US3111901A

US3111901A - Frangible firing device

Info

Publication number: US3111901A
Application number: US70893A
Authority: US
Inventors: Harold L Dodson; William A Danesi
Original assignee: Individual
Current assignee: Individual
Priority date: 1960-11-21
Filing date: 1960-11-21
Publication date: 1963-11-26
Anticipated expiration: 1980-11-26

Description

United States Patent ce Patented Nov. 26, 1963 URE 3. Applied to the exterior of electrically non- 3,111,901 conductive nose-cone section 10 by means well known in FRANGIBLE FIRING DEVICE the art, is printed circuit 18. This printed circuit is ap- Harold L. Dodson, King of Prussia, and William A. Danesi, Wayne, Pa assignors to the United States of America as represented by the Secretary of the Army Filed Nov. 21, 1960, Ser. No. 70,893 1 Claim. (Cl. I027 0.2)

This invention relates to a fuzing device for mounting on a missile and more particularly to an electrical means printed on a frangible body for detonating the missile warhead before warhead damage occurs as a result of impact.

The typical fuzing system generally employs a piezoelectric crystal in such a manner that when compressed, as by impact, an electrical impulse is generated which serves to detonate the warhead. With such devices as these, however, the necessary electrical impulse is generated only when the warhead impacts the target with sufficient force to compress the piezoelectric crystal surfaces. Accordingly, a glancing impact between crystal and target may be insufiicient to generate the necessary detonating voltage. In the case of spike-type targets, it is absolutely essential that the crystal and target meet precisely head-on, otherwise there will be a complete failure to detonate. Additional deficiencies of employing piezoelectric crystals lie in their sensitivity to temperature changes and their ability to accumulate and retain electrical charges on their surfaces thereby adding to the drawbacks and inadequacies previously mentioned.

A surface fuzing system must supply the proper fuzing signal to the warhead before any warhead damage occurs as a result of impact. The ultimate surface fuzing system would be one that would fuze the missile at instant of impact with the target. However, practical aspects of this system must include safety factor allowances for handling, shock, vibration, temperature extremes, and the like.

It is an object of this invention, therefore, to overcome these objectional features of the prior art and provide a fuzing system which will detonate the warhead almost instantly upon impact.

A further object of this invention is to provide a missile nose cone of frangible material having a printed circuit thereon, which nose cone will shatter on impact interrupting said circuit and detonate the warhead.

These and other objects will become more apparent when reference is had to the following detailed description and drawings in which:

FIGURE 1 illustrates an elevation of a stepped nosecone having a printed circuit schematically shown thereon;

'FIGURE 2 illustrates a cross-sectional view taken on line 2-2 of FIGURE 1;

FIGURE 3 shows a typical missile body having mounted thereon on frangible nose-cone having a printed circuit interiorly thereof and connected to a conventional warhead;

FIGURE 4 illustrates a cross-section of the nose-cone of FIGURE 3 taken on line 4-4 and showing the printed circuit on the interior thereof;

FIGURE 5 illustrates a nose-cone having a solid nosecone shown in section, and a frangible portion with a printed circuit immediately to the rear of the solid section; and

FIGURE 6 schematically illustrates a typical fuzing and detonatin g circuit.

Referring now in more detail to the drawings and particularly to FIGURES 1 and 2 thereof, there is shown a stepped, resinous nose-cone section 10 of thermosetting plastic or other frangible, electrically non-conductive material, having a substantial ring portion 12 with a plurality of equally spaced mounting holes 14 for attaching to a conventional missile body 16, typically shown in FIG- plied in a pattern such that maximum coverage over the entire nose-cone section is obtained. The ends of printed circuit 18 terminate in connections 2% which extend through to the interior of nose-cone section '10 for connection to a warhead section 11 schematically shown in FIGURE 3.

In operation, the circuit 18 may be energized at or before missile launching. However, on impact with a target, the resinous nose-cone, because of its brittle character, will shatter, thereby interrupting the energized printed circuit causing the warhead to detonate. The circuit schematically illustrated in FIGURE 6 shows, by way of example, only a typical arrangement for accomplishing the detonation, wherein such circuit comprises a source of potential P, a switch S which is closed just prior to launching, a resistor R, a gas-filled diode D, and warhead E. Short-circuit xy depicts what in actuality is printed circuit 18 whereby at launching and prior to impact only that portion of the circuit comprised of P, S, R, x, and y is energized. At impact, x-y becomes interrupted thereby allowing electrical flow from R to D and E resulting in the det-onating of the warhead. The time which elapses between circuit rupture and detonation amounts to only a few milli-seconds; consequently the distance which the warhead continues to travel toward the target during this brief interval is insufficient to do any damage to the warhead portion. By proper design of the nose cone, shattering of this component can be predicted for high or low velocity impacts.

FIGURE 4 illustrates a modification of the preferred embodiment of this invention wherein the printed circuit portion 18a of the fuze circuitry is placed on the interior surface of a nose-cone portion 102:: so as to adequately cover the entire expected target contact area of the nosecone. Circuit connections 20a extend through the nosecone body from the interior to the exterior surface for suitable connections thereto and to facilitate the required missile check-out procedure prior to launching.

FIGURE 5 is a further modification illustrating a nosecone section having a solid tip portion 22 with a frangible section 2'4 immediately rearward thereof, the frangible portion having a printed circuit 18b on its surface terminating in connections Ztlb. As shown in FIGURE 5, the nose cone is connected to the missile body 24 by circumferential means 26. Any target impact forward of connection 26 will cause shattering of the nosepone thus producing the switch opening necessary to generate a pulse to initiate a firing train.

Thus, it is now readily apparent that by fitting an electrical circuit on a frangible missile component of dielectric material, and locating this component so as to impact with a target with sufiicient force to fracture the material and interrupt the printed circuit, a fuz-ing pulse can be generated to detonate the warhead almost instantly. By fabricating the frangible component from a resinous material, standard techniques of applying printed circuits can be readily utilized with ease and economy.

This invention is not limited to nose-cone applications, however, but may be employed on any portion of a missile body and the resinous material need not necessarily rupture completely, but just enough to interrupt the electrical continuity of the printed circuit on its surface.

Having particularly described our invention, it is obvious that many modifications and variations may be re sorted to by those skilled in the art without departing from the scope of the appended claim.

We claim:

A surface fuz-ing device for a missile having a warhead and a detonating circuit for said warhead, said fuzing References Cited in the file of this patent UNITED STATES PATENTS Winkley June 3-0, 1925 Bleakney et a1 July 12, 1955 Ward May 28, 1958 Perret May 19, 1959 FOREIGN PATENTS Great Britain Oct. 2, 1957