US3883209A

US3883209A - Missile connector

Info

Publication number: US3883209A
Application number: US374823A
Authority: US
Inventors: Sverre Kongelbeck
Original assignee: US Department of Navy
Current assignee: US Department of Navy
Priority date: 1973-06-29
Filing date: 1973-06-29
Publication date: 1975-05-13
Anticipated expiration: 1992-05-13

Abstract

Invention is a connector for providing electrical connections to an aerial missile from a missile launcher of the box type. A novel feature resides in the provision of structure which allows limited shifting movement of the missile in the launcher without disturbing these electrical connections.

Description

United States Patent 1 May 13, 1975 Kongelbeck MISSILE CONNECTOR [75] Inventor: Sverre Kongelbeck, Silver Spring [73] Assignee: The United States of America as represented by the Secretary of the Navy, Washington, DC.

[22] Filed: June 29, 1973 [21] Appl. No.: 374,823

[52] US. Cl 339/125 R; 89/1.8l l; 339/28; 339/64 R; 339/119 C [51] Int. Cl. H011 13/60 {58] Field of Search 339/28, 34, 45, 46, 64, 339/119, 125; 89/1.811

[56] References Cited UNITED STATES PATENTS 2,943,138 6/1960 Reager 339/119 C '1 ,:---l 1 {l 11 I 'L-J: l l l' 3.094364 6/1963 Lingg 339/64 M 3,111,355 11/1963 Samburoff el 211....

3,245,319 4/1966 Kossan et a1 339/45 R X 3,488,623 1/1970 Stephenson et a1 339/64 M 3,518,613 6/1970 Alpert 339/45 M Primary Examiner-Richard E. Moore {57] ABSTRACT lnvention is a connector for providing electrical connections to an aerial missile from a missile launcher of the box type. A novel feature resides in the provision of structure which allows limited shifting movement of the missile in the launcher without disturbing these electrical connections.

8 Claims, 9 Drawing Figures ga-zamaasas 3.883.209

SHEET u 0F 5 0 FIG. 7

Pmmgg my saws 73 883 209 SHEET 5 [IF 5 MISSILE CONNECTOR BACKGROUND AND OBJECTS OF THE INVENTION The present invention relates generally to electrical connectors and more particularly to an improved connector for a missile launcher.

Surfaceto-surface missile launchers of the box type require umbilical electric connecting systems that are expendable because of the lack of space available for the use of retracting mechanisms such as are usually found on turret type launchers. It is also a requirement that electrical connections be maintained between the missiles and the launchers for long periods of time and often under adverse conditions, as when a ship mounting such launchers is operating under cruise conditions in heavy seas.

To solve the problem of making electrical connections to a missile in the launcher an adapter which has pins that engage in lead pot contacts in the permanent receptacle on the missile is provided. This adapter moves with the missile as it leaves the launcher and mates with the contactor plug employed in such a manner that withdrawal of said plug upon missile launch will not impose intolerable forces on the electrical connecting system. Thus, it is an object of the invention to provide a connector, for establishing positive electrical connections between a missile and a launcher prior to missile launch, that will detach from the missile as it leaves the launcher without causing damage to the aft end of the missile, to said launcher, or to the electrical connecting system.

Another object of the invention resides in the provision of a connector which will permit limited movement of the missile within the launcher during long periods of storage under adverse conditions without disturbing the electrical connections between the missile and said launcher.

A further object of the invention is to provide a connector that is of simple and rugged construction and one that will be effective in use.

Other objects of the invention not specifically mentioned hereinabove will become evident as the description proceeds.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. I is a perspective view showing the improved connector in operative position at the aft end of a missile in a box type launcher, only small portions of the launcher and missile being shown;

FIG. 2 is a top plan view, partly in section, showing the connector in operative position with the connector plug employed in engagement with the adapter that is mounted on the missile;

FIG. 3 is an end view ofthe device with parts omitted for the sake of clarity;

FIG. 4 is an enlarged detail section, partly in elevation, showing the missile receptacle, the adapter and the connector plug in connected relation;

FIG. 5 is a front elevation showing the face of the connector plug;

FIG. 6 is a front elevation of the adapter;

FIG. 7 is a sectional view of the adapter on the line 7-7 of FIG. 6;

FIG. 8 is an enlarged detail section showing corresponding end portions of the adapter and the receptacle, the adapter being secured to the receptacle and the receptacle being secured to a mounting plate at the aft end of the missile; and

FIG. 9 is a detail perspective showing the aft end of the missile with the receptacle in place.

