Research On The Rigid-flexible Coupling Dynamics Of Carrier-based Aircraft Arrested Deck-landing Under Complex Loads

When the carrier-based aircraft is arresting landing,it was decelerating along the intended track,and the arresting hook was engaged with the obstructing rope.After that,the aircraft was decelerated by blocking the obstructing rope to force the brake to stop.Finally,the carrier-based aircraft was stopped on the deck.In the process of carrier-based aircraft landing on the ship,the load is large,the acceleration is large,the distance is short,and the time is short,and it is influenced by the conditions of aircraft carrier movement and airflow disturbance,there is a complex strong nonlinear multidisciplinary dynamics coupling problem.There are a series of safety issues in the landing process,such as: asymmetrical landing leading the aircraft out of the deck,collision of the arresting hooks with deck,structural or load problems leading the damage of the arresting hooks or cables,and excessive impact loads causing damage to the landing gear,local damage and other issues caused by excessive stress or overload.Therefore,the process of arresting landing is usually regarded as the highest accident rate of a carrier based aircraft.Based on the theory of flexible multi-system dynamics,this paper uses ADAMS and PATRAN,NASTRAN,and HYPER-MESH software,according a certain type of shipboard drone,consider the aircraft as a flexible body,the landing gear and the arresting hook as a rigid body,establishing carrier-based aircraft arresting hook coupled multi-body dynamics model.The frequency and structural damping parameters of the aircraft under different vibration modes were obtained according to the ground resonance experiment of the whole aircraft,thereby adding structural damping to the aircraft flexible body,taking into account the buffer effect of the buffer of the landing gear,the buffer effect of the longitudinal buffer of the arresting hook,according to the experimental data getting from the quality of the car to put forward a method of applying arresting loads under the condition of no blocking device and considering the aerodynamic load on the aircraft during the arresting process,to establish a complex-strong non-linear aircraft mechanics model.Research a certain type of ship-based drone under the symmetry arresting landing and the asymmetry arresting landing,obtained the posture changes laws and the transmission path of the longitudinal overload of the aircraft,as well as the stress and strain distribution rules,to provide a kind of safe and reliable assessment method for carrier-based aircraft on board.At the same time,it also provides a certain reference for the optimization of the aircraft fuselage structure and landing gear.The influence of the aerodynamic load on the carrier-based aircraft is resrarched during the arresting process.When the aerodynamic load is considered in the landing process,the posture of the aircraft will be more stable,the amplitude of the upper and lower vibration of the Z displacement of the wing tip will be smaller,and the transient peak value of the oil fluid resistance and the air spring force of the landing gear is smaller,and the vertical overload of the wing is also smaller.Whether there is aerodynamic load in arresting process has no obvious influence on longitudinal overload and stress strain magnitude and distribution rule of fuselage.To research the posture change and the dynamic response of the aircraft under the symmetry arresting landing and the asymmetry arresting landing,We can found that the asymmetric arresting landing has an influence on the longitudinal displacement of the aircraft and also has lateral displacement.In addition,the changing trend of the buffer force of the main landing gear is inconsistent and asymmetrical;The variation trend of Z direction displacement of aircraft wing tip is also inconsistent.The longitudinal overload on the left and right sides of the aircraft fuselage near the arresting hook is different.Asymmetrical arresting has no significant effect on the stress and the strain distribution and size of the aircraft fuselage.