Ducted oblique-rotor VTOL vehicle

• US 9,688,396 B2
• Filed: 06/18/2015
• Issued: 06/27/2017
• Est. Priority Date: 06/18/2015
• Status: Active Grant

• Current Assignee: John Leonard Avery
• Original Assignee: Avery Aerospace Corporation
• Inventors: Avery, III, John Leonard
• Primary Examiner(s): MCFALL, NICHOLAS A
• Application Number:
  US14/742,878
• Publication Number:
  US 20160368601A1
• Time in Patent Office: 740 Days
• CPC Class Codes: B64C 1/0009 Aerodynamic aspects
• CPC Class Codes: B64C 11/30 Blade pitch-changing mechanisms
• CPC Class Codes: B64C 15/00 Attitude, flight direction, or altitude control by jet reaction
• CPC Class Codes: B64C 27/605 including swash plate, spider or cam mechanisms
• CPC Class Codes: B64C 27/625 including rotating masses or servo rotors
• CPC Class Codes: B64C 29/0025 the propellers being fixed relative to the fuselage
• CPC Class Codes: Y02T 50/10 Drag reduction

Abstract

The present invention is a winged VTOL aircraft of novel configuration that utilizes a single-axis rotor mounted at an oblique angle within a forward-facing, bifurcating duct, that is controlled by a plurality of servo driven vanes, producing a mechanically simple, redundantly controlled vehicle that can carry cargo, people, or otherwise, directly from point to point. The configuration uses sets of vanes to produce both moments and forces referenced around the vehicle'"'"'s center of gravity, thereby, allowing the vehicle to translate in a level position, or stay stationary relative to the ground while at a slight pitch or roll attitude. This feature is very important for autonomous vehicles to accurately pick up and drop off payloads on unlevel terrain or in windy conditions. Other rotor vehicles require pitch or roll attitude to translate or compensate for wind. Complementing this vehicle'"'"'s mechanically simple rotor system is a novel mechanism that collectively drives the pitch of the rotor blades by combining the input from three separate servos. Each servo can be controlled by redundant fight control systems.

Claims

1. A vertical takeoff and landing vehicle, comprising:

a. a rotor with a plurality of radial blades mounted to said vehicle with spin axis at oblique angle between said vehicle'"'"'s longitudinal axis and vertical axis as means of accelerating air to provide lift and propulsion;

b. a duct with an inlet facing forward to direct air into said rotor and direct air downward and aft;

c. a plurality of vertical exit vanes near the bottom of said vehicle to control said vehicle;

d. wherein each vertical exit vane of said plurality of vertical exit vanes has a rotational axis along its length about which it rotates independently to restrict and direct airflow;

e. a plurality of aft exit vanes near the aft end of said vehicle to control said vehicle during, and transition to and from, horizontal flight mode;

f. wherein said duct contains a left-hand vertical duct exit and a right-hand vertical duct exit, separated laterally and both extending longitudinally along the bottom of said vehicle;

g. wherein said duct contains an aft duct exit that faces to the rear of said vehicle.

2. A vertical takeoff and landing vehicle of claim 1, further including a wing as primary means of providing lift when said vehicle is in horizontal flight mode.