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 helicopter rotor and fuselage, which can solve problems such as danger and reduce damping margin

Active Publication Date: 2021-03-19
CHINA HELICOPTER RES & DEV INST
View PDF18 Cites 4 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, because the rotor shimmy frequency in the frequency domain is very close, it causes continuous excitation to the rotor/body coupling system, and the input excitation frequency of the flig

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Helicopter rotor and fuselage coupling stability modeling method
  • Helicopter rotor and fuselage coupling stability modeling method
  • Helicopter rotor and fuselage coupling stability modeling method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0048] The helicopter rotor and fuselage coupling stability modeling method considering the flight control system involved in the present invention will be described in further detail below in conjunction with the accompanying drawings.

[0049] 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 non-rotating hub coordinate system, the hub rotating coordinate system, the blade flapping coordinate system, the blade shimmy coordinate system and the blade pitch variable coordinate system. The body and rotor hub coordinate system see figure 1 As shown, {O g ,X g ,Y g ,Z g} is the ground fixed coordinate system, and its coordinate vector is represented by {i g , j g ,k g} means that the aircraft gravity along -k g direction. {O f ,X f ,Y f ,Z f} is the body coordinate system, the coordinate origin O f It is selected at the position of the cente...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to view more

PUM

No PUM Login to view more

Abstract

The invention discloses a helicopter rotor and fuselage coupling stability modeling method, and belongs to the helicopter dynamics modeling and analysis technology. The method includes: adopting a modal synthesis technology to perform comprehensive modeling on a rotor and fuselage dynamics coupling system, describing the motion of a fuselage and rotors in different coordinates, establishing structural dynamics finite element method models of isolated rotor blades and an airframe structure respectively, adopting an aerodynamic model to model aerodynamic force, and deducing a rotor/airframe coupling system kinetic equation by applying the Hamilton principle; establishing an automatic flight control system control model, and deriving an aerodynamic load matrix related to the pitch variable, thereby establishing a rotor wing and aircraft body coupling aeroelastic stability analysis model considering the flight control system; and finally, solving a characteristic value through a characteristic value method, and judging the stability of the coupling system through a characteristic value solution. The model can be used for calculating and analyzing the'ground resonance 'and'air resonance' stability of all advanced helicopters, and key technical support is provided for model design and development.

Description

technical field [0001] The invention belongs to the modeling and analysis technology of helicopter dynamics, and relates to a modeling method for coupling stability of a helicopter rotor and a fuselage. Background technique [0002] Modern advanced helicopters usually use Automatic Flight Control System (AFCS) or Stability Augmentation System (SAS) to increase the stability of helicopter handling. Although AFCS can achieve increased handling stability, if the design does not consider its impact on the helicopter's "ground resonance" and "air resonance", the completion may deteriorate the "ground resonance" and "air resonance", especially the "air resonance". [0003] The automatic flight control system uses the state of the helicopter's flight attitude as the feedback variable, and increases the flight stability of the helicopter through pitch control. Helicopter flight attitude changes at low frequency. The flight control system controls the rotor pitch in real time accord...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to view more

Application Information

Patent Timeline
no application Login to view more
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
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Try Eureka
PatSnap group products

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic.

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap