摘要
着重分析在核爆炸冲击波环境中飞机结构动力响应有关问题,推导了动力学基本方程,介绍了飞机在核爆炸冲击波中非定常气动载荷计算方法,给出了结构动力响应分析的思路和计算过程,提出了飞行飞机在核爆炸冲击波作用下总体结构安全边界值的估算方法,并对存在的问题进行了讨论。
Aircraft operating in the nuclear explosion environment may be subjected to five kinds of damage, electromagnetic pulse, early nuclear radiation, ray radiation, shock waves, and radiative dustfall resulting from the nuclear explosion. The load of the shock waves of the nuclear explosion that acts upon the aircraft mainly consists of two parts. One is the overpressure caused by the shock waves, which crushes the organic glass on the aircraft cockpit and makes the wing trailing-edge and flap skin sink and 'barefaced'. In more serious cases, the stringers, ribs and bulkheads under the skin are broken. The other is the wave gust, i. e. the velocity of the air particles inside the shock waves. This stream, when acting upon the aircraft, especially those in flight, will produce unsteady aerodynamic load, leading to aircraft stall and breakage of the wing or vertical tail and threatening aircraft operational safety. This paper focuses on the analysis of the problems relating to the dynamic response of the aircraft structure in the nuclear explosion shock waves. Fundemental dynamic equations are derived in detail, methods for computing the unsteady aerodynamic load in the nuclear explosion shock waves described, processes for analysing and computing the structural dynamic response given, methods for estimating the total structural safety boundary values for aircraft in the nuclear explosion shock waves presented, and existing problems discussed, with the aim of providing references for aircraft already used or designed to carry nuclear weapons.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1992年第9期A510-A515,共6页
Acta Aeronautica et Astronautica Sinica
关键词
核爆炸
冲击波
结构动力响应
飞机
nuclear explosion, shock waves, structural dynamic response
