• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    ACTUATOR FOR A DYNAMIC AIR TURBINE SYSTEM. An actuator for a dynamic air turbine system includes a locking pin having multiple lateral supports arranged circumferentially. A piston rod supports multiple upper locking wedges. Multiple rollers are supported on the sides with chamfers on the rollers engaging one another and are configured to radially support the upper locking wedges in a retracted position.
    公开号:BR102012012372B1
    申请号:R102012012372-0
    申请日:2012-05-23
    公开日:2021-01-12
    发明作者:David J. Lang；Gary SASSCER
    申请人:Hamilton Sundstrand Corporation；
    IPC主号:
    专利说明:

    [0001] [001] This exhibition refers to a dynamic air turbine extension system (RAT), and more particularly, the exhibition refers to an actuator for the system.
    [0002] [002] Aerodynamic Air Turbines (RATs) are used in numerous aircraft to provide hydraulic and electrical energy in emergency situations. The RAT is collected in the aircraft structure and extended into the air stream by means of an extension actuator. The extension actuator is attached to the aircraft structure and to an arm over the RAT upright. On extension, the extension actuator forces the RAT to spin out of its retracted, or retracted, position on the aircraft and into the air stream. The air current acts on the RAT blades to rotate the turbine and governor assembly, which in turn operates an electric generator and hydraulic pump providing power to the aircraft. The RAT is retained on the aircraft by an upper locking mechanism and is held in the extended position by a lower locking mechanism, both of which are contained in the extension actuator.
    [0003] [003] Typical upper and lower lock mechanisms use locking wedges, which restrict the actuator either in the retracted or extended position. Extending the actuator when only limited electrical power is available in an emergency is challenging. The loads on the actuator in an extended scenario can become relatively high due to the flight conditions of the aircraft. These emergency conditions can cause high loads in the ports when trying to push the RAT into the chain in flight. Various wedge arrangements have been used to lock the actuator in position on numerous actuators. In one example, four upper locking wedges are released by sliding the safety pin through an inner diameter of the wedges, so that the wedges fall into a groove in the safety pin which then releases the actuator to extend the RAT.
    [0004] [004] In another hydraulic locking actuator, rollers are used between two wedges to reduce the amount of force required to move the lock pin to release the actuator. However, the load that can be applied to the actuator is limited. SUMMARY
    [0005] [005] An actuator for a dynamic air turbine system includes a locking pin having a central support. A piston rod supports multiple upper locking wedges. Multiple rollers are supported on the lock pin and are configured to radially support the upper lock wedges in a stowed position. The rollers include chamfers latching together. BRIEF DESCRIPTION OF THE DRAWINGS
    [0006] [006] The exhibition can be better understood by reference to the following detailed description when considered in connection with the accompanying drawings, in which:
    [0007] [007] Figure 1 is a perspective view of a RAT in an extended position.
    [0008] [008] Figure 2 is a perspective view of an actuator illustrated in figure 1 in a retracted or retracted position before extending the RAT.
    [0009] [009] Figure 3 is a cross-sectional view of the actuator illustrated in figure 2.
    [0010] [0010] Figure 4A is a cross-sectional view of the actuator similar to figure 3, but with the safety pin released by a lock set.
    [0011] [0011] Figure 4B is an enlarged view of the actuator illustrated in figure 4A.
    [0012] [0012] Figure 4C is a cross-sectional view of the actuator along line 4C-4C in figure 4B.
    [0013] [0013] Figure 5 is a cross-sectional view of the actuator with upper locking wedges released.
    [0014] [0014] Figure 6 is a cross-sectional view of the actuator in a fully extended position.
    [0015] [0015] Figure 7 is a cross-sectional view of the actuator in a fully extended position with the lower locking wedges engaged. DETAILED DESCRIPTION
    [0016] [0016] Figure 1 illustrates a RAT system 10 attached to an aircraft structure 12 by a frame 14. The frame 14 pivotally supports an upright 16 having a turbine 18 at one end. The turbine 18 includes blades 20, which provide the rotational drive to a generator 22 and a hydraulic pump 30. An actuator 24 is attached to the upright 16 at a first end 26 and the housing at a second end 28. Actuator 24 is illustrated in extended position.
