US3711040A - Outboard missile control surface and actuator - Google Patents

Outboard missile control surface and actuator Download PDF

Info

Publication number
US3711040A
US3711040A US00135737A US3711040DA US3711040A US 3711040 A US3711040 A US 3711040A US 00135737 A US00135737 A US 00135737A US 3711040D A US3711040D A US 3711040DA US 3711040 A US3711040 A US 3711040A
Authority
US
United States
Prior art keywords
control surface
missile
hydraulic
cylinders
actuation system
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
US00135737A
Inventor
A Carver
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.)
US Department of Navy
Original Assignee
US Department of Navy
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 US Department of Navy filed Critical US Department of Navy
Application granted granted Critical
Publication of US3711040A publication Critical patent/US3711040A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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 present invention comprises a control surface actuation system capable of disposition within a restricted volume.
  • the present actuation system and control surface is disposed outboard of the missile due to space limitations imposed by an unusually large nozzle diameter.
  • the system comprises four independent electro-hydraulic actuators of the push-push configuration for driving four aerodynamic control surfaces arranged in cruciform and disposed at the aft end of the missile.
  • the actuation system arrangement allows passage of the missile through existing launchers having typical volume restraints.
  • This invention relates to aerodynamic control surfaces for missiles and more particularly relates to an aerodynamic control surface and actuating system which is completely external to the missile.
  • Thrust requirements for a number of recently proposed missile systems have necessitated the use of much larger nozzles than in the past.
  • the increased size of the nozzles results in an constricted volume in the aft end of the missile thereby preventing the use of inboard control surface actuation systems of conventional design.
  • the increased nozzle size resulting in severely constricted volume dictates the need for an actuation system and control surface which can be mounted on the external portion of the missile and not exceed the pass-through envelope of existing launchers.
  • Present hydraulic systems are not susceptible to exterior mounting on missiles because they take up too much space.
  • Systems which have folding control surfaces are also available. These systems have internal hydraulic actuators not suitable for external mounting.
  • Other folding control surface systems are mechanically operated and are not as efficient as hydraulic systems and not capable of taking high bending moment loads.
  • the present invention overcomes these difficulties by providing an in line or series connected hydraulic actuator system.
  • the purpose of this invention is to provide a hydraulically operated actuation system which can be mounted on the exterior portion of a missile within an restricted volume while still providing a highly efficient system useful with standard restricted volume launchers.
  • a compact control surface and actuation system capable of disposition within a restricted volume is provided by mounting a push-push hydraulic system in a line parallel to the longitudinal axis of the missile body and utilizing folding control surfaces.
  • the system is comprised of four independent electro-hydraulic actuators of the push-push configuration for driving four aerodynamic control surfaces arranged in cruciform and disposed at the aft end of the missile. This system provides control surface movement within a normally required i limits while still conforming to the space limitations imposed by unusuallylarge nozzle diameters.
  • Yet another object of the present invention is to provide a control surface and actuation system for use with large nozzle missiles which allows passage through standard launchers having typical volume restraints.
  • FIG. 1 is a top view of a portion of the missile showing the control surface in an erect position.
  • FIG. 2 is an axial half-section taken through the aft end of the missile at line 22 and the control surface actuation system.
  • FIG. 3 is a section taken through the aft end of and perpendicular to the longitudinal axis of the missile illustrating the control surface in the folded position.
  • FIG. 4 is a section taken through the line 4-4 of FIG. 3 and illustrating the hydraulic actuators and midpanel support bearing.
  • a missile is seen generally at 1 having a nozzle throat section 3 which comprises a large proportion of the volume within the main body 5 of the missile.
