EP0384965A2 - Sous-projectile avec ailettes stabilisatrices - Google Patents

Sous-projectile avec ailettes stabilisatrices Download PDF

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Publication number
EP0384965A2
EP0384965A2 EP19890120959 EP89120959A EP0384965A2 EP 0384965 A2 EP0384965 A2 EP 0384965A2 EP 19890120959 EP19890120959 EP 19890120959 EP 89120959 A EP89120959 A EP 89120959A EP 0384965 A2 EP0384965 A2 EP 0384965A2
Authority
EP
European Patent Office
Prior art keywords
submunition
microreaction
submunition body
stabilized
engines
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Withdrawn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
EP19890120959
Other languages
German (de)
English (en)
Other versions
EP0384965A3 (fr
Inventor
Gerhard Dr. Glotz
Werner Grosswendt
Helmut Dr. Peller
Jens Dr. Seidensticker
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 EP0384965A2 publication Critical patent/EP0384965A2/fr
Publication of EP0384965A3 publication Critical patent/EP0384965A3/fr
Withdrawn legal-status Critical Current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
    • 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
    • F42B10/60—Steering arrangements
    • F42B10/66—Steering by varying intensity or direction of thrust
    • F42B10/661—Steering by varying intensity or direction of thrust using several transversally acting rocket motors, each motor containing an individual propellant charge, e.g. solid charge
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/2233—Multimissile systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/2253—Passive homing systems, i.e. comprising a receiver and do not requiring an active illumination of the target
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/2273—Homing guidance systems characterised by the type of waves
    • F41G7/2293—Homing guidance systems characterised by the type of waves using electromagnetic waves other than radio waves
    • 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
    • F42B15/01—Arrangements thereon for guidance or control

Definitions

  • the invention relates to a wing-stabilized submunition body with the features of the preamble of claim 1.
  • a known submunition of this type is usually accommodated in an artillery projectile which is fired in a twist-stabilized manner in indirect aiming.
  • the submunition body is ejected from the carrier shell in a manner known per se, then braked and swirled.
  • the stabilizing wings are then unfolded and an energy supply for a target detection device is activated, ground targets are detected by a corresponding search head when the submunition body is falling steadily, and the submunition body is optionally aligned with the detected target.
  • movable components are required for target acquisition and alignment of the submunition, such as e.g. a gimbal-mounted seeker head, a conventional gyroscope and standard actuators or rudder elements.
  • these moveable components undesirably reduce the firing strength and thus the reliability of such submunitions, moreover they require a high level of construction complexity and lead to undesirable cost developments.
  • the invention is therefore based on the object, while avoiding as many movable components as possible, to create a submunition body which is simple and inexpensive structure, as well as being characterized by high launch resistance and reliability.
  • a preferred embodiment of a wing-stabilized submunition 10 is shown.
  • a plurality of tail unit wings 12 projecting radially from the submunition body 10 and pivoting out of it.
  • the submunition body 10 contains a rigid sensor 14 as a seeker head, preferably an infrared sensor or a focal plain array.
  • a three-axis laser gyroscope 16 which is arranged directly behind the rigid sensor 14 in the submunition body 10, serves as the reference platform.
  • microreaction engines 18 are provided on the circumferential side and parallel to a longitudinal axis (not specified in any more detail), which function as individually ignitable small, once-burning, thrust-generating rocket motors.
  • Radial bores in the submunition body 10, which are not described in detail, are provided as nozzles for generating thrust by the combustion products generated in the microreaction engines 18.
  • the microreaction engines 18 are preferably arranged in front of the center of gravity of the submunition 10 directly behind the rigid sensor 14 and the laser gyro 16, so that the thrusts turn on the wing-stabilized submunition 10 and thus, together with the buoyancy of the submunition 10 and the tail unit 12, generate a transverse acceleration necessary for alignment to a dedicated target.
  • the individual microreaction engines 18 can be designed to be very small, so that up to 100 or more microreaction engines 18 can be accommodated in a suitable submunition body 10, thus enabling quasi-continuous projectile control.
  • an electronic part 20 a battery 22 serving for electrical supply and a warhead 24 as well as an ignition and safety device 26 associated therewith are shown in the illustration in the case of the submunition body 10 according to the invention.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Electromagnetism (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Gyroscopes (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Preparation Of Compounds By Using Micro-Organisms (AREA)
  • Lasers (AREA)
EP19890120959 1989-03-01 1989-11-11 Sous-projectile avec ailettes stabilisatrices Withdrawn EP0384965A3 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3906372 1989-03-01
DE3906372A DE3906372A1 (de) 1989-03-01 1989-03-01 Fluegelstabilisierter submunitionskoerper

