Comprehensive avionics test bench for electric vertical take-off and landing multi-rotor aircraft

Abstract

The invention relates to the technical field of aircraft testing, in particular to a comprehensive avionics test bench for an electric vertical take-off and landing multi-rotor aircraft. Comprising a base, a support, a test platform, an arm test module and an upper computer. The base is connected with the bottom of the bracket; the top of the bracket is connected with the test platform; the arm test module is connected with the test platform; the base is used for fixing the test bench; the support is used for supporting the testing platform. The test platform and the arm test module are used for testing avionics of the aircraft; the upper computer is used for controlling the test mode of the test bench. According to the invention, modular design is adopted, disassembly and assembly can be realized, expansion can be realized, a group of motor assemblies can be tested, multiple groups of motor assemblies can be tested, a whole machine can be tested, power can be supplied by using a battery, an external power supply can be used, remote control and wire control can be realized, and various test requirements can be realized.

Description

Technical Field

[0001] This invention relates to the field of aircraft testing technology, and in particular to an integrated avionics test bench for electric vertical takeoff and landing multirotor aircraft. Background Technology

[0002] In recent years, with the development of the low-altitude economy, electric vertical takeoff and landing (eVTOL) multirotor aircraft have gradually become a research hotspot for urban low-altitude aircraft. The product development process involves numerous tests, requiring specialized testing equipment and test benches, such as motor power test benches and vibration test benches. Extensive space or airspace is needed for flight testing. Therefore, the testing cycle is long and costly, and accidents during testing can have extremely high consequences. Consequently, higher demands are placed on testing methods and facilities, requiring a universal and scalable test bench to perform more tests, reduce costs, shorten testing cycles, and improve safety. Pre-testing the aircraft's structure, motors, systems, and subsystems on a ground-based test bench ensures that relevant data can be verified before actual flight testing to guarantee the aircraft's performance, safety, and reliability. It can also serve as an indicator test for certain performance parameters and aging tests. However, currently, there is no indoor simulation testing equipment for multi-mission performance testing of eVTOL multirotor aircraft. Summary of the Invention

[0003] This invention aims to at least solve one of the technical problems existing in related technologies. To this end, this invention provides an integrated avionics test bench for electric vertical takeoff and landing (eVTOL) multirotor aircraft. It is detachable and assembleable, expandable, and can test one set of motor components, multiple sets of motor components, or the entire aircraft. It can be powered by batteries or an external power source, and can be remotely controlled or wired controlled, fulfilling various testing needs.

[0004] This invention provides an integrated avionics test bench for an electric vertical takeoff and landing multirotor aircraft, comprising: a base, a support, a test platform, an arm test module, and a host computer; The base and the bottom of the bracket are connected; The top of the bracket is connected to the test platform; The robotic arm testing module is connected to the testing platform; The base is used to fix the test bench; The bracket is used to support the test platform; The test platform and arm test module are used to test the avionics of the aircraft. The host computer is used to control the test mode of the test bench.

[0005] According to the present invention, a comprehensive avionics test bench for an electric vertical takeoff and landing multirotor aircraft is provided, wherein the base further includes a counterweight and fixing bolts; The counterweight is installed above the base; The fixing bolts are installed above the base; The counterweight is installed inside the fixing bolt; The counterweight is used to fix the test bench and prevent it from shaking. The fixing bolts are used to secure the test bench and prevent it from shaking.

[0006] According to the present invention, an integrated avionics test bench for an electric vertical takeoff and landing multirotor aircraft is provided, wherein the support is a truss structure.

[0007] According to the present invention, an integrated avionics test bench for an electric vertical takeoff and landing multirotor aircraft is provided. The test platform includes a first tensile and compressive sensor group, a second tensile and compressive sensor group, a test truss, a torque sensor, a flange, a mounting plate, and a vertical beam. The first tension / compression sensor group is installed below the mounting plate; The first tension / compression sensor group is connected to the bracket; The second tensile and compressive sensor group, the test truss, the torque sensor, and the upright beam are mounted above the mounting plate; The second tensile and compressive sensor group is connected to the test truss; One end of the test truss is connected to the vertical beam; The other end of the test truss is connected to the flange; The vertical beam is used to support the truss; The flange is used to connect the robotic arm testing module.

[0008] According to the present invention, an integrated avionics test bench for an electric vertical takeoff and landing multirotor aircraft is provided. When performing single-axis power testing, the test platform further includes a limiting frame, which is connected to the tail end of the truss. The limiting frame is used to reduce the sway of the truss.

