EVTOL aircraft take-off and landing performance test system

Abstract

The invention provides an eVTOL aircraft take-off and landing performance test system. The test stand comprises a stand base, a platform gradient adjusting support column, a lifting platform, an ascending airflow simulation module, a descending airflow simulation module, a turbulent flow and wind simulation module, a vertical holding joint, a horizontal holding joint, a lower bracket, a vertical bracket, an upper bracket, a test stand control module, a test monitoring module and a protection net. The device is used for simulating various air flow disturbances and takeoff and landing platform gradients possibly faced in the takeoff and landing process of the eVTOL aircraft, the takeoff and landing performance of the eVTOL aircraft is efficiently, safely and conveniently tested, and an effective testing means is provided for the specialties of the eVTOL aircraft, such as overall, power, flight control, manipulation and the like. And an available conformity verification means is provided for airworthiness authentication of the aircraft.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft performance testing, and in particular to an eVTOL aircraft take-off and landing performance testing system. Background Art

[0002] In recent years, with the development of related disciplines such as aviation power, composites, control, computers, and micro-electromechanical sensors, the emergence of performance bottlenecks of traditional fixed-wing aircraft and helicopters, and the emergence of demands for urban air mobility (UAM), short-distance passenger transport / logistics / distribution, electric vertical take-off and landing (eVTOL) aircraft has once again become a research hotspot in industry and academia, and has received extensive attention from industries such as defense, civil aviation, general aviation, automobiles, and drones, becoming an important development direction for future aircraft.

[0003] In a typical UAM operation scenario, the eVTOL aircraft needs to take off and land on the apron on top of a building and fly between buildings. This scenario has the following characteristics:

[0004] (1) The aircraft is close to buildings during takeoff and landing, and the space is limited;

[0005] (2) The wind speed on the roof is high and the cross-wind between buildings may cause strong turbulence;

[0006] (3) The distributed power layout of the eVTOL aircraft has high rotor load and high downwash airflow velocity. The vortex ring characteristics and ground effect during descent are stronger than those of traditional helicopters.

[0007] The above problems greatly increase the difficulty of eVTOL aircraft take-off and landing, and put forward high requirements on the wind resistance of eVTOL aircraft during take-off and landing, as well as the high-precision position and altitude control capabilities in a limited space. From the perspective of flight safety and ride quality, the take-off and landing performance of eVTOL needs to be fully tested and confirmed.

[0008] In addition, when the weight of the eVTOL machine exceeds a certain level, especially considering the scenarios of operation and passenger transportation over cities, if the take-off and landing performance and safety cannot be well guaranteed, it will not only cause great harm to the public, but also bring great risks to R&D or operating companies and even the entire industry.

[0009] For eVTOL aircraft weighing tons, it is very expensive to conduct flight tests in actual scenarios such as rooftop helipads. Once an accident occurs during the test, the cost is extremely high. Therefore, higher requirements are placed on the test methods and facilities for the take-off and landing phases. Effectively evaluating the take-off and landing performance of eVTOL aircraft is an important prerequisite for improving the safety and ride quality of eVTOL aircraft, but there is currently no test equipment or system for the take-off and landing performance of eVTOL aircraft. Summary of the invention

[0010] In order to solve the problems existing in the prior art, the purpose of the present invention is to provide an eVTOL aircraft take-off and landing performance test system, which is used to simulate various airflow disturbances and take-off and landing platform slopes that may be encountered during the eVTOL take-off and landing process, and to perform efficient, safe and convenient tests on the take-off and landing performance of the eVTOL aircraft, thereby providing effective testing means for the overall, power, flight control, and manipulation of the eVTOL aircraft, and providing available compliance verification means for the airworthiness certification of such aircraft.

[0011] The present invention achieves the above-mentioned purpose through the following technical solutions:

[0012] An eVTOL aircraft take-off and landing performance test system, comprising:

[0013] a platform base, which is used to provide a mounting foundation for the platform grade adjustment struts;

[0014] A platform slope adjustment support is installed on the platform base;

[0015] The landing platform is the actual support platform for the aircraft before takeoff and after landing. Its lower part is supported by the platform slope adjustment pillars. The middle of the landing platform is a hollow structure, and an updraft simulation module is embedded inside it.

[0016] The updraft simulation module is embedded in the hollow structure of the take-off and landing platform, and is used to receive the speed command sent by the test bench control module, and simulate the updraft speed in the test area by adjusting the motor speed;

[0017] The downdraft simulation module is installed on the horizontal bracket, and is used to receive the speed command sent by the test bench control module, and simulate the downdraft speed in the test area by adjusting the motor speed;

[0018] The turbulence and wind simulation module is installed on the vertical bracket, and is used to receive the speed command sent by the test bench control module, and simulate the turbulence and wind speed in the test area by adjusting the motor speed;

[0019] The vertical holding joint measures the angle of the vertical bracket deviation from the vertical through the bracket attitude sensor, and controls the rotation of the servo motor through the motor driver to adjust the vertical bracket to stabilize it in a vertical state;

[0020] The horizontal joint is maintained by measuring the angle of the upper bracket deviating from the horizontal through the bracket attitude sensor, and the servo motor is controlled to rotate through the motor driver to adjust the upper bracket to stabilize it in a horizontal state;

[0021] The test bench control module is used to receive the test condition setting instruction sent by the test monitoring module and set the test conditions;

[0022] The test monitoring module is used to receive the test system data fed back by the test bench control module, and at the same time receive the test data of the eVTOL aircraft under test, set the test conditions according to the test outline, and monitor the status of the aircraft under test in real time. In case of an emergency, it will issue a command to terminate the test, control the shutdown of the updraft simulation module, the downdraft simulation module, the turbulence and wind simulation module, and level the take-off and landing platform.

