摘要
飞/发一体化设计是从整个飞机系统出发进行机体、发动机的研究设计。其中,约束分析是一体化设计的首要任务,其目的是确定飞机满足技术要求的可行域,并从中选出初步设计的推重比和机翼载荷。本文介绍了一般飞机气动特性计算模型和约束分析的模型,并以某民用飞机为例,进行了推重比和翼载的约束分析。根据相关数据,发现其真实值落在可行域中,可对飞机的性能有初步的认识。
Integmted design of aircraft/engine is the research and design of airframe and engine from the whole aircraft system. The constraint analysis is the primary task of integrated design, and purpose of constraint analysis is to ensure that the aircraft meets the technical requirements of the feasible region, and select the preliminary design of thrust-weight ratio and wing load from the feasible region. The general aerodynamic characteristics model and constraint analysis model of aircraft arc introduced. As an example of a civil aircraft, the constraint analysis of thins-weight ratio and wing load is analyzed. Acconting to the relevant data, it can be found that the true value falls in the feasible region, and can have a general understanding of the aircraft performance.
出处
《工程与试验》
2017年第1期30-31,45,共3页
Engineering and Test
关键词
一体化设计
约束分析
推重比
翼载
integrated design
constraint analysis
thrust-weight ratio
wing load
