|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||B64C-001/38 F42B-012/02 F42B-015/34 B64G-001/62|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 0 인용 특허 : 14|
An apparatus and method for mitigating the shock front or reducing drag of a rocket or aerospace plane flying at hypersonic speeds by using a modified nose cone that incorporates a low temperature substance, such as liquid nitrogen, and where the nose cone simultaneously interacts with the ambient air to further supercool the nose cone during operation.
1. A thermally reactive nosecone mounted on a projectile for achieving hypersonic transport comprising: a tip, the tip having a slanted intake aperture;a shaft;a thermally reactive bore andthe nosecone functioning as a vortex generator. 2. The nosecone as described in claim 1, wherein the vortex triggering transformation of an incipient hypersonic streamline to a circular streamline is via a shear transformation plane. 3. The nosecone as described in claim 2, wherein the circular streamline transgresses through the super cooled bore. 4. The nose cone as ...