초록 ▼

An aircraft includes at least one airfoil having a leading edge and a trailing edge. A number of pulse detonation engines are distributed along one of the leading and trailing edges of the airfoil and are positioned beneath the airfoil. Each pulse detonation engine is adapted for impulsively detonat

An aircraft includes at least one airfoil having a leading edge and a trailing edge. A number of pulse detonation engines are distributed along one of the leading and trailing edges of the airfoil and are positioned beneath the airfoil. Each pulse detonation engine is adapted for impulsively detonating a fuel/oxidizer mixture to generate a thrust force and to apply the thrust force to the aircraft. At least one of the pulse detonation engines is movably configured for altering a direction of the thrust force relative to the airfoil.

대표청구항 ▼

The invention claimed is: 1. An aircraft comprising: at least one airfoil having a leading edge and a trailing edge; and a plurality of pulse detonation engines (PDE) distributed along one of said leading and trailing edges of said airfoil and positioned beneath said airfoil, each pulse detonation

The invention claimed is: 1. An aircraft comprising: at least one airfoil having a leading edge and a trailing edge; and a plurality of pulse detonation engines (PDE) distributed along one of said leading and trailing edges of said airfoil and positioned beneath said airfoil, each pulse detonation engine being adapted for impulsively detonating a fuel/oxidizer mixture to generate a thrust force and to apply the thrust force to said aircraft, wherein at least one of said pulse detonation engines is movably configured for altering a direction of the thrust force relative to said airfoil, and wherein at least two of said pulse detonation engines are configured to impulsively detonate the fuel/oxidizer mixtures out of phase. 2. The aircraft of claim 1, further comprising a plurality of connectors, each of said connectors being configured to connect two of said pulse detonation engines to facilitate cross-fire initiation between said two pulse detonation engines. 3. The aircraft of claim 1, further comprising a control means for selectively activating and deactivating at least one of said pulse detonation engines. 4. The aircraft of claim 3, wherein said control means is configured for selectively activating and deactivating each of said pulse detonation engines. 5. The aircraft of claim 1, comprising at least two airfoils, each airfoil having a leading edge and a trailing edge, wherein said pulse detonation engines are distributed along one of said leading and trailing edges of each of said airfoils and are positioned below each of said airfoils. 6. The aircraft of claim 5, wherein said pulse detonation engines are distributed along said trailing edges of said airfoils, and wherein at least one of said pulse detonation engines comprises a PDE flap, said PDE flap being movably configured to alter the direction of the thrust force relative to said respective airfoil. 7. The aircraft of claim 6, further comprising a control means for selectively activating and deactivating at least one of said pulse detonation engines on each of said airfoils. 8. The aircraft of claim 5, wherein said pulse detonation engines are distributed along said leading edge of each of said airfoils. 9. The aircraft of claim 8, further comprising: a plurality of rear pulse detonation engines; and at least two flaps, each of said flaps being attached to a respective one of said airfoils along said trailing edge of the respective one of said airfoils, wherein each of said flaps is movably configured to alter a direction of the thrust forces relative to the respective one of said airfoils, and wherein said rear pulse detonation engines are distributed along said flaps. 10. The aircraft of claim 8, further comprising a control means for selectively activating and deactivating at least one of said pulse detonation engines on each of said airfoils, wherein each of said pulse detonation engines is movably configured for altering a direction of the thrust force relative to the respective one of said airfoils. 11. An aircraft comprising: at least one airfoil having a leading edge and a trailing edge; and a plurality of pulse detonation engines (PDE) distributed along one of said leading and trailing edges of said airfoil and positioned beneath said airfoil, each pulse detonation engine being adapted for impulsively detonating a fuel/oxidizer mixture to generate a thrust force and to apply the thrust force to said aircraft, wherein at least one of said pulse detonation engines is movably configured for altering a direction of the thrust force relative to said airfoil, wherein each of said pulse detonation engines comprises an inlet for receiving oxidizer, an outlet for exhausting an exhaust flow, and a PDE body extending between said inlet and said outlet, wherein at least one of said inlet and said outlet has an elliptical cross-sectional area with a semi-major axis oriented along said airfoil, and wherein the semi-major axis is greater than a semi-minor axis of said outlet. 12. The aircraft of claim 11, wherein said PDE body has a cross-sectional area that increases from a smaller cross-sectional area at said inlet to a larger cross-sectional area at said outlet. 13. The aircraft of claim 11, wherein each of said inlet and said outlet have an elliptical cross-sectional area with the semi-major axis oriented along said airfoil, and wherein the semi-major axis of said inlet is greater than a semi-minor axis of said inlet. 14. The aircraft of claim 1, wherein each of said pulse detonation engines comprises an inlet for receiving oxidizer, an outlet for exhausting an exhaust flow, and a PDE body extending between said inlet and said outlet, wherein said PDE body has a cross-sectional area that decreases from a larger cross-sectional area at said inlet to a smaller cross-sectional area at said outlet. 15. The aircraft of claim 1, further comprising a plurality of separators extending from said airfoil and beneath said airfoil, each of said separators being in intimate contact with at least one of said pulse detonation engines, and at least one of said separators being in intimate contact with two of said pulse detonation engines.