Helicopter with blade-tip thrusters and annular centrifugal fuel supply tank and concentric cabin and fuselage

摘要

A helicopter includes a rotor with short blades and tip thrusters. The blades extend from an annular fuel tank that rotates with the blades. Centrifugal force propels fuel from the interior compartment of the annular tank, through conduits extending through the blades from root to tip, to the tip thrusters. Valves (e.g., solenoid valves and/or a flyweight governor) regulate fuel flow to achieve and maintain a determined steady rotational speed. A fuselage covered by a canopy is mounted atop a bearing on the annular fuel tank. The pitch of each blade may be adjusted collectively and cyclically using a swash ring and hydraulic linear actuators.

主权项

1. A thruster powered helicopter comprising
a fuselage having an outer periphery of circular cross section of a first diameter, and a rotating annular fuel tank having an inner periphery of circular cross section of a second diameter and an outer periphery, said second diameter being greater than the first diameter, said rotating annular fuel tank having an interior fuel compartment for containing a fuel, and said fuselage and rotating annular fuel tank being concentric, and a swash ring disposed between the fuselage and rotating annular fuel tank, said swash ring having a grooved outer periphery, and a plurality of thrusters mechanically coupled to the outer periphery of the rotating annular fuel tank, a fuel supply line extending from the interior fuel compartment of the annular fuel tank to each of the plurality of thrusters, and each of said plurality of thrusters combusting fuel from said interior fuel compartment to produce thrust, and said thrust causing said rotating annular fuel tank to rotate relative to the fuselage, and rotation of said rotating annular fuel tank expelling fuel from said interior fuel compartment through each fuel supply line to each of said plurality of thrusters for combustion and consequent thrust; a blade for each of the plurality of thrusters, the blade being coupled to the outer periphery of the rotating annular fuel tank and extending from the outer periphery of the rotating annular fuel tank to one of the plurality of thrusters, each blade mechanically coupling the outer periphery of the rotating annular fuel tank to one of the plurality of thrusters, each blade having an airfoil cross-section shape and generating aerodynamic lift when rotated with said rotating annular fuel tank; and each blade mounted to a crank arm and being pivotally coupled by the crank arm to the rotating annular fuel tank, said crank arm allowing pivoting adjustment of the pitch of each blade, said crank arm including a free engageable for pivoting adjustment of the pitch of each blade.