Aircraft device test system and method based on full-voyage flight simulation

Abstract

The embodiment of the invention discloses an aircraft device test system based on full-voyage flight simulation, and the system comprises an aircraft control subsystem which is used for providing a test control instruction for a simulation flight subsystem; the simulation flight subsystem is used for sending a control instruction to a tested aircraft device according to the test control instruction and receiving test data of the tested aircraft device; carrying out full-voyage flight simulation, generating flight simulation data, and transmitting the flight simulation data to a performance calculation system; the tested aircraft device is used for testing according to the control instruction and sending the test data to the simulated flight subsystem; and the performance calculation subsystem is used for calculating flight performance according to the flight simulation data.

Description

Technical Field

[0001] This application relates to the technical field of high-lift system tests / experiments, and particularly to an aircraft device test system and method based on full-range flight simulation. Background Art

[0002] The design of civil aircraft is a collaborative design process involving multiple disciplines and specialties, and a large number of design cycles and iterations are required during the product system design process. With the development of modern computer technology and modeling and simulation, modeling and simulation can significantly improve the business level and become an important means in the design process of modern complex products. More and more aviation design units adopt virtual simulation technology of system modeling to optimize product design, reduce product development costs and development time. Therefore, aiming at the characteristics of multi-disciplinary coupling of civil aircraft, it is of great significance to accumulate, manage and reuse aircraft model data assets, carry out multi-disciplinary field modeling and simulation research, establish typical flight scenarios, complete virtual tests of aircraft systems, analyze performance indicators of aircraft under different scenarios, and the entire aircraft design process.

[0003] Taking the movable trailing edge as an example, the variable camber wing technology of the movable trailing edge (movable trailing edge technology) is to use the deflection combination of movable surfaces such as flaps, ailerons, and spoilers arranged on the trailing edge of the wing to change the spanwise load distribution of the wing according to flight conditions, improve the average lift-drag ratio in the cruise stage, and provide technical support for improving the fuel economy of aircraft products. This technology aims to achieve cruise drag reduction as the main goal, and at the same time realizes functions such as structural load reduction and buffeting delay. Among them, cruise drag reduction means that in the cruise stage, the inner and outer flaps cooperate to change the camber of the wing section to improve the lift-drag ratio of the aircraft; structural load reduction means that through the differential movement of the inner and outer flaps, the load is shifted inward to reduce the wing root bending moment; buffeting delay means that in the near-buffeting condition, the differential movement of the inner and outer flaps cooperates with the ailerons to increase the buffeting boundary.

[0004] The existing hardware-in-the-loop tests for movable trailing edge devices are closed-loop tests based on the equipment itself. The operator directly gives control commands for the equipment to judge the motion and working state of the equipment, and more considers the control and motion characteristics of the equipment itself, and cannot reflect the working characteristics of the equipment integrated in the system. For the flight characteristics brought by the movable trailing edge equipment itself, a more complete simulation framework still needs to be established, and then the flight characteristics during flight can be calculated according to the characteristics of the movable trailing edge equipment, and the benefits brought by the movable trailing edge device to the aircraft operation can be evaluated. In addition, the separate hardware-in-the-loop test lacks synchronous movement of the visual scene and simulation, and cannot achieve real-time comparison between simulation and physical object, which makes it difficult to intuitively reflect the difference between theoretical design and physical object feedback. Summary of the Invention

[0005] The embodiments of this specification provide an aircraft device test system and method based on full-range flight simulation to solve the technical problem of how to improve the test effect and efficiency of aircraft devices.

[0006] An embodiment of this specification provides an aircraft device test system based on full - flight - range flight simulation. The system includes:

[0007] An aircraft control subsystem, configured to provide test control instructions to the simulated flight subsystem;

[0008] A simulated flight subsystem, configured to send control instructions to the aircraft device under test according to the test control instructions, receive test data of the aircraft device under test; perform full - flight - range flight simulation, generate flight simulation data, and transmit the flight simulation data to the performance calculation system;

[0009] The aircraft device under test, configured to conduct tests according to the control instructions and send the test data to the simulated flight subsystem;

[0010] A performance calculation subsystem, configured to calculate flight performance according to the flight simulation data.

