EP0834717A2 - Dispositif de manoeuvre pour changer la position des ailettes de guidage d'un missile guidé - Google Patents

Dispositif de manoeuvre pour changer la position des ailettes de guidage d'un missile guidé Download PDF

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Publication number
EP0834717A2
EP0834717A2 EP97116925A EP97116925A EP0834717A2 EP 0834717 A2 EP0834717 A2 EP 0834717A2 EP 97116925 A EP97116925 A EP 97116925A EP 97116925 A EP97116925 A EP 97116925A EP 0834717 A2 EP0834717 A2 EP 0834717A2
Authority
EP
European Patent Office
Prior art keywords
rudder
control system
missile
drive wheels
sprockets
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
EP97116925A
Other languages
German (de)
English (en)
Other versions
EP0834717A3 (fr
EP0834717B1 (fr
Inventor
Hans-Günter Ing. Ullrich
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.)
LFK Lenkflugkoerpersysteme GmbH
Original Assignee
LFK Lenkflugkoerpersysteme GmbH
Daimler Benz Aerospace AG
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 LFK Lenkflugkoerpersysteme GmbH, Daimler Benz Aerospace AG filed Critical LFK Lenkflugkoerpersysteme GmbH
Publication of EP0834717A2 publication Critical patent/EP0834717A2/fr
Publication of EP0834717A3 publication Critical patent/EP0834717A3/fr
Application granted granted Critical
Publication of EP0834717B1 publication Critical patent/EP0834717B1/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
    • F42B10/62—Steering by movement of flight surfaces
    • F42B10/64—Steering by movement of flight surfaces of fins

Definitions

  • the invention relates to a rudder control system for a guided missile the preamble of claim 1.
  • Such a rudder control system is known from DE 38 27 590 C2.
  • the sprockets are mounted in a rotor ring that is relative to the missile is constantly rotating around the longitudinal axis of the missile.
  • the rotatable rotor ring lies between in the front part of the missile the missile tip and the engine part.
  • the arrangement is also for flight stability the rudder in the front area of the missile is inappropriate.
  • the invention has for its object a rudder control system of the beginning mentioned type so that it fits into the available space can be integrated at the rear of the missile.
  • Fig. 1 shows a guided missile 1, which in its tail structure instead of one Fuselage constriction has a rudder control system 2. It essentially exists of four rudder blades 3 offset by 90 °, which are driven by electric motors 4 and 5, Zannkränze 7 and 8 and four drive wheels 11 can be operated. There are also two air inlets 12 and flow flaps 13 evident.
  • Fig. 2 shows schematically in an exploded view the rudder control system 2 for a rudder 3.
  • the sprockets 7 and 8 running on needle bearings are through Pinion 15 and 16 driven in the same direction of rotation.
  • Each ring gear 7 and 8 is assigned a drive wheel 17 and 11, so that the ring gear 7 with the drive wheel 17 and the ring gear 8 cooperate with the drive wheel 11.
  • the drive wheels 17 and 11 run in opposite directions Circulation directions on a rudder axis 18 freely movable.
  • the rudder axis 18 with tongue and groove 21 is connected and optionally with the drive wheels 11 and 17 non-positively can be connected, whereby the rudder 3 in the desired direction deflects.
  • the drive wheels 11 and 17 can be uncoupled and the rudder axis 18 can be held in the existing position by a brake 22.
  • fine control can be carried out in a known manner e.g. through a change the outer geometry of the rudder 3.
  • One on the rudder axis 18 attached increment encoder 23 shows the respective position of the rudder 3 with respect to its zero position defined when the missile 1 departed also serves as a signal generator for a steering control loop.
  • the zero position of the rudder 3 is realized by a bolt 24, which at the launch of the missile 1 e.g. is cut by fuse wire. Changes in diameter and shape of the engine tube due to thermal influences are by rings 25 added between the missile tube and the needle bearings of the Sprockets 7 and 8 are arranged.
  • the rudder control system 2 is with an aerodynamically favorable fairing 26 protected.
  • FIG. 3 In the longitudinal section of FIG. 3, two of the four rudder control systems 2 are shown. From this figure, almost all of which have already been described with reference to FIG. 2 Individual parts shows, the operation of the rudder control systems 2 is particularly good to understand. It can be clearly seen that the drive wheels 11 and 17 at parallel sprockets 7 and 8 have opposite directions of rotation, whereby the rudder 3 when coupled with the clutch disks 19 adjust in the opposite direction.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Retarders (AREA)
  • Toys (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
EP97116925A 1996-10-01 1997-09-30 Dispositif de manoeuvre pour changer la position des ailettes de guidage d'un missile guidé Expired - Lifetime EP0834717B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19640540A DE19640540C1 (de) 1996-10-01 1996-10-01 Ruderstellsystem für einen Lenkflugkörper
DE19640540 1996-10-01

Publications (3)

Publication Number Publication Date
EP0834717A2 true EP0834717A2 (fr) 1998-04-08
EP0834717A3 EP0834717A3 (fr) 1999-05-06
EP0834717B1 EP0834717B1 (fr) 2000-12-13

Family

ID=7807603

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97116925A Expired - Lifetime EP0834717B1 (fr) 1996-10-01 1997-09-30 Dispositif de manoeuvre pour changer la position des ailettes de guidage d'un missile guidé

