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Publication numberUS3477376 A
Publication typeGrant
Publication dateNov 11, 1969
Filing dateMar 6, 1968
Priority dateMar 6, 1968
Publication numberUS 3477376 A, US 3477376A, US-A-3477376, US3477376 A, US3477376A
InventorsBlatt Milton D, Miller Howard A, Nelson Harry A, Oeland Ernest N Jr
Original AssigneeUs Navy
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Missile nose cap
US 3477376 A
Abstract  available in
Previous page
Next page
Claims  available in
Description  (OCR text may contain errors)


Tfiwh www fwfiiw. T T A y T m o wmr mm iii55:55::t:=-55::iiiit:ibnzfii: 5? w Om United States Patent 3,477,376 MISSILE NOSE CAP Harry A. Nelson, Sierra Madre, Ernest N. Oeland, Jr., West Covina, Howard A. Miller, Altadena, and Milton D. Blatt, (Jovina, Califi, assignors to the United States of America as represented by the Secretary of the Navy Filed Mar. 6, 1968, Ser. No. 711,471 Int. Cl. F42b /20, 15/22, 22/00 Us. or. 102 s4 3 Claims ABSTRACT OF THE DISCLOSURE The invention described herein may be manufactured and used by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor.

BACKGROUND OF THE INVENTION The ASROC (antisubmarine rocket) system comprises an underwater missile which is launched from shipboard by a tandem rocket motor which separates at a point in the air trajectory, the missile thence following a ballistic trajectory to the point of impact with the water. In one variation of the missile, it carries a depth charge payload and sinks to a target locus without propulsion. The forward end of the missile is flat with a radiused transition to its outer diameter, this configuration being optimum for course stability after it enters the water and also for obviating broaching upon water entry. Such configuration, however, is not ideal for the air trajectory since it has undesirable air drag and other aerodynamic characteristics. It has been the practice, accordingly, to provide a frangible nose cap on the missile which reduces air resistance and disintegrates upon Water entry, thus providing an optimum nose configuration for both the air trajectory and directional course in the water. It also serves the purpose of absorbing some of the energy of water impact to obviate damaging shock loads on its internal components. Due to the desire to increase the range of such missile, a redesign of the nose cap has been found necessary, due to increased water entry velocity and its attendant increase in water entry shock. Also, to improve its stability in its ballistic trajectory, after separation from the rocket motor, it has been found desirable to shift the center of mass of the missile forwardly. Nose caps of the type referred to are well known, the patent to Howard, US. 2,889,772, being exemplary of an early development disclosing the use of a frangible foam material for mitigating shock. The patent to West, US. 3,048,110, is exemplary of a later development, utilizing foam material and other frangible components, and the patent to West, US. 3,110,262, is exemplary of a still later development utilizing the addition of a mass of lead shot.

BRIEF DESCRIPTION OF THE DRAWING FIG. 1 is a side elevation of a conventional missile and the attached nose forming the subject of the invention;

FIG. 2 is an enlarged section taken on line 22, FIG. 1; and

FIG. 3 is a fragmentary view in the direction of arrow 3, FIG. 2.


DESCRIPTION OF THE PREFERRED EMBODIMENT Missile 10 is circular in cross section, having a generally cylindrical forward end 12 and a generally frustoconical tail cone 14 to which is affixed stationary stabilizing fins 16. A rocket motor (not shown) is affixed to the rear end of the missile which separates from same at a desired point in the air trajectory. The forward end of the missile is provided with a flat face 18 and a curved transition surface 20 with a radius of approximately of the missile diameter, the construction so far described being conventional.

Nose 22 comprises an ogival shell 24 formed of epoxy impregnated fibre glass cloth which is spirally wound on a mandrel and cured, the outer surface thereafter being machined to a smooth finish. The front end is provided with an aperture 26 which receives one end of a fibre glass tube 28, the purpose of which will subsequently be described. A frangible cast aluminum member 30 comprises a disc shaped base 32, a tubular portion 34 and equiangularly spaced radial ribs 36, joining the base and tubular portion. Slots 38, disposed between the ribs, extend through the base and tubular portion to weaken the member and facilitate break-up of same. A mass of lead shot 40 is disposed in the forward end of the shell and the remainder of the space is filled with foam material 42. The rear end of a stud 44 threadedly engages the missile and a nut 46 threadedly engages its front end, the nut abutting a shoulder 48 on member 34 which retains the entire nose assembly on the missile. A metallic nose tip fairing 50, having a projection 52, threadedly engages the front end of member 34.

In the fabrication of the nose, shell 24 is disposed on a support with the plane of its rear end in a horizontal position. Tube 28 is then inserted in aperture 26. The desired amount of lead shot 40 is then poured into the shell and leveled. A measured quantity of liquid foaming material is then poured into the shell to a level somewhat below the upper end of tube 28. Member 30 is then dropped into the tube, seating on an annular abutment 54, and a plug (not shown) having the shape of the front end of the missile, is disposed in the base end of the shell and suitably clamped therein in engagement with the rear face of base 32. As the foaming material expands it fills the entire space between the shot and the front surface of base 32 and around its periphery and against the plug.

