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Helicopter rotor airframe coupling system model and application thereof

A technology of helicopter rotor and coupling system, applied in the field of helicopter design, can solve the problems of difficulty in accurately predicting the dynamic stability of helicopters, without considering the influence of the body, etc.

Inactive Publication Date: 2012-10-10
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

But in the actual helicopter system, the vibration of the body will also affect the movement of the rotor blades, but this method does not consider the influence of the body on the rotor, so it is difficult to accurately predict the dynamic stability of the helicopter

Method used

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  • Helicopter rotor airframe coupling system model and application thereof
  • Helicopter rotor airframe coupling system model and application thereof
  • Helicopter rotor airframe coupling system model and application thereof

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Embodiment

[0047] In order to verify the validity of the helicopter rotor and airframe coupling system model proposed by the present invention and its application, this embodiment is adopted for verification. The model parameters of the helicopter rotor and airframe coupling system used are: 3 blades, the rotor radius is 0.81m, the section chord length is 0.0419m, the section airfoil is NACA 2301, the equivalent hinge overhang is 0.0851m, the blades are hinged The moment of inertia is 0.0173kg.m 2 , the natural frequencies of blade flapping and shimmy vibration are 3.14Hz and 6.70Hz respectively, the damping ratio of the shimmy vibration structure is 0.52%, and the pitching moment of inertia, restraint stiffness and damping ratio of the airframe are 0.607kg.m 2 、11.20kg.m.rad -1 and 3.2%, the body rolling moment of inertia, damping ratio and restraint stiffness are 0.177kg.m 2 、6.19kg.m.rad -1 and 0.929%.

[0048] Adopt the helicopter rotor and airframe coupling system dynamics model...

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Abstract

The invention discloses a helicopter rotor airframe coupling system model and application thereof, which are used for analyzing the dynamic stability judgment of articulated, hingeless and bearingless rotor helicopter systems and belong to the technical field of the design of a helicopter. In the invention, an equivalent paddle rigid model with an equivalent hinge overhanging beam or a 15-degree-of-freedom beam element model is used as a rotor paddle; a rigid model with the pitching and rolling degrees of freedom or a 15-degree-of-freedom beam element model is used as an airframe structure; and the aerodynamic force of the section of the paddle is calculated by utilizing the lifting line theory. A paddle motion equation, an airframe motion equation and an aerodynamic force model equation are subjected to simultaneous processing to form a motion equation set so as to obtain a motion equation of a helicopter rotor airframe coupling system; and the motion equation is solved to obtain the dynamic stability of the helicopter system. The helicopter rotor airframe coupling system model disclosed by the invention has higher reliability; and the dynamic stability of the helicopter system can be accurately analyzed by adopting a time domain analysis method.

Description

technical field [0001] The invention belongs to the field of helicopter design, in particular to a helicopter rotor body coupling system model, which can be used to judge the dynamic stability of the rotor body coupling system of articulated, hingeless and bearingless rotor helicopters. Background technique [0002] Helicopter system is a complex dynamical system, and dynamic stability is one of the basic issues in its dynamic design, among which ground and air resonance have always been the main considerations of designers. The main vibration sources of helicopters are various, mainly including main rotor system, tail rotor and engine. The helicopter system is extremely complex, mainly including the rotor and the body. Not only there are coupling effects such as flapping, shimmy and torsion inside the rotor blades, but also there are coupling effects between the rotor and the body. Exciting vibration. In order to improve the performance of the helicopter and avoid the dy...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCY02T90/00
Inventor 向锦武任毅如罗漳平郭俊贤张亚军黄明其
Owner BEIHANG UNIV
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