  • Recently designed missiles have a throat 3 which is greater than percent of the body diameter 5.
  • the remaining volume within the main body of the missile 5 is insufficient to house an inboard control surface actuation system.
  • the present invention provides a control surface actuation system generally indicated at 11 which is housed substantially within a spar housing 31 which is an extension of a dorsal fin 33 disposed along the main body 5 of the missile.
  • the actuation system 11 includes push-push hydraulic actuators 13, a mid-panel.
  • the support bearing 15 has a shaft portion 16 one end of which is operably joined to the control surface 21. Needle bearings 14 at the end of shaft 16 also provide movable support for control surface 21. Further, the bearing 15 has an enlarged disc portion 18 which mechanically engages piston 39 through shaft 35 of the push-push hydraulic actuators 13.
  • the actuators 13 are seen to comprise cylinders 37 in which pistons 39 are caused to operate under the influence of the electric motor/hydraulic pump combination 19, which influence is directed through the hydraulic servo valve 17.
  • Ports (not shown) drilled in the spar housing 31 connect the servo valve 17 to the pump combination 19 in the conventional manner.
  • the piston shafts 35 are joined to opposite sides of enlarged disc portion 18 of the support bearing 15 and control the rotational movement of the control surface 21 within a normally required i40 limits.
  • the cylinders 27 are pidgeon-toed, i.e., angled, to keep within the restricted volume of the spar housing 31.
  • Positional control of the push-push hydraulic actuators 13 is accomplished through normal electro/mechanical servo arrangements (not shown) which are directed by a position feed-back potentiometer (not shown) mechanically linked to the control surface through the support bearing 15.
  • FIG. 3 the control surface 21 is illustrated in its folded position to permit launching through standard GMLS MK ll or MK 13 launchers. Fin erection mechanisms associated with said launchers (not shown) provide erecting force for the control surface 21 and a lock-pin mechanism (FIG. 2) provides positive locking of the control surface 21 in the flight position.
  • the lock-pin mechanism is seen to comprise in part, a locking pin 27 and a hinge pin 29. Locking pin 27 is forced into a locking position by a spring 28 when the control surface 21 reaches upright position. This type of erection and locking mechanism is conventional.
  • FIG. 3 the pass-through envelope of the standard launchers mentioned above is indicated by the phantom line 43. With the control surface 21 folded against the main body 5 the missile is in the prelaunch configuration.
  • the actuation system 11 varies the pitch angle of the movable control surface 21 which is shown in the erect position in FIG. 1.
  • Four of these systems 11 independently drive one each of four control surfaces 21 arranged in cruciform and located at the aft end of the missile.
  • the usual servo arrangements (not shown) operates the electric motor/hydraulic pump combination 19, which influence is directed through the hydraulic servo valve 17 to provide the pushing force on piston 39 and thereby rotate the control surface 21 to guide the flight path of the missile.
  • Each of the control surfaces 21 and actuation systems I] operate independently of the other to provide complete missile guidance. Control surface position is provided by a feedback potentiometer (not shown) mechanically linked to support bearing 15.
  • An externally mounted missile control system comprising:
  • a housing formed as an extension of a dorsal fin of a missile and adapted to be secured on the external surface of the missile;
  • a series connected hydraulic actuation system mounted in said housing in a line parallel to the axis of said missile including a dual electric motor and hydraulic pump combination;
  • a folding control surface mounted on said housing and supported by a rotatable bearing; means for rotating said control surface connected to said hydraulic actuation system; said rotating means comprising two hydraulic pistons and cylinders connected to opposite sides of said control surface by shafts; said pistons, cylinders and shafts arranged vperpendicular to the axis of said control surface bearing and said pistons and cylinders being angled with respect to each other to minimize space requirements whereby said control surface is operated in a push-push arrangement.
  • control surface is in a first folded position during launching of said missile and in a second flight position after launch of said missile and erection means within said housing for moving said control surface from the first to the second position.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Actuator (AREA)
  • Transmission Devices (AREA)

