Aircraft aerodynamic servo elastic ground simulation test system

Abstract

The invention provides an aircraft aero-servo-elasticity (Aero-servo-elasticity, ASE) ground simulation test system, and its application object is an aircraft that may have the problem of aero-servo-elasticity instability. The whole system includes: the test object aircraft (including the control stability augmentation system), the motion signal sensor installed on the aircraft structure, the central control computer, the aircraft aerodynamic numerical calculation module, the aerodynamic simulation loading device, etc. This system measures and processes the motion signal of the aircraft in real time, calculates the unsteady aerodynamic force of the aircraft through a specific algorithm on the basis of relevant theories, and realizes the aerodynamic simulation loading through the vibrator. This system is connected with the test aircraft to evaluate the aeroservoelastic stability of the aircraft, and can be used for the improved design of the original aircraft control stability augmentation system and the verification research of advanced control methods.

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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