EP0587969B1 - Submunition - Google Patents

Submunition Download PDF

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Publication number
EP0587969B1
EP0587969B1 EP92850217A EP92850217A EP0587969B1 EP 0587969 B1 EP0587969 B1 EP 0587969B1 EP 92850217 A EP92850217 A EP 92850217A EP 92850217 A EP92850217 A EP 92850217A EP 0587969 B1 EP0587969 B1 EP 0587969B1
Authority
EP
European Patent Office
Prior art keywords
sub
combat unit
combat
axis
unit
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.)
Expired - Lifetime
Application number
EP92850217A
Other languages
English (en)
French (fr)
Other versions
EP0587969A1 (de
Inventor
Dan Borgström
Lasse Karlsen
Lars Paulsson
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
Priority to SE9101037A priority Critical patent/SE468261B/sv
Application filed by Bofors AB filed Critical Bofors AB
Priority to EP92850217A priority patent/EP0587969B1/de
Priority to DE69219468T priority patent/DE69219468T2/de
Priority to AT92850217T priority patent/ATE152511T1/de
Priority to US07/957,488 priority patent/US5280752A/en
Priority claimed from US07/957,488 external-priority patent/US5280752A/en
Publication of EP0587969A1 publication Critical patent/EP0587969A1/de
Application granted granted Critical
Publication of EP0587969B1 publication Critical patent/EP0587969B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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
    • F42B10/50—Brake flaps, e.g. inflatable

