Honeywell International Inc.

Honeywell G.m.b.h.

Emray R Goossen

Steven D Martinez

Glen A Mantych

Yogendra Y Sheoran

Yunqian Ma

Larry A Nelson

Ken E Young

Dan T Horak

James W Woods

Jonathan Fleming

Carl Edward Lippitt

Derick Lucas Gerlock

David Baughman

William T Campbell

Katherine Goossen

David K Shema

Charles Boyd Anderson

Randall E Horn

Ronald Ray Banning

A system for planning and executing a response to an incident includes a planning and execution data source and a processing system. The processing system is in operable communication with the planning and execution database. The processing system is configured to generate pre-planned responses to be executed by associated response assets, store data representative of the pre-planned responses in the planning and execution database, selectively retrieve a pre-planned response from the planning and execution database, communicate with the response assets associated with the retrieved pre-planned response, provide real-time tracking of the retrieved pre-planned response being executed by the associated response assets, and selectively generate recommendations for modifying the retrieved pre-planned response.

Response planning and execution aiding system and method

A method for autonomous landing of an unmanned aerial vehicle (UAV) comprising: obtaining sensor data corresponding to one or more objects outside of the aircraft using at least one onboard sensor; using the sensor data to create a three dimensional evidence grid, wherein a three dimensional evidence grid is a three dimensional world model based on the sensor data; combining a priori data with the three dimensional evidence grid; locating a landing zone based on the combined three dimensional evidence grid and a priori data; validating an open spots in the landing zone, wherein validating includes performing surface condition assessment of a surface of the open spots; generating landing zone motion characterization, wherein landing zone motion characterization includes characterizing real time landing zone pitching, heaving, rolling or forward motion; processing the three dimensional evidence grid data to generate flight controls to land the aircraft in one of the open spots; and controlling the aircraft according to the flight controls to land the aircraft.

Systems and methods for autonomous landing using a three dimensional evidence grid

The present invention provides a catch and snare system for an unmanned aerial vehicle comprising: (a) a detection system, (b) a deployment system in communication with the detection system, (c) a capture system placed at an interference position by the deployment system, wherein the capture system comprises a net, a plurality of foam deploying canisters attached to the net for deploying foam, and at least one canister for deploying a decelerating parachute attached to the net, wherein the foam prevents the release of chemical or biological agents from the captured unmanned aerial vehicle, and (d) a descent system to bring the capture system and a captured unmanned aerial vehicle back to earth.

Catch and snare system for an unmanned aerial vehicle

An unmanned aerial vehicle selectively formed of high strength composite structural part portions and lightweight aerodynamic foam portions to provide a low-cost and lightweight UAV that comports with export, civil airspace, and safety regulations. To further to reduce an overall weight of the UAV, mechanical elements are designed to provide multiple functionalities. Structural elements may be manufactured in same or similar non-specialized processes, and non-structural elements manufactured in same or similar non-specialized processes, reducing overall manufacturing costs. Materials and bonding elements are selected to provide frangibility and yet maintain normal flight structural integrity.

Vertical take off and landing unmanned aerial vehicle airframe structure

Systems, devices, and methods are described that facilitate the transmission of image data collected by a sensor within a gimbal assembly. A gimbal assembly includes one or more sensors positioned within the gimbal assembly. The one or more sensors collect data. The gimbal assembly is controllable to aim the one or more sensors. The gimbal assembly further includes a communications module within the gimbal assembly. The communications module transmits at least one directional optical signal to communicate data collected by the sensor. At least one transducer is positioned to receive the at least one directional electromagnetic signal.

Non-contact data transfer from moving systems

A manipulator arm system on a ducted air-fan UAV is disclosed herein. The target site may be accurately located by the UAV, and the manipulator system may accurately locate the payload at the target site. The manipulator arm may select tools from a toolbox located on-board the UAV to assist in payload placement or the execution of remote operations. The system may handle the delivery of mission payloads, environmental sampling, and sensor placement and repair.

Airborne manipulator system

A transforming unmanned aerial-to-ground vehicle assembly comprising: an aerodynamic flying assembly comprising an unmanned aerial vehicle integrated with an unmanned ground vehicle, a power unit shared by the unmanned aerial vehicle and the unmanned ground vehicle, vehicle controls shared by the unmanned aerial vehicle and the unmanned ground vehicle, a disengagement mechanism to separate the unmanned ground vehicle from the unmanned aerial vehicle, one or more manipulator arms located on either the unmanned aerial vehicle or the unmanned ground vehicle, and landing gear.

