US3712229A - Missile having a casing and containing secondary projectiles - Google Patents

Missile having a casing and containing secondary projectiles Download PDF

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Publication number
US3712229A
US3712229A US00161574A US3712229DA US3712229A US 3712229 A US3712229 A US 3712229A US 00161574 A US00161574 A US 00161574A US 3712229D A US3712229D A US 3712229DA US 3712229 A US3712229 A US 3712229A
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United States
Prior art keywords
segments
missile
projectiles
secondary projectiles
extension
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Expired - Lifetime
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US00161574A
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English (en)
Inventor
J Schock
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rheinmetall Air Defence AG
Original Assignee
Werkzeugmaschinenfabrik Oerlikon Buhrle AG
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Classifications

    • 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

Definitions

  • ABSTRACT A missile of the type having a casing composed on individual segments containing movable secondary projectiles, the segments in a locked position being mu tually parallel, and means for allowing a head wind striking the missile in flight to swing the segments radially outwards.
  • Each segment contains a plurality of secondary projectiles.
  • the segments are hingeably deflectable through an angle of approximately 170.
  • the secondary projectiles are slidably ejected from the segments by the centrifugal forces generated by the outward swing of the segments.
  • This arrangement does without an ejecting charge for each secondary projectile and therefore saves space.
  • the invention relates to a missile of the type having a casing composed of individual hinged segments containing movable secondary projectiles, said segments in a locked position being mutually parallel, and means for allowing a head wind striking the missile in flight to swing the segments radially outwards.
  • a known missile of this type contains an ejecting charge for each secondary projectile. Such an ejecting charge occupies a fairly considerable space and it is therefore desirable to do without such a charge. Moreover, in this missile each segment contains only one secondary projectile which is ejected after the segment has swung out through an angle of about 90. The range of scatter is therefore restricted and it is an aim of the invention that this range should be improved.
  • a missile having a casing composed of separate hinged segments containing movable secondary projectiles, said segments in locked position being mutually parallel and means for allowing a head wind striking the missile in flight to swing the segments outwards, in which a plurality of secondary projectiles are contained in each segment, the segments being hingeably deflectable through an angle of substantially 170, and in which the outward swing of the segments the secondary projectiles are slidably ejectable from the segments by the centrifugal forces generated by their outward swing.
  • FIG. 1 is a longitudinal section taken on the line II of FIG. of a missile according to the invention prior to its discharge, some of the parts being shown in elevation;
  • FIG. 2 is a section taken on the line Il-II of FIG. 5, on a larger scale of a first example of a hinge of one of the segments;
  • FIG. 3 is a section taken on the line IlIIII of FIG. 2;
  • FIG. 4 is a section taken on the line IV-IV of FIG. 1, on a larger scale, of unlocking means for one of the segments;
  • FIG. 5 is a cross section taken on the line V-V of FIG. 1;
  • FIG. 6 is a longitudinal section of the missile of FIG. 1, in flight shortly after the secondary projectiles have begun to move;
  • FIG. 7 is a drawing similar to FIG. 4 of another example of unlocking means for one of the segments of a missile according to the invention.
  • FIG. 8 is a section taken on the line VIllVlII of FIG. 7;
  • FIGS. 9 and 10 are drawings similar to FIG. 2 of the two further examples of hinges of the segments of a missile according to the invention.
  • FIG. 11 is a section taken on the line XIXI of FIG.
  • a flange 1 formed with a collar 2 is attached to the casing of a rocket motor.
  • the flange 1 is formed with a forwardly projecting coaxial hub 4.
  • a tube 5 filled with explosive 6 is fitted into the hub 4.
  • the front end of the tube 5 is closed by a cap 7 and this end carries a bush 8 (FIG. 4).
  • the missile has a head 9 having an inwardly projecting flange 10 forming a hub portion 11.
  • the hub portion 11 is screwed to the front end of the bush 8.
  • An impact fuse 12 forms the nose of the head 9.
  • Coaxially located inside the head 9 is a sleeve 13 which rests on the flange 10.
  • a time fuse 14 is contained inside the sleeve 13.
  • the direct action impact fuse 12 and the time fuse 14 are of conventional construction and are therefore not described in detail.
  • An annular chamber defined by the sleeve 13 and the head 9 of the missile contains an explosive charge 15.
  • a piston 16 having the form of a recessed disc is provided with a central bore in its crown l7 and in its base 18.
  • the bore in the crown 17 is of smaller diameter than the bore in the base 18.
  • the piston 16 is slidably movable on the bush 8 and guided in the head 9 of the missile.
  • a ring 19 is screwed on to the bush 8, spaced from the hub 11 in the head 9 of the missile.
  • the crown 17 of the piston 16 in a position of rest bears against the ring 19 and the side of the bore in the base 18 is in contact with the edge of the flange 20 of the bush 8.
  • a pyrotechnic charge 21 comprising a gas and a smoke generating component is accommodated in a recessed cavity of the piston 16.
  • the bush 8 has a blind bore 22 parallel to the missile axis which is in communication through a transverse bore 23 with the recessed cavity in the piston 16.
  • a container for a priming charge 24 is attached to the cap 7 of the tube 5 and covers the bore 22 in the bush 8.
  • the priming charge 24 is adjacent a detonator cap 25 of the time fuse 14.
  • a ring 26 is slidably mounted on the hub 4 of the flange 1.
  • a collar 27 projecting from the flange 1 in the forward direction forms an internal step 28.
  • a ring 29 is fitted into the wider diameter portion 30 of the collar 27 and bears against the step 28.
  • the rings 26 and 29 are each formed with six slots 31, 32 disposed in pairs at equiangular intervals, so that their planes of symmetry coincide with axial planes of the missile.
  • the cylindrical casing of the missile between the collar 27 and the piston 16 consists of six segments 33 of equal size, the abutting edges 34 being parallel to the missile axis.
  • edges 34 Machined into these edges 34 are grooves of semicircular cross section extending the entire length of the edges.
  • the longitudinal axes of all these grooves 85 are parallel to the missile axis.
  • the grooves 85 in each two abutting edges 34 enclose a cord 86 of circular section.
  • the cords 86 serve for sealing the joints between adjacent segments. They also prevent the external face of any edge 34 of a segment 33 being bent outwards and projecting beyond the corresponding edge of the abutting face 34 so as to form a cutting edge when the missile is in a launching tube or impairing the flying properties of the missile.
  • Another annular seal 87 is secured tov the collar 27 of the flange 1 and seals the joint between the collar 27 and the rear ends of the segments 33.
  • Each segment is formed on its inside with two ribs 35 that extend the full axial length of each segment and which are located at equal distances from the axial plane of symmetry of each segment 33.
  • the ribs 35 have faces 36 which are parallel to the missile axis, and which are contained in planes that intersect in the missile interior.
  • the ribs 35 also have faces 37 which forms parts of a cylinder having an axis contained in the plane of symmetry of the associated segment 33.
  • prismatic block 38 FIG. 3
  • a slit 40 having an enlarged portion 41 is machined into the block 38.
  • the planes of symmetry of the slits 40, 41 coincide with the planes of symmetry of the segments 33 and of the rings 26 and 29.
  • Machined into the walls of the slit 40 are slots 42 parallel to the missile axis.
  • the missile includes three cranked levers 43, 44 of identical construction having arms of different lengths as shown in FIG. 2.
  • the longer arms of the two levers 43 are connected by a pin 45 which engages the slot 42 in the block 38.
  • the shorter arms of the levers 43 engage a slit 32 in the ring 29 and are hingeably attached to a hinge pin 46 in the ring.
  • the lever 44 is located between the two levers 43 and is fulcrumed at its vertex to pivot about a pin 47 which is fixed in the vertex of each of the levers 43 on either side.
  • the shorter arm of the lever 44 is hinged to a pin 48 which crosses the slit 41, and which is fitted into the block 38.
  • the longer arm of the lever 44 engages a slit 31 in the ring 26 and is hingeably attached to a pin 49 in this ring.
  • the pins 45, 47, 46, 48, 49 are parallel and their axes are perpendicular to the missile axis.
  • the levers 43 and 44 form a hinge connection between a segment 33 and the collar 27 of the flange 1 as described and illustrated in the published unexamined specification of German Pat. application No. I4 53 819.
  • the piston 16 is provided with studs 50 projecting rearwards parallel to the missile axis.
  • the studs 50 bear against the faces 36 of the ribs 35 of the segments 33 (FIG. and retain them in the position shown in FIG. 1.
  • a sleeve 51 is mounted on the tube 5 and interposed between the bush 8 and the hub 4 of the flange l.
  • the sleeve 51 is formed, as shown in FIG. 5, with five equiangularly disposed enlarged portions 52 of semicircular cross section.
  • the radial side faces 34 of the segments 33 are contained in the planes of symmetry of the enlarged portions 52. Facing the center region of each segment 33 the sleeve 51 carries a steel blade 53.
  • the blades are formed by leaf springs which are retained in a cocked position as will be hereunder described.
  • Each segment 33 embraces a set of secondary projectiles 54 placed nose to tail.
  • the secondary projectiles 54 are held between the surfaces 37 of the ribs 35 of the segments and between the inside surface of the segment 33 and two enlarged portions 52 on the sleeve 51.
  • the secondary projectiles 54 have radially projecting studs 55 which bear against the faces 35 of the ribs on the segments 33.
  • the leading projectile 54 ofa set is kept in contact with the base 18 of the piston 16 by the spring 56.
  • the segment 33 is urged by the spring 56 acting through the levers 43, 44 and the rings 26, 29 against the flange l.
  • the forward ends of the blades 53 bear against the secondary projectiles 54 and are thus kept in an energized position.
  • the detonator 25 When in course of the flight of the missile the time fuse operates, the detonator 25 is fired in a conventional manner and ignites the priming charge 24 in turn fires the pyrotechnic charge 21 through the bores 22, 23 in the bush 8. Since the crown of the piston 16 exceeds the base of the piston in area the gas pressure that builds up in the recessed cavity of the piston, by virtue of the combustion of the charge, forces the piston forwards. The threads of the ring 19 shear off and the piston 16 together with the ring 19 are thrown forwards against the hub 11 of the missile head 9 (FIG. 6). At the end of its displacement the base 18 of the piston is in a position in front of the edge of the flange 20 of the bush 8. The dark colored gas escapes to the outside through the opening 57 thus formed which indicates that the ejection of the secondary projectiles 54 has begun. By the displacement of the piston 16 the studs 50 are withdrawn from the faces 36 of the segments 33 and these are therefore released.
  • the effect of the thrust of the leaf springs forming the blades 53 is now to pivot the segments 33 about the hinges 46 and 49.
  • the secondary projectiles 54 experience an acceleration in the axial direction of the segments 33 by the centrifugal forces generated by their outward swing.
  • the secondary projectiles 54 are guided by the segments 33, i.e., by the ribs 35 and the studs 55 and consecutively leave these guideways, flying away from their segments 33 at different speeds and in different directions.
  • the secondary projectile 54 that is originally located closest to the hinge of its segment is accelerated away quickly by the action of the spring 56 until major centrifugal forces can take effect.
