Flir Unmanned Aerial Systems As

Prox Dynamics As

Tandberg Telecom As

Other

Proxflyer As

Cisco Technology, Inc.

Cisco Systems International S.a.r.l.

Petter Muren

Trygve Frederik Marton

Pal Hagh Sandberg

Dag Henning Paulsen

Ivar Johnsrud

Tom-Ivar Johansen

Jo Eyvin Bjaarstad

Christian Moengen

Johan Ludvig Nielsen

Hallgrim Sagen

Snorre Kjesbu

Torgeir Grothe Lien

Finn Helge Lunde

Päl Hagh Sandberg

Jorunn Helene Melby

Jorgen Syvertsen

Tor Marius Sollie

Erik Falk-Pettersen

Geir Morten Mellem

Alexander Philip Hall

Ola Roer Thorsen

Geir Morten Egeberg Mellem

Ola RØER Thorsen

Pål Hagh Sandberg

Radio link coverage mapping systems and related techniques are provided to improve the operation of unmanned mobile sensor or survey platforms. A radio or communication link coverage mapping system includes a logic device configured to communicate with a communication module and a position sensor coupled to a mobile platform, where the communication module is configured to establish a wireless communication link with a base station associated with the mobile platform and the position sensor is configured to provide a position of the mobile platform as it maneuvers within a survey area. The logic device determines communication link quality data associated with the wireless communication link as the mobile platform maneuvers within the survey area, receives corresponding position data, and generates corresponding communication coverage information, which may be used to generate a radio link coverage map.

Radio link coverage map generation using link quality and position data of mobile platform

Embodiments disclosed herein present a spring system for use in a torque dependent rotor assembly designed to operate in resonance, where changes in applied torque controls the blade pitch angle and ultimately the movements of a rotary wing aircraft. More specifically, the present invention relates to a spring system used in such a rotor assembly where the stiffness of an associated spring member is allowed to vary in response to the torque applied from a motor to the assembly.

Spring system varying stiffness with applied force for use in a torque dependent rotor of a rotary wing aircraft

The present invention relates to a rotor assembly where associated electric motors are configured to rotate the rotor, control the collective pitch of the rotor/assembly, and/or control the cyclic pitch of the rotor/assembly, by varying the relative rotational angle between two or more of the associated electric motors.

Controlling blade pitch by a plurality of electric motors

The present embodiments disclose a torque dependent and resonant operating thrust-generating rotor assembly including a cyclic pitch control system for controlling tilting moments about a longitudinal rotor blade axis of one or more rotor blades, in order to control the pitch angle of the rotor blades and thereby also the horizontal movements of a helicopter vehicle or a rotary wing aircraft. A rotor torque assembly of the rotor assembly is further configured to operate in resonance, thereby providing a resonant gain effecting a rotational offset in relation to changes in torque generated by the motor.

Resonant operating rotor assembly

Provided herein is a rotor attachment assembly for an aircraft. A rotor attachment assembly includes a connecting assembly associated with the aircraft and a rotor assembly configured to be connected to the connecting assembly. The rotor assembly includes a plurality of fins configured to fit a respective plurality of cut-outs of the connecting assembly, a hollow section configured to accommodate at least a part of a pin of the connecting assembly so as to center the rotor assembly relative to the connecting assembly, and a spring configured to expand to allow the fins to pass and to close to retain the fins when the rotor assembly is connected to the connecting assembly.

Quick release rotor attachment systems and methods

The presented embodiments relates to a path-based flight maneuvering system and a method for providing easier operation control and enhanced operation capability of unmanned aerial vehicles and their associated features. The embodiments further entails a method for maneuvering an aircraft by means of a positioning device, a camera and a display displaying an image captured by the camera including a cursor projected on the image in the display.

Path-based flight maneuvering system

The present invention discloses a rotor control system where rapid changes in rotor torque are transferred into moment forces acting about the blade pitch axis of a rotor blade in a thrust-generating rotor, to ultimately control the movements of a rotary wing aircraft. The moment forces acting on the rotor blade are transferred through a carefully adjusted damping member in order to allow rapid changes in rotor torque to create cyclic changes in blade pitch angle, while slow or permanent changes are cancelled out and affects the rotational speed and the thrust generated by the rotor, without permanently affecting the blade pitch angle of individual rotor blades.

