ハイブリッド推進式垂直離着陸航空機 - Aurora Flight Sciences Corporation

Title:

ハイブリッド推進式垂直離着陸航空機

Document Type and Number:

Japanese Patent JP6942710

Kind Code:

B2

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.

More Like This:

WO/2019/225859	FLYING OBJECT AND FLYING OBJECT POSITION CONTROL SYSTEM
WO/2004/089746	NON-ARTICULATED ROTOR AND ROTORCRAFT COMPRISING A ROTOR OF THIS TYPE
WO/1997/016342	FILIMONOV HYBRID DIRIGIBLE CRAFT

Inventors:

Giannini, Francesco
Gomez, Martin
Cottrell, Dan
Reed, Jean-Charles
Roberts, Tom
Schaefer, Carl G., Junior
Corus, durian
Whipple, Brian
Tim, new fur
Hunter herbs
Grace, Jonathan
Steve, Petro

Application Number:

JP2018537536A

Publication Date:

September 29, 2021

Filing Date:

January 12, 2017

Export Citation:

Click for automatic bibliography generation Help