Mobile testing system and method for aircraft landing device

Abstract

The invention discloses a mobile testing system and method for an aircraft landing device. The mobile test system may include a vehicle body rack, a flight simulation system, a loading module, and a simulated onboard hydraulic and power system. The flight simulation system may generate attitude simulation signals that simulate a flight phase of the aircraft, including a load control signal and an energy control signal. The loading module can be docked with the aircraft landing device and load the aircraft landing device according to the loading control signal. And the simulated airborne hydraulic and power supply system provides hydraulic pressure and / or power supply for the aircraft landing device according to the energy control signal, so that the aircraft landing device performs take-off or landing operation on the road surface, and the aircraft landing device is tested.

Description

Technical Field

[0001] The present invention relates to an aircraft, and in particular to a mobile testing system and method for an aircraft landing device. Background Art

[0002] The ground operation quality and handling characteristics of an aircraft are directly related to the safety of the aircraft's take-off and landing. Good ground operation and handling qualities can greatly improve the aircraft's ground maneuverability. The ground operation and handling characteristics of an aircraft involve factors such as the aircraft structure, landing gear system structure, wheel brake system, tires and pavement. They are affected by aircraft load (aircraft weight, center of gravity), aircraft landing and taxiing status (landing roll angle, taxiing speed, turning angle, braking status, etc.), pavement status (asphalt runway, cement runway, concrete runway, dry runway and wet runway, etc.), environmental status (temperature, etc.), etc. They directly affect the aircraft's landing gear torque, turning radius, brake control law, braking distance and comfort, affect the aircraft's airport and runway adaptability, and are directly related to the aircraft's function, performance, safety and reliability during ground operation. They are important indicators for modern aircraft design and verification.

[0003] Modern aircraft design often uses modeling and simulation systems to confirm and verify development requirements, and evaluates ground handling characteristics at the beginning of physical development, thereby reducing development costs and risks. However, the simulation model of aircraft ground handling characteristics involves multiple factors and multiple states, with complex structures and many nonlinear factors. Traditional tests that can set tire states cannot meet the system simulation and test requirements of landing devices. For example, the inertial turntable provides a rotating hub, loading and measurement and control system, which can carry out tire handling characteristics tests under different loads, turning angles, roll angles, and speeds. However, due to the use of a rotating hub to simulate the pavement, the simulated pavement is limited by the inability to simulate the flatness, mechanics, and pollution status of the real pavement, so there is a certain gap between its handling characteristics data and the real characteristics.

[0004] Therefore, there is a need in the art for an improved testing system and method for aircraft landing equipment. Summary of the invention

[0005] Therefore, the present invention proposes a mobile test system and method for ground testing of aircraft landing gear, which can be used for simulating ground handling characteristics testing of aircraft tires, brakes and landing gear.

[0006] The present invention uses a flight simulation system to simulate different flight phases of an aircraft and provide corresponding attitude simulation signals, which can more accurately simulate the changing flight attitudes of the aircraft, such as speed, load, lifting, etc., thereby providing a more accurate landing device test. In addition, the flight simulation system can also simulate other aircraft system signals or instructions associated with the tested test piece, thereby forming a complete aircraft landing system test loop.

[0007] The test content of existing mobile test benches is limited. The aircraft landing gear system has a hydraulic and power supply system that is different from the test trolley. Therefore, the existing mobile test bench cannot test the ground handling characteristics of the landing gear, wheel brakes, and tires at the same time, and cannot provide effective data for the system simulation of the landing device. In one embodiment, the test trolley of the present invention has a hydraulic system that simulates the quality of the onboard hydraulic system, and can carry out the control and testing of the real hydraulic landing gear system and wheel brake system. At the same time, a real power supply system is provided to carry out the control and testing of multiple electrical systems such as electric brakes and electric turns.

[0008] In one embodiment of the present invention, a mobile test system for an aircraft landing device is provided, comprising: a vehicle body test bench having wheels for traveling on a pavement; a flight simulation system, the flight simulation system generating an attitude simulation signal simulating a flight phase of an aircraft according to a received test control signal, the attitude simulation signal comprising a loading control signal and an energy control signal; a loading module located on the vehicle body test bench, the loading module having a hardware interface for docking with a test piece, the test piece comprising an aircraft landing device, wherein the loading module loads the aircraft landing device according to the loading control signal generated by the flight simulation system; a simulated airborne hydraulic and power supply system located on the vehicle body test bench, the simulated airborne hydraulic and power supply system providing hydraulic pressure and / or power supply to the aircraft landing device according to the energy control signal generated by the flight simulation system, so that the aircraft landing device performs a takeoff or landing operation on the pavement, thereby testing the aircraft landing device.

[0009] In one embodiment, the loading module controls one or more of the vertical speed, output displacement or force, rotation angle, and tilt angle of the aircraft landing device according to the loading control signal to simulate the take-off or landing posture of the aircraft, and the take-off or landing posture includes one or more of lift, load, side deviation, and roll.

[0010] In one embodiment, the energy control signal comprises a voltage signal, and the simulated airborne hydraulic and power supply system provides power according to the voltage signal for the aircraft landing device to perform electric braking and / or electric turning tests.

[0011] In one embodiment, the energy control signal includes hydraulic flow and pressure signals, and the simulated onboard hydraulic and power system includes a flow regulating valve and a pressure setting valve, which are respectively used to set the hydraulic flow and pressure states according to the hydraulic flow and pressure signals.

[0012] In one embodiment, the attitude simulation signal further includes an engine speed simulation signal for controlling the acceleration and vehicle speed of the vehicle body test bench, thereby simulating the speed of the aircraft.

[0013] In one embodiment, the flight simulation system receives trolley parameter information of the mobile test system, and further generates the attitude simulation signal based on the trolley parameter information.

[0014] In one embodiment, the road surface comprises an asphalt runway, a cement runway, or a concrete runway, and the road surface is a dry runway or a wet runway.

[0015] In one embodiment, the aircraft landing device includes one or more of the following: landing gear, wheel brake system, and tire, and the test of the aircraft landing device includes one or more of landing gear retraction and extension test, landing gear turning test, wheel brake test, and tire performance test.

