Dynamic modeling method for flight motion simulation of morphing aircraft with any number of rotating parts

By abstracting the multi-rigid-body system of a variant aircraft into a tree system and combining it with the Kane equation, the problem of dependence on specific configurations in existing dynamic modeling methods is solved, enabling flexible adaptation to changes in the number and position of rotating parts, and improving the versatility of modeling and simulation efficiency.

CN122333644AActive Publication Date: 2026-07-03NORTHWESTERN POLYTECHNICAL UNIV
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Patent Information

Application Number
CN202610640578.6
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2026-05-11
Publication Date
2026-07-03
Estimated Expiration
2046-05-11

AI Technical Summary

Technical Problem

Existing methods for modeling the dynamics of variant aircraft are only applicable to specific configurations and cannot adapt to changes in the number or relative position of rotating parts, resulting in poor scalability and versatility.

Method used

The multi-rigid-body system is abstracted into a tree system by using virtual rigid bodies and virtual hinges. The rigid bodies and hinges are uniformly numbered by depth-first traversal search, and the system topology is described based on the path matrix. A general dynamic model is established by combining the Kane equation.

Benefits of technology

It achieves universal modeling of variant aircraft with any number of rotating parts, and can update only the path matrix and geometric parameters when the configuration changes, without having to re-derive the dynamic equations, thus improving simulation efficiency and the convenience of numerical solution.

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Abstract

The invention relates to the field of multi-body system dynamics, in particular to a dynamics modeling method for flight motion simulation of a variant aircraft with any number of rotating parts. According to the method, firstly, a variant aircraft is abstracted into a tree-shaped multi-rigid-body system containing virtual rigid bodies and virtual hinges, the rigid bodies and the hinges are numbered in a unified mode through depth-first traversal search, and relative rotation angles between the rigid bodies serve as generalized coordinates; then describing a system topological structure by adopting a path matrix, and deducing a centroid velocity, a centroid acceleration, an angular velocity and an angular acceleration of each rigid body in combination with generalized coordinates; based on the kinematics parameters, partial velocity, deflection velocity, generalized active force and generalized inertia force are calculated and substituted into a Kane equation to establish a multi-body system kinetic equation; and finally, solving the kinetic equation, updating the motion state according to a set time step, and circularly executing until the simulation of a set time length is completed. The method is high in universality, good in expansibility and suitable for flight motion simulation of variant aircrafts with any number of rotating parts.
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