US3861627A - Foldable control flap unit, especially for rockets - Google Patents

Foldable control flap unit, especially for rockets Download PDF

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Publication number
US3861627A
US3861627A US429271A US42927173A US3861627A US 3861627 A US3861627 A US 3861627A US 429271 A US429271 A US 429271A US 42927173 A US42927173 A US 42927173A US 3861627 A US3861627 A US 3861627A
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United States
Prior art keywords
rocket
ring member
control flap
surface portion
unit according
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
US429271A
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English (en)
Inventor
Rainer Schoffl
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.)
Dynamit Nobel AG
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Dynamit Nobel AG
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Filing date
Publication date
Application filed by Dynamit Nobel AG filed Critical Dynamit Nobel AG
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Publication of US3861627A publication Critical patent/US3861627A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • 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
    • F42B10/20—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel deployed by combustion gas pressure, or by pneumatic or hydraulic forces
    • 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
    • F42B10/18—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel using a longitudinally slidable support member

Definitions

  • the present invention relates to a foldable control flap unit, especially for rockets.
  • the rudder fins are pivotably attached to rigid bearings and are unfolded individually by way of springs, pistons, or the like.
  • a synchronous unfolding of all rudder fins is not sufficiently ensured with such arrangements.
  • a foldable control flap unit especially for rockets, which is characterized by rudder fins hingedly joined to a ring axially displaceable on a cylindrical section of the rocket engine and/or the nozzle thereof, which fins are synchronously spread outwardly by a rearwardly oriented axial pressure on the ring by the fins sliding along a rigid, correspondingly beveled counterpart member disposed behind the initially flat rudder fins.
  • the counterpart member can be the conical portion of a rocket nozzle or a sabot wherein suitably special guide slots are provided for the spread-open rudder fins.
  • the axial pressure on the mounting of the rudder fins can be provided by one or more springs, or by one or more piston rods of cylinders connected to a gas stream branched off from the rocket engine.
  • FIGS. 1a and lb illustrate a rocket having a foldable control flap unit in accordance with the present invention with FIGS. la and 1b illustrating the control flap unit in the closed and open positions, respectively;
  • FIG. 1c illustrates another embodiment of the control flap unit in the open position
  • FIGS. 20 and 2b illustrate another embodiment of a control flap unit in accordance with the present invention in the closed and open positions, respectively;
  • FIG. 2c illustrates, in sectional view, another embodiment of a control flap unit utilizing a piston system for unfolding the unit.
  • FIG. la illustrates a rocket having a payload nose portion 1 and a rocket engine 2.
  • a ring 3 having a forwardly directed conical surface is fixedly attached at the rear end of the engine and surrounds the nozzle of the rocket engine, not shown, as an adapter disk or sabot.
  • An axially displaceable ring 4 is attached to the rocket engine 2 and has four rudder fins 5 pivotably mounted at pins 6 to the ring 4 and forms the control flap unit for rocket.
  • the rudder fins 5 have an oblique or inclined end surface 7 contacting the conical ring 3.
  • a compression spring 8, particularly fashioned as a cylindrical coil spring is positioned between the displaceable ring 4 and the rocket nose 1 for forcing the ring 4 with therudder fins 5 against the conical ring 3.
  • the ring 4 with the rudder fins 5 cannot be displaced.
  • FIG. 1b illustrates the rocket of FIG. la after leaving the launching tube with the control flap unit in the unfolded condition. Due to the pressure force of the spring 8, the ring 4 has been pushed rearwardly with the rudder fins 5 sliding upwardly along the conical ring 3 and displaced into the unfolded condition.
  • a locking means can be provided, in order to avoid an arbitrary collapse of the control flap unit due to aerodynamic forces.
  • Such a locking means can consist, for example, of a spring-loaded pin in the ring 4 which, when the control flap unit is unfolded, engages a groove at the rear end of the rocket engine 2.
  • FIG. 1c illustrates another embodiment of the control flap unit, wherein a rectangular ring 9 is employed instead of the forwardly directed conical ring 3.
  • the ring 9 is provided with inclined slots ltll with the rudder fins 5 being laterally guided in the slots 10 into the unfolded condition, whereby a more stable mounting of the rudder fins 5 is attained due to the location thereof within the slots.
  • FIG. 2a illustrates another embodiment of the present invention wherein the rear end 11 of a rocket engine fashioned in a conventional manner, is provided with a nozzle 12 consisting of an outwardly cylindrical section 13 and an outwardly conical section 14.
  • a displaceable ring 15 is arranged at the cylindrical section 13 and carries four rudder fins l6 pivotably mounted at the bearing members 17.
  • FIG. 2b illustrates the condition wherein the ring 15 has been pushed rearwardly and during this step, the rudder fins 16 are unfolded outwardly because of the sliding movement against the conical section 14.
