US3304030A - Pyrotechnic-actuated folding fin assembly - Google Patents

Pyrotechnic-actuated folding fin assembly Download PDF

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US3304030A
US3304030A US490143A US49014365A US3304030A US 3304030 A US3304030 A US 3304030A US 490143 A US490143 A US 490143A US 49014365 A US49014365 A US 49014365A US 3304030 A US3304030 A US 3304030A
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fin
swinging
secured
erect position
per
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James E Weimholt
Jr Lawrence M Biggs
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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

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  • the present invention relates to a folding fin assembly for an aerial missile and more particularly to means for effecting in-fiight erection of the fins in a positive and reliable manner.
  • Folded fin assemblies have been employed on various types of aerial missiles in the interests of space limitations during storage in a magazine and carriage on an aircraft. Such assemblies have relied upon aerodynamic forces or used spring-loaded devices to effect erection after launching from the aircraft and have the disadvantage that the fins do not always unfold simultaneously with the result that the flight of the missile is unstable.
  • Another object is the provision of means for unfolding the fins in a rapid, positive and reliable manner.
  • a further object is to provide a folding fin assembly which is simple in construction, economical to manufacture and is reliable in its manner of operation.
  • FIG. 1 is a vertical elevation of the folding fin assembly of this invention, with parts broken away to illustrate certain structural details;
  • FIG. 2 is an end elevation of the assembly looking in the direction of the arrow 2, FIG. 1;
  • FIG. 3 is a view similar to FIG. 1 but showing the fins in erect or unfolded position.
  • FIG. 1 a folding fin assembly attached to the aft end of a missile body 12, shown only in part.
  • the assembly 10 comprises an attaching band 14 and an aft plate 16 interconnected by a plurality of fin housings 18.
  • Each housing 18 comprises a pair of elongated, generally triangular mounting plates 20 disposed spacedapart and generally parallel to the longitudinal axis of the assembly and suitably secured at their fore and aft ends to band 14 and plate 16, as by welding or the like.
  • Each pair of plates 20 has secured thereto at its forward portions a fairing plate 22.
  • Plate 16 is disposed substantially perpendicular to the longitudinal axis of the assembly and is provided with extensions or tabs 24, there being one such tab for each housing 18 into which the tab extends, for a reason hereinafter appearing, and which is secured to the rear ends of plates 20 thereof.
  • each housing 18 Adjacent to plate 16, each housing 18 has a pivot pin 26 upon which is pivotally mounted a cam block 28.
  • Each cam block is formed with a curved cam surface 30 and a shoulder 32 and carries a fin blade 34, the shoulder 32 engaging with the outer end 35 of the tab 24 associated therewith when the cam block has pivoted and the fin blade has been unfolded to erect position; see FIG. 3.
  • Pins 34 may be retained in folded position by 3,304,030 Patented Feb. 14, 1967 "ice means of shear-pins 36, force-fitted into holes 37 in cam blocks 28.
  • the means for erecting the fin blades comprises an expandable chamber 38 including a pair of telescoping cuplike members 40 and 42, member 40 being suitably secured to aft plate 16 centrally thereof and extending forwardly, member 42 closing off the open end of member 40 and carrying a conventional gas generating pyrotechnic device 44 such as a cartridge or the like.
  • Slidably mounted on member 42 is a sleeve 46 forming part of a pusher assembly comprising pusher arms 48 rigidly secured to the sleeve, member 42 being formed with a lip 50 for engaging sleeve 46 and moving the same.
  • Each arm 48 is formed with a pusher element or finger 52 having a facing 54.
  • the number of arms 48 is the same as the number of housings 18 with a pusher finger disposed adjacent the curved surface 30 of each cam block 28 when the fin blade associated therewith is in its folded position; FIG. 1.
  • Attaching band 14 may be secured to the missile body 12 by any suitable means.
  • Such means may take the form, if desired, of a plurality of pairs of circumferentially spaced projections 62 on the inner periphery of the band 14, each pair of projections 62 being adapted to receive therebetween one of a plurality of circumferentially-spaced projections 64 on the body 12.
