EP1533589A1 - Système de contrôle utilisant un jet transversal - Google Patents

Système de contrôle utilisant un jet transversal Download PDF

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Publication number
EP1533589A1
EP1533589A1 EP04023729A EP04023729A EP1533589A1 EP 1533589 A1 EP1533589 A1 EP 1533589A1 EP 04023729 A EP04023729 A EP 04023729A EP 04023729 A EP04023729 A EP 04023729A EP 1533589 A1 EP1533589 A1 EP 1533589A1
Authority
EP
European Patent Office
Prior art keywords
contact element
conductor
control block
control device
ignition
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
EP04023729A
Other languages
German (de)
English (en)
Other versions
EP1533589B1 (fr
Inventor
Thomas Heitmann
Michael Schwenzer
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 Waffe Munition GmbH
Original Assignee
Rheinmetall Waffe Munition 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 Waffe Munition GmbH filed Critical Rheinmetall Waffe Munition GmbH
Publication of EP1533589A1 publication Critical patent/EP1533589A1/fr
Application granted granted Critical
Publication of EP1533589B1 publication Critical patent/EP1533589B1/fr
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
    • F42B10/60—Steering arrangements
    • F42B10/66—Steering by varying intensity or direction of thrust
    • 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

Definitions

  • the invention relates to a transverse thrust control device for influencing the trajectory of a missile taking a multiple shots for corresponding correction engines comprising control block, wherein in each of the recordings an ignition element for the corresponding correction engine is arranged, and wherein each of the ignition elements Has at least one contact element, which via an electrical line with a electronic control unit is connectable.
  • Such lateral thrust control devices for correcting the trajectory e.g. ballistic Projectiles or rockets
  • the contact elements of the ignition initially connected to cables. Subsequently The cables are then passed through usually radial bores of the Threaded control block in a central, axially extending recess of the control block and the ignition elements screwed into the control block.
  • a disadvantage of the known shear thrust control devices therefore, inter alia, the very time-consuming assembly of the ignition elements and their electrical connection with the electronic control unit.
  • the lateral thrust control device a includes a large number of correction engines (in some cases, up to 180 correction engines Act) is due to the very limited space inside the control block takes an extremely long time for the assembly. Besides, it can by twisting the individual cables when screwing the ignition easily to cancel the cables e.g. in the area of the contacts of the respective ignition element come.
  • control of the electrical connection is often the case Connecting the cables to the electronic control unit difficult because after screwing the ignition elements whose contact elements are no longer accessible.
  • the invention is based on the object, a transverse thrust control device of the beginning to be disclosed, in which the electrical lines between the ignition elements and the electronic control unit are easy to install safely.
  • the invention is based essentially on the idea that with the ignition elements connected electrical cables by conductor tracks, which on tubular, in the recess of the control block rotatably and 29iebeêt arranged line carrier are fixed, and which only when screwing or plugging the ignition contacted in the recordings of the control block of the contact elements become.
  • the interconnects can be applied in a conventional manner on the Kaussträgem (e.g., by electroplating or adhering conductive sheeting).
  • the lateral thrust control device On ignition which provided for safety reasons with two contact elements are and therefore also on two tracks with the electronic control unit are connected.
  • two telescoping and in their end position against rotation and displaceable fixable cable carrier provided on which each one of the two tracks is fixedly arranged such that e.g. when screwing a Anzündiatas a contact element, the conductor track on the Anzündelement contacted adjacent first line carrier and the other Contact element is passed through the first conductor carrier and the corresponding Conductor contacted on the second conductor carrier.
  • the transverse thrust control device Ignition elements comprises, each having a first rod-shaped contact element and a second, cylindrically shaped contact element, which surrounds the rod-shaped contact element, but has a shorter length than the latter.
  • the respectively arranged on the first conductor carrier each first conductor track from a portion of the cylindrical contact element of the corresponding ignition element contacted.
  • the respective first conductor track in the area, in the rod-shaped contact element is passed through the first conductor carrier, a ring-shaped, the rod-shaped contact element not contacting the conductor region on.
  • the tubular Nahssträgem can be plastic moldings, which at one end each with an outside of the recording of the control block arranged, tab-shaped head part are provided, which are perpendicular to Longitudinal axis of the control device extends and at the e.g. the connections of the tracks are arranged for connection to the electronic control unit.
  • This head part of the cable carrier for non-rotatable and secure displacement of the cable carrier be used.
  • the respective tab-shaped head part at least one bore through which a pin or screw-shaped fixing element is passed, which with the conductor carrier facing end wall of the Control block is positively connected.
  • a transverse thrust control device is denoted by 1, which, for example, in FIG an unillustrated ballistic projectile can be used, in which case then the central longitudinal axis 2 of the control device 1 with the longitudinal axis of the corresponding Projectile coincide.
  • the lateral thrust control device 1 comprises a control block 3 made of metal, in FIG the plurality distributed over the circumference arranged correction engines 4 in corresponding Shooting 5 are arranged.
  • the receptacles 5 each have a longitudinal axis 6, which are opposite to a radial, the longitudinal axis 2 of the control block 3 intersecting Level is arranged slightly inclined.
  • the in the known correction engines 4 essentially include one in the respective 5 recordable ignition element 7, a propellant 8 and a nozzle. 9
  • the respective ignition element 7 has two in the illustrated embodiment Contact elements 10 and 11 ( Figure 2).
  • the first contact element 10 is rod-shaped and the second contact element 11 is cylindrical and surrounds the first contact element 10.
  • the first contact element 10 also has a greater length than the second contact element 11.
  • the control block 3 has a central axially extending recess 12 which is cylindrical or may be conical and in which the contact elements 10, 11 of the respective Anzündiatas 7 edge protrude slightly.
  • the recess 12 are three nested, tubular, the longitudinal axis of the control block 3 enclosing Molded parts 13-15 ( Figure 2), which are arranged on the control block 3 against rotation and against displacement are.
  • a molding 13 made of an electrically insulating material, e.g. Plastic, on.
  • the other two are tubular Conduit formed mold parts 14 and 15.
  • Each of these two line carriers 14, 15th consists of a molded part made of an electrically insulating material (for example plastic) and has on the outside conductor tracks 17, 18, each of one of the two contact elements 10, 11 of a Anzündiatas 7 are contacted.
  • the three mold parts 13-15 For positioning the three mold parts 13-15 in the circumferential direction, they each have one end thereof disposed outside the recess 12 of the control block 3 strap-shaped head part 20, which is perpendicular to the longitudinal axis 2 of the control device 1 extends.
  • the respective head part 20 is supported on an end face 21 of the control block 3 and has a bore through which as the positioning element of Shaft of a screw 22 is passed.
  • the screw 22 therefore causes additional for positioning the mold parts 13-15 in the circumferential direction and a fixation in the axial direction Direction.
  • one of the two conductor carriers can be dispensed with are when the ignition elements each only one outwardly guided contact element (The second electrical connection can then be made via ground).
  • control block is made of an electrically insulating material (e.g., fiberglass reinforced Plastic), also the first molded body can be omitted, as an insulation between the first trace and the inner surface of the control block is not required is.
  • electrically insulating material e.g., fiberglass reinforced Plastic
  • the Multilayer construction preferably initially made on a flat flexible circuit board and then transferred to a tube.
  • the multilayer board to a Support tube laid around and optionally also fixed to this.
  • the longitudinal axes 6 of the receptacles 5 for the correction engines 4 need not may be formed inclined, but the longitudinal axis 2 of the control block 3 also below cut a right angle.
  • the ignition elements of the control block can instead of the introduction of boreholes in the individual moldings and the control block, through which subsequently a screw or a pen is guided, e.g. also provided a milled into all parts with a feather key become.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Air Bags (AREA)
  • Plasma Technology (AREA)
  • Installation Of Indoor Wiring (AREA)
  • Vehicle Body Suspensions (AREA)
  • Transmission Devices (AREA)
  • Elimination Of Static Electricity (AREA)
EP04023729A 2003-11-19 2004-10-05 Système de contrôle utilisant un jet transversal Expired - Lifetime EP1533589B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10354098A DE10354098A1 (de) 2003-11-19 2003-11-19 Querschub-Steuervorrichtung
DE10354098 2003-11-19

