US3181908A - Single-point launching device - Google Patents

Single-point launching device Download PDF

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Publication number
US3181908A
US3181908A US141410A US14141061A US3181908A US 3181908 A US3181908 A US 3181908A US 141410 A US141410 A US 141410A US 14141061 A US14141061 A US 14141061A US 3181908 A US3181908 A US 3181908A
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Prior art keywords
store
launcher
bearing
missile
launching
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Expired - Lifetime
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US141410A
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John R Clark
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Northrop Grumman Corp
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Northrop Grumman Corp
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Priority to US141410A priority Critical patent/US3181908A/en
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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D1/00Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
    • B64D1/02Dropping, ejecting, or releasing articles
    • B64D1/04Dropping, ejecting, or releasing articles the articles being explosive, e.g. bombs
    • B64D1/06Bomb releasing; Bombs doors

Description

May 4, 1965 Filed Sept. 28, 1961 J. R. CLARK 3,181,908
SINGLE-POINT LAUNCHING DEVICE 2 Sheets-Sheet 1 May 4, 1965 J. R. CLARK SINGLE-POINT LAUNCHING DEVICE 2 Sheets-Sheet 2 Filed Sept. 28. 1961 United States Patent O 3,181,908 SINGLE-POINT LAUNCHING DEVICE .lohn R. Clark, Rolling Hills Estates, Calif., assignor to Northrop Corporation, Beverly Hills, Calif., a corporation of California Filed Sept. 28, 1961, Ser. No. 141,410 4 Claims. (Cl. 294-83) This invention relates to a launching device for a releasable store, and more particularly, to a launching device for an airborne external store, having a single point Y of attachment to the store, this attachment being releasable to drop or forcibly eject the store.
Conventional launchers for airborne bodies such as external tanks, bombs, rockets, cargo packs and the like use two attaching points, in the form of hooks -or releasable shackles for example. Since it is desired to dropthe store straight away from the carrying vehicle, both release means must operate simultaneously to prevent malfunction. However, this is a troublesome `factor in actual practice, and the stores are still subject to becoming cocked at an angle d-ue to sticking of a release element or adverse aerodynamic forces, thus causing damage, improper release, or no release at all.
A single-point attachment would eliminate the problem of obtaining simultaneous release at two or more points. However, additional bracing means must be employed, and it has been found that relative adjust-ment o-f the bracing means and the single attachment device when installing the store causes binding and misalignment between the store and the attachment device. Therefore, no successful singleapoint launching device is known.
Accordingly, it is an object of the present invention to provide -a single-point launching device which will not be subject to factors ordinarily producing internal binding, misalignment stresses and the like, and which will insure a clean, positive, reliable release.
Further `objects ot this invention are to provide a single-point launching device which is more economical and simpler than conventional launchers, and which permits faster loading of the store to be carried.
Briefly, my invention comprises a combination of fore and aft sway braces pressing down on a `droppable store, and a single central attaching point where releasable holding means fits into a self-aligning spherical bearing retainer assembly in the store.
In the accompanying drawings,
FIGURE l is a perspective view of an airborne mis- -sile attached to a launcher by means of the present invention, the View being cut away to show the attachment location.
FIGURE 2 is an enlarged detail View of a swaybolt as used in FIGURE 1.
FIGURE 3 is a fragmentary cross sectional view of the missile and launcher mechanism viewed as indicated by the line 3-3 in FIGURE l, showing the launcher device in attached position.
FIGURE 4 is a similar cross sectional view, showing the device in released position.
Referring first to FIGURE l for a detailed description of specific apparatus, a missile 1, for example, is suspended from a launcher 2 adapted to be attached at its upper portion to a pylon or to the lower side of an airplane Wing, for example. The launcher carries four sway brace assemblies 4 each consisting of a swaybolt 5 and a lock nut 6, as further shown in FIGURE 2. The swaybolts are screwed into the lower side of athreaded fitting S and 9, respectively, on the launcher 2, and are each provided with a special fiat bearing head and a recessed wrench socket 11 in the upper end of the bolt. The swaybolts 5 merely press against the outer skin 12 of the missile 1.
SSLQS Patented May 4, 1965 ICC Near the center of the launcher 2, and substantially at the center of gravity of the missile 1, a launching mechanism 14 installed in the launcher 2 cooperates with a socket assembly 15 in the missile 1, to releasably secure the missile to the bottom of the launcher. Electrical or other plug connection (not shown) may be made through the launcher 2 to the missile 1, for example, but the mis- `sile is held only at the one central location.
FIGURES 3 and 4 show the construction and operation of the attachment and release features. In the launcher mechanism 14, which does not form a part of this invention per se, a sear member 16 has a central shank 17 ywith an enlarged circular head 19 thereon. A series of collet-like spring fingers 20 bear inwardly on the sear 16. The outer sides of the fingers 20 have a protruding fiange surface 21 to take the supporting load for the missile 1 as will be described later.
An auxiliary cylinder 22 surrounds the spring fingers 20, and a hollow piston 24 surrounds the cylinder. In this particular launching mechanism, a retaining nut 25 screws into the end of an outer fitting 26, and a second cylinder 27 fits inside an upper rim 29 of the nut 25.
