US3387537A - Torpedo suspension band - Google Patents

Description

June 11, 1968 G. CHAKOIAN ET AL 3,387,537

TORPEDO SUSPENSION BAND 2 Sheets-Sheet l Fild Feb. 17, 1967 INVENTORS. GEORGE CHAKOIAN RUSSELL T. CROWELL NATHAN M. SOUTHWICK BY V. C. MULLER ROY MILLER ATTORNEYS.

June 11, 1968 CHAKOIAN ET AL 3,387,537

TORPEDO SUSPENSION BAND Filed Feb. 17, 1967 2 Sheets-Sheet 2 INVENTORS.

GEORGE CHAKOIAN RUSSELL T. CROWELL NATHAN M. SOUTHWICK BY V. C. MULLER ROY MILLER ATTORNEYS.

United States Patent Office Patented June 11, 1968 Ma..- a.

ABSTRACT OF THE DISCLOSURE A latching mechanism including a sensitive trigger, maintains band locked on a missile and releases it from the missile upon application of a relatively small force applied to a trigger actuating wedge, which is separated from the band by a parachute or a static line.

This invention relates to breakaway bands for suspending and launching missiles, such as torpedoes, from aircraft and more particularly to improvements in bands of the type disclosed in the Patents to Rhodes 3,077,818, Barrowman 2,826,119 and Niedling 2,786,392.

Of the patents just referred to, the patent to Barrowman is the most closely related to this invention in that a pivoted suspension lug (21) looks one end of the band against separation, the lug being restrained against pivotal movement by a releasable locking plate or key (22) which is removed by a lanyard (37) attached to the aircraft, thus effecting release at some distance below the aircraft and preventing the separated band from striking rearward portions of the aircraft. Among the disadvantages of the Barrowman band are the requirement that the pull on the lanyard must be substantially vertical to remove the locking plate or key from its retaining slots and the tension in the lanyard must be suflicient to overcome the high locking force exerted between the pivoted lug and the locking plate.

One of the objects of the present invention is to provide a suspension band which may be released from a missile by a lanyard, the pull of which may be in various directions relative to the direction of fall of the missile.

Another object is to provide a release mechanism which, with a relative small tension in the lanyard, may trigger the release against considerably higher locking forces.

Another object is to provide a suspension band of simplified construction with a minimum number of parts.

Still further objects, advantages, and salient features will become more apparent from the description to follow, the appended claims, and the accompanying drawing, in which:

FIG. 1 is a perspective of the invention;

FIG. 2 is a section and side elevation taken on line 2-2, FIG 3;

FIG. 3 is a top plan as viewed in the direction of arrow 3, FIG. 2; and

FIG. 4 is a view, like FIG. 2, showing the parts in released position.

Referring first to FIG. 1, the invention comprises a suspension device which encircles a missile (not shown) which is suspended by a moveable hook of a bomb rack (not shown) which engages lug 12, this being one of a pair of identical devices disposed at spaced points along the length of the missile, as is conventional in the prior art referred to.

Referring to FIGS. 2 and 3, device 10 comprises a platelike saddle member 14 to which is secured a pair of bands 16 having looped ends 18 which engage ends of a cross pin 20 which is secured to a lug 22 on the saddle member by a bolt 24 which passes through the center of the pin and threadedly engages the lug. The other ends of the bands have like looped ends 26 which engage ends of a cross pin 28.

A pair of parallel upstanding flanges 30 are integrally formed on the saddle member, providing a slot 32 between the flanges. The lower end of lug 12 is disposed within the slot and pivotally connected to the flanges by a pin 34. As best shown in FIG. 2, each flange is provided with an inclined ramp 36, the two ramps and a curved portion 38 on the lug forming a V block which is engaged by pin 28. When the lug is restrained against pivotal movement in a clockwise direction, as viewed in FIG. 2, it will be apparent that the tension in the bands forces pin 28 into the V block in the direction of arrow 40, preventing release of the bands from the missile which they encircle. Referring now to FIG. 4, the parts are shown in a position in which lug 12 has been permitted to rotate in a clockwise direction. As will be apparent, the V block has now opened, permitting pin 28 to slide over one side of the lug, thus releasing ends of the bands from the saddle member assembly.