  • the fin assembly is slipped over the rear end of body 12 so that projections 64 are disposed in the circumferential spaces between pairs of projections 62 after which the assembly is rotated slightly to have the pairs of projections 62 receive the projections 64 and then locked in place.
  • the missile In operation, the missile is launched and as it falls away from the aircraft the pyrotechnic device 44 is activated, the gas generated expanding chamber 38 and imparting movement to member 42, sleeve 46 and arms 48. Facings 54 on fingers 52 engage curved surfaces 30 of the cam blocks 28 and swing the blocks and fin blades 34 attached thereto to the unfolded or erect position. Facing 54 on each finger 52 is of a relatively hard material, for example, steel, while the material of each block 28 is relatively softer, for example, aluminum, and the structural dimensions are so chosen that in the unfolded position the facings wedge and dig into the respective cam blocks, thus locking the fin blades in erect position and arresting movement of the pusher assembly and member 42.
  • the energy imparted to member 42 may be predetermined by selection of a pyrotechnic device 44 having an energy output of desired proportions and adjusted by the location of perforations 66 in member 40 which vent the gas in chamber 38 to the atmosphere as they are uncovered by movement of member 42.
  • An unitary folding fin assembly comprising:
  • each fin housing comprising a pair of parallel mounting plates having rear ends disposed on either side of one of said tabs and secured thereto;
  • an attaching band disposed generally parallel to said circular plate and secured to the front portions of said mounting plates;
  • cam blocks one per pivot pin and supported thereon for swinging from a folded position to an erect position in which swinging is limited by engagement of the block with the end of the associated tab;
  • an unitary pusher structure disposed between said fin housings and having a plurality of pusher fingers, one per cam block and engageable therewith for swinging the same upon movement of the structure;
  • gas generating means in said chamber for expanding the same and imparting movement to said movable part.
  • each said pusher finger is provided with a facing of a material harder than the material of the associated cam block and is dimensioned so that each facing digs into its associated cam block after said block has been swung to erect position for locking the blocks and fins in erect position.
  • a folding fin assembly for an aerial body comprising:
  • transverse means secured to said housings at the rear ends thereof;
  • each housing pivotally mounting a cam block, respectively;
  • each cam block carrying a fin disposed wholly within its respective housing when said fin is in folded position
  • pyrotechnic means in said chamber for expanding said chamber and moving said part and structure for swinging said cam blocks and associated fins to erect position.
  • each of said pusher elements is of a material that is harder than the material of the cam block associated therewith
  • a folding fin assembly comprising:
  • each housing including a pair of mounting plates rigidly secured at their front and rear ends to said band and support plate, respectively;
  • a plurality of fin members one per housing and pivotally mounted on the pivot pin thereof for swinging from a folded position with the fin member disposed wholly within the housing to an erect position with a major portion of the fin member outside the housa plurality of rigidly interconnected radially-etxending arms mounted on said support plate for axial movement forwardly thereof;
  • the number of arms being equal to the number of fin members and associated therewith so that the radial end of each arm is engageable with its associated fin member for swinging the same to erect position in response to forward movement of said arms;

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  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)

Description

Feb. 14, 1967 J. E. WEIMHOLT ETAL 3,304,030
FYROTEGHNIC-ACTUATED FOLDING FIN ASSEMBLY Filed Sept. 24, 1965 INVENTORS. JAMES E. WElMHOLT ATTORNEY.
LAWRENCE M. BIGGS,JR.
United States Patent 3,304,030 PYROTECHNIC-ACTUATED FOLDING FIN ASSEMBLY James E. Weimholt and Lawrence M. Biggs, Jr., China Lake, Califi, assignors to the United States of America as represented by the Secretary of the Navy Filed Sept. 24, 1965, Ser. No. 490,143 6 Claims. (Cl. 2443.28)
The invention described herein may be manufactured and used by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor.