  • the missile which has discharged its secondary projectiles 54 flying with its segments 33 widely opened and eventually hitting the ground the impact fuse 12 in the nose ignites the priming charge 15 in a manner not illustrated in detail and the priming charge in turn fires the explosive charge 6 contained in the center tube 5.
  • FIGS. 7 to 11 like components are identified by the same reference numbers as used in FIG. 1 to 6. Components that differ in shape are distinguished by a suffix a or b. Original components are given a new reference number.
  • the head 9a of the missile has a rearward sleeve-like extension 60.
  • a peripheral groove 61 in the end face of the extension 60 has two intersecting flanks 62, 63.
  • the flank 62 which is furthest away from the missile axis forms part of the surface of a cone which diverges towards the rear.
  • the inside wall of the extension 60 contains another peripheral groove 64 of triangular cross section.
  • the inside surface of the extension 60 also contains triangular grooves 65 disposed at equiangular intervals. The crests of the grooves 65 are parallel to the missile axis and intersect the crests of the two grooves 61 and 64.
  • the forward ends of the segments 33 engage the groove 61, the segments being thereby kept closed.
  • the bush 8a has a flange 66 which with its outer wall bears against the inside of the extension 60.
  • the bottom 59 of the missile head 9a and the flange 66 an annular chamber 67 containing a pyrotechnic charge 21.
  • the annular chamber 67 communicates with the priming charge 24 through bores 23 and 22.
  • the charge 21 is fired by the priming charge 24, as has already been described.
  • the gas pressure which builds up in the annular chamber 67 destroys the extension 60 by fracturing it along the lines of weakness defined by the grooves 62, 64 and 65, the fragments being thrown outwards. This releases the segments 33 which are accelerated by the outwardly projected fragments and lifted off the missile to be swung out by other forces in the manner already described with reference to the missile shown in FIGS. 1 to 6.
  • the collar 27a of the flange 1 contains a bore having two different diameters divided by a step and provided with axial slits 68 at equidistant angular intervals.
  • a coupling ring 69 is slidably movable on the hub 4 of the flange 1.
  • the coupling ring 69 has as many slits 70 as the collar 27a.
  • the planes of symmetry of the slits 70 are axial planes of the missile and coincide with the planes of symmetry of the slits 68.
  • Two slots 71 having planes of symmetry normal to the missile axis are machined into the flanks of the slits 70.
  • Each segment 33 is firmly attached to a connecting member 72.
  • a hinge arm 73 is affixed to the connecting member 72.
  • the arm 73 extends from the connecting member 72 along the hub 4 to the rear and in outwardly off-set to form a kind of hook.
  • Two studs 74 are fitted to the hook-shaped end 75.
  • the vertex of the hook-shaped portion 75 extends into the slit 70 in the coupling ring 69, whereas the studs 74 are guided in the slots 71.
  • the end of the hook-shaped portion 75 is received into a slit 68 in the collar 27a and linked therein to a hinge pin 76.
  • the outer shank of the hooked portion 75 is straight and the inner shank is bent slightly inwards.
  • a ring 77 is tightly fitted into the bore of the collar 27b of the flange 1.
  • the ring 77 has slits 78 disposed at equiangular intervals and having planes of symmetry that are axial planes of the missile.
  • a coupling ring 69 containing slits 70 is slidable on the hub 4 of the flange.
  • the planes of symmetry of the slits and 78 coincide.
  • Slots 71 and 79 respectively are cut into the walls of the slits 70 and 78.
  • the planes of symmetry of the slots 71 are normal to the missile axis as well as to the planes of symmetry of the slots 79.
  • a hinge arm 80 is connected to a segment by a connecting member 72.
  • the hinge arm 80 is parallel to the segment 33 and has two arcuately curved ends.
  • the rear portion 83 of the arm 80 substantially forms a circular arc towards the outside which carries a pair of studs 74 and 84 which engage the slot 71 in ring 70 and the slot 79 in ring 77.