Abstract

The present invention comprises a control surface actuation system capable of disposition within a restricted volume. The present actuation system and control surface is disposed outboard of the missile due to space limitations imposed by an unusually large nozzle diameter. The system comprises four independent electro-hydraulic actuators of the push-push configuration for driving four aerodynamic control surfaces arranged in cruciform and disposed at the aft end of the missile. The actuation system arrangement allows passage of the missile through existing launchers having typical volume restraints.

Description

United States Patent Carver Jan. 16, 1973 OUTBOARD MISSILE CONTROL SURFACE AND ACTUATOR August B. Carver, Wheaton, Md.
Assignee: The United States of America as represented by the Secretary of the Navy Filed: April 20, 1971 Appl. No.: 135,737
Inventor:
US. Cl ..244/3.21, 244/324 Int. Cl. ..F42b 15/16, F42b 15/02 Field of Search ..244/3.2l, 3.22, 3.24, 3.27,
References Cited UNITED STATES PATENTS Bell et a1 ..244/3.24 X Jaffe ..244/3.2l X
3,l72,332 3/1965 Strickland ..92/72 X Primary ExaminerBenjamin A. Borchelt Assistant ExaminerJames M. Hanley Att0rneyR. S. Sciascia and Thomas 0. Watson, Jr.
57 ABSTRACT The present invention comprises a control surface actuation system capable of disposition within a restricted volume. The present actuation system and control surface is disposed outboard of the missile due to space limitations imposed by an unusually large nozzle diameter. The system comprises four independent electro-hydraulic actuators of the push-push configuration for driving four aerodynamic control surfaces arranged in cruciform and disposed at the aft end of the missile. The actuation system arrangement allows passage of the missile through existing launchers having typical volume restraints.
6 Claims, 4 Drawing lFigures VIIA PATENTEUJAH 16 I975 INVENTOR. AUGUST 8. CARVER VA, 0, 424%,}.
ATTORNEY OUTBOARD MISSILE CONTROL SURFACE AND ACTUATOR STATEMENT OF GOVERNMENT INTEREST 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.
BACKGROUND OF THE INVENTION This invention relates to aerodynamic control surfaces for missiles and more particularly relates to an aerodynamic control surface and actuating system which is completely external to the missile.
Thrust requirements for a number of recently proposed missile systems have necessitated the use of much larger nozzles than in the past. The increased size of the nozzles results in an constricted volume in the aft end of the missile thereby preventing the use of inboard control surface actuation systems of conventional design. The increased nozzle size resulting in severely constricted volume dictates the need for an actuation system and control surface which can be mounted on the external portion of the missile and not exceed the pass-through envelope of existing launchers. Present hydraulic systems are not susceptible to exterior mounting on missiles because they take up too much space. Systems which have folding control surfaces are also available. These systems have internal hydraulic actuators not suitable for external mounting. Other folding control surface systems are mechanically operated and are not as efficient as hydraulic systems and not capable of taking high bending moment loads. The present invention overcomes these difficulties by providing an in line or series connected hydraulic actuator system.
SUMMARY OF THE INVENTION The purpose of this invention is to provide a hydraulically operated actuation system which can be mounted on the exterior portion of a missile within an restricted volume while still providing a highly efficient system useful with standard restricted volume launchers.
A compact control surface and actuation system capable of disposition within a restricted volume is provided by mounting a push-push hydraulic system in a line parallel to the longitudinal axis of the missile body and utilizing folding control surfaces. The system is comprised of four independent electro-hydraulic actuators of the push-push configuration for driving four aerodynamic control surfaces arranged in cruciform and disposed at the aft end of the missile. This system provides control surface movement within a normally required i limits while still conforming to the space limitations imposed by unusuallylarge nozzle diameters.
It is an object of the present invention to provide a control surface and actuation system which can be mounted on the external surface ofa missile.
It is a further object of the present invention to provide a control surface and actuation system which can conform to the space limitations imposed by large nozzle diameter missiles.
Yet another object of the present invention is to provide a control surface and actuation system for use with large nozzle missiles which allows passage through standard launchers having typical volume restraints.
Other objects, advantages and novel features of the invention will become apparent from the following detailed description of the invention when considered in conjunction with the accompanyingv drawings.
BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a top view of a portion of the missile showing the control surface in an erect position.
FIG. 2 is an axial half-section taken through the aft end of the missile at line 22 and the control surface actuation system.
FIG. 3 is a section taken through the aft end of and perpendicular to the longitudinal axis of the missile illustrating the control surface in the folded position.
