Reconfigurable unmanned aircraft system

Patent metadata

Field	Value
Publication number	US-2016159472-A1
Application number	US-201514639369-A
Country	US
Kind code	A1
Filing date	Mar 5, 2015
Priority date	Dec 4, 2014
Publication date	Jun 9, 2016
Grant date	—

Abstract

A reconfigurable unmanned aircraft system is disclosed. A system and method for configuring a reconfigurable unmanned aircraft and system and method for operation and management of a reconfigurable unmanned aircraft in an airspace are also disclosed. The aircraft is selectively reconfigurable to modify flight characteristics. The aircraft comprises a set of rotors. The position of at least one rotor relative to the base can be modified by at least one of translation of the rotor relative to the boom, pivoting of the boom relative to the base, and translation of the boom relative to the base; so that flight characteristics can be modified by configuration of position of at least one rotor relative to the base. A method of configuring an aircraft having a set of rotors on a mission to carry a payload comprises the steps of determining properties of the payload including at least mass properties, determining the manner in which the payload will be coupled to the aircraft, determining configuration for each of the rotors in the set of rotors at least partially in consideration of the properties of the payload, and positioning the set of rotors in the configuration for the aircraft to perform the mission.

First claim

1 - 162 . (canceled)

163 . A method of reconfiguring selectively reconfigurable aircraft for unmanned flight comprising the steps of:
(a) positioning a first rotor on a first boom coupled to the base; (b) positioning a second rotor on a second boom coupled to the base; (c) modifying the position of at least one rotor relative to the base; wherein position of the rotor relative to the base can be modified by at least one of (1) translation of the rotor relative to the boom; (2) pivoting of the boom relative to the base; (3) translation of the boom relative to the base; so that flight characteristics can be modified by reconfiguration of the position of at least one rotor relative to the base.

164 . The method of claim 163 wherein position of a rotor on a boom can be modified by at least one of (4) retraction of the boom relative to the base; (5) pivoting of the rotor relative to the boom; (6) raising the height of the boom relative to the base; (7) lowering the height of the boom relative to the base; (8) rotating the rotor relative to boom; and (9) rotating the boom relative to the base.

165 . (canceled)

166 . The method of claim 163 further comprising at least one of: positioning a third rotor on a third boom coupled to the base; positioning a fourth rotor on a fourth boom coupled to the base; positioning a fifth rotor on a fifth boom coupled to the base; positioning a sixth rotor on a sixth boom coupled to the base; positioning a seventh rotor on a seventh boom coupled to the base; and positioning an eighth rotor on an eighth boom coupled to the base.

167 - 171 . (canceled)

172 . The method of claim 163 wherein flight characteristics can be modified by at least one of: (a) changing rotation speed of at least one rotor; (b) changing pitch of vanes of at least one rotor; (c) changing position of a rotor relative at least one other rotor; (d) modifying the positioning of one boom relative to another boom; and (e) modifying the positioning of one rotor relative to the base.

173 . The method of claim 163 wherein flight characteristics comprise at least one of aerodynamic profile, maneuverability, available thrust, available lift, energy consumption, energy efficiency, mass, mass properties, center of mass, center of gravity, balance point, stability, controllability, control axes, maximum relative ground velocity, maximum relative air speed, ascent rate, descent rate, sink rate, flight altitude, aerodynamic drag, number of operational rotors, control system type, equipment status.

174 . The method of claim 163 wherein flight characteristics can be modified in response to operating conditions for a mission.

175 . The method of claim 174 wherein operating conditions for a mission comprise at least one of operability of each rotor, energy storage capacity, remaining energy storage, payload profile, payload mass, payload type, payload shape, payload size, payload changes, route, altitude, traffic, weather conditions, weather effects, wind velocity, wind direction, distance of mission, remaining distance of mission, time for mission, remaining time for mission, fuel storage capacity, remaining fuel, energy storage capacity, remaining stored energy.

176 - 188 . (canceled)

189 . The method of claim 174 further comprising the step of responding to a change in operating conditions.

