US10385784B2 - Clevis link for toggle mechanism of ram air turbine actuator - Google Patents

Clevis link for toggle mechanism of ram air turbine actuator Download PDF

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Publication number
US10385784B2
US10385784B2 US15/068,151 US201615068151A US10385784B2 US 10385784 B2 US10385784 B2 US 10385784B2 US 201615068151 A US201615068151 A US 201615068151A US 10385784 B2 US10385784 B2 US 10385784B2
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Prior art keywords
hole
parallel
holes
clevis
pivot holes
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US15/068,151
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US20170260906A1 (en
Inventor
Stephen Michael Bortoli
Paul Henry Verstrate
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Hamilton Sundstrand Corp
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Hamilton Sundstrand Corp
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Priority to US15/068,151 priority Critical patent/US10385784B2/en
Assigned to HAMILTON SUNDSTRAND CORPORATION reassignment HAMILTON SUNDSTRAND CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BORTOLI, STEPHEN MICHAEL, VERSTRATE, PAUL HENRY
Priority to FR1751966A priority patent/FR3048676B1/fr
Publication of US20170260906A1 publication Critical patent/US20170260906A1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/32—Arrangement, mounting, or driving, of auxiliaries
    • 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
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C7/00—Connecting-rods or like links pivoted at both ends; Construction of connecting-rod heads
    • F16C7/02—Constructions of connecting-rods with constant length
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/34—Application in turbines in ram-air turbines ("RATS")
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/50—Kinematic linkage, i.e. transmission of position