The present invention relates to a folding fin assembly for an aerial missile and more particularly to means for effecting in-fiight erection of the fins in a positive and reliable manner.
Folded fin assemblies have been employed on various types of aerial missiles in the interests of space limitations during storage in a magazine and carriage on an aircraft. Such assemblies have relied upon aerodynamic forces or used spring-loaded devices to effect erection after launching from the aircraft and have the disadvantage that the fins do not always unfold simultaneously with the result that the flight of the missile is unstable.
It is therefore a purpose and object of this invention to provide a folding fin assembly having spatial and other advantageous features while in storage or attached to the aircraft, yet also possessing aerodynamically advantageous features of large caliber stabilizing fins upon launching of the missile.
Another object is the provision of means for unfolding the fins in a rapid, positive and reliable manner.
A further object is to provide a folding fin assembly which is simple in construction, economical to manufacture and is reliable in its manner of operation.
Other objects, advantages and novel features of the invention will become apparent from the following detailed description of the invention when considered in conjunctio with the accompanying drawings wherein:
FIG. 1 is a vertical elevation of the folding fin assembly of this invention, with parts broken away to illustrate certain structural details;
FIG. 2 is an end elevation of the assembly looking in the direction of the arrow 2, FIG. 1; and
FIG. 3 is a view similar to FIG. 1 but showing the fins in erect or unfolded position.
Referring now to the drawings, there is shown in FIG. 1 a folding fin assembly attached to the aft end of a missile body 12, shown only in part. The assembly 10 comprises an attaching band 14 and an aft plate 16 interconnected by a plurality of fin housings 18.
Each housing 18 comprises a pair of elongated, generally triangular mounting plates 20 disposed spacedapart and generally parallel to the longitudinal axis of the assembly and suitably secured at their fore and aft ends to band 14 and plate 16, as by welding or the like. Each pair of plates 20 has secured thereto at its forward portions a fairing plate 22.
Plate 16 is disposed substantially perpendicular to the longitudinal axis of the assembly and is provided with extensions or tabs 24, there being one such tab for each housing 18 into which the tab extends, for a reason hereinafter appearing, and which is secured to the rear ends of plates 20 thereof. Adjacent to plate 16, each housing 18 has a pivot pin 26 upon which is pivotally mounted a cam block 28. Each cam block is formed with a curved cam surface 30 and a shoulder 32 and carries a fin blade 34, the shoulder 32 engaging with the outer end 35 of the tab 24 associated therewith when the cam block has pivoted and the fin blade has been unfolded to erect position; see FIG. 3. Pins 34 may be retained in folded position by 3,304,030 Patented Feb. 14, 1967 "ice means of shear-pins 36, force-fitted into holes 37 in cam blocks 28.
The means for erecting the fin blades comprises an expandable chamber 38 including a pair of telescoping cuplike members 40 and 42, member 40 being suitably secured to aft plate 16 centrally thereof and extending forwardly, member 42 closing off the open end of member 40 and carrying a conventional gas generating pyrotechnic device 44 such as a cartridge or the like. Slidably mounted on member 42 is a sleeve 46 forming part of a pusher assembly comprising pusher arms 48 rigidly secured to the sleeve, member 42 being formed with a lip 50 for engaging sleeve 46 and moving the same. Each arm 48 is formed with a pusher element or finger 52 having a facing 54. The number of arms 48 is the same as the number of housings 18 with a pusher finger disposed adjacent the curved surface 30 of each cam block 28 when the fin blade associated therewith is in its folded position; FIG. 1.
For aerodynamic reasons, it is desirable to close the open spaces between housings 18 with sections 56 of metallic skin or the like secured to the attaching band 14, the aft plate 16 and plates 20 by screws 58 of the like, plates 20 being provided at their inner edges with narrow strips 60 extending laterally sufficiently to form supporting ledges for the adjacent edges of sections 56; FIG. 2.