DETAILED DESCRIPTION OF THE INVENTION Reference is now made to the drawings in more detail and first to FIGS. 1 and 2 thereof. In this view a portion of the aft end of a box type missile launcher is shown at 10, said launcher including a vertical wall I2. The aft end, or boattail, of a missile in the launcher is shown at 14.

Formed in the wall 12 at a point conveniently located with respect to the aft end of the missile 14 is an opening 16, and secured in the opening 16 is the mounting ring 18 of a two part cable coupling 20. As will be de scribed in more detail hereinafter, the cable coupling 20 forms a part of a flexible cable system 22 that extends between a control console (not shown) located remotely from the launcher and the connector plug of the present invention.

The structure of the improved connector comprises a bracket 24 which comprises a base 26 that is secured to the wall 12 in close spaced relation to the coupling 20 and an arm 28 which has its inner end portion se cured to the base 26 and has an enlarged circular outer end portion 30. As best seen in FIG. 2, the outer end portion 30 is formed with a recess 32 and a slot 34 that is located centrally of the recess, the slot having a curved wall at its inner end and having its outer end extending to and opening upon the outer rim of said outer end portion. A closure plate 36 having a curved inner wall is removably mounted in the slot by a bolt 38 which is passed through outwardly extending parallel lugs 40. As will be seen by referring to FIG. 3, the lugs 40 are formed integrally on the outer end portion 30 and straddle the plate 36. The curved inner wall of the closure plate and the curved wall of the slot 34 cooperate to form a circular opening in said outer end portion 30.

Attention is now directed to FIGS. 2 and 4 which best show the receptacle, plug and adapter structure of the present invention. The receptacle, which is prior art, is shown at 42 and is mounted in the aft end of the missile 14. The receptacle 42 includes recesses 44 which are filled with a relatively soft metal, such as lead, to constitute contacts 46. At its aft end the receptacle is provided with a cover membrane 48 which is of soft insulating material such as neoprene and which extends slightly beyond the aft end of the missile 14. The receptacle is secured to the missile by a pair of bolts 50, one of which is shown in FIG. 8. Each of the bolts 50 includes a shank SI which has a threaded forward end portion 52 that is passed through an opening in a base plate 53 on the missile aft end portion and is secured by a nut 54 and lock washer. The shank 51 of the bolt is counter-bored to provide a recess 55 and a threaded socket 56, and the aft end portion of the bolt has a flange 57 that engages the aft end wall of the receptacle.

The contacts 46 of the receptacle are engaged by the sharpened ends of spring-pressed pins 59 of an adapter 60, said pins being forced through the neoprene cover membrane 48. The adapter 60, which is also prior art. is secured to the receptacle by bolts 61, one of which is shown in FIG. 8, that pass through sleeves 62 and are screwed into the threaded sockets 56. As will be seen,

the sleeves 62 are carried on the adapter and fit into the recesses 55 in the bolts 50. As best seen in FIG. 7, the pins 59 have enlarged bifurcated aft end portions which define jaws 63 to receive prongs 64 on the plug 65 of the connector, to be described hereinafter. The aft end of the adapter is closed by a wall 66 of insulating mate rial, said wall being formed with openings 67 aligned with the jaws 63, and apertures 68 to receive orienting pins 69 on the plug 65.

The plug 65 includes a shell 70 which has a thickened forward portion that terminates in a radial flange 7] at its forward end. A shoulder is formed in the inner surface of the forward portion to define a seat 72 for a face plate 73. The face plate, which is of insulating material, carries the prongs 64 and the orienting pins 69 that engage in the apertures 68. A snap ring 75 is fitted into a groove in the front rim of the face plate and engages the plug wall to retain said plate in place in the shell. At its base, or aft, end the shell 70 is provided with a hollow neck 76 which carries a generally disk-shape head 77 and aft of said head a nipple 79 to receive the mating end of a flexible cable section 80 which forms a part of the cable system 22. As will be seen in FIGS. 2 and 4 in particular, the neck 76 is positioned for limited movement in the slot 34 in the bracket 24, entry of the neck into said slot being effected by removing the closure plate 36. The interior of the plug shell is normally filled with a potting compound 81 which surrounds conductors 82 that extend from the nipple 79 to the prongs 64. The plug 65 is urged into engagement with the adapter 60 by a coil spring 83 that surrounds said plug and is confined between the front face of the bracket 30 and the flange 7].

