Abstract: For exploring new ideas of air-breathing hypersonic airframe/propulsion integrative design methods (“hypersonic integrative design” for short)， the schemes are classified and discussed under comparing the vehicles with different missions such as hypersonic aircraft and Single/Two Stage To Orbit vehicles (“SSTO/TSTO” for short). Analysis results show that the hypersonic integrative design methods of missile are mostly focused on putting inlet as forebody directly， while that of hypersonic aircraft consider mainly the total aerodynamic performances of wide-speed range， in contrast to less requirement of that of SSTO/TSTO by using rocket engine as combined propulsion system. Besides， the integrative methods based on “weak-interference” or “non-interference” between the in/external flow characteristics of hypersonic vehicles have became one of the most important development tendency. Moreover， preliminary research results of “non-interference” dorsal typed and “strong-interference” ventral typed integrative configurations indicate that lift-to-drag ratio and other related aerodynamic performances of the former is better， as well as owing a more stable and wide adaptable aerodynamic characteristics under the off-design flight conditions， and which are worthy to be studied further in the future.

Key words: Air-breathing；Hypersonic aircraft；SSTO/TSTO；Airframe/propulsion integrative design；Research progress

摘要： 为了探索吸气式高超声速飞行器机体/推进一体化设计技术新理念，按照高超声速飞机和SSTO/TSTO分类对其一体化设计技术主要研究进展进行了对比分析，结果表明:高超声速弹用一体化设计技术采用将进气道直接作为前体的方案较多；高超声速飞机一体化设计技术需重点兼顾宽速域整体气动性能；SSTO/TSTO一体化设计技术则由于火箭发动机的引入在一定程度上改善了其对一体化设计的具体需求；同时，近年来高超声速内/外流“弱干涉”和“无干涉”等新型一体化设计技术已逐渐成为一个重要发展方向。对背负式进气的内/外流“无干涉”一体化和常规腹部进气的前体预压缩内/外流“强干涉”一体化方案开展初步对比，研究表明“无干涉”一体化方案升阻比等气动性能更优，同时整体气动特性对飞行条件变化不敏感，具有更好的宽速域适应性，值得进行深入研究。

关键词: 吸气式；高超声速飞机；单/双级入轨；机体/推进一体化设计；研究进展