[0011] Optionally, the simulated flight subsystem includes one or more of an environment module, a flight control module, a landing gear module, an engine module, an aircraft body and aerodynamic module, and a runway pavement module.

[0012] Optionally, the simulated flight subsystem is built based on Modelica.

[0013] Optionally, the aircraft device under test is a movable trailing - edge device.

[0014] Optionally, the movable trailing - edge device includes a control subsystem and an actuating subsystem;

[0015] Wherein, the control subsystem is configured to communicate with the outside and control the operation of the actuating subsystem; and / or, the actuating subsystem is configured to drive the inner and outer flaps to generate actions.

[0016] Optionally, the control subsystem includes a control computer and a motor driver;

[0017] and / or,

[0018] The actuating subsystem includes one or more of a flap power drive device, a flap rotary actuator, a flap differential actuator, a wing - tip brake device, a torque - tube universal joint, and a position sensor.

[0019] Optionally, the aircraft control subsystem receives test information, generates test control instructions according to the received test information, and provides the test control instructions to the simulated flight subsystem;

[0020] Or,

[0021] The aircraft control subsystem generates test control instructions based on the test information stored therein and provides the test control instructions to the simulated flight subsystem.

[0022] Optionally, the system further includes:

[0023] A visual scene subsystem, configured to receive the flight simulation data sent by the simulated flight subsystem and perform information display according to the flight simulation data.

[0024] An embodiment of this specification provides an aircraft device test method based on full-range flight simulation. The method includes:

[0025] Obtain test control instructions;

[0026] Send control instructions to the aircraft device under test according to the test control instructions, so that the aircraft device under test performs tests according to the control instructions, and receive the test data of the aircraft device under test; and perform full-range flight simulation and generate flight simulation data;

[0027] Calculate flight performance according to the flight simulation data.

[0028] Optionally, calculating flight performance according to the flight simulation data includes:

[0029] Judge different flight phases through aircraft altitude and speed, and calculate flight performance in different flight phases.

[0030] At least one of the above technical solutions adopted in the embodiments of this specification can achieve the following beneficial effects:

[0031] Aiming at the characteristics of the aircraft device under test, an aircraft control subsystem, a simulated flight subsystem and a performance calculation subsystem are constructed, which support full-range flight simulation, can calculate the flight characteristics after the deployment of the aircraft device under test according to the flight simulation data, effectively support the calculation of the flight characteristic optimization results of the aircraft device under test under high simulation degree, and provide a test environment combining simulation test and semi-physical test for the application of the aircraft device under test, thereby improving the test effect and efficiency. Description of the Drawings

[0032] In order to more clearly illustrate the technical solutions in the embodiments of this specification or the prior art, the following will briefly describe the drawings required for the description of the embodiments of this specification or the prior art. Obviously, the following only illustrates the drawings required for some embodiments of this application. For those of ordinary skill in the art, other drawings can be obtained according to these drawings without creative efforts.

[0033] Figure 1It is a schematic diagram of the architecture of an aircraft device test system based on full-flight simulation provided by the first embodiment of this specification.

[0034] Figure 2 It is a schematic diagram of the architecture of the movable trailing edge device in the first embodiment of this specification.

[0035] Figure 3 It is a schematic diagram of the working process of an aircraft device test system based on full-flight simulation provided by the first embodiment of this specification.

[0036] Figure 4 It is a schematic diagram of the process of an aircraft device test method based on full-flight simulation provided by the second embodiment of this specification. Specific implementation manners

[0037] In order to enable those skilled in the art to better understand the technical solutions in this specification, the technical solutions in the embodiments of this specification will be clearly and completely described below with reference to the accompanying drawings. Obviously, the embodiments involved in the specific implementation manners are only a part of the embodiments of this application, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the specific implementation manners without creative efforts shall fall within the protection scope of this application.

[0038] The first embodiment of this specification (hereinafter referred to as "Embodiment 1") provides an aircraft device test system based on full-flight simulation, and the system includes:

[0039] An aircraft control subsystem, configured to provide test control instructions to the simulated flight subsystem;

[0040] A simulated flight subsystem, configured to send control instructions to the aircraft device under test according to the test control instructions, receive the test data of the aircraft device under test; and perform full-flight simulation, generate flight simulation data, and transmit the flight simulation data to the performance calculation system;

[0041] The aircraft device under test, configured to perform tests according to the control instructions and send the test data to the simulated flight subsystem;

[0042] A performance calculation subsystem, configured to calculate flight performance according to the flight simulation data.

