Active thermal protection system for hypersonic aircraft nose cone

The invention discloses an active thermal protection system for a hypersonic aircraft nose cone. Active control on a hypersonic incoming flow is realized by utilizing a combined structure of a pneumatic rod, a pneumatic disc and a rear low-temperature jet flow, so that the wall surface heat flow of the hypersonic aircraft nose cone is reduced, and heat prevention is realized. With the active thermal protection system, a problem that a traditional passive thermal protection system cannot work in an extreme thermal environment is solved; the system has the advantages of being high in thermal protection efficiency, simple in structure and easy to manufacture, install and replace, and has universality for thermal protection of the nose cone of the hypersonic flight vehicle. 本发明公开了一种高超声速飞行器头锥主动热防护系统，利用气动杆、气动盘和后部低温喷流的组合构型实现对高超声速来流的主动控制，从而降低高超声速飞行器头锥的壁面热流，实现防热。本发明的主动热防护系统能克服传统被动式热防护系统无法在极端热环境下工作的问题，其具有防热效率高，结构简单，易于制造、安装和更换的优点，且对高超声速飞行器的头锥防热具有通用性。