A Method of Improving the Elastic Stability of Pneumatic Servo

Abstract

The invention discloses a design method for improving the elastic stability of aerodynamic servo, which adopts the whole machine ground resonance test or the whole machine ground structure modal coupling test data design optimization technology to correct the body elastic model and transfer function, and then uses the flight control law to dynamically adjust the parameters technology to improve the elastic stability of aerodynamic servo; the present invention can take into account the coupling relationship between aerodynamic force, structural elasticity and control systems, so as to meet flight quality requirements, control system stability margin requirements, and aerodynamic servo Elastic stability requirements have been applied and verified in multi-control surface UAVs. It solves the problem that the aeroservoelastic stability of a multi-control surface unmanned aerial vehicle is difficult to control.

Description

technical field

[0001] The invention belongs to the field of joint design of aviation flight control and aerodynamic servo elasticity, and in particular relates to a method for improving the stability of aerodynamic servo elasticity. Background technique

[0002] Aeroservoelasticity refers to the mutual coupling characteristics of aircraft structural dynamics, unsteady aerodynamic force and servo control system (including inertial set, stability augmentation control law and steering gear). As an elastic aircraft as an automatic control object, the sensors on the body not only receive the rigid body motion signal of the aircraft, but also receive the elastic vibration signal of the structure, which is converted into the deflection signal of the control surface through the servo control system, thereby forming the aerodynamic control force; In turn, the control forces affect the elastic vibrations of the structure. The structure and control feed back each other, forming a pne...

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