[0043] The following is a specific description:

[0044] Aircraft control subsystem

[0045] The aircraft control subsystem can be used to set test information, which characterizes the specific content of flight simulation. For example, before performing simulation analysis on an aircraft, flight plans and control instructions of the aircraft are set, such as waypoints of the aircraft, preset altitudes of flight, scaling instructions for the landing gear of the aircraft, instructions for the aircraft flaps, and other test information. The test information can include various flight instructions, and the specific content of the test information is not limited.

[0046] The aircraft control subsystem can have a manual control mode and an automatic control mode.

[0047] In the manual control mode, test information can be received. For example, the above test information can be received from various devices such as hardware, a control device, or a control equipment by using an external function. Among them, the aircraft control subsystem can include a computer, a server, or other data processing devices. The hardware, control device, or control equipment includes, but is not limited to, an aircraft sidestick, a rudder pedal, or a throttle pedestal device. The external function can be deployed on the data processing device of the aircraft control subsystem for receiving and / or reading external instructions.

[0048] In the automatic control mode, the above test information can be predefined for the aircraft control subsystem, and then the program set on the aircraft control subsystem automatically controls the simulation flight subsystem to perform automatic flight according to the test information. For example, the test information can be defined by another computer or other devices and transmitted to the aircraft control subsystem for execution and storage, or the aircraft control subsystem itself can define and store the test information.

[0049] The aircraft control subsystem can provide test control instructions to the simulation flight subsystem according to the test information. For example, the aircraft control subsystem receives the test information, generates test control instructions according to the received test information, and provides the test control instructions to the simulation flight subsystem; or, the aircraft control subsystem generates test control instructions according to the test information stored in itself and provides the test control instructions to the simulation flight subsystem. In the process of generating test control instructions from the test information, necessary processing (such as data format conversion) may be required to generate test control instructions. If no processing is required, the test information can be directly used as the test control instructions.

[0050] In addition, the aircraft control subsystem and the simulation flight subsystem can be connected by wire or wirelessly in a suitable manner, so as to transmit the test control instructions to the simulation flight subsystem.

[0051] Simulation flight subsystem

[0052] The simulation flight subsystem can include one or more of an environment module, a flight control module, a landing gear module, an engine module, an aircraft body and aerodynamic module, and a runway pavement module.

[0053] Among them, the simulated flight subsystem can be built based on Modelica. That is, the simulated flight subsystem is a comprehensive system model or the aircraft body model, and this system model can include multiple sub-models built based on Modelica. These multiple sub-models can be respectively an environment module, a flight control module, a landing gear module, an engine module, an aircraft body and aerodynamic module, and a runway pavement module.

[0054] Specifically, the environment module builds an environment interaction model using the http data interface, inputs the aircraft position coordinates, and connects to the PostGIS spatial database in real time to obtain geographical data. That is, by inputting specific longitude and latitude positions, the encapsulated model is called, and the spatial database is called in the form of a dynamic library to obtain the geographical data of specific targets.

[0055] The flight control module mainly includes the aileron, elevator, rudder control units and the flap and slat control unit of the aircraft (where the flap part includes a movable trailing edge unit) to achieve aircraft control.

[0056] The engine module establishes the relationships between engine thrust, engine fuel consumption, throttle lever position, maximum thrust, maximum throttle lever position, flight Mach number, and altitude.

[0057] The landing gear module is mainly divided into a steering control unit, a brake control unit, and a landing gear retraction control unit. The aircraft body and aerodynamic module establish the aircraft shape and consider the aerodynamic forces acting on the aircraft during takeoff, landing, or in-flight. Among them, the aerodynamic forces mainly depend on factors such as the flight state of the aircraft, aircraft configuration, landing gear state, aerodynamic shape, and deflection angle of control surfaces.

[0058] The runway pavement module mainly considers different runway surface conditions and simulates and emulates the friction of the pavement, the resistance of obstacles, etc.

