Integrated test platform for electric vertical take-off and landing aircraft
By designing an integrated testing platform, the problems of low efficiency and difficulty in intuitively displaying risks in the testing of flight control systems for electric vertical takeoff and landing aircraft were solved, achieving efficient and safe testing and cost savings.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-02-21
- Publication Date
- 2026-04-14
AI Technical Summary
Existing testing platforms cannot efficiently test the flight control systems of electric vertical takeoff and landing aircraft, especially under fault conditions and extreme conditions. The testing process is cumbersome and costly, and it is not possible to intuitively understand the flight risks.
An integrated test platform for electric vertical takeoff and landing aircraft was designed, which includes a ground station system, a host computer operating system, a cabinet and a test bench. It is equipped with a multi-functional display screen and casters, supports switching between real and dummy components, and integrates a simulation excitation and acquisition system to achieve efficient testing and intuitive risk display.
It improved testing efficiency, reduced the cost of real-aircraft testing, shortened the development cycle, and ensured flight safety and testing integration.
Smart Images
Figure CN224117530U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of vertical takeoff and landing aircraft technology, specifically to an integrated test platform for electric vertical takeoff and landing aircraft. Background Technology
[0002] With the country's vigorous development of the low-altitude economy, eVTOL (electric vertical takeoff and landing aircraft) has also become a hot topic. However, at present, integrated test platforms are mainly used in the new energy vehicle industry, and there are no detailed reference cases in the eVTOL industry. In order to improve the safety of the aircraft and reduce the testing cost on the actual aircraft, it is particularly important to conduct comprehensive testing of the flight control system, especially the testing under fault conditions and extreme conditions.
[0003] Existing testing platforms may not be able to efficiently test all low-voltage devices connected to the flight control computer. The testing process requires multiple steps, and test data is difficult to process centrally, resulting in a lengthy and cumbersome testing process. At the same time, because the simulated flight of the aircraft model cannot be clearly seen during testing, users cannot gain a more detailed understanding of the risks that the aircraft may face during flight, and cannot guarantee safety during flight. This leads users to need to conduct frequent tests to verify the performance and safety of the aircraft, which not only prolongs the testing time but also increases the development cost. Utility Model Content
[0004] The purpose of this invention is to provide an integrated test platform for electric vertical takeoff and landing aircraft, which has the advantage of high testing efficiency and solves the problems mentioned in the background art.
[0005] To achieve the above objectives, this utility model provides the following technical solution: an integrated test platform for electric vertical takeoff and landing aircraft, comprising a ground station system, a host computer operating system, a cabinet, and a test stand for placing various avionics equipment. The ground station includes three displays and a power-on / off unlocking device. The three displays of the ground station are the main flight display interface, the multi-function display interface, and the navigation display interface. The power-on / off unlocking device is located to the right of the navigation display. The host computer operating system is located to the right of the ground station. The cabinet, containing a simulation excitation and acquisition system, is located to the right of the host computer. The test stand is located to the right of the cabinet.
[0006] Furthermore, as a preferred embodiment of this utility model, each of the four corners of the bottom of the cabinet is fixedly connected with a caster wheel, and the four caster wheels are arranged symmetrically.
[0007] Furthermore, as a preferred embodiment of this utility model, the inner cavity of the cabinet is provided with a low-voltage equipment circuit breaker, and the number of the low-voltage equipment circuit breakers is several.
[0008] Furthermore, as a preferred embodiment of this utility model, the inner cavity of the cabinet is provided with a dummy component control path, and the surface of the dummy component control path is electrically connected to a real component control path.
[0009] Furthermore, as a preferred embodiment of this utility model, the low-voltage equipment circuit breaker is located above the dummy component control path and the real component control path, and is separated by a baffle.
[0010] Beneficial effects: The technical solution of this application has the following technical effects: This utility model has the advantages of high testing efficiency and high integration in actual use; it can test all low-voltage devices connected to the flight control computer at the same time, which improves testing efficiency; the potential risks of the aircraft model in simulated flight can be intuitively discovered on the display screen of the ground station; it can reduce the cost of real aircraft flight testing, save testing time, shorten the aircraft development cycle, and ensure flight safety.
[0011] It should be understood that all combinations of the foregoing concepts and the additional concepts described in more detail below can be considered as part of the utility model subject matter of this disclosure, provided that such concepts do not contradict each other. Attached Figure Description
[0012] The accompanying drawings are provided to further illustrate the present invention and form part of the specification. They are used together with the embodiments of the present invention to explain the present invention, but do not constitute a limitation thereof. In the drawings:
[0013] Figure 1 This is a three-dimensional structural diagram of the present invention;
[0014] Figure 2 This is a schematic diagram of the cabinet of this utility model. Detailed Implementation
[0015] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings. To better understand the technical content of the present utility model, specific embodiments are provided and described in conjunction with the accompanying drawings. Various aspects of the present utility model are described in this disclosure with reference to the accompanying drawings, which show many illustrative embodiments. It should be understood that the various concepts and embodiments described above, as well as those described in more detail below, can be implemented in any of many ways. All other embodiments obtained by those skilled in the art based on the embodiments of the present utility model without creative effort are within the scope of protection of the present utility model.
