US3188957A - Ring stabilizer - Google Patents

Description

June 15, 1965 P. c. PETRE 3,188,957

RING STABILIZER Filed April 3, 1962 2 sheets sheet 1 P c zgmvrox HILIP ETRE wwz p ATTORNEYS June 15, 1965 P. c. PETRE 3,188,957

RING STABILIZER Filed April 3, 1962 2 Sheets-Sheet 2 INVENTOR. 25 24 PHILIP C. PETRE WW6? ATTORNEYS 3,?L88fi5? Fatenteel June 15, 1965 iee 3,183,957 RING STABILIZER I" iiip (I. Petr-e, Santa Barbara, Calif, assigns-r, by mesne assignments, to Aerojet-General Corporation, Azusa, Cali, a corporation of Ohio Filed Apr. 3, 1962, Ser. No. 184,703 2 tjiairns. (Cl. 192-53) This invention relates generally to aerodynamic stabi lizing structures and more particularly to a novel collapsible type ring stabilizer useful on small non-recoverable rockets or missiles.

Conventional missiles are usually stabilized by tail fins. In many instances, such missiles are launched from tubes or similar structures which require that the fins be collapsed in order to minimize the overall diameter of the missile. Such collapsible type structures as have been provided, however, are relatively complicated and add materially to the bulk and expense of the missile itself. The increased expense alone can become material when employed on non-recoverable type missiles. In addition, it has been found that a two or more fin structure for tail stabilization of a missile is not necessarily the most efiicient type of structure from an aerodynamic standpoint.

With the foregoing in mind, it is a primary object of this invention to provide a novel tail stabilizing assembly which is collapsible to a size less than the diameter of the largest body portion of the missile to the end that the missile or rocket with which the structure is employed may be launched from tubes or from places in which space is at a premium.

More particularly, it is an object to provide a novel tail stabilizer for a missile which is aerodynamically more efficient by exhibiting less drag and less mass than stabilizers heretofore employed.

Another object of this invention is to provide a novel tail stabilizer for use on non-recoverable missiles or rockets which may be expanded by means considerably more economical and less bulky than expanding mechanisms employed heretofore.

Briefly, these and many other objects and advantages of this invention are attained by employing a thin ring structure as the stabilizer element. The ring itself is made up of a plurality of arcuate sections hinged together end to end in such a manner that they may be collapsed into a compact configuration. The overall diameter of the structure in its collapsed configuration is less than that of the diameter of the largest body portion of the missile so that the missile may readily be launched from tubes or other areas in which available space is at a minimum.

In the preferred embodiment of the invention, the ring structure is formed from four major arcuate sections and four minor sections alternately connected between the major sections by piano type hinges. Suitable movable members in turn are connected between the major sections and the tail portion of the missile body in such a manner that the structure may be collapsed to a'compact configuration or alternatively expanded into the desired ring shape.

With the foregoing arrangement, all of the advantages of a ring stabilizer are realized together with a tail stabilization assembly which may readily be collapsed to a small size.

A better understanding of the invention will be had by referring to the accompanying drawings illustrating a preferred embodiment, in which:

FIGURE 1 is a fragmentary perspective view of the rear portion of a missile incorporating the improved ring stabilizer of this invention in collapsed configuration;

FIGURE 2 illustrates the ring stabilizer of FIGURE 1 in partially expanded condition;

FIGURE 3 illustrates the stabilizer in completely expanded condition to define a ring; and

FIGURE 4 is a fragmentary cross section of a portion of the stabilizer taken in the direction of the arrows 44 of FIGURE 2.

Referring to FIGURE 1, there is illustrated the rear portion of a missile or rocket body Ill having a longi tudinal axis L as shown by the dash-dot line. Coupled to the rear portion of the missile is the ring stabilizer of this invention designated generally by the numeral 11 and shown in collapsed configuration. In this state, the maximum diameter D of the ring stabilizer is less than the diameter D of the largest portion of the missile body Ill. Accordingly, it will be appreciated that the missile as shown in FIGURE 1 may be readily launched from tubes and the like.

