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.