  • a missile comprising, a casing formed of separate hinged segments, secondary projectiles contained in said segments, said segments in a locked position being mutually parallel, means for allowing a head wind striking the missile in flight to swing said segments outwards wherein the improvement resides in each of said segments containing a plurality of said secondary projectiles, saidsegments being hingeably deflectable through an angle of substantially and said secondary projectiles being slidably ejectable from said segments during its outward swingof said segments by the centrifugal forces generated by said outward swing.
  • a missile as defined in claim 1 including guideways contained in said segments to guide said secondary projectiles and prevent them from lifting off.
  • a missile'as defined in claim 2 including slots defined by said guideways, and studs mounted on said secondary projectiles which engage said slots to prevent said projectiles from lifting off said guideways.
  • a missile as defined in claim 1 wherein said means for allowing a head wind striking the missile in flight to swing said elements outwards comprises a piston operable by gas pressure and adapted to keep the segments together in their locked positions and to release the segments when displaced in the axial direction of the missile.
  • a missi'ie as defined in claim 4 including a recessed cavity defined by said piston, and two facing surfaces of different size bounding said cavity so that gas pressure generated in said cavity will displace said piston in a direction for releasing said segments.
  • a missile as defined in claim 1 including a missile head, a rearward sleeve-like extension formed on said head and embracing the front ends of said segments, an annular chamber defined by said extension, a pyrotechnic charge contained in said chamber, and grooves defined by said extension defining lines of weakness to enable said extension to be shattered when said pyrotechnic charge explodes and to release said segments.
  • a missile as defined in claim 1 including hinges linking said segments to the missile and an axially movable ring to which all of said segments are operatively coupled for opening said segments in unison.
  • a missile comprising a casing formed of separate segments hinges linking said segments to the missile, a plurality of movable secondary projectiles conformed in each of said segments, said segments in a locked position being mutually parallel, means for allowing a head wind striking the missile in flight to swing said elements outwards, said means comprising a piston operable by gas pressure and adapted to keep the segments together in their locked positions and to release the segments when displaced in the axial direction of the missile, and an axially movable ring to which all of said segments are operatively coupled for opening said segments in unison, said segments being hingeably deflectable through an angle of substantially 170 and said secondary projectiles being slidably ejectable from said segments during its outward swing of said segments by the centrifugal forces generated by said outward swmg.
  • a missile as defined in claim 8 including a recessed cavity defined by said piston, and two facing surfaces of different size bounding said cavity so that gas pressure generated in said cavity will displace said piston in a direction for releasing said segments.
  • a missile as defined in claim 8 including a missile head, a rearward sleeve-like extension formed on said head and embracing the front ends of said segments, an annular chamber defined by said extension, a pyrotechnic charge contained in said chamber, and grooves defined by said extension defining lines of weakness to enable said extension to be shattered when said pyrotechnic charge explodes and to release said segments.
  • a missile as defined in claim 8 including guideways contained in said segments to guide said secondary projectiles, slots defined by said guideways and studs mounted on said secondary projectiles which engage said slots to prevent said projectiles from lifting off said guideways.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Portable Nailing Machines And Staplers (AREA)
US00161574A 1970-07-17 1971-07-12 Missile having a casing and containing secondary projectiles Expired - Lifetime US3712229A (en)

