset data is within a certain range, it can be determined that the operating status of the avionics system under test meets the requirements.

[0020] The distributed stimulus test system 1 consists of multiple programmable discrete devices.

[0021] In one embodiment, the excitation data source system 3 uses human-in-the-loop FlightGear flight simulation software or a custom automatic flight envelope model to generate dynamic flight parameters.

[0022] Multiple programmable discrete devices are distributed according to the location of each avionics system under test.

[0023] Dynamic flight parameters include: relative pressure altitude, vacuum speed, indicated airspeed, latitude and longitude, pitch angle, roll angle, true heading, magnetic heading, and yaw angle.

[0024] The preset period is determined based on the maximum excitation delay of the discrete devices in the excitation test system. It is typically 200ms.

[0025] The tested avionics system includes the integrated navigation system, the air data system, and the radio navigation system.

[0026] See Figure 2 For the integrated navigation system, the excitation data source system 3 generates dynamic flight parameters, including flight latitude and longitude, flight pitch angle, flight roll angle, flight true heading, and flight magnetic heading, and sends the dynamic flight parameters to the distributed excitation test system 1 according to a preset period. The distributed excitation test system 1 converts the dynamic flight parameters into motion signals of the three-axis turntable and radio signals of the GPS simulator, triggering the integrated navigation system to work. The integrated navigation system senses the three-axis motion and GPS excitation signals, judges and calculates the changes in parameters such as latitude and longitude, pitch angle, roll angle, and heading angle, and sends the calculated data through the bus. The bus monitoring system 2 collects the calculated data of the integrated navigation system through the bus, compares the data with the preset data of the excitation data source system 3, and judges whether the working status of the integrated navigation system meets the requirements.

[0027] See Figure 3 For the atmospheric data system, the excitation data source system 3 generates dynamic flight parameters, including flight vacuum speed, flight indicated airspeed, and flight relative pressure altitude, and sends the dynamic flight parameters to the distributed excitation test system 1 according to a preset cycle; the distributed excitation test system 1 converts the dynamic flight parameters into dynamic pressure and total pressure excitation signals and sends them to the atmospheric data system; the atmospheric data system senses the external dynamic pressure and total pressure excitation signals, calculates the flight altitude and flight speed, and sends the calculated data through the bus; the bus monitoring system 2 collects the response data of the atmospheric data system through the bus, compares the response data with the preset data of the excitation data source system 3, and determines whether the working status of the atmospheric data system meets the requirements.

[0028] See Figure 4For the radio navigation system, the excitation data source system 3 generates dynamic flight parameters, mainly the flight yaw angle, and sends these dynamic flight parameters to the distributed excitation test system 1 according to a preset period. The distributed excitation test system 1 converts the dynamic flight parameters into radio position deviation excitation signals and sends them to the radio navigation system. The radio navigation system processes the received radio deviation excitation signals, calculates the yaw error for the current period, and sends the calculated data through the bus. The bus monitoring system 2 collects the response data of the radio navigation system through the bus, compares the response data with the preset data of the excitation data source system 3, and determines whether the working status of the tested avionics system meets the requirements.

[0029] An embodiment of the present invention provides a distributed dynamic stimulus testing method for use in Figure 1 The distributed dynamic stimulus testing system shown includes the following method: The excitation data source system 3 generates dynamic flight parameters and sends the dynamic flight parameters to the distributed excitation test system 1 according to a preset period; The distributed excitation test system 1 converts dynamic flight parameters into excitation signals and sends them to the avionics system under test. The tested avionics system responds to the excitation signal; The bus monitoring system 2 collects the response data of the avionics system under test through the bus, compares the response data with the preset data, and determines whether the working status of the avionics system under test meets the requirements.

[0030] The above description merely illustrates embodiments of the present invention and is quite specific and detailed; however, it should not be construed as limiting the scope of the patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these all fall within the scope of protection of the present invention. Furthermore, any parts of the present invention not described in detail are conventional techniques.

Claims

1. A distributed dynamic stimulus testing system, characterized in that, The system includes: The excitation data source system (3) generates dynamic flight parameters and sends the dynamic flight parameters to the distributed excitation test system (1) according to a preset cycle; The distributed excitation test system (1) converts dynamic flight parameters into excitation signals and sends them to the avionics system under test; The tested avionics system responds to the excitation signal; The bus monitoring system (2) collects the response data of the avionics system under test through the bus, compares the response data with the preset data, and judges whether the working status of the avionics system under test meets the requirements.

2. The system as described in claim 1, characterized in that, The distributed stimulus test system (1) consists of multiple programmable discrete devices.

3. The system as described in claim 1, characterized in that, The excitation data source system (3) uses human-in-the-loop FlightGear flight simulation software or a custom automatic flight envelope model to generate dynamic flight parameters.

4. The system as described in claim 2, characterized in that, Multiple programmable discrete devices are distributed according to the location of each avionics system under test.

5. The system as described in claim 2, characterized in that, The tested avionics system includes the integrated navigation system, the air data system, and the radio navigation system.

6. The system as described in claim 1, characterized in that, Dynamic flight parameters include: relative pressure altitude data, vacuum speed, indicated airspeed, latitude and longitude, pitch angle, roll angle, true heading, magnetic heading, and yaw angle.

7. The system as described in claim 1, characterized in that, The preset cycle is determined based on the maximum excitation delay of the discrete devices in the excitation test system.

8. A distributed dynamic stimulus testing method, characterized in that, For the distributed dynamic stimulus testing system according to any one of claims 1 to 7, the method comprises: The excitation data source system (3) generates dynamic flight parameters and sends the dynamic flight parameters to the distributed excitation test system (1) according to a preset cycle; The distributed excitation test system (1) converts dynamic flight parameters into excitation signals and sends them to the avionics system under test; The tested avionics system responds to the excitation signal; The bus monitoring system (2) collects the response data of the avionics system under test through the bus, compares the response data with the preset data, and judges whether the working status of the avionics system under test meets the requirements.

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