Search Images Maps Play YouTube News Gmail Drive More »
Sign in
Screen reader users: click this link for accessible mode. Accessible mode has the same essential features but works better with your reader.

Patents

  1. Advanced Patent Search
Publication numberUS3745928 A
Publication typeGrant
Publication dateJul 17, 1973
Filing dateDec 3, 1971
Priority dateDec 3, 1971
Publication numberUS 3745928 A, US 3745928A, US-A-3745928, US3745928 A, US3745928A
InventorsCasadevall J, Kinnaird L, Moorhead S
Original AssigneeUs Army
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Rain resistant, high strength, ablative nose cap for hypersonic missiles
US 3745928 A
Abstract
An ablative nose cap for slender type missiles in which the nose cap has a base member for securing the nose cap to the missile proper, an insulation member at the head end of the base member, a back-up nose tip mounted relative to the insulation member, a unidirectional fiber rod in front of the back-up tip and an outer wrap of reinforced phenolic about the outer surfaces of the several members to provide an outer ablative cover. The nose cap is designed for hypersonic speeds and for maintaining its structural and thermal integrity after particle impact encounters with rain, ice or dust at hypersonic velocities.
Images(1)
Previous page
Next page
Claims  available in
Description  (OCR text may contain errors)

[111 3,745,928 [4 1, July 17, 1973 RAIN RESISTANT, HIGH STRENGTH,

ABLATIVE NOSE CAP FOR I'IYPERSONIC MISSILES Inventors: Laird D. Kinnaird; Seth B.

Moorhead, Jr.; James L. Casadevall, all of Orlando, Fla.

The United States of America as represented by the Secretary of the Army, Washington, DC.

Filed: Dec. 3, 1971 Appl. No.: 204,591 I [73] Assignee:

us. c1. 102 105, 244/117 A Int. Cl. F42b 11 00, F42b 13/00 Field of Search 102/105; 244/117 A, 244/23 3,026,806 3/1902 Runton et al. 102/105 Primary Examiner-Robert F. Stahl Attorney-Williarn G. Gapcynski, Lawrence A.

Neureither et al.

ABSTRACT An ablative nose cap for slender type missiles in which the nose cap has a base member for securing the nose cap to the missile proper, an insulation member at the head end of the base member, a back-up nose tip mounted relative to the insulation member, a unidirectional fiber rod in front of the back-up tip and an outer wrap of reinforced phenolic about the outer surfaces of the several members to provide an outer ablative cover. The nose cap is designed for hypersonic speeds and for maintaining its structural and thermal integrity after particle impact encounters with rain, ice or dust at hypersonic velocities.

7 Claims, 1 Drawing Figure PATENIEB Jul 7 Laird D.Kinnc|ird Seth B. Moorheud Jr.

James L.Cosadevoll, INVENTORS RAIN RESISTANT, HIGH STRENGTH, ABLATIVE NOSE CAP FOR HYPERSONIC MISSILES BACKGROUND OF THE INVENTION In missiles, there is a need for a nose cap that can be suited to slender vehicles and capable of operating with high ballistic factors in the supersonic and hypersonic (6,000-25,000 ft/sec) flight regime. It is also important that the nose cap remain sharp during ablation and that the nose cap be capable of carrying high structural and shock loads without failure. The nose cap must maintain vehicle integrity after particle encounter with rain, ice or dust at hypersonic velocities. Present nose caps are unable to attain these requirements.

Therefore, it is an object of this invention to provide a nose cap that is capable of operating on high acceleration vehicles that reach ballistic factors in the supersonic and hypersonic flight regime.

Another object of this invention is to provide an ablative nose cap that is capable of carrying high structural and shock loads without failure.

A further object of this invention is to provide a nose cap that maintains vehicle integrity after rain, ice or dust encounter at hypersonic velocities.

SUMMARY OF THE INVENTION In accordance with this invention, a nose cap is provided that includes a body structure that is generally frustoconical in shape and has provisions at the forward end for receiving an insulating member. Supported by the insulating member is a back-up nose tip. Forward of the back-up nose tip, unidirectional fibers in the form of a center reinforcement rod is mounted. About the center reinforcement rod, the back-up nose tip, the insulating member, and the body structure, outer'layers of molded fiber reinforced plastic is mounted. This structure provides a nose cap that is capable of carrying high structural and shock loads and still maintain vehicle integrity after particle encounters at hypersonic velocities. This is accomplished by allowing the center rod and outer ablative materials to be eroded away and by providing the back-up, refractory and impact resistant, nose tip that takes over when the ablative materials have been eroded or ablated away.

BRIEF DESCRIPTION OF THE DRAWING The single FIGURE of the drawing is a sectional view through a nose cap according to this invention.

DETAILED, DESCRIPTION OF THE INVENTION Referring to the drawing, nose cap 11 includes body structure 13 with opening 15 at one end which mounts insulating material 17 that acts as heat insulation for back-up nose tip 19. Heat insulating member 17 is secured to the forward end of body structure 13 by conventional heat resistant bonding material. Back-up tip 19 is secured to heat insulating member 17 by conventional bonding adhesive. Heat insulating material 17 is preferably made from materials such as quartz phenolic, silica phenolic, zirconium or the like. This heat insulating member may be molded or machined. Back-up tip 19 is preferably made from tungsten impregnated with l7 percent copper, but may also be made from tungsten, tungsten copper, tungsten moly, tungsten silver, tungsten tantalum, or other refractory metal as the particular case may warrant.

