Aircraft with integrated lift and propulsion system
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-029/00
B64C-003/10
B64C-027/28
B64C-027/467
B64C-003/38
출원번호
US-0010382
(2013-08-26)
등록번호
US-8939393
(2015-01-27)
발명자
/ 주소
Karem, Abe
출원인 / 주소
Karem, Abe
대리인 / 주소
Fish & Tsang, LLP
인용정보
피인용 횟수 :
0인용 특허 :
10
초록▼
A vertical take off and landing (VTOL) aircraft is designed to be so efficient that it can be commercially competitive with runway dependent aircraft operating in a range of 100 to 1000 miles. Improvements include a high efficiency tilting rotor and wing design that enable both vertical takeoff and
A vertical take off and landing (VTOL) aircraft is designed to be so efficient that it can be commercially competitive with runway dependent aircraft operating in a range of 100 to 1000 miles. Improvements include a high efficiency tilting rotor and wing design that enable both vertical takeoff and efficient high speed cruising, a high aspect ratio wing, and a variable speed propulsion system that is efficient in both hover and cruise flight. Preferred aircraft use thin inboard and outboard wings, thin rotor blades, and use efficient lightweight design to achieve unusually low empty weight fraction. Inventive methods include utilization of advanced design and analysis techniques, which allow for accurate prediction of an aircraft's physical behavior.
대표청구항▼
1. A flight operational tilt rotor aircraft, comprising: a fuselage;a rotor having a diameter of at least 20 feet, with at least first and second radially extending rotor blades, and disc loading of at least 23-30 pounds per square foot at a maximum hover weight;a propulsion system that rotates the
1. A flight operational tilt rotor aircraft, comprising: a fuselage;a rotor having a diameter of at least 20 feet, with at least first and second radially extending rotor blades, and disc loading of at least 23-30 pounds per square foot at a maximum hover weight;a propulsion system that rotates the rotor at variable speed during forward flight to at least as low as 70 -75% of maximum rpm in hover;an inboard wing that couples the rotor to the fuselage; anda tilting outboard wing coupled to the inboard wing. 2. The aircraft of claim 1, wherein the fuselage has a fineness ratio of at least 4. 3. The aircraft of claim 1, wherein the fuselage has a cross sectional area between 3%-12% of a planform area of the inboard wing. 4. The aircraft of claim 1, wherein the rotor has a diameter of at least 40 feet. 5. The aircraft of claim 1, wherein the rotor has a disc loading of 30-40 pounds per square foot at a maximum hover weight. 6. The aircraft of claim 1, wherein the rotor has a disc loading of 40-50 pounds per square foot at a maximum hover weight. 7. The aircraft of claim 1, wherein the rotor has a disc loading of 50-60 pounds per square foot at a maximum hover weight. 8. The aircraft of claim 1, wherein the rotor has a disc loading of 60-70 pounds per square foot at a maximum hover weight. 9. The aircraft of claim 1, wherein the rotor is configured to provide a cruise propulsion efficiency of at least 0.83. 10. The aircraft of claim 1, wherein the rotor is configured to propel the aircraft in forward cruise speed of at least Mach 0.55. 11. The aircraft of claim 1, wherein the propulsion system rotates the rotor during forward flight to at least as low as 50% to 60% of maximum rpm in hover. 12. The aircraft of claim 1, wherein the propulsion system rotates the rotor during forward flight to as low as 30% to 50% of maximum rpm in hover. 13. The aircraft of claim 1, where the inboard wing has an aspect ratio of at least 5. 14. The aircraft of claim 1, where the inboard wing has an aspect ratio of at least 10. 15. The aircraft of claim 1, where the inboard wing has a wing loading of at least 60 pounds per square foot at maximum take-off weight. 16. A flight operational tilt rotor aircraft, comprising: a fuselage;a rotor having a diameter of at least 20 feet, with at least first and second radially extending rotor blades, wherein the rotor is configured to propel the aircraft in forward cruise speed of at least Mach 0.55;a propulsion system that rotates the rotor at variable speed during forward flight to at least as low as 70-75% of maximum rpm in hover;an inboard wing that couples the rotor to the fuselage; anda tilting outboard wing coupled to the inboard wing. 17. The aircraft of claim 16, wherein the fuselage has a fineness ratio of at least 4. 18. The aircraft of claim 16, wherein the fuselage has a cross sectional area between 3%-12% of a planform area of the inboard wing. 19. The aircraft of claim 16, wherein the rotor has a diameter of at least 40 feet. 20. The aircraft of claim 16, wherein the rotor has a disc loading of 23-30 pounds per square foot at a maximum hover weight. 21. The aircraft of claim 16, wherein the rotor has a disc loading of 30-40 pounds per square foot at a maximum hover weight. 22. The aircraft of claim 16, wherein the rotor has a disc loading of 40-50 pounds per square foot at a maximum hover weight. 23. The aircraft of claim 16, wherein the rotor has a disc loading of 50-60 pounds per square foot at a maximum hover weight. 24. The aircraft of claim 16, wherein the rotor has a disc loading of 60-70 pounds per square foot at a maximum hover weight. 25. The aircraft of claim 16, wherein the rotor is configured to provide a cruise propulsion efficiency of at least 0.83. 26. The aircraft of claim 16, wherein the propulsion system rotates the rotor during forward flight to at least as low as 50% to 60% of maximum rpm in hover. 27. The aircraft of claim 16, wherein the propulsion system rotates the rotor during forward flight to as low as 30% to 50% of maximum rpm in hover. 28. The aircraft of claim 16, where the inboard wing has an aspect ratio of at least 5. 29. The aircraft of claim 16, where the inboard wing has an aspect ratio of at least 10. 30. The aircraft of claim 16, where the inboard wing has a wing loading of at least 60 pounds per square foot at maximum take-off weight.
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이 특허에 인용된 특허 (10)
Dornier ; Jr. ; deceased Claudius (Viehrutenweg 3 late of Hochstadt DEX) Dornier-Tiefenthaler ; legal representative by Martine (Viehrutenweg 3 D-8031 Hochstadt DEX) Windischbauer Florian (Buerlinsha, Aircraft with engine pods tiltable about a transverse axis.
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