A method and system for on-board testing of aerodynamic parameters of a low-speed aircraft

Abstract

A vehicle-mounted testing method and system for aerodynamic parameters of a low-speed aircraft, the system comprising a vehicle (1), a force measuring bench unit (2) installed on the vehicle (1), a data acquisition unit (3), The control unit (4), the measurement and control unit (5); the measurement and control unit (5) sends the current test flight parameters to the control unit (4), and the control unit (4) sends the test flight parameters to the force measuring bench unit (2) according to the received flight parameters. Send corresponding control instructions; install aircraft or flight model on the force measuring bench unit (2), under the control of the control unit (4), the force measuring bench unit (2) adjusts the flight attitude of the aircraft or flight model; data acquisition The unit (3) collects the wind pressure on the head of the aircraft or the flight model, and sends the wind pressure to the measurement and control unit (5), and the measurement and control unit sends instructions according to the wind pressure to control the vehicle to adjust the driving speed, so that the head wind speed reaches the preset wind speed; and Notify the data collection unit (3) to collect the aerodynamic parameters of the aircraft or flight model and send them to the measurement and control unit (5) for storage.

Description

technical field [0001] The invention is suitable for the aerodynamic load test in the development stage of the low-speed aircraft so as to realize functions such as aerodynamic type selection, size parameter optimization and aerodynamic characteristic evaluation for the aircraft, and is especially suitable for the aircraft with a flight speed below 100m / s. Background technique [0002] For small-sized low-speed aircraft, the low Reynolds number effect of its flight is more significant, and under the strict constraints of external dimensions and power plant performance, it requires as long as possible flight time and range, which constitutes a certain problem for related aerodynamic design issues. challenge. [0003] Aiming at the problem of aerodynamic load measurement of low-speed aircraft flight in the early stage of development, there are three main methods commonly used at present: 1. Put the full-scale model or scaled model into the test system such as wind tunnel and t...

AI Technical Summary

Problems solved by technology

Wind tunnel tests are mostly suitable for the early development of low-speed aircraft, and can simulate the flight flow field. However, due to the size of the wind tunnel test section, only scaled model tests can be performed, and the test mechanism is complex, the flow field environment is single, and the flow field is disturbed. Larger, which increases the system error; numerical simulation technology simulates the flight flow field through the calculation program, and the calculation grid distribution, calculation format accuracy and other factors will affect the accuracy of the simulation results; the reliability of the test data obtained from the real flight test is good , but the cost is extremely high, and the test cycle is relatively long, and the supporting test method mechanism is complicated

Images