CN-121978984-A - Semi-physical simulation test platform of vertical take-off and landing single aircraft

CN121978984ACN 121978984 ACN121978984 ACN 121978984ACN-121978984-A

Abstract

The semi-physical simulation test platform of the vertical take-off and landing single aircraft comprises an aircraft semi-physical system, ground test equipment and a tool system, wherein the aircraft semi-physical system comprises a power component serving as a physical component, a physical sensor, a control mechanism, test equipment, an on-board computer, flight control software running on the on-board computer, a power simulator, a control simulator and a sensor simulator running on the on-board computer or the ground computer, the ground test equipment comprises a test controller and simulation dynamics software running on the ground computer, the tool system is used for connecting the platform with an external test device and comprises an on-board tool, a ground tool and a tool connecting piece, the on-board tool is used for fixing the aircraft semi-physical system, the ground tool is used for fixing the ground test equipment, and the tool connecting piece is used for movably and detachably connecting the on-board tool and the ground tool. By using the platform for testing, the cost can be effectively reduced, and the iteration period of the aircraft can be quickened.

Inventors

LUO GUANCHEN
WANG TING
PAN XUETAO
YAN MI
WANG YONGXING
WANG JING
DUO LAN
LI DEQUAN
ZHANG XIAOXIAN

Assignees

北京轩宇空间科技有限公司

Dates

Publication Date: 20260505
Application Date: 20251222

Claims (9)

