A vehicle-mounted force measurement system for low-speed aircraft

Abstract

The invention discloses a low-speed aircraft vehicle-mounted force measuring system. The low-speed aircraft vehicle-mounted force measuring system includes a testing platform (1), a posture adjustingunit (2), a model supporting unit (3), an aerodynamic parameter measuring unit (4) and a six-component force measuring balance (5); the testing platform (1) is fixed in a car hopper of a car, the posture adjusting unit (2) is fixedly connected with the testing platform (1), the model supporting unit (3) is fixedly connected with the posture adjusting unit (2), the six-component force measuring balance (5) is mounted on the model supporting unit (3), the balance is fixedly connected with a to-be-tested model, and measuring of force and moment of force in the three-dimensional direction of the to-be-tested model is achieved; and the fixed position of the aerodynamic parameter measuring unit (4) is consistent with the height of the to-be-tested model, horizontal distance is 400-500mm, the posture of the to-be-tested model can be changed in pitching and yaw direction under the action of the posture adjusting unit, and aerodynamic parameters of the to-be-tested model under different statesare measured by the aerodynamic parameter measuring unit (4).

Description

technical field [0001] The invention relates to a low-speed model vehicle-mounted dynamometer system, which is mainly suitable for the aerodynamic load test in the development stage of low-speed aircraft so as to realize functions such as aerodynamic type selection, size parameter optimization, and aerodynamic characteristic evaluation of the aircraft. 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 test ...

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