-
公开(公告)号：EP4361032A3
公开(公告)日：2024-07-31
申请号：EP24163761.0
申请日：2021-11-12
发明人： KNOLL, Jonathan Andrew , THOMPSON, George Matthew , SPELLER, Charles Hubert , BEALL, Grant Michael
CPC分类号： B64C27/12 , B64C29/0033 , F16H1/28 , B64D27/24 , B64D35/02
摘要： A drive system (200) for providing rotational energy to a rotor assembly via a rotor mast, the drive system (200) comprising: an aft end having an electric motor for providing rotational energy to a drive shaft, a forward end connected to the drive shaft for receiving rotational energy from the electric motor via the drive shaft and providing rotational energy to the rotor mast via a rotor shaft, and an adapter (240) having a first interface connected to the electric motor and a second interface connected to the forward end, wherein the drive system (200) is rotatable relative to a wing about a tilt axis (230) located on the adaptor (240) between the electric motor and the forward end.
-
公开(公告)号：EP4310007A1
公开(公告)日：2024-01-24
申请号：EP23182294.1
申请日：2023-06-29
摘要： In an embodiment, a rotorcraft (101) includes a control element (201); a first detent sensor (235) connected to the control element, the first detent sensor being operable to generate detent slip rate data indicating movement of the control element and detent state data indicating pilot control (233) of the control element; a first trim motor (213) connected to the control element and operable to generate trim rate data; and an FCC (205) in signal communication with the first detent sensor and the first trim motor, the FCC including an error monitor (903, 905, 907) operable to compare the detent slip rate data with the trim rate data and determine whether the first detent sensor is functional or defective, operable to provide a first flight management function when the first detent sensor is determined to be functional, and operable to provide a second flight management function when the first detent sensor is determined to be defective.
-
公开(公告)号：EP4201817A1
公开(公告)日：2023-06-28
申请号：EP23154982.5
申请日：2021-06-09
摘要： An aircraft (101) comprising a plurality of rotors (109) and a propulsion system (120) for controlling propulsion of the aircraft (101). The propulsion system (120) comprises: a plurality of electric motors (122) including for each rotor (109) of the plurality of rotors, two or more electric motors coupled therewith, for driving the rotors; a propulsion motor control (130) comprising: a plurality of propulsion control units (132), wherein each propulsion control unit (132) is electrically coupled to a pair of electric motors of the plurality of electric motors (122), wherein one of the electric motors of the pair of electric motors is coupled with a first rotor and wherein the other of the electric motors of the pair of electric motors is coupled with a second rotor diagonally positioned relative to the first rotor, wherein each propulsion control unit (132) is configured to actuate a respective pair of the electric motors (122), and at least one battery (134a-f) electrically connected with at least one of the plurality of propulsion control units (132) of the propulsion motor control (130) and at least one electric motor of the plurality of electric motors (122), wherein the at least one battery (134a-f) is configured to provide power to the at least one propulsion control unit and the at least one electric motor; and a flight control (140) coupled with the plurality of propulsion control units (132), wherein the flight control (140) is configured to transmit a desired torque level to the plurality of propulsion control units (132). The propulsion motor control (130) is configured to actuate the plurality of electric motors (122) based on the desired torque level to drive each rotor (109) to provide propulsion of the aircraft (101).
-
公开(公告)号：EP4201810A1
公开(公告)日：2023-06-28
申请号：EP22216155.6
申请日：2022-12-22
发明人： COLLADO, Paul C. , COZINE, Brian T.
IPC分类号： B64C11/44
摘要： An electromechanical pitch control system (100) for modifying a collective blade pitch of a multi-blade propeller (104) includes a pitch control rod (108) mechanically coupled via a distal end to a plurality of blades (102) of a propeller (104), a bearing assembly (115) operatively connected to a proximal end of the pitch control rod (108), and an electric actuator (122) operatively connected to the bearing assembly (115). The bearing assembly (115) allows the electric actuator (122) to remain stationary while the pitch control rod (108) rotates with the propeller (104). The electric actuator (122) is configured to translate the pitch control rod (108) in a longitudinal direction for adjusting an incidence angle of the blades (102).
-
公开(公告)号：EP4151525A1
公开(公告)日：2023-03-22
申请号：EP22187992.7
申请日：2022-07-31
发明人： SCHAFER, Steven Ryan
IPC分类号： B64C29/02
摘要： An aircraft (10) operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft (10) includes an airframe (12) having first (14) and second (16) wings in a staggerwing configuration with first and second swept pylons (18, 20) extending therebetween. A distributed thrust array is attached to the airframe (12). The thrust array includes a first plurality of propulsion assemblies (34a, 34b) coupled to the first wing (14) and a second plurality of propulsion assemblies (34c, 34d) coupled to the second wing (16). A flight control system (30) is coupled to the airframe (12) and is configured to independently control each of the propulsion assemblies (34a, 34b, 34c, 34d). The first plurality of propulsion assemblies (34a, 34b) is longitudinally offset relative to the second plurality of propulsion assemblies (34c, 34d) such that rotors of the first plurality of propulsion assemblies (34a, 34b) rotate in a different plane than rotors of the second plurality of propulsion assemblies (34c, 34d).
