Bell Textron Patente

In an example, a computing apparatus includes a hardware platform, having a processor and a memory, and instructions encoded within the memory to instruct the processor to receive a peak power demand for a landing maneuver of a VTOL aircraft (100) powered at least partly by a battery, receive flight profile data for a flight profile of the VTOL aircraft (100), and configuration data for the VTOL aircraft (100), estimate power consumption of the flight profile in context of the configuration, and estimate a peak power capacity (304, 404) available for the landing maneuver, and provide an error notice if the peak power capacity does not meet the peak power demand.

Zusammenfassung wird geladen …

A method (500) of modeling and integrating engine installation deltas includes receiving (502) flight data related to an aircraft that includes an engine installed therein. The flight data includes values of an engine parameter. The method also includes determining (504) values of a measured installation delta for the engine based, at least in part, on the flight data. The method also includes determining (506) values of a measured power parameter for the engine based, at least in part, on the flight data. The method also includes generating (510) a mathematical model of a plurality of installation deltas for the engine as a function of the engine parameter, where the plurality of installation deltas include the measured installation delta and an unmeasured installation delta. The method also includes validating (512) the mathematical model based, at least in part, on the values of the measured installation delta. The method also includes generating (516) a performance profile of the engine.

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

In an embodiment, a method (401) includes: obtaining a first signal from a first sensor of a rotorcraft, the first signal indicating measured angular velocity around a first axis of the rotorcraft (403); filtering the first signal with a lag compensator to estimate angular position around the first axis of the rotorcraft (405); and adjusting flight control devices of the rotorcraft according to the estimated angular position and the measured angular velocity around the first axis of the rotorcraft, thereby changing flight characteristics of the rotorcraft around the first axis of the rotorcraft.

Zusammenfassung wird geladen …

One embodiment is an electric drive system for an aircraft (100) including a motor (912), a gear box (904) associated with the motor (912), and a cooling fan (906) for drawing air into the unit across an electronic component (914) to cool the electronic component (914) and for expelling air into an oil cooler (908) for cooling oil contained therein. The electric drive system further includes an oil distribution system for distributing oil cooled by the oil cooler (908) to at least one motor (912) and at least one gearbox (904), the distributed oil being used to cool the motor (912) and the gearbox (904), a reservoir (920) for collecting the distributed oil after it has been used to cool the motor (912) and the gearbox (904), and at least one structural element (1104) for retaining the motor, gearbox, the cooling fan, the oil distribution system, and the reservoir together as a unit.

Zusammenfassung wird geladen …

In an embodiment, a rotorcraft (101) includes: a flight control computer (205) configured to: receive a first sensor signal from a first aircraft sensor (207) of the rotorcraft; receive a second sensor signal from a second aircraft sensor (207) of the rotorcraft, the second aircraft sensor being different from the first aircraft sensor; combine the first sensor signal and the second sensor signal with a complementary filter (403) to determine an estimated vertical speed of the rotorcraft; adjust flight control devices of the rotorcraft according to the estimated vertical speed of the rotorcraft, thereby changing flight characteristics of the rotorcraft; and reset the complementary filter in response to detecting the rotorcraft is grounded.

A motor assembly is described and includes a housing; a plurality of motors (406A-C) disposed within the housing; and a drive shaft comprising a plurality of interconnected drive shaft segments (410A-C), wherein each one of the drive shaft segments (410A-C) is driven by a different one of the motors (406A-C) connected to the drive shaft segment (410A-C) via an integrated overrunning clutch (412A-C).

An embodiment rotorcraft main rotor system (103), including a yoke (301), a rotor blade (105), and a grip assembly (305) attaching the rotor blade to the yoke. The grip assembly (305) includes a grip body (501) formed from a contiguous laminated composite and has a substantially constant thickness, where the grip body (501) has an upper extension (315), a lower extension (317) and a connecting portion (401) connected between an inboard end of the upper extension and an inboard end of the lower extension. An inside surface of the upper extension (315) faces, and is substantially parallel to, an inside surface of the lower extension (317), and the upper extension has first features and the lower extension has second features that are aligned with the first features, where the first features and second features each include at least one of an edge contour, attachment holes (503), or first protective elements.

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

A rotor assembly (108) including a rotor mast (130), a rotor hub (126) coupled to the rotor mast (130), a plurality of rotor blades (114) coupled to the rotor hub (126), a control tube (132) extending through the rotor mast (130), a crosshead (134) coupled to the control tube (132), and a mechanism configured to drive the rotor mast (130) in rotation. Wherein the mechanism is longitudinally positioned between a top portion (178) and a bottom portion (180) of the control tube (132) and translation of the control tube (132) relative to the rotor mast (130) causes rotation of the rotor blades (114) about their pitch-change axes (154). While the crosshead (134) is installed, the crosshead (134) is prevented from angular rotation about the mast axis (116). A pin (162) of a rotor blade assembly (128) is captured between opposing tabs (196, 198) of the crosshead (134) and movable relative to the opposing tabs (196, 198) in response to translation of the crosshead (134) along the mast axis (116).

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

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) has an airframe including first and second wings (14, 16) with a fuselage (18) extending therebetween. A propulsion assembly (22) is coupled to the fuselage (18) and includes a counter-rotating coaxial rotor system (24) that is tiltable relative to the fuselage (18) to generate a thrust vector. A flight control system (20) is configured to direct the thrust vector. In the VTOL orientation, the first wing (14) is forward of the fuselage (18), the second wing (16) is aft of the fuselage (18) and the coaxial rotor system (24) is configured to provide thrust in line with a yaw axis of the aircraft (10). In the biplane orientation, the first wing (14) is below the fuselage (18), the second wing (16) is above the fuselage (18) and the coaxial rotor system (24) is configured to provide thrust in line with a roll axis (10a) of the aircraft (10).

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …