System, apparatus and methods for hypersonic shockwave muffler

Abstract

An apparatus and method that improves the operation of aerospace planes or rockets having an integrated flute and hat components whereby the flute functions as a hypersonic refrigeration engine and the hat as a flat plate heat exchanger to achieve an isothermal compression of the incipient hypersonic air in front of the nosecone to reduce hypersonic vibrations during flight, these improvements allow for the reduction in temperature during flight operation allowing for improved cooling of the aerospace plane or rocket.

Claims

1. A rocket capable of hypersonic travel comprising: an integrated flute and hat proximately mounted on to a nosecone of the rocket; and the integrated flute and hat comprising a first open end and a second open end, the first open end having a first flare structure and the second open end having a second flare structure with a serrated edge.

2. The rocket as described in claim 1, wherein the integrated flute and hat bring about an isothermal compression of an airstream in front of the nosecone of the rocket.

3. The rocket as described in claim 1, wherein the integrated flute and hat is made up of material chosen from a group consisting of aluminum, copper, silver or composites.

4. The rocket as described in claim 1, wherein the integrated flute and hat is positioned such that two-third of the length of the integrated flute and hat is placed on the nosecone and one-third placed in front of the nosecone.

5. The rocket as described in claim 1, wherein the shape of the flute can be chosen from a group consisting of continuous, slotted, oval or rounded.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) FIG. 1 illustrates an elemental flute and hat.

(2) FIG. 2 illustrates the integration of an elemental flute on to a hat.

(3) FIG. 3 illustrates the integration of an elemental flute, hat on the nosecone.

(4) FIG. 4 illustrates the integration of an elemental flute, hat, nosecone in conjunction with the rocket.

(5) FIG. 5 illustrates the integration of an elemental flute, hat and the nosecone onto an aerospace plane.

(6) FIG. 6 illustrates an integration of an elemental flute with a hybrid rocket nosecone.

(7) FIG. 7 illustrates integration of an elemental flute with a hybrid rocket nosecone.

(8) FIG. 8 illustrates the makeup of a supercritical shockwave piercing hypersonic wing with the slotted elemental flute.

(9) FIG. 9 illustrates the biplane shockwave.

(10) FIG. 10 illustrates an articulated clamshell turbojet.

DETAILED DESCRIPTION

(11) In the following description, numerous specific details are set forth such as examples of specific materials, methods, components, etc. in order to provide a thorough understanding of the present inventive subject matter. It will be apparent, however, to one skilled in the art that these specific details need not be employed to practice the present invention. In other instances, well-known materials or methods have not been described in detail in order to avoid unnecessarily obscuring the present inventive subject matter.

(12) The present inventive subject matter describes a method and apparatus for a hypersonic shockwave muffler.

(13) As shown in FIG. 1, 100 represents an expanded representation of a thermally conductive elemental flute 101 and hat 102. The elemental flute 101 is typically a tube-like structure that is placed in front of the aerospace plane or rocket. The hat 102, is usually a flange-like structure that is mounted on one end of the elemental flute 101 and attached to the nosecone.

(14) During operation of the rocket at hypersonic speeds, the ambient air stream enters the elemental flute 101 The air then spins as a vortex down the tube, then expands across the nosecone and is constrained by the hat 102. This results in the cooling of the incoming air.

(15) The elemental flute 101 and the hat 102 may be constructed using any type of thermally conductive material with sufficient strength to operate at hypersonic speeds. Typical materials are thermally conductive copper, aluminum, silver but other materials and/or composite metal alloys may also be used. The specific structural and material configurations of flute and hat are exemplary only. Other similar design configurations may be used that generally fall within the spirit and scope of the present disclosure.

(16) Referring to FIG. 2, 200 illustrates the integrated elemental flute and hat 203 comprising of a flute portion 201 and a hat portion 202. The integrated elemental flute and hat 203 functions as a plate heat exchanger which enables isothermal compression of the external airstream on contact via cooling/chilling the heat of compression at formation.

(17) Now referring to FIG. 3, 300 represents integrated flute and hat 203 as placed proximate to a nosecone 303. This combination functions as a heat exchanger which enable supersonic isothermal compression of the external airstream on contact via a cooling/chilling the heat of compression at formation around the nosecone.