[0016] In one embodiment of the present invention, a mobile testing method for an aircraft landing device is provided, which comprises: docking a test piece with a loading module located on a vehicle body test bench, the vehicle body test bench having wheels for traveling on a pavement, the test piece comprising an aircraft landing device; generating an attitude simulation signal simulating a flight phase of the aircraft in a flight simulation system according to a received test control signal, the attitude simulation signal comprising a loading control signal and an energy control signal; causing the loading module to load the aircraft landing device according to the loading control signal generated by the flight simulation system; using a simulated airborne hydraulic and power supply system located on the vehicle body test bench to provide hydraulic pressure and / or power supply to the aircraft landing device according to the energy control signal generated by the flight simulation system, so that the aircraft landing device performs a takeoff or landing operation on the pavement, thereby testing the aircraft landing device.

[0017] In one embodiment, the loading module controls one or more of the vertical speed, output displacement or force, rotation angle, and tilt angle of the aircraft landing device according to the loading control signal to simulate the take-off or landing posture of the aircraft, and the take-off or landing posture includes one or more of lift, load, side deviation, and roll.

[0018] In one embodiment, the energy control signal comprises a voltage signal, and the simulated airborne hydraulic and power supply system provides power according to the voltage signal for the aircraft landing device to perform electric braking and / or electric turning tests.

[0019] In one embodiment, the energy control signal includes hydraulic flow and pressure signals, which are respectively used to set the hydraulic flow of the flow regulating valve and the pressure state of the pressure setting valve in the simulated onboard hydraulic and power system.

[0020] In one embodiment, the attitude simulation signal further includes an engine speed simulation signal for controlling the acceleration and vehicle speed of the vehicle body test bench, thereby simulating the speed of the aircraft.

[0021] In one embodiment, the flight simulation system receives the trolley parameter information of the mobile test system, and further generates the attitude simulation signal based on the trolley parameter information.

[0022] In one embodiment, the road surface comprises an asphalt runway, a cement runway, or a concrete runway, and the road surface is a dry runway or a wet runway.

[0023] In one embodiment, the aircraft landing device includes one or more of the following: landing gear, wheel braking method, and tires. The test of the aircraft landing device includes one or more of a landing gear retraction test, a landing gear turning test, a wheel braking test, and a tire performance test.

[0024] The test trolley of the present invention has a hydraulic system that simulates the quality of an airborne hydraulic system, and can carry out control and testing of a real hydraulic landing gear system and wheel brake system. It can also provide a real power supply system to control and test multiple electrical systems such as electric braking and electric turning, thereby obtaining high-confidence test data of landing gear, wheel brakes and tires under different loads, different landing and taxiing conditions, different pavement conditions and different environmental conditions.

[0025] The present invention can test the landing gear, wheel brake system and tires simultaneously or individually under different aircraft states, system states, pavement states and environmental states, and obtain high-confidence test data of the landing gear, wheel brakes and tires under different loads, different landing and taxiing states, different pavement states and different environmental states, which can be used to establish a high-confidence mathematical model, carry out landing gear, wheel brake system design, equipment selection and control characteristic simulation and test evaluation. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 is a system schematic diagram of a mobile testing system according to an embodiment of the present invention.

[0027] Figure 2 is a schematic diagram of a module vehicle according to an embodiment of the present invention.

[0028] Figure 3 is a schematic diagram of a loading module according to an embodiment of the present invention.

[0029] Figure 4 is a schematic diagram of a loading module according to another embodiment of the present invention.

[0030] Figure 5 is a schematic diagram of a simulated onboard hydraulic and electrical power system according to one embodiment of the present invention.

[0031] Figure 6 is a signal flow diagram of a mobile testing system according to an embodiment of the present invention.

[0032] Figure 7 is a flow chart of a mobile testing method according to an embodiment of the present invention. DETAILED DESCRIPTION

[0033] The present invention will be further described below in conjunction with specific embodiments and drawings. The following description will include many specific details, but this should not limit the scope of protection of the present invention. The present invention can also be implemented without using these details.

[0034] The test bench for the aircraft landing gear mainly needs to simulate the speed of the aircraft, the load on the landing gear, and the runway pavement. Conventionally, a fixed tire inertia simulation test bench is used to carry out the force and torque test of the landing gear. It simulates the relative speed of the landing gear sliding on the ground by rotating the transmission belt or flywheel at high speed, and simulates the surface friction characteristics of the runway pavement by installing concrete pavement on the transmission belt or flywheel surface and spraying water. By applying various dynamic loads to the landing gear, such as vertical, bending, steering, driving / braking and other motion loads, and letting the tire rotate on the transmission plane or flywheel, the force and torque properties that affect the performance and control of the aircraft are obtained.

[0035] The above test system or method has certain limitations in simulating the pavement of the aircraft landing device. On the one hand, due to the size limitation of the transmission belt or flywheel, the curvature and thickness of the simulated pavement are quite different from the actual flight pavement. For example, the actual flight pavement is a straight pavement, including soil bases and pavements of different thicknesses, and its slope is required to be no more than 0.6%. On the other hand, external factors such as water, snow, and ice that affect the friction characteristics of the pavement and the safety of the landing device cannot be effectively attached to the high-speed rotating flywheel or conveyor belt, which affects the accurate testing of the force and torque characteristics of the aircraft landing device on the contaminated runway.

[0036] The present invention proposes an improved mobile test system and method for aircraft landing equipment. The mobile test system of the present invention (for example, it can also be called a test trolley) has multiple wheels and can move freely, so that it can travel on real aircraft runways in various states, and simulate the take-off and landing postures of the aircraft through a loading module, so as to effectively test the ground running quality and handling characteristics of the test piece.

[0037] In addition, the existing test system mainly focuses on the force and torque test of tires and pavement, but does not consider that the performance of aircraft landing equipment such as turning and braking is affected by its energy supply system - onboard hydraulic system or power supply system. In comparison, the present invention provides simulation functions such as corresponding hydraulic, power and flight simulation systems, which can realize the aircraft turning ground characteristic test and braking ground characteristic test under real energy and aircraft communication control, and improve the accuracy and effectiveness of aircraft landing equipment ground test.

[0038] Figure 1 is a system schematic diagram of a mobile testing system 100 according to an embodiment of the present invention.