  • FIG. 2c illustrates, in a partial sectional view another embodiment of the present invention wherein the rudder fins 16 are pushed rearwardly by means of gas pressure instead of spring force.
  • the rocket includes a combustion chamber having a rear end portion 19 with a solid propellant charge 20 having an insulation member 21 and a support member 22.
  • a hollow cylinder 23 is attached to the nozzle 12, for example by welding, and a piston 24 with a sealing member 25 and a piston rod 26 is housed in this cylinder.
  • a bore 27 connects the free engine space 29 with the space 28 in the hollow cylinder 23. In this way, pressure is produced in the space 28 upon the ignition of the propellant charge 20, pushing the piston 24 rearwardly.
  • the ring 15 is pushed rearwardly by way of the piston rod 26 contacting the ring 15, so. that the rudder fins 16 are pivoted outwardly by sliding contact along the surface 14.
  • Foldable control flap unit especially for rockets, comprising a plurality of control flap members, connecting means disposed on a rocket for hingedly connecting said flap members for movement from a substantially folded closed position to an unfolded open position, said flap members having a first inclined surface portion, and counterpart means having a second correspondingly inclined surface portion, at least one of said connecting means and said counterpart means being responsive to axial force for synchronously unfolding said flap members by causing said first and second inclined surface portions to slidingly engage with a consequent unfolding of said flap members, said connecting means including a ring member mounted for axial movement along a portion of the rocket from a first position to a second position in the rearward direction of the rocket, said flap members being hingedly connected thereto, said counterpart means being a fixedly disposed rigid member at a rearward portion of the rocket, and said ring member being responsive to axial force in the rearward direction for causing said first inclined surface portion to slidingly engage said second inclined surface portion.
  • Foldable control flap unit according to claim 2, further comprising displacement means for providing axial force in the rearward direction for displacing said ring member.
  • said displacement means includes at least one spring member mounted on the rocket for biasing said ring member rearwardly.
  • said displacement means includes at least one piston and cylinder means, said cylinder means being disposed on the rocket and the rocket being provided with at least one bore means providing a communicating path between said cylinder means and the free engine space of the rocket engine, said piston means being disposed within said cylinder means and connected to said ring member, said piston means being responsive to a force supplied via said bore means for displacing said ring member rearwardly.
  • Foldable control flap unit according to ulaim 2 further comprising locking means for locking said ring member in the second position thereof. claim 12.
  • Foldable control flap unit according to claim 9, wherein said second inclined surface portion of said counterpart means includes means forming inclined slots for receiving said flap members for movement therein.
  • Foldable control flap unit according to claim 10, wherein said ring member is disposed about a cylindrical surface portion of the rocket.
  • Foldable control flap unit according to claim 10, wherein said second inclined surface portion of said counterpart means includes means forming inclined slots for receiving said flap members for movement therein.
  • Foldable control flap unit especially for rockets, comprising a plurality of control flap members, connecting means disposed on a rocket for hingedly connecting said flap members for movement from a substantially folded closed position to an unfolded open position, said connecting means including a ring member mounted for axial movement along a portion of the rocket from a first position to a second position in the rearward direction of the rocket, said flap members being hingedly connected to said ring member, said flap members having a first inclined surface portion, and counterpart means having a second correspondingly inclined surface portion, said ring member being responsive to axial force in the rearward direction of the rocket for synchronously unfolding said flap members by causing said first and second inclined surface portions to slidingly engage with a consequent unfolding of said flap members with said flap members pivoting outwardly with respect to said ring member during at least a portion of the axial movement thereof.
  • Foldable control flap unit according to claim 16, wherein said flap members are configured to extend in the longitudinal direction of the rocket and are disposed within the longitudinal extent of the rocket in the first position thereof.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Testing Of Engines (AREA)
  • Toys (AREA)
US429271A 1972-12-30 1973-12-28 Foldable control flap unit, especially for rockets Expired - Lifetime US3861627A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2264338A DE2264338A1 (de) 1972-12-30 1972-12-30 Ausklappbares leitwerk, insbesondere fuer raketen

Publications (1)

Publication Number Publication Date
US3861627A true US3861627A (en) 1975-01-21

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ID=5865891

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US429271A Expired - Lifetime US3861627A (en) 1972-12-30 1973-12-28 Foldable control flap unit, especially for rockets