1. The semi-physical simulation test platform of the vertical take-off and landing single aircraft is characterized by comprising an aircraft semi-physical system and ground test equipment; The aircraft semi-physical system comprises a power component, a control mechanism, test equipment, an on-board computer, flight control software, a power simulator, a control simulator and a sensor simulator, wherein the power component, the control mechanism, the test equipment and the on-board computer are used as physical components, and the flight control software is loaded and run on the on-board computer; the ground test equipment comprises simulation dynamics software which is loaded and operated on a ground computer and used for simulating dynamics environment; The simulation dynamics software is used for calculating and generating environment parameters and motion state parameters according to the received external input test matrix, task parameters and simulation initial values, motion state signals changed by the power component after executing the control command converted by the power simulator, and execution effect parameters of the control mechanism after executing the control command sent by the flight control software or simulation execution effect parameters of the control simulator after simulating and executing the control command sent by the flight control software, and sending the environment parameters and the motion state parameters to the sensor simulator and the power simulator; the sensor simulator is used for simulating sensor measurement data which is actually to be installed on the aircraft according to the environmental parameters and the motion state parameters; the flight control software is used for calculating and generating a control instruction for the power simulator and a control instruction for the control mechanism or the control simulator according to the measurement data simulated by the sensor simulator; the power simulator is used for simulating the response effect of the power component according to the control instruction of the flight control software and the environmental parameters and the motion state parameters sent by the simulation dynamics software, and forming an operation instruction of the power component by reverse pushing according to the response effect; The test equipment is used for collecting test data and downloading the test data to the simulation dynamics software.
2. The semi-physical simulation test platform of a vertical take-off and landing single person aircraft of claim 1 wherein the power component comprises a ducted fan engine or a propeller engine.
3. The semi-physical simulation test platform of a single vertical take-off and landing aircraft according to claim 1, wherein the test equipment is a follow-up test equipment on the aircraft, comprising at least one of a navigation equipment, a pressure and/or stress test equipment, a velocimeter, a barometer and a high-speed camera, and the navigation equipment comprises at least one of a satellite navigation device, an inertial navigation device and an astronomical navigation device.
4. The semi-physical simulation test platform of the vertical take-off and landing single-person aircraft according to claim 3, wherein the test equipment is at least one of a velocimeter, a barometer and a high-speed camera when used for a motion test; When the device is used for a linear motion test, the test equipment also selects at least one of a satellite navigation device, an inertial navigation device and an astronomical navigation device; When the device is used for rotation test, the test equipment also selects at least one of an inertial navigation device and an astronomical navigation device.
5. The semi-physical simulation test platform of the vertical take-off and landing single-person aircraft according to claim 3, wherein at least one of pressure and/or stress test equipment and a barometer is selected as the test equipment in the pneumatic test.
6. The semi-physical simulation test platform of a vertical take-off and landing single person aircraft of claim 1 wherein the platform has a first closed loop simulated flight test procedure comprising: the simulation dynamics software receives an external input test matrix, task parameters and simulation initial values as closed loop initial conditions; The simulation dynamics software sends environmental parameters of a simulation environment and motion state parameters of simulation motion to the sensor simulator and the power simulator; The sensor simulator simulates measurement data of a sensor actually to be installed on the aircraft according to the environmental parameters and the motion state parameters; The flight control software calculates and generates a control instruction for the power simulator and a control instruction for the control mechanism or the control simulator according to the measurement data simulated by the sensor simulator; the power simulator simulates the response effect of the power component according to the control instruction of the flight control software and the environmental parameter and the motion state parameter sent by the simulation dynamics software, and reversely pushes the response effect to form an operation instruction of the power component; The control mechanism executes the control instruction sent by the flight control software and feeds the execution effect parameter back to the simulation dynamics software, or the control simulator simulates and executes the control instruction sent by the flight control software and feeds the simulation execution effect parameter back to the simulation dynamics software; The simulation dynamics software combines the closed-loop initial conditions, the motion state signals and the execution effect parameters or simulates the execution effect parameters, and recalculates the environmental parameters and the motion state parameters to be transmitted.
7. The semi-physical simulation test platform of a single vertical take-off and landing aircraft according to claim 6, wherein the platform further comprises a tooling set for connecting the platform with an external test device; The entity part of the aircraft semi-entity system also comprises an entity sensor, wherein the entity sensor is a sensor set which is actually to be installed on the aircraft; the ground test equipment also comprises a test controller, a test control unit and a test control unit, wherein the test controller is used for starting the semi-physical simulation test platform to perform a test and sending a control instruction to an external test device; the tooling sleeve comprises an on-machine tooling, a ground tooling and tooling connectors; The on-board tooling is a tooling component of the aircraft semi-physical system, and is used for fixing a physical part of the aircraft semi-physical system and reinforcing a counterweight; the ground tool is fixed on the ground or an external test device and is used for fixing ground test equipment; The tool connecting piece is used for movably and detachably connecting the tool on the machine and the ground tool, and is used for temporarily fixing and assisting in protecting the tool on the machine and the entity part of the semi-physical system of the aircraft; the semi-physical simulation test platform of a vertical take-off and landing single aircraft according to claim 7, wherein the platform is further provided with a second closed-loop simulation flight test procedure, and the first closed-loop simulation flight test procedure or the second closed-loop simulation flight test procedure is selected to be executed when the platform is applied; the second closed loop simulated flight test procedure comprises: the simulation dynamics software receives an external input test matrix, task parameters and simulation initial values as closed loop initial conditions; The simulation dynamics software sends environmental parameters of a simulation environment and motion state parameters of a simulation motion to the test controller, the sensor simulator and the power simulator; The test controller calculates and generates a control instruction according to the environmental parameter and the motion state parameter, and sends the control instruction to the external test device so that the external test device can execute according to the control instruction; the sensor simulator simulates measurement data of a sensor actually to be installed on the aircraft according to the environmental parameters and the motion state parameters and sends the measurement data to the flight control software, wherein the measurement data simulated by the sensor simulator is used as the supplement of the measurement data acquired by the physical sensor; The flight control software combines the measurement data acquired by the physical sensor and the measurement data simulated by the sensor simulator, calculates and generates a control instruction for the power simulator and a control instruction for the control mechanism or the control simulator; the power simulator simulates the response effect of the power component according to the control instruction of the flight control software and the environmental parameter and the motion state parameter sent by the simulation dynamics software, and reversely pushes the response effect to form an operation instruction of the power component; The control mechanism executes the control instruction sent by the flight control software and feeds the execution effect parameter back to the simulation dynamics software, or the control simulator simulates and executes the control instruction sent by the flight control software and feeds the simulation execution effect parameter back to the simulation dynamics software; The simulation dynamics software combines the closed-loop initial conditions, the motion state signals and the execution effect parameters or simulates the execution effect parameters, and recalculates the environmental parameters and the motion state parameters to be transmitted.
8. The semi-physical simulation test platform of the vertical take-off and landing single aircraft according to claim 7, wherein the external test device is a ground test platform test device, a high-speed camera and a high tower or a high platform are selected for detecting a fault flow and a throwing test of emergency rescue equipment, a three-axis turntable is selected for detecting navigation precision and a turntable test of a guidance control flow, and a wind tunnel and a test machine matched with the wind tunnel are selected for detecting a mechanical test of a pneumatic load and a structure.
9. The semi-physical simulation test platform of a vertical take-off and landing single aircraft according to claim 8, wherein the simulation dynamics software is further used for adjusting parameters sent to the test controller according to test data downloaded by the test equipment so as to adjust control instructions sent by the test controller.

