Hybrid propulsion vertical take-off and landing aircraft

US10926874B2 · kind B2 · utility

Assignee

• Aurora Flight Sciences Corporation · US

Inventors

• Francesco Giannini · Falls Church, US
• Martin Gomez · Fairfax, US
• Daniel Cottrell · Centreville, US
• Jean-Charles Lede · Manassas, US
• Thomas A. Roberts · Morristown, US
• Carl G. Schaefer, Jr. · Salem, US
• Dorian Frederic Marie Colas · Seattle, US
• Brian Whipple · Manassas, US
• Timothy Nuhfer · Sterling, US
• Herbert E. Hunter · Rochester, US
• Jonathan Grohs · Manassas, US
• Steve Petullo · Bristow, US

Key dates

• Filing date: Jan 11, 2017
• Grant date: Feb 23, 2021
• Expiry date: Aug 22, 2038

Classification

• Technology area (CPC Y): Emerging Cross-Sectional Technologies
• CPC primary: Y02T50/60
• WIPO field: Transport
• WIPO sector: Mechanical engineering

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.