Center reinforcement rod 23 is made of unidirectional high strength fibers that run down the center of the nose cap to provide high bending and longitudinal strength. Reinforcement rod 23 is preferably made of unidirectional quartz roving impregnated with phenolic resin, but may also be made from silica, glass or other unidirectional fibers. Further, a first outer layer 25 of bonded silica or quartz phenolic covers a portion of the reinforcement rod, the back-up nose tip, the insulating member and a portion of the body structure, and an outermost layer 27 of spiral wrapping of silica phenolic forms the outermost layer of the nose cap. Outerrnost layer 27 is spirally wrapped on edge in a tapering manner as illustrated by the cross hatching in the drawing. After assembling, the entire nose cap is cured under temperature and pressure as required such as for example approximately 4 hours at approximately 330350 F. After curing, the nose cap is then ready for use except for smoothing of the outer surface if desired.

In operation, inclusion of end grain high strength center rod 23 enables the nose tip to carry high shock and static loads and the favorable fiber orientation provided by the end grain rod allows the nose to stay sharp during ablation. Back-up tungsten tip 19 provides impact protection when center rod 23 has been ablated away. The cone angle and tip radius of the nose cap illustrated is not critical and can be varied as required by aerodynamic and/or structural requirements.

We claim:

1. A nose cap comprising a body member that has a generally frustoconical outer surface and a forward end with an opening therein, a heat insulating member mounted at the forward end of said body member and in said opening of said body member, said heat insulating member having an opening therethrough, a refractory metal back-up tip secured to and mounted in said opening of said heat insulating member, a center reinforcement rod mounted forward of said back-up tip, and ablative fiber reinforced plastic about the outer surface of said body member, said heat insulating member, said back-up tip and said center reinforcement rod to form said nose cap.

2. A nose cap as set forthin claim 1, wherein said heat insulating member is made from materials selected from the group consisting of silica phenolic, quartz phenolic and zirconium.

3. A nose cap as set forth in claim 2, wherein said back-up tip is made from refractory metal selected from the group consisting of tungsten, tungsten moly, tungsten copper, tungsten silver, and tungsten tantalum.

4. A nose cap as set forth in claim 3, wherein said back-up tip is made from the metal tungsten impregnated with 17 percent copper.

5. A nose cap as set forth in claim 4, wherein the fibers of said reinforcement rod are selected from the group consisting of quartz, silica, and glass.

6. A nose cap as set forth in claim 5, wherein said ablative fiber reinforcement plastic includes a first outer layer of quartz phenolic and an outermost layer of silica phenolic.

heat insulating member phenolic.

i i i i l is made from molded silica

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US3026806 *Mar 22, 1957Mar 27, 1962Russell Mfg CoBallistic missile nose cone
US3536011 *Dec 26, 1967Oct 27, 1970Martin Marietta CorpSelf-sharpening,high ballistic factor vehicle nose cap
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US3949682 *Jun 10, 1974Apr 13, 1976The United States Of America As Represented By The Secretary Of The NavyTowline thermal protection system
US4220297 *Dec 20, 1978Sep 2, 1980The United States Of America As Represented By The Secretary Of The ArmyFinlet injector
US4392624 *Feb 6, 1981Jul 12, 1983The United States Of America As Represented By The Secretary Of The Air ForceImplanted boundary layer trip
US4686128 *Jul 1, 1985Aug 11, 1987Raytheon CompanyProtective covering of an ablative layer and a fibermatrix insulation layer having venting grooves; aircraft; aerospace
US4702439 *Jan 20, 1987Oct 27, 1987The United States Of America As Represented By The Secretary Of The NavyTolerance gap containing frangible washer
US4706912 *Dec 16, 1985Nov 17, 1987The United States Of America As Represented By The Secretary Of The ArmyStructural external insulation for hypersonic missiles
US5173350 *Sep 18, 1990Dec 22, 1992Aerospatiale Societe Nationale IndustrielleThermal protection coating comprising a fiber reinforced main layer and an insulative sublayer
US5232534 *Sep 24, 1992Aug 3, 1993Aerospatiale Soiete Nationale IndustrielleThermal protection coating, and method and installation for manufacturing it
US5340058 *Sep 28, 1992Aug 23, 1994Rheinmetall GmbhProjectile with cooled nose cone
US7237752 *May 18, 2004Jul 3, 2007Lockheed Martin CorporationSystem and method for reducing plasma induced communication disruption utilizing electrophilic injectant and sharp reentry vehicle nose shaping
US7267303 *Nov 18, 2004Sep 11, 2007Lockheed Martin CorporationMethod and system for providing cruciform steered, bent biconic and plasma suppression for maximum accuracy
US7721997Aug 1, 2007May 25, 2010Lockheed Martin CorporationMethod and system for providing cruciform steered, bent biconic and plasma suppression for maximum accuracy
US8497456 *Mar 30, 2011Jul 30, 2013Raytheon CompanyGuided munitions including interlocking dome covers and methods for equipping guided munitions with the same
US20120248236 *Mar 30, 2011Oct 4, 2012Raytheon CompanyGuided munitions including interlocking dome covers and methods for equipping guided munitions with the same
WO2007065175A2 *Dec 4, 2006Jun 7, 2007American Spacecraft CorpReusable space launch, orbital, and re-entry vehicle
Classifications
U.S. Classification244/159.1, 244/117.00A
International ClassificationF42B10/46, F42B10/00
Cooperative ClassificationF42B10/46
European ClassificationF42B10/46