EP0077954A2 - Missile - Google Patents

Missile Download PDF

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Publication number
EP0077954A2
EP0077954A2 EP82109324A EP82109324A EP0077954A2 EP 0077954 A2 EP0077954 A2 EP 0077954A2 EP 82109324 A EP82109324 A EP 82109324A EP 82109324 A EP82109324 A EP 82109324A EP 0077954 A2 EP0077954 A2 EP 0077954A2
Authority
EP
European Patent Office
Prior art keywords
missile
segments
rod
longitudinal axis
missile according
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP82109324A
Other languages
German (de)
English (en)
Other versions
EP0077954B1 (fr
EP0077954A3 (en
Inventor
Dieter Dipl.-Ing. Böder
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 Industrie AG
Original Assignee
Rheinmetall GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rheinmetall GmbH filed Critical Rheinmetall GmbH
Publication of EP0077954A2 publication Critical patent/EP0077954A2/fr
Publication of EP0077954A3 publication Critical patent/EP0077954A3/de
Application granted granted Critical
Publication of EP0077954B1 publication Critical patent/EP0077954B1/fr
Expired legal-status Critical Current

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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
    • F42B12/60—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected radially

Definitions

  • the invention relates to a missile for transporting a plurality of payloads to be ejected at a predeterminable point of the trajectory, with a tubular shell enclosing the payload space and means for ejecting the payload.
  • a missile in which the payloads are ejected in the axial direction of the missile, in particular in the direction of flight, is known from DE-OS 25 58 060. It is also known to eject payloads in the axial direction of the missile from the rear.
  • the invention has for its object to provide a missile with which the distribution of payloads over relatively wide terrain strips along the trajectory of the missile is possible and which is characterized by a particularly robust acceleration-resistant mechanical design.
  • FIG. 1 shows a schematic representation of a missile for transporting a plurality of payloads ejected at a predeterminable point of the flight path.
  • the tail unit 2 arranged at the rear of the missile there is an essentially hollow-cylindrical part of the missile 10, which is delimited on the outside by a tubular casing 12.
  • This envelope 12 encloses a payload space 4, in which payloads 11 are arranged separately, if necessary, by floors 24 extending transversely to the longitudinal axis of the missile 10.
  • these payloads 11 In order to be able to cover the widest possible terrain strip along the trajectory of the missile with payloads 11 to be ejected, these payloads 11 must be ejected in the radial direction, that is, perpendicular to the direction of travel of the missile 10. For this purpose, it is necessary that at a predeterminable point in time, namely when the missile 10 has reached a specific point on its trajectory, the tubular envelope surrounding the payload space 4 is removed in order to enable the payloads to be ejected in the radial direction.
  • the invention is particularly concerned with the configuration of the tubular shell 12 of the missile, which has to withstand considerable acceleration values both in the longitudinal axis direction of the missile 10 and in the circumferential direction when the missile 10 is launched and moved.
  • the cover 12 must nevertheless be easily ejectable in order to enable the unimpeded ejection of the payloads 11.
  • FIG. 2 shows a partial sectional illustration in the longitudinal axis direction of the missile 10 in the region of the payload space of the missile 10.
  • FIG. 3 shows a view of a cross-sectional plane of the missile 10 as viewed from line 3 - 3 according to FIG. Fig. 2.
  • FIG. 4 shows a detailed illustration from FIG. 3 on a substantially enlarged scale
  • the tubular sleeve 12 consists of a plurality of segments 13, 13 'which are detachably connected to one another and which abut one another with their side edges 16, 16' in such a way that they essentially form a cylindrical surface.
  • each side edge 16, 16' of each segment 13, 13 ' is adjacent to the inside surface 14 of each segment and projecting hook-shaped extensions 15, 15 'arranged.
  • FIG. 5 shows a partial sectional view in the longitudinal axis direction of the missile 10 in the region of such a rod 18.
  • the rod 18 has eccentric and / or conical or stepped seats 19 in the region of the hook-shaped extensions 15, 15 ', to which the hook-shaped brake sets 15, 15 'can create, whereby they can be clamped against each other when the rod 18 moves relative to the hook-shaped extensions 15, 15'.
  • this bracing is achieved by moving the rod 18 during assembly of the segments 13, 13 'in the longitudinal axis direction of the missile 10.
