EP1108972A2 - Dispositif pour le montage d'une ailette de guidage dans un missile - Google Patents

Dispositif pour le montage d'une ailette de guidage dans un missile Download PDF

Info

Publication number
EP1108972A2
EP1108972A2 EP00126530A EP00126530A EP1108972A2 EP 1108972 A2 EP1108972 A2 EP 1108972A2 EP 00126530 A EP00126530 A EP 00126530A EP 00126530 A EP00126530 A EP 00126530A EP 1108972 A2 EP1108972 A2 EP 1108972A2
Authority
EP
European Patent Office
Prior art keywords
rudder
missile
shaft
bearing
recess
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
EP00126530A
Other languages
German (de)
English (en)
Other versions
EP1108972B1 (fr
EP1108972A3 (fr
Inventor
Walter Hetzer
Ernst Lenz
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
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 filed Critical LFK Lenkflugkoerpersysteme GmbH
Publication of EP1108972A2 publication Critical patent/EP1108972A2/fr
Publication of EP1108972A3 publication Critical patent/EP1108972A3/fr
Application granted granted Critical
Publication of EP1108972B1 publication Critical patent/EP1108972B1/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 device for rudder connection for Guided missile, with the rudder blade in one on the missile cell attached interface fitting mounted on a rudder shaft and by means of a Rudder drive lever is pivotable.
  • the guided missiles are for medium Range mainly carried on the fuselage in a partially submerged arrangement, to reduce the air resistance and the radar signature cheaply influence.
  • the shape of the aircraft interface is due to the currently introduced air-to-air guided missile of the type AMRAAM and was also specified for example with the prototypes of the Eurofighter EF 2000 in this form realized.
  • For the rudders and wings of the AMRAAM are in the Airplane fuselage slot-shaped recesses with a width of 41 mm specified
  • Fig. 1 shows the environment for the subject of the invention.
  • the fuselage or the wings of the aircraft - is a recess with a fixed predetermined width of 41 mm available, which is for the inclusion of the Airplane-facing rudder blade R of a ready-to-use missile FK (AMRAAM) serves. With this space must be a compatible missile get along.
  • AMRAAM Airplane-facing rudder blade R of a ready-to-use missile FK
  • Fig. 2 shows the construction principle of the AMRAAM-compatible Rudder support for a ramjet-powered missile after Invention.
  • 2a shows the proposed solution with a view to the Rudder axis W in the direction of the missile FK.
  • 2b shows a section through the arrangement and the bending load curve BL through the Main elements interface fitting B and rudder shaft W.
  • the interface fitting B for fastening to the thin-walled Dust separation chamber of the FK missile cell has an outer diameter B2 which on the one hand ensures compatibility and freedom of movement and on the other hand through the conical recess B3 in the cross-sectional profile to the bending stress that occurs due to the one acting on the rudder Air force Fq is caused is adjusted.
  • the Rudder shaft W in ceramic needle bearings L.
  • the cross-sectional profile of the rudder shaft W is due to the choice of the bearing diameter d1 (22 mm) and d2 (12 mm) also the load curve on the Rudder shaft W adapted.
  • the rudder shaft W takes a slot-like shape Recess W4 the rudder R, which is the cylindrical part of the Interface fitting B2 encloses to the root as shown in Fig. 2c.
  • the rudder drive lever H is form-fitting on the inside of the fitting the rudder shaft W connected.
  • the rudder drive lever H is, as in the initially mentioned document explained by an electromechanical Actuating system actuated.
  • the formation of the rudder interface W4 i.e. the connection between the rudder R and rudder shaft W, enables easy manufacture and quick
  • the rudder blade can be fitted using standard tools Battle conditions.
  • the rudder interface is also close to the pressure point of the rudder blade, therefore there are small root bending moments at the clamping point Furthermore, the sealing of the missile to the outside in the area of Missile interface fitting B and the rudder drive lever H simple and done perfectly, since the position of the relative movement at the outer end of the Interface fitting is.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Sliding-Contact Bearings (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP00126530A 1999-12-16 2000-12-11 Dispositif pour le montage d'une ailette de guidage dans un missile Expired - Lifetime EP1108972B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19960738A DE19960738C1 (de) 1999-12-16 1999-12-16 Ruderanbindung für Lenkflugkörper
DE19960738 1999-12-16

Publications (3)

Publication Number Publication Date
EP1108972A2 true EP1108972A2 (fr) 2001-06-20
EP1108972A3 EP1108972A3 (fr) 2003-11-19
EP1108972B1 EP1108972B1 (fr) 2007-03-21

