Superconductive Hypersonic Liquefaction Nosecone

• US 20150048208A1
• Filed: 08/16/2013
• Published: 02/19/2015
• Est. Priority Date: 08/16/2012
• Status: Active Grant

• Current Assignee: Charl Emelio Janeke
• Original Assignee: Charl Emelio Janeke
• Inventors: Janeke, Charl Emelio
• Granted Patent: US 9,193,457 B2
• Time in Patent Office: Days
• US Class Current: 244/130
• CPC Class Codes: B64C 1/0009 Aerodynamic aspects
• CPC Class Codes: B64C 1/38 Constructions adapted to reduce effects of aerodynamic or other external heating
• CPC Class Codes: B64C 2001/0045 Fuselages characterised by special shapes
• CPC Class Codes: B64C 23/04 by generating shock waves
• CPC Class Codes: B64C 30/00 Supersonic type aircraft
• CPC Class Codes: B64D 27/023 of rocket type, e.g. for assisting taking-off or braking

Abstract

An apparatus and method for mitigating the shock front of a rocket or aerospace plane flying at hypersonic speeds while simultaneously distilling liquid chemical elements from the ambient air. The invention employs supercooling (through a combination of superconductivity and/or superemissivity) driven by the cryogenic power of liquid hydrogen and/or regenerative evaporation of liquid hydrogen and/or liquid nitrogen to drive isothermal compression and consequentially usurp the shock front in totality at Mach 1. The ensuing supercool/chilled air that is rendered as a consequence of supercooling may hence be compressed, regeneratively intercooled & flashed into liquid air. By means of extension liquid air may be rendered as a direct result of said supercooling throughout the hypersonic regime into space. Under conditions of optimality the incipient air stream may be compressed in accord with the stagnation pressure of the Mach number and liquefacted in one-step via the power of supercooling and isothermal compression

Claims

1. A aerospace plane flying hypersonically through the atmosphere comprising:

a body;

a nosecone on the leading end, said nosecone including an aperture for the intake of ambient air; and

, a rocket engine on the tail end.

2. The aerospace plane of claim 1 wherein the nosecone has a surface, the surface further selected from a group comprising smooth, etched, finned, dimpled, warped, and fluted.

3. The aerospace plane of claim 1 wherein the nosecone is configured into an oval, tubular, or warped format.

4. The aerospace plane of claim 2 wherein the nosecone is etched or coated with micro or nano prisms on the source and sink surfaces.

5. The aerospace plane of claim 4 wherein the micro or nano prisms may be diamond granules or diamond dust.

6. The aerospace plane of claim 1 wherein the nosecone is made of copper and is of spherical form.

7. The aerospace plane of claim 1 wherein the nosecone is a close-coupled, double-decker, optically black spherical heat exchanger with a superconductive outer shell and a supercooled inner shell.

8. The aerospace plane of claim 7 wherein the outer sphere is etched or coated glass so that it is optically black.

9. The aerospace plane of claim 1 further comprising a regenerative or secondary heat exchanger behind the nosecone that may be finned or of shell-and-tube construction.

10. The aerospace plane of claim 1 further comprising a tank for storing a chemical element in liquid form for use in driving the heat exchange at the nosecone or at the secondary heat exchanger.

11. An aerospace plane flying hypersonically through the atmosphere comprising:

a rocket or aerospace plane body;

a nosecone wherein are housed means to simultaneously usurp the shock front and distill a liquid chemical element from the ambient air; and

, a rocket engine on the tail end.

12. The aerospace plane of claim 11 wherein the chemical element distilled from the ambient air is oxygen, nitrogen, or both.

13. The aerospace plane of claim 11 wherein said means are accomplished through either superconductivity or superemissivity to dissipate the heat of compression of the incipient shock wave at formation at an infinite rate, isothermally compress the incident air, and condense or cause the liquefaction of a portion of the incident air without employing mechanical means or the attribution of another medium.

14. The aerospace plane of claim 11 wherein the superconductivity or superemissivity is driven by the expansion of tanked liquid hydrogen, liquefacted oxygen, liquid methane or liquefacted nitrogen.