  • bracing can be achieved the hook-shaped extensions 15, 15 'by rotating the rod 18 about its longitudinal axis and / or simultaneous longitudinal movement of the rod 18 in the longitudinal axis direction of the missile 10.
  • the locking of the segments 13, 13 'achieved with the aid of the rod 18 can be achieved after reaching the end agreed discharge point of the payloads 11 can be easily removed by moving the rod 18 in the opposite direction - as during assembly - and / or rotating.
  • This longitudinal or. Rotary movement of the rod 18 naturally requires a certain force. This can be provided in a particularly simple and reliable manner by means of a pyrotechnic charge 20 provided with an optionally electrically activatable igniter 21.
  • the rod 18 is expediently designed as a hollow cylinder which is closed on one side and rests with its open end piece 22 on the pyrotechnic charge 20.
  • the gases generated when the pyrotechnic charge 20 is ignited can consequently penetrate through the open end piece 22 of the rod 18 into its interior and exert a force on its end face opposite the open end piece. Since the pryoretic charge 20 also acts on the circular surface of the rod 18 with which it rests on the pyrotechnic charge 20, there is a particularly advantageous compressive-tensile force on the rod 18 which moves it in the longitudinal axis direction of the missile and this leads to an unlocking of the segments 13, 13 '.
  • floors 24 extending transversely to the longitudinal axis of the missile 10 are provided, on the lateral surface 25 of which the segments 13 , 13 'rest with their inner surface.
  • grooves 26 are recessed into the lateral surfaces 25 of the floors, into which a collar 27 arranged on the segments 13, 13' engages.
  • grooves 26 and collar 27 are preferably wedge-shaped in cross section (FIG. 6).
  • the missile At launch, the missile is given a rotational movement about its longitudinal axis, which can also be maintained or reinforced during flight, if necessary, by additionally arranged engines.
  • This rotational movement leads to force components directed transversely to the longitudinal axis, which act on the segments 13, 13 'forming the shell 12 with the aim of torsion.
  • the segments 13, 13' and the bottoms 24 are either hooked in the area of their wedge-shaped connection (FIG. 7) or equipped with interlocking teeth 28 (FIG. 8).
  • FIG. 8 shows a sectional illustration along the line 8-8 according to FIG. Fig. 7.
  • the segments 13, 13 ' are preferably produced from light metals commonly used in aircraft construction or also from plastic, in particular fiber-reinforced plastic.
  • a support structure extending in the longitudinal axis direction of the missile is advantageously provided in the interior of the missile 10, which on the one hand divides the payload space 4 into individual compartments 4 'for receiving a payload 11 each and which on the other hand offers support points or support surfaces 29 to which the segments 13 , 13 'can additionally support with their inner surface 14.
  • the support structure expediently comprises partition walls 30 which are arranged parallel to the longitudinal axis of the missile and which enclose an angle between them and which partition off the rods 18, the hook-shaped extensions 15, 15 'and the joints between the segments 13, 13' in relation to the payloads 11.
  • the segments 13, 13 'simultaneously serve to hold additional or correction engines, which, for example during the flight phase of the missile 10, maintain or reinforce the swirl communicated to it during takeoff. This additional or correction engines are then separated from the missile together with the segments 13, 13 'during unlocking.
  • the unlocking of the segments 13, 13 ' can be carried out simultaneously or with a time delay if necessary.
  • the chronological order can be checked by activating the pyrotechnic charges 20.
  • the ejection of the payloads 11 can either take place simultaneously with the separation of the segments 13, 13 'or take place with a time delay.
  • the latter possibility allows the targeted ejection of a payload 11 in correlation to the rotational movement of the missile 10 with respect to its longitudinal axis. This proves to be particularly expedient in those cases in which a large radial throw range is aimed at when the payloads 11 are ejected.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Toys (AREA)
  • Elimination Of Static Electricity (AREA)
EP82109324A 1981-10-24 1982-10-08 Missile Expired EP0077954B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3142313 1981-10-24
DE19813142313 DE3142313A1 (de) 1981-10-24 1981-10-24 Flugkoerper

Publications (3)

Publication Number Publication Date
EP0077954A2 true EP0077954A2 (fr) 1983-05-04
EP0077954A3 EP0077954A3 (en) 1983-11-16
EP0077954B1 EP0077954B1 (fr) 1986-08-13

Family

ID=6144802

Family Applications (1)

Application Number Title Priority Date Filing Date
EP82109324A Expired EP0077954B1 (fr) 1981-10-24 1982-10-08 Missile

