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公开(公告)号：CA3081733A1
公开(公告)日：2020-11-30
申请号：CA3081733
申请日：2020-05-29
Applicant: BELL TEXTRON INC
Inventor： MCCULLOUGH JOHN RICHARD , OLDROYD PAUL K , ISBELL GLENN EDWARD , HILL MATTHEW JOHN
Abstract: An aircraft is operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes an airframe having first and second wings with first and second pylons extending therebetween forming a central region. A two-dimensional distributed thrust array and a flight control system are coupled to the airframe. A nose cone and an afterbody are each selectively coupled to the airframe. In a cargo delivery flight configuration, the nose cone and the afterbody are coupled to the airframe such that the nose cone and the afterbody each extend between the first and second wings and between first and second pylons to form a cargo enclosure with an aerodynamic outer shape. In a minimal drag flight configuration, the nose cone and the afterbody are not coupled to the airframe such that air passes through the central region during flight.
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公开(公告)号：CA3077958A1
公开(公告)日：2020-10-15
申请号：CA3077958
申请日：2020-04-15
Applicant: BELL TEXTRON INC
Inventor： BERNARD GUY
Abstract: A multimodal unmanned aerial system (10) includes a fuselage (12) forming a payload bay (22), a control wing (14) forward of the fuselage (12) including a first plurality of propulsion assemblies (30,32) and a primary wing (16) aft of the fuselage (12) including a second plurality of propulsion assemblies (34, 36). The primary wing (16) has a greater wingspan than the control wing (14). The multimodal unmanned aerial system (10) includes linkages (40, 42, 44, 46) rotatably coupling the fuselage (12) to the control wing (14) and the primary wing (16). The fuselage (12), the control wing (14) and the primary wing (16) are configured to synchronously rotate between a vertical takeoff and landing flight mode and a forward flight mode. The fuselage (12), the control wing (14) and the primary wing (16) are substantially vertical in the vertical takeoff and landing flight mode and substantially horizontal in the forward flight mode.
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公开(公告)号：CA3117164C
公开(公告)日：2022-06-07
申请号：CA3117164
申请日：2021-05-03
Applicant: BELL TEXTRON INC
Inventor： KUANG CHEN , BUSTAMANTE MARC , SENTHILNATHAN THUVARAGAN , OUELLET MARC , BIRON GUILLAUME
Abstract: An electric distributed propulsion system includes one or more generators connected to a gearbox, a first and a second plurality of motors connected to the generators, each motor connected to a blade to provide thrust, a first and a second power bus electrically connected between the generators and the first and the second motors, each power bus independent of the other power bus, a first and a second controller independently connected to each of the first and second motors, each of the first and second controllers serving as a primary and a backup controller to provide redundant control to both the first and the second plurality of motors, and dual channels in communication between pilot input sensors and the first and the second controllers, each channel independent of the other channels, and the channels including an additional channel to provide redundant communication to the first and second controllers.
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公开(公告)号：CA3101770A1
公开(公告)日：2022-04-16
申请号：CA3101770
申请日：2020-12-04
Applicant: BELL TEXTRON INC
Inventor： TETREAULT SIMON
Abstract: A weighing system includes a support, a load cell mounted to the support, and a part platform suspended from the load cell to receive a part to be weighed. The load cell is operable to generate thousands of weight values for the part per second over a period of less than twenty seconds. The load cell is operable to output a weight of the part by averaging the weight values over the period of less than twenty seconds. A method of weighing the part suspended from the load cell is also disclosed.
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公开(公告)号：CA3101756A1
公开(公告)日：2022-04-16
申请号：CA3101756
申请日：2020-12-04
Applicant: BELL TEXTRON INC
Inventor： LALIBERTE FREDERIC
Abstract: A cart for supporting a part to be inspected in a non-destructive testing (NDT) machine. The cart includes a base with wheels, a first support extending upright from the base, a second support extending upright from the base, and mounting fixtures being removably attachable to the first and second supports and having mounting ends engageable with the part to support the part from the first support or the second support. The base is displaceable with the wheels to enter and exit the NDT machine. The cart is lockable upon being within the NDT machine to secure the cart in position.