Applications Claiming Priority (1)

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CH1090270A CH526764A (de) 1970-07-17 1970-07-17 Geschoss mit einem Geschossmantel

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US3712229A true US3712229A (en) 1973-01-23

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US (1) US3712229A (fr)
JP (1) JPS513159B1 (fr)
BE (1) BE770114A (fr)
CA (1) CA945004A (fr)
CH (1) CH526764A (fr)
DE (1) DE2134945C3 (fr)
FR (1) FR2101786A5 (fr)
GB (1) GB1355862A (fr)
IL (1) IL37320A (fr)
NL (1) NL148701B (fr)
SE (1) SE368085B (fr)

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3916794A (en) * 1972-09-26 1975-11-04 Oerlikon Buehrle Ag Projectile with secondary projectiles and firing apparatus for such projectile
US3943854A (en) * 1973-04-12 1976-03-16 Dynamit Nobel Aktiengesellschaft Ejection head with active elements for rockets
US4221167A (en) * 1978-10-16 1980-09-09 The United States Of America As Represented By The Secretary Of The Army Delay burster for a projectile
DE3048617A1 (de) * 1980-12-23 1982-07-22 Dynamit Nobel Ag, 5210 Troisdorf Gefechtskopf mit sekundaerkoerpern als nutzlast
US4342262A (en) * 1976-02-23 1982-08-03 Rheinmetall Gmbh Carrier missile for ejectable bodies
US4372216A (en) * 1979-12-26 1983-02-08 The Boeing Company Dispensing system for use on a carrier missile for rearward ejection of submissiles
US4448106A (en) * 1978-07-05 1984-05-15 Mcdonnell Douglas Corporation Method of identifying hard targets
US4625646A (en) * 1980-10-06 1986-12-02 The Boeing Aerospace Company Aerial missile having multiple submissiles with individual control of submissible ejection
US4726297A (en) * 1985-05-22 1988-02-23 Bueno Leoncio M Submunition ejection system
US4754706A (en) * 1983-06-27 1988-07-05 Etienne Lacroix Tous Artifices Munition scattering projectile
US5605308A (en) * 1994-06-06 1997-02-25 Mcdonnell Douglas Corp. Space vehicle dispenser
US6138951A (en) * 1998-08-10 2000-10-31 Mcdonnell Douglas Corporation Spacecraft dispensing system
US6296206B1 (en) 1999-12-01 2001-10-02 The Boeing Company Cantilever, bi-level platform satellite dispenser
US6357698B1 (en) 2000-02-02 2002-03-19 The Boeing Company Twin lobe spacecraft dispenser apparatus and method
US6416018B2 (en) 1996-09-17 2002-07-09 The Boeing Company Satellite dispenser
US6718883B2 (en) * 2000-01-26 2004-04-13 Giat Industries Device for neutralizing a payload
US6874425B1 (en) 2001-05-18 2005-04-05 Day & Zimmermann, Inc. Projectile carrying sub-munitions
US7007607B1 (en) * 2004-04-14 2006-03-07 The United States Of America As Represented By The Secretary Of The Army Missile system for breaching reinforced concrete barriers utilizing hinged explosively formed projectile warheads
US20090288573A1 (en) * 2006-11-13 2009-11-26 Rafael Advanced Defense Systems Ltd. Warhead for intercepting system
US9188417B2 (en) * 2013-08-01 2015-11-17 Raytheon Company Separable sabot for launching payload
US20220049940A1 (en) * 2020-08-17 2022-02-17 The Boeing Company Targeting systems and methods
US11407532B2 (en) 2017-08-23 2022-08-09 Thales Alenia Space Italia S.P.A. Con Unico Socio Innovative system for deploying satellites from launch vehicles

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Publication number Priority date Publication date Assignee Title
GB2134228B (en) * 1979-10-31 1985-05-15 Secr Defence Multi source cartridge
IT1167034B (it) * 1983-11-30 1987-05-06 Simmel Spa Dispositivo di allontanamento reciproco delle submunizioni di un proiettile non rotante a submunizioni
FR2638227B1 (fr) * 1988-10-21 1993-11-05 Thomson Brandt Armements Systeme de maintien de sous-munitions embarquees
DE102011010183A1 (de) * 2011-02-02 2012-08-02 Rheinmetall Waffe Munition Gmbh Sprenggeschoss
SE1700293A2 (en) * 2017-11-28 2020-05-12 Bae Systems Bofors Ab Device and method for counteracting a tumbling motion of elongated sub-projectiles

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US3023703A (en) * 1955-08-24 1962-03-06 Beatty John William Chaff dispensing device
US3093072A (en) * 1957-01-30 1963-06-11 George L Pigman Spin-induced dispersal bomb
US3276367A (en) * 1964-07-24 1966-10-04 William R Edwards Air delivery apparatus and method
US3295444A (en) * 1956-08-02 1967-01-03 Vincent J Cushing Dispersal type cluster warhead

Patent Citations (4)

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Publication number Priority date Publication date Assignee Title
US3023703A (en) * 1955-08-24 1962-03-06 Beatty John William Chaff dispensing device
US3295444A (en) * 1956-08-02 1967-01-03 Vincent J Cushing Dispersal type cluster warhead
US3093072A (en) * 1957-01-30 1963-06-11 George L Pigman Spin-induced dispersal bomb
US3276367A (en) * 1964-07-24 1966-10-04 William R Edwards Air delivery apparatus and method

