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Hypersonic flight vehicle wing flutter damage estimation method based on dynamic flight

A hypersonic, flight dynamic technology, applied in instrumentation, computing, design optimization/simulation, etc.

Active Publication Date: 2018-05-18
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0006] In order to solve the technical problems raised by the above-mentioned background technology, the present invention aims to provide a hypersonic aircraft wing flutter damage estimation method based on flight dynamics, which makes up for the fact that the existing flutter models are not linked to the flight dynamics of the entire aircraft and only consider local aircraft. Deficiencies in wing flutter damage, enabling more accurate prediction of wing flutter and estimation of real-time wing flutter damage

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  • Hypersonic flight vehicle wing flutter damage estimation method based on dynamic flight
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  • Hypersonic flight vehicle wing flutter damage estimation method based on dynamic flight

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Embodiment Construction

[0083] The technical solution of the present invention will be described in detail below in conjunction with the accompanying drawings.

[0084] Consider the binary wing model. Assuming that the air flow in each wing section is parallel and the force is the same, a two-degree-of-freedom model of the wing is established as figure 1 Shown. The bending and torsion deformation of the wing flutter can be equivalent to the rotation of the vertical bending spring and torsion spring around the rigid center. figure 1 The chord length of the middle wing is 2b, E is the rigid center, V is the flying speed of the aircraft, that is, the flight speed of the wing, d is the dimensionless distance from the elastic axis to the center of the wing, and x is any point on the wing to the leading edge of the wing. When the wing flutters, the displacement of any point on the wing can be expressed as z(x,t)=h(t)+(x-bd-b)α 1 (t), where α 1 (t) is actually tanα 1 (t), but due to α 1 The true value of (t) ...

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Abstract

The invention discloses a hypersonic flight vehicle wing flutter damage estimation method based on dynamic flight. The method comprises the following steps: establishing a flutter model of a hypersonic flight vehicle wing according to a lagrange equation, and solving unsteady aerodynamics and a torque thereof of the wing according to a piston theory; by combining the established wing flutter model, and on the basis of a considering longitudinal short-period dynamatic model of the elastically-fluttered hypersonic flight vehicle, establishing a more accurate wing flutter model and analyzing quasi-steady aerodynamics and a torque thereof; and analyzing the influence of a wing flutter stress on the flutter damage of the wing according to a stress-strain model and a strain-fatigue service lifemodel, establishing a damage dynamic model, and acquiring damage information of the hypersonic flight vehicle when the wing flutters in a flight task process in real time. By adopting the method, thedefects that the existing flutter model is not dynamically associated with the flight of the whole airplane and only the local wing flutter damage is considered can be overcome, the wing flutter can be more accurately predicted, and the real-time wing flutter damage can be estimated.

Description

Technical field [0001] The invention belongs to the technical field of aircraft flutter reduction control, and particularly relates to a hypersonic aircraft wing flutter damage estimation method based on flight dynamics. Background technique [0002] Reliability and rapidity make the hypersonic aircraft the most promising next-generation aerospace vehicle. The new generation of hypersonic aircraft widely adopts new lightweight and high-strength composite materials. The selection of special structural materials and aerodynamic layout will bring new aeroelasticity. problem. In high-speed flight, the wing is the main lift surface of the aircraft. Due to the existence of structural nonlinearity and aerodynamic nonlinearity, the coupling of elastic force, inertial force and aerodynamic force can easily cause a complex self-excited vibration-flutter. When an aircraft is flying at hypersonic speed, the aerodynamic force received by the wing will increase with the increase of the airflo...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/20
Inventor 王玉惠张晓辉吴庆宪冯星凯陈谋侯思远徐超
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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