Definitions

  • the subject matter disclosed herein generally relates to ram air turbine actuators, and more specifically to devises for use in a toggle mechanism of a ram air turbine (RAT) actuator.
  • RAT ram air turbine
  • RATs are commonly used on modern aircraft to provide a secondary and/or emergency power source in the event the primary power source is insufficient or fails.
  • a typical RAT includes a turbine that remains internal to the aircraft until needed. When additional power is required, a door in the aircraft's fuselage will open and the actuator will deploy the RAT's turbine into the freestream air. The turbine is rotated by the freestream air and the rotational torque from the turbine is transferred through a drivetrain to be converted into electrical power by a generator.
  • a RAT may also be used to drive a hydraulic pump.
  • a toggle mechanism internal to a RAT actuator may act as an over center mechanism to initiate the actuation process.
  • solenoids pull on a cross rod, which turns over a clevis to move the toggle mechanism past its over center position. This motion then allows the actuator to actuate and deploy the RAT.
  • the cross rod and clevis experience loading from the solenoids and also back loading from internal components of the actuator. Accordingly, clevis and cross rod capable of withstanding the loading, while being easy to install and maintain would provide both cost and reliability benefits.
  • a clevis for use in a toggle mechanism of a ram air turbine actuator.
  • the clevis comprises a first side and a second side parallel to the first side.
  • the second side rigidly connected to the first side via at least one brace perpendicular to the first side and the second side.
  • the clevis also comprises a first set of parallel pivot holes. A first hole of the first set of parallel pivot holes being located in the first side and a second hole of the first set of parallel pivot holes being located in the second side.
  • the clevis further comprises a second set of parallel pivot holes. A first hole of the second set of parallel pivot holes being located in the first side and a second hole of the second set of parallel pivot holes being located in the second side.
  • the clevis yet further comprises a set of parallel through holes.
  • a first hole of the set of parallel through holes being located in the first side and a second hole of the set of parallel through holes being located in the second side.
  • the clevis also further comprises a helicoil blind hole. The helicoil blind hole being located in the first side and extending into the at least one brace.
  • further embodiments of the clevis may include that the second hole of the first set of parallel pivot holes is a blind hole, wherein the blind hole opens towards the first side.
  • a toggle mechanism of a ram air turbine actuator comprising a clevis.
  • the clevis includes a first side and a second side parallel to the first side. The second side rigidly connected to the first side via at least one brace perpendicular to the first side and the second side.
  • the clevis also includes a first set of parallel pivot holes. A first hole of the first set of parallel pivot holes being located in the first side and a second hole of the first set of parallel pivot holes being located in the second side.
  • the clevis further includes a second set of parallel pivot holes. A first hole of the second set of parallel pivot holes being located in the first side and a second hole of the second set of parallel pivot holes being located in the second side.
  • the clevis yet further includes a set of parallel through holes. A first hole of the set of parallel through holes being located in the first side and a second hole of the set of parallel through holes being located in the second side.
  • the clevis also further includes a helicoil blind hole. The helicoil blind hole being located in the first side and extending into the at least one brace.
  • the toggle mechanism also comprises a cross rod operably connected to the clevis and located in the set of parallel through holes.
  • the toggle mechanism further comprises a cap screw located in the helicoil blind hole. The cap screw securing the cross rod to the clevis.
  • toggle mechanism may include that the second hole of the first set of parallel pivot holes is a blind hole, wherein the blind hole opens towards the first side.
  • toggle mechanism may include that the cross rod has a first section, a second section, and a midsection between the first section and the second section, the midsection includes a flange having a through hole.
  • further embodiments of the toggle mechanism may include that the first section has a first diameter, the second section has a second diameter, and the midsection has a third diameter, the third diameter being larger than at least one of the first diameter and the second diameter.
  • toggle mechanism may include that the midsection includes a clearance notch.
  • toggle mechanism may include a lock piston operably connected to the clevis through a link, the link being operably connected to the first set of parallel pivot holes via a pivot pin, wherein the pivot pin is secured in the first set of parallel pivot holes by the flange.
  • toggle mechanism may include a bracket operably connected to the clevis at the second set of parallel pivot holes via a biasing mechanism.
  • toggle mechanism may include that the cap screw secures the cross rod to the clevis via the through hole.
  • a method of manufacturing a toggle mechanism of a ram air turbine actuator comprises forming a first side of a clevis; forming a second side of a clevis; and rigidly connecting the second side to the first side via at least one brace perpendicular to the first side and the second side.
  • the first side being parallel to the second side.