FIG. 4 is a section taken through the line 4-4 of FIG. 3 and illustrating the hydraulic actuators and midpanel support bearing.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT Referring now to FIG. 2 a missile is seen generally at 1 having a nozzle throat section 3 which comprises a large proportion of the volume within the main body 5 of the missile. Recently designed missiles have a throat 3 which is greater than percent of the body diameter 5. As can readily be seen at 7 the remaining volume within the main body of the missile 5 is insufficient to house an inboard control surface actuation system. The present invention provides a control surface actuation system generally indicated at 11 which is housed substantially within a spar housing 31 which is an extension of a dorsal fin 33 disposed along the main body 5 of the missile. The actuation system 11 includes push-push hydraulic actuators 13, a mid-panel. support bearing 15, hydraulic servo valve 17, and an electric motor/hydraulic pump combination 19 which is arranged in series as shown. The control surface 21 surmounts the spar housing 31 and is mechanically connected with the actuation system 11 through the mid-panel support hearing 15. The support bearing 15 has a shaft portion 16 one end of which is operably joined to the control surface 21. Needle bearings 14 at the end of shaft 16 also provide movable support for control surface 21. Further, the bearing 15 has an enlarged disc portion 18 which mechanically engages piston 39 through shaft 35 of the push-push hydraulic actuators 13.
In FIG. 4 the actuators 13 are seen to comprise cylinders 37 in which pistons 39 are caused to operate under the influence of the electric motor/hydraulic pump combination 19, which influence is directed through the hydraulic servo valve 17. Ports (not shown) drilled in the spar housing 31 connect the servo valve 17 to the pump combination 19 in the conventional manner. The piston shafts 35 are joined to opposite sides of enlarged disc portion 18 of the support bearing 15 and control the rotational movement of the control surface 21 within a normally required i40 limits. The cylinders 27 are pidgeon-toed, i.e., angled, to keep within the restricted volume of the spar housing 31.
Because of space limitations in spar housing 31 two motors were required in the electric motor/hydraulic pump combination 19. A single motor which could operate the control surface 21 under bending movements up to 4,000 lbs. and still meet the space limitations is not available. Therefore the system with dual motors on either side of the pump was devised.
Positional control of the push-push hydraulic actuators 13 is accomplished through normal electro/mechanical servo arrangements (not shown) which are directed by a position feed-back potentiometer (not shown) mechanically linked to the control surface through the support bearing 15.
In FIG. 3 the control surface 21 is illustrated in its folded position to permit launching through standard GMLS MK ll or MK 13 launchers. Fin erection mechanisms associated with said launchers (not shown) provide erecting force for the control surface 21 and a lock-pin mechanism (FIG. 2) provides positive locking of the control surface 21 in the flight position. In FIG. 2 the lock-pin mechanism is seen to comprise in part, a locking pin 27 and a hinge pin 29. Locking pin 27 is forced into a locking position by a spring 28 when the control surface 21 reaches upright position. This type of erection and locking mechanism is conventional. In FIG. 3 the pass-through envelope of the standard launchers mentioned above is indicated by the phantom line 43. With the control surface 21 folded against the main body 5 the missile is in the prelaunch configuration.
In operation the actuation system 11 varies the pitch angle of the movable control surface 21 which is shown in the erect position in FIG. 1. Four of these systems 11 independently drive one each of four control surfaces 21 arranged in cruciform and located at the aft end of the missile. The usual servo arrangements (not shown) operates the electric motor/hydraulic pump combination 19, which influence is directed through the hydraulic servo valve 17 to provide the pushing force on piston 39 and thereby rotate the control surface 21 to guide the flight path of the missile. Each of the control surfaces 21 and actuation systems I] operate independently of the other to provide complete missile guidance. Control surface position is provided by a feedback potentiometer (not shown) mechanically linked to support bearing 15.
Thus there has been disclosed an actuator combination disposed externally of the missile body between the missile skin and the control surface which is capable of withstanding the bending moments imposed on the control surface. The outboard actuation system described herein is seen to provide effective control surface actuation while conforming to existing launcher limitations. Obviously many modifications and variations of the present invention are possible in light of the above teachings.
What is claimed is:
1. An externally mounted missile control system comprising:
a housing formed as an extension of a dorsal fin of a missile and adapted to be secured on the external surface of the missile;
a series connected hydraulic actuation system mounted in said housing in a line parallel to the axis of said missile including a dual electric motor and hydraulic pump combination;
a folding control surface mounted on said housing and supported by a rotatable bearing; means for rotating said control surface connected to said hydraulic actuation system; said rotating means comprising two hydraulic pistons and cylinders connected to opposite sides of said control surface by shafts; said pistons, cylinders and shafts arranged vperpendicular to the axis of said control surface bearing and said pistons and cylinders being angled with respect to each other to minimize space requirements whereby said control surface is operated in a push-push arrangement.
2. The apparatus of claim 1 wherein the hydraulic piston shafts are connected at points on said control surface bearing to rotate said control surface through a range of 3. The apparatus of claim 1 wherein said rotatable bearing has one end connected to said control surface and the other end has a disc portion thereon connected to said shafts.
4. The apparatus of claim 3 wherein said pistons and cylinders are arranged at an acute angle with respect to each other.
5. The apparatus of claim 1 wherein said control surface is in a first folded position during launching of said missile and in a second flight position after launch of said missile and erection means within said housing for moving said control surface from the first to the second position.
6. The apparatus of claim 1 wherein the central axis of the hydraulic cylinders lie in the same plane.

