Textron Innovations Patente

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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.

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.

The present invention includes a bypass apparatus for lubricant in an unregulated pressurized gearbox (202) including: a block (204) including a lubricant inlet (210) in fluid communication with a pressure relief valve (212), wherein the pressure relief valve (212) diverts lubricant into the gearbox (202) or into an oil filter, wherein lubricant is returned to the gearbox (202) when the lubricant is cold and/or pressure at the pressure relief valve (212) is high to reduce damage to the gearbox (202) caused by high pressure during a cold start, and when the lubricant temperature increases and the pressure is reduced the pressure relief valve (212) closes and lubricant enters the oil filter.

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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.

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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.

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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.

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).

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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).

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<div notation="docdba" type="abstract" xml:lang="en"><p>A rotorcraft (101) includes a flight control computer (FCC) (201), a GPS receiver (402) configured to calculate a groundspeed based on a first carrier signal, and an attitude and heading reference system (AHRS) (404) configured to determine an acceleration of the rotorcraft. The AHRS (404) is operable to receive an indication of the groundspeed from the GPS receiver (402) and to calculate a velocity of the rotorcraft (101) based on the indication of the groundspeed and the acceleration. The FCC (201) is operable to receive an indication of the velocity from the AHRS (404), to generate the flight control device control signal according to the indication of velocity, and to send a flight control device control signal to one or more flight control devices.</p></div>