  • the method also comprises forming a first set of parallel pivot holes. A first hole of the first set of parallel pivot holes being located in the first side and a second hole of the first set of parallel pivot holes being located in the second side.
  • the method further comprises forming a second set of parallel pivot holes.
  • a first hole of the second set of parallel pivot holes being located in the first side and a second hole of the second set of parallel pivot holes being located in the second side.
  • the method yet further comprises forming a set of parallel through holes. The first hole of the set of parallel through holes being located in the first side and a second hole of the set of parallel through holes being located in the second side.
  • the method also comprises drilling a helicoil blind hole. The helicoil blind hole being located in the first side and extending into the at least one brace.
  • the method further comprises inserting a cross rod into the set of parallel through holes within the clevis and installing a cap screw in the helicoil blind hole. The cap screw securing the cross rod to the clevis.
  • further embodiments of the method may include that the second hole of the first set of parallel pivot holes is a blind hole, wherein the blind hole opens towards the first side.
  • further embodiments of the method may include that the cross rod has a first section, a second section, and a midsection between the first section and the second section, the midsection includes a flange having a through hole.
  • further embodiments of the method may include that the first section has a first diameter, the second section has a second diameter, and the midsection has a third diameter, the third diameter being larger than at least one of the first diameter and the second diameter.
  • further embodiments of the method may include that the midsection includes a clearance notch.
  • further embodiments of the method may include operably connecting a lock piston to the clevis through a link, the link being operably connected to the first set of parallel pivot holes via a pivot pin, wherein the pivot pin is secured in the first set of parallel pivot holes by the flange.
  • further embodiments of the method may include operably connecting a bracket to the clevis at the second set of parallel pivot holes via a biasing mechanism.
  • FIG. 1 is a perspective view of an aircraft that may incorporate embodiments of the present disclosure
  • FIG. 2 is a perspective view of ram air turbine (RAT) assembly that may incorporate embodiments of the present disclosure
  • FIG. 3 is a cross-sectional side view of an actuator for use in the RAT assembly of FIG. 2 , according to an embodiment of the present disclosure
  • FIG. 4 is an enlarged cross-sectional top view of the actuator of FIG. 3 , according to an embodiment of the present disclosure
  • FIG. 5 is a schematic illustration of a toggle mechanism for use in the actuator of FIG. 3 , according to an embodiment of the present disclosure
  • FIG. 6 is a schematic illustration of an alternate toggle mechanism capable of being using in the actuator of FIG. 3 ;
  • FIG. 7 is a schematic illustration of a cross rod for use in the toggle mechanism of FIG. 5 , according to an embodiment of the present disclosure
  • FIG. 8 is a schematic illustration of an alternate cross rod for use in the alternate toggle mechanism of FIG. 6 ;
  • FIG. 9 is a schematic cross-sectional illustration of a cross rod and clevis assembly for use in the toggle mechanism of FIG. 5 , according to an embodiment of the present disclosure.
  • FIG. 10 is a schematic cross-sectional illustration of an alternate cross rod and alternate clevis assembly for use in the toggle mechanism of FIG. 6 .
  • Second wing 18 extends from a second root portion (not shown) to a second tip portion 31 through a second airfoil portion 33 .
  • Second airfoil portion 33 includes a leading edge 35 and a trailing edge 36 .
  • Tail portion 8 includes a stabilizer 38 .
  • Aircraft 2 includes a ram air turbine (RAT) assembly 40 mounted within fuselage 4 or nose portion 6 .
  • RAT ram air turbine
  • the RAT assembly 40 may include a turbine assembly 42 , a gearbox assembly 44 , a shaft assembly 48 , a generator 46 , and the actuator 50 .
  • the turbine assembly 42 rotates, the rotational torque is transferred from the turbine assembly 42 , through the gearbox assembly 44 to a driveshaft (not shown) in the strut assembly 48 , and then to the generator 46 .
  • the generator 46 may be an electrical generator, hydraulic pump, or both an electrical generator and a hydraulic pump.
  • the link 120 shifts and subsequently allows the lock piston 110 to translate in direction X.
  • the lock piston 110 had been originally preloaded to translate in direction X but was previously prevented from translating by the link 120 .
  • the motion of the lock piston 110 activates the actuator 50 , and thus as the lock piston 110 completes its motion, the actuator 50 begins translating the rod end 52 in direction X.
  • the motion of the rod end will deploy and/or retract the RAT (e.g. RAT assembly 40 as shown in FIG. 2 ).
  • the force generated by the solenoids 60 imparts a large bending force on the cross rod 300 .
  • the preload on the lock piston 110 also imparts a large bending force on the cross rod 300 .
  • FIG. 5 shows a schematic illustration of a toggle mechanism 100 for use in the actuator 50 of FIG. 3 , according to an embodiment of the present disclosure.
  • FIG. 7 shows a schematic illustration of a cross rod 300 for use in the toggle mechanism 100 of FIG. 5 , according to an embodiment of the present disclosure.
  • the toggle mechanism 100 includes a clevis 200 and a cross rod 300 operably connected to the clevis 200 .
  • the cross rod 300 having a first section 310 , a second section 320 , and a midsection 330 between the first section 310 and the second section 320 .
  • the flange 340 and the through hole 350 may be formed in a variety of different manors including but not limited to molding, machining and drilling.