Attaching band 14 may be secured to the missile body 12 by any suitable means. Such means may take the form, if desired, of a plurality of pairs of circumferentially spaced projections 62 on the inner periphery of the band 14, each pair of projections 62 being adapted to receive therebetween one of a plurality of circumferentially-spaced projections 64 on the body 12. In attachmerit, the fin assembly is slipped over the rear end of body 12 so that projections 64 are disposed in the circumferential spaces between pairs of projections 62 after which the assembly is rotated slightly to have the pairs of projections 62 receive the projections 64 and then locked in place.
In operation, the missile is launched and as it falls away from the aircraft the pyrotechnic device 44 is activated, the gas generated expanding chamber 38 and imparting movement to member 42, sleeve 46 and arms 48. Facings 54 on fingers 52 engage curved surfaces 30 of the cam blocks 28 and swing the blocks and fin blades 34 attached thereto to the unfolded or erect position. Facing 54 on each finger 52 is of a relatively hard material, for example, steel, while the material of each block 28 is relatively softer, for example, aluminum, and the structural dimensions are so chosen that in the unfolded position the facings wedge and dig into the respective cam blocks, thus locking the fin blades in erect position and arresting movement of the pusher assembly and member 42. The energy imparted to member 42 may be predetermined by selection of a pyrotechnic device 44 having an energy output of desired proportions and adjusted by the location of perforations 66 in member 40 which vent the gas in chamber 38 to the atmosphere as they are uncovered by movement of member 42.
There has thus been provided a folding fin assembly in which the fins are erected simultaneously in a rapid, positive and reliable manner.
Obviously many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be practiced otherwise than as specifically described.
What is claimed is:
1. An unitary folding fin assembly comprising:
a circular plate;
a plurality of radially extending tabs on said plate arranged equi-angularly around the periphery thereof;
a plurality of fin housings, each comprising a pair of parallel mounting plates having rear ends disposed on either side of one of said tabs and secured thereto;
an attaching band disposed generally parallel to said circular plate and secured to the front portions of said mounting plates;
a plurality of pivot pins, one per fin housing supported in the mounting plates thereof adjacent the associated tab;
a plurality of cam blocks, one per pivot pin and supported thereon for swinging from a folded position to an erect position in which swinging is limited by engagement of the block with the end of the associated tab;
a plurality of fins, one per cam block and secured thereto for swinging therewith from folded to erect position; and
means engaging said cam blocks for swinging the same and the fins to erect position.
2. The fin assembly of claim 1, wherein said means comprises:
an unitary pusher structure disposed between said fin housings and having a plurality of pusher fingers, one per cam block and engageable therewith for swinging the same upon movement of the structure;
an expandable chamber supported on said circular plate and having a movable part carrying said pusher sup port structure; and
gas generating means in said chamber for expanding the same and imparting movement to said movable part.
3. The fin assembly of claim 2, wherein:
each said pusher finger is provided with a facing of a material harder than the material of the associated cam block and is dimensioned so that each facing digs into its associated cam block after said block has been swung to erect position for locking the blocks and fins in erect position.
4. A folding fin assembly for an aerial body comprising:
an attachment means adapted to receive one end of said body;
a plurality of fin housings secured to said attachment means and extending rearwardly therefrom;
transverse means secured to said housings at the rear ends thereof;
each housing pivotally mounting a cam block, respectively;
each cam block carrying a fin disposed wholly within its respective housing when said fin is in folded position;
an expandable chamber mounted centrally of said transverse means and having a forwardly movable part;
a structure carried by said part and movable thereby;
a plurality of pusher elements rigid with said structure, there being one element per cam block and engageable therewith for swinging the same and the fin carried thereby from unfolded to erect position; and
pyrotechnic means in said chamber for expanding said chamber and moving said part and structure for swinging said cam blocks and associated fins to erect position.