Publications (2)

Publication Number Publication Date
EP0384965A2 true EP0384965A2 (fr) 1990-09-05
EP0384965A3 EP0384965A3 (fr) 1992-08-12

Family

ID=6375175

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19890120959 Withdrawn EP0384965A3 (fr) 1989-03-01 1989-11-11 Sous-projectile avec ailettes stabilisatrices

Country Status (4)

Country Link
US (1) US5037040A (fr)
EP (1) EP0384965A3 (fr)
CA (1) CA2011046A1 (fr)
DE (1) DE3906372A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110077588A (zh) * 2019-04-22 2019-08-02 大连理工大学 一种可垂直起降的海陆空潜四栖航行器

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5261629A (en) * 1989-04-08 1993-11-16 Rheinmetall Gmbh Fin stabilized projectile
DE29512894U1 (de) * 1995-08-10 1995-10-26 Mafo Systemtechnik Dr.-Ing. A. Zacharias GmbH & Co. KG, 83317 Teisendorf Waffe
US6502785B1 (en) * 1999-11-17 2003-01-07 Lockheed Martin Corporation Three axis flap control system
US20070089628A1 (en) * 2005-10-20 2007-04-26 Elder Steven M Firearm ammunition having improved flight and impact characteristics
SE534614C2 (sv) * 2010-02-25 2011-10-25 Bae Systems Bofors Ab Granat anordnad med utfällbara vingar och styranordning
US9464876B2 (en) * 2014-05-30 2016-10-11 General Dynamics Ordnance and Tacital Systems, Inc. Trajectory modification of a spinning projectile by controlling the roll orientation of a decoupled portion of the projectile that has actuated aerodynamic surfaces

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3282540A (en) * 1964-05-05 1966-11-01 Henry S Lipinski Gun launched terminal guided projectile
EP0028966A1 (fr) * 1979-11-09 1981-05-20 Thomson-Brandt Armements Procédé de pilotage et de guidage de projectiles en phase terminale de vol
EP0081421A1 (fr) * 1981-12-09 1983-06-15 Thomson-Brandt Armements Méthode de guidage terminal et missile guidé opérant selon cette méthode
DE3337873A1 (de) * 1982-10-18 1984-04-19 Raytheon Co., 02173 Lexington, Mass. Geschoss fuer granatwerfersysteme
US4598884A (en) * 1984-11-28 1986-07-08 General Dynamics Pomona Division Infrared target sensor and system

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3304434A (en) * 1965-06-01 1967-02-14 Bunker Ramo Position control system employing pulse producing means indicative of magnitude and direction of movement
US4533094A (en) * 1982-10-18 1985-08-06 Raytheon Company Mortar system with improved round

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3282540A (en) * 1964-05-05 1966-11-01 Henry S Lipinski Gun launched terminal guided projectile
EP0028966A1 (fr) * 1979-11-09 1981-05-20 Thomson-Brandt Armements Procédé de pilotage et de guidage de projectiles en phase terminale de vol
EP0081421A1 (fr) * 1981-12-09 1983-06-15 Thomson-Brandt Armements Méthode de guidage terminal et missile guidé opérant selon cette méthode
DE3337873A1 (de) * 1982-10-18 1984-04-19 Raytheon Co., 02173 Lexington, Mass. Geschoss fuer granatwerfersysteme
US4598884A (en) * 1984-11-28 1986-07-08 General Dynamics Pomona Division Infrared target sensor and system

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110077588A (zh) * 2019-04-22 2019-08-02 大连理工大学 一种可垂直起降的海陆空潜四栖航行器
WO2020215304A1 (fr) * 2019-04-22 2020-10-29 大连理工大学 Véhicule adapté aux milieux sous-marin, marin, terrestre et aérien capable d'effectuer un décollage et un atterrissage verticaux
CN110077588B (zh) * 2019-04-22 2022-05-20 大连理工大学 一种可垂直起降的海陆空潜四栖航行器
US11433999B2 (en) 2019-04-22 2022-09-06 Dalian University Of Technology Vehicle capable of taking off and landing vertically and operating in water, land, air and submarine environments

Also Published As

Publication number Publication date
CA2011046A1 (fr) 1990-09-01
DE3906372C2 (fr) 1991-06-27
US5037040A (en) 1991-08-06
EP0384965A3 (fr) 1992-08-12
DE3906372A1 (de) 1990-09-13

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