-
公开(公告)号：EP4122753A1
公开(公告)日：2023-01-25
申请号：EP22176593.6
申请日：2022-06-01
发明人： FAN, Yue , HULL, Michael R
摘要： There is disclosed in one example an apparatus, including: a hardware platform including a processor and a memory; and instructions encoded within the memory to instruct the processor to: receive stored performance data for an aircraft battery (120), the stored performance data including data that correlate power density to temperature and remaining charge; simulate a planned flight for an aircraft, including predicting a plurality of temperature and remaining charge values; and direct operation of a heat exchange apparatus to precondition the battery (120) to a selected temperature before the planned flight.
-
公开(公告)号：EP4011773A1
公开(公告)日：2022-06-15
申请号：EP21209634.1
申请日：2021-11-22
摘要： The disclosure relates to an aircraft and a storage pod for an aircraft. In an example embodiment, an aircraft (100) comprises: first and second wings (104); a plurality of propulsion assemblies (115), the plurality of propulsion assemblies (115) comprising a propulsion assembly (115) connected to each end of each of the first and second wings (104); first and second vertical supports (105) disposed between the first and second wings (104); and a storage pod (102) disposed between the first and second vertical supports (105), the storage pod (102) comprising a nose portion (347) that extends forward of the plurality of propulsion assemblies (115), the nose portion (347) comprising at least one radar (324) and at least one camera (326).
-
公开(公告)号：EP4008646A1
公开(公告)日：2022-06-08
申请号：EP21207894.3
申请日：2021-11-12
发明人： LANDRY, Martin
IPC分类号： B65D19/38
摘要： An integrated battery cargo platform (10) includes a housing (12) having an exterior surface (16) and a structural strength to support cargo for transit on a top surface (18), and a battery (14) enclosed in the housing (12) with power contacts (24) exposed at the exterior surface (16).
-
公开(公告)号：EP4008631A1
公开(公告)日：2022-06-08
申请号：EP21209428.8
申请日：2021-11-19
发明人： DUGRE, Alexis , BIRON, Guillaume , OUELLET, Marc
摘要： A yaw control system (24; 102; 202, 250; 302; 402; 502; 602) for a helicopter (10; 100; 200, 264; 300; 400; 500; 600) having a tailboom (20; 106; 206, 268; 306; 406; 506; 606) and a forward flight mode includes a surface coupled to the tailboom (20; 106; 206, 268; 306; 406; 506; 606), one or more tail rotors (42, 44, 46, 48; 112, 114, 116, 118; 136, 142, 150, 162, 172, 180, 188; 212, 214, 216, 218; 312, 314, 316, 318; 412, 414, 416, 418; 512, 514, 516, 518; 612, 614, 616, 618) coupled to the surface, a flight control computer (56; 230; 334; 426; 626) implementing a yaw controller (66; 228) having a rudder control module (234) and a tail rotor rotational speed reduction module (232) and a rudder (222) rotatably coupled to the surface. The tail rotor rotational speed reduction module (232) is configured to selectively switch the one or more tail rotors (42, 44, 46, 48; 112, 114, 116, 118; 136, 142, 150, 162, 172, 180, 188; 212, 214, 216, 218; 312, 314, 316, 318; 412, 414, 416, 418; 512, 514, 516, 518; 612, 614, 616, 618) into a rotational speed reduction mode in the helicopter (10; 100; 200, 264; 300; 400; 500; 600) forward flight mode. The rudder control module (234) is configured to rotate the rudder (222) in the rotational speed reduction mode of the one or more tail rotors (42, 44, 46, 48; 112, 114, 116, 118; 136, 142, 150, 162, 172, 180, 188; 212, 214, 216, 218; 312, 314, 316, 318; 412, 414, 416, 418; 512, 514, 516, 518; 612, 614, 616, 618) to control the yaw of the helicopter (10; 100; 200, 264; 300; 400; 500; 600).
-
公开(公告)号：EP4008630A1
公开(公告)日：2022-06-08
申请号：EP21209426.2
申请日：2021-11-19
摘要： An electrically distributed yaw control system (24; 102; 202, 250; 302; 402; 502; 602) for a helicopter (10; 100; 200, 264; 300; 400; 500; 600) having a tailboom (20; 106; 206, 268; 306; 406; 506; 606) and a power system (58; 522) includes one or more tail rotors (42, 44, 46, 48; 112, 114, 116, 118; 136, 142, 150, 162, 172, 180, 188; 212, 214, 216, 218; 312, 314, 316, 318; 412, 414, 416, 418; 512, 514, 516, 518; 612, 614, 616, 618) including a motor (42b, 44b, 46b, 48b; 612a, 614a, 616a, 618a) rotatably coupled to the tailboom (20; 106; 206, 268; 306; 406; 506; 606) and a power distribution unit (534, 564). The power distribution unit (534, 564) includes a power management monitoring module (72a; 538) configured to monitor one or more flight parameters of the helicopter (10; 100; 200, 264; 300; 400; 500; 600) and a power management command module (72b; 540) configured to allocate power between the power system (58; 522) and the one or more tail rotor motors (42b, 44b, 46b, 48b; 612a, 614a, 616a, 618a) based on the one or more flight parameters of the helicopter (10; 100; 200, 264; 300; 400; 500; 600).
-
-
-
-
-
-
-
-
-
搜索结果
112 条记录 (耗时 0.022 秒)