    [0017] [0017] With reference to figures 2 and 3, the actuator 24 includes a housing 32 having first cylinder 34 and separate second cylinder 36, not attached to the housing 32, telescopically arranged in relation to each other. An extension spring 38 is disposed between the first and second cylinders 34, 36 in a compressed state with the actuator 24 in its retracted position. An extension solenoid 40 is mounted on the housing 32 and is actuated to initiate an extension sequence inside the actuator 24.
    [0018] [0018] The second cylinder 36 is received inside the first cylinder 34. A piston rod 42 is affixed to the housing 32 so that it is rigidly affixed to the first cylinder 34, such that the second cylinder 36 slides between and in relation to to the piston rod 42 and the first cylinder 34. The piston rod 42 includes first and second openings 44, 46, which respectively receive upper lock and lower lock wedges 48, 50. A lock pin 52 is slidably arranged inside the piston rod 42 to actuate the upper lock and lower lock wedges 48, 50 during the extension sequence. The piston rod 42 includes a flange 58 and a collar 60 spaced from each other. A lock pin spring 54 is provided between, and engages, flange 58 and collar 60 to skew piston rod 42 and lock pin 52 away from each other along axis A. a roller assembly 56 is supported by the locking pin 52 and arranged radially between the locking pin 52 and the upper locking wedges 48.
    [0019] [0019] A lock assembly 62 is provided on housing 32 next to extension solenoid 40. A lever 64 is pivotally supported by a pivot 68 at one end, and lever 64 includes a lock pin 64 opposite pivot 68. One tilt member 72 holds lever 64 in a normally retracted position. Lock pin 66 engages an end 74 of lock pin 52 in the stowed position. A rod 70 extending from extension solenoid 40 cooperates with lever 64 to move lever 64 from a retracted position (figure 3) to an extended position (figure 4A).
    [0020] [0020] In operation, to start an extension sequence, the extension solenoid 40 moves the rod 70 to rotate the lever 64 around pivot 68, overcoming the tilt force from the lock pin spring 54. With the lock pin 66 disengaged from end 74, lock pin 52 is forced to move axially (to the right in figure 4A) in response to the tilting force from the lock pin spring 54.
    [0021] [0021] With reference to figures 4A-4C, the movement of the roller assembly 56 (to the right in the figures) allows the upper locking wedges 48 to move radially inward and disengage from the cylinders 36, thus allowing the second cylinder 36 moves axially away from the first cylinder 34. The roller assembly 56, as illustrated in figures 4A-4C, is shown in the retracted position. The roller assembly 56 includes rollers 76 supported by a side support 78 of the lock pin 52. The rollers 76 are provided in slots 90 evenly spaced circumferentially on the lock pin 52. The side support 78 includes two flat surfaces 86 and 87, provided for each slot 90, which support the rollers 76. The slots in the slots 90 offer the contact line L with the rollers 76, retaining them axially. This line contact is the only friction that the rollers suffer in relation to the lock pin 52, allowing the assembly of a smaller lock pin spring 54. The flat surfaces 86 and 87 are perpendicular to the A axis of the actuator. Lock pin 52, used to space rollers 76 evenly around the circumference of the lock pin and in a plane perpendicular to axis A, holds four rollers 76 axially. The rollers 76 are supported radially by their own corner chamfers 96 that rest against each other. The four rollers radially support four upper locking wedges 48 in the same plane, which are axially retained by the piston rod 42.
    [0022] [0022] The second cylinder 36 includes an inclined surface 80. The upper locking wedges 48 include a first angled surface 82 which engages the inclined surfaces 80. The rollers 76 support an inner surface 84 of the upper locking wedges 48. A second surface angled 88 is provided on the upper locking wedges 48, next to the rollers 76 opposite the first angled surface 82.
