Low-speed aircraft aerodynamic parameter vehicle-mounted testing method and system

Abstract

The invention provides a low-speed aircraft aerodynamic parameter vehicle-mounted testing method and system. The low-speed aircraft aerodynamic parameter vehicle-mounted testing system comprises a carrier (1), a force measuring bench unit (2), a data collection unit (3), a control unit (4) and a measuring and controlling unit (5), wherein the force measuring bench unit (2), the data collection unit (3), the control unit (4) and the measuring and controlling unit (5) are mounted on the carrier (1); the measuring and controlling unit (5) transmits a current testing flying parameter to the control unit (4); the control unit (4) transmits a corresponding control instruction to the force measuring bench unit (2) according to the received flying parameter; an aircraft or a flying model is mounted on the force measuring bench unit (2); under the control of the control unit (4), the force measuring bench unit (2) adjusts a flying attitude of the aircraft or the flying model; the data collection unit (3) collects wind pressure of the head part of the aircraft or the flying model and transmits the wind pressure to the measuring and controlling unit (5); the measuring and controlling unit transmits an instruction according to the wind pressure to control the carrier to adjust a running speed so that the wind speed of the head part reaches a preset wind speed; and the data collection unit(3) is informed to collect aerodynamic parameters of the aircraft or the flying model and transmit the aerodynamic parameters to be measuring and controlling unit (5) to be stored.

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

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