VTOL aircraft control method

• US 5,419,514 A
• Filed: 11/15/1993
• Issued: 05/30/1995
• Est. Priority Date: 11/15/1993
• Status: Expired due to Fees

• Current Assignee: Terry A. Ducan
• Original Assignee: Terry A. Ducan
• Inventors: Ducan, Terry A.
• Primary Examiner(s): Kashnikow, Andres
• Assistant Examiner(s): MARQUIS, LISSI MOJICA
• Application Number:
  US08/152,027
• Time in Patent Office: 561 Days
• Field of Search: 244/12.5, 244/12.4, 244/12.5, 244/23 D, 244/23 D, 244/56
• US Class Current: 244/12.4
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage

Abstract

In a vertical take-off and landing vehicle, the invention is a method for improving stability by virtue of establishing conversion of thrust vectors over the center of gravity of the vehicle while in the hover position. Through the use of selected angles of inclination of the thrust-generating devices, a positive static stability of the aircraft is maintained. In addition, the spars supporting the thrust-generating devices are mounted in a fixed angular relationship to the centerline of the aircraft'"'"'s fuselage, to achieve the desired inclination of the thrust vectors of the lift-generating devices toward the centerline of the vehicle, by simple rotation of the spars on which the lift-generating devices are mounted.

Claims

1. In an aircraft adapted for vertical takeoff and landing, including a plurality of thrust generating elements having an axis of thrust selectively pivotable between a first horizontal thrust generating position and a second vertical thrust generating position, the improvement comprising enhancing in-flight stability of said aircraft in vertical flight by further selectively pivoting the axis of thrust of at least one of said thrust generating elements toward the vehicle center of gravity when said thrust generating element is configured in said vertical thrust generating position such that said axis of thrust intersects a point directly above said vehicle.

2. In an aircraft adapted for vertical takeoff and landing, including a plurality of thrust generating elements having an axis of thrust selectively pivotable between a first horizontal thrust generating position and a second vertical thrust generating position, the improvement comprising:

further selectively pivoting the axis of thrust of at least one of said thrust generating elements toward the vehicle center of gravitvy when said thrust generating element is configured in said vertical thrust generating position;

selective pivoting of the axis of thrust of at least one of said thrust generating elements toward the vehicle center of gravity includes at least one pivotable spar fixed in a rearward swept first angular relation to the fore and aft centerline of said aircraft and adapted for rotational movement;

at least one of said thrust generating devices mounted, in second fixed angular relation to the axis of thrust of said thrust generating device, to the end of said spar opposite the fore and aft centerline of said aircraft;

said first swept angular relation of said spar to said centerline being a fixed angle less than 90;

said second fixed angular relation of said thrust generating device being an angle substantially equal to said first angle; and

whereby, rotation of said spar results in orientation of the thrust axis of said thrust generating device between intersection of a point located above the vehicle center of gravity and an alignment substantially parallel with said centerline of said aircraft.