Flight dynamics modeling method considering structure and pneumatic nonlinearity

A technology of flight dynamics and modeling methods, applied in CAD numerical modeling, instrumentation, geometric CAD, etc., can solve problems such as adverse effects of design, unstable motion modes, low rigid body free flutter velocity, etc.

Pending Publication Date: 2021-12-31
BEIHANG UNIV
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Problems solved by technology

[0005] (3) Coupling of the elastic motion of the structure and the rigid body motion of the whole machine: the flying wing layout is a typical representative of this problem. When the natural frequency of the flexible structure is very low, it will be coupled with the rigid body motion, which may lead to unstable motion modes or lower Rigid body free flutter speed, which has adverse effects on scheme design

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  • Flight dynamics modeling method considering structure and pneumatic nonlinearity
  • Flight dynamics modeling method considering structure and pneumatic nonlinearity
  • Flight dynamics modeling method considering structure and pneumatic nonlinearity

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Embodiment Construction

[0037] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and examples.

[0038] Such as figure 1 As shown, a flight dynamics modeling method considering structural and aerodynamic nonlinearity includes the following steps:

[0039] Step 1. Decouple the three-dimensional beam problem of the UAV structure into nonlinear beam motion analysis and beam section deformation analysis, and establish a nonlinear structural model of the UAV;

[0040] Step 2. Establish a nonlinear aerodynamic model of the UAV based on the aerodynamic reduced-order model;

[0041] Step 3, through the coupling of the UAV nonlinear structural model and the UAV nonlinear aerodynamic model, the UAV nonlinear aeroelastic model is established;

[0042] Step 4. Substituting the contribution items of the gravity load and the aerodynamic load and the boundary c...

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Abstract

The invention discloses a flight dynamics modeling method considering structure and pneumatic nonlinearity, and the method comprises the following steps: decoupling a three-dimensional beam problem of an unmanned aerial vehicle structure into nonlinear beam motion analysis and beam section deformation analysis, and establishing an unmanned aerial vehicle nonlinear structure model; establishing an unmanned aerial vehicle nonlinear aerodynamic model based on an aerodynamic reduced-order model, establishing an unmanned aerial vehicle nonlinear aeroelastic model through coupling of a structural model and an aerodynamic model, substituting contribution items and boundary condition items of a gravity load and an aerodynamic load into a structural semi-discretization equation, obtaining a nonlinear aeroelasticity and flight dynamics coupling model of the flexible aircraft, solving a static equilibrium solution of a system equation based on a Newton-Raphson method, and solving nonlinear time domain response by adopting a Generalized-alpha algorithm.

Description

technical field [0001] The invention belongs to the technical field of unmanned aerial vehicles, and in particular relates to a flight dynamics modeling method considering structure and aerodynamic nonlinearity, which can be used for considering structure and aerodynamic nonlinearity. Background technique [0002] In order to reduce the weight and increase the lift-to-drag ratio of the high-altitude and long-endurance aircraft, lightweight and anisotropic materials are used, and the wings are slender and flexible. Large structural deformation, aerodynamic stall, and coupling of low-frequency structural vibration and rigid body motion are common phenomena of high-altitude long-endurance flexible aircraft in conventional low-speed flight conditions, which significantly affect its aeroelasticity and flight dynamics characteristics. High-altitude and long-endurance UAVs have extremely important application value and development potential. However, in the face of demanding fligh...

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Application Information

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IPC IPC(8): G06F30/15G06F30/23G06F111/10G06F119/14
CPCG06F30/15G06F30/23G06F2111/10G06F2119/14Y02T90/00
Inventor李道春赵仕伟张健申童阚梓邵浩原姚卓尔
OwnerBEIHANG UNIV