US2994271A

US2994271A - Fuze arming device

Info

Publication number: US2994271A
Application number: US425058A
Authority: US
Inventors: Silver Meyer; Donald F Herdman; William F Hassel
Original assignee: Individual
Current assignee: Individual
Priority date: 1954-04-22
Filing date: 1954-04-22
Publication date: 1961-08-01
Anticipated expiration: 1978-08-01

Description

Aug. 1, 1961 M. SILVER ETAL FUZE ARMING DEVICE Filed April 22. 1954 INVENTORS MEYER SILVER DONALD F. HERDMAN WILLIAM F, HASSEL ATTORNEYS United States Patent 2,994,271 FUZE ARMING DEVICE Meyer Silver, Donald F. Herdman, and William F. Hassel, China Lake, Calif., assignors to the United States of America as represented by the Secretary of the Navy Filed Apr. 22, 1954, Ser. No. 425,058 1 Claim. (Cl. 102-'70.2) (Granted under Title '35, US. Code (1952), sec. 266) 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.

The present invention relates to fuze arming devices and has more particular reference to apparatus for arming a missile-carried fuze at a predetermined missile flight distance regardless of variation in missile acceleration during the arming period.

Heretofore, various missile fuze arming devices have been evolved. Such prior arming devices were, however, excessively complex, costly to manufacture, ditficult to adjust, and were frequently subject to anal-operation. Moreover, many of the prior arming devices were not designed to compensate for variations in missile acceleration during the fuze arming period with the result that the arming distance of different missiles might vary over a large range. Thus, many of the previous arming devices comprised a clock work mechanism for arming the fuze after a predetermined missile flight time, and owing to variations in missile acceleration during the arming period and variations in the arming-period-accelerations of diflerent rockets, the arming distance of a given rocket could not be fixed within reasonably close limits nor could the arming distances of a series of rockets be made the same within reasonably close tolerances.

The present invention avoids the disadvantages which have been inherent in prior fuze arming devices for missiles by providing a fluid flow, time delay fuze arming device wherein arming of the fuze is accomplished by the movement of an arming plunger through a predetermined distance in a fluid under the force arising from acceleration of the missile, the arrangement being such that the fuze will be armed at a fixed missile flight distance regardless of the value of missile acceleration during the arming period or variations in missile acceleration during the arming period.

In accordance with the foregoing, it is an object of the present invention to provide an improved missile tuze arming device.

Another object of the invention is to provide a device for arming the fuze of a missile at a fixed flight distance from the point of launching regardless of the value of, or variations in the value of missile acceleration during the arming period.

Still a further object of the invention is to provide a fuze arming device as in the foregoing wherein a plunger is, under the force of acceleration of rocket during the arming period, caused to move through a fluid for a predetermined distance whereby to cause the fuze to arm at a fixed predetermined missile flight distance from the point of launching regardless of the value of, or variations in the value of the missile acceleration during the arming period.

Other objects and many of the attendant advantages of the present invention will become apparent as the same becomes better understood from the following detailed description had in conjunction with the annexed drawings wherein:

FIG. 1 is a longitudinal sectional view of the present fuze arming device; and

FIG. 2 is a transverse sectional view taken substantially along line 22 of FIG. 1.

Referring now to the drawing and more particularly to FIG. 1, the fiuze arming device of the present invention comprises a housing or shell 10, which may be cylindrical in cross-section as shown, closed at one end wall portion 12 and at the other end by closure member 14 which may be removably secured within the shell 10 by a threaded connection, as shown, or other suitable means. Shell 10 and its

end closures

12 and 14 form a fluid-tight container which is filled with a temperature stable fluid 16, such as a silicone oil. Secured at opposite ends to the

closure members

12 and 14 and disposed on the axis of shell 10 is a longitudinally extending rod 18 having slid-ably mounted thereon a plunger 20 of desired crosssectional configuration. The transverse dimensions of plunger 20 are substantially less than those of shell 10 whereby to define a clearance space or orifice 22, as shown more clearly in FIG. 2, between the plunger 20 and the inner wall of shell 10. A spring member 24 which abuts the closure member 14 and the plunger 20 serves to bias the latter to one end of the shell 10, as shown. Aflixed to shell 10, adjacent one end of, is some suitable type of electrical switching means for completing an electrical circuit to arm the fuze (not shown). Thus, switch 26 may comprise a magnetic arrangement which will be actuated to its closed position owing to a change in the magnetic field when the plunger 20, which may be of a magnetically permeable material, is moved adjacent switch 26.

In the operation of the present invention, a force proportional to the product of plunger mass and missile acceleration will act on the plunger 20 during the period of missile acceleration following launching of the latter. Plunger 20 will, under the action of this force, be caused to accelerate along rod 18 and through the fluid 16 with a resultant flow of the latter around the plunger and through the space 22. During such plunger movement, fluid 16 will exert force on plunger 20 which opposes that due to missile acceleration and whose instantaneous value is proportional to the square of instantaneous plunger velocity. As the plunger continues to accelerate, its velocity reaches first a critical value, whereat the fluid flow rate around the plunger attains a critical value and laminar flow changes to turbulent flow, and finally a limit value at which the acceleration force acting on the plunger is exactly balanced by the restraining force of the fluid. Upon the plunger attaining the limit velocity, acceleration thereof ceases, owing to the balance of the forces acting thereon, and it will continue to move along rod 18 at a uniform fixed velocity, namely the limit velocity, Whose value is proportional to the missile acceleration. If the latter remains constant the limit velocity will remain constant. If, however, missile acceleration should vary, owing to a change in thrust, for example, the limit velocity of the system will change until the restraining force of the fluid on the plunger equals that due to the new value of missile acceleration. The physical characteristics of the system, such as the mass and shape of the plunger and viscosity of fluid 16, are made such that the plunger will be accelerated to its limit velocity within a relatively small movement along rod 18 whereby the plunger will move at the limit velocity along substantially the entire length of the rod and, therefore, a given total plunger movement will correspond to a given missile flight distance. Thus, by locating the switch means 26, a predetermined distance from the normal or at rest position of the plunger, the fuze may be armed at any desired missile flight distance. Because of the above described characteristics of the system, the fuze will be armed at the same flight distance regardless of variations in missile acceleration. Spring 24 serves to retain plunger in its rest position illustrated and prevent arming of the fuZe under impact loads such as might be occasioned if the missile is dropped.

Obviously many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claim, the invention may be practiced otherwise than as specifically described.

What is claimed is:

In a missile subjected to forward acceleration in the direction of its trajectory, the improvements in combination, comprising: a fuze arming device carried by the missile having an element adapted to move in a substantially rearward direction relative to said forward direction, and electrical switching means adapted to be actuated in response to a predetermined rearward movement of said element, said device including a cylinder, and said element comprising a piston adapted to move in said cylinder, said cylinder containing a fluid adapted to bypass from one side of said piston to the opposite side of same as the piston moves rearwardly within the cylinder, said piston being constructed of magnetically permeable material, and said switching means comprising a magnetic switching device positioned externally of said cylinder adapted to be actuated when said piston moves adjacent thereto.

References Cited in the file of this patent UNITED STATES PATENTS