[0059] The aircraft under test device

[0060] What specific device the aircraft under test device is can be divided or defined according to needs, and Example 1 is not limited.

[0061] For example, the aircraft under test device is a movable trailing edge device. The movable trailing edge device is mainly used to control the synchronous movement and differential movement of the inner and outer flaps to achieve the lift augmentation function during takeoff and landing and the differential camber function of the inner and outer flaps during cruise.

[0062] Preferably, the movable trailing edge device includes a control subsystem and an actuation subsystem; among them, the control subsystem is used for external communication and controlling the operation of the actuation subsystem; and / or, the actuation subsystem is used to drive the inner and outer flaps to generate actions.

[0063] Preferably, the control subsystem includes a control computer and a motor driver; and / or, the actuation subsystem includes one or more of a flap power drive device, a flap rotary actuator, a flap differential actuator, a wingtip brake device, a torque tube universal joint, and a position sensor.

[0064] The aircraft device under test can conduct tests according to control instructions and feed back the generated test data to the simulated flight subsystem. The specific content of the test data is not limited.

[0065] Performance calculation subsystem

[0066] The performance calculation subsystem can perform various aircraft performance calculations, including determining different flight phases through aircraft altitude and speed, and supporting the calculation of flight performance under different flight phases. Among them, the calculation content that the performance calculation subsystem can perform includes but is not limited to: climb gradient, climb rate, fuel consumption, descent speed, descent rate, and the radius of the glide trajectory arc. If the aircraft device under test is a movable trailing edge device, the calculation content that the performance calculation subsystem can perform also includes: calculating the lift-drag ratio and lift coefficient relationship at different deflection angles of the inner and outer flaps for the movable trailing edge device, the relationship between the wing root moment and the angle of attack under the deflection of the inner flap and the inner and outer ailerons under typical working conditions, and the moment-lift coefficient curve at different deflection angles of the inner and outer flaps.

[0067] Visual scene subsystem

[0068] The aircraft device test system provided in the first embodiment may further include a visual scene subsystem, and the visual scene subsystem is used to receive the flight simulation data sent by the simulated flight subsystem and perform information display according to the flight simulation data.

[0069] The content of the first embodiment is further described below through examples (the first embodiment is not limited to the following examples):

[0070] Reference Figure 1, in this example, the aircraft device test system based on full - flight - course flight simulation includes an aircraft control subsystem, a simulated flight subsystem, a performance calculation subsystem, and a visual display subsystem. The aircraft device under test is a movable trailing - edge device. The aircraft control subsystem can include a computer or other devices with data - processing functions. The simulated flight subsystem and the performance calculation subsystem can both be deployed on a computer or other devices with data - processing functions. Preferably, the aircraft control subsystem, the simulated flight subsystem, and the performance calculation subsystem can share one computer, server, or other device with data - processing functions, or the programs of these three subsystems can be deployed on the same device, or the aircraft control subsystem, the simulated flight subsystem, and the performance calculation subsystem can be deployed on different computers, servers, or other devices with data - processing functions, or the aircraft control subsystem, the simulated flight subsystem, and the performance calculation subsystem all include a computer, server, or other device with data - processing functions. The visual display subsystem can include a computer, a display, or other devices with information - display functions.

[0071] Reference Figure 2 , the movable trailing - edge device includes a control subsystem and an actuating subsystem. The control subsystem is used for upper - computer communication and controlling the working mode, position closed - loop control, fault monitoring, and signal transmission of the actuating subsystem, etc. The control subsystem includes 1 test control computer and 2 motor drivers. The actuating subsystem is used for driving the inner and outer flaps to move synchronously, differentially, for fault braking, and position feedback, and includes 1 flap power driving device, 4 flap rotary actuators, 1 flap differential actuator, 1 wing - tip brake device, 7 torque - tube universal joints, and 1 position sensor.

[0072] The simulated flight subsystem can be deployed on a computer, server, or other device. The simulated flight subsystem is respectively connected to the aircraft control subsystem, the performance calculation subsystem, the visual display subsystem, and the aircraft device under test. The connection method is not limited for data transmission between them. For example, a UDP communication connection is established between the test control computer of the movable trailing - edge device and the simulated flight subsystem to obtain the control instructions of the movable trailing - edge device of the simulated flight subsystem.

