Title:
Rocket stabilizing fins
United States Patent 2430896
Abstract:
The invention described herein may be manufactured and used by or for the Government for governmental purposes without the payment to us of any royalty thereon. This invention relates to flight stabilizing fins for a rocket projectile, more particularly to collapsible stabilizing fins therefor....


Inventors:
Uhl, Edward G.
Skinner, Leslie A.
Application Number:
US51753044A
Publication Date:
11/18/1947
Filing Date:
01/08/1944
Assignee:
Uhl, Edward G.
Skinner, Leslie A.
Primary Class:
International Classes:
F42B10/14
View Patent Images:
US Patent References:
1879840Bladed projectile1932-09-27
1166879N/A1916-01-04
Description:

The invention described herein may be manufactured and used by or for the Government for governmental purposes without the payment to us of any royalty thereon.

This invention relates to flight stabilizing fins for a rocket projectile, more particularly to collapsible stabilizing fins therefor.

It is an object of this invention to provide improved collapsibly mounted stabilizing fins for a rocket projectile.

The specific nature of the invention as well as other objects and advantages thereof will clearly appear from a description of a preferred embodiment as shown in the accompanying drawing in which: Fig. 1 is a fragmentary side view of a rocket projectile partly in longitudinal section with the fins in the collapsed position showing the manner of mounting such fins about the periphery of the rocket nozzle.

Fig. 2 is a fragmentary side elevational view of the rocket showing the collapsible fins in the extended position.

Fig. 3 is a right end elevational view of Fig. 1 showing the ends of the collapsed fins.

Fig. 4 is a side elevational view of the nozzle showing in detail the grooved and slotted flange utilized for pivotally mounting the collapsible fins.

Fig. 5 is a right end elevational view of Fig. 4.

Referring to the drawing wherein like characters refer to similar parts there is shown in Fig. 1 a, rocket projectile embodying this invention. A nozzle 2 having an interior of conventional Venturi construction commonly employed in rocket projectiles is secured to a rocket motor housing I as by threads 3. An integral flange 4 is provided about the outer periphery of nozzle 2. An annular groove 5 is provided about the periphery of flange 4 and is centrally located therein. A plu- 4 rality of equally disposed transverse slots 6 are provided about flange 4 for mounting fins 7, one fin in each of such slots.

Fin 7 comprises a thin strip of metal having a short tab 8 on one end bent at right angles to the 4 body portion of each fin 7. Each tab 8 is also sloped as shown in Fig. 2 so that the air resistance forces on the fins during flight of the projectile will maintain the fins in extended position. A small rectangular notch 9 is provided in 56 the other end 15 of fin 7 thereby forming a stop surface 10. Each fin 7 is then inserted in a corresponding slot 6 in flange 4, with tab 8 facing forwardly or to the right as shown in Fig. 1, so that notch 9 rests on top of nozzle 2 and stop 56 surface 10 abuts the forward end of nozzle 2. A transverse hole II is provided in each fin 7 and is so positioned that when fins 7 are mounted on nozzle 2 the holes II will be aligned with groove 5. A wire 12 is then threaded thru each of the 6 holes I in fins 7 and lies in groove 5. The ends of wire 12 are then suitably secured together by twisting or soldering. The wire 12 may be further secured within groove 5 by upsetting the sides of flange 4 into groove 5 as indicated at 13 in Fig. 2 midway between each of the fins 7. A rounded corner 14 is provided on the squared end of each fin 7 to permit the fins 7 to pivot about wire 12.

As previously mentioned fins 7 are mounted with tabs 8 facing the head of the projectile (not shown). Thus when the projectile is launched -the tabs 8 being at a substantial angle to the axis of the projectile will be forced outwardly to the extended position shown in Fig. 2. The fins 7 are stopped in this extended position by the end 15 of each fin engaging the bottom of slots 6 and they will be maintained in such position as long as the projectile is in flight by the air pressure against the fins.

In the practice of this invention it was discovered that an even number of fins, preferably six fins as showh in the accompanying drawing, proved highly satisfactory. Greatly improved stabilizing effects were obtained in flight trials with rockets embodying this invention when the tabs 8 were bent alternately in a right hand and a left hand direction and each pair of opposed fins spaced 120° apart as shown in Fig. 3.

It is thus apparent that a simple and easily manufactured positive securing means for pivotally mounting collapsible fins on a rocket projectile is hereby provided.

We claim: In a rocket projectile the improvement comprising a projecting flange around the periphery of the rocket projectile, an annular groove in said flange, a plurality of fins, each of said fins having a hole in one end thereof, means on said flange for receiving said fins in spaced relation 0 about the periphery of the flange and with said holes aligned with said annular groove, each of said fins having a portion at its distal end bent transversely to the plane of the fin, and said fins being disposed on said projectile in equi-spaced 5groups of two adjacent fins, each group having their bent end portions in mutually facing relation and a fastener traversing said holes and said annular groove whereby said fins are pivotally secured to said flange.

0 EDWARD G. UHL.

LESLIE A. SKINNER.

REFERENCES. CITED The following references are of record in the 5 file of this patent: UNITED STATES PATENTS Number Name Date 1,166,879 Alard -------------- Jan. 4, 1916 1,879,840 Brandt ----------- Sept. 27, 1932