US3146670A - Missile launcher assembly - Google Patents

Description

Sept. 1, 1964 Filed Nov. 27, 1962 E. T. SUYDAM 3,146,670

MISSILE LAUNCHER ASSEMBLY 2 Sheets-Sheet 1 Edmond T. Suydam,

INVENTOR.

BY ,q-KJW Sept. 1, 1964 Filed Nov. 27, 1962 E. T. SUYDAM MISSILE LAUNCHER ASSEMBLY I x l lmhh F IG. 4

2 Sheets-Sheet 2 Edmond T. Suydom,

INVENTOR.

United States Patent 3,146,67 MISSILE LAUNCHER ASSEMBLY Edmond T. Suydam, Burlington, Vt., assignor, by mesne assignments, to the United States of America as represented by the Secretary of the Army Filed Nov. 27, 1962, Ser. No. 240,464 7 Claims. (Cl. 891.7)

The present invention pertains to launchers for rockets and more particularly relates to a jettisonable launcher assembly fitting for engaging the guide rail of the launcher.

In the use of prior launch fittings, the fitting was not jettisonable and therefor added additional weight to the missile cutting down the range for the same. Further the aerodynamic drag of the launch fittingnot only decreased the range but it caused an unbalanced torque on the missile which affected the trajectory of the missile. In some cases an additional launch fitting was placed in the opposite side of the missile to balance the aerodynamic drag. This practice further added to the weight and drag affecting the missile flight.

An object of the present invention is to provide a missile launcher assembly which employs a jettisonable launch fitting to reduce the missile weight during flight.

Another object of the invention is to provide a missile launcher assembly wherein the launch fitting is jettisonable from the missile during the launching to reduce aerodynamic drag and unbalanced torque on the missile during flight.

One of the important features of the invention is to provide a launcher assembly which employs a launch fitting to accurately guide the missile on the launcher rails and which is subsequently positively and mechanically separated from the missile at the terminal end of the launcher rail.

These and other objects and advantages of the present invention will become apparent from the following detailed description taken with the accompanying drawings, wherein:

FIGURE 1 is a fragmentary side elevation view partially broken away illustrating the missile launcher assembly of the present invention.

FIGURE 2 is a fragmentary bottom view of the launch er along line 22 of FIGURE 1;

FIGURE 3 is a sectional view taken on line 33 of FIGURE 1; and

FIGURE 4 is a perspective view of the launch fitting.

Referring now to the drawings and particularly to FIGURE 1 thereof, indicates a missile on a launcher 12 adjacent the end of its travel on the launcher. Launcher rail 14 is broken away to illustrate a jettisonable fitting 16 which forms an important part of the launcher assembly of the present invention. Fitting 16 is illustrated in phantom at two further positions 16a and 1612 representing the positions of the fitting at later periods during the launching process, and illustrating the manner of separation of the fitting from the missile.

Fitting 16 is in the form of a pin or shank portion 18 (FIGURE 4) having a rectangular head 20, the sides of which define guide faces. A J-slot 22 is formed in pin 18 at the distal end thereof. Head 20 is provided with a cam surface 24 which is inclined with respect to the axis of the pin for purposes explained hereinbelow.

A spacer ring 25 is mounted on pin 18, for purposes described hereinbelow, by a retaining pin 26 which is fixed in a radial bore in ring 25 and projects inwardly therefrom into a vertical slot 28 formed in pin 18. Thus ring 25 is capable of limited movement longitudinally of pin 18 but is precluded from removal from the pin.

The skin 30 of missile 10 (FIGURE 3) is provided with internal bosses 32 at points adapted to be adjacent rails 14 of the launcher. Each boss 32 is provided with "ice a blind bore 34 which is radial of the missile and leads tot the exterior thereof. A shear pin 36 extends radially through the wall of boss 32 and projects into blind bore 34 for engagement with J-slot 22 on fitting 16. When the missile is to be launched, launch fitting 16 is inserted into blind bore 34 so that shear pin 36 engages J-slot 22. A degree turn of the fitting then seats shear pin 36 in the bottom of J-slot 22 and locks the fitting in place.

The guide rail 14 is generally U-shaped in cross section, as best seen in FIGURE 3, and comprises a bottom 40, two sides 42 and 44, and two inwardly projecting top plates 46 and 48 at the upper edges of side plates 42 and 44, respectively. When the rectangular head 26 of launch fitting 16 is inserted within side rail 14 it cannot turn and thus the fitting cannot disengage itself from the missile.

