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 ensuing supercool/chilled air that is rendered as a consequence of supercooling may hence be compressed, regeneratively intercooled &amp; 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. Also described are the details of an isentropically expanded hypersonic stochastic switch (a singularity), which is mainly achieved via the addition of a high pressure supersonic isentropic expansion nozzle whereby a continuous flow continuum is transformed into a stochastic flux.

Description:
CROSS REFERENCE TO RELATED APPLICATIONS 
     The present application claims the benefit of U.S. Utility patent application Ser. No. 14/564,024, filed on Aug. 12, 2014 and entitled “Apparatus and Methods for Hypersonic Nosecone”, U.S. Utility patent application Ser. No. 14/313,976, filed on Jun. 24, 2014 and entitled “Thermally Conductive Hypersonic Nosecones” and U.S. Provisional Patent Application No. 61/838,454, filed on Jun. 24, 2013 and entitled “Hypersonic Vortex Tube,” which is herein incorporated by reference in its entirety. 
    
    
     BACKGROUND 
     This inventive subject matter relates to the systems, apparatus, and methods for the reduction of drag in a spacecraft or missiles and a hypersonic stochastic switch. The reduction of drag in spacecraft and missiles is of particular concern as atmospheric friction can cause the nosecone to increase beyond the failure point. Clearly ways to reduce would benefit missiles, allowing them to travel at higher speeds, and spacecraft, allowing them to reenter the atmosphere without the fear of destruction. Also described are the details of an isentropically expanded hypersonic stochastic switch (a singularity), which is mainly achieved via the addition of a high pressure supersonic isentropic expansion nozzle. 
     SUMMARY OF THE INVENTION 
     The invention comprises the systems, apparatus, and methods for the reduction of drag in a missile using a vortex tube. 
     Illustrated herein is a method for reducing drag at hypersonic speed that includes the steps of mounting a liquefaction nosecone on the forward portion of a projectile; where the projectile is either a missile or spacecraft. 
     Further describes is a method for reducing drag at hypersonic speed also having the steps of drawing an atmosphere external to the liquefaction nose cone an intake aperture or a discharge shaft. 
     Further presented is a method for achieving hypersonic transport that has an aerospace plane intercontinental hypersonic airliner equipped with a hypersonic vortex generator in support turbojet powered hypersonic means. 
     Further presented are the details of an isentropically expanded hypersonic stochastic switch, which is mainly achieved via the addition of a high pressure supersonic isentropic expansion nozzle. 
     This specification is not limited to a single embodiment, rather the methods and systems presented should be construed broadly and further incorporate the material presented in the drawings. 
    
    
     
       DESCRIPTION OF THE DRAWINGS 
         FIG. 1  illustrates the hypersonic nose cone. 
         FIG. 2  illustrates the configuration on a hypersonic nose cone on a missile. 
         FIGS. 3A and 3B  illustrates a schematic rendering of the stagantion pressure surges. 
         FIG. 4  illustrates the vortex triggering transformation. 
         FIGS. 5A and 5B  illustrates the transformation of the incipient shear vortex. 
         FIG. 6  illustrates isentropically expanded hypersonic stochastic switch. 
         FIG. 7  illustrates homogenous helium liquefaction. 
         FIG. 8  illustrates homogenous helium and hydrogen liquefaction. 
         FIG. 9  illustrates Helium liquefaction scheme. 
         FIG. 10  illustrates the addition of regenerative loop. 
         FIGS. 11A and 11B  illustrates the setup for distillation. 
         FIGS. 12A and 12B  illustrates the chart of Mach number with ABS-ZERO refrigeration dynamics. 
     
    
    
