US20170158344A1 - Unlocking apparatus for a ram air turbine actuator - Google Patents

Unlocking apparatus for a ram air turbine actuator Download PDF

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Publication number
US20170158344A1
US20170158344A1 US15/368,209 US201615368209A US2017158344A1 US 20170158344 A1 US20170158344 A1 US 20170158344A1 US 201615368209 A US201615368209 A US 201615368209A US 2017158344 A1 US2017158344 A1 US 2017158344A1
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US
United States
Prior art keywords
unlocking
actuator
locking
follower element
recess
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
Application number
US15/368,209
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English (en)
Inventor
Tomasz Janisiow
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.)
Hamilton Sundstrand Corp
Original Assignee
Hamilton Sundstrand Corp
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 Hamilton Sundstrand Corp filed Critical Hamilton Sundstrand Corp
Publication of US20170158344A1 publication Critical patent/US20170158344A1/en
Priority to US16/577,135 priority Critical patent/US11021262B2/en
Abandoned legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D41/00—Power installations for auxiliary purposes
    • B64D41/007—Ram air turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H25/00—Gearings comprising primarily only cams, cam-followers and screw-and-nut mechanisms
    • F16H25/18—Gearings comprising primarily only cams, cam-followers and screw-and-nut mechanisms for conveying or interconverting oscillating or reciprocating motions

