Aircraft aero-servo-elasticity ground simulating test system

Abstract

The invention provides an aircraft aero-servo-elasticity (ASE) ground simulating test system which is applied to an aircraft capable of generating the ASE stability loss problem. The whole system comprises a test object aircraft (comprising a control and stability augmentation system), and a motion signal sensor, a central control computer, an aircraft pneumatic force number calculating model, a pneumatic force simulating loading device and the like which are arranged on the aircraft structure. The system carries out real-time measurement and processing on a motion signal of the aircraft, calculates the normal-stationary pneumatic force of the aircraft through a special algorithm on the basis of relevant theory, and realizes the pneumatic force simulating loading through a vibrator. The system is connected with the test aircraft to evaluate the ASE of the aircraft, and can be used for the improvement design of the control and stability augmentation system of the original aircraft and the verification research of the advanced control method.

Description

technical field [0001] The patent of the present invention relates to an aircraft aeroservoelastic ground simulation test system, which can realize the simulated loading of unsteady aerodynamic force of the aircraft, so as to complete the aeroservoelastic ground simulation test of the real aircraft. Background technique [0002] Real aircraft have a certain degree of elasticity, and the mutual coupling of the elastic force, inertial force, and unsteady aerodynamic force of the aircraft will cause aeroelasticity problems; the traditional aircraft control and stabilization system is designed to treat the aircraft as a rigid body. This approach ignores the impact of aircraft structural vibration and unsteady aerodynamic forces on the control and stability augmentation system, which may lead to aero-servo-elasticity (ASE) problems of the aircraft, which will reduce the stability of the aircraft and cause instability in severe cases. . At present, there are two main ways to stud...

AI Technical Summary

Problems solved by technology

[0002] Real aircraft have a certain degree of elasticity, and the mutual coupling of the elastic force, inertial force, and unsteady aerodynamic force of the aircraft will cause aeroelasticity problems; the traditional aircraft control and stabilization system is designed to treat the aircraft as a rigid body. This approach ignores the impact of aircraft structural vibration and unsteady aerodynamic forces on the control and stability augmentation system, which may lead to aero-servo-elasticity (ASE) problems of the aircraft, which will reduce the stability of the aircraft and cause instability in severe cases.

At present, there are two main ways to study the problem of aircraft aeroservoelasticity: one is numerical calculation, which requires mathematical modeling of the aircraft as the analysis object and its control and stability augmentation system. This process requires the introduction of many assumptions and it is difficult to consider the real Therefore, the analysis results only have a certain reference value; the other method is wind tunnel test, but the strict requirements of this method on model design and wind tunnel conditions also severely limit its feasibility.

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