Claims (6)

1. An externally mounted missile control system comprising: a housing formed as an extension of a dorsal fin of a missile and adapted to be secured on the external surface of the missile; a series connected hydraulic actuation system mounted in said housing in a line parallel to the axis of said missile including a dual electric motor and hydraulic pump combination; a folding control surface mounted on said housing and supported by a rotatable bearing; means for rotating said control surface connected to said hydraulic actuation system; said rotating means comprising two hydraulic pistons and cylinders connected to opposite sides of said control surface by shafts; said pistons, cylinders and shafts arranged perpendicular to the axis of said control surface bearing and said pistons and cylinders being angled with respect to each other to minimize space requirements whereby said control surface is operated in a push-push arrangement.
2. The apparatus of claim 1 wherein the hydraulic piston shafts are connected at points on said control surface bearing to rotate said control surface through a range of + or - 40* .
3. The apparatus of claim 1 wherein said rotatable bearing has one end connected to said control surface and the other end has a disc portion thereon connected to said shafts.
4. The apparatus of claim 3 wherein said pistons and cylinders are arranged at an acute angle with respect to each other.
5. The apparatus of claim 1 wherein said control surface is in a first folded position during launching of said missile and in a second flight position after launch of said missile and erection means within said housing for moving said control surface from the first to the second position.
6. The apparatus of claim 1 wherein the cEntral axis of the hydraulic cylinders lie in the same plane.
US00135737A 1971-04-20 1971-04-20 Outboard missile control surface and actuator Expired - Lifetime US3711040A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13573771A 1971-04-20 1971-04-20

Publications (1)

Publication Number Publication Date
US3711040A true US3711040A (en) 1973-01-16

Family

ID=22469427

Family Applications (1)

Application Number Title Priority Date Filing Date
US00135737A Expired - Lifetime US3711040A (en) 1971-04-20 1971-04-20 Outboard missile control surface and actuator

Country Status (1)

Country Link
US (1) US3711040A (en)