[0023] According to an eVTOL aircraft take-off and landing performance test system provided by the present invention, the platform slope adjustment pillar includes three linear motion pillars, the three linear motion pillars are vertically distributed and installed on the test bench base, and the angle between the three linear motion pillars and the center point of the platform is 120 degrees; the test bench control module realizes precise adjustment of the platform slope by adjusting the extension and retraction of the three linear motion pillars according to the actual attitude measured by the platform attitude control sensor and the attitude command sent by the test monitoring module.

[0024] According to an eVTOL aircraft take-off and landing performance test system provided by the present invention, the updraft simulation module includes a first grid, a first fan, a first DC brushless motor and a first DC brushless motor speed regulator, wherein the first DC brushless motor speed regulator receives a speed command sent by the test bench control module, and simulates the updraft speed of the test area through the first grid and the first fan by adjusting the speed of the first DC brushless motor;

[0025] The downdraft simulation module includes a second grid, a second fan, a second brushless DC motor and a second brushless DC motor speed regulator, wherein the second brushless DC motor speed regulator receives a speed command from the test bench control module, and simulates the downdraft speed of the test area through the second grid and the second fan by adjusting the speed of the second brushless DC motor;

[0026] The turbulence and wind simulation module includes a third grid, a third fan, a third DC brushless motor and a third DC brushless motor speed regulator, wherein the third DC brushless motor speed regulator receives a speed command from the test bench control module, and simulates the turbulence and wind speed in the test area through the third grid and the third fan by adjusting the speed of the third DC brushless motor.

[0027] According to an eVTOL aircraft take-off and landing performance test system provided by the present invention, a vertical holding joint includes a first bracket attitude sensor, a first servo motor, a first motor driver and a first joint controller, wherein the first joint controller measures the angle of deviation of the vertical bracket from the vertical in real time through the first bracket attitude sensor, and controls the rotation of the first servo motor through the first motor driver according to the angle deviation, thereby realizing automatic adjustment of the vertical bracket to ensure that it is stable in a vertical state.

[0028] According to an eVTOL aircraft take-off and landing performance test system provided by the present invention, a horizontal maintaining joint includes a second bracket attitude sensor, a second servo motor, a second motor driver and a second joint controller, wherein the second joint controller measures the angle of deviation of the upper bracket from the horizontal in real time through the second bracket attitude sensor, and controls the rotation of the second servo motor through the second motor driver according to the angle deviation, thereby realizing automatic adjustment of the upper bracket to ensure that it is stable in a horizontal state.

[0029] According to an eVTOL aircraft take-off and landing performance test system provided by the present invention, the test bench control module includes:

[0030] The wind speed regulating unit is used to receive the wind speed command sent by the test monitoring module through wired / wireless communication means, obtain the motor speed command by looking up the table according to the preset wind speed-rotation speed correspondence law, and send the command to the motor speed regulator of the rising airflow simulation module, the motor speed regulator of the falling airflow simulation module and the motor speed regulator of the turbulence and wind simulation module respectively, so as to adjust the wind speed of each test area;

[0031] The platform slope adjustment unit is used to receive the take-off and landing platform slope command sent by the test monitoring module, and combined with the actual attitude information measured by the platform attitude control sensor, calculate the extension and retraction amount of the three linear motion pillars through the extension and retraction amount calculation module, and adjust the platform slope by adjusting the extension and retraction of the three linear motion pillars.

[0032] According to an eVTOL aircraft take-off and landing performance test system provided by the present invention, the platform slope adjustment unit also includes a telescopic amount calculation module, which is used to calculate the telescopic amounts of the three linear motion struts through the following control algorithm:

[0033] According to the actual attitude information measured by the platform attitude control sensor and the target attitude command sent by the test monitoring module, the attitude deviation that needs to be adjusted for the platform is determined;

[0034] Based on the geometric relationship that the angle between the three linear motion pillars and the center point of the platform is 120 degrees and evenly distributed, and the mathematical model between the pillar extension and extension amount and the platform posture change, a set of linear or nonlinear equations is constructed;

[0035] The system of equations is solved by numerical or analytical methods to obtain the specific value of the expansion and contraction required for each pillar;

[0036] The calculated extension and retraction instructions are sent to the motor drivers of the three linear motion pillars. By controlling the rotation of the servo motor, the extension and retraction of the three linear motion pillars can be precisely adjusted, thereby adjusting the slope of the platform to the target posture.

