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Method for improving elastic stability of pneumatic servo

A technology of servo elasticity and aeroelasticity, which is applied to aircraft parts, ground devices, sustainable transportation, etc., can solve problems such as the limited capacity of aerodynamic servo elasticity, and achieve the effect of solving coupling problems and accurate analysis

Active Publication Date: 2020-06-26
CHENGDU AIRCRAFT INDUSTRY GROUP
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Problems solved by technology

However, the complex coupling between aerodynamics, structural elasticity, and control systems makes it necessary to consider flight quality and requirements, control system stability margin requirements, and aeroservoelasticity stability requirements to improve aeroservoelasticity, which is a complex multidisciplinary optimization technology. problem, so traditional methods have limited ability to improve pneumatic servo elasticity

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  • Method for improving elastic stability of pneumatic servo
  • Method for improving elastic stability of pneumatic servo
  • Method for improving elastic stability of pneumatic servo

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Embodiment 1

[0027] The invention is a method for improving the elastic stability of pneumatic servo, combining figure 1 , figure 2 , image 3 , Figure 4 , Figure 5 , Image 6 As shown, taking a certain type of unmanned aerial vehicle as an example, the principle is as follows figure 1 , as shown, first establish the body elastic model and transfer function, and perform model correction in combination with the ground resonance test of the whole machine and the structural modal coupling test of the whole machine; figure 2 As shown in the process flow, the influence of aircraft control law parameters on the aeroservoelastic stability and flight quality is studied, and on this basis, the control law is dynamically adjusted and optimized to make the aircraft meet the flight quality and aeroservoelastic stability requirements at the same time;

[0028] The finite element model of the whole machine is calibrated by the ground resonance test of the whole machine; the free horizontal flig...

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Abstract

The invention discloses a design method for improving the elastic stability of an aerodynamic servo. The method comprises the steps: correcting a body elastic model and a transfer function through employing a whole-plane ground resonance test or whole-plane ground structure modal coupling test data design optimization technology, and then improving the elastic stability of the aerodynamic servo through employing a flight control law dynamic parameter adjustment technology; the aerodynamic force, the structural elasticity and the coupling relation between control systems can be well considered,so that the flight quality requirement, the stability margin requirement of the control systems and the pneumatic servo elastic stability requirement are met within the full envelope range, and the method is already applied and verified in the multi-control-surface unmanned aerial vehicle. The problem that the pneumatic servo elastic stability of a multi-control-surface unmanned aerial vehicle isdifficult to control is solved.

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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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/00
CPCB64F5/00Y02T90/00
Inventor 韩婵张瞿辉徐焱
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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