摘要
提出基于飞机传统部件设计参数的广义参数概念,描述未来飞行器概念外形,并通过初步的性能验算公式体系验证其合理、有效性。外形广义参数的探讨是为实现未来飞行器概念外形创新设计进行的一种有益尝试。以飞翼布局在民用运输机中的应用为例,在巡航马赫为0.85的设计点下,采用广义参数设计体系进行飞翼布局外形概念设计,在概念设计中实现广义参数定义飞翼外形,完成飞翼的初步选型。对该外形在应用中的性能结果进行分析,着重体现升阻比及容积率两项重要性能指标,方案设计中,在容积率损失相对不大的情况下实现了飞翼的高升阻比。
Based on the conventional parameters, the general parameters were proposed in conceptual aircraft design to define the configuration of new future aircraft. The performance calculation and analysis to demonstrate its reasonability and validity were carried out. The cruising flying wing layout was adopted on the civil aircraft. For example, three conceptual design cases were presented, which on design Mach number was 0.85 and realized the flying wing conceptual design by taking use of general parameters. Besides the lift drag ratio and volume ratio were emphasized in the aerodynamic performances calculations. It demonstrates that the higher lift drag ratio is possible with the less losing of volume ratio.
出处
《力学季刊》
CSCD
北大核心
2006年第2期305-310,共6页
Chinese Quarterly of Mechanics
基金
国家自然科学基金(90205006)
教育部网格项目(CG2003-GA005)
上海市科技启明星计划(02QG14031)资助
关键词
未来飞行器
飞翼
广义参数
概念设计
性能验算
future aircraft
flying wing
general parameter
conceptual design
performance calculation