[0009] According to the present invention, an integrated avionics test bench for an electric vertical takeoff and landing multirotor aircraft is provided. When performing multi-axis power testing, the test platform further includes a hinge support for connecting two adjacent trusses and for reducing truss sway.

[0010] According to the present invention, an integrated avionics test bench for an electric vertical takeoff and landing multirotor aircraft is provided, wherein the arm test module includes a mating flange, an arm, a torque sensor, a motor, and a propeller; The mating flange is connected to the test platform; The arm is connected to the mating flange; The torque sensor is connected to the robotic arm; The motor is connected to the machine arm; The motor and the propeller are connected; The arms and propellers are used to simulate an aircraft; The motor is used for power supply.

[0011] According to the present invention, an integrated avionics test bench for an electric vertical takeoff and landing multirotor aircraft further includes a battery pack connected to the test platform, the battery pack being used for power supply.

[0012] According to the present invention, an integrated avionics test bench for an electric vertical takeoff and landing multirotor aircraft is provided, wherein the support is a square tube support and the height of the support is greater than or equal to 3 meters.

[0013] According to the present invention, a comprehensive avionics test bench for an electric vertical takeoff and landing multirotor aircraft is provided, wherein the test modes include: single-axis or multi-axis power test, full-weight power test, flight control vibration test, flight control electromagnetic interference test, flight control electronic adjustment and connection, flight control BMS connection test, aging test, and energy management test.

[0014] The above-described one or more technical solutions in the embodiments of the present invention have at least one of the following technical effects: This invention provides an integrated avionics test bench for electric vertical takeoff and landing (eVTOL) multirotor aircraft. It features a modular design, allowing for disassembly and assembly, and is expandable. It can test one or more motor assemblies, or perform complete aircraft testing. It can be powered by batteries or an external power source, and can be remotely controlled or wired controlled. The bench utilizes a tubular frame structure, enabling quick and robust assembly and easy expansion and modification to add functions such as arm loading. The bottom has bolts for fixing to a concrete floor and provides space for counterweights. A platform is mounted on top of the tubular frame structure, at least 3 meters above the ground to minimize the impact of propeller downwash. A central chassis houses the necessary electronic equipment. Mounting holes can be pre-drilled or subsequently machined on the platform for mounting batteries and other accessories of different structures. The platform also features flange interfaces for connecting power arms and motor assemblies of different structures.

[0015] Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in this invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0017] Figure 1 This is an isometric view of the test bench of the present invention.

[0018] Figure 2 This is a schematic diagram of the single-axis dynamic test of the present invention.

[0019] Figure 3 This is a schematic diagram of the multi-axis dynamic test of the present invention.

[0020] Figure Labels 1. Counterweight; 2. Bolt; 3. Base; 4. Bracket; 5. First tension / compression sensor group; 6. Mounting plate; 7. Second tension / compression sensor group; 8. Flange; 9. First torque sensor group; 10. Test truss; 11. Chassis; 12. Hinge support; 13. Motor; 14. Second torque sensor group; 15. Arm; 16. Pairing flange; 17. Limiting frame; 18. Vertical beam; 19. Battery pack; 20. Propeller. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of this invention will be clearly and completely described below. Obviously, the described embodiments are only some, not all, of the embodiments of this invention. Based on the embodiments of this invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this invention. The following embodiments are used to illustrate this invention but cannot be used to limit the scope of this invention.

[0022] In the description of the embodiments of the present invention, it should be noted that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the embodiments of the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the embodiments of the present invention. In addition, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0023] In the description of the embodiments of the present invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "connected" and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in the embodiments of the present invention based on the specific circumstances.

[0024] In embodiments of the present invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0025] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0026] The following is combined Figures 1 to 3 This invention is described.

[0027] Example like Figure 1 As shown, Figure 1 This is an isometric view of the test bench of the present invention. It includes: a base 3, a support 4, a test platform, a test arm 15, a test module, and a host computer; The bottoms of the base 3 and the bracket 4 are connected; The top of the bracket 4 is connected to the test platform; The test module of the robotic arm 15 is connected to the test platform; The base 3 is used to fix the test bench; The bracket 4 is used to support the test platform; The test platform and arm 15 test module are used to test the avionics of the aircraft. The host computer is used to control the test mode of the test bench.

[0028] Specifically, the base 3 also includes a counterweight 1 and a fixing bolt 2; The counterweight 1 is installed above the base 3; The fixing bolt 2 is installed above the base 3; The counterweight 1 is installed inside the fixing bolt 2; The counterweight 1 is used to fix the test bench and prevent the test bench from shaking. The fixing bolt 2 is used to fix the test stand and prevent the test stand from shaking.