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4296895A (en) * 1979-01-15 1981-10-27 General Dynamics Corporation Fin erection mechanism
US4418610A (en) * 1980-09-08 1983-12-06 The United States Of America As Represented By The Secretary Of The Navy Electrohydraulic control system
US4512537A (en) * 1973-08-10 1985-04-23 Sanders Associates, Inc. Canard control assembly for a projectile
US4532853A (en) * 1979-10-24 1985-08-06 The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland Fluid-powered actuators
US4592525A (en) * 1985-02-07 1986-06-03 The United States Of America As Represented By The Secretary Of The Army Counter-rotating folding wings
US4599044A (en) * 1985-01-07 1986-07-08 The United States Of America As Represented By The Secretary Of The Navy Electronic feedback area control system for TVC gas generator
US4655420A (en) * 1983-06-09 1987-04-07 The United States Of America As Represented By The Secretary Of The Air Force Low height fin control actuator
US4795110A (en) * 1986-12-30 1989-01-03 Sundstrand Corporation Flight control surface actuation lock system
US4884766A (en) * 1988-05-25 1989-12-05 The United States Of America As Represented By The Secretary Of The Air Force Automatic fin deployment mechanism
US5125596A (en) * 1989-05-23 1992-06-30 Cavalleri Robert J Fluid shielded movable strut for missile and rocket thrust vector control
US5762294A (en) * 1997-03-31 1998-06-09 The United States Of America As Represented By The Secretary Of The Army Wing deployment device
US5775636A (en) * 1996-09-30 1998-07-07 The United States Of America As Represented By The Secretary Of The Army Guided artillery projectile and method
US5816532A (en) * 1996-12-17 1998-10-06 Northrop Grumman Corporation Multiposition folding control surface for improved launch stability in missiles
US5950963A (en) * 1997-10-09 1999-09-14 Versatron Corporation Fin lock mechanism
US6092264A (en) * 1998-11-13 2000-07-25 Lockheed Martin Corporation Single axis fold actuator and lock for member
US6250584B1 (en) 1999-10-18 2001-06-26 Hr Textron, Inc. Missile fin locking mechanism
US6352217B1 (en) 2000-04-25 2002-03-05 Hr Textron, Inc. Missile fin locking and unlocking mechanism including a mechanical force amplifier
US7125058B2 (en) 2003-10-27 2006-10-24 Hr Textron, Inc. Locking device with solenoid release pin
US20070007383A1 (en) * 2005-02-11 2007-01-11 Hsu William W Techniques for controlling a fin with unlimited adjustment and no backlash
WO2010099228A1 (en) * 2009-02-24 2010-09-02 Blue Origin, Llc Bidirectional control surfaces for use with high speed vehicles, and associated systems and methods
US20100320329A1 (en) * 2009-02-24 2010-12-23 Blue Origin, Llc Launch vehicles with fixed and deployable deceleration surfaces, and/or shaped fuel tanks, and associated systems and methods
US20110017872A1 (en) * 2009-06-15 2011-01-27 Blue Origin, Llc Sea landing of space launch vehicles and associated systems and methods
US9079674B1 (en) 2009-09-18 2015-07-14 Blue Origin, Llc Composite structures for aerospace vehicles, and associated systems and methods
US9487308B2 (en) 2013-03-15 2016-11-08 Blue Origin, Llc Launch vehicles with ring-shaped external elements, and associated systems and methods
US20170343328A1 (en) * 2012-04-24 2017-11-30 Omnitek Partners Llc Very Low Power Actuation Devices
US10822122B2 (en) 2016-12-28 2020-11-03 Blue Origin, Llc Vertical landing systems for space vehicles and associated methods
US11300390B1 (en) 2018-03-05 2022-04-12 Dynamic Structures And Materials, Llc Control surface deployment apparatus and method of use

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3172332A (en) * 1961-05-01 1965-03-09 Thyco Engineering Corp Fluid operated motor
US3276332A (en) * 1963-09-03 1966-10-04 Daniel L Jaffe Hydraulic rotary actuator capable of taking high bending moments
US3403873A (en) * 1963-01-24 1968-10-01 Navy Usa Guided missile