Definitions

  • This disclosure relates to unlocking apparatus and in particular to an unlocking apparatus for an actuator, more particularly, but not exclusively, a ram air turbine (RAT) actuator.
  • RAT ram air turbine
  • Ram air turbines are used in aircraft to provide electric and/or hydraulic power to components of the aircraft, for example in the event of failure of other electrical or hydraulic power generating equipment on board the aircraft.
  • the RAT In normal operation of the aircraft, the RAT is housed within the aircraft, but when needed it is extended into the airflow around the aircraft such that it may turn and generate electrical and/or hydraulic power.
  • the RAT is typically pivoted into position by means of an actuator, for example a hydraulic actuator.
  • the actuator typically includes a piston which extends to deploy the RAT.
  • the actuator has a lock mechanism which prevents inadvertent movement of the piston and thus inadvertent deployment of the RAT.
  • the locking mechanism typically comprises a spring loaded lock piston which must be moved in an axial direction to unlock the actuator. Such a mechanism is disclosed for example in US 2013/0327207 A1.
  • the unlocking mechanism comprises a two link, knee type linkage, one end of which is rotatably coupled to one end of the locking piston and the other end of which is axially fixed and rotatably coupled to a support.
  • a linear solenoid moves the linkage between a locked and an unlocked position.
  • the linkage must go “over centre” and initially displace the lock piston against the force of the lock piston spring, which means that a relatively large solenoid may be necessary.
  • an apparatus for unlocking an actuator comprising:
  • the unlocking member may be generally cylindrical in shape, whereby the surface of the first member may be generally cylindrical in shape.
  • the cylindrical shape may have a generally circular cross section.
  • the recess may comprise a circumferentially extending groove in the surface of the unlocking member.
  • a pair of recesses separated by a section of the unlocking member surface may be provided.
  • the unlocking member may be spring biased into its first position by one or more springs, for example one or more coil springs.
  • the coil spring may be mounted around a portion of the first member.
  • the unlocking member may be provided with a circumferentially extending flange, and the spring be arranged between the flange and a fixed part.
  • a pair of flanges may be provided at opposed end portions of the unlocking member.
  • a pair of unlocking actuators may be provided for moving the unlocking member.
  • the unlocking actuator or actuators may be a solenoid or solenoids.
  • the unlocking member may be mounted in a bore of the housing, and the solenoid or solenoids mounted around the unlocking member to support the unlocking member in the housing.
  • the unlocking member may be substantially symmetrical about a central transverse axis.
  • the apparatus may further include the second member.
  • the disclosure therefore also provides an apparatus for unlocking an actuator, the apparatus comprising:
  • the follower element of the second member may be a roller.
  • the apparatus may further comprise a biasing spring for biasing the follower element into contact with the unlocking member.
  • the disclosure also extends to an actuator comprising an unlocking apparatus as described above.
  • the actuator may comprise a locking rod axially movable between a locking and an unlocking position, and the second member of the locking apparatus may be coupled to an end of the locking rod such that movement of the follower element of the second member into the recess of the unlocking member allows the locking rod to move to its unlocking position.
  • the actuator may further comprise a spring for biasing the locking rod towards the unlocking member, that spring providing the biasing for the second member.
  • the actuator may be a ram air turbine actuator.
  • the disclosure also extends to a method of unlocking an actuator comprising moving a first, unlocking member along an axis from a first position in which a follower element of a second member coupled to the actuator and biased into engagement with the first member engages a surface of the first member and a second position in which the follower element is at least partially received within a recess in the surface of the first member.
  • FIG. 1 illustrates a ram air turbine (RAT)
  • FIG. 2 illustrates a partial view of a locking mechanism for a RAT actuator
  • FIG. 3 shows a part cut away view of phantom perspective view of a further part of the locking mechanism
  • FIG. 4 shows a cross sectional view of the mechanism of FIG. 3 ;
  • FIGS. 5A and 5B illustrate a schematic cross sectional view of the locking mechanism in locked and unlocked configuration respectively.
  • FIG. 1 illustrates an RAT system 10 which is secured to an aircraft structure 12 by a housing 14 .
  • the housing 14 pivotally supports a strut 16 having a turbine 18 at one end.
  • the turbine 18 includes blades 20 , which impart rotational drive to a generator 22 and hydraulic pump 30 for example.
  • An actuator 24 is secured to the strut at a first end 26 and to the housing at a second end 28 .
  • the actuator 24 is illustrated in its deployed position.
  • the actuator 24 comprises a cylinder 32 which is biased by a spring 34 in order to deploy the strut 16 .
  • a spring 34 in order to deploy the strut 16 .
  • the locking mechanism comprises a locking piston or bolt 38 which is received slidably within a sleeve 40 .
  • the locking piston 38 is biased to the right in the sense of FIG. 2 by means of a biasing spring 42 which extends between a seat 44 provided on the locking piston 38 and a seat 46 provided on the sleeve 40 .
  • the extensible cylinder 32 of the actuator is slidably mounted around the sleeve 40 . Extension of the cylinder 32 is prevented by locking elements 48 mounted at the end of the sleeve. In the locking position, respective shoulders 50 , 52 of the cylinder 32 and locking wedges 48 engage to prevent axial movement of the cylinder 32 .
  • a number of rollers 54 are mounted in the distal end 56 of the locking piston 38 .
  • the wedges 48 may displace in the direction of arrows 60 thereby disengaging the shoulders 50 , 52 and allowing the cylinder 32 to extend to deploy the RAT.
  • This unlocking movement of the locking piston 38 is made possible by means of an unlocking apparatus 60 which will be described with reference to FIGS. 3 to 5 .
  • the apparatus 60 comprises a first, unlocking member 62 and a second member 64 .
  • the first member 62 is mounted for longitudinal movement along an axis A in a bore 66 of a housing 68 .
  • the housing 68 will be fixed in a suitable manner to the housing of the actuator 24 .
  • member as used herein is not limited to unitary elements, and embraces both unitary elements and assemblies.