[0073] In practical applications, reference Figures 1 to 3 , the working mode of the flight control subsystem can be set, and the flight can be started by manipulation. The working modes include a manual - manipulation mode and an automatic - manipulation mode, and different working modes can be custom - selected for simulation. Under the set working mode, test information is obtained, test control instructions are generated, and the test control instructions are transmitted to the simulated flight subsystem. [[ID=!]]

[0074] The simulated flight subsystem conducts full - flight - course flight simulation or flight simulation according to the test control instructions, including simulating or emulating aircraft flight data.

[0075] The simulated flight subsystem determines the control command for the maneuvering trailing edge device according to the test control command (since the experiment is conducted on the maneuvering trailing edge device, the test information and test control command may both contain relevant test commands for the maneuvering trailing edge device, and the simulated flight subsystem can determine the control command for the maneuvering trailing edge device based on this), and sends the control command for the maneuvering trailing edge device to the maneuvering trailing edge device, for example, to the test control computer. After receiving the control command, the maneuvering trailing edge device conducts tests according to the control command, for example, controls the synchronous movement and differential movement of the inner and outer flaps according to the control command, drives the inner and outer flaps to generate actions, and conducts corresponding deflections. The maneuvering trailing edge device feeds back its status to the simulated flight subsystem, including feedback of test data. For example, the position sensor, flap power drive device, and motor driver of the maneuvering trailing edge device feed back their status to the test control computer, and the test control computer feeds back its status to the simulated flight subsystem.

[0076] The simulated flight subsystem can also calculate flight simulation data, which includes various flight parameters. The flight parameters can be calculated after the maneuvering trailing edge device feeds back test data. The simulated flight subsystem transmits the flight simulation data required for performance calculation to the performance calculation subsystem; and transmits the flight simulation data required for visual display (such as visualization display parameters) to the visual display subsystem, for example, to the display device included in the visual display subsystem.

[0077] The performance calculation subsystem receives the flight simulation data transmitted by the simulated flight subsystem, calculates the performance indicators at different stages of the aircraft flight, and evaluates the flight performance or characteristics in the full flight process simulation.

[0078] In particular, the performance calculation subsystem can calculate the theoretical flight performance of the maneuvering trailing edge device simulated by the simulated flight subsystem (i.e., the simulation performance or simulated performance in the simulation environment) according to the flight simulation data, and can also calculate the actual performance of the maneuvering trailing edge device according to the test data actually fed back by the maneuvering trailing edge device, and compare the two; or, the performance calculation subsystem can compare the control command sent by the simulated flight subsystem to the maneuvering trailing edge device with the test data actually fed back by the maneuvering trailing edge device. Through these comparisons, the improvement of the aircraft flight state by the maneuvering trailing edge device can be reflected or evaluated. For example, the test data fed back by the maneuvering trailing edge device includes the different deflection positions of the inner and outer flaps fed back by the position sensor, based on which the matching of the command response and feedback of the physical device can be judged, and the lift-drag ratio and lift at different deflection position configurations can be confirmed.

[0079] Similarly, the above comparisons can be made separately for other types of tested aircraft devices.

[0080] The visual display subsystem forwards the flight simulation data transmitted by the simulated flight subsystem to the scene display software to visually display the entire aircraft flight process. For example, what the visual display subsystem shows is a simulated aircraft model, reflecting the flight situation of the aircraft. The flight simulation data received by the visual display subsystem may include the test data actually fed back by the movable trailing edge device. For example, the different deflection positions of the inner and outer flaps fed back by the position sensors, so that the simulated display of the flap movement can be realized.

[0081] Preferably, the visual display subsystem can use the UDP transmission protocol to transmit the flight simulation data to the scene display software for display.

[0082] In this example, it has been verified that the physical object of the movable trailing edge device has formed a semi-physical simulation environment, supporting external data access; the full-range flight simulation environment has formed a simulation closed-loop test environment based on Modelica, supporting the export of control instructions to the physical object of the movable trailing edge device.

