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公开(公告)号：US10281890B1
公开(公告)日：2019-05-07
申请号：US16126062
申请日：2018-09-10
发明人： Ilan Kroo , Marshall Gusman , Neel Vora , Jim Bungener , Eric Allison
摘要： A flight control system is disclosed. In various embodiments, a flight control system includes a data storage device configured to store an aerodynamic model; and a processor coupled to the data storage device and configured to use the aerodynamic model to determine a set of actuators and for each actuator in the set a corresponding set of one or more actuator parameters to achieve a desired set of forces and moments. The aerodynamic model provides for each actuator in the set of actuator corresponding force and moment data for each of a first set of operating conditions based on a first set of simulations performed by varying one or more actuator parameters while holding other actuators at a baseline value and a second set of simulations to determine interactions between the actuator and said other actuators under each of a second set of operating conditions.
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公开(公告)号：US09845150B2
公开(公告)日：2017-12-19
申请号：US13764697
申请日：2013-02-11
发明人： Ilan Kroo
CPC分类号： B64C27/22 , B64C3/56 , B64C29/00 , B64C29/0025 , B64C39/08 , Y02T50/14 , Y02T50/145
摘要： A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotors and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotors provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight.
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公开(公告)号：US10101719B1
公开(公告)日：2018-10-16
申请号：US15838790
申请日：2017-12-12
发明人： Ilan Kroo , Marshall Gusman , Neel Vora , Jim Bungener , Eric Allison
摘要： A flight control system is disclosed. In various embodiments, a flight control system includes a data storage device configured to store an aerodynamic model; and a processor coupled to the data storage device and configured to use the aerodynamic model to determine a set of actuators and for each actuator in the set a corresponding set of one or more actuator parameters to achieve a desired set of forces and moments. The aerodynamic model provides for each actuator in the set of actuator corresponding force and moment data for each of a first set of operating conditions based on a first set of simulations performed by varying one or more actuator parameters while holding other actuators at a baseline value and a second set of simulations to determine interactions between the actuator and said other actuators under each of a second set of operating conditions.
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公开(公告)号：US20180065737A1
公开(公告)日：2018-03-08
申请号：US15811510
申请日：2017-11-13
发明人： Ilan Kroo
摘要： A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotors and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotors provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight.
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公开(公告)号：US20180086448A1
公开(公告)日：2018-03-29
申请号：US15717716
申请日：2017-09-27
发明人： Ilan Kroo , Herve Martins-Rivas , Eric Allison
IPC分类号： B64C29/00
CPC分类号： B64C29/0033 , B64C3/385 , B64C11/001
摘要： In various embodiments, a tilt-wing aircraft includes a fuselage; a first wing tiltably mounted at or near a forward end of the fuselage; and a second wing rotatably mounted to the fuselage at a position aft of the first wing. A first plurality of rotors is mounted on the first wing at locations on or near a leading edge of the first wing, with two or more rotors being mounted on wing portions on each side of the fuselage; and a second plurality of rotors mounted on the second wing at locations on or near a leading edge of the second wing, with two or more rotors being mounted on wing portions on each side of the fuselage. A flight control system generates a set of actuators and associated actuator parameters to achieve desired forces and moments.
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