Test platform and test method for power flight test of all-electric aircraft and anti-collision device

Abstract

A test platform for an all-electric aircraft power flight test comprises a test platform for verifying the function, the performance, the consistency and the safety of airborne equipment according to the function and performance requirements of an all-electric aircraft, the airborne equipment can be protected during rollover of the all-electric aircraft power flight test, and the safety of the airborne equipment is improved. The propeller is prevented from hitting the ground to damage the blades. The technical scheme provided by the invention has a high-reliability reinforcing mechanism, expandability and design of anti-collision measures, reduces equipment loss, improves safety and reliability in testing, comprehensively considers design tests of single and multiple systems, and realizes optimal resource configuration.

Description

Technical Field

[0001] The present invention relates to the field of aircraft, and in particular to an aircraft with an H-configuration and rotary wings for realizing vertical take-off and landing. Background Art

[0002] The current all-electric flight platform cannot realize test verification in various scenarios. In various postures of flight tests, propellers and motors are prone to damage, and repeatable, damage-free flight test verification cannot be achieved. It is difficult to reproduce faults in flight tests and conduct complete flight test verification. Summary of the invention

[0003] The present invention aims to solve the technical problems existing in the prior art. In order to verify that the functions and performance of the powered flight system of an all-electric aircraft meet the requirements of the all-electric flight of the aircraft, based on the needs of all-electric aircraft flight experimental verification, a test platform, experimental method and anti-collision device for all-electric aircraft powered flight testing are invented, which can solve the problems that the existing all-electric aircraft powered flight test platform cannot realize repeatable and non-destructive flight testing.

[0004] The technical solutions adopted are as follows:

[0005] According to one aspect of the present invention, a test verification platform, a test verification method and an anti-collision device for all-electric aircraft powered flight testing are proposed, comprising the following steps:

[0006] In response to the functional and performance requirements of all-electric aircraft, the test platform is used to verify the functions, performance, consistency and safety of airborne equipment. When the all-electric aircraft rolls over during powered flight testing, it can protect the airborne equipment and prevent the propeller from hitting the ground and causing damage to the blades.

[0007] Furthermore, the test configuration is similar to the real configuration of the aircraft. In this experiment, the motors that provide powered flight are located in the same position as the motors of the all-electric aircraft.

[0008] Verify that the system's functions meet the design requirements, verify that the system's dynamic and static performance meet the design requirements, verify the system's fault monitoring / isolation / alarm functions, and verify the correctness of the interface between the system and other systems.

[0009] According to the overall planning and requirements of the aircraft verification test, the design planning and configuration of the test platform are optimized based on the feasibility of the site and test:

[0010] Furthermore, the test platform uses the method of bundling heavy objects to verify whether the static performance of the system meets the design requirements, verify the system's fault monitoring / isolation / alarm functions, and verify the correctness of the interface between the system and other systems.

[0011] Furthermore, when verifying the indoor flight status and flight mode simulation test, the test platform adopts the protection measures of suspension hoisting to complete fully autonomous takeoff, hovering and landing, dynamically check the aircraft system interaction logic, the aircraft system and flight control logic interface, and the logic between systems under fault conditions, verify whether the design of the whole aircraft warning system is reasonable, expose the internal defects of the coordinated work of the aircraft system, and improve the maturity of the aircraft system design and integration.

[0012] Furthermore, the suspension device is installed based on various flight attitudes and the anti-collision protection measures in the Y and Z directions are designed to avoid damage to equipment such as motors or propellers. The X direction can buffer the impact of descent in sudden situations to prevent the aircraft arm from directly touching the ground. The length of the anti-collision protection rod in the Y and Z directions is greater than the radius of the propeller blade. During the dynamic test flight with large angles and flip attitude verification tests, the Y and Z direction protection rods can land first in the event of a fault, playing a role of buffering protection.

[0013] Furthermore, since new test verification requirements may arise as problems are encountered during the aircraft development process, full consideration is given to expanding test functions when planning the test platform. Various verification platforms and functional extensions can be built in the middle of the test verification platform. The dynamic response and flight verification of the four motors during all-electric flight are considered to ensure the overall structural stress, torque and safety. The central platform adopts a double-layer structural reinforcement, and the corresponding support structure can be added according to the stress simulation conditions.

[0014] Furthermore, it can support flight tests, reproduce faults and troubleshoot.

[0015] The technical effects achieved by the present invention are as follows:

[0016] Based on the requirements of all-electric aircraft flight tests, combined with dynamic and static test requirements, single and multi-system integration verification, and test requirements and requirements in different environments, a test verification platform, test verification method, and anti-collision measures for all-electric aircraft power flight tests were invented. Considering the actual flight configuration, the motor position and landing structure were designed and planned, and the funds, equipment, and venues for the test were optimized. The design of high-reliability reinforcement mechanisms, scalability, and anti-collision measures reduces equipment losses, improves safety and reliability during testing, and comprehensively considers the design tests of single and multi-systems to achieve optimal resource allocation. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 The present invention is a schematic diagram of an embodiment of a test verification platform, a test verification method and an anti-collision measure for a powered flight test of an all-electric aircraft. DETAILED DESCRIPTION

[0018] The technical solution of the present invention is described in detail below. The embodiments of the present invention are only for illustrating the specific structure, and the scale of the structure is not limited by the embodiments. A test verification platform, experimental method and anti-collision device for all-electric aircraft powered flight test Figure 1 As shown, the test platform has the following components, including: a test platform body 1, a flight control 2, a power supply 3, a motor 4, and a protection rod 5.

[0019] Test platform body 1: The test platform configuration is close to the real configuration of the aircraft, and the position of motor 4 is consistent with that of the all-electric aircraft. The platform can perform dynamic and static tests on the interface logic of the system on its plane to verify the system function and design. Various verification platforms and functional extensions can be built in the middle of the platform, and the dynamic response and flight verification of the four motors during the all-electric flight are considered to ensure the overall structural stress, torque and safety. The central platform adopts a double-layer structure reinforcement, and the corresponding support structure can be added according to the stress simulation.

[0020] The X-direction design of the protection bar 5 can buffer the impact of descent in unexpected situations and prevent the aircraft arm from directly touching the ground. The length of the anti-collision protection bar designed in the Y and Z directions is greater than the radius of the propeller blade. During dynamic flight test with large angles and flip attitude verification tests, the Y and Z direction protection bars can land first in the event of a fault, playing a role of buffering protection.

[0021] Therefore, the present invention can be used for flight tests under different attitude conditions, can reproduce and troubleshoot aircraft flight failures, reduce equipment losses during the research and development process of the aircraft, and improve the safety and reliability of the test.

Claims

1. A test platform for all-electric aircraft powered flight testing, characterized by It includes a test platform for verifying the functions, performance, consistency and safety of airborne equipment in response to the functional and performance requirements of all-electric aircraft. It can protect the airborne equipment when the all-electric aircraft rolls over during powered flight testing and prevent the propeller from hitting the ground and causing damage to the blades.

2. The test platform for all-electric aircraft powered flight test according to claim 1 is characterized by: The test configuration is similar to the real configuration of the aircraft, and the motors that provide powered flight are located in the same position as the motors of an all-electric aircraft.

3. The test platform for all-electric aircraft powered flight test according to claim 1 is characterized by: According to the overall planning and requirements of the aircraft verification test, the design planning and configuration of the test platform are optimized based on the feasibility of the site and test.

4. The test platform for all-electric aircraft powered flight test according to claim 1 is characterized by: The test platform uses the method of bundling heavy objects to verify whether the static performance of the system meets the design requirements.

5. The test platform for all-electric aircraft powered flight test according to claim 4 is characterized by: The test platform uses the method of bundling heavy objects to verify the system's fault monitoring / isolation / alarm functions and verify the correctness of the interface between the system and other systems.

6. The test platform for all-electric aircraft powered flight test according to claim 1 is characterized by: When the test platform verifies the indoor flight status and flight mode simulation test, it adopts suspension and hoisting protection measures to complete fully autonomous take-off, hovering and landing.

7. The test platform for all-electric aircraft powered flight test according to claim 6 is characterized by: When verifying the indoor flight status and flight mode simulation test, the test platform also dynamically checks the aircraft system interaction logic, the aircraft system and flight control logic interface, and the logic between systems under fault conditions, verifies whether the design of the entire aircraft warning system is reasonable, exposes internal defects in the coordinated work of the aircraft system, and improves the maturity of the aircraft system design and integration.

8. The test platform for all-electric aircraft powered flight test according to claim 1 is characterized by: The suspension device is installed based on various flight attitudes and the anti-collision protection measures in the Y and Z directions are designed to avoid damage to equipment such as motors or propellers. The length of the anti-collision protection rod in the Y and Z directions is greater than the radius of the propeller blade.

9. The test platform for all-electric aircraft powered flight test according to claim 1, characterized in that Various verification platforms and functional extensions can be built in the middle of the test verification platform, and the dynamic response and flight verification of the four motors during all-electric flight are taken into consideration to ensure the overall structural stress, torque and safety. The central platform adopts a double-layer structure reinforcement, and the corresponding support structure can be added according to the stress simulation conditions.

10. An experimental method for powered flight testing of an all-electric aircraft, characterized in that It comprises the test platform for powered flight testing of all-electric aircraft as described in claim 1.

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