Flight Characteristics of a Tilt-Wing, Distributed-Propulsion, Vertical Take-Off and Landing Aircraft Concept

Abstract

Unmanned aircraft are starting to be utilized in a diverse set of applications ranging from military surveillance to railroad inspections and natural disaster damage assessment. Given the nature of these missions, runways may not be available and long distance, high endurance flights required. Fixed wing aircraft typically have the endurance required for these missions, but require long flat areas for landing, and in some cases taking off. There have been various approaches to fixed wing aircraft taking off and landing vertically, but these systems generally have reduced endurance and efficiency. A proposed solution by to this issue is ElectraWing. This aircraft concept was designed by retired Boeing Technical Fellow Darrold Cummings and utilizes a tilting wing and horizontal stabilizer, distributed propulsion, and a twin-boom design. The goal of this project was to determine the flight characteristics of the tilt-wing distributed-propulsion vertical take-off and landing aircraft concept, ElectraWing. A base airframe was selected and modified to test the concept. The effect of tilt-wing transient weight distribution on longitudinal static stability was considered and the aircraft was determined to be statically stable. Additionally, wind effects on the aircraft in VTOL flight and the effects of VTOL flight on the wing rotation joint was examined. It was found the aircraft was susceptible to wind without appropriate compensation. It was also found that VTOL flight caused high shear stress to the point of rotation on the wings.