Referring now to FIGURE 2, the ring stabilizer is illustrated in partially expanded position. As shown, the stabilizer itself is formed from a plurality of curved sections Ila, 11b, 11c, 11d, lie, 11 llllg, and lllh. Four of these sections Ila, Illa, lie, and 11g are major sections composed of resilient curved metallic bands. The remaining sections 11b, 11d, 11f, and 1th are minor sections alternately disposed between the major sections and having their ends hinged thereto. With this arrangement, the various sections are all hinged together in an end-to-end manner to define an overall ring configuration when the structure is in expanded form. Two such hingings are illustrated in FIGURE 2 at 12 and 13 for the sections 11g and 11h and the sections 11a and lib, respectively.

The various sections are coupled to the rear portion of the missile by a plurality of movable supporting members 14, 15, 116, and 17. First ends of these members are arranged to be received within longitudinal slots running generally parallel to the longitudinal axis of the missile 10 and circumferentially spaced about the rear body portion thereof. Two of these slots are indicated at is and 19 in FIGURE 2 and serve to receive in slidable relationship the first ends of the members 14 and 11.5, respectively.

The other ends of each of the members are pivoted to central under side portions of the major sections of the ring, such as at 28 and 21 for the major sections Ila and lie.

The configuration in its completely expanded form is illustrated in FIGURE 3 wherein it will be noted that the inner or first ends of each of the members l4, I5, 16, and 1 .7 are positioned at the extreme rear portions of the various slots on the rear of the missile body.

Referring now in detail to the cross section of FIG- URE 4, the various slot structures are defined by walls or flanges such as 22 and 23 for the slot 19. Each of these walls includes an undercut groove such as indicated at 24 for the wall portion 22 in FIGURE 4. Cooperating with these grooves is a transverse projecting member in the form of a pin 25 passing normally through the movable member 15. By this arrangement, the lower end of the movable member 15 may slide back and forth in the slot 19 with the member retained within the slot.

In order that the ring may be locked in its external expanded condition, the ends of the grooves 24 may terminate in a bayonet slot type structure such as indicated at 26 so that the pin 25 will be received in the slot structure 26 and thus the movable members will be prevented from sliding back along the slots.

Preferably, the major sections Ila, lie, lie, and 11g are biased from a curved position towards a fiat condition to lie in an individual plane. Thus, when interconnected with the other sections to form a ring, the natural bias of the section itself will tend to expand the structure into the ring shape or a shape of maximum diameter. Each of the members 14, 15, 16, and 17 is therefore subject to a pulling force from its upper end 9 wherein it is pivoted to the major section in question so that the lower transverse pin 25 will fall within the bayonet portion of the groove as indicated at 24: and as shown in dotted lines in FIGURE 4.

To provide further insurance that the members will remain in a locked position, there may be provided any suitable locking or actuating structure such as a piston rod 27 terminating in a transverse pin structure 28 slidable in a vertical slot 29 formed in the first end of each of the members such as the member 15 shown in FTGURE 4. The piston rod 27 may be moved forwardly and rearwardly generally parallel to'the'slot 19 by a simple hydraulic cylinder, a fragmentary portion of which is shown at 35) in FIGURE 4. The piston and cylinder shown are merely diagrammatic and any other equivalent actuating means may be used. V

In addition to locking of the major sections by the members 14, 15, 16, and 17, it is preferable to provide a means for locking the minor sections to the major sections at their hinge points after expansion into the ring shape has taken place. This locking may be achieved in any number of ways such as by means of bias springs in the hinges themselves tending to bias them to a given position. 7 l I In the operation of the structure as described, the various sections forming the ring are initially in the collapsed position illustrated in FIGURE 1. The manner in which the sections are collapsed will best be understood by referring to FIGURE 2 wherein it will be noted that first ends 11h and 11b of the minor sections 1111 and llb'are folded inwardly so that the minor sections 11h and lib will be sandwiched between the major section 11:; and each oi the major sections Mg and lie,

respectively. The other minor sections similarly fold inwardly.

The structure is maintained in its compact configuration by any suitable means such as hydraulic pressure in the cylinder 39 to hold the piston rod 27 shown in FIGURE 4 in its fully retracted position. When the missile is launched as, for example, from a tube, a suitable mechanism may automatically trigger a release means such as the cylinder 3t and piston rod 27 to permit the compact configuration to expand into its natural ring shape. Alternatively, actual hydraulic pressure may be applied to the cylinderfiii to urge the members, such as the member 15 shown in FIGURE 4, rearwardly, thereby expanding the structure'into the ringshape.

