A low-speed wind tunnel model flight test system and method

Abstract

The present invention discloses a low-speed wind tunnel model flying experimental system and a method. The system comprises an aircraft dynamic similarity ratio model, a model aircraft attitude measurement system, a rudder surface movement driving system, an engine power simulation system, a flight control system, a flight operation system, a wind tunnel operation system, and a safety protection system. The experimental system of present invention is equipped with the safety protection system, thus the aerodynamic characteristics of the model are not affected and the six-degree-of-freedom flying state of a real aircraft can be simulated, the thrust simulation of an engine can be realized, the flight control system and the flight operation system are added, the six-degree-of-freedom flying of the aircraft model in a wind tunnel testing segment can be realized through pilot operation, the aircraft air flying movement environment is fully simulated in the wind tunnel, and the pneumatic, flight mechanics and flight control characteristics of the aircraft can be researched in the wind tunnel.

Description

technical field [0001] The invention belongs to the technical field of wind tunnel experiments, in particular to a low-speed wind tunnel model flight experiment system and method. Background technique [0002] At the level of design concepts and methods of modern aircraft, multidisciplinary optimization design is more prominent, especially at the initial stage of design, it is necessary to fully consider and evaluate the impact of the flight control system on the overall performance of the aircraft, and conduct research and analysis on the flight mechanics and flight control characteristics of the aircraft. Experimental verification. [0003] As far as the existing research methods are concerned, the conventional static and dynamic wind tunnel experiments can study and analyze the aerodynamic characteristics of the aircraft and the flight dynamics characteristics of the aircraft body, but have the following disadvantages: First, it has a model support device, and the aerodyn...

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Problems solved by technology

[0003] As far as the existing research methods are concerned, the conventional static and dynamic wind tunnel experiments can study and analyze the aerodynamic characteristics of the aircraft and the flight dynamics characteristics of the aircraft body, but have the following disadvantages: First, it has a model support device, and the aerodynamic characteristics of the model The characteristics are affected to varying degrees; the second is that the angular motion or linear motion of the model is constrained to varying degrees, which cannot simulate the real six-degree-of-freedom flight state of the aircraft; the third is that only the characteristics of the aircraft body can be studied, and the flight control system cannot be studied Human-machine closed-loop control characteristics after stabilization

[0004] At present, the experimental verification of the flight mechanics and flight control characteristics of aircraft mainly depends on the free flight test of the atmospheric model and the flight test of the full-scale aircraft. System verification and confirmation, but in the early stage of aircraft development, when the aerodynamic, flight and control characteristics are not fully grasped, or in the face of new aerodynamic layouts, new control technology applications, etc., there is no relevant engineering experience, and it is difficult to carry out accurate When modeling and flight simulation research, directly carrying out this type of experimental verification faces problems such as high risk, high cost, and long cycle, and the experimental conditions are difficult to control, difficult to repeat, and easily affected by the weather

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