Aircraft with integrated lift and propulsion system
View Patent ↗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.
1. An aircraft, comprising
a propulsion system with a rotor that lifts the aircraft, and
the rotor having sufficient area to hover the aircraft with a rotor disc loading of at most 60 pounds per square foot at the maximum hover takeoff weight of the aircraft at sea level and standard atmosphere; and
wherein the rotor is configured to propel the aircraft in forward cruise speed of at least Mach 0.55 and a rotor speed less than 70% of maximum rpm in hover.
2. The aircraft of claim 1 , further comprising a second rotor, wherein both the rotor and the second rotor are used for lifting the aircraft, and are tilting rotors.
3. The aircraft of claim 2 , wherein the rotors operate together to supply the only propulsive forces in forward flight.
4. The aircraft of claim 1 , wherein the propulsion system comprises:
a mechanism that tilts the rotor:
the rotor has dimensions that provide a hover Figure of Merit of between 0.83 and 0.90 at the disc loading; and
the dimensions also provide the rotor with cruise propulsion efficiency at between 0.83 and 0.92 at a flight Mach of 0.6 while producing at most 5% of the maximum rotor thrust in hover at sea level and standard atmosphere.
5. The aircraft of claim 1 , wherein the rotor is configured to provide a cruise propulsion efficiency of at least 0.83.
6. The aircraft of claim 1 , wherein the rotor is configured to propel the aircraft in forward cruise speed of at least Mach 0.6.
7. The aircraft of claim 1 , wherein the rotor supplies the only propulsive force in forward flight.
8. The aircraft of claim 7 , where the aircraft has a configuration that achieves a cruise lift-to-drag ratio of between 13 and 26 at a flight Mach of 0.65.
9. The aircraft of claim 7 , where the aircraft has a configuration that achieves a level cruise speed of more than Mach 0.65.
10. The aircraft of claim 7 , where the aircraft has a configuration that achieves a cruise lift-to-drag ratio of at least 13 at a cruise speed of Mach of 0.60.
11. The aircraft of claim 7 , where the rotor disc loading is less than 50 pounds per square foot at the maximum hover takeoff weight of the aircraft.
12. The aircraft of claim 7 , where the rotor disc loading is of less than 40 pounds per square foot at the maximum hover takeoff weight of the aircraft.
13. The aircraft of claim 7 , wherein the rotor has a maximum blade root thickness ratio of less than 25%.
14. The aircraft of claim 7 , further comprising a fixed wing with sufficient area to cruise at an altitude of at least 31,000 feet.
15. The aircraft of claim 14 , where the fixed wing has an aspect ratio of at least 10.
16. The aircraft of claim 14 , where the improvement further comprises a fuselage having a cross sectional area between 10%-15% of a planform area of the fixed wing.
17. The aircraft of claim 7 , wherein the rotor has a disc loading of no more than 30 pounds per square foot.
18. The aircraft of claim 7 , wherein the rotor has a disc loading of no more than 20 pounds per square foot.