  • the midsection 330 also includes a clearance notch 360 .
  • the clearance notch 360 allows the cross rod 300 to avoid hitting the link 120 when lock piston 110 translates.
  • the lock piston 110 may be operably connected to the clevis 200 via the link 120 .
  • the lock piston 110 may be operably connected to the link 120 via a pin 182 .
  • the clevis 200 includes a first side 200 a , a second side 200 b parallel to the first side 200 a , the second side 200 b rigidly connected to the first side 200 a via at least one brace (e.g. 200 c & 200 d of FIG. 10 ) perpendicular to the first side 200 a and the second side 200 b .
  • the clevis 200 also includes a first set of parallel pivot holes 210 . A first hole 210 a of the first set of parallel pivot holes 210 being located in the first side 200 a and a second hole 210 b of the first set of parallel pivot holes 210 being located in the second side 200 b .
  • the clevis 200 also includes a helicoil blind hole 240 .
  • the helicoil blind 240 hole being located in the first side 200 a and extending into the brace 200 d (see FIG. 10 ).
  • the first set of parallel pivot holes 210 , the second set of parallel pivot holes 220 , the set of parallel through holes 230 , and the helicoil blind hole 240 may be formed in a variety of different manors including but not limited to molding, machining and drilling.
  • the toggle mechanism 100 may also include a bracket 140 operably connected to the clevis 200 at the second set of parallel pivot holes 220 via a biasing mechanism 130 .
  • the biasing mechanism 130 may include a pin 186 .
  • the biasing mechanism 130 may be a spring.
  • the toggle mechanism 100 also includes a cap screw 160 located in the through hole 350 .
  • the cap screw 160 secures the cross rod 300 to the set of parallel through holes 230 of the clevis 200 .
  • the cap screw 160 secures the cross rod 300 to the clevis 200 via the helicoil blind hole 240 .
  • the cap screw 160 prevents the cross rod 300 from rotating in the clevis 200 . If the cross rod 300 had bent due to heavy loads, and then rotated in the clevis 200 , the over center position may change for various cross rod 300 rotational positions. In order to prevent the cross rod from bending, various changes were incorporated into the cross rod 300 in FIG. 7 versus alternate cross-rod designs.
  • FIG. 6 shows a schematic illustration of an alternate toggle mechanism 102 capable of being using in the actuator 50 of FIG. 3 .
  • FIG. 8 shows a schematic illustration of an alternate cross rod 302 for use in the alternate toggle mechanism 102 of FIG. 6 .
  • the diameter (D 1 , D 2 , and D 3 ) of cross rod 300 is greater than the diameter D 4 of the alternate cross rod 302 . Having a larger diameter allows cross rod 300 to withstand larger bending forces.
  • the third diameter D 3 may be larger than at least one of the first diameter D 1 and the second diameter D 2 . Having a larger diameter in the middle allows the cross rod 300 to be stronger where it is needed most.
  • the alternate cross rod 302 includes a scallop 390 near the center of the alternate cross rod 302 , which results in a smaller diameter D 5 . The smaller diameter D 5 creates a weak point near the center of the alternate cross rod 302 , where the bending forces are often elevated.
  • the flange 340 allows the pivot pin 184 connecting the link 120 to the clevis 200 to remain in the first set of parallel pivot holes 210 of the clevis 200 .
  • the second hole 210 b may be a blind hole and the blind hole opens towards the first side 200 a .
  • the pivot pin 184 may be pressed into the blind second hole 210 b of the first set of parallel pivot holes 210 and then the flange 340 will cover up the pivot pin 184 on the first hole 210 a .
  • the alternate toggle mechanism 102 required a separate piece, called a retainer 188 , to keep the pivot pin 184 in its place.
  • FIG. 9 shows a schematic cross-sectional illustration of a cross rod 300 and clevis 200 assembly for use in the toggle mechanism 100 of FIG. 5 , according to an embodiment of the present disclosure.
  • FIG. 10 shows a schematic cross-sectional illustration of an alternate cross rod 302 and alternate clevis 202 assembly for use in the alternate toggle mechanism 102 of FIG. 6 .
  • the cross rod 300 is secured to the clevis 200 via the cap screw 160 , such that the flange 340 is abutting the clevis 200 , as shown.
  • the cap screw 160 is located in the through hole 350 of the flange 340 and screws into the clevis 200 at the helicoil blind hole 240 .
  • the thickness of the alternate cross rod 302 is reduced at the scallop 390 , in order to accommodate a set screw 190 , which reduces movement in direction Y.
  • the cap screw 160 , the flange 340 and the helicoil blind hole 240 in FIG. 9 eliminates the need to reduce the thickness of the cross rod 200 in the midsection 330 , unlike the alternate cross rod 302 .
  • a thicker diameter at the midsection 330 helps make the cross rod 300 stronger and more resistant to bending and/or breaking than the alternate cross rod 302 .
  • the flange 340 of the cross rod 300 eliminates the need for the retainer 188 , which was required by the alternate cross rod 302 and alternate clevis 202 assembly of FIG. 10 .
  • the elimination of the retainer 188 and the set screw 190 reduces part count and simplifies assembly.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Transmission Devices (AREA)
  • Wind Motors (AREA)
US15/068,151 2016-03-11 2016-03-11 Clevis link for toggle mechanism of ram air turbine actuator Active 2038-06-21 US10385784B2 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US15/068,151 US10385784B2 (en) 2016-03-11 2016-03-11 Clevis link for toggle mechanism of ram air turbine actuator
FR1751966A FR3048676B1 (fr) 2016-03-11 2017-03-10 Liaison de chape pour mecanisme a bascule d'actionneur d'eolienne de secours