[0039] The mobile test system 100 is a mobile test system for an aircraft ground dynamics test platform (also referred to as a test trolley), which may include a loading module 120 located on a vehicle body frame 110, a simulated airborne hydraulic and power supply system 130, a flight simulation system 140, a mobile positioning communication system 160, a power system, a test trolley control system, an environmental protection system, etc. The test piece 150 to be tested can be installed or connected to the loading module 120 and loaded by the loading module 120. The power system is used to realize the drive / power and braking of the test trolley, etc. In one embodiment, the power system can be a hybrid power system, for example, including an engine, a generator, a battery, etc.

[0040] The vehicle body 110 may have multiple wheels so that it can be moved or transported to a test site / surface, such as a high-altitude airport, an airport with a different surface, etc. The test vehicle control system can be used to manually or automatically operate the test vehicle, such as controlling the running trajectory, speed, acceleration, etc.

[0041] In addition, the test trolley control system can communicate with the mobile positioning communication system 160 and the flight simulation system 140, accept control instructions from the flight simulation system 140, and control the speed and turning of the test trolley. The mobile positioning communication system 160 can transmit data and control instructions to remote devices (e.g., laboratory communication equipment, servers, mobile terminals, etc.). The mobile positioning communication system 160 can also be used to locate the test trolley and transmit the positioning information to other devices.

[0042] In one embodiment, the vehicle body platform 110 can be assembled in a modular manner. For example, the vehicle body platform 110 can be divided into a plurality of detachable modules, such as a plurality of module vehicles and a loading platform. Each module vehicle can include wheels, a vehicle frame, and corresponding on-board equipment. In one embodiment, the largest single module vehicle can be transported using a 40-foot standard container. Figure 1The figure shows four single-module vehicles and an intermediate loading platform. Two module vehicles are connected to the front and rear of the loading platform. The two module vehicles are connected laterally. Each module vehicle is spliced ​​by a hook structure and an articulated structure. The four single-module vehicles are detachably connected and each has multiple wheels. They can be spliced ​​together to form a support platform for the test vehicle, or they can be disassembled and run separately as independent vehicles under the action of their own drive / power devices.

[0043] In one embodiment, the vehicle body test bench 110 may be equipped with a flight simulation system 140, which is used to simulate a real flight system and its electronic and communication functions. The flight simulation system 140 may be implemented by executing program instructions through electronic devices such as computers, processors, controllers, and state machines. The flight simulation system 140 may simulate different flight phases of the aircraft and generate attitude simulation signals based on the received test control signals. The flight simulation system 140 may also simulate other aircraft system signals or instructions associated with the test piece 150 to form a complete aircraft landing system test loop.

[0044] The loading module 120 (also referred to as a loading system) may be located on a loading platform in the middle of the vehicle body. The loading module interfaces with the test piece 150 (e.g., aircraft landing gear, such as tires, brake systems, and landing gear systems) through various hardware interfaces and protocols, thereby implementing the testing of tires, brakes, and landing gear systems. The hardware interface of the loading module 120 may include a notch or a bayonet for physically connecting with the test piece 150, so as to install or fix the test piece 150 to the loading module 120.

[0045] The loading module 120 simulates the attitude and load of the test object by loading the test piece 150, thereby simulating the take-off or landing attitude of the aircraft, such as pitch, roll and / or yaw attitude. In one embodiment, the loading module can simulate the take-off or landing attitude of the aircraft according to the attitude simulation signal provided by the flight simulation system 140. Take-off may include stages such as taxiing and take-off, and landing may include stages such as descent, approach, landing, and taxiing. As an example and not limitation, the loading module 120 can control the output displacement or force to achieve the application of load to the test piece, control the vertical speed to achieve loading lifting, control the rotation of the test piece to achieve loading lateral deviation, control the tilt of the test piece to achieve loading tilt, etc.

[0046] The hardware interface of the loading module 120 may also include an energy interface for providing energy (e.g., power or hydraulic pressure) to the test piece 150. In one embodiment, the hardware interface connected to the hydraulic system may use a high-pressure hydraulic connector, such as a JIC (Joint Industry Council) connector, an NPT (National Pipe Thread) connector, or an O-ring face seal connector. The design of the hydraulic interface of the loading module must ensure that it matches the interface of the hydraulic actuator of the landing gear device to achieve seamless connection. The flight simulation system sends instructions, and the hydraulic control valve group adjusts the flow of hydraulic oil according to the instructions, so that the landing device can complete actions such as retraction, extension, and locking. The hardware interface connected to the power system may use an aviation plug socket or a terminal block. Based on the instructions sent by the flight simulation system, the power system can supply power to the test piece 150.

[0047] The loading system implemented by the loading module 120 can provide a real mechanical interface of the landing gear, wheel brakes, and tires, and can realize vertical loading of the landing gear, wheel brakes, and tires, as well as deflection and roll control of the test object. For example, the process from extension to landing of the test object can be simulated in the landing phase, the taxiing and turning of the test object on the pavement can be simulated in the landing taxiing phase, and the process from extension to retraction of the test object in the take-off phase can be simulated.

[0048] The simulated onboard hydraulic and power supply system 130 provides a hydraulic and power supply system that simulates the hydraulic and power supply quality of the aircraft for the wheel brake system and the landing gear system, thereby effectively carrying out the control and testing of the real hydraulic landing gear system and the wheel brake system. In addition, the simulated onboard hydraulic and power supply system 130 can simulate the real power supply system to carry out the control and testing of multiple electrical systems such as electric brakes and electric turns. The simulated onboard power supply system can use a programmable power supply to simulate different voltage outputs, including stable voltages and variable voltages, and then simulate working conditions such as only RAT power supply or only battery power supply. In one embodiment, by combining the loading module 120 with the simulated onboard hydraulic and power supply system 130, landing gear retraction and extension tests, wheel brake tests, tire performance tests, etc. can be carried out.

[0049] The simulated airborne hydraulic system is unique for the landing gear buffer strut, for example, it uses aviation hydraulic oil and meets the hydraulic flow and high pressure requirements of the landing gear system under conditions such as retraction, turning, and braking. The simulated airborne power system can truly simulate the electrical load of the landing gear system, such as the working logic switching of the landing gear control unit in different flight phases, and can simulate the loss of some functions when only RAT power is supplied and only battery power is supplied.