[0029] Specifically, the support 4 is a truss structure.

[0030] Specifically, the test platform includes a first tensile and compressive sensor group 5, a second tensile and compressive sensor group 7, a test truss 10, a first torque sensor group 9, a flange 8, a mounting plate 6, and a vertical beam 18; The first tension / compression sensor group 5 is installed below the mounting plate 6; The first tension / compression sensor group 5 is connected to the bracket 4; The second tensile and compressive sensor group 7, the test truss 10, the first torque sensor group 9, and the upright beam 18 are mounted above the mounting plate 6. The second tensile and compressive sensor group 7 is connected to the test truss 10; One end of the test truss 10 is connected to the vertical beam 18; The other end of the test truss 10 is connected to the flange 8; The first torque sensor group 9 is connected to the flange 8; The vertical beam 18 is used to support the truss; The flange 8 is used to connect the test module of the machine arm 15.

[0031] The mounting plate 6 has a chassis 11 at its center for housing the required electronic equipment.

[0032] Specifically, such as Figure 2 As shown, when performing single-axis dynamic testing, the test platform also includes a limiting frame 17, which is connected to the tail end of the truss and is used to reduce the sway of the truss.

[0033] Specifically, such as Figure 3 As shown, when performing multi-axis dynamic tests, the test platform also includes a hinge support 12, which is used to connect two adjacent trusses and to reduce truss sway.

[0034] Specifically, the arm 15 test module includes a mating flange 16, an arm 15, a second torque sensor group 14, a motor 13, and a propeller 20; The mating flange 16 is connected to the test platform; The arm 15 is connected to the mating flange 16; The second torque sensor group 14 is connected to the arm 15; The motor 13 is connected to the arm 15; The motor 13 is connected to the propeller 20; The arm 15 and propeller 20 are used to simulate an aircraft; The motor 13 is used for power supply.

[0035] Specifically, it also includes a battery pack 19, which is connected to the test platform and is used for power supply.

[0036] This invention provides an integrated avionics test bench for electric vertical takeoff and landing (eVTOL) multirotor aircraft. It features a modular design, allowing for disassembly and assembly, and is expandable. It can test one or more motor assemblies, or perform complete aircraft testing. It can be powered by batteries or an external power source, and can be remotely controlled or wired controlled. The bench utilizes a tubular frame structure, enabling quick and robust assembly and easy expansion and modification to add functions such as arm loading. The bottom has bolts for fixing to a concrete floor and provides space for counterweights. A platform is mounted on top of the tubular frame structure, at least 3 meters above the ground to minimize the impact of propeller downwash. A central chassis houses the necessary electronic equipment. Mounting holes can be pre-drilled or subsequently machined on the platform for mounting batteries and other accessories of different structures. The platform also features flange interfaces for connecting power arms and motor assemblies of different structures.

[0037] Specifically, the test modes include: single-axis or multi-axis power test, full-weight power test, flight control vibration test, flight control electromagnetic interference test, flight control electronic adjustment and connection, flight control BMS connection test, aging test, and energy management test.

[0038] Specifically, the single-axis power test involves installing a second torque sensor group 14 between the motor 13 and the boom 15 to verify the power system's compatibility: checking whether the combination of the motor, ESC, propeller 20, and battery can provide the expected thrust, current, and voltage, ensuring there are no abnormalities such as overload or overheating. A single boom assembly, including the combination of the motor, ESC, propeller 20, and battery, is tested. Before testing, the motor mounting device must be checked to prevent it from falling off at high speeds, and a protective net must be installed around the test bench. Two limit brackets 17 restrict the lateral movement of the test truss 10; they are not connected or fixed, allowing the test truss 10 to slide up and down along the limit brackets 17. The boom 15 and the test truss 10 are connected as one unit via a set of flanges 8 and mating flanges 16. When motor 13 starts, the rotating propeller provides upward lift and pulls the boom 15 upward, creating a rotational tendency centered on the shoulder bolt. Simultaneously, the tension / compression sensor connected to boom 15 experiences tension. Since the deformation of the tension / compression sensor is extremely small and negligible, the direction of the propeller-generated tension can be considered perpendicular to the mounting platform. The torque sensor measures the motor torque, and the tension / compression sensor measures the motor tension. Speed, current / voltage can be directly measured using a tachometer and a wattmeter.