[0037] According to an eVTOL aircraft take-off and landing performance test system provided by the present invention, the simulated wind volume of the updraft simulation module is 0-8.5 m / s, the simulated wind volume of the downdraft simulation module is 0-5 m / s, and the simulated wind volume of the turbulence and wind simulation module is 0-6 m / s.

[0038] An eVTOL aircraft take-off and landing performance test system provided by the present invention also includes:

[0039] A data receiving and processing module is configured to receive the test system data fed back by the test bench control module through wired / wireless communication means; at the same time, the module also receives the test data transmitted by the eVTOL aircraft under test through wireless communication means;

[0040] The emergency termination control module is connected to the data receiving and processing module and is used to perform the following operations immediately upon receiving a data signal indicating an emergency or an emergency termination command manually triggered by the operator when the test operator sets the test conditions according to the test outline and monitors the status of the aircraft under test in real time:

[0041] Sending a stop signal to the updraft simulation module, the downdraft simulation module, and the turbulence and wind simulation module to shut down their operations;

[0042] Control the take-off and landing platform adjustment mechanism to adjust the take-off and landing platform to a horizontal state or a safe posture;

[0043] At the same time, an emergency stop command is sent to the test bench control module and all related subsystems to ensure that the entire test system stops running safely and orderly.

[0044] According to an eVTOL aircraft take-off and landing performance test system provided by the present invention, the data receiving and processing module includes:

[0045] A real-time data analysis submodule configured to receive and process test data from the test bench control module and the eVTOL aircraft under test, the submodule using parallel processing technology and distributed computing architecture;

[0046] Anomaly recognition algorithm library, which integrates a variety of advanced data analysis algorithms, statistical analysis methods and pattern recognition technologies;

[0047] When the real-time data analysis submodule detects data anomalies or deviations exceeding the preset threshold, it immediately triggers the corresponding algorithm in the anomaly identification algorithm library to conduct in-depth analysis to determine the type, severity and possible causes of the anomaly; then, it provides instant feedback to the test operator through the user interface.

[0048] It can be seen that compared with the prior art, the system provided by the present invention has the following beneficial effects:

[0049] 1. The system of the present invention uses a platform slope simulation module to accurately simulate the slope changes of the take-off and landing site, and uses an airflow simulation module to reproduce various airflows and ground effect environments that may be encountered on the apron on the top of the building, so that the eVTOL aircraft can experience flight challenges similar to actual usage scenarios during the test, thereby more accurately evaluating its take-off and landing performance.

[0050] 2. Traditional helipad tests on the top of buildings have many potential safety hazards, including but not limited to high-altitude operation risks, flight uncertainty in complex airflow environments, etc. The present invention uses a test bench to replace actual field tests, effectively avoiding these risks, making the test process safer and more controllable, and protecting the safety of the aircraft and test personnel.

[0051] 3. The present invention can be used to quickly set and adjust test conditions, such as slope, wind speed, airflow direction, etc., in a short time, greatly shortening the test cycle. At the same time, the real-time data monitoring and analysis function provided by the system enables test personnel to quickly obtain key performance parameters, find problems in time and optimize them, further improving the test efficiency.

[0052] 4. Compared with the actual building rooftop helipad test, the test bench and simulation equipment required by the present invention are relatively low in cost and reusable, which greatly reduces the test cost. In addition, since the test process is safer and more controllable, it also reduces the additional losses caused by accidents or failures.

[0053] 5. This invention provides an effective evaluation method for the design of eVTOL aircraft, enabling the R&D team to iterate and optimize the aircraft design more quickly, accelerating the process from R&D to marketization. This not only promotes the rapid development of eVTOL aircraft technology, but also lays a solid foundation for the popularization of future urban air traffic (UAM).

[0054] 6. Through the rigorous testing conducted by the present invention, it can be ensured that the eVTOL aircraft has good performance and stability in complex and changeable take-off and landing environments, thereby enhancing its competitiveness in the market. This is of great significance for promoting the overall development of the eVTOL aircraft industry and enhancing the public's trust and acceptance of this type of new aircraft.

[0055] The present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0056] Figure 1 It is a schematic diagram of the overall structure of an embodiment of an eVTOL aircraft take-off and landing performance test system of the present invention.

[0057] Figure 2 It is a top view schematic diagram of a test bench base, a platform slope adjustment support and a protective net in an embodiment of an eVTOL aircraft take-off and landing performance test system of the present invention.

[0058] Figure 3 It is a schematic diagram of wind speed setting and control in an embodiment of an eVTOL aircraft take-off and landing performance test system of the present invention.

[0059] Figure 4 It is a schematic diagram of the principle of support attitude control in an embodiment of an eVTOL aircraft take-off and landing performance test system of the present invention.

[0060] Figure 5 It is a schematic diagram of a landing test of an embodiment of an eVTOL aircraft take-off and landing performance test system of the present invention.

[0061] Figure 6 It is a schematic diagram of test data flow of an embodiment of an eVTOL aircraft take-off and landing performance test system of the present invention.