[0050] The test trolley control system can also receive the engine speed simulation signal from the flight simulation system 140 to control the speed and acceleration of the test trolley, thereby simulating the forward speed of the aircraft. Thus, the test article 150 (e.g., aircraft landing device) can be tested for takeoff and landing at the simulated aircraft speed.

[0051] The mobile test system 100 may also include a data acquisition module (not shown), such as various sensors, video monitors, etc., for collecting test data when testing the aircraft landing device. The collected test data may be stored and / or transmitted to other devices (e.g., computers or servers) through a mobile positioning communication system for processing and analysis.

[0052] Although Figure 1 The test trolley control system, flight simulation system and mobile positioning communication system are shown separately, but any two or more of the systems and other electronic signal systems not shown can be implemented in combination. For example, the flight simulation system can be integrated with the test trolley control system, or the mobile positioning communication system can be integrated with the test trolley control system, or the three can be integrated together, etc.

[0053] The mobile test system of the present invention can travel on a real road surface, avoiding the inaccuracy caused by using a simulated road surface, and simulates the take-off or landing posture of the aircraft through a flight simulation system and a loading module, thereby effectively testing the ground operation quality and control characteristics of the aircraft landing device.

[0054] Figure 2 2 is a schematic diagram of a module vehicle 200 according to an embodiment of the present invention. The module vehicle 200 may be Figure 1 The module vehicle 200 may include a plurality of wheels, a frame and corresponding on-board equipment (not shown). The module vehicle 200 may have a path keeping / turning control system for enabling the module vehicle 200 to advance along a specified path or to make a turn. The module vehicle 200 may also have a speed control system for controlling the forward speed of the module vehicle 200. When a plurality of module vehicles are coupled to each other, each module vehicle 200 may advance at the same speed and may make a turn in coordination with each other. For example, the movement of a plurality of module vehicles may be coordinated and controlled by a test vehicle control system.

[0055] Figure 3is a schematic diagram of a loading module 300 according to an embodiment of the present invention. Figure (a) shows the loading module 300, which may have a loading control system (not shown) for receiving a loading control signal from a flight simulation system, so that the loading module 300 can simulate the flight attitude of the aircraft according to the loading control signal, such as load, lifting, side deviation, etc. The loading module 300 can be powered by the energy system (e.g., hydraulic pressure, power supply, etc.) of the test trolley to achieve various loading operations.

[0056] The loading module 300 has various hardware interfaces to dock with the test piece 310, and the test piece 310 can be an aircraft landing device, such as a tire, a brake system and / or a landing gear system. In one embodiment, the loading module 300 has a real mechanical interface of a landing gear, wheel brakes, and tires to realize vertical loading of the landing gear, wheel brakes, and tires, wherein the vertical loading can simulate the vertical load of the aircraft. The loading module 300 can also control the vertical speed of the test piece 310 to simulate the lifting and lowering of the aircraft. In addition, during the landing process of the aircraft, due to crosswind, improper operation of the pilot or other external factors, the fuselage may deflect, roll, and shift. The loading module 300 can deflect, roll, and / or displace the test piece, thereby simulating the deflection, roll, and shift in the take-off or landing posture.

[0057] The hardware interface of the loading module may also include an energy interface for providing energy (e.g., power or hydraulic pressure) from the simulated airborne hydraulic and power system 130 to the test piece 310. The flight simulation system sends instructions, and the hydraulic control valve group adjusts the flow of hydraulic oil according to the instructions, so that the test piece 310 (e.g., landing device) can complete the actions of retracting, releasing, locking, etc.

[0058] In one embodiment, the loading module 300 may include a six degree of freedom loading system. Figure 3 FIG. 1( b ) shows a schematic diagram of a six-degree-of-freedom loading system according to an embodiment of the present invention. The six-degree-of-freedom loading system may be a specific implementation of the loading module 120 .

[0059] The six-degree-of-freedom loading system mainly includes a fixed upper plate 41, six telescopic actuators (composed of a universal joint 42, an upper leg 43, a cylindrical joint 44, and a lower telescopic leg 45), and a movable lower plate 46. Six universal joints are set between the fixed upper plate 41 and the actuator, and three attachment points are set on the movable lower plate 46, so that the movable lower plate 46 has six degrees of freedom and can rotate and translate about the x-axis, y-axis, and z-axis. The movable lower plate 46 has a detachable joint to install different test pieces, which can realize the loading and lifting, loading and lateral deviation, loading and lateral displacement, and loading and tilting of the test piece.

[0060] Taking the tire test piece as an example, the loading lifting function can achieve a constant slow touchdown and a maximum accelerated touchdown speed of 3.05m / s for the tested tire. The loading sideways function can rotate the tested tire ±90° along the vertical line, with the rotation axis located at the center of the test bench. The loading sideways function can tilt the tire left and right ±5° in the vertical position. The loading sideways function can offset the tire's touchdown center relative to the rotation axis after the tire tilts, and can adjust the tire contact point on the rotation axis of the loading mechanism.

[0061] Figure 4 FIG. 4 is a schematic diagram of a loading module 400 according to another embodiment of the present invention. The loading module 400 may be a specific implementation of the loading module 120. Figure 4 Figure (a) shows a front view of the loading module 400, and figure (b) shows a schematic diagram of the internal structure of the loading module 400.

[0062] The loading module 400 mainly includes a loading actuator 410, a rotary actuator 412, a rotary gear mechanism 414, etc. The loading actuator 410 realizes the loading and lifting of the test piece. By adjusting the output force or displacement of the loading actuator 410, it can be ensured that the test piece is subjected to a predetermined loading force. The rotary gear mechanism 414 and the rotary actuator 412 realize the loading lateral deviation of the test piece. The rotary actuator 412 provides a stable rotational torque to rotate the test piece at a predetermined angle or speed. The rotary gear mechanism 414 transmits the power of the rotary actuator 412 to the part of the test piece, and realizes the power transmission and speed conversion through the gear meshing relationship inside it. In the process of loading lateral deviation, the rotary gear mechanism 414 can ensure that the rotational motion of the rotary actuator 412 is accurately transmitted to the test piece, while realizing the matching and adjustment of the speed.

