Methods for providing a durable solar powered aircraft with a variable geometry wing
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G05D-001/00
B64C-039/02
B64F-005/00
B64C-003/42
B64D-027/24
B64C-003/16
B64C-011/28
H02S-010/40
H02S-040/38
B64F-005/10
출원번호
US-0052699
(2016-02-24)
등록번호
US-10005541
(2018-06-26)
발명자
/ 주소
Karem, Abe
Tigner, Benjamin
출원인 / 주소
KAREM AIRCRAFT, INC.
대리인 / 주소
Fish IP Law, LLP
인용정보
피인용 횟수 :
0인용 특허 :
12
초록▼
Methods of manufacturing and operating a solar powered aircraft having segmented wings that can be reconfigured during flight to optimize collection of solar energy are described. The aircraft have rigid construction that is resistant to inclement weather and is configured to rely on free flight con
Methods of manufacturing and operating a solar powered aircraft having segmented wings that can be reconfigured during flight to optimize collection of solar energy are described. The aircraft have rigid construction that is resistant to inclement weather and is configured to rely on free flight control at high altitude and under conventional conditions, thereby providing flight duration in excess of 2 months. The aircraft is particularly suitable for use as part of a telecommunications network.
대표청구항▼
1. A method of manufacturing a solar powered aircraft comprising: molding a plurality of wing segments using a composite material;assembling a wing comprising a plurality of the wing segments, wherein at least two of the plurality of wing segments are joined by a hinge and wherein at least one of th
1. A method of manufacturing a solar powered aircraft comprising: molding a plurality of wing segments using a composite material;assembling a wing comprising a plurality of the wing segments, wherein at least two of the plurality of wing segments are joined by a hinge and wherein at least one of the at least two segments comprises a photovoltaic cell coupled to at least one of at least two segments and is configured to supply electrical power to the aircraft, wherein the wing has a stiffness that provides a natural frequency that is greater than or equal to 1.3 Hz times (100 ft/wing span, ft)1.5,wherein the hinge is configured to reversibly deflect at least one of the at least two segments to a positive or negative dihedral angle while the aircraft is in flight, andwherein the aircraft has a center of gravity having a positive static pitch stability margin of at least 3% of mean aerodynamic chord;coupling a plurality of motor-propeller assemblies each comprising a variable pitch propeller to a central segment of the aircraft, and wherein greater than 50% of the motor-propeller assemblies are coupled to the central segment of the aircraft;incorporating an active control surface that is coupled with an actuator into the aircraft; andincorporating a controller that is communicatively coupled with at least one of the plurality of motor-propeller assemblies and with the actuator into the aircraft, wherein the controller is configured to optimize flight reliability of the aircraft through provision of a first command to the at least one of the plurality of motor-propeller assemblies in slow response conditions and wherein the controller is second command to the actuator in rapid response conditions, wherein the controller is configured to provide an actuator duty cycle of less than 5% during a flight duration of at least 2 months. 2. The method of claim 1, wherein the aircraft does not include a tail, and wherein the wing has a stiffness that provides a natural frequency that is greater than or equal to 3.2 Hz times (100 ft/wing span, ft)1.5. 3. The method of claim 1, wherein the wing is a swept wing. 4. The method of claim 1, wherein each of the assemblies comprises an electric motor that is directly plurality of motor-propeller coupled to a propeller. 5. The method of claim 1, wherein slow response conditions comprise calm weather conditions. 6. The method of claim 1, wherein rapid response conditions comprise inclement weather conditions. 7. The method of claim 1, wherein the controller is configured to maintain flight endurance of the aircraft at an altitude of at least 50,000 feet for at least 2 winter months at from 400 N latitude to 300 S latitude. 8. The method of claim 1, wherein the controller is configured to maintain flight endurance of the aircraft at an altitude of at least 50,000 feet for up to 5 years at from 400 N latitude to 300 S latitude. 9. The method of claim 1, wherein the controller is configured to provide an actuator duty cycle of less than 2.5% during a flight duration of at least 2 months. 10. The method of claim 1, wherein the controller is configured to provide an actuator duty cycle of less than 1% during a flight duration of at least 2 months. 11. The method of claim 1, wherein the controller utilizes free flight control in slow response conditions, wherein free flight control utilizes only the motor-propeller assemblies. 12. The method of claim 1, further comprising the step of incorporating a telecommunications transmitter/receiver into the aircraft. 13. The method of claim 1, further comprising the step of incorporating an energy storage device selected from the group consisting of a battery, a fuel cell, and a capacitor bank, wherein the energy storage device is electrically coupled to the photovoltaic cell. 14. A method of controlling a solar powered aircraft comprising: providing a solar powered aircraft comprising a wing, the wing comprising a plurality of the wing segments, wherein at least two of the plurality of wing segments are joined by a hinge and wherein at least one of the at least two segments comprises a photovoltaic cell coupled to at least one of at least two segments and is configured to supply electrical power to the aircraft, wherein the wing has a stiffness that provides a natural frequency that is greater than or equal to 1.3 Hz times (100 ft/wing span, ft)1.5, wherein the hinge is configured to reversibly deflect at least one of the at least two segments to a positive or negative dihedral angle while the aircraft is in flight, and wherein the aircraft has a center of gravity having a positive static margin of at least 3% of mean aerodynamic chord;directing the aircraft in a free flight mode for a first portion of a flight duration of at least 2 months, wherein the first portion comprises at least 95% of the flight duration; anddirecting the aircraft in an active mode for a second portion of the flight duration,wherein the active mode comprises use of a control surface comprising an actuator, and free flight mode does not include use of active control of the aircraft. 15. The method of claim 14, wherein the free flight mode consists of adjustment of a motor speed. 16. The method of claim 14, wherein the free flight mode is implemented in slow response conditions. 17. The method of claim 14, wherein the active mode is implemented in fast response conditions. 18. The method of claim 17, wherein fast response conditions are selected from the group consisting of takeoff, landing, inclement weather, and remotely-directed course changes. 19. The method of claim 14, wherein the control surface is an elevator or an aileron. 20. The method of claim 14, wherein the first portion is selected to reduce wear of the actuator to provide function of the actuator for the flight duration. 21. The method of claim 20, wherein the flight duration is from 2 months to 5 years. 22. The method of claim 14, wherein both free flight mode and active mode are controlled by a controller located on the aircraft.
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이 특허에 인용된 특허 (12)
Hibbs Bart D. ; Lissaman Peter B. S. ; Morgan Walter R. ; Radkey Robert L., Aircraft.
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