[0062] In the figure: 1-test bench base, 2-platform slope adjustment support, 3-take-off and landing platform, 4-upward airflow simulation module, 5-downward airflow simulation module, 6-turbulence and wind simulation module, 7-vertical holding joint, 8-horizontal holding joint, 9-lower bracket, 10-vertical bracket, 11-upper bracket, 12-test bench control module, 13-test monitoring module and 14-protection net. DETAILED DESCRIPTION

[0063] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the drawings of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0064] Reference to "embodiments" herein means that a particular feature, structure, or characteristic described in conjunction with the embodiments may be included in at least one embodiment of the present application. The appearance of the phrase in various locations in the specification does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment that is mutually exclusive with other embodiments. It is explicitly and implicitly understood by those skilled in the art that the embodiments described herein may be combined with other embodiments.

[0065] See also Figures 1 to 6 The present invention provides an eVTOL aircraft take-off and landing performance test system, comprising:

[0066] The platform base 1 is used to provide an installation foundation for the platform slope adjustment pillar 2. The platform base 1 is cast with cement.

[0067] The platform slope adjustment pillar 2 is installed on the test bench base 1. The platform slope adjustment pillar 2 includes three linear motion pillars, which are vertically distributed on the test bench base 1 and evenly distributed with the angle between the three linear motion pillars and the center point of the platform being 120 degrees. The test bench control module 12 adjusts the platform slope by adjusting the extension and retraction of the three linear motion pillars according to the actual posture measured by the platform posture control sensor and the posture command sent by the test monitoring module 13.

[0068] The landing and take-off platform 3 is used as the actual support platform before the aircraft takes off and after landing. The lower part is supported by the platform slope adjustment pillar 2. The middle of the landing and take-off platform 3 is a hollow structure, and an updraft simulation module 4 is embedded in it.

[0069] The rising airflow simulation module 4 is embedded in the hollow structure of the take-off and landing platform 3, and is used to receive the speed command sent by the test bench control module 12, and simulate the rising airflow speed in the test area by adjusting the motor speed.

[0070] The downdraft simulation module 5 is installed on a horizontal support, and is used to receive the speed command sent by the test bench control module 12, and simulate the downdraft speed in the test area by adjusting the motor speed.

[0071] The turbulence and wind simulation module 6 is installed on the vertical support 10, and is used to receive the speed command sent by the test bench control module 12, and simulate the turbulence and wind speed in the test area by adjusting the motor speed.

[0072] The vertical holding joint 7 measures the angle of deviation of the vertical bracket 10 from the vertical through the bracket attitude sensor, and controls the rotation of the servo motor through the motor driver to adjust the vertical bracket 10 so that it is stabilized in the vertical state.

[0073] The joint 8 is kept horizontal, and the angle of deviation of the upper bracket 11 from the horizontal is measured by the bracket attitude sensor, and the servo motor is controlled to rotate by the motor driver to adjust the upper bracket 11 so that it is stabilized in a horizontal state.

[0074] The test bench control module 12 is used to receive the test condition setting instruction sent by the test monitoring module 13 and set the test conditions.

[0075] The test monitoring module 13 is used to receive the test system data fed back by the test bench control module 12, and at the same time receive the test data of the eVTOL aircraft under test, set the test conditions according to the test outline, and monitor the status of the aircraft under test in real time. In case of an emergency, it issues a command to terminate the test, controls the updraft simulation module 4, the downdraft simulation module 5, and the turbulence and wind simulation module 6 to close, and levels the take-off and landing platform 3.

[0076] The protection net 14 is used to provide safety protection.

[0077] like Figure 3 As shown, Figure 3 This is the wind speed setting and control principle diagram of this embodiment. The corresponding relationship between the expected wind speed and the rotation speed in the test area is calibrated before the test. During the test, the test system operator sends the expected wind speed command, and the test bench control module 12 receives the command, obtains the expected rotation speed according to the expected wind speed table, and sends it to the corresponding airflow simulation module 4 / 5 / 6. The airflow simulation module achieves the expected wind speed by adjusting the motor speed.

[0078] In this embodiment, the rising air flow simulation module 4 includes a first grid, a first fan, a first DC brushless motor and a first DC brushless motor speed regulator, wherein the first DC brushless motor speed regulator receives a speed command from the test bench control module 12, and simulates the rising air flow speed in the test area through the first grid and the first fan by adjusting the speed of the first DC brushless motor.

[0079] In this embodiment, the downward airflow simulation module 5 includes a second grid, a second fan, a second DC brushless motor and a second DC brushless motor speed regulator, wherein the second DC brushless motor speed regulator receives a speed command from the test bench control module 12, and simulates the downward airflow speed in the test area through the second grid and the second fan by adjusting the speed of the second DC brushless motor.

