US3166980A

US3166980A - Arming tool mechanism

Info

Publication number: US3166980A
Application number: US305012A
Authority: US
Inventors: Robert M Harris; Roger H Wiethoff
Original assignee: Individual
Current assignee: Individual
Priority date: 1963-08-27
Filing date: 1963-08-27
Publication date: 1965-01-26
Anticipated expiration: 1982-01-26

Description

R. M. HARRIS ETAL ARMING TOOL MECHANISM Jan. 26, 1965 2 Sheets-Sheet 1 Filed Aug. 27, 1963 Fir/455F55 INVENTORS ROBERT M. HARRIS ROGER H. W/E'THOFF' ATTORNEY Jan. 26, 1965 R. M. HARRIS ETAL ARMING TOOL MECHANISM 2 Sheets-Sheet 2 Filed Aug. 27, 1963 FIG. 3

United States Patent 3,166,980 ARMING T001. MECHANISM Robert M. Harris, Minneapolis, and Roger H. Wiethoif,

Wayzata, Minn., assignors, by mesne assignments, to

the United States of America as represented by the Secretary of the Navy Filed Aug. 27, 1963, Ser. No. 305,012 2 Claims. (Cl. 89-17) This invention relates to a missile launching system of the type having a magazine for storing missiles in a vertical position and for transferring these missiles to a launcher arm supported directly above the magazine, and, more particularly, to the arming mechanism which arms the missile after it is on the launching arm.

Launching a missile requires many operations. Even the transfer of the missile from the magazine or storage compartment to the launching arm requires many operations and takes a definite period of time for each operation. Whenever possible, these operations are carried out contemporaneously.

The arming tool is a cylindrical piece that is retained by, and rotates within, a bore sleeve located in the retractable rail. The tool is located within the retractable rail between the two igniters for the missle. A cut-out within the tool engages a splined actuating link of the operating mechanism.

As a missile is loaded onto the guide arm, the missile lever arm moves between the two projections on the face of the arming tool. arming tool is mechanically rotated counterclockwise. In turn, a projection contacts the missile lever arm, forcing it to rotate and likewise arm the missile. The arming tool is then free to move forward as the missile is fired.

After the missile is fired, the arming tool mechanically recocks through spring action of the arming tool operating mechanism. Or, if an armed missile is to be returned to the magazine, the arming tool is first mechanically rotated clockwise. A projection contacts the missile lever arm to rotate and disarm the missile. The arming tool lever is then free to move aftward as the missile is returned to the magazine.

It is one object of the present invention to provide mechanism located within the retractable rail of the launcher arm which will, while the missile is on the rail, engage the arming mechanism of the missile and actuate such mechanism to arm the missile.

It is another object of the present invention to provide an arming tool mechanism which will mechanically open and close circuitry between the missile firing contacts and the rocket ignition squibs for the missile.

It is a further object of the present invention to provide an arming tool mechanism, located within the retractable rail, which will rotate a missile rotor shaft counterclockwise approximately 80 from the safe position to mechanically close the circuit between the firing contacts and the squibs for subsequent ignition of the rocket motor squibs.

his a still further object of the present invention to provide an arming tool mechanism, located within the retractable rail which will rotate a missile rotor shaft approximately 80 from the armed position to a safe position.

It is a still further object of the present invention to With the missile in position, the

3,1663% Patented Jan. 26, 1965 ice provide a cylindrical rotating piece of mechanism within the retractable rail which will contact the. missile arming lever and rotate said lever through such an are as to arm the missile.

Other objects, advantages and novel features of the invention will become apparent from the following detailed description of the invention when considered in conjunction with the accompanying drawings wherein:

FIG. 1 is a dimetric view of the retractable rail shown in two parts, one a continuance of the other, with such parts of the retractable rail omitted where not essential to show the function of the arming mechanism;

FIG. 2 is a dimetric view of the rotation part of the arming mechanism which contacts the arming lever of the missile;

FIG. 3 is a partial end view of the missile showing the shoe and the arming lever;

FIGS. 4, 5 and 6 show the engagement of the arming mechanism with the arming lever in different positions.

