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公开(公告)号：EP3459845A1
公开(公告)日：2019-03-27
申请号：EP17203232.8
申请日：2017-11-23
摘要： Disclosed herein is an aircraft (101) that includes an exhaust manifold (200) for combining one or more system exhaust paths located upstream of equipment inlets and directing the exhausts upwards towards the rotor linkages such that the exhaust is expelled and diffused forward of the equipment inlets. According to one aspect of the present disclosure, the exhaust manifold includes a structure (404) for supporting a transmission cowling (115) at the top of the aircraft and/or on the sides of the aircraft. For example, the exhaust manifold may include a platform (202) that contains the exhaust duct (204, 206, 208, 210) and may include a frame extending from the platform that follows the contours of the cowling, such that the cowling lays along the support frame for additional mechanical support.
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公开(公告)号：EP3459718A1
公开(公告)日：2019-03-27
申请号：EP17201978.8
申请日：2017-11-15
IPC分类号： B29C70/52 , B29C64/118
摘要： In one embodiment, a method may comprise heating a composite material into a viscous form, wherein the composite material comprises a thermoplastic (216) and a plurality of reinforcement fibers (217), wherein the plurality of reinforcement fibers is randomly arranged within the thermoplastic. The method may further comprise extruding a plurality of strands of the composite material, wherein extruding the plurality of strands causes the plurality of reinforcement fibers within each strand to align. The method may further comprise arranging the plurality of strands of the composite material to form an assembly fixture (200), wherein the assembly fixture comprises an anisotropic thermal expansion property, and wherein the anisotropic thermal expansion property is based on an orientation of the plurality of reinforcement fibers within the assembly fixture.
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公开(公告)号：EP3456627A1
公开(公告)日：2019-03-20
申请号：EP18167019.1
申请日：2018-04-12
摘要： In an embodiment, a rotorcraft (101) includes: tail rotor blades (111); a tail rotor actuator (113) coupled to the tail rotor blades (111) such that the pitch of the tail rotor blades (111) varies according to a current extension of the tail rotor actuator (113); pilot flight controls electrically coupled to the tail rotor actuator (113); and a flight control computer (205) electrically coupled to the tail rotor actuator (113) and the pilot flight controls, the flight control computer (205) configured to: determine the current extension of the tail rotor actuator (113); determine whether the current extension of the tail rotor actuator (113) is within a margin of a maximum extension of the tail rotor actuator (113); and indicate a first warning to a pilot in response to the current extension of the tail rotor actuator (113) being within the margin of the maximum extension of the tail rotor actuator (113).
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公开(公告)号：EP3450320A1
公开(公告)日：2019-03-06
申请号：EP17204969.4
申请日：2017-12-01
IPC分类号： B64D15/12
摘要： An ice protection system (59) is configured for a rotor blade having a leading edge along at least a portion of a spanwise length extending between a root portion (75) and a tip portion (73). The system has an electric spanwise anti-ice heater configured for placement on the leading edge of the blade and a first electric spanwise de-ice heater adjacent the anti-ice heater and having varying chordwise dimensions. The de-ice heater is configured for placement on an upper surface of the blade or a lower surface of the blade. Electrical connectors for each heater are configured for connection near the root portion of the blade to a source of electrical power.
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公开(公告)号：EP3450308A1
公开(公告)日：2019-03-06
申请号：EP17195083.5
申请日：2017-10-05
发明人： MILLER, Gary , STAMPS, Frank B.
IPC分类号： B64C27/605
CPC分类号： B64C11/32 , B64C11/06 , B64C11/30 , B64C27/605 , B64C29/0033 , B64C2027/7216 , B64C2027/7255
摘要： In one embodiment, a rotor hub comprises a yoke (202) for attaching a plurality of rotor blades, a constant velocity joint (206) to drive torque from a mast (201) to the yoke (202) and to enable the yoke (202) to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate (210), a phase adapter fulcrum (212), a plurality of actuators (221a-c) controlled based on a flight control input, a plurality of lower pitch links (222) configured to transfer motion between the plurality of actuators (221a-c) and the swashplate (210), a plurality of phase adjustment levers (213) configured to adjust a control phase associated with motion transferred between the plurality of actuators (221a-c) and the plurality of lower pitch links (222), and a plurality of upper pitch links (224) configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links (224) than lower pitch links (222).
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公开(公告)号：EP3351373B1
公开(公告)日：2019-03-06
申请号：EP17166889.0
申请日：2017-04-18
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公开(公告)号：EP3428065A1
公开(公告)日：2019-01-16
申请号：EP17184462.4
申请日：2017-08-02
发明人： EHINGER, Ryan , BOCKMILLER, David , SINUSAS, Eric
摘要： A variable-speed gearbox (26) for a tiltrotor with fixed engine (24) and rotating proprotor (28) includes an input shaft (34) coupled to the respective fixed engine (24), an output shaft (36) coupled to the respective proprotor (28); a high-speed clutch (74) integrated into a high-speed gear train (40), the high-speed gear train (40) having an input coupled to the input shaft (34) and an output coupled to the output shaft (36); and a low-speed clutch (76) integrated into a low-speed gear train (42), the low-speed gear train (42) having an input coupled to the input shaft (34) and an output coupled to the output shaft (36). The high-speed clutch (74) and the low-speed clutch (76) can be freewheeling clutches capable of disconnecting the output and the input of the respective gear train of the high and low-speed gear trains (40, 42) in an overrunning condition when the output rotates faster than the input of the respective gear train (40, 42). The low-speed clutch (76) can be permanently engaged. In accordance to some embodiments the variable-speed gearboxes (26) may include an accessory drive (50).
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公开(公告)号：EP3428064A1
公开(公告)日：2019-01-16
申请号：EP17193350.0
申请日：2017-09-26
摘要： A device is provided. The device includes a first pillar (501). The first pillar (501) includes a bottom portion (507) having an opening (513). The first pillar (501) further includes a top portion (511) coupled to the bottom portion (507) by a middle portion (509). The top portion (511) includes a plurality of shelves (521) stacked along a common axis intersecting the bottom portion (507). Each of the shelves (521) has a respective recess (527). The first pillar (501) further includes a plurality of clamps (523). Each of the shelves (521) has a respective clamp of the clamps. Each respective clamp (523) and respective recess (527) of the shelves (521) forms an airfoil cross-sectional shape. The first pillar (501) further includes a plurality of locks (525). Each of the shelves (521) has a respective lock of the locks. Each of the locks (525) has a first locking portion on respective shelves and a second locking portion on respective clamps of the shelves.
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公开(公告)号：EP3418183A1
公开(公告)日：2018-12-26
申请号：EP17195407.6
申请日：2017-10-09
摘要： One example of a cowling assembly for a rotorcraft (100) includes a stationary fairing (301) affixed to an airframe of the rotorcraft (100), an articulated fairing (303) hinged on the stationary fairing (301) for articulation relative to the stationary fairing (301) between a closed position, a first partially open maintenance position and a second fully open maintenance position. The articulated fairing (303) is supported in the first maintenance position by a for example gas-charged strut (401) and is releasably locked in the second maintenance position against the stationary fairing (301) by a locking mechanism. The locking mechanism includes a latch blade (307) disposed on the stationary fairing (303) and a latch arranged on the articulated fairing (303), wherein a latch pin engages with a hole or recess in the latch blade (307) when the latch blade (307) extends through a slot (308) in the articulated fairing (303).
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