kIn the missile l, the socket assembly 15 comprises a generally cylindrical socket opening 36 with a spherical recess 31 in its upper end. A spherical bearing 32 has a spherical outer surface which fits the recess l31. A large central opening 34 in bearing 32 carries an inwardly extending lip 35 at the upper end to engage the spring fingers 20 previously described. A snap ring 36 positions, the bearing 32 in its recess 31 while permitting ample movement of the bearing relative to the recess.
A spring-loaded .plug 37 is slidably mounted in the lower portion of socket opening 36 and is urged upwardly by la relatively light compression spring 39. An outer shoulder 40 on plug 37 is designed to engage the bearing lip 35 in position to place the plug 37 in a iiush position when the missile is separate-d from the launcher, thus protecting the socket assembly against entrance of foreign matter when not attached to the launcher.
The operation of the present invention will now be described. In the attached position shown in FIGURE 3, the sear 16 is retracted relative to the spring fingers 2li so that the latter are forced outwardly under the bearing lip 35. The piston 24 is also in its retracted position in the launching mechanism 14. Swaybolts 5 are tightened against the missile 1 (or other store) to a predetermined torque to hold the missile rigidly secured. During this operation, it will be noted that the spherical bearing 32 will move ,in any direction of pitch and roll of the missile, within its limits of operation, to produce only tension loads on the spring ngers 20. No binding on the bearing, fingers, or socket parts and no bending of the sear can exist which would otherwise occur due to rocking or twisting of the missile as the swaybolt forces are built up. The missile connection is now complete, ready for transport and/ or release.
When the missile or other store is to be released, the launching mechanism is operated, which first extends the scar 16 to the position shown in FIGURE 4. The spring fingers 20 automatically press inwardly to follow the scar shank 17, thus disconnecting the missile. Beveled surfaces on the bearing lip 35 and spring finger flanges 21 insure separation of these parts. The missile 1 is now free to drop away, and may be actually ejected in this instance by sequential action of piston 24, which is forced downwardly upon the surrounding top area of the socket assembly, and goes through an extension stroke away lfrom the launcher 2, to forcibly push the missile away. Since the details of the release mechanism control are not important to the present invention, they have not been included herein. All that is necessary to this invention is a suitable releasable attachment means to the spherical bearing 32, such as actuation of the sear 16 in the example described.
Thus it is seen that a simple foolproof mechanical single-point attachment system has been provided. The store to be carried and subsequently released is easily and quickly snapped over the sear to` attach it, and a reliable free release is insured by the universally movable lspherical bearing retaining means which eliminates friction and sticking normally present when more than one attachment point is involved.
While in order to comply with the statute, the invention has been described in language more or less specic as to structural features, it is to be understood that the invention is not limited to the specific features shown, but that the means and construction herein disclosed comprise the preferred form of putting the invention into effect, and the invention is therefore claimed in any of its forms or modications within the legitimate and valid scope of the appended claims.
What is claimed is:
1. A single-point launching device comprising an airborne store to be launched, a launcher to carry said store, a socket assembly substantially at the center of gravity in said store containing a self-aligning bearing universally movable in said socket assembly, holding means in said bearing whereby said store is suspended by said bearing, releasable tension means in said launcher fitting into said holding means, and sway brace means on said launcher bearing on the outer surface of said store to steady it in installed position, said self-aligning bearing allowing suicient rocking and pitching of said store while said sway brace means are being tightened to prevent misaiignment stresses between said store and said launcher.
2. A single-point launching device comprising a store to be launched, a launcher to carry said store, a socket assembly in said store containing a self-aligning bearing, releasable means in said launcher fitting into said bearing, and sway brace means on said launcher adapted tobear on said store and steady it in installed position.
3. In a launching system including a launcher and a store to be releasably carried thereby, the combination of a socket assembly in the store containing a spherical bearing universally movable in said socket assembly, releasable means in the launcher fitting into said bearing and releasably connected therein for suspended support of the store, and sway brace means on the launcher adapted to bear on the outer surface of the store.
4. In a single-point launching device, a socket assembly containing a self-aligning bearing, and holding means in said bearing adapted -to engage suspension means external of said socket assembly for carrying said assembly thereby, said socket assembly containing a space beneath said bearing, said bearing having a large opening therein with an inwardly extending lip at the upper end of said opening, and including a plug slidably mounted in said socket space, said plug having a closed top face, `an outer shoulder of said plug shaped to engage said bearing lip to determine a position of said top face substantially ush with the outer surface of said socket assembly, and elastic means in said socket assembly normally urging said plug toward said tush position.
Reerenees Cited by the Examiner UNITED STATES PATENTS 2,043,111 6/ 36 Meyer 287-87 2,726,576 12/55 Musser.
2,852,299 9/58 Johnson.
2,941,835 6/60 Musser 294-83.l 2,955,866 10/60 Firman 294-83 2,996,781 8/ 61 Oliveau 24-230.l 3,009,730 11/61 Gantschnigg 294-83 3,102,536 9/63 Rose 287-124 X ROBERT B. REEVES, Acting Primary Examiner.
JAMES S. SHANK, ANDRES H. NIELSEN, ERNEST A. FALLER, J R., SAMUEL P. COLEMAN, WILLIAM B. LA BORDE, Examiners.