Transforming unmanned aerial-to-ground vehicle

The present invention provides apparatus and methods for accurate guidance of small munitions to a target. The guidance for the small munition is mainly provided by a device external to the small munition, such as an unmanned aerial vehicle (UAV). The UAV may provide external guidance commands by use of a command transmitter to the small munition. The small munition is equipped to receive the guidance commands and consequently use a maneuvering mechanism to react to the guidance commands. The UAV may determine a successful release point of the small munition and track a flight path from a release point toward the target of the small munition using a passive sensor mounted in a gimbaled mount, which is controlled by use of a closed-loop control system. The UAV may be controlled by a ground control device, such as an operator control unit (OCU), to release small munitions.

Guided delivery of small munitions from an unmanned aerial vehicle

A launch and capture system for capturing a vertical take-off and landing (VTOL) vehicle having a thruster and a duct configured to direct airflow generated by the thruster includes a capture plate and an extension. The capture plate is configured to alter the airflow and generate a force attracting the duct to the capture plate. The extension is coupled to the capture plate, and is configured to at least facilitate holding the VTOL vehicle against the capture plate.

Launch and capture systems for vertical take-off and landing (VTOL) vehicles

Methods and systems are provided for attaching and detaching a payload device to and from, respectively, a gimbal system without requiring use of a mechanical tool. The gimbal system includes a gimbal assembly that includes a payload socket arranged to attach a payload device to the gimbal assembly. The payload socket is preferably arranged to allow any of a plurality of payload devices to attach to and detach from the payload socket without requiring use of a mechanical tool.

Methods and systems for attaching and detaching a payload device to and from, respectively, a gimbal system without requiring use of a mechanical tool

Systems and methods for inertially controlling a hovering unmanned aerial vehicle (HUAV) are provided. One inertial controller includes a frame and a sensor for detecting a change in an orientation and/or motion of the frame with respect to a predetermined neutral position. The inertial controller also includes a processor for generating commands to the HUAV to modify its current orientation and/or motion in accordance with the change. A system includes the above inertial controller and a sensor for determining a second change for an orientation and/or motion for the HUAV based on the change, and a processor for generating a signal commanding an HUAV control system to orient and/or move the HUAV in accordance with the second change. One method includes detecting a change in an orientation and/or motion of an inertial controller frame and commanding the HUAV to modify its current orientation and/or motion in accordance with the change.

Systems and methods for inertially controlling a hovering unmanned aerial vehicles

An air data system and method for a ducted fan air-vehicle is described. The air data system includes a plurality of air pressure sensors placed around a lip of an air duct of the ducted fan air-vehicle. The air data system calculates the speed and direction of airflow surrounding the ducted fan air-vehicle based on pressure data measured across the lip of the air duct. Additionally, the air data system may estimate forces generated by airflow surrounding the air-vehicle.

Ducted fan air data system

Self-leveling legs are used to accommodate landing a ducted fan hovercraft on a sloped surface such as a roof-top. These legs move to accommodate a variation of slope within their range of motion irrespective to the azimuth of the vehicle body. The configuration and operation of the landing legs allow the hovercraft to land in a stable fashion with the hovercraft vehicle body maintained in a vertical orientation. The basic kinematics of the present invention is the displacement of one landing leg upwards is connected by a horizontal member to the opposite leg and displaces it downwards, and visa-versa. Planar surface contact is accomplished by the unique curvature of the legs and the splay of the legs from the vehicle body.

Landing gear for a hovercraft

A dual ducted fan arrangement in which the duct components, engine, and avionics/payload pods are capable of being quickly disassembled to fit within common backpacking systems. Each duct is identical in fan, stator, and control vane design. Assembly connections between ducted fans and electronic modules are also identical. An engine or APU drives the dual ducted fans through a splined shaft to a differential or through electric motors. Energy is transferred to the ducted fans by a single gear mounted to the stator hub. Relative speeds of the individual ducted fans are controlled through separate frictional or generator load control braking mechanisms on each of the splined shafts between the differential and ducted fans. In the electric motor case relative speed is through electronic speed control. The fans are counter rotating for torque balancing. The electronic module locations are vertically variable for longitudinal center of gravity for variations in payloads.

Double ducted hovering air-vehicle

A Micro Air-Vehicle (MAV) starting system that provides the combined functions of: packing protection of sensitive vehicle components, a mechanical starting assembly, and a launch pad. The preferred embodiment comprises a container and a container lid with the MAV clamped to the lid. Also disposed on the container lid is a starting assembly. The lid which doubles as a launching pad with the attached MAV is removed from the container, placed on the ground, the MAV is started with the starting mechanism and launched. The arrangement minimizes the physical risk to the operator, minimizes weight of the total MAV system, consumes minimum space in the operators transport system, and eliminates dependence on supply lines for battery replacement or charging.

Growing community of inventors

Albuquerque, NM, United States of America

Emray R Goossen