(18) Reviewing FIG. 4, 400 represents the integrated flute and hat 203 as connected to a rocket nosecone 403, on an air-breathing rocket 404 functioning as a plate heat exchanger enabling isothermal compression of the external airstream at supersonic speeds. This cooling/chilling is caused by the expansion of the airstream at the nosecone.

(19) Referring to FIG. 5, 500 represents the integrated flute and hat 203 as connected to the aerospace plane nosecone 503 on an air-breathing hypersonic aerospace plane 506 with wings 507, intakes 508 and propulsion engines 509. As the aerospace plane travels at supersonic speed, the integrated flute and hate 203 functions as a plate heat exchanger enabling isothermal compression around the aerospace plane nosecone 503.

(20) Referring to FIG. 6 and FIG. 7. FIG. 6 is a close-up top view 600 of the front part of the hybrid rocket with an internal shaft 612. Illustrated in FIG. 6 is an integrated flute and hat 203 mounted on a frustum shaped nosecone 603, the frustrum shaped nosecone has a shaft 612 that runs the length of the hybrid rocket with 613 and 614 representing the cryogenic conduits. The air entering through the shaft air intake 610 becomes a vortex which is funneled via shaft 612. Now referring to FIG. 7, the airstream 610 runs the length of the hybrid rocket to an air-breathing hybrid propulsion rocket engine 709 as shown in FIG. 7. 700 illustrates the integrated flute and nosecone 203, integrated onto an air-breathing hybrid rocket 704 with fins 707 and an air-breathing hybrid propulsion rocket 709.

(21) In a preferred embodiment, the integrated flute and hat 203 is configured on a rocket or airplane such that two-thirds of the length of the integrated flute and hat is placed on the airplane/rocket/or a nosecone and one-third of its length is in front of the nosecone to bring about the isothermal compression of the air in front of nosecone. The flare design of the hat mitigates the length of the choke.

(22) Referring to FIG. 8, 800 which illustrates the elements of a (fluted) supercritical shockwave piercing hypersonic wing whereby flutes 801/811 and 850/860/807/880 (which may be continuous slotted, stepped, oval and/or rounded) functions as micro-scaled shockwave abatement Busemann biplane wings with the refractive shock front expanding linearly within hat section 812 over vortex wedges 831/832 and supercritical area ruled chord 840 in accordance with the isothermal chilling protocol FIG. 400.

(23) Referring to FIG. 9, 900 which illustrates the transformation of the legacy Busemann (biplane) shockwave abatement postulation whereby leading shockwaves 911 generated refractive shockwaves 912 as (1) macro-scaled Busemann supersonic Mach 2/5 airliner with leading/refractive shockwaves 921/922, supersonic Busemann biplane wings 920 and (supersonic) airframe 923 (2) a micro-scaled Busemann supersonic shockwave abatement leading edge slots 930/934 and (3) regenerative cryogenically chilled M2/20 SPINNX hypersonic vortex choke 940/944/945.

(24) Referring to FIG. 10, 1000 which illustrates an alternate embodiment of FIG. 5. The articulated clamshell Busemann turbojet air intake aperture 1011 housing turbojet 1012 that may be opened/closed in accordance with the Mach domain that may be (1) applied for takeoff and transonic acceleration power and (2) supply bleed air to drive combustion of the primary hybrid propulsion unit 20013 at takeoff. Pointer 1001 illustrates the fluted Busemann derivative hypersonic shockwave muffler, 1009 illustrates the primary air-breathing propulsion unit and pointer 1031 an ancillary/piggy-back orbital incretion payload.

(25) The many aspects and benefits of the invention are apparent from the detailed description, and thus, it is intended for the following claims to cover all such aspects and benefits of the invention which fall within the scope and spirit of the invention. In addition, because numerous modifications and variations will be obvious and readily occur to those skilled in the art, the claims should not be construed to limit the invention to the exact construction and operation illustrated and described herein. Accordingly, all suitable modifications and equivalents should be understood to fall within the scope of the invention as claimed herein.