Aircraft landing gear and tail hook dynamic load coupled analytic method

Abstract

The invention belongs to the technical field of a fixed-wing aircraft and particularly relates to a fixed-wing aircraft landing gear and tail hook dynamic load coupled analytic method. The fixed-wing aircraft landing gear and tail hook dynamic load coupled analytic method is characterized in that on the basis of an overall landing configuration and geometric layout parameters of the aircraft, a landing gear and tail hook kinematical/ kinetic equation is established, and by the parametrization design of an oil-air type damper and parameter regulation iteration re-inspection in the software environment, the multi-body dynamic modeling and numerical analysis work of a plurality of subsystems such as an aircraft tail hook and a landing gear is completed. Interactive influence of a load and vibration of each subsystem in a combined state is calculated so as to implement coupling research. A steady state component and a dynamic component of the load of a certain subsystem under the coupled condition are analyzed and are compared with a dynamic load simulated test result in a separated state; difference and a sensitive parameter are discriminated; a coupling/decoupling research method and a tail hook oscillation and main landing gear load oscillation peak shifting avoidance design method are given.

Description

technical field [0001] The invention belongs to the technical field of fixed-wing aircraft, and in particular relates to a dynamic load coupling analysis method of landing gear and tail hook of the fixed-wing aircraft. Background technique [0002] The dynamic load analysis of landing gear and tail hook of fixed-wing aircraft is the key technology of aircraft body structure strength. The previous dynamic load analysis methods for landing gear and tail hook of fixed-wing aircraft all took isolated single structures as the research objects, and did not fully consider the interaction effect of dynamic loads between individual structures, and used empirical algorithms instead Static research on sex, the calculation results obtained from this are often untrue or conservative. [0003] Establish the dynamic load coupling analysis method of the landing gear and the tail hook, and carry out the coupling analysis of the dynamic load of the landing gear and the tail hook as the chara...

AI Technical Summary

Problems solved by technology

[0003] Establish the dynamic load coupling analysis method of the landing gear and the tail hook, and carry out the coupling analysis of the dynamic load of the landing gear and the tail hook as the characteristic basis for evaluating the structural integrity of the aircraft. In this sense, only a single landing gear or It is difficult to cover the service characteristics of the aircraft in the study of the dynamic load of the tail hook

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