Method for determining dynamic response of elastic aircraft

A determination method and aircraft technology, applied in the field of aircraft simulation, can solve problems such as the nonlinear characteristics of the flight dynamics equation of the destroyed rigid body, unfavorable dynamics modeling and simulation, etc.

Active Publication Date: 2021-09-14
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

[0003] The method for determining the dynamic response of an elastic vehicle mainly focuses on the rigid-elastic coupling modeling technology. In the implementation process, the traditional method needs to linearize the nonlinear dynamic equation of the rigid body with small disturbances, which destroys the rigid-body flight dynamic equation. Non-linear characteristics, and not conducive to dynamic modeling and simulation

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  • Method for determining dynamic response of elastic aircraft
  • Method for determining dynamic response of elastic aircraft
  • Method for determining dynamic response of elastic aircraft

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[0034] In order to make the objectives, technical solutions and advantages of the implementation of the application clearer, the technical solutions in the implementation modes of the application will be described in more detail below with reference to the drawings in the implementation modes of the application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the present application. The embodiments described below by referring to the figures are exemplary and are intended to explain the present application, and should not be construed as limiting the present application. Based on the implementation manners in this application, all other implementation manners obtained by persons of ordinary skill in the art without creative efforts fall within the scope of protection of this application. Embodiments of the pr...

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Abstract

The invention belongs to the technical field of aircraft simulation, and particularly relates to a method for determining the dynamic response of an elastic aircraft. The method comprises the following steps: S1, determining the aerodynamic resistance, lift force and pitching moment of a rigid body of the aircraft at the current moment; S2, determining modal coordinate dynamic response of elastic vibration of the aircraft according to the gust speed; S3, determining rigid body aerodynamic force correction caused by elastic deformation of the aircraft according to the modal coordinate dynamic response; S4, correcting the aerodynamic resistance, the lift force and the pitching moment of the rigid body in the step S1 based on the aerodynamic force correction of the rigid body to obtain corrected aerodynamic resistance, lift force and pitching moment of the aircraft; and S5, performing dynamic response solution on the aircraft according to the corrected aerodynamic resistance, lift force and pitching moment of the aircraft, updating the aerodynamic attack angle, elevator skewness and gust speed at the next moment based on a solution result, and returning to the step S1 for iterative calculation until simulation is finished. According to the invention, the simulation precision is improved.

Description

technical field [0001] The application belongs to the technical field of aircraft simulation, and in particular relates to a method for determining the dynamic response of an elastic aircraft. Background technique [0002] The dynamic response generally refers to the response of the output of the control system from the initial state to the final state under the action of a typical input signal. [0003] The method for determining the dynamic response of an elastic vehicle mainly focuses on the rigid-elastic coupling modeling technology. In the implementation process, the traditional method needs to linearize the rigid-body nonlinear dynamic equation with small disturbances, which destroys the rigid-body flight dynamic equation. Non-linear characteristics, and not conducive to dynamic modeling and simulation. Contents of the invention [0004] In order to solve the above technical problems, the application provides a method for determining the dynamic response of an elast...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/28G06F30/15
CPCG06F30/28G06F30/15G06F2119/14G06F2113/08Y02T90/00
Inventor 荆志伟王立波唐朕肖启之
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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