US3918664A - Launchable missile having a tail unit - Google Patents

Launchable missile having a tail unit Download PDF

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Publication number
US3918664A
US3918664A US492875A US49287574A US3918664A US 3918664 A US3918664 A US 3918664A US 492875 A US492875 A US 492875A US 49287574 A US49287574 A US 49287574A US 3918664 A US3918664 A US 3918664A
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US
United States
Prior art keywords
missile
guidewings
torsion spring
arm
torsion
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
US492875A
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English (en)
Inventor
Werner Grosswendt
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
Application granted granted Critical
Publication of US3918664A publication Critical patent/US3918664A/en
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
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel

Definitions

  • Missiles of known types use either guidewings which are not locked in the unfolded position and are therefore easily manufacturableas, for example, described in DT-OS 2 .059.951, or else have a tail unit constructed with complicated opening and locking systems of a type actuated by spring or gas pressure and using additional locking sliders, members or the like, and which are therefore costly to manufacture.
  • a launchable missile having a tail unit including at least two guidewings symmetrically disposed with respect to the longitudinal axis of the missile and unfoldable upon launching, the rear part of the missile being provided with a pivot axle in the form of a bolt.
  • the guidewings are pivotable around that pivot axle, brought into an unfolded position and locked therein by means of a torsion spring wound around a torsion-spring axle formed with a coil and two bent arms, one arm abutting the body of the missile, the other arm abutting the guidewings.
  • Each of the latter has a guidewing edge formed with a recess, one arm being locked into the recess upon unfolding of the guidewings.
  • two parallel crosspieces formed with a groove extend from the rear part of the missile, one arm of the torsion spring resting in that groove.
  • FIG. 1 shows a fragmentary side-elevational view of the rear part of the missile with one guidewing in a folded position
  • FIG. 2 shows a fragmentary cross-sectional in side elevation of the rear part of the missile with one guidewing in an unfolded position
  • FIG. 3 shows a fragmentary elevational rear-view of part of the tail unit of the missile with the guidewings in an unfolded position.
  • the missile which may be a self-propelled rocket or a wingstabilized missile, consists of a missile body 2 having a missile rear-portion 2a, to which there are attached crosspieces 2b, on which guidewing 4 of a tail unit only shown partially in FIG. 3 are pivotable around a bolt 6.
  • Guidewings 4 are unfolded by means of double-armed torsion springs 8; one arm 8a of the latter abuts in its folded position against a guidewing edge 4, while the other arm 8b abuts against crosspieces 2b of missile rear portion 2a.
  • Coils 8d of torsion springs 8 are wrapped around an axle 10 which is spaced apart from bolt 6, the latter forming a pivotable axis for guidewings 4.
  • ends 8e of arms 8b are bent to fit into a groove 20 formed between crosspieces 2b.
  • the unfolding and locking system described according to my invention permits a particularly simple form of construction of either a rocket or wing-stabilized missile, and is equally applicable for guidewings unfoldable from front to rear or from rear to front, as well as for guidewings unfoldable in a raidal direction or within a plane, such as a plane tangential to the missile body.
  • a launchable missile having a longitudinal axis and a tail unit including at least two guidewings symmetrically disposed with respect to said longitudinal axis and unfoldable upon launching, said missile having a body and a rear part provided with a pivot axle including at least one double-armed torsion spring, said guidewings being pivotable around said pivot axle, guided into an unfolded position and locked therein by means of said torsion spring, one arm of said torsion spring abutting said body of saidmissile, the other arm of said torsion spring abutting said guidewings, comprising a torsionspring axle mounted on said missile and spaced from said pivot axle, and wherein said torsion spring is formed with a coil mounted on said torsion-spring axle and each of said guidewings has a guidewing edge formed with a recess, said other arm having a bent end locked in said recess when said guidewings are unfolded.
  • a missile as defined in claim 1 further comprising two parallel crosspieces extending from said rear part and formed with a groove, and wherein said pivot axle is a bolt and said arms of said torsion spring are disposed beyond said cross-pieces, said coil being wound around said torsion-spring axle, and wherein said one arm has a doubly bent end resting in said groove.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
US492875A 1973-08-24 1974-07-29 Launchable missile having a tail unit Expired - Lifetime US3918664A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2342783A DE2342783C2 (de) 1973-08-24 1973-08-24 Mit einem Leitwerk versehenes Geschoß

