Helicopter multi-modal coupling ground resonance calculation method

By employing a multimodal coupled ground resonance calculation method, the problems of multi-degree-of-freedom coupling and modal simplification in helicopter ground resonance calculation are solved, thereby achieving accuracy and reliability in helicopter ground resonance stability design and providing realistic stability curves, which have high engineering application value.

CN120493575BActive Publication Date: 2025-10-21CHINA HELICOPTER RES & DEV INST
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Patent Information

Application Number
CN202510969768.8
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2025-07-15
Publication Date
2025-10-21
Estimated Expiration
2045-07-15

AI Technical Summary

Technical Problem

Existing technologies cannot effectively consider multi-degree-of-freedom coupling and multiple body modes, resulting in inaccurate calculations of helicopter ground resonance, failing to accurately reflect the vibration characteristics of the rotor hub center, and the calculation methods are complex and do not conform to actual motion conditions.

Method used

The multimodal coupled ground resonance calculation method is adopted, which considers the various modes and multiple degrees of freedom coupling of the airframe on the landing gear. By calculating the compressive stiffness and damping of the main engine wheel, tail wheel and buffer strut, a full-aircraft dynamic model is established. Stability calculation is carried out by combining the vibration characteristics of the rotor hub center and the blade oscillation motion.

Benefits of technology

It provides a more realistic simulation of the vibration characteristics of the propeller hub center, obtains accurate ground resonance stability curves, ensures the reliability and accuracy of ground resonance stability design, and has high engineering application value.

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Abstract

The application belongs to the field of helicopter structure strength design, and relates to a helicopter multi-modal coupling ground resonance calculation method. The method comprises the following steps: selecting a typical weight state and a typical lift state of a certain type of helicopter, and calculating the compression stiffness and compression damping of the main landing gear, the tail landing gear and the buffer strut; simulating the compression stiffness and compression damping of the main landing gear and the tail landing gear in the full machine dynamics model, and establishing the full machine dynamics model on the landing gear; performing body complex modal calculation on the full machine dynamics model on the landing gear, and selecting six rigid body modes, modal mass, damping ratio and modal shape of the body on the main landing gear and the tail landing gear from the calculation results; and on the basis of the body motion, considering the hub center two directions and the blade oscillation motion, combining several modes to perform ground resonance stability calculation. The application can obtain more real ground resonance stability curve, and provides an accurate and reliable calculation method for ground resonance design.
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