US3276367A - Air delivery apparatus and method - Google Patents

Air delivery apparatus and method Download PDF

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US3276367A
US3276367A US385009A US38500964A US3276367A US 3276367 A US3276367 A US 3276367A US 385009 A US385009 A US 385009A US 38500964 A US38500964 A US 38500964A US 3276367 A US3276367 A US 3276367A
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missiles
frame
bomblets
cluster
delivery system
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William R Edwards
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
    • F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles
    • F42B12/60—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected radially
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
    • B64D1/02—Dropping, ejecting, or releasing articles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
    • F42B10/58—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding of rotochute type

Definitions

  • the present invention generally relates to a delivery system utilized to disperse articles from an aircraft. More particularly, the invention relates to a new delivery system wherein a cluster of missiles or bombs is ejected from an aircraft and rotated to propagate centrifugal force which propels the individual bombs or missiles from the cluster for the desired dispersal.
  • the delivery systems utilizing the technique of clustering bombs, or missiles have various modes of operation for dispersing the bombs, or missiles, once the cluster is clear of the delivering aircraft.
  • many known delivery systems utilizing the clustering technique secure the bombs or missiles together in a cluster by various devices characterized by an active mode of operation.
  • Other systems utilize casings to surround the cluster of bombs or missiles to hold the bombs or missiles in the cluster until the time of dispersion.
  • the known delivery systems also utilize various devices for dispersing or separating the bombs or missiles once the cluster is clear of the delivery aircraft.
  • a prominent manner of separating a cluster of bombs is by an explosive charge which propels the bombs from the cluster into the desired dispersal pattern.
  • An explosive charge has also been utilized to burst the casing surrounding the missiles or bombs there by to allow the bombs or missiles to disperse.
  • the general purpose of this invention to provide an article delivery system to deliver articles from aircraft which delivery system embraces all of the advantages of the prior art delivery systems and additionally possesses the advantage of being simple, reliable, and compact.
  • the present invention contemplates a unique arrangement of components to provide a cluster delivery system which is compact, utilizes no moving parts to eject the bomblets, bombs, or missiles, from the cluster, and which is economical to manufacture and, therefore, expandable.
  • Another object of the present invention is to provide a bomblet delivery system which is compact and utilizes a frangible casing to cover the cluster of bomblets and which casing does not interfere with the accomplishment of dispersal in any manner adversely affecting the pattern of the bomblets, upon being fragmentized.
  • a further object of the preset invention is to provide a delivery system which disperses the bomblets from a cluster by the utilization of centrifugal force imparted to the bomblets by the rotation of the entire cluster of the delivery system.
  • Yet another object of the present invention is to provide a delivery system utilizing a plurality of bomblets normally secured together in a clustered relationship and whereby dispersal occurs without the necessity for use of mechanisms or other operating delivery devices.
  • FIG. 1 is generally a diagrammatic pictorial view of two delivery systems of the present invention, one being ejected from an aircraft, and the other as dispersal of the bomblets is taking place;
  • FIG. 2 is generally a diagrammatic view of one section of the delivery package with the bomblets shown in place;
  • FIG. 3 is an enlarged end view of the device taken along line 33 of FIG. 2;
  • FIG. 4 is a longitudinal cross-sectional view of the delivery system taken along line 4-4 of FIG. 3;
  • FIG. 5 is an enlarged cross-sectional view of the delivery system taken along line 5-5 of FIG. 4;
  • FIG. 6 is a pictorial view of a retaining component upon which the aft end of each bomblet rests;
  • FIG. 7 is a cross-sectional view of the delivery system taken along line 77 of FIG. 3;
  • FIG. 8 is a cross-sectional view of the taken along line 88 of FIG. 7;
  • FIG. 9 is a pictorial view of the separaotr clip which is utilized to separate the bomblets.
  • FIG. 1 An illustration of the operation of the present invention.
  • a delivery system of the present invention is depicted at 11 as it is being ejected from an aircraft 12.
  • the delivery system 11 of FIG. 1 utilizes aerodynamic control surfaces 13 which are retractable and which are illustrated as being in movement towards their extended position.