Definitions

  • the present invention relates to a sub-combat unit disposed to be separated from a flying body, for example a carrier shell or the like over a target area, the sub-combat unit comprising a warhead, a target detector and a device which imparts to the sub-combat unit a rotation for scanning the target area in a helical pattern during the fall of the sub-combat unit towards the target area.
  • a flying body for example a carrier shell or the like over a target area
  • the sub-combat unit comprising a warhead, a target detector and a device which imparts to the sub-combat unit a rotation for scanning the target area in a helical pattern during the fall of the sub-combat unit towards the target area.
  • a sub-combat unit has been previously described in European patent specification 0 252 036.
  • the target detector is pivotally disposed on a journal shaft which is parallel to the line of symmetry of the warhead so as to permit outward pivoting of the target detector from a closed position where the optical axis of the target detector coincides with the line of symmetry of the warhead, and to in opened position where the optical axis of the target detector is parallel to the line of symmetry of the warhead so as to permit a free view of the target detector beside the warhead, and that, furthermore, carrier surface is pivotally disposed on a journal shaft which is also parallel to the line of symmetry of the warhead so as to permit outward pivoting of the carrier surface from a closed position to an opened position beside the warhead.
  • Swedish patent application number 8903474-8 describes a sub-combat unit in which the retarding area has been made considerably larger.
  • the characterizing feature of the sub-combat unit is that two diametrically located carrier surfaces are pivotally disposed each on their shaft located in a plane which is at right angles to the axis of symmetry of the warhead, from a closed position where the carrier surfaces follow the casing surface of the sub-combat unit, to a 90 opened position where both of the carrier surfaces form a retarding area for the fall velocity of the sub-combat unit.
  • the carrier surfaces are made of an elastically flexible material, so that, when they pivot out from their closed position, they are at the same time bent to a substantially straight or gently curved surface.
  • both of the carrier surfaces may be made comparatively thin, which is favourable from the point of view of weight and payload.
  • the carrier surfaces may be made of titanium and bent so that, in their opened position, they have a certain radius. The bending may be varied and the carrier surfaces may be of different lengths, in which event further parameters for varying the aeronautical properties of the unit will be obtained.
  • the sub-combat units are disposed to be separated from a missile, a carrier shell or other flying platform, for example a canister which in its turn has been separated from a carrier shell or missile, for example a 15.5 cm artillery shell.
  • the flying state of the sub-combat units is, however, highly varied, depending upon discharge descent, different from the described state, i.e. a state in which the axis of rotation is near to vertical as is to apply during the scanning phase.
  • the carrier for example an artillery shell, missile or canister
  • the sub-combat units will, on discharge of the sub-combat units, have a trajectory which may be as good as horizontal.
  • the sub-combat unit will begin to rotate about its major main inertia axis, at the same time as this axis will begin to oscillate.
  • the major direction of the axis will, however, be largely parallel to the trajectory tangent of the carrier prior to separation.
  • the object of the present invention is to obviate the problem inherent in causing the direction of the axis of rotation of the sub-combat unit to be deflected to as good as vertical, at the same time as the pendulum motion of the axis is damped, i.e. changing the orientation of the sub-combat unit into the prescribed state.
  • the mass of the subcombat unit is distributed such that the ratio between the largest main inertia moment and the other main inertia moments of the sub-combat unit lies within the range of between 1.05 to 1.15.
  • a value of lower than 1.05 means that the pendulum motion or oscillation of the axis of rotation is damped too slowly
  • a value higher than 1.15 implies that the deflection of the axis to almost vertical position will take too long time, i.e. will require too long a trajectory length.
  • the moment is developed as a result of the angle of entry or angle of attack and the angle of wind impingement on the sub-combat unit.
  • the moment also damps oscillations in the sub-combat unit, so that stationary flying state with small oscillation amplitudes is achieved at the beginning of the scanning phase. In stationary flight state, the aerodynamic moments are slight on the sub-combat unit.
  • sub-combat units which are described here are disposed in an artillery shell which is discharged by means of a 155 mm howitzer in a ballistic trajectory towards the target area.
  • the artillery shell may, for instance carry two sub-combat units.
  • the sub-combat units are separated from the shell and, during a transitional phase, the sub-combat units are to be set in a pre-determined rotation, fall velocity and orientation at the beginning of the scanning phase.
  • the sub-combat units are enclosed in a cylindrical canister which is fitted with brake fins in order to deduce the rotation of the sub-combat units.
  • two diametrically located carrier surfaces 1, 2 on the sub-combat unit are activated, the two carrier surfaces being pivotally disposed from a collapsed position where the carrier surfaces follow the casing surface 3 of the sub-combat unit, and to an opened position where both of the retarding surfaces form a retarding area.
  • the sub-combat unit comprises a warhead 4 and a target detector 5 which is displaced from a collapsed position in a stirrup-like superstructure 6 on the warhead to an opened position where it has free view beside the warhead.
  • the detector When the prescribed flying state of the sub-combat unit has been achieved, i.e. predetermined rotation, fall velocity and orientation, and additional conditions such as prescribed altitude over the target area have been achieved, the detector is activated and the scanning phase begins.
  • the detector scans the target area in a helical pattern, similar to the groove in a gramophone record, during the fall of the sub-combat unit down towards the target area.
  • a SAF safety, arming and firing unit
  • a directed explosive projectile is discharged with high kinetic energy towards the target, for example the turret roof on a tank.
  • the carrier surfaces, detector and warhead proper are of per se known type and will not, therefore, be described in greater detail here.
  • the sub-combat unit will, after the separation, begin to rotate about its major main inertia axis. It is important that a sufficient aerodynamic moment is created so that oscillations in the sub-combat unit are damped and that the orientation of the main inertia axis is modified to almost vertical. According to the present invention, this is achieved by causing the moment of inertia to maintain a ratio in a given manner.
  • the ratio between the largest main inertia moment, i.e. the moment of inertia of the main inertia axis and the other main inertia moments must be about 1:1.
  • the co-ordinate system XYZ (see figure) of the sub-combat unit coincides with the main inertia axis, with the largest inertia moment on the X axis and the other main inertia axis on the Z and Y axes which make an angle of 90 with the X axis.
  • the X axis makes an angle of 30 with the line of symmetry of the warhead.
  • the rotation vector of the sub-combat unit must coincide with the X axis.
  • the aerodynamic damping must be sufficiently great such that both directions are caused to coincide before the beginning of the scanning phase, i.e. any possible oscillations in the sub-combat unit are damped out.
  • the aerodynamic carrier surfaces 1, 2 develop moments in suitable directions in order, together with gyration forces of the rotating sub-combat unit, to modify the orientation to the prescribed state, i.e. that the orientation of the main inertia axis, the X axis, will be close to vertical.
  • the relationship between the main inertia moment must lie within the range of between 1.05 and 1.15, preferably about 1.1. If the main inertia moment is of such relationship, a sufficiently rapid modification will be obtained of the orientation of the sub-combat unit, at the same time as a sufficient damping of oscillations in the sub-combat unit will be obtained.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Radar Systems Or Details Thereof (AREA)