Family

ID=7932920

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00126530A Expired - Lifetime EP1108972B1 (fr) 1999-12-16 2000-12-11 Dispositif pour le montage d'une ailette de guidage dans un missile

Country Status (5)

Country Link
US (1) US6398156B2 (fr)
EP (1) EP1108972B1 (fr)
JP (1) JP4560206B2 (fr)
DE (2) DE19960738C1 (fr)
ES (1) ES2280172T3 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016022183A1 (fr) * 2014-08-05 2016-02-11 Raytheon Company Véhicule aérien ayant un coupleur mécanique de système de commande
CN115031587A (zh) * 2022-05-30 2022-09-09 洛阳安怀达智能科技有限公司 一种飞行器舵面锁止机构

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10118216A1 (de) * 2001-04-12 2002-10-17 Diehl Munitionssysteme Gmbh Ruderblatt-Lagereinrichtung für ein Geschoß
US6474594B1 (en) * 2001-05-11 2002-11-05 Raytheon Company Output shaft assembly for a missile control actuation unit
PL3708482T3 (pl) * 2019-03-13 2023-09-11 Becker Marine Systems Gmbh Ster do jednostek pływających z przyrządem do pomiaru luzu łożyskowego, sposób pomiaru luzu łożyskowego w sterze oraz przyrząd do pomiaru luzu łożyskowego steru
CN113154955B (zh) * 2020-12-28 2022-12-27 航天科工火箭技术有限公司 一种自旋稳定的火箭分离体残骸落区精准控制系统及方法

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19635847C2 (de) 1996-09-04 1998-07-16 Daimler Benz Aerospace Ag Lenkflugkörper mit Staustrahlantrieb

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3223034A (en) * 1964-05-06 1965-12-14 Atlantic Res Corp Rocket fin assembly
SE331242B (fr) * 1969-05-14 1970-12-14 Bofors Ab
DE2227104C2 (de) * 1972-06-03 1982-07-15 Dynamit Nobel Ag, 5210 Troisdorf Geschoß oder Rakete mit aufklappbarem Leitwerk
DE2227103A1 (de) * 1972-06-03 1973-12-13 Dynamit Nobel Ag Klappleitwerk
US4327886A (en) * 1972-11-30 1982-05-04 The United States Of America As Represented By The Secretary Of The Navy Integral rocket ramjet missile
DE2264338A1 (de) * 1972-12-30 1974-07-04 Dynamit Nobel Ag Ausklappbares leitwerk, insbesondere fuer raketen
US4568041A (en) * 1984-03-19 1986-02-04 The United States Of America As Represented By The Secretary Of The Navy Fin attachment
DE3441534A1 (de) * 1984-11-14 1986-05-15 Diehl GmbH & Co, 8500 Nürnberg Lageranordnung fuer das ruderblatt eines flugkoerpers
JPH0424499A (ja) * 1990-05-17 1992-01-28 Mitsubishi Heavy Ind Ltd 飛昇体
DE4135557C2 (de) * 1991-10-29 1999-05-06 Diehl Stiftung & Co Ruderstelleinrichtung
JPH08210799A (ja) * 1995-02-02 1996-08-20 Mitsubishi Heavy Ind Ltd 飛しょう体等の方向・姿勢制御装置
DE19827277B4 (de) * 1998-06-19 2006-08-10 Diehl Stiftung & Co.Kg Lageranordnung für die aufschwenkbaren Ruderblätter eines lenkbaren Flugkörpers
DE19827278A1 (de) * 1998-06-19 1999-12-23 Diehl Stiftung & Co Lenkbarer Flugkörper

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19635847C2 (de) 1996-09-04 1998-07-16 Daimler Benz Aerospace Ag Lenkflugkörper mit Staustrahlantrieb

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016022183A1 (fr) * 2014-08-05 2016-02-11 Raytheon Company Véhicule aérien ayant un coupleur mécanique de système de commande
US9546853B2 (en) 2014-08-05 2017-01-17 Raytheon Company Air vehicle with control system mechanical coupler
CN115031587A (zh) * 2022-05-30 2022-09-09 洛阳安怀达智能科技有限公司 一种飞行器舵面锁止机构

Also Published As

Publication number Publication date
DE50014181D1 (de) 2007-05-03
JP4560206B2 (ja) 2010-10-13
US20010030259A1 (en) 2001-10-18
ES2280172T3 (es) 2007-09-16
EP1108972B1 (fr) 2007-03-21
JP2001174197A (ja) 2001-06-29
DE19960738C1 (de) 2001-08-23
US6398156B2 (en) 2002-06-04
EP1108972A3 (fr) 2003-11-19

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