The previously mentioned ring 25 is interposed be tween missile 10 and the upper surfaces of top plates 46 and 48 to prevent damage to the missile skin by rubbing on the rail surface, and to provide clearance between the missile and the rail to prevent tilting of the missile when the center of gravity thereof passes the end of the launcher rail and before the rear end of the missile leaves the rail. The clearance also permits movement of the missile due to crosswind without causing tilting of the missile.

As best seen in FIGURES 1 and 2, bottom plate 40 of guide rail 14 is cut away at 50 adjacent the terminal end of the guide rail. Two fitting retracting plates 52 and 54 v are fastened to the inner surfaces of side plates 42 and 44, respectively, of guide rail 14 by capscrews 55. The lower edges of retraction plates 52 and 54 are inclined downwardly and forwardly from guide rail 14 at substantially the same angle as cam surface 24 on head 20 of launch fitting 16.

When the missile approaches the terminal ends of rails 14, the cam surfaces 24 on head 20 of launch fitting 18 contact the under side of retraction plates 52 and 54. Further forward movement of the missile causes the launch fitting to be withdrawn from the missile, as illustrated in phantom at 16a (FIGURE 1) shearing pin 36. When the launch fitting reaches the ends of plates 52 and 54 it drops to the ground, as illustrated at 16b, and can then be reused to launch another missile.

While a preferred embodiment of the invention has been described herein it should be noted that various changes may be made therein without departing from the spirit of the invention as defined in the appended claims.

I claim:

1. In a missile launcher assembly the combination which comprises, a missile, a U-shaped guide rail, a launch fitting releasably mounted in a lateral bore in said missile, said fitting having a rectangular head for engagement within said guide rail, a pair of retraction plates fixed to the side sections of said U-shaped guide rail adjacent the forward end thereof, said retraction plates projecting forwardly and downwardly from said guide rail, and inclined cam surfaces formed on the head of said launch fitting for engagement with said retraction plates, whereby as the missile moves forward on said guide rail the retraction plates will engage said launch fitting and withdraw said fitting from said missile.

2. A missile launcher assembly as set forth in claim 1 wherein a shear pin is mounted in said missile and projects into said lateral bore, and a J-slot is formed in said fitting for engagement with said shear pin.

3. A missile launcher assembly as set forth in claim 1, wherein a spacer ring is mounted on said fitting between said missile and said launcher rail.

4. A missile launcher assembly as set forth in claim 3 wherein said spacer ring is mounted for limited movement with respect to said fitting by a pin radially affixed to said ring and projecting inwardly into a longitudinal groove formed in said fitting.

5. For use in a missile launcher assembly the combination which comprises, a missile having a lateral bore formed therein, a shear pin projecting into said bore, a launch fitting having a shank portion and a head, said shank portion being received in said bore, a J-slot formed in said shank portion of said fitting, said shear pin being received in said J-slot so as to latch said shank portion in said bore, and said head having cam surface means and flat guide faces for coaction with means on a guide rail to adapt said fitting for removal from said bore by sufiicient force being applied to said cam surface means so as to cause shearing of said shear pin.

6. For use in a missile launcher assembly, the combination which comprises, a missile having a lateral bore formed therein, a shear pin projecting into said bore, a launch fitting having a shank portion and a rectangular head portion, said shank portion being received in said References Cited in the file of this patent UNITED STATES PATENTS 2,397,572 Weaver Apr. 2, 1946 2,771,811 Lauritsen Nov. 27, 1956 2,826,960 Schiavi Mar. 18, 1958 2,962,934 Seidner Dec. 6, 1960 3,017,835 Holtz Jan. 23, 1962 3,038,382 Noyes et al June 12, 1962

Claims (1)

1. IN A MISSILE LAUNCHER ASSEMBLY THE COMBINATION WHICH COMPRISES, A MISSILE, A U-SHAPED GUIDE RAIL, A LAUNCH FITTING RELEASABLY MOUNTED IN A LATERAL BORE IN SAID MISSILE, SAID FITTING HAVING A RECTANGULAR HEAD FOR ENGAGEMENT WITHIN SAID GUIDE RAIL, A PAIR OF RETRACTION PLATES FIXED TO THE SIDE SECTIONS OF SAID U-SHAPED GUIDE RAIL ADJACENT THE FORWARD END THEREOF, SAID RETRACTION PLATES PROJECTING FORWARDLY AND DOWNWARDLY FROM SAID GUIDE RAIL, AND INCLINED CAM SURFACES FORMED ON THE HEAD OF SAID LAUNCH FITTING FOR ENGAGEMENT WITH SAID RETRACTION PLATES, WHEREBY AS THE MISSILE MOVES FORWARD ON SAID GUIDE RAIL THE RETRACTION PLATES WILL ENGAGE SAID LAUNCH FITTING AND WITHDRAW SAID FITTING FROM SAID MISSILE.

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