Design method of flight flutter test distributed full excitation input signal

Abstract

The invention provides a design method of a flight flutter test distributed full excitation input signal. The design method aims at solving the problem in the prior art that the excitation position ofa ground vibration testing point and a signal are difficult to select. A miniature temperature sensor, an airflow and vibration sensor and an image sensor are installed on an aircraft body, flight data of discrete time is obtained through a vibration flight test, on this basis, a grid point approximation model of aircraft vibration is built, a state space method is executed to describe an integration model of all grid points of an aircraft, an excitation signal deconvolution estimation method is given, and the technical problem in the prior art that the excitation position of the ground vibration testing point and the signal are difficult to select is solved.

Description

technical field [0001] The invention relates to a ground comprehensive test method for flight safety of civil aircraft, fighter jets, unmanned aerial vehicles and the like, in particular to a method for designing a distributed full excitation input signal for an aircraft flutter test, and belongs to the field of aerospace and information technology. Background technique [0002] Flutter is a large-amplitude vibration phenomenon that occurs when an elastic structure is coupled by aerodynamic, elastic, and inertial forces in a uniform airflow. For aircraft, vibration occurs after an uncertain disturbance in flight. At this time, due to the effect of the airflow, the elastic structure of the aircraft such as the wing, empennage or control surface will generate additional aerodynamic force; as an exciting force, the additional aerodynamic force will aggravate the vibration of the structure. At the same time, the damping force of the air on the aircraft structure tries to weaken...

AI Technical Summary

Problems solved by technology

[0005] Although the field of aviation and mechanics has conducted research on the problem of avoiding flutter earlier, the current research is still in its infancy, and a systematic theoretical method system has not been formed; the existing methods lack the equivalent ground flutter test methods and evaluation of aircraft ; Especially the prior art method is difficult to select the excitation position and signal of the ground flutter test point, making the ground flutter test difficult to model the results of the actual flight test

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