[0063] Figure 5 Schematic diagram of a simulated airborne hydraulic and power supply system 500 according to an embodiment of the present invention. The simulated airborne hydraulic and power supply system 500 may include a simulated airborne hydraulic system and a simulated airborne power supply system. The simulated airborne hydraulic and power supply system 500 provides a hydraulic and power supply system with simulated aircraft quality for the wheel brake system and the landing gear system, and carries out control and testing of a real hydraulic landing gear system and a wheel brake system. At the same time, a real power supply system is provided to carry out control and testing of multiple electrical systems such as electric brakes and electric turns.

[0064] The simulated onboard hydraulic and power system 500 may include an onboard power simulation device 510 for providing power to the system, such as 230V, 115V, etc. onboard AC power, and 28V onboard DC power. In one embodiment, the DC / AC voltage output may be adjusted according to the test requirements.

[0065] The AC output of the airborne power simulation device 510 can be converted into DC via an inverter to charge the battery pack. When the airborne power simulation device 510 fails, the battery pack outputs a reserve DC voltage, and the inverter converts the DC power into AC power to power the airborne equipment.

[0066] The simulated airborne hydraulic system may include an oil source, an electric hydraulic pump, a pressure setting valve 520, and a flow regulating valve 530, etc. The oil source stores hydraulic oil and provides a continuous power source for the system. The electric hydraulic pump provides hydraulic power for the system, pumps the hydraulic oil from the oil source, and delivers it to the hydraulic interface on the interface 540 through the flow regulating valve 530 to supply oil to the load equipment (for example, the landing gear system, the wheel brake system). The electric hydraulic pump can adjust the speed and pressure output according to the test requirements. The pressure setting valve 520 can set the system pressure according to the test or actual flight requirements. The flow regulating valve 530 can adjust the flow of hydraulic oil to meet the needs of different systems or tests.

[0067] The flight simulation system 140 can simulate different flight phases of the aircraft according to the input instructions received on the user interaction panel or the remote controller (which can receive signals and output instructions), for example, provide the system cross-linking signals of the landing gear control system and the power supply and hydraulic energy in the stages of aircraft take-off, climb, cruise, descent, approach, etc., to realize the normal operation of the landing gear control system. Specifically, the flight simulation system 140 can output a hydraulic flow control signal to the flow regulating valve 530 to control the hydraulic flow. The flight simulation system 140 can also output a pressure control signal to the pressure setting valve 520 to control the hydraulic pressure. By controlling the hydraulic flow and hydraulic pressure, combined with the flight state (e.g., airspeed, altitude, etc.) simulated by the flight simulation system, the operating state of the real landing gear system in different flight phases can be simulated.

[0068] The hydraulic flow control signal and hydraulic pressure control signal generated by the flight simulation system 140 can simulate the real hydraulic flow and pressure state of the aircraft. The flight simulation system 140 can also generate a voltage control signal for controlling the voltage and frequency of the programmable power supply in the simulated onboard hydraulic and power system 500.

[0069] Interface 540 can provide connections for multiple power sources, multiple signal sources, and hydraulic sources. The hydraulic source can be in the form of a quick-release interface for convenient and quick connection or disconnection of hydraulic pipelines to avoid hydraulic oil leakage when connecting or removing hydraulic pipelines.

[0070] By controlling the onboard power simulation device 510 through the flight simulation system 140, the simulation of the aircraft power quality can be achieved. Through the flight simulation system, the onboard power simulation device 510 and the hydraulic simulation device can be controlled to simulate the power supply and hydraulic energy supply logic and quality on the aircraft, and at the same time, provide signals such as aircraft flight parameters to the test system under test. Through the electric hydraulic pump, hydraulic oil filter, pressure setting valve, flow regulating valve, oil source (purple oil or red oil source), hydraulic energy simulating the real state of the aircraft can be provided to the test system, and the flow of the hydraulic system is controlled by the flow regulating valve. As an example and not limitation, the pressure can be set according to the state, such as 21MPa, 28MPa or 35MPa.

[0071] Figure 6 is a signal flow diagram of a mobile test system according to an embodiment of the present invention. The mobile test system may be, for example, an embodiment of the mobile test system 100 described above.

[0072] In one embodiment, the test trolley control system 601 can monitor the position, speed, direction and other information of the test trolley in real time, and send the parameter information of the test trolley (such as trolley start signal, trolley speed, trolley acceleration, trolley direction, trolley position, pavement information, etc.) to the flight simulation system 602 in step 611, so as to provide basic data support for the flight simulation system 602, such as test scene setting and initialization of the flight simulation system 602, generation and update of attitude simulation signals, etc.

[0073] The user can provide input instructions on the remote controller or on the user interaction panel of the mobile test system. The remote controller can be separated from the mobile test system and can be fixed or movable, such as laboratory communication equipment, server, mobile terminal, etc. In step 612, the input instructions received on the remote controller or the user interaction panel can be passed to the flight simulation system 602. For example, the input instructions received on the remote controller can be passed to the mobile positioning communication system of the mobile test system, and further passed to the flight simulation system. The input instructions received on the user interaction panel of the mobile test system can be directly or indirectly passed to the flight simulation system.

[0074] In one embodiment, the input instructions may include a test control signal, which is used to simulate the pilot's operating instructions, such as operating instructions for take-off, climb, descent, landing, etc., thereby driving the test trolley to perform flight simulation according to a predetermined flight path and speed.

[0075] In one embodiment of step 612 , the test control signal received by the flight simulation system 602 may include control commands, such as takeoff, climb, descent, approach, landing, normal power supply, RAT power supply only, battery power supply only, etc.

[0076] The flight simulation system 602 may receive the test control signal (step 612), and generate an attitude simulation signal simulating the flight phase of the aircraft in combination with the trolley parameter information (step 611) collected from the test trolley control system 601. For example, the trolley speed and acceleration may simulate the flight speed and acceleration of the aircraft, and the flight simulation system 602 may generate an attitude simulation signal according to the corresponding flight phase (e.g., different phases in takeoff or landing) and the pavement information. The attitude simulation signal is used to simulate the flight state of different flight phases (e.g., takeoff, climb, descent, approach, landing, etc.).

