USE OF INDIVIDUAL BLADE CONTROL ON A PROPELLER OR ROTOR IN AXIAL FLIGHT FOR THE PURPOSE OF AERODYNAMIC BRAKING AND POWER RESPONSE MODULATION

WIPO Patent Application WO/2018/223089

A3

Systems and methods are contemplated for favorably improving flight dynamics of aircraft, including enhanced aerodynamic braking and improved flight maneuverability. Air braking systems selectively position a first set of blades at a negative thrust pitch to product a net negative thrust across first and second sets of blades, while balancing torque of the drive shafts to zero. First and second sets of IBC blades can be driven by the same shaft or torque-linked shafts. Flight maneuver systems operate a powerplant at a high power mode, and dissipate the energy from the high power output by positioning a first set of IBC blades at a low efficiency pitch while maintaining constant thrust. As increased or rapid flight maneuverability is required, the first set of blades is positioned toward a high efficiency pitch to instantly increase thrust to the aircraft without requiring a related increase in energy output from the powerplant.

WO/2008/032125	MARINE PROPULSION AND CONSTRUCTIONAL DETAILS THEREOF
WO/2024/033590	PROPELLER FOR AN AIRCRAFT TURBINE ENGINE
WO/2016/030646	VARIABLE-PITCH BLADED DISC

KAREM ABE (US)
TIGNER BENJAMIN (US)

PCT/US2018/035735

January 10, 2019

June 01, 2018

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KAREM AIRCRAFT INC (US)

B64C11/30; B64C27/54; B64C29/00; B64D27/10; B64D27/24

US20050067527A1	2005-03-31
US20020187041A1	2002-12-12
US20150298803A1	2015-10-22
US20100127119A1	2010-05-27
US5054998A	1991-10-08

FISH, Robert et al. (US)

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