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3916794A (en) * 1972-09-26 1975-11-04 Oerlikon Buehrle Ag Projectile with secondary projectiles and firing apparatus for such projectile
US3943854A (en) * 1973-04-12 1976-03-16 Dynamit Nobel Aktiengesellschaft Ejection head with active elements for rockets
US4342262A (en) * 1976-02-23 1982-08-03 Rheinmetall Gmbh Carrier missile for ejectable bodies
US4448106A (en) * 1978-07-05 1984-05-15 Mcdonnell Douglas Corporation Method of identifying hard targets
US4221167A (en) * 1978-10-16 1980-09-09 The United States Of America As Represented By The Secretary Of The Army Delay burster for a projectile
US4372216A (en) * 1979-12-26 1983-02-08 The Boeing Company Dispensing system for use on a carrier missile for rearward ejection of submissiles
US4625646A (en) * 1980-10-06 1986-12-02 The Boeing Aerospace Company Aerial missile having multiple submissiles with individual control of submissible ejection
DE3048617A1 (de) * 1980-12-23 1982-07-22 Dynamit Nobel Ag, 5210 Troisdorf Gefechtskopf mit sekundaerkoerpern als nutzlast
US4488489A (en) * 1980-12-23 1984-12-18 Dynamit Nobel Aktiengesellschaft Ordnance system having a warhead with secondary elements as a payload
US4754706A (en) * 1983-06-27 1988-07-05 Etienne Lacroix Tous Artifices Munition scattering projectile
US4726297A (en) * 1985-05-22 1988-02-23 Bueno Leoncio M Submunition ejection system
US5605308A (en) * 1994-06-06 1997-02-25 Mcdonnell Douglas Corp. Space vehicle dispenser
US6416018B2 (en) 1996-09-17 2002-07-09 The Boeing Company Satellite dispenser
US6138951A (en) * 1998-08-10 2000-10-31 Mcdonnell Douglas Corporation Spacecraft dispensing system
US6296206B1 (en) 1999-12-01 2001-10-02 The Boeing Company Cantilever, bi-level platform satellite dispenser
US6718883B2 (en) * 2000-01-26 2004-04-13 Giat Industries Device for neutralizing a payload
US6357698B1 (en) 2000-02-02 2002-03-19 The Boeing Company Twin lobe spacecraft dispenser apparatus and method
US6874425B1 (en) 2001-05-18 2005-04-05 Day & Zimmermann, Inc. Projectile carrying sub-munitions
US7007607B1 (en) * 2004-04-14 2006-03-07 The United States Of America As Represented By The Secretary Of The Army Missile system for breaching reinforced concrete barriers utilizing hinged explosively formed projectile warheads
US20090288573A1 (en) * 2006-11-13 2009-11-26 Rafael Advanced Defense Systems Ltd. Warhead for intercepting system
US8091482B2 (en) * 2006-11-13 2012-01-10 Rafael Advanced Defense Systems Ltd. Warhead for intercepting system
US9188417B2 (en) * 2013-08-01 2015-11-17 Raytheon Company Separable sabot for launching payload
US11407532B2 (en) 2017-08-23 2022-08-09 Thales Alenia Space Italia S.P.A. Con Unico Socio Innovative system for deploying satellites from launch vehicles
US20220049940A1 (en) * 2020-08-17 2022-02-17 The Boeing Company Targeting systems and methods
US11619474B2 (en) * 2020-08-17 2023-04-04 The Boeing Company Targeting systems and methods

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CA945004A (en) 1974-04-09
DE2134945B2 (de) 1973-10-31
DE2134945A1 (de) 1972-01-20
IL37320A0 (en) 1972-01-27
IL37320A (en) 1975-06-25
FR2101786A5 (fr) 1972-03-31
NL148701B (nl) 1976-02-16
NL7109753A (fr) 1972-01-19
JPS513159B1 (fr) 1976-01-31
CH526764A (de) 1972-08-15
DE2134945C3 (de) 1974-05-30
BE770114A (fr) 1971-12-01
GB1355862A (en) 1974-06-05
SE368085B (fr) 1974-06-17

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