    [0023] [0023] Each roller 76 includes ends 92, opposite each other, which provide a gap 94 between the rollers 76 and the slots 90 to allow axial movement of the roller 76 along the roller axis R. Each roller 76 includes chamfers 96 at each end 92. The chamfers 96 of the rollers 76 engage with each other with the gap 94 provided to accommodate misalignment with the components and support the roller loading due to the reaction of the upper lock wedge loads 48 developed from the contact surfaces 80 and 82. For the example arrangement, where four rollers are used, the chamfers are at a 45 ° angle to the cylindrical roller support surface of rollers 76. In this way, the loads between rollers 76 are shared between the conjugated chamfers 96 and the frictional loads are reduced due to the rolling contact between the roller chamfers 96. Thus, the loads on the upper locking wedges 48 are more evenly distributed, which means permits a higher capacity actuator with reduced release force. It should be understood that the number of wedges and the number of rollers may vary for other actuator applications, depending on the loads.
    [0024] [0024] With reference to figures 5-7, the lock pin spring 54 continues to move the lock pin 52 (to the right in the figures), allowed by the roller assembly 56 sliding relatively easily within the piston rod 42. Once when the rollers 76 moved out of engagement with the inner surface 84 of the upper latch wedges 48, the inclined surface 80 forces the upper latch wedges 48 radially inward in response to the force of the extension spring 38, as illustrated in figure 5. The locking pin 52 moves axially in relation to the piston rod 42 until a stop 98 engages the lower locking wedges 50.
    [0025] [0025] The second cylinder 36 continues to move axially outwardly relative to the first cylinder 34 until a stop 100 on the piston rod 42 engages a surface on the second cylinder 36, limiting its axial position in relation to the first cylinder 34 (figure 6 ). Lock pin 52 continues to move axially to the right in response to force from lock pin spring 54, applied to an inclined surface 102 of lock pin 52 forces the lower lock wedges 50 radially outwardly inward of a groove 104 of the second cylinder 36.
    [0026] [0026] Although an example modality has been exposed, a worker of common knowledge in this art would recognize that certain modifications would fall within the scope of the claims. For this reason, the following claims must be studied to determine their true scope and content.
    权利要求:
    Claims (7)
    [0001]
    Actuator (24) for a dynamic air turbine system (10), comprising: a locking pin (52) providing multiple circumferentially arranged side supports (78); a piston rod (42) supporting multiple upper locking wedges (48); characterized by the fact that it comprises multiple rollers (76), each of which is supported on one of the side supports (78) and configured to radially support the upper locking wedges (48) in a retracted position, the rollers (76) including chamfers (96) engaging one another; and, first and second cylinders (34, 36) arranged telescopically in relation to each other and configured to be axially skewed away from each other by an extension spring (38), the piston rod (42) and lock pin (52) arranged inside the second cylinder (36).
    [0002]
    Actuator (24), according to claim 1, characterized by the fact that the locking pin (52) includes slots (90) providing the side supports (78), and the rollers (76) arranged in the slots (90).
    [0003]
    Actuator (24), according to claim 2, characterized by the fact that it comprises a gap (94) between each roller (76) and its corresponding slot (90) to allow axial movement of each roller (76) within its respective slot (90).
    [0004]
    Actuator (24), according to claim 3, characterized by the fact that the lateral supports (78) allow the rollers (76) to provide load sharing between all the upper locking wedges (48) by movement both radially due to roller chamfers (96) as well as axially due to the gap (94) between each roller within its respective slot (90).
    [0005]
    Actuator (24) according to claim 3, characterized in that each roller (76) includes opposite ends (92), each having the chamfer (96).
    [0006]
    Actuator (24), according to claim 5, characterized by the fact that the multiple rollers (76) are provided by four rollers having a chamfer (96) of 45 ° at the opposite ends (92).
    [0007]
    Actuator (24) according to claim 1, characterized by the fact that it comprises a lock assembly (62) cooperating with the lock pin (52) and configured to move between retracted and extended positions, and a pin spring latch (54) configured to skew the piston rod (42) and latch pin (52) away from each other with the latch assembly (62) in the extended position.
