A Calculation Method of Aircraft Wing Motion and Dynamic Deformation Coupling Velocity Error

Abstract

The invention discloses an aircraft wing motion and dynamic deformation coupling speed error calculation method. An aircraft wing is equivalent to a cantilever beam, and the dynamic deformation adoptsan Euler-Bernoulli model, mathematical analysis is made for different excitation forces and the deformation displacement of the beam is deduced under different excitation forces; the deformation displacement of the beam includes rigid body displacement and dynamic elastic deformation displacement, and the amplitude and phase relation between the velocity corresponding to rigid body displacement and the velocity corresponding to dynamic elastic displacement is further deduced; a lever arm between main and sub-systems of an aircraft wing deformation measurement inertial navigation system is dynamically changed; and the speed corresponding to the dynamic elastic displacement is taken into account in the lever arm compensation process, and the speed error expression in the transfer alignmentprocess is corrected. Compared with the prior art that the lever arm between the main and sub-systems is taken as a constant value, the aircraft wing motion and dynamic deformation coupling speed error calculation method analyzes and deduces the transmission alignment speed error between the main and sub-systems of the dynamic lever arm, and can improve the transmission alignment precision.

Description

technical field [0001] The invention belongs to the technical field of inertial navigation, and uses an inertial navigation system to measure the wing deformation of an aircraft, which involves the process of calibrating a low-precision sub-inertial navigation system by a high-precision main inertial navigation system, and specifically relates to an aircraft based on the Euler-Bernoulli model Calculation method of velocity error coupled with wing motion and dynamic deformation. Aiming at the dynamic deflection of the aircraft wing, the additional velocity generated by the dynamic deformation is mathematically derived, and combined with the additional velocity generated by the dynamic deformation, the spatial geometry analysis of the lever arm velocity error during the transfer alignment process of the main and sub inertial navigation systems is carried out. Background technique [0002] The carrying capacity of the aircraft is limited, especially the wing part, so the measur...

AI Technical Summary

Problems solved by technology

However, the flexible lever arm effect produced by the deflection between the main body and the sub-section is the main factor affecting its accuracy. The existing dynamic deformation measurement of the aircraft wing regards the wing as a rigid body and does not consider the deflection deformation. The accuracy is difficult to achieve the required accuracy

Images