Claims (1)

  1. Gefechtsuntereinheit, die zur Abtrennung von einem fliegenden Körper, z.B. einem Trägergeschoß od. dgl., über einem Zielgebiet vorgesehen ist, wobei die Gefechtsuntereinheit einen Gefechtskopf (4), einen Zieldetektor (5) und zwei diametral angeordnete Trägerflächen (1, 2) aufweist, die der Gefechtsuntereinheit eine Rotation zum Abtasten des Zielgebietes in einem Spiralmuster während des Falls der Gefechtsuntereinheit zum Zielgebiet verleihen, wobei beide Trägerflächen (1, 2) aus einer eingeklappten Position in eine geöffnete Position ausklappbar sind, in der beide Trägerflächen eine Verzögerungsfläche für die Fallgeschwindigkeit der Gefechtsuntereinheit bilden,
    dadurch gekennzeichnet, daß die Masse der Gefechtsuntereinheit so verteilt ist, daß das Verhältnis zwischen dem größten Hauptträgheitsmoment und den anderen Hauptträgheitsmomenten der Gefechtsuntereinheit im Bereich zwischen 1,05 und 1,15 liegt.
EP92850217A 1991-04-08 1992-09-14 Submunition Expired - Lifetime EP0587969B1 (de)

Priority Applications (5)

Application Number Priority Date Filing Date Title
SE9101037A SE468261B (sv) 1991-04-08 1991-04-08 Substridsdel anordnad att avskiljas fraan en flygkropp
EP92850217A EP0587969B1 (de) 1992-09-14 1992-09-14 Submunition
DE69219468T DE69219468T2 (de) 1992-09-14 1992-09-14 Submunition
AT92850217T ATE152511T1 (de) 1992-09-14 1992-09-14 Submunition
US07/957,488 US5280752A (en) 1991-04-08 1992-10-07 Sub-combat unit

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP92850217A EP0587969B1 (de) 1992-09-14 1992-09-14 Submunition
US07/957,488 US5280752A (en) 1991-04-08 1992-10-07 Sub-combat unit

Publications (2)

Publication Number Publication Date
EP0587969A1 EP0587969A1 (de) 1994-03-23
EP0587969B1 true EP0587969B1 (de) 1997-05-02

Family

ID=26132595

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92850217A Expired - Lifetime EP0587969B1 (de) 1991-04-08 1992-09-14 Submunition

Country Status (1)

Country Link
EP (1) EP0587969B1 (de)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE452505B (sv) * 1986-03-27 1987-11-30 Bofors Ab Substridsdel med svengbart anordnad maldetektor
USH685H (en) * 1988-06-20 1989-10-03 The United States Of America As Represented By The Secretary Of The Army Deployable fin configuration for free flight control of cylindrical bodies
SE464834B (sv) * 1989-10-20 1991-06-17 Bofors Ab Substridsdel med svaengbara baerytor
SE465440B (sv) * 1990-04-04 1991-09-09 Bofors Ab Substridsdel

Also Published As

Publication number Publication date
EP0587969A1 (de) 1994-03-23

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