Country Status (7)

Country Link
US (1) US4524694A (fr)
EP (1) EP0077954B1 (fr)
JP (1) JPS5883199A (fr)
AU (1) AU555916B2 (fr)
CA (1) CA1186561A (fr)
DE (2) DE3142313A1 (fr)
ES (1) ES516686A0 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2000853A6 (es) * 1986-08-08 1988-03-16 Esperanza & Cie Sa Proyectil portador para mortero
FR2617464B1 (fr) * 1987-07-03 1990-02-16 Thomson Brandt Armements Dispositif de fermeture ejectable, notamment pour roquettes a sous-munitions
FR2641858B1 (fr) * 1989-01-17 1991-03-15 Thomson Brandt Armements Dispositif de deverrouillage pneumatique pour munitions largables a partir d'un vecteur
FR2656414B1 (fr) * 1989-12-22 1993-01-22 Thomson Brandt Armements Systemes de retenue de sous-munitions embarquees dans un vecteur.
SE503719C2 (sv) * 1992-06-30 1996-08-12 Bofors Ab Sätt och anordning för separation av substridsdelar
US6003809A (en) * 1997-02-25 1999-12-21 Honigsbaum; Richard F. Process and apparatus for discouraging countermeasures against a weapon transport device

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE298070C (fr) *
US2411432A (en) * 1943-05-31 1946-11-19 Imber Jack Aerial bombs, pyrotechnic devices, and the like
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
US3215082A (en) * 1962-09-24 1965-11-02 Aerojet General Co Rapid release device for connecting rocket stages
US3253842A (en) * 1963-12-10 1966-05-31 Thiokol Chemical Corp Shear key joint
FR2336656A1 (fr) * 1975-12-22 1977-07-22 Rheinmetall Gmbh Projectile porteur pour corps ejectables
US4120519A (en) * 1977-10-03 1978-10-17 The Bendix Corporation Collet type cylinder separation device
DE2920347A1 (de) * 1979-05-19 1980-11-20 Messerschmitt Boelkow Blohm Gefechtskopf mit ausstossbaren wirkkoerpern

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2450910A (en) * 1938-10-07 1948-10-12 George M O'rear Aerial bomb
US2604043A (en) * 1946-05-16 1952-07-22 Foster Wheeler Corp Bomb
US2809583A (en) * 1952-12-04 1957-10-15 Roman L Ortynsky Cluster bomb
US3461801A (en) * 1968-01-25 1969-08-19 Us Navy Multi-canister ejecting device
DE1955777C3 (de) * 1969-11-06 1979-11-22 Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen Gefechtskopf
US4178851A (en) * 1972-03-08 1979-12-18 The United States Of America As Represented By The Secretary Of The Army Dual purpose munition
DE2739299C2 (de) * 1977-09-01 1984-01-19 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Halterung für Streuwaffengroßbehälter
DE2903938A1 (de) * 1979-02-02 1980-08-14 Messerschmitt Boelkow Blohm Streumunition

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE298070C (fr) *
US2411432A (en) * 1943-05-31 1946-11-19 Imber Jack Aerial bombs, pyrotechnic devices, and the like
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
US3215082A (en) * 1962-09-24 1965-11-02 Aerojet General Co Rapid release device for connecting rocket stages
US3253842A (en) * 1963-12-10 1966-05-31 Thiokol Chemical Corp Shear key joint
FR2336656A1 (fr) * 1975-12-22 1977-07-22 Rheinmetall Gmbh Projectile porteur pour corps ejectables
US4120519A (en) * 1977-10-03 1978-10-17 The Bendix Corporation Collet type cylinder separation device
DE2920347A1 (de) * 1979-05-19 1980-11-20 Messerschmitt Boelkow Blohm Gefechtskopf mit ausstossbaren wirkkoerpern

Also Published As

Publication number Publication date
EP0077954B1 (fr) 1986-08-13
JPS5883199A (ja) 1983-05-18
AU555916B2 (en) 1986-10-16
US4524694A (en) 1985-06-25
EP0077954A3 (en) 1983-11-16
ES8309004A1 (es) 1983-10-16
ES516686A0 (es) 1983-10-16
DE3142313A1 (de) 1983-05-05
DE3272598D1 (en) 1986-09-18
CA1186561A (fr) 1985-05-07
AU8862682A (en) 1983-04-28

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