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    KR20120132345A|2012-12-05|
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    CA2775470A1|2012-11-25|
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    US20120297924A1|2012-11-29|
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    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2764132A|1954-05-06|1956-09-25|Boeing Co|Piston-mounted end lock for hydraulic actuators|
    US3107933A|1961-05-17|1963-10-22|Robert H Royster|Extensible and retractable device having manually releasable positive locking means|
    US3469871A|1967-08-14|1969-09-30|Norco Inc|Releasable locking device|
    US3813065A|1969-06-23|1974-05-28|Decoto Aircraft Inc|Locking mechanisms and actuator assemblies of coaxial locked remotely at selected locations after motions of a nearly complete circumferential one piece chamfered locking ring|
    NO140690C|1977-11-02|1979-10-17|Kongsberg Vapenfab As|DEVICE FOR FRAME AIR TURBINES.|
    US4392556A|1978-08-25|1983-07-12|Arkwin Industries, Inc.|Actuator locking device|
    US4240332A|1978-08-25|1980-12-23|Arkwin Industries, Inc.|Fluid operated locking actuator|
    US4676458A|1984-12-24|1987-06-30|Sundstrand Corporation|Deployment mechanism for a ram air turbine|
    US4742976A|1985-06-10|1988-05-10|Sundstrand Corporation|Ram air turbine and deployment mechanism|
    US4717095A|1985-06-10|1988-01-05|Sundstrand Corporation|Ram air turbine indexing mechanism|
    DE8533253U1|1985-11-26|1986-01-16|Karl Hertel GmbH, 8510 Fürth|Quick change clamping device|
    DE3734052A1|1987-10-08|1989-04-20|Hertel Ag Werkzeuge Hartstoff|QUICK-CHANGE CLAMPING DEVICE FOR MACHINE TOOLS|
    US4991796A|1988-11-14|1991-02-12|Sundstrand Corporation|Ram air turbine drive system|
    US5366313A|1992-11-02|1994-11-22|Norco, Inc.|Strut construction|
    US5398780A|1993-02-19|1995-03-21|Sundstrand Corporation|Linear actuator with speed controlling brake|
    US5820074A|1996-12-20|1998-10-13|Sundstrand Corporation|Deployment mechanism for RAM air turbine|
    US6238292B1|1998-05-27|2001-05-29|Monadnock Lifetime Products, Inc.|Push button controlled police baton with ball bearing locking mechanism|
    US6580179B2|2001-06-07|2003-06-17|Honeywell International Inc.|Ram air turbine with high power density generator and self-contained fluid cooling loop|
    US6832540B2|2003-03-17|2004-12-21|Kenneth E. Hart|Locking hydraulic actuator|
    US7100465B1|2003-06-05|2006-09-05|Venture Mfg, Co.|Actuator|
    US6948685B2|2003-10-27|2005-09-27|Hr Textron, Inc.|Locking device with solenoid release pin|
    JP4240514B2|2004-02-24|2009-03-18|本田技研工業株式会社|Direct acting actuator|
    US7097014B2|2004-06-04|2006-08-29|Tan-Cheng Huang|Shock absorber|
    US7290509B2|2005-08-01|2007-11-06|Zheng Lou|Variable valve actuator|
    US7416392B2|2005-09-07|2008-08-26|Hamilton Sundstrand Corporation|Stow abort mechanism for a ram air turbine|
    US7610828B2|2005-11-15|2009-11-03|Honeywell International Inc.|Flight control surface actuator assembly including a free trial mechanism|
    US7762739B2|2007-08-31|2010-07-27|Strategic Ideas, Llc|Fastener and assembly utilizing the same|
    US8251606B2|2007-08-31|2012-08-28|The Blanchard Patent Holding Company, Llc|Fastener and assembly utilizing the same|
    WO2009152563A1|2008-06-16|2009-12-23|Chad Arthur Evans|Linearly adjustable device|
    GB0817775D0|2008-09-29|2008-11-05|Goodrich Actuation Systems Ltd|Actuator|US20130181448A1|2012-01-17|2013-07-18|Hamilton Sundstrand Corporation|Electric actuators in aircraft systems|