  • Shown generally at 15 is the delivery system with the aerodynamic airfoils 14 fully extended to cause the custer to rotate at a sufficient speed to create the centrifugal force necessary for the bomblets 16 to separate from the cluster and break through the frangible casing 17.
  • the aerodynamic control surfaces, or wings, 14 are shown in their retracted position as extending along and in close proximity to the frangible casing 17.
  • the wings 14 are secured to the main structure of the delivery system by hinges 21, which allow the wings 14 to pivot to the extended position as illustrated generally at 22.
  • the Wings 14 are pivoted to the extended position 22 by reaction with air current as the delivery system is falling through the air thereby to impart rotation to the entire assembly.
  • the aerodynamic configurations of the wings 14 will determine the rotational speed of the delivery system, therefore, the amount of centrifugal force imparted to the bomblets 16 can be controlled.
  • the frangible casing 17 is shown enclosing the bomblets 16in FIG. 2 and is made of a plastic material which will fragmentize upon being subjected to a loading created by the application of centrifugal force to the bomblets.
  • the bombs, or bomblets, or missiles, 16 are shown as clustered in phantom form in FIG. 2, The casing 17 abuts against the end plate 24 to completely encase the individual bomblets 16 of the cluster.
  • FIG. 3 shows the end plate 24 secured to the main I-beam 25 by bolts 26 and securing plates 27, which details are more clearly shown in FIG. 7. Also, shown in phantom form in FIG. 3 is perforated or open weave reinforcing structure 28 within the frangible casing 17. The reinforcing structure may be of mesh, nylon, light plaster burlap, or cotton knitting.
  • FIG. 6 is a pictorial view of the bomblet retainer member 29 which is shown in association with the I-beam 25 in FIG. 4.
  • the retaining members 29 serve to support the aft end of the bomblets 16 to retain the aft end of the bomblets 16 from outward movement away from the I-beam 25.
  • FIG. more clearly shows the relative disposition of the retaining member 29 with the I-beam 25.
  • the bomblets 16 have a magnetic head 31 which is a permanent magnet creating a magnetic field.
  • the I-beam or main structural member 25 supports keeper buttons 32, which are more clearly shown in FIG. 7.
  • the I-beam 25 is made of a very light material such as aluminum and the keepers 32 are of a heavier magnetic metal, as for example iron.
  • FIG. 4 shows one section containing four bomblets, however, there could be as many sections as desired along the I-beam depending upon its length.
  • FIG. 7 shows the pOrtion of the I-beam which is adjacent the magnetic heads 31 of the bomblets 16.
  • the keepers 32 react with the magnetic field established by the magnets 31 so that the magnets holdthe bomblet against the keeper and consequently in juxtaposition to the I-beam 25.
  • the I-beam 25 separates a pair of bomblets 16 from a pair on the other side of the I-beam, and in addition, as shown in FIG. 7, spacers 33 are utilized to separate the two bomblets on the same side of the I-beam 25.
  • FIG. 9 is a pictorial view of the spacer element 33, which spacer element is more clearly shown in FIG. 7 and FIG. 8.
  • the entire capsule is ejected from an aircraft as illustrated in FIG. 1.
  • the frangible casing 17 is necessary to surround the bomblets to protect them during storage and to ease handling.
  • the casing 17 is very fragile and offers little resistance to the bomblets 16 when the bomblets separate from the I-beam 25 due to centrifugal force which is developed as a result of the rotation of the entire assembly by the wings 14.
  • the bomblets are disposed four in a section along the I-beam 25 and are held in close proximity to the I-beam 25 by the retaining element 29, which holds the aft end of the bomblets against the I-beam, and the magnetic heads 31, which react with the keepers 32 to hold the bomblets to the I-beam.
  • the casing 17 is of a light weight material and does not interfere with the bomblets as they are dispersed from the I-beam; that is to say, the
  • fragmentized casing 17 is not heavy enough to affect the trajectory of any one of the individual bomblets 16.
  • the present invention is of considerable significance in that it teaches a delivery system utilizing a very light weight structural member about which are disposed individual missiles, bombs, or bomblets retained in a cluster by means of a magnetic field thereby requiring only passive mechanisms or components.
  • the delivery package utilizes a frangible casing which is extremely light in weight and which does not interfere with dispersal pattern of the bomblets but yet streamlines the cluster.
  • the present invention provides a unique bomblet delivery system to be used for dispersing a cluster of bomblets that have been dropped from an airplane which system is light, compact, economical to manufacture, efiicient, and highly reliable.
  • An aircraft launched bomb assembly adapted to contain a plurality of individual missiles comprising:
  • said means being normally retracted to a position in juxtaposition to said frame and being extendable to a position of protrusion from said frame

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)

Description

Oct. 4, 1966 w. R. EDWARDS AIR DELIVERY APPARATUS AND METHOD 4 Sheets-Sheet 1 Filed July 24, 1964 INVENTOR William A. Edwards Oct 1966 w. R. EDWARDS AIR DELIVERY APPARATUS AND METHOD 4 Sheets-Sheet 2 Filed July 24, 1964 I ll T Oct. 4, 1966 w. R. EDWARDS AIR DELIVERY APPARATUS AND METHOD 4 Sheets-Sheet 5 Filed July 24, 1964 Oct. 4, 1966 w. R. EDWARDS AIR DELIVERY APPARATUS AND METHOD 4 Sheets-Sheet 4 Filed July 24, 1964 United States Patent Ofiiice 3,276,367 Patented Oct. 4, 1966 3,276,367 AIR DELIVERY APPARATUS AND METHOD William R. Edwards, (Ialifornia, MIL, assignor to the United States of America as represented by the Secretary of the Navy Filed July 24, 1964, Ser. No. 385,009 4 Claims. (Cl. 1027.2)
The invention described herein may be manufactured and used by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor.
The present invention generally relates to a delivery system utilized to disperse articles from an aircraft. More particularly, the invention relates to a new delivery system wherein a cluster of missiles or bombs is ejected from an aircraft and rotated to propagate centrifugal force which propels the individual bombs or missiles from the cluster for the desired dispersal.
It is an old and well known technique in the delivery of articles from an aircraft to cluster the articles for efficient packaging and ejection from the aircraft. The delivery systems utilizing the technique of clustering bombs, or missiles, have various modes of operation for dispersing the bombs, or missiles, once the cluster is clear of the delivering aircraft. For example, many known delivery systems utilizing the clustering technique secure the bombs or missiles together in a cluster by various devices characterized by an active mode of operation. Other systems utilize casings to surround the cluster of bombs or missiles to hold the bombs or missiles in the cluster until the time of dispersion. In addition to the differing clustering techniques, the known delivery systems also utilize various devices for dispersing or separating the bombs or missiles once the cluster is clear of the delivery aircraft. A prominent manner of separating a cluster of bombs is by an explosive charge which propels the bombs from the cluster into the desired dispersal pattern. An explosive charge has also been utilized to burst the casing surrounding the missiles or bombs there by to allow the bombs or missiles to disperse.
In known delivery systems it is necessary to have some operation of apparatus; that is to say, there must be a mechanism to detonate an explosive charge, if used, or an operating mechanism to mechanically disperse the individual missiles or bombs, as may be the case. There is need for an article delivery system which clusters a group of bombs or missiles and disperses the bombs or missiles at a predetermined point along the flight path of the cluster after it has been ejected from an aircraft; which cluster system operates independently of the aircraft, or any signal from the aircraft, in dispersion of the bombs or missiles, and has no operating components or devices to separate the bombs or missiles from the cluster.
It is, therefore, the general purpose of this invention to provide an article delivery system to deliver articles from aircraft which delivery system embraces all of the advantages of the prior art delivery systems and additionally possesses the advantage of being simple, reliable, and compact. To attain the desired results, the present invention contemplates a unique arrangement of components to provide a cluster delivery system which is compact, utilizes no moving parts to eject the bomblets, bombs, or missiles, from the cluster, and which is economical to manufacture and, therefore, expandable.
Accordingly, it is an object of the present invention to provide a bomblet delivery system utilizing a cluster arrangement of bomblets which are dispersed Without the utilization of any operating components.
Another object of the present invention is to provide a bomblet delivery system which is compact and utilizes a frangible casing to cover the cluster of bomblets and which casing does not interfere with the accomplishment of dispersal in any manner adversely affecting the pattern of the bomblets, upon being fragmentized.
A further object of the preset invention is to provide a delivery system which disperses the bomblets from a cluster by the utilization of centrifugal force imparted to the bomblets by the rotation of the entire cluster of the delivery system.
Yet another object of the present invention is to provide a delivery system utilizing a plurality of bomblets normally secured together in a clustered relationship and whereby dispersal occurs without the necessity for use of mechanisms or other operating delivery devices.
Other objects and many of the attendant advantages of this invention will be readily appreciated as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein:
FIG. 1 is generally a diagrammatic pictorial view of two delivery systems of the present invention, one being ejected from an aircraft, and the other as dispersal of the bomblets is taking place;
FIG. 2 is generally a diagrammatic view of one section of the delivery package with the bomblets shown in place;
FIG. 3 is an enlarged end view of the device taken along line 33 of FIG. 2;
FIG. 4 is a longitudinal cross-sectional view of the delivery system taken along line 4-4 of FIG. 3;
FIG. 5 is an enlarged cross-sectional view of the delivery system taken along line 5-5 of FIG. 4;
FIG. 6 is a pictorial view of a retaining component upon which the aft end of each bomblet rests;
FIG. 7 is a cross-sectional view of the delivery system taken along line 77 of FIG. 3;
FIG. 8 is a cross-sectional view of the taken along line 88 of FIG. 7; and
FIG. 9 is a pictorial view of the separaotr clip which is utilized to separate the bomblets.
Referring now to the drawings, wherein like reference characters designate like or corresponding parts throughout the several views, there is shown pictorially in FIG. 1 an illustration of the operation of the present invention. A delivery system of the present invention is depicted at 11 as it is being ejected from an aircraft 12. The delivery system 11 of FIG. 1 utilizes aerodynamic control surfaces 13 which are retractable and which are illustrated as being in movement towards their extended position. Shown generally at 15 is the delivery system with the aerodynamic airfoils 14 fully extended to cause the custer to rotate at a sufficient speed to create the centrifugal force necessary for the bomblets 16 to separate from the cluster and break through the frangible casing 17.
In FIG. 2, the aerodynamic control surfaces, or wings, 14 are shown in their retracted position as extending along and in close proximity to the frangible casing 17. The wings 14 are secured to the main structure of the delivery system by hinges 21, which allow the wings 14 to pivot to the extended position as illustrated generally at 22. The Wings 14 are pivoted to the extended position 22 by reaction with air current as the delivery system is falling through the air thereby to impart rotation to the entire assembly. The aerodynamic configurations of the wings 14 will determine the rotational speed of the delivery system, therefore, the amount of centrifugal force imparted to the bomblets 16 can be controlled.
The frangible casing 17 is shown enclosing the bomblets 16in FIG. 2 and is made of a plastic material which will fragmentize upon being subjected to a loading created by the application of centrifugal force to the bomblets.
delivery system J3 Casing made of polyurethane are very satisfactory for use in this delivery system. The bombs, or bomblets, or missiles, 16 are shown as clustered in phantom form in FIG. 2, The casing 17 abuts against the end plate 24 to completely encase the individual bomblets 16 of the cluster.
FIG. 3 shows the end plate 24 secured to the main I-beam 25 by bolts 26 and securing plates 27, which details are more clearly shown in FIG. 7. Also, shown in phantom form in FIG. 3 is perforated or open weave reinforcing structure 28 within the frangible casing 17. The reinforcing structure may be of mesh, nylon, light plaster burlap, or cotton knitting. I The relative disposition of the bomblets 16 on either side of the main structural I-beam 25 is shown in FIG. 4. FIG. 6 is a pictorial view of the bomblet retainer member 29 which is shown in association with the I-beam 25 in FIG. 4. The retaining members 29 serve to support the aft end of the bomblets 16 to retain the aft end of the bomblets 16 from outward movement away from the I-beam 25. FIG. more clearly shows the relative disposition of the retaining member 29 with the I-beam 25. The bomblets 16 have a magnetic head 31 which is a permanent magnet creating a magnetic field. The I-beam or main structural member 25 supports keeper buttons 32, which are more clearly shown in FIG. 7. In the ideal configuration, the I-beam 25 is made of a very light material such as aluminum and the keepers 32 are of a heavier magnetic metal, as for example iron. FIG. 4 shows one section containing four bomblets, however, there could be as many sections as desired along the I-beam depending upon its length. When the I-beam is long, more than one set of wings may be used or the wings may be disposed along the I-beam rather than at the end. The enlarged view, FIG. 7, shows the pOrtion of the I-beam which is adjacent the magnetic heads 31 of the bomblets 16. The keepers 32 react with the magnetic field established by the magnets 31 so that the magnets holdthe bomblet against the keeper and consequently in juxtaposition to the I-beam 25. As shown in FIG. 4, the I-beam 25 separates a pair of bomblets 16 from a pair on the other side of the I-beam, and in addition, as shown in FIG. 7, spacers 33 are utilized to separate the two bomblets on the same side of the I-beam 25. The keepers 32 are retained in place by retaining plates 34 on either side of the I-beam 25, as is best shown in FIG. 8. The plates 34 are attached to the I-beam 25 in any convenient manner, as for example, by the rivets 35 shown in FIG. 7. FIG. 9 is a pictorial view of the spacer element 33, which spacer element is more clearly shown in FIG. 7 and FIG. 8.
In the operation of the device, the entire capsule is ejected from an aircraft as illustrated in FIG. 1. The frangible casing 17 is necessary to surround the bomblets to protect them during storage and to ease handling. The casing 17 is very fragile and offers little resistance to the bomblets 16 when the bomblets separate from the I-beam 25 due to centrifugal force which is developed as a result of the rotation of the entire assembly by the wings 14. The bomblets are disposed four in a section along the I-beam 25 and are held in close proximity to the I-beam 25 by the retaining element 29, which holds the aft end of the bomblets against the I-beam, and the magnetic heads 31, which react with the keepers 32 to hold the bomblets to the I-beam. Nothing restrains the magnet end of the bomblets 16 to the I-beam 25 except the coaction of the magnetic field with the keepers 32. Upon rotation of the I-beam 25 by the aerodynamic control surfaces 14, sufficient centrifugal force is generated to overcome the magnetic field, the magnet ends 31 of the bomblets 16 separate from the I-beam, the bomblets 16 break or shatter the frangible casing 17, and fly off individual trajectories. The casing 17 is of a light weight material and does not interfere with the bomblets as they are dispersed from the I-beam; that is to say, the
fragmentized casing 17 is not heavy enough to affect the trajectory of any one of the individual bomblets 16.
It is, therefore, submitted that the present invention is of considerable significance in that it teaches a delivery system utilizing a very light weight structural member about which are disposed individual missiles, bombs, or bomblets retained in a cluster by means of a magnetic field thereby requiring only passive mechanisms or components. The delivery package utilizes a frangible casing which is extremely light in weight and which does not interfere with dispersal pattern of the bomblets but yet streamlines the cluster.
Also, it is within the confines of the present inventive concept to use various components of the combination of elements with each other; for example, instead of magnetic retaining means for the bomblets, they can be retained in a conventional manner with a mechanical clip device from which they could move when subjected to a sufficient mount of centrifugal force thereby to produce a delivery system utilizing the same overall configuration and fragile casing as illustrated but Without the magnetic retaining means. Also, the frangible casing 17 could be eliminated in certain instances.
As is apparent from the foregoing description, the present invention provides a unique bomblet delivery system to be used for dispersing a cluster of bomblets that have been dropped from an airplane which system is light, compact, economical to manufacture, efiicient, and highly reliable.
The invention has been described in an illustrative manner and it is to be understood that the terminology which has been used herein is intended to be in the nature of words of description rather than of limitation.
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 aircraft launched bomb assembly adapted to contain a plurality of individual missiles comprising:
an I beam frame made of non-magnetic material,
means affixed to said frame for effecting rotation thereof subsequent to launching from an aircraft,
said means being normally retracted to a position in juxtaposition to said frame and being extendable to a position of protrusion from said frame,
a plurality of missiles nestled in tandem groups along the longitudinal axis of said frame,
individual magnet means attached to each of said missiles,
magnetic means secured to said frame for coacting with said magnet means for holding said missiles secured to said frame until a predetermined force is applied to each of said missiles to separate each of said missiles from said frame, and
frangible means surrounding said frame and said missiles.
2. The bomb assembly of claim 1 wherein said frangible casing comprises a plastic material.
3. The bomb assembly of claim 2 wherein said plastic material is polyurethane.
4. The bomb assembly of claim 1 wherein said nonmagnetic material is aluminum.
References Cited hy the Examiner UNITED STATES PATENTS 2,044,819 6/ 1936 Taylor 102-4 2,264,906 12/1941 Roby 102-5 2,455,620 12/1948 Sreb 102-79 2,476,973 7/ 194-9 Gillon 102-72 3,016,011 1/196'2 \Brown 102-72 3,088,404 5/ 1963 Brown et a1. 102-7.2
BENJAMIN A. BO'RCHELT, Primary Examiner.
SAMUEL W. ENGLE, Examiner.