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US (1) US3861627A (it)
DE (1) DE2264338A1 (it)
FR (1) FR2212528B1 (it)
IT (1) IT1002569B (it)

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4844386A (en) * 1987-04-14 1989-07-04 Diehl Gmbh & Co. Airborne body with extendable fins
US5417139A (en) * 1993-10-01 1995-05-23 Unisys Corporation Delivery system and method for flexible array
US5671899A (en) * 1996-02-26 1997-09-30 Lockheed Martin Corporation Airborne vehicle with wing extension and roll control
US5685503A (en) * 1994-06-28 1997-11-11 Luchaire Defense As Deployment device for the fin of a projectile
US5927643A (en) * 1997-11-05 1999-07-27 Atlantic Research Corporation Self-deploying airfoil for missile or the like
US6224013B1 (en) * 1998-08-27 2001-05-01 Lockheed Martin Corporation Tail fin deployment device
US6398156B2 (en) * 1999-12-16 2002-06-04 Lfk Lenkflugkoerpersysteme Gmbh Mounting for attaching a rudder to a missile
US20040011919A1 (en) * 2000-07-03 2004-01-22 Stig Johnsson Fin-stabilized shell
WO2005026651A1 (en) * 2003-09-05 2005-03-24 Selex Sensors And Airborne Systems Limited Drag-producing devices
US20050224631A1 (en) * 2004-03-05 2005-10-13 The Boeing Company Mortar shell ring tail and associated method
WO2007133247A2 (en) * 2005-10-05 2007-11-22 General Dynamics Ordnance And Tactical Systems, Inc. Fin retention and deployment mechanism
US20110024550A1 (en) * 2009-07-31 2011-02-03 Mcdermott Brian K Deployable boat-tail device for use on projectiles
US20120074256A1 (en) * 2010-04-07 2012-03-29 Amy Pietrzak Compression spring wing deployment initiator
CN104833276A (zh) * 2015-05-18 2015-08-12 中国船舶重工集团公司第七○二研究所 栅格翼同步展开机构
CN105424314A (zh) * 2015-12-18 2016-03-23 中国航天空气动力技术研究院 自由飞模型舵面展开风洞试验装置
CN107421403A (zh) * 2017-09-20 2017-12-01 成都云鼎智控科技有限公司 一种用于纵向折叠弹翼的多杆联动式折叠机构
CN109141143A (zh) * 2018-07-26 2019-01-04 重庆长安工业(集团)有限责任公司 一种折叠翼面卡锁机构
CN109696088A (zh) * 2018-12-07 2019-04-30 上海机电工程研究所 紧凑式弹翼缩展机构及导弹
CN110906807A (zh) * 2019-12-13 2020-03-24 北京中科宇航探索技术有限公司 一种火箭用嵌入式气动控制舵面及其控制方法
CN114216647A (zh) * 2021-12-16 2022-03-22 中国航天空气动力技术研究院 一种风洞试验用舵翼瞬态展收装置
US11340052B2 (en) 2019-08-27 2022-05-24 Bae Systems Information And Electronic Systems Integration Inc. Wing deployment initiator and locking mechanism
US11852211B2 (en) 2020-09-10 2023-12-26 Bae Systems Information And Electronic Systems Integration Inc. Additively manufactured elliptical bifurcating torsion spring

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE8406351L (sv) * 1984-12-13 1986-04-21 Ffv Affersverket Styrverk for utfellning av fenor hos projektil

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3098446A (en) * 1960-07-11 1963-07-23 Hotchkiss Brandt Openable fin arrangement
US3622103A (en) * 1968-07-11 1971-11-23 Oerlikon Buehrle Ag Twistless projectile with launching tube
US3684214A (en) * 1969-02-07 1972-08-15 Messerschmitt Boelkow Blohm Flying body having extensible fins

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1187193A (fr) * 1957-11-15 1959-09-08 Hotchkiss Brandt Empennage déployant perfectionné pour projectile
FR1418696A (fr) * 1963-12-28 1965-11-19 Breda Mecc Bresciana Gouvernail à ailettes pliantes pour fusées

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3098446A (en) * 1960-07-11 1963-07-23 Hotchkiss Brandt Openable fin arrangement
US3622103A (en) * 1968-07-11 1971-11-23 Oerlikon Buehrle Ag Twistless projectile with launching tube
US3684214A (en) * 1969-02-07 1972-08-15 Messerschmitt Boelkow Blohm Flying body having extensible fins