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3172332A (en) * 1961-05-01 1965-03-09 Thyco Engineering Corp Fluid operated motor
US3403873A (en) * 1963-01-24 1968-10-01 Navy Usa Guided missile
US3276332A (en) * 1963-09-03 1966-10-04 Daniel L Jaffe Hydraulic rotary actuator capable of taking high bending moments

Cited By (42)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4512537A (en) * 1973-08-10 1985-04-23 Sanders Associates, Inc. Canard control assembly for a projectile
US4296895A (en) * 1979-01-15 1981-10-27 General Dynamics Corporation Fin erection mechanism
US4532853A (en) * 1979-10-24 1985-08-06 The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland Fluid-powered actuators
US4418610A (en) * 1980-09-08 1983-12-06 The United States Of America As Represented By The Secretary Of The Navy Electrohydraulic control system
US4655420A (en) * 1983-06-09 1987-04-07 The United States Of America As Represented By The Secretary Of The Air Force Low height fin control actuator
US4599044A (en) * 1985-01-07 1986-07-08 The United States Of America As Represented By The Secretary Of The Navy Electronic feedback area control system for TVC gas generator
US4592525A (en) * 1985-02-07 1986-06-03 The United States Of America As Represented By The Secretary Of The Army Counter-rotating folding wings
US4795110A (en) * 1986-12-30 1989-01-03 Sundstrand Corporation Flight control surface actuation lock system
US4884766A (en) * 1988-05-25 1989-12-05 The United States Of America As Represented By The Secretary Of The Air Force Automatic fin deployment mechanism
US5125596A (en) * 1989-05-23 1992-06-30 Cavalleri Robert J Fluid shielded movable strut for missile and rocket thrust vector control
US5775636A (en) * 1996-09-30 1998-07-07 The United States Of America As Represented By The Secretary Of The Army Guided artillery projectile and method
US5816532A (en) * 1996-12-17 1998-10-06 Northrop Grumman Corporation Multiposition folding control surface for improved launch stability in missiles
US5762294A (en) * 1997-03-31 1998-06-09 The United States Of America As Represented By The Secretary Of The Army Wing deployment device
US5950963A (en) * 1997-10-09 1999-09-14 Versatron Corporation Fin lock mechanism
US6092264A (en) * 1998-11-13 2000-07-25 Lockheed Martin Corporation Single axis fold actuator and lock for member
US6250584B1 (en) 1999-10-18 2001-06-26 Hr Textron, Inc. Missile fin locking mechanism
US6352217B1 (en) 2000-04-25 2002-03-05 Hr Textron, Inc. Missile fin locking and unlocking mechanism including a mechanical force amplifier
US7125058B2 (en) 2003-10-27 2006-10-24 Hr Textron, Inc. Locking device with solenoid release pin
US20070007383A1 (en) * 2005-02-11 2007-01-11 Hsu William W Techniques for controlling a fin with unlimited adjustment and no backlash
US7195197B2 (en) 2005-02-11 2007-03-27 Hr Textron, Inc. Techniques for controlling a fin with unlimited adjustment and no backlash
WO2010099228A1 (en) * 2009-02-24 2010-09-02 Blue Origin, Llc Bidirectional control surfaces for use with high speed vehicles, and associated systems and methods
US10518911B2 (en) * 2009-02-24 2019-12-31 Blue Origin, Llc Control surfaces for use with high speed vehicles, and associated systems and methods
US20100327107A1 (en) * 2009-02-24 2010-12-30 Blue Origin, Llc Bidirectional control surfaces for use with high speed vehicles, and associated systems and methods
US11649073B2 (en) 2009-02-24 2023-05-16 Blue Origin, Llc Control surfaces for use with high speed vehicles, and associated systems and methods
US8408497B2 (en) 2009-02-24 2013-04-02 Blue Origin, Llc Launch vehicles with fixed and deployable deceleration surfaces, and/or shaped fuel tanks, and associated systems and methods
US20100320329A1 (en) * 2009-02-24 2010-12-23 Blue Origin, Llc Launch vehicles with fixed and deployable deceleration surfaces, and/or shaped fuel tanks, and associated systems and methods
US8876059B2 (en) 2009-02-24 2014-11-04 Blue Origin, Llc Bidirectional control surfaces for use with high speed vehicles, and associated systems and methods
US8878111B2 (en) 2009-02-24 2014-11-04 Blue Origin, Llc Bidirectional control surfaces for use with high speed vehicles, and associated systems and methods
US8894016B2 (en) 2009-02-24 2014-11-25 Blue Origin, Llc Bidirectional control surfaces for use with high speed vehicles, and associated systems and methods
US8991767B2 (en) 2009-02-24 2015-03-31 Blue Origin, Llc Control surfaces for use with high speed vehicles, and associated systems and methods
US9580191B2 (en) 2009-02-24 2017-02-28 Blue Origin, Llc Control surfaces for use with high speed vehicles, and associated systems and methods
US8678321B2 (en) 2009-06-15 2014-03-25 Blue Origin, Llc Sea landing of space launch vehicles and associated systems and methods
US20110017872A1 (en) * 2009-06-15 2011-01-27 Blue Origin, Llc Sea landing of space launch vehicles and associated systems and methods
US9469418B1 (en) 2009-09-18 2016-10-18 Blue Origin, Llc Composite structures for aerospace vehicles, and associated systems and methods
US9079674B1 (en) 2009-09-18 2015-07-14 Blue Origin, Llc Composite structures for aerospace vehicles, and associated systems and methods
US20170343328A1 (en) * 2012-04-24 2017-11-30 Omnitek Partners Llc Very Low Power Actuation Devices
US10794673B2 (en) * 2012-04-24 2020-10-06 Omnitek Partners Llc Very low power actuation devices
US11243056B2 (en) * 2012-04-24 2022-02-08 Omnitek Partners Llc Very low power actuation devices
US9487308B2 (en) 2013-03-15 2016-11-08 Blue Origin, Llc Launch vehicles with ring-shaped external elements, and associated systems and methods
US10266282B2 (en) 2013-03-15 2019-04-23 Blue Origin, Llc Launch vehicles with ring-shaped external elements, and associated systems and methods
US10822122B2 (en) 2016-12-28 2020-11-03 Blue Origin, Llc Vertical landing systems for space vehicles and associated methods
US11300390B1 (en) 2018-03-05 2022-04-12 Dynamic Structures And Materials, Llc Control surface deployment apparatus and method of use