Publications (1)

Publication Number Publication Date
US3918664A true US3918664A (en) 1975-11-11

Family

ID=5890609

Family Applications (1)

Application Number Title Priority Date Filing Date
US492875A Expired - Lifetime US3918664A (en) 1973-08-24 1974-07-29 Launchable missile having a tail unit

Country Status (5)

Country Link
US (1) US3918664A (de)
DE (1) DE2342783C2 (de)
FR (1) FR2241761B3 (de)
GB (1) GB1431619A (de)
SE (1) SE7409982L (de)

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4203569A (en) * 1977-10-17 1980-05-20 Bei Electronics, Inc. Fin and nozzle unit for a free-flight rocket
US4384691A (en) * 1980-12-22 1983-05-24 The United States Of America As Represented By The Secretary Of The Army Rocket fin hold down spring
US4588146A (en) * 1984-03-29 1986-05-13 The United States Of America As Represented By The Secretary Of The Army Biaxial folding lever wing
US4709878A (en) * 1984-04-17 1987-12-01 British Aerospace Plc Fin assembly deployment spring
US4714216A (en) * 1985-03-23 1987-12-22 British Aerospace Public Limited Company Fin erecting mechanisms
US4869442A (en) * 1988-09-02 1989-09-26 Aerojet-General Corporation Self-deploying airfoil
EP0540484A1 (de) * 1991-09-18 1993-05-05 Bofors AB Subgefechtskopf
US5326049A (en) * 1992-04-30 1994-07-05 State Of Israel - Ministry Of Defense Rafael-Armament Development Authority Device including a body having folded appendage to be deployed upon acceleration
US5584448A (en) * 1993-12-02 1996-12-17 State Of Israel Ministry Of Defense, Rafael Armaments Development Authority Flight control device
US6559370B1 (en) * 2002-08-06 2003-05-06 The United States Of America As Represented By The Secretary Of The Navy Submarine countermeasure vehicle with folding propeller
US6578792B2 (en) * 2001-04-12 2003-06-17 Diehl Munitionssysteme Gmbh & Co. Kg Rudder blade mounting arrangement for a missile
US20090218437A1 (en) * 2007-12-17 2009-09-03 Raytheon Company Torsional spring aided control actuator for a rolling missile
US20110186678A1 (en) * 2008-02-07 2011-08-04 Sankovic John R Pyrotechnic fin deployment and retention mechanism
WO2011126970A2 (en) * 2010-04-07 2011-10-13 Bae Systems Information And Electronic Systems Integration Inc. Compression spring wing deployment initiator
WO2011127369A2 (en) * 2010-04-09 2011-10-13 Bae Systems Information And Electronic Systems Integration Inc. Torsion spring wing deployment initiator
US20160169642A1 (en) * 2014-12-11 2016-06-16 Mbda Deutschland Gmbh Rudder System
RU2601889C1 (ru) * 2015-09-11 2016-11-10 Акционерное общество "Конструкторское бюро приборостроения им. академика А.Г. Шипунова" Вращающийся стабилизатор управляемой ракеты
CN109895987A (zh) * 2017-12-11 2019-06-18 中国科学院沈阳自动化研究所 一种海洋机器人用舵折叠装置
WO2021101607A1 (en) * 2019-08-27 2021-05-27 Bae Systems Information And Electronic Systems Integration Inc. Wing deployment initiator and locking mechanism
WO2022055766A1 (en) * 2020-09-10 2022-03-17 Bae Systems Information And Electronic Systems Integration Inc. Additively manufactured elliptical bifurcating torsion spring