[0039] The test involved gradually increasing the throttle by 5% increments at different throttle openings, testing three modes: from low throttle to high throttle, stable throttle, and rapid throttle reduction. During this process, the stability of the structure could be preliminarily assessed by observing whether there was significant vibration or bending in the motor 13 and the arm 15. If instability was detected, the test was stopped and the structure needed to be redesigned.

[0040] Verify whether the performance parameters of the power motor, such as tension, speed, current, voltage, and torque, meet the design requirements, evaluate its stability, efficiency, and dynamic response capabilities, and provide data support for the overall design and flight control design.

[0041] Basic performance testing included measuring the motor's speed, thrust, torque, current, and voltage at different throttle openings. The throttle was controlled from 0, increasing in 5% increments up to 100%, and the steady-state motor speed, thrust, torque, current, and voltage were recorded.

[0042] Dynamic response test: Tests the dynamic response performance of the motor at different speed ranges.

[0043] Set the throttle to increase suddenly from 10% to 50%, and record the response time of the motor to reach the target speed.

[0044] Set the throttle to suddenly increase from 50% to 90%, and record the response time of the motor to reach the target speed.

[0045] Set the throttle to increase suddenly from 10% to 90%, and record the response time of the motor to reach the target speed.

[0046] Set the throttle to suddenly decrease from 50% to 10%, and record the response time of the motor to reach the target speed.

[0047] Set the throttle to suddenly decrease from 90% to 50%, and record the response time of the motor to reach the target speed.

[0048] Set the throttle to suddenly decrease from 90% to 10%, and record the response time of the motor to reach the target speed.

[0049] Environmental adaptability testing measures the temperature and stability of the motor during long-term operation.

[0050] Set the throttle to 50%, let the motor work stably for 10 minutes, and record the motor temperature and current.

[0051] Set the throttle to 80%, let the motor work stably for 1 minute, and record the motor temperature and current.

[0052] Finally, the data was organized into tables and charts, and thrust-related data were analyzed.

[0053] To verify whether the overall performance of the power system meets the requirements for safe flight under the maximum design takeoff weight.

[0054] The test included all power arm components, including the combination of motor, ESC, propeller and battery, with the battery fully charged.

[0055] Before testing, the motor fixing device must be checked to prevent it from falling off at high speeds, and a protective net must be set up around the test bench.

[0056] Specifically, the full-weight dynamic test simulates the entire process from hovering to maximum thrust. After all motors start, four tension and compression sensors at the bottom of the mounting platform transmit tension and compression data in real time, accurately measuring the total tension. The testing method is a gradual thrust loading test: First, set up test points. The steps are as follows: throttle from the estimated hovering point to 100% throttle, and divide each 10% interval into a test point.

[0057] Point-by-point testing and data recording: Stabilize the throttle at the first test point. Maintain this stability for approximately 30 seconds to allow the system to reach thermal equilibrium.

[0058] During the stabilization phase, the following data are recorded simultaneously: total tension, total current, total voltage, total power, and the temperatures of each motor, ESC, and power supply.

[0059] After completing the recording, push the throttle to the next test point and repeat the above process.

[0060] Reaching the full-weight test point: When the tension and compression data transmitted by the four tension and compression sensors show that the total tension equals the aircraft's full weight, record the throttle percentage and power at this point. This represents the theoretical hovering point.

[0061] Reaching maximum power: Record the maximum pulling force and maximum power at 100% throttle. For continuous full-load testing, maintain the throttle at 100% for at least 2 minutes.

[0062] During this stage, the temperature is closely monitored to observe whether the temperature of the motor and ESC will rise to a dangerous level, and at the same time, the sound of the power system is listened for any abnormal changes.

[0063] In the final stage, the throttle is slowly reduced to zero, and the power system and structural components are inspected. The recorded data is then compiled into charts for analysis.

[0064] Specifically, the core purpose of flight control vibration testing is to verify whether the flight control system can function normally under vibration conditions in a real flight environment.

[0065] Detecting resonances and identifying resonance frequencies provides a reference for avoiding the excitation of resonances.

[0066] The primary source of vibration on the aircraft is the unbalanced rotation of the motors and propellers. Similar to the full-weight power test, the test includes all power arm components, comprising a combination of motors, ESCs, propellers, and a fully charged battery.

[0067] The throttle was controlled from 0, increasing in increments of 5% to 100%, with each 10% increment serving as a test point. Each test point remains stable for approximately 10 seconds, and four tension and compression sensors installed below the mounting platform record the data at each test point. Vibration data will generate different data types under different conditions of resonance and non-resonance. Finally, the recorded data will be organized into charts for analysis.