Similar Documents

Publication Publication Date Title
US3711040A (en) Outboard missile control surface and actuator
US6073880A (en) Integrated missile fin deployment system
US5806791A (en) Missile jet vane control system and method
US5505408A (en) Differential yoke-aerofin thrust vector control system
US3260205A (en) Fin actuated spin vane control device and method
CN108871103B (en) Time delay unfolding mechanism of small missile folding rudder piece
US8530809B2 (en) Ring gear control actuation system for air-breathing rocket motors
US20170146328A1 (en) Very Low-Power Actuation Devices
US11243056B2 (en) Very low power actuation devices
US6827310B1 (en) Apparatus and method for fin actuation in a portable missile
SE8600812D0 (en) AIRCRAFT WITH UBERKALIBRIGEM LEITWERK
EP2222551B1 (en) System and method for deployment and actuation
JP2020531339A (en) Operating system
US4143838A (en) Folding fin assembly detent
US6752060B1 (en) Missile launcher
US5398887A (en) Finless aerodynamic control system
US3136250A (en) Integrated auxiliary power unit
US4210298A (en) Electro-mechanical guidance actuator for a missile
WO2010036412A2 (en) Robotic manipulator
US7434762B2 (en) Retractable thrust vector control vane system and method
US3272124A (en) Solid propellant actuation system
US5235916A (en) Warhead directed-charge positioner system
CN114370790A (en) Ballistic two-dimensional correction mechanism
US4923142A (en) Gyroscopic stabilizing device for a projectile control instrument
KR102692544B1 (en) Driving apparatus for displacement movable and guided vehicle including the same