System and method for operation and management of reconfigurable unmanned aircraft

Patent metadata

Field	Value
Publication number	US-2016159471-A1
Application number	US-201514630114-A
Country	US
Kind code	A1
Filing date	Feb 24, 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 . A method of configuring an aircraft having a set of repositionable rotors for unmanned flight on a mission to carry a payload from an initial configuration into a configuration for the mission comprising the steps of:
(a) determining properties of the payload including at least mass properties; (b) determining the manner in which the payload will be coupled to the aircraft; (c) determining a configuration for the mission for each of the rotors in the set of rotors at least partially in consideration of the properties of the payload; (d) positioning the set of rotors into the configuration for the mission for the aircraft to perform the mission.

2 . The method of claim 1 wherein the configuration for the mission is different from the initial configuration.

3 . The method of claim 1 wherein determining the configuration for the mission comprises at least one of at least partially considering flight characteristics for the aircraft and at least partially considering anticipated operating conditions for the aircraft.

4 . (canceled)

5 . The method of claim 1 wherein the step of positioning the set of rotors comprises repositioning the set of rotors from the initial configuration into the configuration for the mission in consideration of the properties of the payload and desired flight characteristics for the mission.

6 . The method of claim 1 wherein the initial configuration is a storage configuration used to store the aircraft in a compact arrangement when not in use and the configuration for the mission is a flight configuration used when the aircraft is to be in flight to carry payload.

7 - 11 . (canceled)

12 . The method of claim 1 further comprising the step of operating the aircraft in the configuration.

13 . The method of claim 1 further comprising the step of determining flight characteristics for the aircraft with payload.

14 . The method of claim 1 further comprising the step of evaluating operating conditions for the mission.

15 - 34 . (canceled)

35 . The method of claim 3 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, or (c) changing position of a rotor relative at least one other rotor.

36 . The method of claim 3 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.

37 . The method of claim 3 wherein flight characteristics can be modified in response to operating conditions for a mission.

38 - 41 . (canceled)

42 . The method of claim 1 wherein the aircraft comprises a base and the set of rotors is coupled to the base and wherein configuration of a rotor on a boom 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.

43 . The method of claim 1 wherein the aircraft comprises a base and the set of rotors is coupled to the base and wherein configuration of a rotor on a boom relative to the base 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) rotation of a rotor relative to the base; (9) rotational twist of the boom relative to the base; (10) changing spacing of the rotor relative to another rotor; (11) changing incline of the rotor; (12) changing horizontal position of the rotor relative to the base; (13) changing the vertical position of the rotor relative to the base; (14) moving the rotor inward relative to the base; (15) moving the rotor outward relative to the base; (16) tilting the rotor; (17) changing the rotor thrust; (18) disabling the rotor; (19) adjusting the pitch of vanes of a rotor; (20) changing the rotation speed of the rotor.

44 - 87 . (canceled)

88 . The method of claim 1 wherein the aircraft comprises a base and the set of rotors is coupled to the base and wherein a payload having a mass is carried and the position of at least one rotor is modified to compensate for the position of the mass of the payload relative to the base.

89 . The method of claim 1 wherein the aircraft comprises a base and the set of rotors is coupled to the base and wherein at least one rotor is repositioned relative to the base to compensate for the mass of the payload.

90 - 101 . (canceled)

102 . The method of claim 1 wherein the configuration is reconfiguration of rotor position and the reconfiguration of rotor position is during a mission to at least one of compensate for a change in center of mass of the aircraft, compensate for a change in mass properties balance of the aircraft, and rebalance mass properties after partial delivery of payload.

103 . (canceled)

104 . (canceled)

105 - 143 . (canceled)

144 . A method of operating a reconfigurable multi-rotor unmanned aircraft having flight characteristics for a mission comprising flight with payload in operating conditions comprising the steps of:
(a) configuring the aircraft in an ascent configuration with flight characteristics for ascent to start a flight; (b) configuring the aircraft in a first flight configuration with flight characteristics for flight in operating conditions; wherein configuring the aircraft comprises positioning of at least one rotor of the aircraft into the configuration; wherein flight characteristics of the aircraft include consideration of properties of any payload carried by the aircraft.

145 - 153 . (canceled)

154 . The method of claim 144 further comprising the step of configuring the aircraft in a descent configuration with flight characteristics for descent to conclude a flight.

155 . The method of claim 144 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, or (c) changing position of a rotor relative at least one other rotor.

156 . The method of claim 144 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.

157 . The method of claim 144 wherein flight characteristics of the aircraft with payload comprise effects of the payload including aerodynamic drag effects of the payload.

158 . The method of claim 144 wherein flight characteristics can be modified in response to operating conditions for a mission.

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

• B64C27/52

  Tilting of rotor bodily relative to fuselage (of see-saw type construction B64C27/43) · CPC title

• B64U50/11

  using internal combustion piston engines · CPC title

• B64U50/19

  using electrically powered motors · CPC title

• B64U30/293 Primary

  Foldable or collapsible rotors or rotor supports · CPC title