Claims (1)

1. AN AIRCRAFT LAUNCHED BOMB ASSEMBLY ADAPTED TO CONTAIN A PLURALITY OF INDIVIDUAL MISSILES COMPRISING: AN I-BEAM FRAME MADE OF NON-MAGNETIC MATERIAL, MEANS AFFIXED TO SAID FRAME FOR EFFECTING ROTATION THEREOF SUBSEQUENT TO LAUNCHING FROM AN AIRCRAFT, SAID MEANS BEING NORMALLY RETRACTED TO A POSITION IN JUXTAPOSITION TO SAID FRAME AND BEING EXTENDABLE TO A POSITION OF PROTRUSION FROM SAID FRAME, A PLURALITY OF MISSILES NESTLED IN TANDEM GROUPS ALONG THE LONGITUDINAL AXIS OF SAID FRAME, INDIVIDUAL MAGNET MEANS ATTACHED TO EACH OF SAID MISSILES, MAGNETIC MEANS SECURED TO SAID FRAME FOR COACTING WITH SAID MAGNET MEANS FOR HOLDING SAID MISSILES SECURED TO SAID FRAME UNTIL A PREDETERMINED FORCE IS APPLIED TO EACH OF SAID MISSILES TO SEPARATE EACH OF SAID MISSILES FROM SAID FRAME, AND FRANGIBLE MEANS SURROUNDING SAID FRAME AND SAID MISSILES.
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Cited By (12)

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US3584581A (en) * 1969-08-06 1971-06-15 Us Army Spin launch rectangular-type canister
US3712229A (en) * 1970-07-17 1973-01-23 Oerlikon Buehrle Ag Missile having a casing and containing secondary projectiles
US3903804A (en) * 1965-09-27 1975-09-09 Us Navy Rocket-propelled cluster weapon
US3943854A (en) * 1973-04-12 1976-03-16 Dynamit Nobel Aktiengesellschaft Ejection head with active elements for rockets
US4072107A (en) * 1967-06-07 1978-02-07 The United States Of America As Represented By The Secretary Of The Army Missile control means
US4143836A (en) * 1975-08-30 1979-03-13 Messerschmitt-Bolkow-Blohm Gmbh Method and device for spread bombing
US4488489A (en) * 1980-12-23 1984-12-18 Dynamit Nobel Aktiengesellschaft Ordnance system having a warhead with secondary elements as a payload
EP0176046A1 (en) * 1984-09-22 1986-04-02 Rheinmetall GmbH Warhead
US5363737A (en) * 1992-03-27 1994-11-15 British Aerospace Public Limited Company Air-vehicle launcher apparatus
US5398615A (en) * 1992-06-30 1995-03-21 Bofors Ab Method and an apparatus for separating subcombat units
US20070266884A1 (en) * 2006-05-16 2007-11-22 Textron Systems Corporation Controlled dispense system for deployment of components into desired pattern and orientation
US11725918B2 (en) * 2017-11-28 2023-08-15 Bae Systems Bofors Ab Device and method for obtaining a horizontal dispersion pattern