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Patent Agency Ranking
公开(公告)号：CA3101754A1
公开(公告)日：2021-06-04
申请号：CA3101754
申请日：2020-12-04
Applicant: BELL TEXTRON INC
Inventor： PELLETIER PIER-ALEXANDRE , GINGRAS RICHARD
Abstract: ABSTRACT A bonded part includes a first surface facing toward a second surface, and a cured adhesive between the first and second surfaces defining a bond line. A surface structure on the first surface is within the bond line and has surface protrusions arranged in a pattern. Each surface protrusion protrudes outwardly from a first end at the first surface to a second end adjacent to the second surface. A thickness of the surface protrusions is substantially equal to the thickness of the bond line. The cured adhesive extends around the surface protrusions. The thickness of the bond line between the first and second surfaces is substantially constant along the bond line, and is greater than a thickness of the cured adhesive between the second ends of the protrusions and the second surface. Date Recue/Date Received 2020-12-04
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公开(公告)号：CA3096609A1
公开(公告)日：2021-04-23
申请号：CA3096609
申请日：2020-10-20
Applicant: BELL TEXTRON INC
Inventor： MORRIS KEVIN , BRODEUR NICHOLAS , FLYNN-ROBITAILLE PASCAL , BELAND MATHIEU
Abstract: An autonomous cargo delivery aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes a fuselage having an aerodynamic shape with a leading edge, a trailing edge and first and second sides. First and second wings are coupled to the fuselage proximate the first and second sides, respectively. A distributed thrust array includes a first pair of propulsion assemblies coupled to the first wing and a second pair of propulsion assemblies coupled to the second wing. A flight control system is operably associated with the distributed thrust array and configured to independently control each of the propulsion assemblies. The first side of the fuselage includes a door configured to provide access to a cargo bay disposed within the fuselage from an exterior of the aircraft with a predetermined clearance relative to the first pair of propulsion assemblies.
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公开(公告)号：CA3060752A1
公开(公告)日：2020-05-01
申请号：CA3060752
申请日：2019-10-29
Applicant: BELL TEXTRON INC
Inventor： KUANG CHEN , GOYER PAUL
Abstract: A series of heated control sticks for rotorcrafts, tiltrotors, and helicopters. The heated collective and cyclic sticks feature several heater assemblies to provide localized heating for pilots and co-pilots. The heater assemblies are formed from several layers of fabrics and resistive materials designed to generate heat while current is provided to conductive materials in the resistive material. A controller provides individualized control for users to adjust the temperature of various zones associated with either the collective stick or the cyclic stick. The heater assemblies can be installed entirely external to the stick like in a retrofit or partially internally.
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公开(公告)号：CA3083284C
公开(公告)日：2022-11-22
申请号：CA3083284
申请日：2020-06-11
Applicant: BELL TEXTRON INC
Inventor： FENNY CARLOS ALEXANDER , BRODEUR NICHOLAS , CHARRON LOUIS , MORRIS KEVIN
Abstract: A method of pitching rotor blades by interrupting torque applied to the hub.
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公开(公告)号：CA3141756A1
公开(公告)日：2022-08-11
申请号：CA3141756
申请日：2021-12-09
Applicant: BELL TEXTRON INC
Inventor： HULL MICHAEL RAYMOND , LOVELAND STEVEN , FAN YUE
Abstract: A configurable electrical architecture for an eVTOL aircraft having a takeoff and landing power mode and a cruise power mode. The configurable electrical architecture includes a power-optimized power source including a high-power battery array and an energy-optimized power source selected from a plurality of interchangeable energy-optimized power sources including a high-energy battery array, a hydrogen fuel cell system and a turbo-generator system. A distribution system is electrically coupled to the power-optimized power source and the energy-optimized power source. At least one electric motor is electrically coupled to the distribution system. In the takeoff and landing power mode, both the power-optimized power source and the energy-optimized power source provide electrical power to the at least one electric motor. In the cruise power mode, the energy-optimized power source provides electrical power to the at least one electric motor and to the power-optimized power source to recharge the high-power battery array.
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