Claims (1)

1. A SINGLE-POINT LAUNCHING DEVICE COMPRISING AN AIRBORNE STORE TO BE LAUNCHED, A LAUNCHER TO CARRY SAID STORE, A SOCKET ASSEMBLY SUBSTANTIALLY AT THE CENTER OF GRAVITY IN SAID STORE CONTAINING A SELF-ALIGNING BEARING UNIVERASALLY MOVABLE IN SAID SOCKET ASSEMBLY, HOLDING MEANS IN SAID BEARING WHEREBY SAID STORE IS SUSPENDED BY SAID BEARING, RELEASABLE TENSION MEANS IN SAID LAUNCHER FITTING INTO SAID HOLDING MEANS, AND SWAY BRACE MEANS ON SAID LAUNCHER BEARING ON THE OUTER SURFACE OF SAID STORE TO STEADY IT IN INSTALLED POSITION, SAID SELF-ALIGNING BEARING ALLOWING SUFFICIENT ROCKING AND PITCHING OF SAID STORE WHILE SAID SWAY BRACE MEANS ARE BEING TIGHTENED TO PREVENT MISALIGNMENT STRESSES BETWEEN SAID STORE AND SAID LAUNCHER.
US141410A 1961-09-28 1961-09-28 Single-point launching device Expired - Lifetime US3181908A (en)