Once the structurehas attained a position such' as illustrated in FIGURE. 2, the resiliency of the major sections tending to straighten out will cause the struc ture to snap into the desired full ring shape illustrated in FIGURE 3. The inner ends of the members 14, 15, 16, and 17 will then be received within the bayonet slot type structures to lock the same in position. Alternatively, the piston rod 27 may be held extended by suitable pressure in the cylinder. 3t) so that the ring by.

whatever means is employed is held in its expanded condition.

While the structure has been described heretofore as being employed with non-recoverable type rockets or missiles, it should be understood that it may equally well may be employed to lock the ring in its final expanded '5 condition and the hydraulic piston and cylinder arrangement may be omitted. 7

Further, it should be understood that while the ring stabilizer has been described in conjunction with rockets and missiles, it may also be employed to advantage on 3 forces, such as a torpedo. feature enables a desired degree of fluid-dynamic stability to be realized without the disadvantage of a large structure being evident during the launching period.

7 From the foregoing description, it will thus be clear that various changes and modifications falling clearly within the scope and spirit of the invention will occur to those skilled in the art. The ring stabilizer is therefore not to be thought'of as limited to the one embodimentset forth merely for illustrative purposes.

What is claimed is: a

l. A ring stabilizer for a missile body comprising,.in combination: four major arcuate sections in the form of resilient bands; four minor sections alternately hinged between said major sections so that all of said sections are hinged together end to end to form a closed ring when in an expanded condition and whereby said minor sections may have first ends urged radially inwardly to fold between said major sections to provide a compact configuration; movable members interconnecting said major sections with the rear portion of said missile body;

and means for moving said movable members to expand said major sections radially outwardly with respect to a central longitudinal axis of said missile body.

2. A ring stabilizer according to claim 1, in which the rear portion of said missile body includes four sets of slots running generally. parallel to said longitudinal axis and circumferentially spaced at substantially ninety Q degrees, said movable members having first ends slidable 1 central under surface portion of said major sections, said slots being defined by parallel sidewalls having opposite undercut grooves therein, said first ends of said members grooves so that said first endsare confined to longitudinal back and forth movement in said slots; and means for locking said members in positions at which said major sections are expanded to define with the other sections,

5 said ring.

References Cited by the Examiner UNITED STATES PATENTS 41,689 2/64 Edge 102 -34.1 55 2,494,885 1/50 Lax et a1; 1024 3,047,259 7/62 Tatnall et a1. 244-1l3 X FOREIGN PATENTS 594,514 11/47 Great Britain.

SAMUEL FEINBERG, Primary Examiner.

ARTHUR M. HORTON, Examiner.

in said slots respectively and second ends pivoted to the i including laterally projecting means receivable in said.

any vehicle traveling through a medium subject to fluid The expanding and collapsing 1

Claims (1)

1. A RING STABILIZER FOR A MISSILE BODY COMPRISING, IN COMBINATION: FOUR MAJOR ARCUATE SECTIONS IN THE FORM OF RESILIENT BANDS; FOUR MINOR SECTIONS ALTERNATELY HINGED BETWEEN SAID MAJOR SECTIONS SO THAT ALL OF SAID SECTIONS ARE HINGED TOGETHER END TO END TO FORM A CLOSED RING WHEN IN AN EXPANDED CONDITION AND WHEREBY SAID MINOR SECTIONS MAY HAVE FIRST ENDS URGED RADIALLY INWARDLY TO FOLD BETWEEN SAID MAJOR SECTIONS TO PROVIDE A COMPACT CONFIGURATION; MOVABLE MEMBERS INTERCONNECTING SAID MAJOR SECTIONS WITH THE REAR PORTION OF SAID MISSILE BODY; AND MEANS FOR MOVING SAID MOVABLE MEMBERS TO EXPAND SAID MAJOR SECTIONS RADIALLY OUTWARDLY WITH RESPECT TO A CENTRAL LONGITUDINAL AXIS OF SAID MISSILE BODY.

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