Cited By (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4844386A (en) * 1987-04-14 1989-07-04 Diehl Gmbh & Co. Airborne body with extendable fins
US5417139A (en) * 1993-10-01 1995-05-23 Unisys Corporation Delivery system and method for flexible array
US5685503A (en) * 1994-06-28 1997-11-11 Luchaire Defense As Deployment device for the fin of a projectile
US5671899A (en) * 1996-02-26 1997-09-30 Lockheed Martin Corporation Airborne vehicle with wing extension and roll control
US5927643A (en) * 1997-11-05 1999-07-27 Atlantic Research Corporation Self-deploying airfoil for missile or the like
US6224013B1 (en) * 1998-08-27 2001-05-01 Lockheed Martin Corporation Tail fin deployment device
US6398156B2 (en) * 1999-12-16 2002-06-04 Lfk Lenkflugkoerpersysteme Gmbh Mounting for attaching a rudder to a missile
US20040011919A1 (en) * 2000-07-03 2004-01-22 Stig Johnsson Fin-stabilized shell
US6886775B2 (en) * 2000-07-03 2005-05-03 Bofors Defence Ab Fin-stabilized shell
WO2005026651A1 (en) * 2003-09-05 2005-03-24 Selex Sensors And Airborne Systems Limited Drag-producing devices
US20050178873A1 (en) * 2003-09-05 2005-08-18 Bae Systems Plc Drag-producing devices
AU2004272795B2 (en) * 2003-09-05 2010-12-16 Selex Galileo Ltd Drag-producing devices
US7513454B2 (en) 2003-09-05 2009-04-07 Selex Sensors And Airborne Systems Limited Drag-producing devices
US20050224631A1 (en) * 2004-03-05 2005-10-13 The Boeing Company Mortar shell ring tail and associated method
US7262394B2 (en) * 2004-03-05 2007-08-28 The Boeing Company Mortar shell ring tail and associated method
US7475846B2 (en) * 2005-10-05 2009-01-13 General Dynamics Ordnance And Tactical Systems, Inc. Fin retention and deployment mechanism
WO2007133247A3 (en) * 2005-10-05 2008-08-28 Gen Dynamics Ordnance & Tactic Fin retention and deployment mechanism
US20080001023A1 (en) * 2005-10-05 2008-01-03 General Dynamics Ordnance And Tactical Systems, Inc. Fin retention and deployment mechanism
WO2007133247A2 (en) * 2005-10-05 2007-11-22 General Dynamics Ordnance And Tactical Systems, Inc. Fin retention and deployment mechanism
US20110024550A1 (en) * 2009-07-31 2011-02-03 Mcdermott Brian K Deployable boat-tail device for use on projectiles
US20120074256A1 (en) * 2010-04-07 2012-03-29 Amy Pietrzak 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
CN104833276A (zh) * 2015-05-18 2015-08-12 中国船舶重工集团公司第七○二研究所 栅格翼同步展开机构
CN105424314A (zh) * 2015-12-18 2016-03-23 中国航天空气动力技术研究院 自由飞模型舵面展开风洞试验装置
CN107421403A (zh) * 2017-09-20 2017-12-01 成都云鼎智控科技有限公司 一种用于纵向折叠弹翼的多杆联动式折叠机构
CN109141143A (zh) * 2018-07-26 2019-01-04 重庆长安工业(集团)有限责任公司 一种折叠翼面卡锁机构
CN109696088A (zh) * 2018-12-07 2019-04-30 上海机电工程研究所 紧凑式弹翼缩展机构及导弹
CN109696088B (zh) * 2018-12-07 2021-06-08 上海机电工程研究所 紧凑式弹翼缩展机构及导弹
US11340052B2 (en) 2019-08-27 2022-05-24 Bae Systems Information And Electronic Systems Integration Inc. Wing deployment initiator and locking mechanism
CN110906807A (zh) * 2019-12-13 2020-03-24 北京中科宇航探索技术有限公司 一种火箭用嵌入式气动控制舵面及其控制方法
US11852211B2 (en) 2020-09-10 2023-12-26 Bae Systems Information And Electronic Systems Integration Inc. Additively manufactured elliptical bifurcating torsion spring
CN114216647A (zh) * 2021-12-16 2022-03-22 中国航天空气动力技术研究院 一种风洞试验用舵翼瞬态展收装置

Also Published As

Publication number Publication date
IT1002569B (it) 1976-05-20
DE2264338A1 (de) 1974-07-04
FR2212528B1 (it) 1977-08-19
FR2212528A1 (it) 1974-07-26

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