Aerovironment, Inc.

Other

John Peter Zwaan

Pavel Belik

Christopher Eugene Fisher

Marc L Schmalzel

Manolis Pavlos Dimotakis

Steven Bradley Chambers

Christopher J D'Aquila

Karl Robert Klingebiel

Bart Dean Hibbs

Alexander Andryukov

Matthew Todd Keennon

Austin Craig Gunder

Pavil Belik

Justin Bates McAllister

Eric James Aagaard

David R Thompson

Tyson R Jensen

David Wayne Ganzer

Karl R Klingbiel

Robert James Johnston

Philip Martin Finn

Glenn Arnold Blevins

Cris James Cornell

Phillip T Tokumaru

Gabriel E Torres

Jeremy D Tyler

Christopher J D'aquila

Manolis Dimotakis

Makoto Ueno

An aircraft apparatus is disclosed that has a fuselage boom having proximal and distal ends, a wing coupled to a proximal end of the fuselage boom and at least one transparent stabilizer coupled to a distal end of the fuselage boom.

Aircraft system for reduced observer visibility

Systems, devices, and methods for an extruded wing protection and control surface comprising: a channel proximate a leading edge of the control surface, a knuckle disposed about the channel, a leading void, a trailing void, and a separator dividing the leading void and the trailing void; and a plurality of notches disposed in the extruded control surface proximate the leading edge of the control surface.

Extruded wing protection system and device

In one possible embodiment, a UAV payload module retraction mechanism is provided including a payload pivotally attached to a housing. A biasing member is mounted to bias the payload out of the housing and a winch is attached to the payload. An elongated flexible drawing member is coupled between the housing and the winch, the elongated drawing flexible member being capable of being drawn by the winch to retract the payload within the housing.

UAV payload module camera assembly and retraction mechanism

A method of unmanned aerial vehicle (UAV) flight includes providing horizontal thrust in-line with the direction of forward flight of the UAV using at least one electric motor, providing primary vertical lift for the UAV during the forward flight using a fixed and non-rotating wing, repositioning the at least one electric motor to provide vertical thrust during transition of the UAV to vertical flight for descent, landing the UAV on a surface using a vertical approach after the motor repositioning, and deploying an anchor to secure the UAV to a surface.

Unmanned aerial vehicle and method of operation

A method of unmanned aerial vehicle (UAV) flight includes providing horizontal thrust in-line with the direction of forward flight of the UAV () using at least one electric motor (), providing primary vertical lift for the UAV () during the forward flight using a fixed and non-rotating wing (), repositioning the at least one electric motor (') to provide vertical thrust during transition of the UAV () to vertical flight (A) for descent (E), landing the UAV () on a surface () using a vertical approach after the motor repositioning, and deploying an anchor () to secure the UAV () to a surface ().

A quadrotor UAV including ruggedized, integral-battery, load-bearing body, two arms on the load-bearing body, each arm having two rotors, a control module mounted on the load-bearing body, a payload module mounted on the control module, and skids configured as landing gear. The two arms are replaceable with arms having wheels for ground vehicle use, with arms having floats and props for water-surface use, and with arms having pitch-controlled props for underwater use. The control module is configured to operate as an unmanned aerial vehicle, an unmanned ground vehicle, an unmanned (water) surface vehicle, and an unmanned underwater vehicle, depending on the type of arms that are attached.

Reconfigurable battery-operated vehicle system

Heavier-than-air, aircraft having flapping wings, e.g., ornithopters, where angular orientation control is effected by variable differential sweep angles of deflection of the flappable wings in the course of sweep angles of travel and/or the control of variable wing membrane tension.

Air vehicle flight mechanism and control method

Extruded control surface having a knuckle and notches

Liquid dispensing assemblies including adhesive anchoring assemblies configured to adhere to a support surface external to a device such as a vehicle. An air vehicle includes (a) a fluid adhesive container assembly detachably attached to the air vehicle, wherein the fluid adhesive container assembly comprises: (i) an adhesive container comprising fluid adhesive; and (ii) one or more fibers, wherein the one or more fibers are configured, or a brush of fibers, or a fabric of fibers, is configured to conduct the fluid adhesive and to structurally support an adhesive bond between the one or more fibers and a surface; and (b) means for dispensing the fluid adhesive from the fluid adhesive container, to the one or more fibers.

Aircraft grounding system

Systems, devices, and methods for impacting, by a small unmanned aerial vehicle (SUAV), a net having at least three sides; and converting the kinetic energy of the SUAV into at least one of: elastic potential energy of one or more tensioned elastic cords connected to at least one corner of the net, gravitational potential energy of a frame member connected to at least one corner of the net, rotational kinetic energy of the frame member connected to at least one corner of the net, and elastic potential energy of the frame member connected to at least one corner of the net.

Small unmanned aerial vehicle (SUAV) shipboard recovery system

Growing community of inventors

Simi Valley, CA, United States of America

John Peter Zwaan