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Aircraft stability analysis method

An analysis method and technology for aircraft, applied in the fields of instruments, special data processing applications, electrical digital data processing, etc., can solve problems such as rapid system divergence, aircraft damage, inability to respond to complex flow phenomena and viscous effects of high-speed aircraft, and improve accuracy. performance, improved accuracy

Active Publication Date: 2019-09-27
BEIJING RES INST OF MECHANICAL & ELECTRICAL TECH
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Problems solved by technology

When the closed-loop loop is unstable, the system will diverge rapidly due to the disturbance of the external unsteady aerodynamic force, causing damage to the aircraft.
[0003] For the analysis of this problem, in the past, the aerodynamic model of the simplified plate panel method is coupled with the structure and control for stability analysis in the frequency domain. However, the calculation of unsteady aerodynamic forces by the plate panel method has limitations and cannot respond The complex flow phenomena and viscous effects of high-speed aircraft lead to inaccurate analysis results of the control stability of the aircraft

Method used

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Embodiment Construction

[0034] The present invention will be described in detail below in conjunction with specific examples and accompanying drawings.

[0035] Such as figure 1 As shown, an aircraft stability analysis method, the steps are as follows:

[0036] Step 1, divide the spatial grid of flow field CFD calculation according to the profile of aircraft, and carry out the fixed-field flow field calculation to the selected state of aircraft, this is known technology in the art;

[0037] Step 2, establishing a structural finite element model according to the aircraft structure and materials, which is a well-known technology in the art, preferably, such as figure 2 As shown, the structural finite element model and the space grid calculated by the flow field keep the same coordinate system and unit, and the flow field object surface is consistent with the geometric shape of the outer surface of the structure; Thermal modal analysis to obtain the modal frequency and mode shape of the aircraft, whi...

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Abstract

The invention provides an aircraft stability analysis method which comprises the following steps: establishing a space grid according to the appearance of an aircraft, and carrying out steady flow field calculation on a selected state of the aircraft to obtain an aerodynamic coefficient and a coefficient matrix; acquiring modal frequency and vibration mode of the aircraft; calculating the vibration mode of the flow field object plane; designing a modal training signal according to the structural characteristics of the aircraft; obtaining an elastic vibration expression formula of the aircraft; obtaining a generalized aerodynamic model of each mode; obtaining an aerodynamic state equation in the discrete space; extracting generalized aerodynamic models with different reduction frequencies; obtaining a pneumatic / structural / control coupled closed-loop system operation equation; and converting the closed-loop system operation equation into a transfer function, and carrying out stability analysis, thereby analyzing the stability of the aircraft. According to the method, the elastic deformation of the aircraft enters the influence on the control system, and the stability analysis accuracy of the control system is improved.

Description

technical field [0001] The invention relates to the stability analysis of aircraft aerodynamic / structure / control coupling, and belongs to the technical field of aircraft aeroelasticity. Background technique [0002] High-speed aircraft, especially air-breathing high-speed aircraft, put forward high requirements for lightweight structures, and the structural stiffness will inevitably decrease. At the same time, the thermal environment of long-term high-speed flight is harsh. Under the action of aerodynamic force and heat, elastic deformation and vibration will inevitably occur. The sensors installed on the aircraft not only receive the rigid body motion signal of the aircraft, but also receive the signal of structural elastic vibration. These signals in the sensor will be transmitted to the control system. The deflection movement of this part of the elastic vibration frequency is added to the commands given by the control system to the rudder surface through servo transmissio...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/23Y02T90/00
Inventor 苑凯华张伟伟刘凯程萌罗金玲操小龙
Owner BEIJING RES INST OF MECHANICAL & ELECTRICAL TECH
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