     DETAILED DESCRIPTION 
     Referring to  FIG. 1  which illustrates the components of the conductive nose cone  1 . A cooling fluid  18 , typically liquid nitrogen, circulates by injection by the input line  19  into the shaft  60 , and exiting via the exit lines  20 . The cooling fluid  18  is provided by the cooling fluid source  40 . Inside the shaft  60 , is a space for the cooling fluid  18 . A perforated Teflon washer  11 , glass tube  12 , laser aiming point  13  and thermocouple sensor probe  14 . The incoming hypersonic streamline  17  is instantaneously transformed into a rotation vector as a consequence of rapid harmonic/isothermal compression surges on the reaction plane  112 . The thermally conductive cone  1  is composed of a tip  50 , a shaft  60 , and a bore  70 . The entry part of the tip  50  has an intake area that is larger in circumference that the bore  70 . The angle of intake area is approximately 30-60 degrees relative to a line drawn in parallel with the bore edge. In a representative embodiment, the intake bore shaft is 5/16 inches and the outer area of the intake is 14/16 inches. Adjusting the scale of the entire apparatus will not affect the ability of the device to reduce drag. 
     Now referring to  FIG. 2  which illustrates a single or multi-stage missile or rocket  90  with a thermally conductive cone  1  based on the double helix vortex phenomenon driven by a rapid isothermal compression surges on the reaction plane. 
     Now referring to  FIGS. 3A and 3B  which illustrates a schematic rendering of the stagnation pressure surges. Pressure surges  61 , 62 , 63 , 64  denotes the stagnation transients for the 30/45/60 degree (60/90/120 degree enclosed angle) ablative shear/reaction planes chilled to −160 C. Pressure surge  65  denotes the pressure surge with −25 C chilling only. Whereas traces  61 , 62 , 63 , 64  which demonstrate the consequence of hypersonic liquefaction and shows an immediate surge responses trace  65  which indicated an initial inertia lag of 1 sec prior to defaulting into conformal stagnation surging. Time periods  60  and  66  denotes a 3 sec testing window and stagnation potential respectively. 
     Now referring to  FIG. 4  which illustrates the vortex triggering transformation of the incipient hypersonic streamline  111  via the supercooled shear transformation plane  112  the nosecone  110  into a circular streamline  113 . The subsequent developed vortex transgressing  114  down the supercooled bore  70 . The coupling vector  109  is shown for reference purposes. 
     Now referring to  FIGS. 5A and 5B , which illustrates the transformation of the incipient shear vortex item  115  ensuing from the shear transformation of the hypersonic streamline item  111  on the reaction plane item  112 . The generation of the refractive (double helix) contraflow vortex item  116 .  FIG. 5A  illustrates the vortex and  FIG. 5B  illustrates the flow pattern schematically. 
     Now referring to  FIG. 6, 600  illustrates the details of an isentropically expanded hypersonic stochastic switch, which is mainly achieved via the addition of a high pressure supersonic isentropic expansion nozzle  616 . The hypersonic front  609  engages with the thermally reactive slanted hypersonic vortex shaft  610  transforming the continuous supersonic flux into a complex stochastic vortex flux which is regeneratively chilled via Joule-Thomson throttling via expansion nozzle  612 . By adding the isentropic expansion nozzle  616  with a high pressure helium resource  617  consequently by development and blasting high pressure helium  619 . A mixtures of He or H2 or O2 or N2 or Ag or CO2 including atmospheric air singularly or collectively can be used in a continuous fashion into the thermally reactive slanted hypersonic vortex shaft  610 , a supersonic singularity switch  618  is being generated whereby the linear hypersonic continuum is transformed into a non-linear stochastic vortex stream  611  and the hypersonic kinetic front into a gyrating stochastic stagnation-pressure flux that is regeneratively chilled via Joule-Thomson throttling via expansion nozzle  612 . 
     Theoretically the stochastic LORENTZ stagnation pressure transformation in accordance with the IDEAL GAS LAW is T2/T1=(p2/p1)^(k−1)/k where k=isentropic gas constant=1.4 (generally). By operation of the LORENTZ RH rule or the magnetic flux equivalent the stochastic stagnation pressure flux is being transformed into a gyrating thermal energy flux, which as a consequence of the transposed stochastically induced gyrations penetrating the saturation zone of Helium proximal to absolute zero. A mixture of He or H2 or O2 or N2 or Ag or CO2 including atmospheric air singularly or collectively can also be used to achieve similar results. 
     Now referring to  FIG. 7, 700  illustrates Joule-Thomson throttling regression from 100K through saturation zone of Helium, subsequent to which complex Carnot liquefaction or refrigeration is being triggered. The regressive throttling from 100K described by  710  representing the entry point which is the isentropic expansion temperature being regressively chilled via Joule-Thomson throttling via expansion nozzles into the saturation zone of Helium @5K described by  720 , whereupon liquefaction of Helium will trigger complex Carnot refrigeration deep into the Helium saturation zone as a consequence of induced stochastic switch gyrations penetrating the saturation zone of Helium. 
     Now referring to  FIG. 8, 800  illustrates Joule-Thomson throttling regression from 100K though saturation zone of hydrogen and helium consequentially to bypass the helium throttling dead zone through 30K by means of hydrogen throttling and liquefaction augmentation (1-5% preferred mixture). The regressive throttling from 100K described by  810  entry point for a mixture of Helium and Hydrogen (1-5% H2), whereby the Hydrogen is acting as catalyst/to accelerate Joule-Thompson throttling because of the extremely low Joule-Thomson coefficient through the 100K to 30K cryogenic zone which is likewise regressively chilled via Joule-Thomson throttling mixture of Hydrogen and Helium via expansion nozzles into the saturation zone of Hydrogen  820  @35K and consequently Helium @5K described by  830 . Once into the Helium saturation zone liquefaction of Helium will initiate complex Carnot refrigeration deep into the Helium saturation zone. However Joule-Thomson throttling will accelerate substantively once the saturation zone of Hydrogen  820  is reached because of the combined power of hydrogen throttling and hydrogen complex Carnot chilling processes. 
     Now referring to  FIG. 9, 900  represents a Helium liquefaction scheme by the addition of a porous core  613 , enclosure  614  and vacuum pump  615  to vent the supercool vortex flux  609  through the porous plug to drive Joule-Thomson throttling into the vacuum range that will result in ZERO-K sub cooling that will generate liquid Helium  606  that will be captured in the cryo-flask  607 . Theoretically throttling potential of dT=4 C @4K, Cp=2.8 and Hfq=10, 1 lb Helium will be able to liquefaction 4×2.8/10=1.12 lb Helium (meaning 2.12 lb compressed Helium @5,000 psi will have the capacity to liquefy 50% of itself back-to-back via the instant isentropic expansion and stochastic switch processes. 
     Now referring to  FIG. 10, 1000  illustrates the addition of regenerative loop  620  redirecting the Helium discharge  621  over the finned  629  choke shaft  611  that will boost Helium liquefaction by 25%, whereby 2.5 lb compressed Helium will generate 1.5 lb liquid Helium. 
     In accordance with  FIGS. 11A and 11B  compressed Helium tank  1100  supplies compressed Helium to the hypersonic Helium liquefaction vortex tube  1101  that is vented via vacuum pump  1102 . Liquid Helium is consequently collected in cryo-container  1103  located on stand  1104 . Optionally liquid Nitrogen (precool) tank  1105  and (precool) heat exchanger  1106  may also be added as shown in  FIG. 11B . 
     Table-1 below illustrates the operation of Mach number (the isentropic driving potential) as to ABS-ZERO regression and liquid Helium liquefaction. Although isentropic expansion of Helium constitutes a powerful refrigeration engine, the saturation zone of Helium remains an enigma with and without liquid Nitrogen (LN2) precooling (100K) and/or Hydrogen (H2 and Helium mixtures (preferred mixture 1-5% Hydrogen). In order to bridge the continuous linear (isentropic) expansion threshold of 7.2K, in a hypersonic Vortex Tube whereby the continuous/linear (isentropic) front is transformed into a perfectly random (Gauss-Markov) harmonic flux whereby the (wild) stochastic (gyrations) strikes and penetrates the Helium saturation zone. Once the Helium saturation zone is entered, specifically “complex” Carnot refrigeration is triggered because it is a product of stochastic gyrations (which itself is the consequence of collapsing Helium liquefaction bubbles because of “gyrations” strikes). However once the complex Carnot engine activates, the isentropic regression is drawn into the Helium saturation zone by operation of the Hypersonic Vortex Tube. Therefore by switching linear/continuous flow into (wildly gyrating) a non-linear/stochasticflux by means of the Hypersonic Vortex Tube (a singularity), the power of stochastic gyrations are being utilized that bridges the ABS-ZERO divide and kick-starts Carnot refrigeration that turns the Hypersonic Vortex Tube into a Helium liquefaction engine. 
     