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3432614A1 (de) * 1984-09-05 1986-03-13 Rheinmetall GmbH, 4000 Düsseldorf Flugkoerper
DE3447852A1 (de) * 1984-12-31 1986-08-28 Heide, Marion, 4030 Ratingen Klappleitwerk fuer fluegelstabilisierte raketengeschosse
DE3660840D1 (en) * 1986-03-14 1988-11-03 British Aerospace Spring for self-erecting fins
US4809929A (en) * 1987-06-26 1989-03-07 Hughes Aircraft Company Splitter plates for alleviation of missile hook drag
DE4016840A1 (de) * 1990-05-25 1991-11-28 Diehl Gmbh & Co Von einem flugkoerper wegklappbarer fluegel
DE4119613C2 (de) * 1991-06-14 1997-03-27 Diehl Gmbh & Co Flugkörper mit ausklappbaren Leiteinrichtungen
FR2712679B1 (fr) * 1993-11-16 1996-02-09 Luchaire Defense Sa Dispositif de déploiement pour une ailette de stabilisation de projectile de type roquette.
DE19941555C5 (de) * 1999-09-01 2004-12-30 Rheinmetall W & M Gmbh Flugkörper
DE19941556C2 (de) * 1999-09-01 2001-07-12 Rheinmetall W & M Gmbh Flugkörper
DE19941557C5 (de) * 1999-09-01 2004-07-15 Rheinmetall W & M Gmbh Flugkörper
DE202005011174U1 (de) * 2005-07-15 2005-09-29 Glau, Felix Schussmunition
FR2949848B1 (fr) 2009-09-10 2012-09-28 Nexter Munitions Dispositif d'ouverture et verrouillage d'une ailette canard.
US8278612B2 (en) * 2010-07-27 2012-10-02 Raytheon Company Aerodynamic fin lock for adjustable and deployable fin

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1879840A (en) * 1930-05-22 1932-09-27 Brandt Edgar William Bladed projectile
US3031967A (en) * 1958-02-13 1962-05-01 Hotchkiss Brandt Fin arrangement for projectiles
US3690595A (en) * 1970-11-19 1972-09-12 Sarmac Sa Self-propelled, vaned missile

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH302186A (fr) * 1952-10-06 1954-10-15 Energa Projectile empenné.
DE1578222A1 (de) * 1966-02-04 1972-02-10 Ind & Mecaniques S T R I M Sich entfaltendes Leitwerk,insbesondere fuer Raketen Societe Technique de Recherches
BE759788A (fr) * 1969-12-05 1971-06-03 Sarmac Sa Projectile autopropulse empenne

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1879840A (en) * 1930-05-22 1932-09-27 Brandt Edgar William Bladed projectile
US3031967A (en) * 1958-02-13 1962-05-01 Hotchkiss Brandt Fin arrangement for projectiles
US3690595A (en) * 1970-11-19 1972-09-12 Sarmac Sa Self-propelled, vaned missile

