[특허]System and method for operation and management of reconfigurable unmanned aircraft

Elwha LLC

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

System and method for operation and management of reconfigurable unmanned aircraft

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G05D-001/00 B64C-039/02 B64C-027/08 B64C-027/52 B64D-027/26 B64D-047/08
출원번호	US-0560765 (2014-12-04)
등록번호	US-9919797 (2018-03-20)
발명자 / 주소	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.
출원인 / 주소	Elwha LLC
인용정보	피인용 횟수 : 0 인용 특허 : 38

초록
▼

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.

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1. A method of reconfiguring a selectively reconfigurable unmanned aircraft having a base, a first rotor on a first boom coupled to the base and a second rotor on a second boom coupled to the base for a mission to carry a payload, the method comprising: (a) determining an effect of the payload on flight characteristics;(b) modifying position of at least one rotor relative to the base;wherein the position of at least one of the first and second rotors relative to the base are modifiable by at least one of (1) translation of at least one of the first and second rotors relative to the first and second booms, respectively; (2) pivoting of at least one of the first and second booms relative to the base; and (3) translation of at least one of the first and second booms relative to the base;so that flight characteristics are modifiable by reconfiguration of position of at least one of the first and second rotors relative to the base. 2. The method of claim 1 wherein position of the rotor relative to the base is modifiable 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 the rotor relative to the boom; and (9) rotation of the boom relative to the base. 3. The method of claim 1 wherein determining the effect of payload on flight characteristics comprises determining the flight characteristics of the aircraft with payload. 4. The method of claim 1 wherein determining the flight characteristics comprises at least one of determining the flight characteristics of the aircraft when the aircraft is in flight on the mission, determining the flight characteristics of the aircraft before the aircraft is in flight on the mission, and determining the effect of a change in the payload during the flight. 5. The method of claim 1 wherein modifying the position of at least one rotor relative to the base is at least partially in consideration of the properties of the payload. 6. The method of claim 1 wherein translation of the rotor relative to the boom comprises translation of the rotor along the boom. 7. The method of claim 1 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, and equipment status. 8. The method of claim 1 wherein flight characteristics are modifiable at least one of in response to operating conditions for a mission and by at least one of (a) changing rotation speed of at least one rotor, (b) changing pitch of vanes of at least one rotor, and (c) changing rotor position relative to at least one other rotor. 9. The method of claim 8 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, and remaining stored energy. 10. The method of claim 8 wherein operating conditions comprises a change in the payload. 11. The method of claim 1 wherein reconfiguration is performed during a mission to rebalance mass properties after partial delivery of payload. 12. The method of claim 1 wherein reconfiguration of a rotor relative to the base is modifiable 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; (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 the 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 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 rotor thrust; (18) disabling the rotor; (19) adjusting pitch of vanes of the rotor; (20) changing rotation speed of the rotor. 13. A selectively reconfigurable aircraft for unmanned flight with payload providing flight characteristics comprising: (a) a base;(b) a first rotor on a first boom coupled to the base;(c) a second rotor on a second boom coupled to the base;(d) a monitoring system configured to monitor conditions of the aircraft including a payload;wherein position of the first rotor relative to the base is modifiable by at least one of (1) translation of the first rotor relative to the first boom; (2) pivoting of the first boom relative to the base; and (3) translation of the first boom relative to the base;wherein position of the second rotor relative to the base is modifiable by at least one of (1) translation of the second rotor relative to the second boom; (2) pivoting of the second boom relative to the base; and (3) translation of the second boom relative to the base;so that flight characteristics are modifiable by reconfiguration of the position of at least one of the first and second rotors relative to the base. 14. The aircraft of claim 13 wherein the monitoring system comprises a sensor to monitor at least one of the condition of the payload, status of the payload, rotor disability, and rotor malfunction. 15. The aircraft of claim 13 wherein the base comprises at least one of a reference point for determining rotor position, an attachment point for an article such as a payload, a power plant, energy storage for powering a rotor, a center of mass, a structure, a frame, a frame member, a space frame, and a compartment. 16. The aircraft of claim 13 wherein at least one rotor comprises at least one of the first rotor, each rotor of a rotor system, and a variable thrust rotor. 17. The aircraft of claim 13 wherein a boom comprises at least one of an arm, a member, a space frame, and a robotic arm. 18. The aircraft of claim 13 wherein each boom comprises at least one of an arm, a member, an adjustable boom, and a boom mounted on a frame of the base. 19. The aircraft of claim 13 wherein (2) pivoting of the boom relative to the base comprises at least one of (a) lateral direction or axis or (b) vertical direction or axis. 20. The aircraft of claim 13 wherein (3) translation of the boom relative to the base comprises at least one of (a) longitudinal direction or axis, (b) lateral direction or axis, or (c) vertical direction or axis. 21. The aircraft of claim 13 further comprising at least one of a fourth rotor on a fourth boom coupled to the base and a fifth rotor on a fifth boom coupled to the base. 22. The aircraft of claim 13 wherein the aircraft comprises a power plant to operate each rotor and energy storage for the power plant. 23. The aircraft of claim 22 wherein the power plant and the energy storage comprise at least one of an electric motor and a battery system, respectively, and an engine and fuel in a compartment, respectively. 24. The aircraft of claim 13 further comprising a control system for configuring rotor position. 25. The aircraft of claim 13 further comprising a monitoring system for at least one of operating conditions and each rotor. 26. The aircraft of claim 13 further comprising a control system that comprises a first system configured to change rotor rotational speed and a second system configured to change rotor position. 27. The aircraft of claim 26 wherein each rotor has a desired operating range of rotor rotational speed for operation. 28. The aircraft of claim 13 wherein one rotor is inoperable and at least one of at least one other rotor is positioned relative to the base to facilitate operation in a balanced configuration and at least one other rotor is repositioned to compensate for the inoperable rotor. 29. The aircraft of claim 13 wherein the aircraft comprises at least one of a tri-copter, a quad-copter, and a penta-copter. 30. The aircraft of claim 13 wherein anticipated disability of a rotor is predicted by a monitoring system. 31. The aircraft of claim 13 wherein the monitoring system monitors at least one of sound data, visual data, vibration data, and performance data from a rotor. 32. The aircraft of claim 13 wherein at least one rotor is configured with at least one of adjustable vanes and modifiable pitch.

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System and method for operation and management of reconfigurable unmanned aircraft

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System and method for operation and management of reconfigurable unmanned aircraft

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이 특허에 인용된 특허 (38)

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