190 . The method of claim 189 wherein responding comprises the step of changing rotor speed.

191 . The method of claim 190 wherein if change in rotor speed is beyond a limit of off-design-point rotor speed then responding further comprises changing rotor position.

192 - 194 . (canceled)

195 . The method of claim 163 wherein each rotor comprises a set of blades rotating on an axis, the method further comprising adjusting pitch of blades of the rotor.

196 . (canceled)

197 . The method of claim 163 further comprising anticipating a rotor malfunction so that reconfiguration of the rotor occurs before malfunction.

198 . A method of reconfiguring selectively reconfigurable aircraft for unmanned flight having a set of rotors configured to provide lift for propulsion with at least one rotor that is at least partially malfunctioning comprising the steps of:
(a) identifying the rotor that is malfunctioning; (b) identifying at least one rotor that is able to function and is in an initial position; (c) repositioning the at least one rotor that is able to function from the initial position to a reconfigured position; so that the at least one functional rotor when after reconfiguration in the reconfigured position is able to compensate for the loss of function of the malfunctioning rotor.

199 . The method of claim 198 wherein the aircraft comprises a base and wherein repositioning of a rotor comprises positioning the rotor relative to the base.

200 . (canceled)

201 . The method of claim 198 wherein a malfunctioning comprises at least one of a rotor being (a) unable to provide commanded rotation speed; (b) unable to provide expected thrust; (c) unable to be given intended blade pitch; (d) unable to be positioned to the intended rotor position.

202 - 204 . (canceled)

205 . The method of claim 198 further comprising monitoring at least one of (a) rotational speed of rotor, (b) force at rotor bearings, (c) force applied at rotor mount, (d) vibration at rotor, (e) temperature at rotor; (f) performance of motor for a rotor.

206 - 208 . (canceled)

209 . The method of claim 198 further comprising anticipating a rotor malfunction so that reconfiguration of the rotor occurs before malfunction.

210 . The method of claim 198 wherein identifying comprises at least one of identifying the rotor that is malfunctioning is done prior to a malfunction and identifying a rotor that is inoperable.

211 - 212 . (canceled)

213 . The method of claim 198 wherein identifying comprises monitoring that includes at least one of acoustic monitoring, visual monitoring, vibration monitoring, stress/strain monitoring, and data monitoring.

214 - 219 . (canceled)

220 . The method of claim 198 further comprising the step of retracting the malfunctioning rotor by at least one of a translating movement and a pivoting movement.

221 - 226 . (canceled)

227 . The method of claim 198 wherein repositioning a rotor comprises at least one of (1) extending the boom; (2) retracting the boom; (3) elevating the boom relative to the base; (4) lowering the boom relative to the base; (5) rotating the boom in a plane relative to the base; (6) translating the rotor along the boom; (7) tilting the rotor relative to the base; (8) rotating the rotor relative to boom; (9) rotating the boom relative to the base.

228 - 231 . (canceled)

232 . The method of claim 198 further comprising the step of hovering the aircraft during the step of repositioning at least one rotor.

233 - 236 . (canceled)

237 . The method of claim 198 further comprising at least one of repositioning pitch of blades of the functional rotor; repositioning pitch of vanes of the functional rotor; regulating rotational speed of the functional rotor; and restricting thrust produced by the functional rotor.

238 - 249 . (canceled)

Assignees

• Elwha Llc

Inventors

• Chan Alistair K
• Cheatham Iii Jesse R
• Chin Hon Wah
• Duncan William David
• Hyde Roderick A
• Ishikawa Muriel Y
• Kare Jordin T
• Pan Tony S
• Petroski Robert C
• Tegreene Clarence T
• Tuckerman David B
• Weaver Thomas Allan
• Wood Jr Lowell L

Classifications

• B64U2101/60

  for transporting passengers; for transporting goods other than weapons · CPC title

• B64C27/08 Primary

  with two or more rotors · CPC title

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title

• B64C27/37

  having articulated joints · CPC title

• B64C27/54

  Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement · CPC title