What is claimed is:

1. In an elongated rocket propelled missile of circular cross section adapted to enter water from a terminal ballistic trajectory after its separation from a rocket motor, the missile having a fiat circular front surface of a diameter approximately one-half of the missile major diameter and a surrounding annular radiused transition surface joining the flat surface with the outside surface of the missile, the improvements comprising an ogival nose affixed to the front end of the missile and projecting forwardly thereof for a distance in excess of the missile major diameter, said nose including:

(a) a frangible fibre glass shell;

(b) a frangible metallic member having a disk shaped fiat base abutting said flat surface of the missile;

(c) an integral tubular portion projecting forwardly from said flat base and to the front end of the shell;

((1) the metallic member having integral angularly spaced radially extending ribs joining its base and the tubular portion and having radially extending weakening slots extending through the base and tubular portion;

(e) a mass of lead shot disposed in the forward end of the shell and surrounding said tubular portion;

(f) frangible foam material filling the space between the lead shot and said base and the space surrounding said transition surface;

(g) a rod afiixed to the forward end of the missile and extending axially and forwardly thereof substantially the length of the shell and adapted to shear from the missile adjacent said flat surface upon water entry of the missile;

(h) a nut threadedly engaging the front end of the rod,


(i) a nose tip providing an ogival fairing for the front end of the shell and closing access to said nut.

2. A nose in accordance with claim 1, including a fibre glass tube having its forward end disposed within an axial bore in the front end of the shell and extending rearwardly thereof, its rear end being disposed between the shot and said base, said tube being of an internal diameter to slideably receive said tubular portion, said tube forming an annular space therearound into which a measured quantity of liquid foaming material may be poured when the longitudinal axis of the shell is disposed vertically and before said tubular portion is slideably inserted in said tube.

3. The method of assemblying a nose for a missile, said nose comprising a prefabricated ogival shell having an open end, a prefabricated frangible metallic member having a disc shaped base and a projecting tubular portion, a mass of lead shot, and a frangible tube, which comprises the steps of:

(a) supporting the shell with its longitudinal axis disposed in a vertical position;

(b) inserting the front end of the tube into the front end of the shell;

(c) pouring the mass of shot into the shell and leveling same;

(d) pouring a measured quantity of liquid foaming material into the shell;

(e) inserting said tubular portion into said tube; and

(f) securing a plug to the open end of said shell in abutting relation with said base, preventing flow of said foaming material fro-m the shell when it expands to fill same.

References Cited UNITED STATES PATENTS 2,889,772 6/1959 Howard 102-7 3,048,110 8/1962 West 102-54 X 3,110,262 11/1963 West 102-54 3,135,204 6/ 1964 Menichelli et a1. 102-54 3,279,405 10/1966 Billmeyer 102-7 X 3,338,167 8/1967 Jurgermann et a1. 102-92.7

VERLIN R. PENDEGRASS, Primary Examiner U.S. Cl. X.R. 102-7

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US2889772 *Jul 9, 1957Jun 9, 1959Howard Earle AProtective nose cap for torpedoes
US3048110 *Sep 15, 1959Aug 7, 1962West Stanley EFrangible nose cone
US3110262 *Feb 2, 1962Nov 12, 1963West Stanley EShock mitigating nose
US3135204 *Feb 13, 1963Jun 2, 1964Baidwin Howard MMeans for explosively removing the nose cone of a missile
US3279405 *Mar 29, 1965Oct 18, 1966Billmeyer Allen KTorpedo nose cap retaining device
US3338167 *Oct 21, 1965Aug 29, 1967Karlsruhe Augsburg IwekaDisintegrating training ammunition for firearms
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US4593637 *Jun 4, 1984Jun 10, 1986The United States Of America As Represented By The Secretary Of The NavyFor a torpedo
US4722876 *May 13, 1987Feb 2, 1988Hummel Roger LLiquid activated battery
US4788914 *Feb 8, 1988Dec 6, 1988Loral CorporationMissile nosepiece
US5955698 *Jan 28, 1998Sep 21, 1999The United States Of America As Represented By The Secretary Of The NavyAir-launched supercavitating water-entry projectile
US8093487 *Jan 28, 2009Jan 10, 2012The Penn State Research FoundationRemovable protective nose cover
US8256086 *Jun 25, 2009Sep 4, 2012Lockheed Martin CorporationMethod of producing missile nose cones
US20100326182 *Jun 25, 2009Dec 30, 2010Shulter Robert AMethod of producing missile nose cones
USH1938 *Jan 13, 1999Feb 6, 2001The United States Of America As Represented By The Secretary Of The NavySupercavitating water-entry projectile
U.S. Classification102/399
International ClassificationF42B10/00, F42B10/46
Cooperative ClassificationF42B10/46
European ClassificationF42B10/46