Dynamic Response And Failure Modes Of Aluminum Alloy Fuselage Panel Subjected To Blast Load

The forms of anti-terrorism at home and abroad have become increasingly severe.Due to its great social influence and political influence,civil aviation passenger planes have always been the targets of terrorist attacks,and hijackings and explosions are the main means of attack.If the civil aircraft explodes in flight,the fuselage structure may be damaged.Under the effect of cabin pressurization,the degree of damage may be further aggravated,and machine crashes will be difficult to avoid.Therefore,the FAA proposes the airworthiness requirements for the least risk bomb location for transport aircraft.It aims to consider such in-cabin explosion risks during the design phase and,through an integrated structure/system design,minimizes subsequent risks in the event of an explosion.Understanding and predicting the dynamic response and failure behavior of an aircraft structure under implosion loads is the premise and basis for the design of the least risk bomb location.it is of great theoretical value to study the structural response and failure modes of aerospace aluminum alloy fuselage panels under explosive shock loading.The transport aircraft least risk bomb location(LRBL)airworthiness requirements is deeply analyzed.Based on design and layout of structures and systems around LRBL and the secondary effects and countermeasures after the explosion,the research progress on response characteristics and failure modes of aircraft structure subjected to internal explosion is discussed.The damage mechanism and damage model of human organs under blast shock wave is summarized.The Projectile speed and projectile trajectory of explosive debris is cleared.The design characteristics,advantages and disadvantages of blast-resistant containers at home and abroad are reviewed.Then,through numerical simulations,the effects of the treatment method for fixed boundary,the number of elements in the thickness direction,the element type,and the material constitutive model on the calculation results of the clamped aluminum alloy circular plate are studied.And the explosive shock experiment of the clamped 2024-T3 circular aluminum alloy plate near the explosion field is completed,and then the validity of the finite element model is verified.Based on the validated finite element model,the dynamic response and deformation failure modes of the clamped aluminum alloy circular plate near the explosion field are studied.The dynamic response and failure modes of circular plates with different charge weights and stand-off distances were obtained.Finally,the numerical model of the clamped aluminum alloy stiffened plate is established with reference to the fuselage panel structure of a typical transport aircraft.The dynamic response and failure modes of stiffened plane with different charge weights and stand-off distances were obtained.