Cited By (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4203569A (en) * 1977-10-17 1980-05-20 Bei Electronics, Inc. Fin and nozzle unit for a free-flight rocket
US4384691A (en) * 1980-12-22 1983-05-24 The United States Of America As Represented By The Secretary Of The Army Rocket fin hold down spring
US4588146A (en) * 1984-03-29 1986-05-13 The United States Of America As Represented By The Secretary Of The Army Biaxial folding lever wing
US4709878A (en) * 1984-04-17 1987-12-01 British Aerospace Plc Fin assembly deployment spring
US4714216A (en) * 1985-03-23 1987-12-22 British Aerospace Public Limited Company Fin erecting mechanisms
US4869442A (en) * 1988-09-02 1989-09-26 Aerojet-General Corporation Self-deploying airfoil
EP0540484A1 (de) * 1991-09-18 1993-05-05 Bofors AB Subgefechtskopf
US5326049A (en) * 1992-04-30 1994-07-05 State Of Israel - Ministry Of Defense Rafael-Armament Development Authority Device including a body having folded appendage to be deployed upon acceleration
US5584448A (en) * 1993-12-02 1996-12-17 State Of Israel Ministry Of Defense, Rafael Armaments Development Authority Flight control device
US6578792B2 (en) * 2001-04-12 2003-06-17 Diehl Munitionssysteme Gmbh & Co. Kg Rudder blade mounting arrangement for a missile
US6559370B1 (en) * 2002-08-06 2003-05-06 The United States Of America As Represented By The Secretary Of The Navy Submarine countermeasure vehicle with folding propeller
US20090218437A1 (en) * 2007-12-17 2009-09-03 Raytheon Company Torsional spring aided control actuator for a rolling missile
US7902489B2 (en) * 2007-12-17 2011-03-08 Raytheon Company Torsional spring aided control actuator for a rolling missile
US20110186678A1 (en) * 2008-02-07 2011-08-04 Sankovic John R Pyrotechnic fin deployment and retention mechanism
US8610042B2 (en) * 2008-02-07 2013-12-17 Simmonds Precision Products, Inc. Pyrotechnic fin deployment and retention mechanism
WO2011126970A2 (en) * 2010-04-07 2011-10-13 Bae Systems Information And Electronic Systems Integration Inc. Compression spring wing deployment initiator
US20120074256A1 (en) * 2010-04-07 2012-03-29 Amy Pietrzak Compression spring wing deployment initiator
WO2011126970A3 (en) * 2010-04-07 2012-04-19 Bae Systems Information And Electronic Systems Integration Inc. Compression spring wing deployment initiator
US8754352B2 (en) * 2010-04-07 2014-06-17 Bae Systems Information And Electronic Systems Integration Inc. Compression spring wing deployment initiator
WO2011127369A3 (en) * 2010-04-09 2012-02-23 Bae Systems Information And Electronic Systems Integration Inc. Torsion spring wing deployment initiator
WO2011127369A2 (en) * 2010-04-09 2011-10-13 Bae Systems Information And Electronic Systems Integration Inc. Torsion spring wing deployment initiator
US8686329B2 (en) 2010-04-09 2014-04-01 Bae Systems Information And Electronic Systems Integration Inc. Torsion spring wing deployment initiator
US20160169642A1 (en) * 2014-12-11 2016-06-16 Mbda Deutschland Gmbh Rudder System
US10006748B2 (en) * 2014-12-11 2018-06-26 Mbda Deutschland Gmbh Rudder system
RU2601889C1 (ru) * 2015-09-11 2016-11-10 Акционерное общество "Конструкторское бюро приборостроения им. академика А.Г. Шипунова" Вращающийся стабилизатор управляемой ракеты
CN109895987A (zh) * 2017-12-11 2019-06-18 中国科学院沈阳自动化研究所 一种海洋机器人用舵折叠装置
WO2021101607A1 (en) * 2019-08-27 2021-05-27 Bae Systems Information And Electronic Systems Integration Inc. Wing deployment initiator and locking mechanism
US11340052B2 (en) 2019-08-27 2022-05-24 Bae Systems Information And Electronic Systems Integration Inc. Wing deployment initiator and locking mechanism
WO2022055766A1 (en) * 2020-09-10 2022-03-17 Bae Systems Information And Electronic Systems Integration Inc. Additively manufactured elliptical bifurcating torsion spring
US11852211B2 (en) 2020-09-10 2023-12-26 Bae Systems Information And Electronic Systems Integration Inc. Additively manufactured elliptical bifurcating torsion spring

Also Published As

Publication number Publication date
FR2241761B3 (de) 1977-07-01
DE2342783C2 (de) 1983-12-22
FR2241761A1 (de) 1975-03-21
SE7409982L (de) 1975-02-25
DE2342783A1 (de) 1975-03-06
GB1431619A (en) 1976-04-14

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