A system for a tail-sitter aircraft includes a fuselage having one or more propellers, a wing structure coupled to the fuselage, and a drag rudder assembly coupled to the wing structure, the drag rudder assembly including a first planar member that is coupled to a second planar member. The drag rudd
A system for a tail-sitter aircraft includes a fuselage having one or more propellers, a wing structure coupled to the fuselage, and a drag rudder assembly coupled to the wing structure, the drag rudder assembly including a first planar member that is coupled to a second planar member. The drag rudder assembly is configured to produce a stabilizing force on the wing structure during higher speeds of the aircraft in tandem rotor flight.
대표청구항▼
1. A system for a tail-sitter aircraft, comprising: a fuselage having one or more propellers;a wing structure coupled to the fuselage; anda drag rudder assembly coupled to the wing structure, the drag rudder assembly including a first planar member that is coupled to a second planar member, the firs
1. A system for a tail-sitter aircraft, comprising: a fuselage having one or more propellers;a wing structure coupled to the fuselage; anda drag rudder assembly coupled to the wing structure, the drag rudder assembly including a first planar member that is coupled to a second planar member, the first planar member and the second planar member are coupled to the wing structure;wherein the aircraft is transformable between a tandem rotor flight mode where a longitudinal axis of the fuselage is oriented in a vertical direction relative to a ground plane and an airplane mode where the longitudinal axis of the fuselage is parallel to the ground plane, and at least one of the first planar member and the second planar member is adjustable between a first position and a second position based on whether the aircraft is in the tandem rotor flight mode or the aircraft mode, wherein in the first position, the first planar member and the second planar member are arranged at an acute angle between about 15 degrees and about 60 degrees with a plane that is parallel to a longitudinal axis of the wing structure in a direction away from the fuselage, and in the second position, the first planar member is parallel to the second planar member and the wing structure. 2. The system of claim 1, wherein the drag rudder assembly is configured to produce a stabilizing force on the wing structure during operation of the aircraft in the tandem rotor flight mode. 3. The system of claim 1, wherein at least one of the first and second planar members is fixed at the acute angle with the wing structure. 4. The system of claim 1, wherein each of the first and second planar members is adjustable to vary the acute angle. 5. The system of claim 1, wherein the acute angle of the first planar member is not equal to the acute angle of the second planar member. 6. The system claim 1, wherein the acute angle of the first planar member is the same as the acute angle of the second planar member. 7. The system of claim 1, wherein the drag rudder assembly is coupled to an aft-end of the wing structure. 8. A method for controlling a tail-sitter aircraft, comprising: providing a fuselage having one or more propellers, the fuselage transforming between a tandem rotor flight mode where a longitudinal axis of the fuselage is oriented in a vertical direction relative to a ground plane and an airplane mode where the longitudinal axis of the fuselage is parallel to the ground plane;attaching a wing structure to the fuselage;coupling a drag rudder assembly to the wing structure, the drag rudder assembly including a first planar member that is coupled to a second planar member,adjusting a position of at least one of the first planar member and the second planar member between a first position and a second position, based on whether the aircraft is in the tandem rotor flight mode or the aircraft mode, wherein in the first position, the first planar member and the second planar member are arranged at an acute angle between about 15 degrees and about 60 degrees with a plane that is parallel to a longitudinal axis of the wing structure in a direction away from the fuselage, and in the second position, the first planar member is parallel to the second planar member and the wing structure. 9. The method of claim 8, wherein the drag rudder assembly produces a stabilizing force on the wing structure during operation of the aircraft in tandem rotor flight mode. 10. The method of claim 8, wherein the acute angle of at least one of the first planar member and the second planar member is fixed. 11. The method of claim 8, wherein the acute angle of the first planar member and the second planar member is variable. 12. The method of claim 8, further comprising providing the acute angle for the first planar member and the acute angle for the second planar member, wherein the acute angle for the first planar member is not equal to the acute angle for the second planar member. 13. The method claim 8, further comprising providing the acute angle for the first planar member that is the same as the acute angle of the second planar member. 14. The method of claim 8, further comprising coupling the drag rudder assembly to an aft-end of the wing structure.
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Waitzman Simon V. (57 Montague St. Brooklyn Heights NY 11201), Airplane airframe.
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