Thrust-generating rotor assembly

The present invention relates to a system and a method for measuring and determining the depth, offset and translation in relation to one or several features in the field of view of an image sensor equipped UAV. The UAV comprises at least an autopilot system capable of estimating rotation and translation, processing means, height measuring means and one or more imaging sensor means. Given the estimated translation provided by the autopilot system, the objective of the present invention is achieved by the following method; capturing an image, initiating a change in altitude, capturing a second image, comparing the images and the change in height provided by the sensor to produce a scale factor or depth. If depth is estimated, then calculating the scale factor from the depth, and calculating the actual translation with the resulting scale factor.

Method for calculating the distance to a ground target from an aerial vehicle

A rotor assembly for helicopter vehicles for providing an easy way of controlling pitch, roll and lift of the aircraft by respective servo actuators. The rotor assembly has a rotor shaft, at least two rotor blades, a rotor head, and a non-rotating swash plate. The rotor assembly also includes a pitch hinge for each rotor blade connecting each rotor blade to the rotor head. The rotor assembly also includes a guide member for each rotor blade. As the rotor assembly rotates, the guide members are in substantial contact with an upper surface of the non-rotating swash plate. Forces such as magnetic and/or an aerodynamic forces are applied on the rotor blades and are sufficiently strong to create a valve effect on the pitch hinge, which in turn maintains contact between the guide members and the non-rotating swash plate.

Rotor assembly

A rotor assembly for helicopter vehicles for stabilizing the aircraft and thus providing an easy way of controlling pitch and roll of the aircraft by respectively associated magnetic actuators. The rotor assembly comprises a rotor with two flexible rotor blades, a rotor head rotationally coupled to the rotor shaft, a rotating swash plate, with at least three fly bars extending therefrom. The swash plate is rotationally coupled to the rotor shaft and adjusted to tilt in all directions relative to a plane perpendicular to the rotor shaft. The rotor head is hinged to the rotor shaft in one direction so that the rotor head and the rotor blades jointly are not able to tilt around their transversal axis. The coupling between the rotating swash plate and the rotor head provide synchronized tilt movements between the rotor head and the rotating swash plate around the longitudinal axis of the rotor head.

The embodiments herein disclose a personal UAV kit for storing, preparing and remote control of micro UAVs (). The UAV kit includes a base unit (), a control unit () and at least one UAV. The UAVs can typically be a winged aircraft with foldable wings or a helicopter with a two-bladed or foldable rotor. The base unit comprises UAV compartments for housing at least one UAV, bay () for storing the control unit, batteries and electronic components for charging, communication, control and processing and storing of data. In addition, the system includes an eye near display device for viewing system information and sensor data, typically live video, transmitted from the UAV.

UAV kit

Local wind fields can be predicted if both the airspeed and the ground speed of the helicopter are known. An aircraft that uses an inertial navigation unit, autopilot and estimator allows a measure of ground speed to be known with good certainty. The embodiments herein extends this system to allow an estimate of the local wind field to be found without actively using an airspeed sensor, but instead combining the measurements of an accelerometer and a drag force model and a model of controlled aerodynamics of the aircraft to estimate the airspeed, which again can be used to estimate the local wind speed.

Passive local wind estimator

The present invention discloses a control stick for controlling an UAV formed by a bar with buttons on the bar head and a GUI displaying airplane like icons providing feedback of current steering control status of a UAV.

Control of UAV

A method and a remote control for controlling and monitoring surrounding areas of an Unmanned Aerial Vehicle (UAV) by an operator with a remote control comprising a flight display are provided. The method and remote control provide an advantageously effect for the purposes of controlling and monitoring the surroundings of a UAV by combining the image captured by a UAV camera with a transparently overlaid positional and navigation map providing a perception enabling the operator to have a complete overall view of the situation, utilizing a common screen section of a flight display and thereby not having to shift eye view. Viewing images and positional and navigation information should not interfere with each other.

Method and device for controlling and monitoring the surrounding areas of an unmanned aerial vehicle (UAV)

A method and device for precise control of and controller design for aircrafts consisting of at least one spinning part and at least one non-spinning part is provided. The required torques for control of the spinning parts and for the non-spinning parts are continuously and individually calculated. All torques are combined to get the correct torque for the complete aircraft. Doing this, it's possible to continuously apply the correct torque, both correctly distributed among the roll and pitch axes (correct angle), and correct magnitude. The result is a decoupling of the roll and pitch axes, simplifying controller design to a design of two single input single output controllers, one for each axe.

Growing community of inventors

Nesbru, Norway

Petter Muren