[0080] In this embodiment, the turbulence and wind simulation module 6 includes a third grid, a third fan, a third DC brushless motor and a third DC brushless motor speed regulator, wherein the third DC brushless motor speed regulator receives the speed command sent by the test bench control module 12, and simulates the turbulence and wind speed in the test area through the third grid and the third fan by adjusting the speed of the third DC brushless motor. In particular, the simulated air volume of the updraft wind simulation module, the simulated air volume of the downdraft wind simulation module, and the simulated air volume of the turbulent wind simulation module vary according to different take-off and landing scenarios and models. Typical values ​​for take-off and landing of 4-5 eVTOLs are given here, as follows:

[0081] Simulated air volume of the updraft wind simulation module: 0~8.5m / s;

[0082] Simulated air volume of downdraft wind simulation module: 0~5m / s;

[0083] Turbulent wind simulation module simulates air volume: 0~6m / s,

[0084] In combination with the simulated wind volume of the above-mentioned specific wind module and the angle adjustment of the take-off and landing platform 33, the detailed processes of the two scenarios of the aircraft ascending and descending are respectively given:

[0085] In the simulated aircraft takeoff scenario:

[0086] First, the test system operator sends the expected simulated air volume of 5m / s. The test bench control module 12 receives the simulated air volume instruction, obtains the expected speed according to the expected wind speed table, and sends it to the corresponding updraft simulation module 4. The airflow simulation module achieves the expected wind speed of 5m / s by adjusting the motor speed.

[0087] Then, the test monitoring module 13 receives the test system data fed back by the test bench control module through wired / wireless communication means, and receives the test data of the eVTOL aircraft under test through wireless communication means. The test operator sets the test conditions according to the test outline and monitors the status of the aircraft under test in real time. If there is a large control error or an onboard system failure, the typical case is as follows:

[0088] (1) Attitude tracking error exceeds the limit ≮2°;

[0089] (2) Position tracking error exceeds the limit ≮0.5m;

[0090] (3) Any power motor temperature exceeds the limit or stops rotating;

[0091] (4) Battery overcurrent or temperature exceeds the limit;

[0092] (5) Vertical velocity tracking error exceeds the limit ≮0.2m / s;

[0093] (6) Altitude tracking error exceeds the limit ≮0.2m.

[0094] Issue a test termination command at any time to close the updraft simulation module 4 and level the take-off and landing platform 3.

[0095] Finally, the test bench control module 12 adjusts the slope of the platform during take-off by adjusting the extension and retraction of the three pillars according to the slope instruction of the take-off and landing platform 3, combined with the actual attitude measured by the platform attitude control sensor and the attitude instruction sent by the test monitoring module 13.

[0096] In the simulated aircraft descent scenario:

[0097] First, the operator of the test system sends the expected simulated air volume of 3m / s. The test bench control module 12 receives the simulated air volume instruction, obtains the expected speed according to the expected wind speed table, and sends it to the corresponding downdraft simulation module 5. The airflow simulation module achieves the expected wind speed of 3m / s by adjusting the motor speed.

[0098] Then, the test monitoring module 13 receives the test system data fed back by the test bench control module 12 through wired / wireless communication means, and receives the test data of the eVTOL aircraft under test through wireless communication means. The test operator sets the test conditions according to the test outline and monitors the status of the aircraft under test in real time. If an emergency occurs, the typical case is as follows:

[0099] (1) Attitude tracking error exceeds the limit ≮2°;

[0100] (2) Position tracking error exceeds the limit ≮0.5m;

[0101] (3) Any power motor temperature exceeds the limit or stops rotating;

[0102] (4) Battery overcurrent or temperature exceeds the limit;

[0103] (5) Vertical velocity tracking error exceeds the limit ≮0.2m / s;

[0104] (6) Altitude tracking error exceeds the limit ≮0.2m.

[0105] The test termination command may be issued at any time to close the downdraft simulation module 5 and level the take-off and landing platform 3.

[0106] Finally, the test bench control module 12 adjusts the slope of the platform during descent by adjusting the extension and retraction of the three pillars according to the slope instruction of the take-off and landing platform 3, combined with the actual posture measured by the platform posture control sensor and the posture instruction sent by the test monitoring module 13.

[0107] In this embodiment, the vertical holding joint 7 includes a first bracket posture sensor, a first servo motor, a first motor driver and a first joint controller. Figure 4 As shown, the posture control principle of the joint is as follows: the first joint controller measures the angle of deviation of the vertical bracket 10 from the vertical in real time through the first bracket posture sensor, and controls the rotation of the first servo motor through the first motor driver according to the angle deviation, thereby realizing automatic adjustment of the vertical bracket 10 to ensure that it is stable in a vertical (perpendicular to the ground) state.

[0108] In this embodiment, the horizontal maintaining joint 8 includes a second bracket attitude sensor, a second servo motor, a second motor driver and a second joint controller, wherein the second joint controller measures the angle of deviation of the upper bracket 11 from the horizontal in real time through the second bracket attitude sensor, and controls the rotation of the second servo motor through the second motor driver according to the angle deviation, thereby realizing automatic adjustment of the upper bracket 11 to ensure that it is stable in a horizontal state.

[0109] In this embodiment, the lower bracket 9 provides an installation base for the vertical bracket 10 , the vertical bracket 10 provides an installation base for the upper bracket 11 and the turbulence and wind simulation module 6 , and the upper bracket 11 provides an installation base for the downdraft simulation module 5 .

