Synthetic modeling method of rotor and airframe coupling dynamics modality

A technology of coupled dynamics and modeling methods, applied in the field of helicopter dynamics design, can solve problems such as the lack of research on multi-rotor helicopter rotor and airframe modeling and analysis methods, and achieve the effect of reducing scale, significant economic benefits, and reducing errors

Inactive Publication Date: 2016-01-20
CHINA HELICOPTER RES & DEV INST
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Problems solved by technology

At present, the helicopter models under research and development in China are all articulated, and the analysis models treat the blades and the body as rigid bodies. There is no m...

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  • Synthetic modeling method of rotor and airframe coupling dynamics modality
  • Synthetic modeling method of rotor and airframe coupling dynamics modality
  • Synthetic modeling method of rotor and airframe coupling dynamics modality

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Embodiment Construction

[0045] The dynamic modeling method of the multi-path power transmission rotor hub structure involved in the present invention will be further described in detail below with reference to the accompanying drawings.

[0046] Step 1: Define the coordinate system and conversion relationship

[0047] (1) figure 1 The coordinate system of the airframe and rotor hub is defined as shown. {Og,Xg,Yg,Zg} is the ground fixed coordinate system, the coordinate vector is expressed by {ig,jg,kg}, and the aircraft gravity is along the -kg direction. {O f ,X f ,Y f ,Z f } Is the body coordinate system, the coordinate origin Of is at the center of gravity of the whole machine, and the coordinate vector is {i f ,j f ,k f } Means that the 6 degrees of freedom of motion of the body relative to the coordinate system {ig,jg,kg} are X f ,Y f ,Z f , X f Forward is positive, Z f Up is positive, Y f The positive direction is determined by the right-hand rule.

[0048] {O H ,X H ,Y H ,Z H } Is the rotor hub co...

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Abstract

The invention discloses a synthetic modeling method of rotor and airframe coupling dynamics modality, and belongs to the dynamic design technology of helicopters. The synthetic modeling method of the rotor and airframe coupling dynamics modality is suitable for the dynamic stability and dynamic response analysis modeling of single-rotor and multi-rotor coupling. The synthetic modeling method analyzes the air resonance instability of a rotor blade by aiming at the rotor blade operation pneumatic environment of a flight state stipulated by a flight envelope rule which needs to considers to cover and properly exceed the performance requirements of the helicopter, researches the influence of high-speed high-overload flight state parameters, looks for the structural design parameters of rotors, blades and a steering control system which cause or affect the generation of the air resonance, and determines the instability boundary of the air resonance. Through the sensitivity analysis of the air resonance by the structural design parameters, a structural design parameter range which affects the air resonance is determined, and a design measure for expanding the security boundary of the air resonance is put forward.

Description

Technical field [0001] The invention belongs to the helicopter dynamics design technology, and in particular relates to a method for comprehensive modeling of the coupling dynamics mode of a rotor and a body. Background technique [0002] The design and analysis of the coupling stability of the rotor and the body occupies a very important position in the helicopter dynamics design. Its dynamic characteristics directly affect the safety, performance and quality of the helicopter. It is a key technology related to the success or failure of the helicopter model development. The research and development of type rotors (such as bearingless rotors) and multi-rotor helicopters has become the new direction of my country's helicopter development. The bearingless rotor uses a flexible beam to replace the horizontal hinge, vertical hinge and axial hinge of the traditional articulated rotor hub. Due to the complicated deformation of the flexible beam, the coupling of blade flapping, shimmy an...

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Application Information

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IPC IPC(8): G06F17/50
Inventor 凌爱民朱艳钱峰
Owner CHINA HELICOPTER RES & DEV INST
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