[0077] The attitude simulation signal may include energy control signals (e.g., hydraulic flow control signals, hydraulic pressure control signals, voltage control signals), loading control signals, and / or engine speed simulation signals corresponding to flight states (e.g., flight speed, flight altitude, angle of attack, sideslip angle, pitch angle, rotation angle, engine speed, etc.) at different flight stages. The flight simulation system 602 may transmit the energy control signal to the simulated onboard hydraulic and power system 603 in step 613, transmit the loading control signal to the loading module 604 in step 614, and transmit the engine speed simulation signal to the test trolley control system 601 in step 615.

[0078] Therefore, by inputting test control signals such as flight phase and test piece test category through the operating panel (such as the user interaction panel of the test trolley or the remote controller), the flight simulation system can automatically output instructions to the test trolley control system, simulated airborne power supply and hydraulic system, and loading system according to the instructions of the operating panel, so as to simulate the corresponding flight attitude.

[0079] In step 621, the test trolley control system 601 can control the speed and acceleration of the test trolley according to the engine speed simulation signal provided by the flight simulation system 602, thereby simulating the forward speed of the aircraft. As an example and not a limitation, during the take-off and climb phases, the simulated engine speed can be gradually increased to simulate the acceleration process of the aircraft; during the approach and landing phases, the speed can be gradually reduced to simulate the deceleration process.

[0080] In step 622, the simulated onboard hydraulic and power system 603 can supply energy to the test piece (e.g., aircraft landing device) according to the energy control signal (e.g., hydraulic flow control signal, hydraulic pressure control signal, voltage control signal) provided by the flight simulation system 602, so that the aircraft landing device can perform takeoff or landing operations on the runway.

[0081] In step 623, the loading module 604 may load the test piece (aircraft landing device) according to the loading control signal, such as controlling one or more of the vertical speed, output displacement or force, rotation angle, and tilt angle of the aircraft landing device, to achieve one or more of the load, lift, side deviation, roll, lateral movement, etc. of the aircraft landing device, so as to simulate the pitch, roll, yaw and other postures of the aircraft during takeoff or landing.

[0082] By utilizing the forward speed of the test trolley to simulate the flight speed, the loading module 604 loads the aircraft landing device, and the onboard hydraulic and power supply system 603 is simulated to power the aircraft landing device for takeoff or landing operations, the takeoff or landing posture of the aircraft can be accurately simulated, thereby effectively testing the aircraft landing device.

[0083] When testing the aircraft landing gear, in step 624, the data acquisition module 605 (e.g., various sensors, cameras, etc.) may collect and save test data. As an example and not limitation, the test data may include tire friction, load deformation, landing gear support capacity, braking force, and brake temperature. In some embodiments, the data acquisition module 605 may send the collected test data to other devices (e.g., computers or servers) for processing and analysis. For example, the data acquisition module 605 may transmit the collected test data to other devices via a mobile positioning communication system.

[0084] In one embodiment, for example, when "landing" and "landing gear retraction and extension test" are input on the operating panel as test control signals, the flight simulation system will send a signal to the test trolley control system to control the test trolley to gradually reduce its speed; send instructions to the simulated airborne power supply system to adjust the distribution and output of power to ensure that each system can obtain the required power supply during landing and landing gear retraction and extension; send instructions to the simulated airborne hydraulic system to adjust the hydraulic pressure to meet the requirements of landing gear retraction and extension; send instructions to the loading module to adjust the size and direction of the loading force to simulate the impact force of the aircraft during landing or the resistance of the landing gear during movement.

[0085] Thus, the flight simulation system 602 can generate dynamically changing attitude simulation signals to simulate the flight state of the aircraft that can change in real time during various flight phases, thereby enabling the test trolley and loading module to more accurately test the ground operation quality and control characteristics of the aircraft.

[0086] As an example but not a limitation, the following embodiments are provided to illustrate a test working example of the mobile test system according to the present invention.

[0087] 1) Landing gear turning test and wheel brake test

[0088] System connection: Install the landing gear to be tested on the movable lower plate of the test bench (for example, the loading module), and connect the landing gear to be tested to the simulated onboard hydraulic system of the test bench (if the system to be tested adopts hydraulic drive) or the simulated onboard power supply system (if the system to be tested adopts electric drive) to ensure that all interfaces are well sealed to prevent unsafe incidents.

[0089] Flight simulation: Start the flight simulation system to simulate the engine speed, attitude, control instructions, etc. during the landing process. The flight simulation system simulates the energy supply status of the aircraft in different flight states, adjusts the onboard power supply simulation equipment or flow control valve and pressure setting valve through energy control signals, simulates the dynamic current / voltage or hydraulic pressure / flow status at the inlet of the system under test, and evaluates the ground control characteristics of the landing system under the energy supply status of the real aircraft. The energy supply status is affected by the engine speed, airspeed, aircraft attitude, weight center of gravity, etc. in the flight simulation.

[0090] Performance test: Under the energy supply conditions set by the flight simulation system, the loading module provides a simulated load of lift pressure (for example, aircraft weight) to perform performance tests on the landing gear retraction and extension system, landing gear turning system, and wheel brakes. Simulate and test the wheel rotation characteristics when the landing gear is lowered under different speed and load conditions and pavement conditions, simulate and test the angle deflection characteristics of the actual wheels under different turning angle control commands, and simulate and test the brake system's brake thermal capacity, brake length, brake system force and torque characteristics under different loads, speeds, pavements, and brake control commands.

[0091] 2) Tire performance test

[0092] Tire installation: Install the tire to be tested onto the movable lower plate of the test bench (e.g., loading module), ensuring that the connection between the tire and the test bench is firm and reliable.

[0093] Flight simulation: Start the flight simulation system to simulate the engine speed, attitude, control instructions, etc. during the landing process. The flight simulation system simulates different flight phases of the aircraft and outputs engine speed simulation signals, energy control signals, and loading control signals.

[0094] Loading module operation: Based on the loading control signal, the movement of the actuator is used to realize the loading lifting, loading sideways, loading lateral movement and loading sideways of the tire. As an example but not a limitation, in one embodiment, the loading module can control the vertical speed (3.05m / s, etc.), output displacement or force (related to the weight of the aircraft), rotation angle (about ±90°), tilt angle (about ±5°), etc. These actions can be flexibly combined and adjusted according to actual test requirements to simulate the complex working conditions of the tire in actual use.