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Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3595126A (en) * 1969-08-14 1971-07-27 Avco Corp Fuze initiator
US4132147A (en) * 1977-08-29 1979-01-02 Sps Technologies, Inc. Store retention and release mechanism
US4257639A (en) * 1979-12-17 1981-03-24 Rockwell International Corporation Ejector device for stores
WO1982002527A1 (en) * 1981-01-26 1982-08-05 Rockwell International Corp An ejector device for stores
US4412475A (en) * 1980-05-27 1983-11-01 Northrop Corporation Aircraft rocket and missile launcher
US4842218A (en) * 1980-08-29 1989-06-27 The United States Of America As Represented By The Secretary Of The Navy Pivotal mono wing cruise missile with wing deployment and fastener mechanism
US4891994A (en) * 1989-02-13 1990-01-09 Plessey Incorporated Linear electromechanical actuator
US5406876A (en) * 1994-06-21 1995-04-18 Northrop Grumman Corporation Store retention and release system
US5961075A (en) * 1997-10-30 1999-10-05 Raytheon Company Universal aircraft-carriage suspension lug system
US6035759A (en) * 1998-05-07 2000-03-14 Mcdonnell Douglas Corporation Single hook ejector rack for miniature munitions
US20060162535A1 (en) * 2004-12-16 2006-07-27 Rafael-Armament Development Authority Ltd. Detachable hanger
US10858102B2 (en) 2018-11-26 2020-12-08 The Boeing Company Container retention and release apparatus for use with aircraft

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2043111A (en) * 1931-05-14 1936-06-02 Continental Motors Corp Engine
US2726576A (en) * 1952-11-26 1955-12-13 Musser C Walton Device for releasing an article from a space traversing object
US2852299A (en) * 1956-04-19 1958-09-16 Francis M Johnson Wing tank rack explosive bolt assembly
US2941835A (en) * 1957-06-26 1960-06-21 Musser C Walton Parachute release connection
US2955866A (en) * 1956-01-16 1960-10-11 Vickers Armstrongs Aircraft Releasable attachments
US2996781A (en) * 1957-07-29 1961-08-22 Aerotec Ind Inc Disconnects
US3009730A (en) * 1958-08-13 1961-11-21 Gen Dynamics Corp Ejector for external carried stores
US3102536A (en) * 1960-12-07 1963-09-03 Robert M Rose Hip prosthesis

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2043111A (en) * 1931-05-14 1936-06-02 Continental Motors Corp Engine
US2726576A (en) * 1952-11-26 1955-12-13 Musser C Walton Device for releasing an article from a space traversing object
US2955866A (en) * 1956-01-16 1960-10-11 Vickers Armstrongs Aircraft Releasable attachments
US2852299A (en) * 1956-04-19 1958-09-16 Francis M Johnson Wing tank rack explosive bolt assembly
US2941835A (en) * 1957-06-26 1960-06-21 Musser C Walton Parachute release connection
US2996781A (en) * 1957-07-29 1961-08-22 Aerotec Ind Inc Disconnects
US3009730A (en) * 1958-08-13 1961-11-21 Gen Dynamics Corp Ejector for external carried stores
US3102536A (en) * 1960-12-07 1963-09-03 Robert M Rose Hip prosthesis

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3595126A (en) * 1969-08-14 1971-07-27 Avco Corp Fuze initiator
US4132147A (en) * 1977-08-29 1979-01-02 Sps Technologies, Inc. Store retention and release mechanism
US4257639A (en) * 1979-12-17 1981-03-24 Rockwell International Corporation Ejector device for stores
US4412475A (en) * 1980-05-27 1983-11-01 Northrop Corporation Aircraft rocket and missile launcher
US4842218A (en) * 1980-08-29 1989-06-27 The United States Of America As Represented By The Secretary Of The Navy Pivotal mono wing cruise missile with wing deployment and fastener mechanism
WO1982002527A1 (en) * 1981-01-26 1982-08-05 Rockwell International Corp An ejector device for stores
US4891994A (en) * 1989-02-13 1990-01-09 Plessey Incorporated Linear electromechanical actuator
US5406876A (en) * 1994-06-21 1995-04-18 Northrop Grumman Corporation Store retention and release system
US5961075A (en) * 1997-10-30 1999-10-05 Raytheon Company Universal aircraft-carriage suspension lug system
US6035759A (en) * 1998-05-07 2000-03-14 Mcdonnell Douglas Corporation Single hook ejector rack for miniature munitions
US20060162535A1 (en) * 2004-12-16 2006-07-27 Rafael-Armament Development Authority Ltd. Detachable hanger
US7178442B2 (en) * 2004-12-16 2007-02-20 Rafael-Armament Development Authority, Ltd Detachable hanger
US10858102B2 (en) 2018-11-26 2020-12-08 The Boeing Company Container retention and release apparatus for use with aircraft

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