    JP6209364B2|2013-06-03|2017-10-04|三菱航空機株式会社|Aircraft door and aircraft equipped with the same|
    US9415880B2|2013-10-09|2016-08-16|Hamilton Sundstrand Corporation|Actuator for rat deployment|
    FR3017600B1|2014-02-20|2016-02-19|Sagem Defense Securite|BLOCKER ACTUATOR AND TORQUE LIMITER THEREFOR|
    US9399522B2|2014-02-20|2016-07-26|Hamilton Sundstrand Corporation|Ram air turbine actuator|
    US9656763B2|2014-08-13|2017-05-23|Hamilton Sundstrand Corporation|Stow lock pawl for a rat actuator|
    US9878800B2|2015-01-16|2018-01-30|Hamilton Sundstrand Corporation|Rat mounting arrangement for a soft aircraft interface|
    US9976636B2|2015-04-22|2018-05-22|Hamilton Sundstrand Corporation|Locking mechanisms for ram air turbines|
    PL3165467T3|2015-11-03|2020-03-31|Hamilton Sundstrand Corporation|Actuator locking mechanism|
    EP3176094B1|2015-12-04|2019-02-06|Hamilton Sundstrand Corporation|Unlocking apparatus for a ram air turbine actuator|
    FR3045014B1|2015-12-11|2019-05-17|Safran Electrical & Power|EMERGENCY WIND POWER SYSTEM COMPRISING A TURBINE ROTATION BLOCKING DEVICE|
    EP3196126B1|2016-01-19|2019-03-13|Hamilton Sundstrand Corporation|Locking and unlocking mechanism|
    PL3196127T3|2016-01-20|2019-04-30|Hamilton Sundstrand Corp|Locking and unlocking mechanism|
    US10113568B2|2016-02-19|2018-10-30|Hamilton Sundstrand Corporation|Ram air turbine hydraulic release mechanism|
    US10081440B2|2016-02-26|2018-09-25|Hamilton Sundstrand Corporation|Ram air turbine release mechanism with stroke amplification|
    US10385784B2|2016-03-11|2019-08-20|Hamilton Sundstrand Corporation|Clevis link for toggle mechanism of ram air turbine actuator|
    EP3216701B1|2016-03-11|2018-12-19|Hamilton Sundstrand Corporation|Latch mechanism|
    US10012246B2|2016-04-14|2018-07-03|Hamilton Sundstrand Corporation|Failsafe deployment feature for actuator|
    EP3239052B1|2016-04-30|2019-02-06|Hamilton Sundstrand Corporation|Locking and unlocking mechanism|
    EP3260375A1|2016-06-24|2017-12-27|Hamilton Sundstrand Corporation|Actuator release mechanism|
    EP3263944A1|2016-07-01|2018-01-03|Hamilton Sundstrand Corporation|Spring compression device|
    EP3284677B1|2016-08-16|2020-04-22|Hamilton Sundstrand Corporation|Locking and unlocking mechanism|
    US10787274B2|2016-08-16|2020-09-29|Hamilton Sundstrand Corporation|Inflight stow of ram air turbine|
    EP3305664B1|2016-10-10|2020-09-16|Hamilton Sundstrand Corporation|Actuator release mechanism|
    US10372150B2|2016-11-04|2019-08-06|Hamilton Sundstrand Corporation|Locking mechanisms for ram air turbine actuators|
    EP3461745B1|2017-09-28|2021-10-27|Hamilton Sundstrand Corporation|Release mechanism for ram air turbine actuator|
    US10661913B2|2018-04-30|2020-05-26|Hamilton Sundstrand Corporation|Hybrid ram air turbine with in-line hydraulic pump and generator|
    EP3741681A1|2019-05-24|2020-11-25|Hamilton Sundstrand Corporation|Locking and unlocking mechanism|
    法律状态:
    2013-11-19| B03A| Publication of a patent application or of a certificate of addition of invention [chapter 3.1 patent gazette]|
    2018-12-11| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|
    2019-12-10| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|
    2020-11-24| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|
    2021-01-12| B16A| Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 23/05/2012, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    US13/115,209|US8640563B2|2011-05-25|2011-05-25|Ram air turbine deployment actuator|
    US13/115,209|2011-05-25|
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