Zero Transition Vertical Take-Off and Landing Aircraft

• US 20140158815A1
• Filed: 05/28/2013
• Published: 06/12/2014
• Est. Priority Date: 12/10/2012
• Status: Abandoned Application

• Current Assignee: Joseph Raymond Renteria
• Original Assignee: Joseph Raymond Renteria
• Inventors: RENTERIA, Joseph Raymond
• Application Number:
  US13/903,471
• Publication Number:
  US 20140158815A1
• Time in Patent Office: Days
• US Class Current: 244/12.1
• CPC Class Codes: B64C 29/0025 the propellers being fixed relative to the fuselage
• CPC Class Codes: B64C 39/04 having multiple fuselages or tail booms

Abstract

A zero transition vertical take-off and landing (VTOL) aircraft, which is stable in all levels of flight, especially the transition phase from vertical to horizontal flight. The zero transition VTOL aircraft is capable of achieving both vertical and horizontal flight without changing the positioning of thrusters, such as through the use of tiltable or rotatable nacelles or wings. Rather a front thruster assembly and a rear thruster assembly are positioned at specific angles in relation to each other along at least one fuselage in order to generate the desired ratio of vertical to horizontal thrust. At least one wing is also positioned at a specific wing angle in order to achieve a desired angle of attack when in horizontal flight. The attitude of the zero transition VTOL aircraft can be controlled through the use of differential thrust alone, or in conjunction with control surfaces.

Claims

1. A zero transition vertical take-off and landing (VTOL) aircraft comprises:

an airframe;

a front thruster assembly;

a rear thruster assembly;

the airframe comprises an at least one wing;

each of the at least one wing comprises a leading wing edge and a trailing wing edge;

a center of gravity;

a longitudinal axis traversing through the center of gravity;

a lateral axis traversing through the center of gravity and being perpendicular to the longitudinal axis;

a first plane being coincident with the longitudinal axis and the lateral axis;

a wing intersection axis, a front intersection axis, and a rear intersection axis being parallel to the lateral axis;

a wing chord plane being coincident with the leading wing edge and the trailing wing edge;

the wing chord plane being coincident with the first plane along the wing intersection axis;

a rear thruster plane being coincident with the wing chord plane along the rear intersection axis;

the rear thruster assembly being positioned normal to the rear thruster plane, wherein the rear thruster assembly produces thrust normal to the rear thruster plane;

a front thruster plane being coincident with the rear thruster plane along the front intersection axis;

the front thruster assembly being positioned normal to the front thruster plane, wherein the front thruster assembly produces thrust normal to the front thruster plane;

the front thruster assembly being positioned adjacent to the center of gravity along the longitudinal axis; and

the rear thruster assembly being positioned adjacent to the center of gravity along the longitudinal axis and opposite to the front thruster assembly.

2. The zero transition VTOL aircraft as claimed in claim 1 comprises:

the wing chord plane and the first plane being positioned at a wing angle;

the wing angle traversing from the first plane to the wing chord plane;

the rear thruster plane and the wing chord plane being positioned at a rear thruster angle;

the rear thruster angle traversing from the wing chord plane to the rear thruster plane;

the front thruster plane and the rear thruster plane being positioned at a front thruster angle; and

the front thruster angle traversing from the rear thruster plane to the front thruster plane.

3. The zero transition VTOL aircraft as claimed in claim 2 comprises:

the wing angle being a positive angle between 0 degrees and 45 degrees;

the rear thruster angle being a positive angle between 80 degrees and 130 degrees; and

the front thruster angle being a negative angle between 90 degrees and 150 degrees.

4. The zero transition VTOL aircraft as claimed in claim 1 comprises:

the front thruster assembly being positioned across the front thruster plane and laterally positioned about the center of gravity, wherein the front thruster assembly provides lateral stability and yaw control;

the front thruster assembly comprises an at least one front nacelle and an at least one front thruster;

the at least one front thruster being positioned within the at least one front nacelle; and

the at least one front nacelle being adjacently connected to the airframe.

5. The zero transition VTOL aircraft as claimed in claim 1 comprises:

the rear thruster assembly being positioned across the rear thruster plane and laterally positioned about the center of gravity, wherein the rear thruster assembly provides lateral stability and yaw control;

the rear thruster assembly comprises an at least one rear nacelle and an at least one rear thruster;

the at least one rear thruster being positioned within the at least one rear nacelle; and

the at least one rear nacelle being adjacently connected to the airframe.

10. The zero transition VTOL aircraft as claimed in claim 1 comprises:

the airframe further comprises a landing gear assembly;

the landing gear assembly being adjacently connected along the airframe; and

the landing gear assembly being positioned below the airframe.

20. The zero transition VTOL aircraft as claimed in claim 5 comprises:

the at least one rear nacelle being pivotally connected to the airframe.

21. The zero transition VTOL aircraft as claimed in claim 1 comprises:

the airframe further comprises an at least one empennage.

22. The zero transition VTOL aircraft as claimed in claim 21 comprises:

the at least one empennage being adjacently connected to the at least one wing.

23. The zero transition VTOL aircraft as claimed in claim 21 comprises:

the at least one empennage comprises an at least one horizontal stabilizer.

24. The zero transition VTOL aircraft as claimed in claim 21 comprises:

the at least one empennage comprises an at least one vertical stabilizer.

25. The zero transition VTOL aircraft as claimed in claim 21 comprises:

the at least one empennage comprises an at least one horizontal stabilizer and an at least one vertical stabilizer; and

the at least one vertical stabilizer being positioned adjacent to the at least one horizontal stabilizer and the rear thruster assembly.

26. The zero transition VTOL aircraft as claimed in claim 1 comprises:

the airframe further comprises an at least one fuselage; and

each of the at least one fuselage comprises a nose cone.

27. The zero transition VTOL aircraft as claimed in claim 26 comprises:

the at least one front nacelle being positioned adjacent to the nose cone.

28. The zero transition VTOL aircraft as claimed in claim 26 comprises:

the at least one wing being adjacently connected to the at least one fuselage; and

the leading wing edge and the trailing wing edge being positioned opposite of each other across the at least one wing.

29. The zero transition VTOL aircraft as claimed in claim 28 comprises:

the airframe further comprises an at least one empennage;

the at least one empennage being adjacently connected to the at least one fuselage;

the at least one empennage being positioned opposite of the nose cone along the at least one fuselage; and

the at least one wing being positioned in between the nose cone and the at least one empennage.

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