Apparatus and methods for hypersonic nosecone
View Patent ↗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 and
the 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 described in claim 1 , wherein the shear vortex ensuing from the shear transformation of an incipient hypersonic streamline is transformed into a refractive double helix contraflow vortex.
5. The nosecone as described in claim 1 , wherein the vortex triggering transformation defaults into a hypersonic (RANQUE) refrigeration engine.
6. The nosecone as described in claim 1 , wherein the hypersonic (RANQUE) refrigeration engine is CARNOT compliant in the cryogenic zone and JOULE-THOMSON driven outside the cryogenic zone.