  • the apparatus 60 further comprises a pair of unlocking actuators 70 , 72 , in this embodiment in the form of solenoid actuators 70 , 72 , which are fixedly mounted, for example press fit, in respective counterbores 74 , 76 in the housing 68 around the first member 62 .
  • the solenoid actuators 70 , 72 move the first member 62 between first and second longitudinal positions relative to the housing 68 .
  • the solenoid actuators 70 , 72 are arranged to provide a movement of the first member 62 in the same direction.
  • One solenoid actuator in effect acts as a back up for the other to provide a degree of redundancy in the system. In some embodiments, where safety may not be of such a concern, only one solenoid actuator 70 , 72 need be provided.
  • the first member 62 is a generally cylindrical shaft member having a longitudinally extending surface 78 .
  • the first member 62 is generally circular in cross section, but other shaft cross sections may be used in accordance with the disclosure.
  • the longitudinally extending surface 78 comprises two end surface portions 82 , 84 which are received within the respective solenoids 70 , 72 and by which the first member 62 are supported in the housing bore 66 .
  • the member 62 may be supported by other means.
  • using the solenoids 70 , 72 will potentially be more cost effective and allow better control of tolerances.
  • the first member 62 further comprises a pair of circumferentially extending flanges 86 , 88 which extend radially outwardly from the inner end of the respective end surface portions 82 , 84 .
  • a pair of recesses in the form of circumferentially extending annular grooves 90 , 92 which are separated by an intermediate, central longitudinally extending surface portion 94 .
  • the grooves 90 , 92 are is formed such that there is a relatively abrupt, rather than gradual, transition between the intermediate longitudinally extending surface portion 94 and the grooves 90 , 92 .
  • the grooves 90 , 92 extend completely around the circumference of the first member 62 , but this is not essential.
  • the first member 62 is substantially symmetrical about a central transverse axis. This is not essential, however, and it would be possible in other embodiments to provide just a single flange 86 and a single groove 92 . However, by duplicating these features as shown, it may facilitate assembly of the apparatus as the apparatus will function properly whichever way around the first member 62 is mounted in the housing bore 66 .
  • a biasing member in this embodiment a coil spring 96 , is arranged between one of the flanges 86 and an inner, fixed part 98 of the solenoid 72 and biases the first member 62 to the position shown in FIGS. 3, 4 and 5A .
  • One or more stop members may be provided to ensure that the first member does not overshoot the position.
  • other forms of biasing spring may be provided.
  • the second member 64 comprises a follower element 100 in the form of a roller.
  • the follower element 100 need not be a roller, but a roller may be advantageous in that it reduces frictional forces between the first and second members 62 , 64 .
  • the roller 100 is rotatably supported on a shaft 102 supported by a yoke 104 .
  • a mounting pin or rod 106 extends from the yoke 104 and, as shown in FIG. 2 , is mounted at one end of the locking piston 38 .
  • the follower 100 will therefore be biased into contact with the central surface portion 94 of the first member 62 by virtue of the biasing spring 42 of the locking mechanism 36 .
  • the apparatus 60 may be assembled by inserting the first member 62 , with the spring 96 arranged over end portion 82 into the housing bore 66 and then mounting the solenoids 70 , 72 over the end portions 82 , 84 of the first member and retaining the solenoids 70 , 72 in the housing counterbores 74 , 76 by suitable means.
  • FIGS. 3, 4 and 5A show the apparatus 60 in a locked position. In this position, the roller 100 of the second member 64 is resiliently biased against the central surface portion 94 of the first member 62 by means of the biasing spring 42 of the actuator 24 .
  • unlocking actuators 70 , 72 When it is desired to unlock the actuator 24 to allow deployment of the strut 16 , power is supplied to the unlocking actuators 70 , 72 . Both unlocking actuators 70 , 72 produce a movement of the first member 62 in the same direction, namely to the right in the sense of FIG. 4 . The first member 62 then moves against the force of the spring 96 towards the position shown in FIG. 5B so as to allow the roller 100 of the second member 62 to move along the central surface portion 94 and, under the biasing effect of actuator biasing spring 42 , into the groove 92 . Movement of the first member 62 beyond the position shown in FIG. 5B may be prevented by a stop (not shown). Since the transition between the groove 92 and the central surface portion 94 is relatively abrupt, the roller element 100 will move into the groove 92 relatively rapidly, allowing a rapid, rather than gradual, unlocking movement.
  • the movement of the second member 64 allows the locking piston 38 to move in an unlocking direction sufficiently to move the rollers 56 of the locking piston 38 out of alignment with the locking surfaces of the locking wedges 48 , thereby allowing deployment of the actuator cylinder 32 .
  • the only forces which need to be overcome in order to effect this unlocking are the biasing forces of the spring 96 and any frictional forces between the first and second members 62 , 64 .
  • the use of a roller element 100 minimises frictional forces.
  • the relative forces of the actuator biasing spring 42 and the spring 96 on the first member 62 are such that when the power supply is discontinued to the solenoids 70 , 72 , the roller 100 remains engaged in the groove 92 .
  • a user may push on the end portion of the first member 62 via suitable means.
  • roller element 100 may be replaced by a low friction element which will slide, rather than roll, on the central surface portion 94 of the first member 62 .
  • the apparatus may comprise just a single unlocking solenoid 72 where redundancy is not required, and the first member need only be provided with just a single flange 86 and groove 92 .
  • an unlocking movement of a lock release element for example a locking piston
  • a lock release element for example a locking piston
  • the embodiments also provide, a number of advantages over the prior art “knee” arrangement. Firstly, the apparatus may use substantially fewer, and less complex components. Moreover, precise shimming of the knee to ensure proper operation is not required, with greater tolerances being accommodated within the apparatus.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Actuator (AREA)
US15/368,209 2015-12-04 2016-12-02 Unlocking apparatus for a ram air turbine actuator Abandoned US20170158344A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US16/577,135 US11021262B2 (en) 2015-12-04 2019-09-20 Unlocking apparatus for a ram air turbine actuator