Publications (2)

Publication Number Publication Date
EP1533589A1 true EP1533589A1 (fr) 2005-05-25
EP1533589B1 EP1533589B1 (fr) 2007-09-19

Family

ID=34428805

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04023729A Expired - Lifetime EP1533589B1 (fr) 2003-11-19 2004-10-05 Système de contrôle utilisant un jet transversal

Country Status (5)

Country Link
US (1) US7118065B1 (fr)
EP (1) EP1533589B1 (fr)
AT (1) ATE373808T1 (fr)
DE (2) DE10354098A1 (fr)
ES (1) ES2290601T3 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7416154B2 (en) * 2005-09-16 2008-08-26 The United States Of America As Represented By The Secretary Of The Army Trajectory correction kit
US7875838B1 (en) * 2007-04-04 2011-01-25 The United States Of America As Represented By The Secretary Of The Navy Post boost control power assembly
US8362408B2 (en) * 2009-10-22 2013-01-29 Honeywell International Inc. Steerable projectile charging system
US20140137539A1 (en) * 2012-11-19 2014-05-22 Raytheon Company Thrust-producing device with detonation motor
US9068808B2 (en) * 2013-01-17 2015-06-30 Raytheon Company Air vehicle with bilateral steering thrusters
US10914559B1 (en) * 2016-11-21 2021-02-09 Lockheed Martin Corporation Missile, slot thrust attitude controller system, and method

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0485897A1 (fr) * 1990-11-14 1992-05-20 DIEHL GMBH & CO. Projectile à correction de trajectoire
US5433399A (en) * 1994-03-10 1995-07-18 Rheinmetall Gmbh Device for guiding a missile
US6367735B1 (en) * 2000-02-10 2002-04-09 Quantic Industries, Inc. Projectile diverter

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3034434A (en) * 1960-03-08 1962-05-15 Frank H Swaim Thrust vector control system
US3868883A (en) * 1964-02-20 1975-03-04 Mc Donnell Douglas Corp Guidance system
US3860199A (en) * 1972-01-03 1975-01-14 Ship Systems Inc Laser-guided projectile system
DE4410326C2 (de) * 1994-03-25 1998-07-02 Rheinmetall Ind Ag Geschoß mit einer Vorrichtung zur Flugbahnkorrektur
DE10141169A1 (de) * 2001-08-22 2003-03-13 Diehl Munitionssysteme Gmbh Artillerierakete

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0485897A1 (fr) * 1990-11-14 1992-05-20 DIEHL GMBH & CO. Projectile à correction de trajectoire
US5433399A (en) * 1994-03-10 1995-07-18 Rheinmetall Gmbh Device for guiding a missile
US6367735B1 (en) * 2000-02-10 2002-04-09 Quantic Industries, Inc. Projectile diverter

Also Published As

Publication number Publication date
ATE373808T1 (de) 2007-10-15
DE10354098A1 (de) 2005-06-23
US7118065B1 (en) 2006-10-10
ES2290601T3 (es) 2008-02-16
DE502004005009D1 (de) 2007-10-31
EP1533589B1 (fr) 2007-09-19

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