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Flight control system and method for wind tunnel virtual flight test

A flight control system and flight test technology, applied in the field of wind tunnel virtual flight test, can solve problems such as single function and inability to meet complex wind tunnel test requirements

Pending Publication Date: 2020-10-27
中国航空工业集团公司哈尔滨空气动力研究所
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In order to solve the problem of identifying the yaw angle of the model, the function is single, and cannot meet the requirements of complex wind tunnel tests, the present invention provides a flight control system for wind tunnel virtual flight tests. The specific scheme is as follows:

Method used

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  • Flight control system and method for wind tunnel virtual flight test

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specific Embodiment approach 1

[0026] Specific implementation mode 1: The flight control system and method of wind tunnel virtual flight test are described in conjunction with the accompanying drawings, and the specific implementation steps are as follows:

[0027] Step 1: The radio station establishes wireless communication with the flight control system, and the operator can remotely control the programmable autopilot or the power supply;

[0028] Step 2: The operator transmits the remote control command through the remote control, and after being received by the remote control receiver, the remote control command is sent to the programmable autopilot through the peripheral interface adapter, and the remote control and the remote control receiver together form a remote control control communication structure;

[0029] Step 3: The programmable autopilot transmits the instructions issued by the operator to the steering gear through the peripheral interface adapter to realize remote flight control.

specific Embodiment approach 2

[0030] Specific implementation mode two: In conjunction with the accompanying drawings, the flight control system of the wind tunnel virtual flight test uses the NI company sbRIO-9627 embedded controller as a programmable autopilot development platform. The controller uses FPGA as the core component, and the FPGA as the Field Programmable Gate Array (Field Programmable Gate Array), the module contains a number of gate circuits, the clock reference is 100 MHz, and any form of logic circuit and program circuit can be designed on this basis;

[0031] Due to the small size of the FPGA, multiple functions, and high integration, the overall structure of the flight control device is compact and the functions are complete, which can meet the various requirements of the wind tunnel virtual flight test for the flight control device. Through the high-speed pulse input and output function of FPGA, 10 PWM output ports are designed to realize the synchronous control of less than 10 servos; a...

specific Embodiment approach 3

[0032] Specific implementation mode three: combination figure 1 Explain that the flight control system of the wind tunnel virtual flight test uses the NI9627RIO embedded platform as the FPGA development platform, which supports 32-bit floating-point operations, which is convenient for motor control; XTEND is used as the data transmission station; the remote control and the receiver are all selected Futaba For the product, in order to increase the number of channels, FutabaT18SZ model remote control is selected, and R2008SB expandable remote control receiver is selected;

[0033] Other ancillary products use general-purpose products in the market to build a virtual flight test flight control device. The flight control program should include steering gear calibration, sensor calibration, control mode switching, control signal input channel control, data display and recording, etc. open-closed-loop control.

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Abstract

The invention relates to a flight control system and method for a wind tunnel virtual flight test, belongs to the field of wind tunnel virtual flight tests, and aims to solve problems of model yaw angle recognition, single function, incapability of meeting complex wind tunnel test requirements and the like. The system is composed of a programmable autopilot, a remote controller receiver, a remotecontroller, a power supply, an adaptive circuit, a radio station, a gyroscope, an encoder, a flight control program and the like. The three-degree-of-freedom supporting device is connected with a model supporting rod, and the flight control device controls a model control surface according to the control law and the control program; measurement of model attitude and attitude angular velocity is realized, meanwhile, wireless communication between equipment and an external computer is achieved, field manual operation of operators is omitted, control difficulty of the aircraft in the wind tunnelsimulation flight test is lowered, control efficiency is improved, problems that a development board is large in size and occupies model space are solved, the weight of the model is effectively reduced, and development difficulty is greatly lowered.

Description

technical field [0001] The invention relates to a flight control system and method for a wind tunnel virtual flight test, in particular to the flight control of a wind tunnel virtual flight test and belongs to the field of wind tunnel virtual flight tests. Background technique [0002] Wind tunnel virtual flight test is a wind tunnel test technology that has just started in China. The aircraft model is installed on a special support device with three rotational degrees of freedom in the wind tunnel, so that the three angular displacements of the model can be rotated freely or according to the flight of the aircraft. Real-time rudder control is required to simulate the maneuvering process of the aircraft more realistically, and the aerodynamic and motion parameters of the aircraft can be measured at the same time, and the response and control characteristics of the aircraft can be tested, so as to achieve the integration of aerodynamics and motion and explore the coupling mech...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/08G01M9/06
CPCG01M9/06G01M9/08
Inventor 王建锋芦士光谭浩杨文
Owner 中国航空工业集团公司哈尔滨空气动力研究所
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