       
                 
         
             
             
         
      
     
     Now referring to  FIGS. 12A and 12B , in general  1201  identifies a starting point of the regression trace which is 300K,  1202  refers to 250K (Freon refrigerated) and  1203  refers the 100K (LN2 precooled).  1204  indicates the Mach 7 threshold whereby 7.2K is ultimately feasible with LN2 precooling, isentropic expansion does not fall into the Helium saturation zone  1205  in isolation. Thus a hypersonic vortex tube is developed to bridge the ABS-ZERO gap by means of the stochastic gyrations  1206  that pierces the Helium saturation zone  1207  and consequential complex-Carnot quasi-saturation refrigeration power that spawns Helium liquefaction  1207 .  1203  focuses on the power of liquid Nitrogen precooling/chilling (100K isentropic entry) and in  1202  focuses on Hydrogen mixing (1-5% hydrogen in helium). The hydrogen preferred ration is derived based on principles of latent heat of condensation and atmospheric oxygen content. 
     A hypersonic vortex tube stochastic Helium liquefaction switch may be utilized for small and large scale Helium liquefaction. Because liquid ABS-ZERO (super cooling) and enterprise Helium is a necessary modern research and enterprise tool, “Hypersonic Vortex Tube” and consequential stochastic Helium liquefaction switch will spawn new technologies and commerce advancements beyond the scope of modern realm. A freestanding thermally reactive nosecone comprising of isentropic hypersonic expansion nozzle wherein liquid helium is directly distilled out of compressed helium. The free standing thermally reactive nosecone is scaled as a personal helium distillation plant driven by tanked and compressed Helium and Liquid Nitrogen. The free standing thermally reactive nosecone is scaled as an enterprise Liquid Helium production facility with/without Liquid Nitrogen and with/without the addition of Hydrogen (preferred ratio 1-5%). 
     All patent and non-patent literature cited herein is hereby incorporated by references in its entirety for all purposes. 
     Persons skilled in the art will recognize that many modifications and variations are possible in the details, materials, and arrangements of the parts and actions which have been described and illustrated in order to explain the nature of this inventive concept and that such modifications and variations do not depart from the spirit and scope of the teachings and claims contained therein.