In brief summary, the present invention will function to maintain positive electrical connection between a launcher and a missile in the launcher, during storage and under other pre-launch conditions, by permitting limited movement of the missile with respect to the launcher. In addition, use of the invention will insure that a missile may be launced from the launcher without damage to the missile, the launcher or the electrical system. I claim:

1. In combination with a missile launcher and a missile positioned in the launcher for launching therefrom, said missile having a receptacle in its aft end and an adapter secured to the receptacle and having electrical contacts,

a missile connector for establishing electrical connections with the missile, said connector including a bracket secured to the launcher,

a plug mounted for limited movement in the outer end portion of the bracket and having contact prongs displaceably engageable with the adapter contacts,

means on the plug and bracket and urging the plug toward the adapter,

and a cable system connecting the plug to a source of electric power,

said means maintaining a positive connection be tween the plug and the adapter when the missile is in the launcher and in the event of relative movement of the missile and launcher prior to launching, said plug separating from the adapter upon movement of the missile from the launcher.

2. The missile connector recited in claim 1,

wherein the means urging the plug toward the adapter comprises a coil spring surrounding the plug and confined between said plug and the bracket.

3. The missile connector recited in claim 1,

wherein the cable system includes a two-part electrical coupling,

a mounting ring securing the coupling to the launcher,

and a flexible cable section connecting the coupling to the plug.

4. The missile connector recited in claim 1,

wherein the bracket includes an enlarged circular outer end portion having a recess with a relatively large slot therein,

and wherein the plug has a relatively small neck which is movable in the slot upon movement of the missile in the launcher prior to launching,

said relative movement of the plug and the bracket upon pre-launch movement of the missile in the launcher preventing damage to the missile or the launcher or the connector.

5. The missile connector recited in claim 4,

including additionally a head on the neck and posi tioned in the recess, said head limiting axial movement of the plug with respect to the bracket.

6. In a missile connector,

a bracket mounted on a missile launcher and having a relatively large slot at its outer end,

a plug for displaceable engagement with an adapter on a missile in the launcher and having a neck positioned for limited movement in the slot,

and a cable system electrically connected with the plug,

limited relative movement of the plug in the slot allowing limited movement of the missile in the launcher without damage to the missile, the launcher or the connector.

7. A missile connector as recited in claim 6,

including additionally means urging the plug toward the adapter,

and means for limiting axial movement of the plug toward the adapter.

8. A missile connector as recited in claim 7,

wherein said first mentioned means is a coil spring surrounding the plug between the plug and the bracket,

and said second mentioned means is a head on the plug.

Claims

1. In combination with a missile launcher and a missile positioned in the launcher for launching therefrom, said missile having a receptacle in its aft end and an adapter secured to the receptacle and having electrical contacts, a missile connector for establishing electrical connections with the missile, said connector including a bracket secured to the launcher, a plug mounted for limited movement in the outer end portion of the bracket and having contact prongs displaceably engageable with the adapter contacts, means on the plug and bracket and urging the plug toward the adapter, and a cable system connecting the plug to a source of electric power, said means maintaining a positive connection between the plug and the adapter when the missile is in the launcher and in the event of relative movement of the missile and launcher prior to launching, said plug separating from the adapter upon movement of the missile from the launcher.

2. The missile connector recited in claim 1, wherein the means urging the plug toward the adapter comprises a coil spring surrounding the plug and confined between said plug and the bracket.

3. The missile connector recited in claim 1, wherein the cable system includes a two-part electrical coupling, a mounting ring securing the coupling to the launcher, and a flexible cable section connecting the coupling to the plug.

4. The missile connector recited in claim 1, wherein the bracket includes an enlarged circular outer end portion having a recess with a relatively large slot therein, and wherein the plug has a relatively small neck which is movable in the slot upon movement of the missile in the launcher prior to launching, said relative movement of the plug and the bracket upon pre-launch movement of the missile in the launcher preventing damage to the missile or the launcher or the connector.

5. The missile connector recited in claim 4, including additionally a head on the neck and positioned in the recess, said head limiting axial movement of the plug with respect to the bracket.

6. In a missile connector, a bracket mounted on a missile launcher and having a relatively large slot at its outer end, a plug for displaceable engagement with an adapter on a missile in the launcher and having a neck positioned For limited movement in the slot, and a cable system electrically connected with the plug, limited relative movement of the plug in the slot allowing limited movement of the missile in the launcher without damage to the missile, the launcher or the connector.

7. A missile connector as recited in claim 6, including additionally means urging the plug toward the adapter, and means for limiting axial movement of the plug toward the adapter.

8. A missile connector as recited in claim 7, wherein said first mentioned means is a coil spring surrounding the plug between the plug and the bracket, and said second mentioned means is a head on the plug.