Description

Semi-physical simulation test platform of vertical take-off and landing single aircraft Technical Field The application belongs to the technical field of manned flight simulation test, and relates to a semi-physical simulation test platform of a vertical take-off and landing single aircraft. Background A number of pilot tests are required before the aircraft is set. Through flight tests, key components such as an avionics system, a transmission system and a power system of the aircraft can be comprehensively detected and evaluated, stability and reliability of the aircraft in a complex environment are ensured, various performance indexes of the aircraft can be verified, potential technical problems are found, and data support is provided for optimal design of the aircraft. The flight test requires a great deal of manpower and material resources, part of test projects are destructive tests, and the damage and consumption of the system to be tested and the auxiliary equipment and instruments thereof are more remarkable. Therefore, in the development process of the general aircraft, a semi-physical simulation test is introduced before the flight test, so that more potential technical problems are more rapidly and iteratively checked out with lower consumption, the optimization of the aircraft is promoted, the safety of the subsequent flight test is ensured, and the flight test effect is improved. Current vertical take-off and landing aircraft, especially single aircraft development, has been integrated with prototypes, but extensive and comprehensive flight tests are in progress. At present, the real object flight test is adopted, the test coverage is low, the safety is poor, and the consumption is extremely high. The urgent need is to establish a semi-physical simulation test platform matched with the test platform, realize the fusion of mathematical simulation and a physical model machine, and fly across the physical model. Disclosure of Invention Aiming at the defects of the related prior art, the application provides a semi-physical simulation test platform of a vertical take-off and landing single aircraft, which is used for indoor or outdoor low-altitude semi-physical simulation test, so that an aircraft system is rapidly and effectively verified, the cost is effectively reduced, and the iteration period is quickened. In order to achieve the above object, the present invention adopts the following technique: The semi-physical simulation test platform of the vertical take-off and landing single aircraft comprises an aircraft semi-physical system and ground test equipment; The aircraft semi-physical system comprises a power component, a control mechanism, test equipment, an on-board computer, flight control software, a power simulator, a control simulator and a sensor simulator, wherein the power component, the control mechanism, the test equipment and the on-board computer are used as physical components, and the flight control software is loaded and run on the on-board computer; the ground test equipment comprises simulation dynamics software which is loaded and operated on a ground computer and used for simulating dynamics environment; The simulation dynamics software is used for calculating and generating environment parameters and motion state parameters according to the received external input test matrix, task parameters and simulation initial values, motion state signals changed by the power component after executing the control command converted by the power simulator, and execution effect parameters of the control mechanism after executing the control command sent by the flight control software or simulation execution effect parameters of the control simulator after simulating and executing the control command sent by the flight control software, and sending the environment parameters and the motion state parameters to the sensor simulator and the power simulator; the sensor simulator is used for simulating sensor measurement data which is actually to be installed on the aircraft according to the environmental parameters and the motion state parameters; the flight control software is used for calculating and generating a control instruction for the power simulator and a control instruction for the control mechanism or the control simulator according to the measurement data simulated by the sensor simulator; the power simulator is used for simulating the response effect of the power component according to the control instruction of the flight control software and the environmental parameters and the motion state parameters sent by the simulation dynamics software, and forming an operation instruction of the power component by reverse pushing according to the response effect; The test equipment is used for collecting test data and downloading the test data to the simulation dynamics software. Further, the power components include ducted fan engines or propeller engines. Further, the test equipment