[0083] In addition, in Embodiment 1, the movable trailing edge device adopts semi-physical simulation, which can realize closed-loop control at the device level and support the verification of control strategies.

[0084] Embodiment 1 can achieve the following beneficial effects:

[0085] Based on the full-range flight simulation, Embodiment 1 realizes the drive of the physical object of the aircraft device under test during the full-range flight simulation, and cooperates with the performance calculation system to realize the parameter calculation during the flight process, and can specifically calculate the working characteristics of the aircraft device under test during the flight process, evaluate the optimization effect, and effectively improve the test effect and efficiency.

[0086] Aiming at the characteristics of the aircraft device under test, an aircraft control subsystem, a simulated flight subsystem and a performance calculation subsystem are constructed, supporting full-range flight simulation. The flight characteristics after the deployment of the aircraft device under test can be calculated according to the flight simulation data, effectively supporting the calculation of the flight characteristics optimization results of the aircraft device under test under high simulation degree, and providing a test environment combining simulation test and semi-physical test for the application of the aircraft device under test, so as to improve the test effect and efficiency.

[0087] In particular, in Embodiment 1, the simulated flight subsystem is implemented relying on the Modelica model. Through the environment module, flight control module, landing gear module, engine module, aircraft body and aerodynamic module, and runway pavement module, simulated flight is carried out, which can better support the full-range flight simulation. In cooperation with the visual display subsystem, synchronous driving of the visual scene and the physical object of the device under test of the aircraft is achieved; in cooperation with the performance calculation subsystem, the flight characteristics can be calculated according to the flight simulation data after the deployment of the device under test of the aircraft, effectively supporting the calculation of the optimization results of the flight characteristics of the device under test of the aircraft under a high degree of simulation, and providing a test environment combining simulation testing and semi-physical testing for the application of the device under test of the aircraft.

[0088] In Embodiment 1, the aircraft control subsystem conducts operations, the model flight subsystem conducts simulation, the performance calculation subsystem conducts performance calculations, and the visual display subsystem conducts visual displays, forming a simulation loop. Moreover, in Embodiment 1, for the content of the simulation research, a part of the system of the object to be simulated is introduced into the simulation loop in the form of a physical object (or physical model). For example, for a physical object such as a maneuvering trailing edge device, through the simulation of the simulated flight subsystem, the maneuvering trailing edge device is introduced into the simulation loop, realizing a semi-physical simulation environment, thereby improving the test effect and efficiency.

[0089] Relying on the full-range flight simulation ability, Embodiment 1 can compare the differences between the performance of the physical object of the device under test of the aircraft and the simulation performance in real time, calculate the flight performance concerned by the device under test of the aircraft, as well as the improvement effect brought by the physical object of the device under test of the aircraft, so as to support and guide the design of the control scheme of the device under test of the aircraft and evaluate the benefits brought to the aircraft operation, which is conducive to improving the aircraft design efficiency.

[0090] Embodiment 1 realizes the comparison between semi-physical simulation and visual display. Relying on the movement of the physical object of the device under test of the aircraft, the degree of simulation visualization is improved. The movement of the physical object of the device under test of the aircraft and the movement effect of the simulation visual scene can be observed in real time, which is convenient for discovering problems existing in the movement of the physical object and guiding the development of the control strategy of the device under test of the aircraft.

[0091] In particular, the device under test of the aircraft can be a maneuvering trailing edge device. For the 3 functional usage scenarios of the maneuvering trailing edge device: the cruise drag reduction function is applicable to the cruise stage, and the two functions of structural load reduction and buffeting delay are applicable to both the cruise stage and the climb stage and the emergency descent stage. Embodiment 1 takes into account the actual application scenarios of each function and overcomes the deficiencies of semi-physical simulation to realize the test of the variable camber wing of the maneuvering trailing edge based on full-range flight simulation.

[0092] Embodiment 1 has a wide range of application scenarios. For example, it can be used for the test verification of the maneuvering trailing edge device of the high-lift system of civil aircraft, support the calculation and verification of the flight characteristics of the maneuvering trailing edge device, and support test visualization.

