Omnidirectional aircraft

• US 20070023581A1
• Filed: 07/16/2005
• Published: 02/01/2007
• Est. Priority Date: 07/16/2004
• Status: Abandoned Application

• Current Assignee: William La
• Original Assignee: William La
• Inventors: La, William
• Application Number:
  US11/182,877
• Publication Number:
  US 20070023581A1
• Time in Patent Office: Days
• US Class Current: 244/165
• CPC Class Codes: B64C 27/20 Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 10/16 with five or more distinct rotor axes, e.g. octocopters
• CPC Class Codes: B64U 2101/30 for imaging, photography or videography
• CPC Class Codes: B64U 2201/20 Remote controls
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 30/26 Ducted or shrouded rotors
• CPC Class Codes: B64U 50/13 using external fans or propellers
• CPC Class Codes: B64U 50/18 Thrust vectoring
• CPC Class Codes: B64U 70/80 Vertical take-off or landing, e.g. using rockets rotorcrafts B64U10/10; VTOL aircraft B64U10/20

Abstract

An omni-directional aircraft with flight capabilities surpassing those of a regular VTOL or helicopter, being able to take full advantage of the simultaneous six degrees of freedom of motion possible in the atmosphere, undergoing any desired combination of translational and rotational movement, and keeping station in the air in any arbitrary attitude. In the preferred embodiment, the flying object comprises a cubic body on the six faces of which are mounted six propulsion units, such that the propellers on each pair of opposite faces are coplanar with each other and with the main axis passing through the centers of these opposite faces, and their thrusts act along the direction of another main axis, each of the three pairs of propellers acting along a different one of the cube'"'"'s three main axes. The thrust from each motion-inducing assembly being continuously variable and reversible, the resultant translational and rotational thrust vectors can be positioned arbitrarily within their respective solid envelopes. A control element with equal freedom of motion allows intuitive piloting of the vehicle. In an alternate embodiment, the propulsion units are disposed along the sides of a tetrahedron.

Claims

1. An omnidirectional aircraft comprising:

a body, six propulsion means, and a control means;

the body defining a reference system comprising an origin where intersect three mutually orthogonal reference axes, a first axis, a second axis, and a third axis, each axis having an origin, a negative direction and a positive direction, the origin and negative direction of said first, second and third axes respectively defining corresponding first, second and third negative half-axes, and the origin and positive direction of said first, second and third axes respectively defining corresponding first, second and third positive half-axes;

each of said six propulsion means being attached to said body through a mounting means, and defining a plane and a center in said plane through which passes a thrust axis having a negative direction and a positive direction, said thrust axis being normal to said plane; and

each propulsion means being able to develop a motion-inducing force in the direction of its corresponding thrust axis, said force being continuously variable from a predetermined maximum negative value to a predetermined maximum positive value;

a first propulsion means having a center substantially located on said first negative half-axis, a second propulsion means having a center substantially located on said first positive half-axis, a third propulsion means having a center substantially located on said second negative half-axis, a fourth propulsion means having a center substantially located on said second positive half-axis, a fifth propulsion means having a center substantially located on said third negative half-axis, and a sixth propulsion means having a center substantially located on said third positive half-axis;

the six propulsion means being configured such that, from their collective action, the resultant translational thrust vector and the resultant rotational thrust vector each spans all directions of said reference system;

the control means being adapted to accept control input signals in the form of vehicle translation and rotation vectors, and to convert said signals to thrust commands for said propulsion means.

2. The device of claim 1 arranged in a cubic configuration, wherein said first and second propulsion means are substantially coplanar, their respective centers are substantially equidistant to said origin, and their respective thrust axes are substantially parallel to said second axis;

said third and fourth propulsion means are substantially coplanar, their respective centers are substantially equidistant to said origin, and their respective thrust axes are substantially parallel to said third axis; and

said fifth and sixth propulsion means are substantially coplanar, their respective centers are substantially equidistant to said origin, and their respective thrust axes are substantially parallel to said first axis.

3. The device of claim 1 arranged in a tetrahedral configuration, wherein said six propulsion means are substantially centrally disposed along the sides of an equilateral tetrahedron whose geometric center coincides with said origin, such that each propulsion means is substantially coplanar with its corresponding tetrahedral side and with said origin.

4. The device of claim 1 wherein said six mounting means are pivotable, such that said device can be reconfigured at will between a cubic configuration and a tetrahedral configuration.

5. The device of claim 1 wherein each said propulsion means comprises a shroud, a reversible electric motor centrally mounted within said shroud, and a propeller mounted on said motor.

6. The device of claim 1 wherein each said propulsion means comprises a shroud, a collectively variable pitch rotor rotatably mounted within said shroud, means for varying said pitch, and transmission means for driving said rotor at a substantially constant speed from a mechanical source located inside said body.

7. The device of claim 1 wherein said control means comprises a control input means, a navigation sensor means, a signal processing means, and a control output means.

8. The device of claim 7 wherein said control input means comprises a compound three-axis linear slide table, which accepts a three-axis angular gimbal system, which accepts a manual control element;

sensor means to convert displacements and deflections of said manual control element into electrical input signals;

trimming means to adjust the neutral levels of said input signals;

mechanical zeroing means to return said manual control element to a neutral position in the absence of operator input;

locking means for selectively engaging said control input means to maintain a steady state level of one or more input parameters; and

mechanical counterbalancing means to prevent spurrious control input during vehicle translational and rotational acceleration and deceleration.