[0016] As attached Figure 1 Appendix Figure 2As shown: This embodiment provides an integrated test platform for an electric vertical takeoff and landing (eVTOL) aircraft, including a ground station. The ground station is equipped with three displays: a main flight display interface 1, a multi-function display interface 2, and a navigation display interface 3. A power-on / off unlocking device 4 is located on the right side of the navigation display interface 3. The right side of the ground station houses the host computer operating system, which has two operating interfaces: host computer 1 5 and host computer 2 6. The host computer operating system is responsible for deploying simulation control software, providing software operation interfaces and configuration file management, and controlling simulation equipment via an Ethernet interface. To the right of host computers 1 5 and 2 6 is a cabinet 7, which contains a simulation excitation and acquisition system. The system outputs control signals for internal functional modules based on the simulation model's operating results. A signal conditioning device conditions various signals according to the characteristics of the input and output signals. The cabinet 7 is connected to the flight control computer on its right-hand platform 8 via a cable.
[0017] Specifically, each of the four corners of the bottom of cabinet 7 is fixedly connected with a caster wheel, and the four caster wheels are arranged symmetrically.
[0018] Specifically, the inner cavity of the cabinet 7 is equipped with a low-voltage equipment circuit breaker 9, and the number of low-voltage equipment circuit breakers 9 is several.
[0019] Specifically, the inner cavity of the cabinet 7 is provided with a dummy control path 10, and the surface of the dummy control path 10 is electrically connected to the real control path 11.
[0020] Specifically, the low-voltage equipment circuit breaker 9 is located above the dummy control path 10 and the real control path 11, and is separated by a baffle.
[0021] During testing, this utility model can switch between real and dummy components. When only interface testing or HIL testing is performed, the dummy component control path 10 of cabinet 7 needs to be connected using a disconnect block. When performing low-voltage equipment physical interface testing, the real component control path 11 of cabinet 7 needs to be connected using a disconnect block, and the corresponding low-voltage equipment circuit breaker 9 needs to be pressed.
[0022] The working principle and usage process of this utility model are as follows: the actual flight control computer is connected to the virtual controlled object constructed in the host computer for testing, and the simulated flight results are displayed through various interfaces of the ground station.
[0023] The user first turns on the power supply of cabinet 7 and the simulation test environment of host computer 5, then presses the power-on / off unlocking device 4 button of the ground station, the indicator light lights up, then controls the corresponding unlocking signal of the host computer software, and finally operates the remote control to observe the equipment status and the simulated flight status of the aircraft on each display interface of the ground station.
[0024] It should be noted that in this document, relational terms such as first and second are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations.
[0025] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Those skilled in the art to which this invention pertains can make various modifications and refinements without departing from the spirit and scope of the present invention. Therefore, the scope of protection of this invention shall be determined by the claims.
Claims
1. An electric vertical take-off and landing aircraft integrated test platform comprising a ground station, characterized in that: The ground station is equipped with three display screens, which are the main flight display interface (1), the multifunctional display interface (2), and the navigation display interface (3), the right side of the navigation display interface (3) is provided with up and down electrical unlocking devices (4), the right side of the ground station is the upper computer operating system, which is provided with two operation interfaces, which are No. 1 upper computer (5) and No. 2 upper computer (6), the right side of the No. 1 upper computer (5) and the No. 2 upper computer (6) is placed with the cabinet (7), the cabinet (7) contains the simulation excitation and acquisition system, the system outputs the function module control signal in the machine according to the simulation model operation result, the signal conditioning device regulates various signals according to the input and output signal characteristics, and the cabinet (7) is connected with the flight control computer on the rack (8) on the right side thereof through a cable.
2. The integrated test platform for an electric vertical take-off and landing aircraft of claim 1, wherein: Universal wheels are fixedly connected to the four corners of the bottom of the cabinet (7), and the four universal wheels are symmetrically arranged.
3. The integrated test platform for an electric vertical take-off and landing aircraft of claim 1, wherein: A low-voltage equipment circuit breaker (9) is arranged in the inner cavity of the cabinet (7).
4. The integrated test platform for an electric vertical take-off and landing aircraft of claim 3, wherein: A false part control channel (10) is arranged in the inner cavity of the cabinet (7), and a true part control channel (11) is electrically connected to the surface of the false part control channel (10).
5. The integrated test platform for an electric vertical take-off and landing aircraft of claim 4, wherein: The low-voltage equipment circuit breaker (9) is located above the false part control channel (10) and the true part control channel (11) and is separated by a baffle.