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Longitudinal helicopter rotor and fuselage coupling stability modeling method

A technology of helicopter rotor and modeling method, which is applied in the field of coupling stability modeling of tandem helicopter rotor and fuselage, and can solve problems such as changing the coupling type and mechanism change of the fuselage and rotor

Active Publication Date: 2021-04-02
CHINA HELICOPTER RES & DEV INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, the difference between two rotors and one rotor is not just the difference between two and one, it may change the coupling type of the airframe and the rotor, resulting in a change in mechanism

Method used

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  • Longitudinal helicopter rotor and fuselage coupling stability modeling method
  • Longitudinal helicopter rotor and fuselage coupling stability modeling method
  • Longitudinal helicopter rotor and fuselage coupling stability modeling method

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Embodiment Construction

[0036] The tandem helicopter rotor-body coupling stability modeling method involved in the present invention will be described in further detail below in conjunction with the accompanying drawings.

[0037] Step 1: Establish the coordinate system of each system and the relationship between coordinate systems. Establish the inertial coordinate system, the body coordinate system, the rotor hub coordinate system, the rotor rotation coordinate system, the rotor blade flapping coordinate system, the rotor blade shimmy coordinate system, and the rotor blade variable pitch coordinate system, such as figure 1 shown.

[0038] The configuration and blade structure parameters of the front and rear rotors of the tandem helicopter are exactly the same, the front rotor rotates counterclockwise from the top view, and the rear rotor rotates clockwise from the top view. The front and rear rotors are connected to the fuselage through the centers of their hubs, and there is no direct coupling b...

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Abstract

A longitudinal helicopter rotor and fuselage coupling stability modeling method belongs to the helicopter dynamics modeling and analysis technology, adopts a fully-articulated rigid blade model, and comprises the following steps: firstly, establishing coordinate systems of all systems and relationships among the coordinate systems, establishing a fuselage motion model, a rotor motion model and anaerodynamic model; after rotor coupling response solving and multi-blade coordinate transformation, combining a rotor body undercarriage blade model mass damping stiffness matrix, establishing a tandem double-rotor helicopter ground resonance analysis model, calculating ground resonance by adopting a characteristic value method, and judging ground resonance stability through a characteristic valuereal part. The model can be used for calculating and analyzing the ground resonance stability of the tandem double-rotor helicopter, and key technical support is provided for model design and modification development.

Description

technical field [0001] The invention belongs to helicopter dynamics modeling and analysis technology, and relates to a tandem helicopter rotor and fuselage coupling stability modeling method. Background technique [0002] With the continuous expansion of the application field of tandem helicopters, it plays an increasingly important role in the fields of military affairs, mining, fire protection, emergency rescue and relief, ocean development, engineering transportation, and infrastructure construction. In the Gulf War, Kosovo, Afghanistan and Iraq wars, tandem helicopters showed irreplaceable advantages and played an important role. During the Vietnam War, tandem helicopters played a great role. [0003] Tandem helicopters can quickly and effectively complete battlefield maneuvering tasks. Tandem helicopters are not limited by ground conditions, and can accurately transport combat personnel and materials to predetermined locations. This is its main task and one of its mai...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F30/23G06F30/28G06F111/04G06F113/08G06F113/28G06F119/14
CPCG06F30/15G06F30/23G06F30/28G06F2111/04G06F2113/08G06F2113/28G06F2119/14Y02T90/00
Inventor 朱艳孙凤楠冯志壮程起有钱峰刘晨代志雄
Owner CHINA HELICOPTER RES & DEV INST
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