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Application Number Priority Date Filing Date Title
US15/068,151 US10385784B2 (en) 2016-03-11 2016-03-11 Clevis link for toggle mechanism of ram air turbine actuator

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US20170260906A1 US20170260906A1 (en) 2017-09-14
US10385784B2 true US10385784B2 (en) 2019-08-20

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Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10829240B2 (en) * 2016-03-11 2020-11-10 Hamilton Sundstrand Corporation Cross rod for toggle mechanism of ram air turbine actuator
EP3348486B1 (fr) * 2017-01-14 2022-04-06 Hamilton Sundstrand Corporation Mécanisme de libération
EP3741681B1 (fr) 2019-05-24 2022-03-30 Hamilton Sundstrand Corporation Mécanisme de verrouillage et de déverrouillage

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4303213A (en) * 1979-02-21 1981-12-01 The Boeing Company Tow plate
FR2516609A1 (fr) * 1981-11-19 1983-05-20 Snecma Dispositif de fixation de deux pieces de revolution en materiaux ayant des coefficients de dilatation differents
US4676458A (en) * 1984-12-24 1987-06-30 Sundstrand Corporation Deployment mechanism for a ram air turbine
US4717095A (en) * 1985-06-10 1988-01-05 Sundstrand Corporation Ram air turbine indexing mechanism
US4742976A (en) * 1985-06-10 1988-05-10 Sundstrand Corporation Ram air turbine and deployment mechanism
US20120297924A1 (en) * 2011-05-25 2012-11-29 Lang David J Ram air turbine deployment actuator
US20130078026A1 (en) * 2011-09-26 2013-03-28 Gary SASSCER Ejection jack release mechanism
US8602736B2 (en) * 2010-03-22 2013-12-10 Hamilton Sundstrand Corporation Stow abort mechanism for a ram air turbine
US20130330121A1 (en) * 2012-06-06 2013-12-12 Gary SASSCER Electromechanical actuator and latch assembly for ram air turbine

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4303213A (en) * 1979-02-21 1981-12-01 The Boeing Company Tow plate
FR2516609A1 (fr) * 1981-11-19 1983-05-20 Snecma Dispositif de fixation de deux pieces de revolution en materiaux ayant des coefficients de dilatation differents
US4676458A (en) * 1984-12-24 1987-06-30 Sundstrand Corporation Deployment mechanism for a ram air turbine
US4717095A (en) * 1985-06-10 1988-01-05 Sundstrand Corporation Ram air turbine indexing mechanism
US4742976A (en) * 1985-06-10 1988-05-10 Sundstrand Corporation Ram air turbine and deployment mechanism
US8602736B2 (en) * 2010-03-22 2013-12-10 Hamilton Sundstrand Corporation Stow abort mechanism for a ram air turbine
US20120297924A1 (en) * 2011-05-25 2012-11-29 Lang David J Ram air turbine deployment actuator
US20130078026A1 (en) * 2011-09-26 2013-03-28 Gary SASSCER Ejection jack release mechanism
US20130330121A1 (en) * 2012-06-06 2013-12-12 Gary SASSCER Electromechanical actuator and latch assembly for ram air turbine

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Publication number Publication date
US20170260906A1 (en) 2017-09-14
FR3048676A1 (fr) 2017-09-15
FR3048676B1 (fr) 2021-11-05

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