5. The fin assembly of claim 4, wherein:
each of said pusher elements is of a material that is harder than the material of the cam block associated therewith,
6. In combination with an elongated aerial body having a longitudinal axis, a folding fin assembly comprising:
an attaching band attached to the rear end of said body;
a circular support plate disposed rearwardly of said band with said longitudinal axis passing through the center thereof perpendicular thereto;
a plurality of fin housings arranged around said band and plate, each housing including a pair of mounting plates rigidly secured at their front and rear ends to said band and support plate, respectively;
a plurality of pivot pins, one per housing and supported in the mounting plates thereof adjacent said support plate;
a plurality of fin members, one per housing and pivotally mounted on the pivot pin thereof for swinging from a folded position with the fin member disposed wholly within the housing to an erect position with a major portion of the fin member outside the housa plurality of rigidly interconnected radially-etxending arms mounted on said support plate for axial movement forwardly thereof;
the number of arms being equal to the number of fin members and associated therewith so that the radial end of each arm is engageable with its associated fin member for swinging the same to erect position in response to forward movement of said arms; and
means for imparting forward movement to said arms.
References Cited by the Examiner UNITED STATES PATENTS 1,181,203 5/1916 Alard 2443.28 2,671,398 3/1954 Peck 102-2, 2,821,924 2/1958 Hansen et al 244-3.28
References Cited by the Applicant UNITED STATES PATENTS 2,977,880 4/ 1961 Kershner. 3,010,677 11/1961 Guthrie et al. 3,057,589 10/1962 Nutkins et a1. 3,103,886 9/1963 Popenoe. 3,125,956 3/ 1964 Kongelback. 3,127,838 4/1964 Moratti et al. 3,165,281 1/ 1965 Gohlke.
BENJAMIN A. BORCHELT, Primary Examiner.
' V. R, PENDEGRASS, Assistant Examiner,

Claims (1)

1. AN UNITARY FOLDING FIN ASSEMBLY COMPRISING: A CIRCULAR PLATE; A PLURALITY OF RADIALLY EXTENDING TABS ON SAID PLATE ARRANGED EQUI-ANGULARLY AROUND THE PERIPHERY THEREOF; A PLURALITY OF FIN HOUSINGS, EACH COMPRISING A PAIR OF PARALLEL MOUNTING PLATES HAVING REAR ENDS DISPOSED ON EITHER SIDE OF ONE OF SAID TABS AND SECURED THERETO; AN ATTACHING BAND DISPOSED GENERALLY PARALLEL TO SAID CIRCULAR PLATE AND SECURED TO THE FRONT PORTIONS OF SAID MOUNTING PLATES; A PLURALITY OF PIVOT PINS, ONE PER FIN HOUSING SUPPORTED IN THE MOUNTING PLATES THEREOF ADJACENT THE ASSOCIATED TAB; A PLURALITY OF CAM BLOCKS, ONE PER PIVOT PIN AND SUPPORTED THEREON FOR SWINGING FROM A FOLDED POSITION TO AN ERECT POSITION IN WHICH SWINGING IS LIMITED BY ENGAGEMENT OF THE BLOCK WITH THE END OF THE ASSOCIATED TAB; A PLURALITY OF FINS, ONE PER CAM BLOCK AND SECURED THERETO FOR SWINGING THEREWITH FROM FOLDED TO ERECT POSITION; AND MEANS ENGAGING SAID CAM BLOCKS FOR SWINGING THE SAME AND THE FINS TO ERECT POSITION.
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Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3380382A (en) * 1966-07-20 1968-04-30 Army Usa Gun launched liquid rocket
US3788578A (en) * 1971-05-19 1974-01-29 T Sweeney Semi-rigid airfoil for airborne vehicles
DE2805496A1 (en) * 1977-02-09 1978-08-10 Bofors Ab DEVICE FOR AN EXTENDABLE LEAF ON A ASSEMBLY IN THE FORM OF A FLOOR, A PROJECTILE, A ROCKET OR THE LIKE.