[0093] The second embodiment of this specification provides a method for testing an aircraft device based on full-flight simulation. Refer to Figure 4 , the method includes:

[0094] S101: Obtain test control instructions;

[0095] S103: Send control instructions to the aircraft device under test according to the test control instructions, so that the aircraft device under test conducts tests according to the control instructions, and receive the test data of the aircraft device under test; and conduct full-flight simulation and generate flight simulation data;

[0096] S105: Calculate flight performance according to the flight simulation data.

[0097] Preferably, calculating flight performance according to the flight simulation data includes:

[0098] Judge different flight phases through aircraft altitude and speed, and calculate flight performance in different flight phases.

[0099] The method described in the second embodiment can be executed by the aircraft device test system based on full-flight simulation described in the first embodiment. For example, the simulation flight subsystem in the first embodiment can obtain test control instructions from the aircraft control subsystem, send control instructions to the aircraft device under test according to the test control instructions, so that the aircraft device under test conducts tests according to the control instructions, and receive the test data of the aircraft device under test; and conduct full-flight simulation and generate flight simulation data.

[0100] The performance calculation subsystem in the first embodiment can calculate flight performance according to the flight simulation data.

[0101] The performance calculation subsystem in the first embodiment can judge different flight phases through aircraft altitude and speed, and calculate flight performance in different flight phases.

[0102] Information display can also be performed in the second embodiment. For example, the visual display subsystem in the first embodiment performs relevant information display.

[0103] For parts not described in detail in the second embodiment, refer to the first embodiment. The second embodiment can achieve the same beneficial effects as the first embodiment.

[0104] The above is only for the embodiments of this specification and is not used to limit this application. For those skilled in the art, various changes and modifications can be made to this application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of this application shall be included within the scope of the claims of this application.

Claims

1. An aircraft device test system based on full-flight simulation, characterized in that, The system includes: An aircraft control subsystem for providing test control instructions to the simulated flight subsystem; A simulated flight subsystem for sending control instructions to the aircraft device under test according to the test control instructions, receiving the test data of the aircraft device under test; and performing full-range flight simulation, generating flight simulation data, and transmitting the flight simulation data to the performance calculation system; The aircraft device under test for conducting tests according to the control instructions and sending the test data to the simulated flight subsystem; A performance calculation subsystem for calculating flight performance according to the flight simulation data.

2. The system according to claim 1, characterized in that, The simulated flight subsystem includes one or more of an environment module, a flight control module, a landing gear module, an engine module, an aircraft body and aerodynamic module, and a runway pavement module.

3. The system according to claim 1 or 2, characterized in that, The simulated flight subsystem is built based on Modelica.

4. The system according to claim 1, wherein The aircraft device under test is a movable trailing edge device.

5. The system according to claim 4, wherein The movable trailing edge device includes a control subsystem and an actuation subsystem; Wherein, the control subsystem is used for communicating with the outside and controlling the operation of the actuation subsystem; and / or, the actuation subsystem is used for driving the inner and outer flaps to generate actions.

6. The system according to claim 5, wherein The control subsystem includes a control computer and a motor driver; and / or, The actuation subsystem includes one or more of a flap power drive device, a flap rotary actuator, a flap differential actuator, a wingtip brake device, a torque tube universal joint, and a position sensor.

7. The system according to claim 1, characterized in that The aircraft control subsystem receives test information, generates test control instructions according to the received test information, and provides the test control instructions to the simulated flight subsystem; Or, The aircraft control subsystem generates test control instructions according to the test information stored in itself and provides the test control instructions to the simulated flight subsystem.

8. The system according to claim 1, wherein The system further includes: A visual scene subsystem for receiving the flight simulation data sent by the simulated flight subsystem and performing information display according to the flight simulation data.

9. An aircraft device test method based on full-flight simulation, characterized in that, The method includes: Obtaining test control instructions; Sending control instructions to the aircraft device under test according to the test control instructions, so that the aircraft device under test conducts tests according to the control instructions and receives the test data of the aircraft device under test; and performing full-range flight simulation and generating flight simulation data; Calculating flight performance according to the flight simulation data.

10. The method according to claim 9, characterized in that, Calculating flight performance according to the flight simulation data includes: Judging different flight phases through aircraft altitude and speed, and calculating flight performance in different flight phases.

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