Referring to the drawings wherein like reference numerals denote like parts throughout the several views, the retractable rail 11 receives the missile on the guide rail 12 from the rail of the magazine and passes it to the guide arm of the launcher.

Located centrally on a portion of the retractable rail is a rod 13 formed at one end with an eye 14 and at the other end with a similar eye 15. The rod 13 is moved vertically through an actuating mechanism (not shown) connected to eye 14. This vertical movement compresses the coil spring 16 and moves the bent lever 17 connected to eye 15. The bent lever is in turn connected to the crank arm 18 of the hub 19 of a rotative element 21. A radial arm 22 of the rotation element is pinned to a link 23 which transfers the rotative movement of element 21 to vertical movement of rod 24. This rod 24 is mounted in the retractable rail but out of vertical alignment with rod 13. Rod 24 terminates in a yoke 25 which actuates a link 26 to rotate a splined shaft 27 through a limited are. This limited rotative movement is transferred to a splined hub 28 which projects into the area of the rail. The hub is formed on its face with

projections

29 and 31 which receive and rotate a pin 32 or" the crank 33. The crank 33 is carried by a shaft 34 which arms the missile through mechanism within the missile (not shown).

The rod 13 is extended by pressure in a cylinder in the guide arm whose piston rod connects to rod 13. When the pressure is relieved, rod 13 is retracted by the coil spring. Alternatively, if a missile having been armed is to be returned to the magazine, the arming tool actuating mechanism may move the rod 13 downwardly thereby rotating the arming tool to return the missile lever arm to its unarmed position.

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. An arming mechanism for a missile launching system having a rail for receiving a missile from a magazine, comprising:

a rod carried by the rail for movement lengthwise of the rail;

a second rod carried by the rail and out of vertical projections carried by said hub adapted to receive and 10 engage a crank mounted arming pin on the missile and rotate the pin to armed position. 2. An arming mechanism according to claim 1 Wherein the projections carried by the hub are spaced at the circumference ofv the hub a distance greater than the 15 diameter of the pin to aid in receiving the pin, said projections converging toward the center of the hub to contact the pin at opposite points.

References Cited by the Examiner UNITED STATES PATENTS 3,049,976' 8/62 Hereth et al. 89 1.7 3,101,026 8/63 Jacobson et a1. 89-1.7 3,110,219 11/63 Wermager et a1. 891.7 X 3,113,486 12/63 Kongelbeck 891.7

BENJAMIN A. BORCHELT, Primary Examiner. SAMUEL w. ENGLE, Examiner.

Claims

1. AN ARMING MECHANISM FOR A MISSILE LAUNCHING SYSTEM HAVING A RAIL FOR RECEIVING A MISSILE FROM A MAGAZINE, COMPRISING: A ROD CARRIED BY THE RAIL FOR MOVEMENT LENGTHWISE OF THE RAIL; A SECOND ROD CARRIED BY THE RAIL AND OUT OF VERTICAL ALIGNMENT WITH SAID FIRST MENTIONED ROD, SAID SECOND ROD BEING MOVABLE LENGTHWISE OF THE RAIL BY MOVEMENT OF SAID FIRST ROD; A LINK MOUNTED ON A SPLINED SHAFT SUPPORTED BY THE RAIL, SAID LINK BEING ENGAGED BY SAID SECOND ROD AND MOVED THROUGH A LIMITED ARC BY LENGTHWISE MOTION OF SAID SECOND ROD; A HUB CARRIED ON THE SPLINED SHAFT SUPPORTING SAID LINK, AND ROTATABLE WITH SAID LINK; PROJECTIONS CARRIED BY SAID HUB ADAPTED TO RECEIVE AND ENGAGE A CRANK MOUNTED ARMING PIN ON THE MISSILE AND ROTATE THE PIN TO ARMED POSITION.