The Boeing Company

Mcdonnell Douglas Helicopter Company

Gregory E Dockter

Brian Koorosh Hamilton

Dino A Cerchie

William Mark Hardesty

Ahmed A Hassan

Stephen Lewis Guymon

Donald G Caldwell

Jason Graham

An apparatus for converting a manned aircraft of a type including at least one pilot control capable of manipulation to affect operation of the aircraft for unmanned flight operations includes first and second actuators, each configured to selectively provide movement or resistance to movement in a first manner including linear or rotational motion, first and second clutches, each configured to selectively couple movement of the associated actuator to or from the pilot control during flight, and a vehicle controller capable of being selectively enabled during flight to operate the pilot control actuators and clutches and thereby provide unmanned operation of the aircraft, or of being disabled, thereby providing for manned operation of the aircraft. The first actuator has a first scope describing a first amount of allowable movement, while the second actuator has a second scope larger than the first scope.

Multi-mode unmanned and manned vehicle systems and methods

An apparatus for converting a manned aircraft of a type including at least one pilot control capable of manipulation to affect operation of the aircraft for unmanned flight operations includes first and second actuators, each configured to selectively provide movement or resistance to movement in a first manner including linear or rotational motion, first and second clutches, each configured to selectively couple movement of the associated actuator to the pilot control, and a vehicle controller capable of being selectively enabled to operate the pilot control actuators and clutches and thereby provide unmanned operation of the aircraft, or of being disabled, thereby providing for manned operation of the aircraft. The first actuator has a first scope describing a first amount of allowable movement, while the second actuator has a second scope larger than the first scope.

An aircraft control system for operations close to the ground includes a camera having a rangefinder for measuring the azimuth, elevation and slant range from a fixed point on the aircraft relative to a selected target point on a surface below the aircraft, a navigation system for measuring the latitude and longitude of the aircraft on the surface, a computer for computing the position of the fixed point on the aircraft relative to the target point from the respective measurements of the camera and the navigation system, and a controller for controlling the movement of the aircraft such that the fixed point is positioned at a selected position above the selected target point on the surface. The controller may also include an automatic tracking mechanism for maintaining the position of the fixed point on the aircraft at the selected position above a moving object.

Aircraft precision approach control

An apparatus for converting a manned aircraft for unmanned flight, the aircraft including at least one pilot control capable of manipulation to affect operation of the aircraft, the apparatus comprising a first actuator and a second actuator each configured to selectively provide movement or resistance to movement in a first manner including linear or rotational motion, a first clutch and a second clutch each configured to selectively couple movement of the associated actuator to the pilot control, and a vehicle controller capable of being selectively enabled to operate the pilot control actuators and clutches providing unmanned operation of the aircraft or disabled providing manned operation of the aircraft. The first actuator has a first scope describing a first amount of allowable movement, while the second actuator has a second scope larger than the first scope.

An airfoil member () includes a geometric morphing device (). The geometric morphing device () has an inflatable member (). The inflatable member () has an exterior wall () and multiple inflated states. The exterior wall () includes a layer with one or more fibers embedded therein. The exterior wall () controls size, shape, and expansion ability of the geometric morphing device ().

Fiber matrix for a geometric morphing wing

An airfoil member () is provided including a geometric morphing device (). The geometric morphing device () has an inflatable member (). The inflatable member () has an exterior wall () and multiple inflated states. A fiber mesh () is coupled to at least a portion of the exterior wall () and changes in shape according to fiber angle. Shape and size of the geometric morphing device () are adjustable by changing inflated state of the inflatable member (). An airfoil member altering system () and a method of performing the same are also provided as well as a method of forming the geometric morphing device ().

Geometric morphing wing

An airfoil member ( ) is provided including a geometric morphing device ( ). The geometric morphing device ( ) has an inflatable member ( ). The inflatable member ( ) has an exterior wall ( ) and multiple inflated states. Multiple layers are coupled to at least a portion of the exterior wall ( ) and control size, shape, and expansion ability of the geometric morphing device ( ). The geometric morphing device ( ) is adjustable in size and shape by changing inflated state of the inflatable member ( ). An airfoil member altering system ( ) and a method of performing the same are also provided as well as a method of forming the geometric morphing device ( ).

Geometric morphing wing with layers

A geometric morphing wing is provided, including a rigid internal core surrounded by an expandable spar and covered by a wing surface overlay . The expandable spar includes an elastomeric bladder movable between a non-inflated state and an inflated state such that the airfoil shape of the geometric morphing wing is adjusted.

Geometric morphing wing with expandable spars

The bi-directional air flow deflector of the present invention efficiently deflects air to the left opening and the right opening, and minimizes any vertical components of force which may be generated. The air flow vector exiting from each of the openings comprises a dominant horizontal force vector rather than a large component of force in the vertical direction. Vertical components of force may be added, if desired. The bi-directional air flow deflector provides reduced transmission torque requirements, and generally comprises a relatively small number of moving parts. A single moving part may be used to deflect air to either the left opening or the right opening, and this single moving part is not exposed to the outside environment and, accordingly, will generally provide reliable functionality. The bi-directional air flow deflector of the present invention is simple in design, comprises a small number of relatively easy to manufacture parts, and can be used to retrofit existing direct jet thrusters. The components of the bi-directional air flow deflector generally comprise relatively straight sides and surfaces, which require less sophisticated tooling and reduce costs. The reduced number of parts will require a smaller stock of parts for inventory and field support. The bi-directional air flow deflector can be assembled with generally less man power than prior art devices, and generally comprises an increased reliability. Since less energy is generally required to operate the bi-directional air flow deflector of the present invention, increased fuel efficiency can also be realized.

Growing community of inventors

Mesa, AZ, United States of America

Gregory E Dockter