Country Status (3)

Country Link
US (1) US5975461A (fr)
EP (1) EP0834717B1 (fr)
DE (2) DE19640540C1 (fr)

Families Citing this family (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6073880A (en) * 1998-05-18 2000-06-13 Versatron, Inc. Integrated missile fin deployment system
AUPR303501A0 (en) 2001-02-09 2001-03-08 Kusic, Tom Spiralling missile
US6502785B1 (en) 1999-11-17 2003-01-07 Lockheed Martin Corporation Three axis flap control system
US6708923B2 (en) 2000-06-26 2004-03-23 Tom Kusic Aircraft spiralling mechanism
GB2374055B (en) * 2000-10-07 2004-08-04 Bayern Chemie Gmbh Flugchemie A rudder blade guidance arrangement for missiles
SE521445C2 (sv) * 2001-03-20 2003-11-04 Bofors Defence Ab Sätt att synkronisera fenutfällningen vid en fenstabiliserad artillerigranat samt en i enlighet därmed utformad artillerigranat
ITMI20010648A1 (it) * 2001-03-27 2002-09-27 Finmeccanica S P A Alenia Dife Gruppo di controllo per alette direzionali di missili e/o proiettili
AUPR583001A0 (en) 2001-06-20 2001-07-12 Kusic, Tom Aircraft spiralling mechanism
US7635104B1 (en) 2001-06-22 2009-12-22 Tom Kusic Aircraft spiraling mechanism with jet assistance—B
US7093791B2 (en) * 2001-06-22 2006-08-22 Tom Kusic Aircraft spiralling mechanism—c
US7637453B2 (en) * 2001-06-22 2009-12-29 Tom Kusic Aircraft spiraling mechanism with jet assistance - A
US7165742B2 (en) * 2001-06-22 2007-01-23 Tom Kusic Aircraft spiralling mechanism - B
US6637699B2 (en) 2002-03-25 2003-10-28 Lockheed Martin Corporation Method and apparatus for controlling a trajectory of a projectile
KR100470820B1 (ko) * 2002-04-19 2005-02-21 한국항공우주연구원 로켓 발사대
DE102004061977B4 (de) * 2004-12-23 2008-04-10 Lfk-Lenkflugkörpersysteme Gmbh Klein-Flugkörper
FR2895496B1 (fr) * 2005-12-26 2008-03-28 Giat Ind Sa Dispositif de mesure de la position angulaire d'une ailette ou gouverne d'un projectile et procede de montage d'un tel dispositif
US7642491B2 (en) * 2007-03-19 2010-01-05 Tom Kusic Aircraft spiraling mechanism with jet assistance—D
US7791007B2 (en) * 2007-06-21 2010-09-07 Woodward Hrt, Inc. Techniques for providing surface control to a guidable projectile
US8530809B2 (en) * 2011-08-03 2013-09-10 Raytheon Company Ring gear control actuation system for air-breathing rocket motors
US8921749B1 (en) * 2013-07-10 2014-12-30 The United States Of America As Represented By The Secretary Of The Navy Perpendicular drive mechanism for a missile control actuation system
US11300390B1 (en) 2018-03-05 2022-04-12 Dynamic Structures And Materials, Llc Control surface deployment apparatus and method of use
KR101892900B1 (ko) * 2018-04-26 2018-08-28 국방과학연구소 유도탄 조종날개의 위치정확도 측정장치 및 측정방법
DE102018133113A1 (de) * 2018-12-20 2020-06-25 Rheinmetall Air Defence Ag Lenkflugkörper mit mehreren mittels einer Antriebsanordnung drehbaren Flügeln mit mindestens einem Aktuator und mindestens einem Planetengetriebe

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3827590A1 (de) 1988-08-13 1990-02-22 Messerschmitt Boelkow Blohm Flugkoerper

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE6606456U (de) * 1963-06-14 1970-09-24 Telefunken Patent Vorrichtung zur verstellung des steuerorgans eines lenkflugkoerpers
US4438893A (en) * 1973-08-10 1984-03-27 Sanders Associates, Inc. Prime power source and control for a guided projectile
US4029270A (en) * 1975-08-11 1977-06-14 General Dynamics Corporation Mechanical roll rate stabilizer for a rolling missile
US4274610A (en) * 1978-07-14 1981-06-23 General Dynamics, Pomona Division Jet tab control mechanism for thrust vector control
JPH01300199A (ja) * 1988-05-27 1989-12-04 Mitsubishi Electric Corp 後翼操舵誘導飛しよう体
US5806791A (en) * 1995-05-26 1998-09-15 Raytheon Company Missile jet vane control system and method
US5829715A (en) * 1996-04-19 1998-11-03 Lockheed Martin Vought Systems Corp. Multi-axis unfolding mechanism with rate controlled synchronized movement
US5662290A (en) * 1996-07-15 1997-09-02 Versatron Corporation Mechanism for thrust vector control using multiple nozzles

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3827590A1 (de) 1988-08-13 1990-02-22 Messerschmitt Boelkow Blohm Flugkoerper

Also Published As

Publication number Publication date
DE19640540C1 (de) 1998-04-02
EP0834717A3 (fr) 1999-05-06
DE59702755D1 (de) 2001-01-18
EP0834717B1 (fr) 2000-12-13
US5975461A (en) 1999-11-02

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