[0068] Specifically, flight control electromagnetic interference (EMI) testing is a crucial system-level test designed to ensure that various electronic devices on the aircraft can coexist harmoniously in complex electromagnetic environments without performance degradation or malfunction. This test bench can perform static tests, simulating a portion of the power system by powering one ESC and motor while keeping the throttle at its lowest position (motor not rotating), and full power system tests, powering all ESCs and motors and allowing them to idle at low speeds. It can also simulate EMI testing under dynamic flight conditions, including hovering and high-speed flight.

[0069] Specifically, the present invention can also perform flight control electronic adjustment and integration tests, flight control BMS integration tests, aging tests, energy management tests, and some electromagnetic interference tests when propellers are loaded.

[0070] While this disclosure has been described with reference to several specific embodiments, it should be understood that this disclosure is not limited to the specific embodiments disclosed. This disclosure is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.

Claims

1. A comprehensive avionics test bench for an electric vertical takeoff and landing multirotor aircraft, characterized in that, include: Base, bracket, test platform, robotic arm test module, and host computer; The base and the bottom of the bracket are connected; The top of the bracket is connected to the test platform; The robotic arm testing module is connected to the testing platform; The base is used to fix the test bench; The bracket is used to support the test platform; The test platform and arm test module are used to test the avionics of the aircraft. The host computer is used to control the test mode of the test bench.

2. The integrated avionics test bench for an electric vertical takeoff and landing multirotor aircraft according to claim 1, characterized in that, The base also includes a counterweight and fixing bolts; The counterweight is installed above the base; The fixing bolts are installed above the base; The counterweight is installed inside the fixing bolt; The counterweight is used to fix the test bench and prevent it from shaking. The fixing bolts are used to secure the test bench and prevent it from shaking.

3. The integrated avionics test bench for an electric vertical takeoff and landing multirotor aircraft according to claim 1, characterized in that, The support structure is a truss structure.

4. The integrated avionics test bench for an electric vertical takeoff and landing multirotor aircraft according to claim 1, characterized in that, The test platform includes a first tensile and compressive sensor group, a second tensile and compressive sensor group, a test truss, a first torque sensor group, a flange, a mounting plate, and a vertical beam; The first tension / compression sensor group is installed below the mounting plate; The first tension / compression sensor group is connected to the bracket; The second tensile and compressive sensor group, the test truss, the first torque sensor group, and the vertical beam are mounted above the mounting plate; The second tensile and compressive sensor group is connected to the test truss; One end of the test truss is connected to the vertical beam; The other end of the test truss is connected to the flange; The first torque sensor group is connected to the flange; The vertical beam is used to support the truss; The flange is used to connect the robotic arm testing module.

5. A comprehensive avionics test bench for an electric vertical takeoff and landing multirotor aircraft according to claim 4, characterized in that, When performing single-axis dynamic testing, the test platform also includes a limiting frame, which is connected to the tail end of the truss and is used to reduce the sway of the truss.

6. The integrated avionics test bench for an electric vertical takeoff and landing multirotor aircraft according to claim 4, characterized in that, When performing multi-axis dynamic tests, the test platform also includes a hinge support for connecting two adjacent trusses and for reducing truss sway.

7. The integrated avionics test bench for an electric vertical takeoff and landing multirotor aircraft according to claim 1, characterized in that, The robotic arm testing module includes a mating flange, a robotic arm, a second torque sensor group, a motor, and a propeller; The mating flange is connected to the test platform; The arm is connected to the mating flange; The second torque sensor group is connected to the machine arm; The motor is connected to the machine arm; The motor and the propeller are connected; The arms and propellers are used to simulate an aircraft; The motor is used for power supply.

8. The integrated avionics test bench for an electric vertical takeoff and landing multirotor aircraft according to claim 1, characterized in that, It also includes a battery pack, which is connected to the test platform and is used to provide power.

9. A comprehensive avionics test bench for an electric vertical takeoff and landing multirotor aircraft according to claim 3, characterized in that, The support is a square tube support, and the height of the support is greater than or equal to 3 meters.

10. A comprehensive avionics test bench for an electric vertical takeoff and landing multirotor aircraft according to claim 1, characterized in that, The test modes include: single-axis or multi-axis dynamic testing, full-weight dynamic testing, flight control vibration testing, flight control electromagnetic interference testing, flight control electronic adjustment and connection, flight control BMS connection testing, aging testing, and energy management testing.

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