EP0413670A1 - Verfahren zum Trennen von Gefechtsköpfen - Google Patents

Verfahren zum Trennen von Gefechtsköpfen Download PDF

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Publication number
EP0413670A1
EP0413670A1 EP90850280A EP90850280A EP0413670A1 EP 0413670 A1 EP0413670 A1 EP 0413670A1 EP 90850280 A EP90850280 A EP 90850280A EP 90850280 A EP90850280 A EP 90850280A EP 0413670 A1 EP0413670 A1 EP 0413670A1
Authority
EP
European Patent Office
Prior art keywords
missile
actuation part
actuation
separating
remaining
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.)
Withdrawn
Application number
EP90850280A
Other languages
English (en)
French (fr)
Inventor
Pal Hellman
Ingmar Johansson
Thomas LÖNNERMO
Stig Nilsson
Yngve Stradalen
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.)
Saab Bofors AB
Original Assignee
Bofors AB
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 Bofors AB filed Critical Bofors AB
Publication of EP0413670A1 publication Critical patent/EP0413670A1/de
Withdrawn legal-status Critical Current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
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means

Definitions

  • the present invention relates to a method and arrangement for separating an actuation part from a non-spin-­stabilized missile, for example a winged shell or the like.
  • the actuation part When an actuation part is to be separated from a non-­spin-stabilized missile, for example a winged shell, the actuation part will be positioned to the side of the trajectory of the missile so as not to collide with other missile parts.
  • This separation can be carried out in several ways.
  • one known method involves the actuation part being positioned to the side of the trajectory by means of a band being secured via a receiving element on the front part and pulled round behind the actuation part and attached to the front edge of the rear part of the missile.
  • the actuation part is lifted by the steel band out of the rear part and, in the final stage when the band is stretched, acquires a velocity perpendicular to the direction of flight.
  • the disadvantage of this method is that the actuation part is not positioned to the side of the missile tra­jectory in a controlled manner.
  • Another known method for smoke shells is to have the actuation part and the rear part of the missile con­stitute one unit. Following an impulse from a rocket motor, which turns the missile, the front body is separ­ated from the rear part of the missile, after which a parachute is released from the separation section of the rear part and lands the actuation part at a suitable, low velocity.
  • the disadvantage of the above method is that it requires a special rocket motor for turning the missile, and the construction is difficult to apply to illuminating shells.
  • the aim of the present invention is to provide a separa­tion method and arrangement for an actuation part in non-­spin-stabilized missiles which in a simple manner posi­tions the actuation part to the side of the trajectory of the missile.
  • Figure 1 shows a missile 1 commencing a separation proce­dure in the top right-hand corner of the figure.
  • the missile can be, for example, a winged shell which has been fired from a shell thrower in a conventional manner in a stable ballistic trajectory, that is to say the centre of gravity of the missile lies with an adequate margin in front of the common point of impact of the air forces, the centre of pressure, so that the shell seeks to fly with its longitudinal axis in the direction of the trajectory tangent.
  • the actuation part can be a lighting unit for illuminating the target area.
  • the separation procedure begins when the front part 2 of the missile is caused to separate from the rest of the missile, consisting of the actuation part 3 and the rear part 4 of the missile, for example by means of an internal overpressure from a pyrotechnic charge.
  • the actuation part and the rear part of the missile become unstable and roll round. If the centre of gravity of the actuation part lies in front of the centre of rotation, the actuation part 3 is slung off from the rear part 4 of the missile by the centrifugal force and ends up to the side of the missile trajectory.
  • a body If a body is exposed to an impinging medium, in this case air, it is subject to external forces.
  • the rolling of the actuation part and of the rear part of the missile can be achieved or reinforced by means of a special design of the actuation part.
  • the asymmetrical front ends of the actuation part as described also acquire an impulse, cooperating with the air forces, from the internal gas pressure separating the missile, if such is used.
  • the impulse arises at the moment when the separation of the front body is completed and it is emptied of the separating gases.
  • a pyrotechnic charge or rocket motor 7 can also be used, which gives an impulse directed transverse to the trajectory, see Figure 4.
  • the above description of the invention is based on the assumption that the front part of the missile is first removed and the actuation part thereafter separates from the rear part of the missile during rolling.
  • the separation method is equally applicable when the rear part of the missile is the first part to be separated.
  • the arrangements above can also be designed so that they are adapted to this case.
  • the advantages of the invention are its simple construc­tion and its use of the impinging of the air and, if ap­propriate, the impulse from the gases separating the missile, or a simple pyrotechnic charge, for tipping the actuation part and rear body and thereby initiating a separation by means of the effect of the centrifugal forces.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Automatic Assembly (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Toys (AREA)
EP90850280A 1989-08-17 1990-08-15 Verfahren zum Trennen von Gefechtsköpfen Withdrawn EP0413670A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
SE8902755 1989-08-17
SE8902755A SE468367B (sv) 1989-08-17 1989-08-17 Separeringssaett foer verkansdelar

Publications (1)

Publication Number Publication Date
EP0413670A1 true EP0413670A1 (de) 1991-02-20

Family

ID=20376681

Family Applications (1)

Application Number Title Priority Date Filing Date
EP90850280A Withdrawn EP0413670A1 (de) 1989-08-17 1990-08-15 Verfahren zum Trennen von Gefechtsköpfen

Country Status (2)

Country Link
EP (1) EP0413670A1 (de)
SE (1) SE468367B (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19518312C1 (de) * 1995-05-18 1996-10-24 Daimler Benz Aerospace Ag Antriebsloser Flugkörper

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2654320A (en) * 1949-03-07 1953-10-06 Roy J Schmid Severable aircraft
LU56243A1 (de) * 1967-06-13 1968-09-23
US3534686A (en) * 1968-10-04 1970-10-20 Nasa Payload/burned-out motor case separation system
FR2189703A1 (de) * 1972-06-22 1974-01-25 State Of Israel Ministry Defen

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2654320A (en) * 1949-03-07 1953-10-06 Roy J Schmid Severable aircraft
LU56243A1 (de) * 1967-06-13 1968-09-23
US3534686A (en) * 1968-10-04 1970-10-20 Nasa Payload/burned-out motor case separation system
FR2189703A1 (de) * 1972-06-22 1974-01-25 State Of Israel Ministry Defen

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19518312C1 (de) * 1995-05-18 1996-10-24 Daimler Benz Aerospace Ag Antriebsloser Flugkörper

Also Published As

Publication number Publication date
SE468367B (sv) 1992-12-21
SE8902755L (sv) 1991-02-18
SE8902755D0 (sv) 1989-08-17

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