[0110] like Figure 5 and 6 As shown, Figure 5 This is a schematic diagram of the landing test of this embodiment. Figure 6 The following is a schematic diagram of the test data flow of this embodiment. Before the test, the aircraft test team and the test system operation team need to work together to complete the test outline, which needs to clearly define the test adjustments and aircraft test actions. During the test, the test system operator and the aircraft operator carry out the test according to the outline.

[0111] In this embodiment, the test bench control module 12 includes:

[0112] The wind speed regulating unit is used to receive the wind speed command sent by the test monitoring module 13 through wired / wireless communication means, obtain the motor speed command by looking up the table according to the preset wind speed-rotation speed correspondence rule, and send the command to the motor speed regulator of the rising airflow simulation module 4, the motor speed regulator of the falling airflow simulation module 5 and the motor speed regulator of the turbulence and wind simulation module 6 respectively, so as to realize the adjustment of the wind speed of each test area.

[0113] The platform slope adjustment unit is used to receive the slope instruction of the take-off and landing platform 3 sent by the test monitoring module 13, and in combination with the actual posture information measured by the platform posture control sensor, calculate the extension and retraction amount of the three linear motion pillars through the extension and retraction amount calculation module, and adjust the platform slope by adjusting the extension and retraction of the three linear motion pillars.

[0114] The platform slope adjustment unit also includes a telescopic amount calculation module, which is used to calculate the telescopic amounts of the three linear motion pillars through the following control algorithm:

[0115] According to the actual attitude information measured by the platform attitude control sensor and the target attitude instruction sent by the test monitoring module 13, the attitude deviation of the platform that needs to be adjusted is determined; based on the geometric relationship that the angle between the three linear motion pillars and the center point of the platform is 120 degrees and is evenly distributed, and the mathematical model between the pillar extension and contraction amount and the platform attitude change, a set of linear or nonlinear equations is constructed; the equations are solved using a numerical solution or an analytical solution to obtain the specific value of the extension and contraction required for each pillar; the calculated extension and contraction amount instructions are sent to the motor drivers of the three linear motion pillars, and the extension and contraction amount of the three linear motion pillars are precisely adjusted by controlling the rotation of the servo motor, thereby adjusting the slope of the platform to the target attitude.

[0116] In this embodiment, the test monitoring module 13 also includes:

[0117] The data receiving and processing module is configured to receive the test system data fed back by the test bench control module through wired / wireless communication means. The data includes but is not limited to wind speed simulation status, platform slope status, motor operation status, etc.; at the same time, the module also receives the test data transmitted by the eVTOL aircraft under test through wireless communication means, such as real-time parameters such as aircraft attitude, speed, altitude, and power system.

[0118] The emergency termination control module is connected to the data receiving and processing module and is used to perform the following operations immediately upon receiving a data signal indicating an emergency or an emergency termination command manually triggered by the operator when the test operator sets the test conditions according to the test outline and monitors the status of the aircraft under test in real time:

[0119] Sending a stop signal to the updraft simulation module 4, the downdraft simulation module 5, and the turbulence and wind simulation module 6 to shut down their operations;

[0120] Control the adjustment mechanism of the take-off and landing platform 3 to adjust the take-off and landing platform 3 to a horizontal state or a safe posture;

[0121] At the same time, an emergency stop command is sent to the test bench control module and all related subsystems to ensure that the entire test system stops running safely and orderly to protect the aircraft under test and the test equipment from damage.

[0122] Specifically, the data receiving and processing module further includes a real-time data analysis submodule and an abnormality recognition algorithm library, which are used to enhance the real-time analysis and processing capabilities of the test data. The specific implementation method is as follows:

[0123] The real-time data analysis submodule is configured to receive and process test data from the test bench control module and the eVTOL aircraft under test, including but not limited to real-time information such as wind speed, airflow simulation status, platform slope, aircraft attitude, power system parameters, etc.; this submodule adopts parallel processing technology and distributed computing architecture to ensure the real-time and accuracy of data processing.

[0124] The anomaly identification algorithm library integrates a variety of advanced data analysis algorithms, such as machine learning models (including but not limited to support vector machines, random forests, neural networks, etc.), statistical analysis methods (such as outlier detection, variance analysis, etc.) and pattern recognition technology; these algorithms are trained and optimized for various abnormal behaviors that may occur in the aircraft during the test (such as attitude loss of control, power system failure, unstable flight, etc.), and can analyze test data in real time, quickly identify and warn of potential abnormal situations.

[0125] When the real-time data analysis submodule detects data anomalies or deviations exceeding the preset threshold, it immediately triggers the corresponding algorithm in the anomaly recognition algorithm library to conduct in-depth analysis to determine the type, severity and possible causes of the anomaly; then, it provides instant feedback to the test operator through the user interface, including abnormal warnings, data analysis reports and recommended response measures, so that the operator can respond quickly, adjust the test conditions or take emergency termination measures to ensure test safety and aircraft safety.

[0126] In addition, the real-time data analysis submodule and anomaly identification algorithm library also have self-learning and optimization functions, which can continuously adjust and improve the algorithm model based on historical data and feedback information, improve the accuracy and efficiency of anomaly identification, and provide more accurate support for future tests.

