Simulation analysis method and system for gust response of elastic aircraft

Abstract

The invention belongs to the technical field of aircraft simulation, and particularly relates to a simulation analysis method and system for gust response of an elastic aircraft. The method comprisesthe steps of according to the dynamics and the structure correspondence of the elastic aircraft under gust excitation, firstly, modeling an aircraft six-degree-of-freedom system, the atmospheric turbulence, the gust excitation and the aerodynamic force data according to the flight state; secondly, under the condition of static elasticity, analyzing the deformation of the aircraft wing under the aerodynamic force load and the change of an angle of attack and the influence of the angle of attack on an aerodynamic coefficient, correcting the aerodynamic coefficient to enable the aerodynamic coefficient to better conform to the real flight state of the elastic aircraft, and finally, connecting all the modules into a system to realize the corresponding analysis under the excitation of gust of the elastic aircraft. The system achieves a good effect in cases of a general aircraft and a civil large-scale passenger plane.

Description

technical field [0001] The invention belongs to the technical field of aircraft simulation, and in particular relates to a simulation analysis method and system for an elastic gust response of an aircraft. Background technique [0002] Accurate aircraft simulation model plays an important role in the design and analysis of aircraft control system. The actual motion of the aircraft in the air is very complicated, not as pure and direct as the simplified motion model in textbooks for the convenience of explaining the problem, and will be affected by various factors such as airflow, speed, temperature, and air compressibility. Simulation analysis is an experimental method that is non-destructive, can be individually controlled, can be repeated many times, is not limited by actual working conditions, and can realize very complete functions. The use of simulation experiments can deepen researchers' understanding of the actual system, quickly find out the causes of problems in th...

AI Technical Summary

Problems solved by technology

Since the mid-20th century, researchers have defined aeroelasticity as an independent branch of science and have continued to develop. Although the results of their research have reduced the number of accidents caused by elastic problems, there are still some serious accidents: In the 1960s, the unmanned target drone developed by Beijing Academy of Aeronautics crashed due to the instability of the airframe caused by aeroelasticity; Hyper-X program hit hard

It is difficult for the usual wind tunnel experiments to fully satisfy the above two conditions. The most common case where the similarity criterion is not satisfied is that the Reynolds number of the sub-transonic wind tunnel does not match.

Taking the Boeing 737 as an example, the aircraft flies at a cruising speed of 927 kilometers per hour at a cruising altitude of more than 9,000 meters, and its Reynolds number reaches Re=2.4×107. The Reynolds number is only about Re=1.4×106 in the case of 1.5 meters, the difference is large, and the experimental results will be affected

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