[0095] Performance test: The tire performance test is carried out under the set speed, load and road surface conditions. The test content includes but is not limited to the tire's longitudinal, lateral and vertical force and torque characteristics on the runway. By adjusting the parameters of the loading system, the stress conditions of the tire under different working conditions are simulated to comprehensively evaluate its performance.

[0096] Figure 7 FIG. 7 is a flow chart of a mobile testing method 700 according to an embodiment of the present invention. The mobile testing method 700 may be used as follows: Figure 1 The mobile test system shown is used to perform the test.

[0097] In step 701, the test piece is docked with a loading module located on a vehicle body stand. The vehicle body stand has wheels to travel on a road surface. The test piece may include an aircraft landing device, such as a landing gear, a wheel brake method, a tire, etc. The road surface may include an asphalt runway, a cement runway, a concrete runway, a grassy field, a soil ground, a gravel ground, a water surface, etc., and the road surface may be a dry runway or a wet runway.

[0098] In step 702, a simulated attitude signal of the flight phase of the aircraft is generated in the flight simulation system according to the received test control signal, and the attitude simulation signal includes one or more of a loading control signal, an energy control signal, and an engine speed simulation signal. In one embodiment, parameter information of the test trolley (e.g., trolley start signal, trolley speed, trolley acceleration, trolley direction, pavement information, etc.) can be received in the flight simulation system, and the attitude simulation signal is further generated based on the parameter information of the test trolley.

[0099] In optional step 703, the acceleration and vehicle speed of the vehicle body test bench are controlled according to the engine speed simulation signal generated by the flight simulation system, thereby simulating the speed of the aircraft.

[0100] In step 704, the loading module is caused to load the aircraft landing device according to the loading control signal generated by the flight simulation system. In one embodiment, the loading module controls one or more of the vertical speed, output displacement or force, rotation angle, and tilt angle of the aircraft landing device according to the loading control signal to simulate the take-off or landing attitude of the aircraft. As an example and not limitation, the take-off or landing attitude includes one or more of lifting, load, side deviation, roll, and lateral movement.

[0101] In step 705, the simulated airborne hydraulic and power supply system located on the vehicle body test bench is used to provide hydraulic pressure and / or power supply to the aircraft landing device according to the energy control signal generated by the flight simulation system, so that the aircraft landing device performs a takeoff or landing operation on the runway, thereby testing the aircraft landing device. As an example and not a limitation, the test of the aircraft landing device includes one or more of a landing gear retraction test, a landing gear turning test, a wheel brake test, and a tire performance test.

[0102] In one embodiment, the energy control signal includes a voltage signal, and the simulated airborne hydraulic and power supply system provides power according to the voltage signal for the aircraft landing device to perform electric braking and / or electric turning tests.

[0103] In one embodiment, the energy control signal includes hydraulic flow and pressure signals, which are used to set the hydraulic flow of the flow regulating valve and the pressure state of the pressure setting valve in the simulated onboard hydraulic and power system, respectively.

[0104] In step 706, test data may be collected while testing the aircraft landing device. The collected test data may be stored and / or transmitted to other devices (eg, computers or servers) for processing and analysis.

[0105] As described above, the mobile test system (e.g., test trolley) of the present invention has multiple wheels and can move freely, so that it can travel on real aircraft runways in various states, thereby effectively testing the ground operation quality and handling characteristics of the test piece. In a preferred embodiment, the mobile test system of the present invention has a flight simulation system, which can simulate different flight phases of the aircraft and simulate other aircraft system signals or instructions associated with the tested specimen, thereby forming a complete aircraft landing system test loop and improving the accuracy of ground testing of aircraft landing equipment. In a preferred embodiment, the mobile test system of the present invention has a loading module that can simulate the take-off or landing posture of the aircraft (e.g., one or more of lifting, load, side deviation, roll, and lateral movement). In a preferred embodiment, the mobile test system of the present invention also has a simulated airborne hydraulic and power supply system, which can effectively test the ground handling characteristics of the landing gear, wheel brakes, and tires with the quality of the airborne hydraulic and power supply systems of a real aircraft.

[0106] The present invention can test the landing gear, wheel brake system and tires simultaneously or individually under different aircraft states, system states, pavement states and environmental states, and obtain high-confidence test data of the landing gear, wheel brakes and tires under different loads, different landing and taxiing states, different pavement states and different environmental states, which can be used to establish a high-confidence mathematical model, carry out landing gear, wheel brake system design, equipment selection and control characteristic simulation and test evaluation.

[0107] The various steps and modules of the methods and devices described above can be implemented with hardware, software, or a combination thereof. If implemented in hardware, the various illustrative steps, modules, and circuits described in conjunction with the present disclosure can be implemented or executed with a general-purpose processor, a digital signal processor (DSP), an application-specific integrated circuit (ASIC), a field programmable gate array (FPGA), or other programmable logic components, hardware components, or any combination thereof. The general-purpose processor can be a processor, a microprocessor, a controller, a microcontroller, or a state machine, etc. If implemented in software, the various illustrative steps and modules described in conjunction with the present disclosure can be stored on a computer-readable medium or transmitted as one or more instructions or codes. The software modules that implement the various operations of the present disclosure can reside in a storage medium, such as RAM, flash memory, ROM, EPROM, EEPROM, registers, hard disks, removable disks, CD-ROMs, cloud storage, etc. The storage medium can be coupled to a processor so that the processor can read and write information from / to the storage medium, and execute corresponding program modules to implement the various steps of the present disclosure. Moreover, the software-based embodiments can be uploaded, downloaded, or remotely accessed by appropriate communication means. Such appropriate communications means include, for example, the Internet, the World Wide Web, an intranet, software applications, cable (including fiber optic cables), magnetic communications, electromagnetic communications (including RF, microwave and infrared communications), electronic communications or other such communications means.

[0108] The numerical values ​​given in each embodiment are only examples and are not intended to limit the scope of the invention. According to specific practice, the specific parameters of each component can be appropriately set as needed, without being limited to the specific values ​​given as examples in this article. The various thresholds required in the implementation of the present invention can be appropriately selected as needed, without being limited to any specific values. In addition, as an overall technical solution, there are other components or steps that are not listed in the claims or description of the present invention. Moreover, a single name of a component does not exclude other names of the component.