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP15461580.1 2015-12-04
EP15461580.1A EP3176094B1 (fr) 2015-12-04 2015-12-04 Appareil de déverrouillage pour un actionneur de turbine à air dynamique

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US16/577,135 Continuation US11021262B2 (en) 2015-12-04 2019-09-20 Unlocking apparatus for a ram air turbine actuator

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US20170158344A1 true US20170158344A1 (en) 2017-06-08

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US16/577,135 Active 2037-02-17 US11021262B2 (en) 2015-12-04 2019-09-20 Unlocking apparatus for a ram air turbine actuator

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160332744A1 (en) * 2015-01-16 2016-11-17 Hamilton Sundstrand Corporation Rat mounting arrangement for a soft aircraft interface
EP3461745A1 (fr) * 2017-09-28 2019-04-03 UTC Aerospace Systems Wroclaw Sp. z o.o. Mécanisme de libération pour actionneur de turbine à air dynamique
US20190329900A1 (en) * 2018-04-30 2019-10-31 Hamilton Sundstrand Corporation Hybrid ram air turbine with in-line hydraulic pump and generator

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3112270B1 (fr) * 2015-06-29 2019-09-04 Hamilton Sundstrand Corporation Mécanisme de déverrouillage pour actionneur de turbine à air dynamique

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3584544A (en) 1968-07-22 1971-06-15 Robert W Haberman Locking mechanism
US4392556A (en) 1978-08-25 1983-07-12 Arkwin Industries, Inc. Actuator locking device
DE10230953A1 (de) * 2002-07-10 2004-01-22 Aug. Winkhaus Gmbh & Co. Kg Sperrmechanismus, insbesondere für einen Schließzylinder
US6948685B2 (en) 2003-10-27 2005-09-27 Hr Textron, Inc. Locking device with solenoid release pin
JP4240514B2 (ja) 2004-02-24 2009-03-18 本田技研工業株式会社 直動アクチエータ
DE102004039531A1 (de) * 2004-08-14 2006-02-23 Aug. Winkhaus Gmbh & Co. Kg Sperrmechanismus
US8640563B2 (en) 2011-05-25 2014-02-04 Hamilton Sundstrand Corporation Ram air turbine deployment actuator
US9511875B2 (en) 2012-06-06 2016-12-06 Hamilton Sundstrand Corporation Electromechanical actuator damping arrangement for ram air turbine
US9399522B2 (en) 2014-02-20 2016-07-26 Hamilton Sundstrand Corporation Ram air turbine actuator

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160332744A1 (en) * 2015-01-16 2016-11-17 Hamilton Sundstrand Corporation Rat mounting arrangement for a soft aircraft interface
US9878800B2 (en) * 2015-01-16 2018-01-30 Hamilton Sundstrand Corporation Rat mounting arrangement for a soft aircraft interface
EP3461745A1 (fr) * 2017-09-28 2019-04-03 UTC Aerospace Systems Wroclaw Sp. z o.o. Mécanisme de libération pour actionneur de turbine à air dynamique
US11014685B2 (en) 2017-09-28 2021-05-25 Hamilton Sunstrand Corporation Release mechanism
US20190329900A1 (en) * 2018-04-30 2019-10-31 Hamilton Sundstrand Corporation Hybrid ram air turbine with in-line hydraulic pump and generator
US10661913B2 (en) * 2018-04-30 2020-05-26 Hamilton Sundstrand Corporation Hybrid ram air turbine with in-line hydraulic pump and generator

Also Published As

Publication number Publication date
EP3176094B1 (fr) 2019-02-06
US20200079523A1 (en) 2020-03-12
EP3176094A1 (fr) 2017-06-07
US11021262B2 (en) 2021-06-01

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