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US2044819A (en) * 1933-10-27 1936-06-23 James G Taylor Projectile
US2264906A (en) * 1940-08-04 1941-12-02 David H Roby Aerial bomb
US2455620A (en) * 1944-09-12 1948-12-07 Jules H Sreb Centrifugal switch
US2476973A (en) * 1945-03-13 1949-07-26 Paul N Gillon Incendiary bomb
US3016011A (en) * 1956-07-11 1962-01-09 Brown Fred Cluster opening method
US3088404A (en) * 1956-11-15 1963-05-07 Brown Fred Interlocking screw threads

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US2044819A (en) * 1933-10-27 1936-06-23 James G Taylor Projectile
US2264906A (en) * 1940-08-04 1941-12-02 David H Roby Aerial bomb
US2455620A (en) * 1944-09-12 1948-12-07 Jules H Sreb Centrifugal switch
US2476973A (en) * 1945-03-13 1949-07-26 Paul N Gillon Incendiary bomb
US3016011A (en) * 1956-07-11 1962-01-09 Brown Fred Cluster opening method
US3088404A (en) * 1956-11-15 1963-05-07 Brown Fred Interlocking screw threads

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3903804A (en) * 1965-09-27 1975-09-09 Us Navy Rocket-propelled cluster weapon
US4072107A (en) * 1967-06-07 1978-02-07 The United States Of America As Represented By The Secretary Of The Army Missile control means
US3584581A (en) * 1969-08-06 1971-06-15 Us Army Spin launch rectangular-type canister
US3712229A (en) * 1970-07-17 1973-01-23 Oerlikon Buehrle Ag Missile having a casing and containing secondary projectiles
US3943854A (en) * 1973-04-12 1976-03-16 Dynamit Nobel Aktiengesellschaft Ejection head with active elements for rockets
US4143836A (en) * 1975-08-30 1979-03-13 Messerschmitt-Bolkow-Blohm Gmbh Method and device for spread bombing
US4488489A (en) * 1980-12-23 1984-12-18 Dynamit Nobel Aktiengesellschaft Ordnance system having a warhead with secondary elements as a payload
EP0176046A1 (en) * 1984-09-22 1986-04-02 Rheinmetall GmbH Warhead
US5363737A (en) * 1992-03-27 1994-11-15 British Aerospace Public Limited Company Air-vehicle launcher apparatus
US5398615A (en) * 1992-06-30 1995-03-21 Bofors Ab Method and an apparatus for separating subcombat units
US20070266884A1 (en) * 2006-05-16 2007-11-22 Textron Systems Corporation Controlled dispense system for deployment of components into desired pattern and orientation
WO2008033170A2 (en) 2006-05-16 2008-03-20 Textron Systems Corporation Controlled dispense system for deployment of components into desired pattern and orientation
WO2008033170A3 (en) * 2006-05-16 2008-05-02 Textron Systems Corp Controlled dispense system for deployment of components into desired pattern and orientation
US7845283B2 (en) 2006-05-16 2010-12-07 Textron Systems Corporation Controlled dispense system for deployment of components into desired pattern and orientation
US11725918B2 (en) * 2017-11-28 2023-08-15 Bae Systems Bofors Ab Device and method for obtaining a horizontal dispersion pattern

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