US4586681A (en) * 1983-06-27 1986-05-06 General Dynamics Pomona Division Supersonic erectable fabric wings
US4667899A (en) * 1984-11-28 1987-05-26 General Dynamics, Pomona Division Double swing wing self-erecting missile wing structure
EP0214888A3 (en) * 1985-08-12 1987-11-11 Grumman Aerospace Corporation Missile folding wing configuration
US4844386A (en) * 1987-04-14 1989-07-04 Diehl Gmbh & Co. Airborne body with extendable fins
EP0389358A1 (en) * 1989-03-24 1990-09-26 Thomson-Brandt Armements Opening system for spreading wings on a projectile
DE3917653A1 (en) * 1989-05-31 1990-12-06 Diehl Gmbh & Co Erecting projectile fins by compression spring energy - applied to piston axially mobile in cylinder with apertured wall
US5040746A (en) * 1990-08-14 1991-08-20 The United States Of America As Represented By The Secretary Of The Army Finned projectile with supplementary fins
US6224013B1 (en) * 1998-08-27 2001-05-01 Lockheed Martin Corporation Tail fin deployment device
US7040210B2 (en) 2003-02-18 2006-05-09 Lockheed Martin Corporation Apparatus and method for restraining and releasing a control surface
US7097132B2 (en) 2002-09-16 2006-08-29 Lockheed Martin Corporation Apparatus and method for selectivity locking a fin assembly
US20070125904A1 (en) * 2005-12-01 2007-06-07 Janka Ronald E Apparatus and method for restraining and deploying an airfoil
US20100032516A1 (en) * 2008-06-13 2010-02-11 Raytheon Company Solid-fuel pellet thrust and control actuation system to maneuver a flight vehicle
US7973270B1 (en) * 2005-09-07 2011-07-05 Omnitek Partners Llc Actuators for gun-fired projectiles and mortars
US20120152142A1 (en) * 2005-09-07 2012-06-21 Omnitek Partners Llc Actuators for Gun-Fired Projectiles and Mortars
DE102019008539A1 (en) * 2019-12-10 2021-06-10 Diehl Defence Gmbh & Co. Kg Missile with pyrotechnic release

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Publication number Priority date Publication date Assignee Title
US1181203A (en) * 1914-01-27 1916-05-02 Louis Alard Means for modifying the trajectory of a projectile.
US2671398A (en) * 1951-05-11 1954-03-09 Allen S Peck Metal pop-out stabilizing tail for small bombs
US2821924A (en) * 1954-07-09 1958-02-04 Lawrence J Hansen Fin stabilized projectile
US2977880A (en) * 1959-04-07 1961-04-04 Richard B Kershner Fin erector
US3010677A (en) * 1957-11-12 1961-11-28 Gen Dynamics Corp Missile control system
US3057589A (en) * 1958-03-14 1962-10-09 Kaman Aircraft Corp Aerial device having rotor for retarding descent
US3103886A (en) * 1960-10-13 1963-09-17 Charles H Popenoe Coiling fin for tube launched missiles
US3125956A (en) * 1964-03-24 Fold able fin
US3127838A (en) * 1960-10-12 1964-04-07 Bombrini Parodi Delfino Spa Retractable blade tail unit for projectiles
US3165281A (en) * 1962-07-11 1965-01-12 Werner J V Gohlke Elastic folding control surfaces for aerodynes

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3125956A (en) * 1964-03-24 Fold able fin
US1181203A (en) * 1914-01-27 1916-05-02 Louis Alard Means for modifying the trajectory of a projectile.