The lug locking means comprises a blocking member 42, a trigger 44 and a wedge 46 for actuating the trigger. Member 42 is disposed within slot 32, one end being pivoted to flanges 30 by a pin 48, its other end engaging one side of lug 12 as best shown in FIG. 2. Trigger 44 is provided with a pair of oppositely extending abutment pins 50 each of which engage an inclined ramp 52 on a flange 30. Its left end, as shown in FIGS. 3 and 4, is provided with a half round notch 54 which engages a cross pin 56 carried by member 42. Wedge 46 is provided with intersecting surfaces 58 (FIG. 4), which abut like intersecting surfaces 60, 61 at the left end of the flanges, and wedging edges 62 formed as a V. Trigger 44 and blocking member 42 form links of a toggle mechanism which, due to the choice of the angle on ramps 52, tend to force pins 50 down the ramp to an overcenter self locking position by the tension in bands 16. If desired, a safety wire (not shown) may be secured to the parts to prevent premature lifting of tail 64 of trigger 44.

In operation, a band unit is wrapped around the missile and pin is disposed in the position shown in FIG. 2 with the lug also in such position. The lug blocking memher is then swung to the position shown, the wedge lain into the position shown, and the trigger 44 inserted so that its notch 54 engages pin 56 and its pins engage ramps 52. The band is then tensioned as desired by bolt 24.

Shortly after launching a missile, when it is clear of its carrying aircraft, wedge 46 is removed from beneath the tail of the trigger. This may be eifected by a static line or lanyard having one end fixed to the aircraft and its other end secured to one end of the wedge. In another mode of removing the wedge, one end of the lanyard is aflixed to a parachute which deploys after dropping the missile, opening of the parachute providing a tension on a lanyard to remove the wedge. In the first mentioned mode, the wedge serves as a lever, pivoting about one end and raising tail 64. In the second mode, the wedge is pulled in the direction of its longitudinal axis and one of surfaces 62 engages tail 64, also lifting it. As the tail lifts, pins 50 slide upwardly along ramps 52 until they move out of engagement with the ramps. At this point, the tension in the bands moves the parts to unlocked position and trigger 44 flys free from engagement with the blocking member which is forced by the lug to the position shown in FIG. 4. Since the V block is now opened, pin 28 is free to pass over the lug and release the entire band assembly from the missile.

FIG. 4 illustrates a refinement to the wedge wherein it is provided with a pair of intersecting camming surfaces 66. Surfaces 61 on the ends of the flanges are milled to the same angle. As the wedge is moved trans-verse to the flanges, one of surfaces 66 engages a surface 61 and cams 3 one end of the wedge outwardly as it is being removed from beneath the tail.

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 claims the invention may be practiced otherwise than as specifically described.

What is claimed is:

1. A break-away suspension device for an aircraft launched elongated missile, such as a torpedo, comprising;

(1) a saddle member adapted to be disposed at the top of the missile having a pair of spaced upwardly extending flanges extending transverse to the missile axis, forming an upwardly open channel therebetween,

(2) a suspension lug having a lower portion disposed between the flanges and pivoted thereto for movement in a plane perpendicular to the missile axis, said lug having an aperture therein for removably receiving a bomb rack hook,

(3) axially aligned inclined surfaces on said flanges forming one face of a V block,

(4) a surface at one side of said lug forming the other face of the V block,

(5) a longitudinally extending circular pin abutting the faces of the V block having a pair of spaced tensioned bands afiixed thereto, one to each end thereof, and encircling the missile, their other ends being secured to the saddle member, and

(6) means for preventing pivotal movement of said lug to thereby maintain a predetermined angle between said faces of the V block which prevents movement of the pin over the top of the lug, said means cornprising;

(a) a blocking member having one end disposed between the flanges and pivoted thereto, its other 4 end engaging said lug at the side opposite the V block,

(b) a trigger disposed above said blocking member having one end pivotally engaging said other end of the blocking member and having intermediate portions slideably engaging inclined ramps on said flanges, the construction being such that said blocking member and trigger form a toggle mechanism adapted to tighten toward a locked position upon application of increasing force applied between the lug and blocking member, the other end of said trigger forming a tail adapted to be lifted, for moving said intermediate portions off of the inclined ramps, and

(c) a removable Wedge disposed beneath said tail adapted to wedgingly engage the tail and portions of the saddle member for lifting the tail and moving said intermediate portions ofi of the inclined ramp to thereby permit the blocking member to rotate, and the lug to rotate, to permit said pin to move over the top of the lug to thereby release the device from the missile as a unit.

2. Apparatus in accordance with claim 1 wherein said Wedge member comprises a pair of wedging edges, forming a V, their intersection being disposed beneath the tail, the construction being such that longitudinal movement of the wedge member in either direction causes one or the other of the edges to engage the tail and lift same.

References Cited UNITED STATES PATENTS 2,786,392 3/ 1957 Niedling 89-15 2,826,119 3/ 1958 Barrowman 89-l.5 3,077,818 2/1963 Rhodes 89-15 SAMUEL W. ENGLE, Primary Examiner.

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