摘要
考虑飞机结构振动刚性模态和前n阶弹性模态,将飞机机体等效地转化为多质量块等效模型,给出了等效系统力学参量的计算方法,为计及机体振动影响的起落架落震试验设计,通过试验检验或确定起落架着陆载荷、功量等提供模型依据,同时也为起落架设计分析、设计计算提供了简明的等效系统。还给出了大柔性飞机着陆功量、机翼位移、剪力、弯矩计算公式。算例结果表明大柔性飞机的起落架设计有必要考虑机体结构弹性,并从全局出发,采用特殊的构造措施和优化设计技术。
For the case in which the rigid mode and the first n modes of a flexible airplane are considered, the body of the airplane is defined as a multi-mass equivalent system and the calculation formulas of the parameters of the system are derived, which presents a model for testing/verifying landing impact load, landing work etc. under the influence of fuselage vibrations and also presents a simple and clear equivalent system for landing gear design analysis. The formula for calculating the landing work, displacement at the wing tip, the shears and bending moments of the wing of a flexible airplane are also given. From an overall point of view, structure deformation of airplane must be considered and optimization design must be used in landing gear design of a flexible airplane.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2006年第4期635-640,共6页
Acta Aeronautica et Astronautica Sinica
关键词
航空器结构与设计
物理模型
等效模态分析
大柔性飞机
起落架
着陆响应
aircraft design
physical model
equivalent modal analysis
flexible airplane
landing gear
landing impact response