US2671398A (en) * 1951-05-11 1954-03-09 Allen S Peck Metal pop-out stabilizing tail for small bombs
US2821924A (en) * 1954-07-09 1958-02-04 Lawrence J Hansen Fin stabilized projectile
US3010677A (en) * 1957-11-12 1961-11-28 Gen Dynamics Corp Missile control system
US3057589A (en) * 1958-03-14 1962-10-09 Kaman Aircraft Corp Aerial device having rotor for retarding descent
US2977880A (en) * 1959-04-07 1961-04-04 Richard B Kershner Fin erector
US3127838A (en) * 1960-10-12 1964-04-07 Bombrini Parodi Delfino Spa Retractable blade tail unit for projectiles
US3103886A (en) * 1960-10-13 1963-09-17 Charles H Popenoe Coiling fin for tube launched missiles
US3165281A (en) * 1962-07-11 1965-01-12 Werner J V Gohlke Elastic folding control surfaces for aerodynes

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3380382A (en) * 1966-07-20 1968-04-30 Army Usa Gun launched liquid rocket
US3788578A (en) * 1971-05-19 1974-01-29 T Sweeney Semi-rigid airfoil for airborne vehicles
DE2805496A1 (en) * 1977-02-09 1978-08-10 Bofors Ab DEVICE FOR AN EXTENDABLE LEAF ON A ASSEMBLY IN THE FORM OF A FLOOR, A PROJECTILE, A ROCKET OR THE LIKE.
US4586681A (en) * 1983-06-27 1986-05-06 General Dynamics Pomona Division Supersonic erectable fabric wings
US4667899A (en) * 1984-11-28 1987-05-26 General Dynamics, Pomona Division Double swing wing self-erecting missile wing structure
EP0214888A3 (en) * 1985-08-12 1987-11-11 Grumman Aerospace Corporation Missile folding wing configuration
AU587817B2 (en) * 1985-08-12 1989-08-31 Grumman Aerospace Corporation Penguin missile folding wing configuration
JPH073320B2 (en) 1985-08-12 1995-01-18 グラマン・エアロスペ−ス・コ−ポレイシヨン Folding wing structure
US4844386A (en) * 1987-04-14 1989-07-04 Diehl Gmbh & Co. Airborne body with extendable fins
US5082203A (en) * 1989-03-24 1992-01-21 Thomson-Brandt Armements System for the opening of an unfolding tail unit for projectiles
FR2644880A1 (en) * 1989-03-24 1990-09-28 Thomson Brandt Armements OPENING SYSTEM FOR EMPLOYING DEPLOYANT FOR PROJECTILE
EP0389358A1 (en) * 1989-03-24 1990-09-26 Thomson-Brandt Armements Opening system for spreading wings on a projectile
DE3917653A1 (en) * 1989-05-31 1990-12-06 Diehl Gmbh & Co Erecting projectile fins by compression spring energy - applied to piston axially mobile in cylinder with apertured wall
US5040746A (en) * 1990-08-14 1991-08-20 The United States Of America As Represented By The Secretary Of The Army Finned projectile with supplementary fins
US6224013B1 (en) * 1998-08-27 2001-05-01 Lockheed Martin Corporation Tail fin deployment device
US7097132B2 (en) 2002-09-16 2006-08-29 Lockheed Martin Corporation Apparatus and method for selectivity locking a fin assembly
US7040210B2 (en) 2003-02-18 2006-05-09 Lockheed Martin Corporation Apparatus and method for restraining and releasing a control surface
US7973270B1 (en) * 2005-09-07 2011-07-05 Omnitek Partners Llc Actuators for gun-fired projectiles and mortars
US20120152142A1 (en) * 2005-09-07 2012-06-21 Omnitek Partners Llc Actuators for Gun-Fired Projectiles and Mortars
US9151581B2 (en) * 2005-09-07 2015-10-06 Omnitek Partners Llc Actuators for gun-fired projectiles and mortars
US20070125904A1 (en) * 2005-12-01 2007-06-07 Janka Ronald E Apparatus and method for restraining and deploying an airfoil
US7559505B2 (en) 2005-12-01 2009-07-14 Lockheed Martin Corporation Apparatus and method for restraining and deploying an airfoil
US20100032516A1 (en) * 2008-06-13 2010-02-11 Raytheon Company Solid-fuel pellet thrust and control actuation system to maneuver a flight vehicle
US8193476B2 (en) * 2008-06-13 2012-06-05 Raytheon Company Solid-fuel pellet thrust and control actuation system to maneuver a flight vehicle
DE102019008539A1 (en) * 2019-12-10 2021-06-10 Diehl Defence Gmbh & Co. Kg Missile with pyrotechnic release

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