[0127] In summary, the system of this embodiment uses the platform slope simulation module to accurately simulate the slope changes of the take-off and landing site, and uses the airflow simulation module to reproduce the various airflows and ground effect environments that may be encountered on the apron on the top of the building, so that the eVTOL aircraft can experience flight challenges similar to actual usage scenarios during the test, thereby more accurately evaluating its take-off and landing performance.

[0128] Furthermore, the traditional helipad test on the top of a building has many potential safety hazards, including but not limited to the risk of high-altitude operations, flight uncertainty in complex airflow environments, etc. This embodiment uses a test bench to replace the actual field test, effectively avoiding these risks, making the test process safer and more controllable, and protecting the safety of the aircraft and test personnel.

[0129] Furthermore, the application embodiment system can quickly set and adjust test conditions, such as slope, wind speed, airflow direction, etc., in a short time, greatly shortening the test cycle. At the same time, the real-time data monitoring and analysis function provided by the system enables test personnel to quickly obtain key performance parameters, find problems in time and optimize them, further improving the test efficiency.

[0130] Furthermore, compared with the actual building rooftop helipad test, the test bench and simulation equipment required by this embodiment are relatively low in cost and reusable, which greatly reduces the test cost. In addition, since the test process is safer and more controllable, it also reduces additional losses caused by accidents or failures.

[0131] Furthermore, the system of this embodiment provides an effective evaluation method for the design of eVTOL aircraft, enabling the R&D team to iterate and optimize the aircraft design more quickly, accelerating its process from R&D to marketization. This not only promotes the rapid development of eVTOL aircraft technology, but also lays a solid foundation for the popularization of future urban air traffic (UAM).

[0132] Furthermore, through the rigorous testing of the system in this embodiment, it can be ensured that the eVTOL aircraft has good performance and stability in complex and changeable take-off and landing environments, thereby enhancing its competitiveness in the market. This is of great significance for promoting the overall development of the eVTOL aircraft industry and enhancing the public's trust and acceptance of this type of new aircraft.

[0133] The technical features of the above embodiments may be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0134] The above-mentioned embodiments are only preferred embodiments of the present invention and cannot be used to limit the scope of protection of the present invention. Any non-substantial changes and substitutions made by technicians in this field on the basis of the present invention shall fall within the scope of protection required by the present invention.

Claims

1. An eVTOL aircraft take-off and landing performance test system, characterized in that: include: a platform base, which is used to provide a mounting foundation for the platform grade adjustment struts; A platform slope adjustment support is installed on the platform base; The landing platform is the actual support platform for the aircraft before takeoff and after landing. Its lower part is supported by the platform slope adjustment pillars. The middle of the landing platform is a hollow structure, in which an updraft simulation module is embedded. The updraft simulation module is embedded in the hollow structure of the take-off and landing platform, and is used to receive the speed command sent by the test bench control module, and simulate the updraft speed in the test area by adjusting the motor speed; The downdraft simulation module is installed on the horizontal bracket, and is used to receive the speed command sent by the test bench control module, and simulate the downdraft speed in the test area by adjusting the motor speed; The turbulence and wind simulation module is installed on the vertical bracket, and is used to receive the speed command sent by the test bench control module, and simulate the turbulence and wind speed in the test area by adjusting the motor speed; The vertical holding joint measures the angle of the vertical bracket deviation from the vertical through the bracket attitude sensor, and controls the rotation of the servo motor through the motor driver to adjust the vertical bracket to stabilize it in a vertical state; The horizontal joint is maintained by measuring the angle of the upper bracket deviating from the horizontal through the bracket attitude sensor, and the servo motor is controlled to rotate through the motor driver to adjust the upper bracket to stabilize it in a horizontal state; The test bench control module is used to receive the test condition setting instruction sent by the test monitoring module and set the test conditions; The test monitoring module is used to receive the test system data fed back by the test bench control module, and at the same time receive the test data of the eVTOL aircraft under test, set the test conditions according to the test outline, and monitor the status of the aircraft under test in real time. In case of an emergency, it will issue a command to terminate the test, control the shutdown of the updraft simulation module, the downdraft simulation module, the turbulence and wind simulation module, and level the take-off and landing platform.

2. The system according to claim 1, characterized in that: The platform slope adjustment pillars include three linear motion pillars, which are vertically distributed on the test bench base and installed with an angle of 120 degrees between the three linear motion pillars and the center point of the platform. The test bench control module adjusts the platform slope by adjusting the extension and retraction of the three linear motion pillars according to the actual posture measured by the platform posture control sensor and the posture instructions sent by the test monitoring module.

3. The system according to claim 1, characterized in that: The rising air flow simulation module includes a first grid, a first fan, a first brushless DC motor and a first brushless DC motor speed regulator, wherein the first brushless DC motor speed regulator receives a speed command sent by the test bench control module, and simulates the rising air flow speed in the test area through the first grid and the first fan by adjusting the speed of the first brushless DC motor; The downdraft simulation module includes a second grid, a second fan, a second brushless DC motor and a second brushless DC motor speed regulator, wherein the second brushless DC motor speed regulator receives a speed command from the test bench control module, and simulates the downdraft speed of the test area through the second grid and the second fan by adjusting the speed of the second brushless DC motor; The turbulence and wind simulation module includes a third grid, a third fan, a third DC brushless motor and a third DC brushless motor speed regulator, wherein the third DC brushless motor speed regulator receives a speed command from the test bench control module, and simulates the turbulence and wind speed in the test area through the third grid and the third fan by adjusting the speed of the third DC brushless motor.

4. The system according to claim 1, characterized in that: The vertical holding joint includes a first bracket attitude sensor, a first servo motor, a first motor driver and a first joint controller, wherein the first joint controller measures the angle of deviation of the vertical bracket from the vertical in real time through the first bracket attitude sensor, and controls the rotation of the first servo motor through the first motor driver according to the angle deviation, thereby realizing automatic adjustment of the vertical bracket to ensure that it is stable in a vertical state.

5. The system according to claim 1, characterized in that: The horizontal maintaining joint includes a second bracket attitude sensor, a second servo motor, a second motor driver and a second joint controller, wherein the second joint controller measures the angle of deviation of the upper bracket from the horizontal in real time through the second bracket attitude sensor, and controls the rotation of the second servo motor through the second motor driver according to the angle deviation, thereby realizing automatic adjustment of the upper bracket to ensure that it is stable in a horizontal state.

6. The system according to claim 2, characterized in that: The test bench control module includes: The wind speed regulating unit is used to receive the wind speed command sent by the test monitoring module through wired / wireless communication means, obtain the motor speed command by looking up the table according to the preset wind speed-rotation speed correspondence law, and send the command to the motor speed regulator of the rising airflow simulation module, the motor speed regulator of the falling airflow simulation module and the motor speed regulator of the turbulence and wind simulation module respectively, so as to adjust the wind speed of each test area; The platform slope adjustment unit is used to receive the take-off and landing platform slope command sent by the test monitoring module, and combined with the actual attitude information measured by the platform attitude control sensor, calculate the extension and retraction amount of the three linear motion pillars through the extension and retraction amount calculation module, and adjust the platform slope by adjusting the extension and retraction of the three linear motion pillars.

7. The system according to claim 2, characterized in that: The platform slope adjustment unit also includes a telescopic amount calculation module, which is used to calculate the telescopic amount of the three linear motion pillars through the following control algorithm: According to the actual attitude information measured by the platform attitude control sensor and the target attitude command sent by the test monitoring module, determine the attitude deviation that needs to be adjusted for the platform; Based on the geometric relationship that the angle between the three linear motion pillars and the center point of the platform is 120 degrees and evenly distributed, and the mathematical model between the pillar extension and extension amount and the platform posture change, a set of linear or nonlinear equations is constructed; The system of equations is solved by numerical or analytical methods to obtain the specific amount of expansion and contraction required for each pillar; The calculated extension and retraction instructions are sent to the motor drivers of the three linear motion pillars. By controlling the rotation of the servo motor, the extension and retraction of the three linear motion pillars can be precisely adjusted, thereby adjusting the slope of the platform to the target posture.

8. The system according to any one of claims 1 to 7, characterized in that: The simulated wind volume of the rising airflow simulation module is 0-8.5 m / s, the simulated wind volume of the falling airflow simulation module is 0-5 m / s, and the simulated wind volume of the turbulence and wind simulation module is 0-6 m / s.

9. The system according to any one of claims 1 to 7, characterized in that: Also includes: A data receiving and processing module is configured to receive the test system data fed back by the test bench control module through wired / wireless communication means; at the same time, the module also receives the test data transmitted by the eVTOL aircraft under test through wireless communication means; The emergency termination control module is connected to the data receiving and processing module and is used to perform the following operations immediately upon receiving a data signal indicating an emergency or an emergency termination command manually triggered by the operator when the test operator sets the test conditions according to the test outline and monitors the status of the aircraft under test in real time: Sending a stop signal to the updraft simulation module, the downdraft simulation module, and the turbulence and wind simulation module to shut down their operations; Control the take-off and landing platform adjustment mechanism to adjust the take-off and landing platform to a horizontal state or a safe posture; At the same time, an emergency stop command is sent to the test bench control module and all related subsystems to ensure that the entire test system stops running safely and orderly.

10. The system according to claim 9, characterized in that: The data receiving and processing module comprises: A real-time data analysis submodule configured to receive and process test data from the test bench control module and the eVTOL aircraft under test, the submodule using parallel processing technology and distributed computing architecture; Anomaly recognition algorithm library, which integrates a variety of advanced data analysis algorithms, statistical analysis methods and pattern recognition technologies; When the real-time data analysis submodule detects data anomalies or deviations exceeding the preset threshold, it immediately triggers the corresponding algorithm in the anomaly identification algorithm library to conduct in-depth analysis to determine the type, severity and possible causes of the anomaly; then, it provides instant feedback to the test operator through the user interface.

Images