초록 ▼

A flying apparatus having a thrust directing wing is disclosed. The flying apparatus can include a wing that receives a thrust flow from a thrust flow generator, and selectively redirect the flow in at least one of a plurality of directions. The wing can redirect the thrust flow so as to generate ve

A flying apparatus having a thrust directing wing is disclosed. The flying apparatus can include a wing that receives a thrust flow from a thrust flow generator, and selectively redirect the flow in at least one of a plurality of directions. The wing can redirect the thrust flow so as to generate vertical thrust, forward thrust, and combinations thereof. The thrust flow generator can include a gas turbine engine, which can include two rotating shafts and a common burner, with each shaft coupling a compressor with a turbine.

대표청구항 ▼

1. A flying apparatus comprising: a thrust flow generator; anda wing coupled with the thrust flow generator, the wing including a left wing portion and a right wing portion, each wing portion including an extendible wing section and an extension mechanism for extending the extendible wing section, e

1. A flying apparatus comprising: a thrust flow generator; anda wing coupled with the thrust flow generator, the wing including a left wing portion and a right wing portion, each wing portion including an extendible wing section and an extension mechanism for extending the extendible wing section, each of the left wing portion and the right wing portion further including a rotating nozzle for selective redirection of at least a portion of a thrust flow, the wing being adapted to receive the thrust flow from the thrust flow generator and selectively redirect the thrust flow in a first direction and in a second direction, wherein when the thrust flow is redirected in the first direction vertical thrust is predominantly generated, and wherein when the thrust flow is redirected in the second direction forward thrust is predominantly generated. 2. The apparatus of claim 1, further comprising a mount configured to couple the flying apparatus with a human operator so as to lift the operator, wherein the left and right wing sections comprise a first folding wing section disposed on a first side of the thrust flow generator and a second folding wing section disposed on a second side of the thrust flow generator, the second side being opposite the first side, each of the first and second folding wing sections having a folded non-flight position and a deployed flight position. 3. The apparatus of claim 2, wherein each of the first and second folding wing sections is movable between its folded non-flight position and its deployed flight position by way of rotary motion about an axis of rotation. 4. The apparatus of claim 2, wherein the first and second folding wing sections are adapted to couple with each other when in their deployed flight positions so as to provide a continuous airfoil. 5. The apparatus of claim 1, wherein each of the extension mechanisms comprises a motor driven screw. 6. The apparatus of claim 1, wherein each of the extendible wing sections comprises an aerodynamic control surface. 7. The apparatus of claim 1, wherein each of the extendible wing sections comprises a leading edge section adapted to accommodate a rotation of one of the rotating nozzles. 8. The apparatus of claim 1, wherein the thrust flow generator comprises a gas turbine engine. 9. The apparatus of claim 1, further comprising a thrust redirecting stabilizing unit to control pitch. 10. A personal flying apparatus comprising: a mount adapted to couple the personal flying apparatus with a human operator;a gas turbine engine coupled with the mount, the gas turbine engine including a first rotating shaft and a second rotating shaft, the first rotating shaft coupling a first compressor with a first turbine, and the second rotating shaft coupling a second compressor with a second turbine, the gas turbine engine further including a common burner for adding thermal energy to a combined flow of air, the combined flow of air including output from both the first and second compressors; anda wing coupled with the gas turbine engine, the wing including a first span and an oppositely disposed second span, the wing being adapted to: receive a first thrust flow from the gas turbine engine, route the first thrust flow along the first span, and selectively redirect the first thrust flow in a first direction and in a second direction, wherein when the first thrust flow is redirected in the first direction vertical thrust is predominantly generated, and when the first thrust flow is redirected in the second direction forward thrust is predominantly generated; andreceive a second thrust flow from the gas turbine engine, route the second thrust flow along the second span, and selectively redirect the second thrust flow in a third direction and in a fourth direction, wherein when the second thrust flow is redirected in the third direction vertical thrust is predominantly generated, and when the second thrust flow is redirected in the fourth direction forward thrust is predominantly generated. 11. The apparatus of claim 10, wherein the first thrust flow is received from the first turbine and the second thrust flow is received from the second turbine. 12. The apparatus of claim 10, further comprising a flight configuration and a non-flight configuration, the flight configuration having each of the first and second spans in a deployed flight position, and the non-flight configuration having each of the first and second spans in a folded non-flight position. 13. The apparatus of claim 12, wherein the first and second spans are adapted to couple with each other when in their deployed flight positions so as to provide a continuous airfoil. 14. The apparatus of claim 10, wherein each of the first and second spans comprises an extendible wing section. 15. The apparatus of claim 10, further comprising a thrust redirecting stabilizing unit to control pitch.