[0109] It should also be noted that these embodiments may be described as a process depicted as a flow chart, flow diagram, structure diagram, or block diagram. Although the flow chart may describe the operations as sequential processes, many of these operations can be performed in parallel or concurrently. In addition, the order of these operations can be rearranged.

[0110] The disclosed methods, devices, and systems should not be limited in any way. On the contrary, the present disclosure covers all novel and non-obvious features and aspects of the various disclosed embodiments (alone and in various combinations and sub-combinations with each other). The disclosed methods, devices, and systems are not limited to any specific aspects or features or combinations thereof, nor do any disclosed embodiments require the existence of any one or more specific advantages or the resolution of specific or all technical problems.

[0111] The present invention is not limited to the above-mentioned specific embodiments, which are merely illustrative and not restrictive. Under the guidance of the present invention, ordinary technicians in this field can make many forms without departing from the scope of protection of the present invention and the claims, all of which belong to the protection scope of the present invention.

Claims

1. A mobile test system for an aircraft landing device, characterized in that: include: A vehicle body platform, the vehicle body platform having wheels for traveling on a road surface; A flight simulation system, wherein the flight simulation system generates an attitude simulation signal of a flight phase of a simulated aircraft according to the received test control signal, wherein the attitude simulation signal includes a loading control signal and an energy control signal; a loading module located on the vehicle body test bench, the loading module having a hardware interface for docking with a test piece, the test piece comprising an aircraft landing device, wherein the loading module loads the aircraft landing device according to the loading control signal generated by the flight simulation system; as well as A simulated airborne hydraulic and power supply system is located on the vehicle body test bench, and the simulated airborne hydraulic and power supply system provides hydraulic pressure and / or power supply to the aircraft landing device according to the energy control signal generated by the flight simulation system, so that the aircraft landing device can perform take-off or landing operations on the runway, thereby testing the aircraft landing device.

2. The mobile testing system for aircraft landing equipment according to claim 1, characterized in that: The loading module controls one or more of the vertical speed, output displacement or force, rotation angle, and tilt angle of the aircraft landing device according to the loading control signal to simulate the take-off or landing posture of the aircraft, and the take-off or landing posture includes one or more of lift, load, side deviation, and roll.

3. The mobile testing system for aircraft landing equipment according to claim 1, characterized in that: The energy control signal includes a voltage signal, and the simulated airborne hydraulic and power supply system provides power according to the voltage signal for the aircraft landing device to perform electric braking and / or electric turning tests.

4. The mobile testing system for aircraft landing equipment according to claim 1, characterized in that: The energy control signal includes hydraulic flow and pressure signals, and the simulated airborne hydraulic and power supply system includes a flow regulating valve and a pressure setting valve, which are respectively used to set the hydraulic flow and pressure states according to the hydraulic flow and pressure signals.

5. The mobile testing system for aircraft landing equipment according to claim 1, characterized in that: The attitude simulation signal also includes an engine speed simulation signal for controlling the acceleration and vehicle speed of the vehicle body test bench, thereby simulating the speed of the aircraft.

6. The mobile testing system for aircraft landing equipment according to claim 1, characterized in that: The flight simulation system receives the trolley parameter information of the mobile test system, and further generates the attitude simulation signal based on the trolley parameter information.

7. The mobile testing system for aircraft landing equipment according to claim 1, characterized in that: The road surface includes an asphalt runway, a cement runway, or a concrete runway, and the road surface is a dry runway or a wet runway.

8. The mobile testing system for aircraft landing equipment according to claim 1, characterized in that: The aircraft landing device includes one or more of the following: landing gear, wheel brake system, and tire. The test of the aircraft landing device includes one or more of the landing gear retraction and extension test, landing gear turning test, wheel brake test, and tire performance test.

9. A mobile testing method for an aircraft landing device, characterized in that: include: docking a test article with a loading module located on a vehicle body stand having wheels for traveling on a road surface, the test article including an aircraft landing device; Generating, in the flight simulation system, an attitude simulation signal of a simulated aircraft flight phase according to the received test control signal, wherein the attitude simulation signal includes a loading control signal and an energy control signal; enabling the loading module to load the aircraft landing device according to the loading control signal generated by the flight simulation system; and A simulated airborne hydraulic and power supply system located on the vehicle body test bench is used to provide hydraulic pressure and / or power supply to the aircraft landing device according to the energy control signal generated by the flight simulation system, so that the aircraft landing device can perform takeoff or landing operations on the runway, thereby testing the aircraft landing device.

10. The mobile testing method for aircraft landing equipment according to claim 9, characterized in that: The loading module controls one or more of the vertical speed, output displacement or force, rotation angle, and tilt angle of the aircraft landing device according to the loading control signal to simulate the take-off or landing posture of the aircraft, and the take-off or landing posture includes one or more of lift, load, side deviation, and roll.

11. The mobile testing method for aircraft landing equipment according to claim 9, characterized in that: The energy control signal includes a voltage signal, and the simulated airborne hydraulic and power supply system provides power according to the voltage signal for the aircraft landing device to perform electric braking and / or electric turning tests.

12. The mobile testing method for aircraft landing equipment according to claim 9, characterized in that: The energy control signal includes a hydraulic flow and a pressure signal, which are respectively used to set the hydraulic flow of the flow regulating valve and the pressure state of the pressure setting valve in the simulated onboard hydraulic and power system.

13. The mobile testing method for aircraft landing equipment according to claim 9, characterized in that: The attitude simulation signal also includes an engine speed simulation signal for controlling the acceleration and vehicle speed of the vehicle body test bench, thereby simulating the speed of the aircraft.

14. The mobile testing method for aircraft landing equipment according to claim 9, characterized in that: The trolley parameter information of the mobile test system is received in the flight simulation system, and the attitude simulation signal is further generated based on the trolley parameter information.

15. The mobile testing method for aircraft landing equipment according to claim 9, characterized in that: The road surface includes an asphalt runway, a cement runway, or a concrete runway, and the road surface is a dry runway or a wet runway.

16. The mobile testing method for aircraft landing equipment according to claim 9, characterized in that: The aircraft landing device includes one or more of the following: landing gear, wheel braking method, and tire. The test of the aircraft landing device includes one or more of the landing gear retraction and extension test, landing gear turning test, wheel braking test, and tire performance test.

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