公开(公告)号：US20170203839A1

公开(公告)日：2017-07-20

申请号：US15403818

申请日：2017-01-11

Applicant: Aurora Flight Sciences Corporation

Inventor： Francesco Giannini ,  Martin Gomez ,  Dan Cottrell ,  Jean-Charles Lede ,  Tom Roberts ,  Carl G. Schaefer, JR. ,  Dorian Colas ,  Brian Whipple ,  Tim Nuhfer ,  Herb Hunter ,  Jonathan Grohs ,  Steve Petullo

IPC: B64C29/00 ,  B64D27/24 ,  B64D29/02 ,  B64C39/12

CPC classification number: B64C29/0033 ,  B64C3/385 ,  B64C5/04 ,  B64C5/16 ,  B64C39/024 ,  B64C39/12 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/048 ,  B64D27/24 ,  B64D29/02 ,  B64D2027/026 ,  Y02T50/14 ,  Y02T50/44 ,  Y02T50/64

Abstract: A hybrid propulsion aircraft is described having a distributed electric propulsion system. The distributed electric propulsion system includes a turbo shaft engine that drives one or more generators through a gearbox. The generator provides AC power to a plurality of ducted fans (each being driven by an electric motor). The ducted fans may be integrated with the hybrid propulsion aircraft's wings. The wings can be pivotally attached to the fuselage, thereby allowing for vertical take-off and landing. The design of the hybrid propulsion aircraft mitigates undesirable transient behavior traditionally encountered during a transition from vertical flight to horizontal flight. Moreover, the hybrid propulsion aircraft offers a fast, constant-altitude transition, without requiring a climb or dive to transition. It also offers increased efficiency in both hover and forward flight versus other VTOL aircraft and a higher forward max speed than traditional rotorcraft.

公开(公告)号：US10926874B2

公开(公告)日：2021-02-23

申请号：US15403818

申请日：2017-01-11

Applicant: Aurora Flight Sciences Corporation

Inventor： Francesco Giannini ,  Martin Gomez ,  Daniel Cottrell ,  Jean-Charles Lede ,  Thomas Roberts ,  Carl G. Schaefer, Jr. ,  Dorian Colas ,  Brian Whipple ,  Timothy Nuhfer ,  Herbert E. Hunter ,  Jonathan Grohs ,  Steve Petullo

IPC: B64C29/00 ,  B64C39/12 ,  B64D27/24 ,  B64C3/38 ,  B64C5/04 ,  B64C5/16 ,  B64D29/02 ,  B64D27/02 ,  B64C39/02

Abstract: A hybrid propulsion aircraft is described having a distributed electric propulsion system. The distributed electric propulsion system includes a turbo shaft engine that drives one or more generators through a gearbox. The generator provides AC power to a plurality of ducted fans (each being driven by an electric motor). The ducted fans may be integrated with the hybrid propulsion aircraft's wings. The wings can be pivotally attached to the fuselage, thereby allowing for vertical take-off and landing. The design of the hybrid propulsion aircraft mitigates undesirable transient behavior traditionally encountered during a transition from vertical flight to horizontal flight. Moreover, the hybrid propulsion aircraft offers a fast, constant-altitude transition, without requiring a climb or dive to transition. It also offers increased efficiency in both hover and forward flight versus other VTOL aircraft and a higher forward max speed than traditional rotorcraft.

公开(公告)号：US09056669B2

公开(公告)日：2015-06-16

申请号：US13632849

申请日：2012-10-01

Applicant: Aurora Flight Sciences Corporation

Inventor： Tom Washington ,  Thorsten Hisam ,  Martin Gomez

IPC: G06F19/00 ,  G06G7/70 ,  B64C13/18 ,  B64D45/00 ,  G05D1/00 ,  G08G5/00

CPC classification number: B64C13/18 ,  B64C2201/145 ,  B64D45/00 ,  G05D1/0055 ,  G08G5/0021 ,  G08G5/0039 ,  G08G5/006

Abstract: The present disclosure endeavors to provide systems, methods and apparatus for ensuring aircraft compliance with governmental guidelines, such as, for example, Missile Technology Control Regime (MTCR) Category II compliance. A hardware-based system may be employed to reduce range and/or payload below predetermined ranges and a payload capacities. Also provided herein are hardware-based systems, methods, and apparatus for restricting a system's range to predetermined range and/or the payload to a predetermined limit using, for example, an Application-Specific Integrated Circuit (ASIC) installed in the flight control system.

Abstract translation: 本公开努力提供用于确保飞机遵守政府准则的系统，方法和装置，例如导弹技术控制制度（MTCR）II类遵守。 可以采用基于硬件的系统来减小低于预定范围和有效载荷容量的范围和/或有效载荷。 本文还提供了基于硬件的系统，方法和装置，其使用例如安装在飞行控制系统中的专用集成电路（ASIC）将系统的范围限制到预定范围和/或有效负载到预定极限 。

公开(公告)号：US20130085629A1

公开(公告)日：2013-04-04

申请号：US13632849

申请日：2012-10-01

Applicant: Aurora Flight Sciences Corporation

Inventor： Tom Washington ,  Thorsten Hisam ,  Martin Gomez

IPC: G06F17/00

CPC classification number: B64C13/18 ,  B64C2201/145 ,  B64D45/00 ,  G05D1/0055 ,  G08G5/0021 ,  G08G5/0039 ,  G08G5/006

Abstract: The present disclosure endeavors to provide systems, methods and apparatus for ensuring aircraft compliance with governmental guidelines, such as, for example, MRCR Category II compliance. A hardware-based system may be employed to reduce range and/or payload below predetermined ranges and a payload capacities. Also provided herein are hardware-based systems, methods, and apparatus for restricting a system's range to predetermined range and/or the payload to a predetermined limit using, for example, a Application-Specific Integrated Circuit (ASIC) installed in the flight control system.

Abstract translation: 本公开努力提供用于确保飞机遵守政府准则的系统，方法和装置，例如MRCR II类合规。 可以采用基于硬件的系统来减小低于预定范围和有效载荷容量的范围和/或有效载荷。 本文还提供了基于硬件的系统，方法和装置，其使用例如安装在飞行控制系统中的专用集成电路（ASIC）将系统的范围限制到预定范围和/或有效负载到预定极限 。