| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244063000 | Launching | 54 |
| 20080203220 | AERIAL VEHICLE LAUNCHING SYSTEM AND METHOD - The present invention discloses an aerial vehicle launching system, which may include a launch platform and a restraint system coupled to the launch platform. The restraint system has at least one passive restraint suitably adapted to indirectly restrain an aerial vehicle, where the restraint system is configured to coordinate the uniform retention and release of the passive restraint in order to launch the aerial vehicle. | 08-28-2008 |
| 20090134273 | UNMANNED AERIAL VEHICLE AND LAUNCH ASSEMBLY - An unmanned aerial vehicle (UAV) is provided, that is cost effective to use and manufacture and that includes a low count of component parts, allowing mission planners to use the UAVs in a disposable manner. The UAV includes an airframe having a central body and wings extending from the central body, defining an interior cavity. The airframe includes an upper and a lower shell, each configured of a unitary piece of plastic. The upper and lower shells have walls among them that define a fuel tank and a payload bay in a stacked configuration. The airframe can further include a payload cover configured to enclose the payload bay and to contribute to the central body of the airframe. A launch assembly is also provided. In a first configuration, a launch assembly is provided, that includes a container for housing multiple UAVs and a deployment mechanism that initiates rapid ejection of the UAVs from the container. In a second configuration, a launch assembly is provided, that includes an elastic tether connecting a UAV to an accelerated mass for gentle acceleration to flight speed under a stable tow. | 05-28-2009 |
| 20090134274 | ACCELERATING DEVICE - [PROBLEMS] Providing an accelerating device capable of safely and efficiently accelerating an aircraft even if the aircraft is a high-speed and heavyweight one. | 05-28-2009 |
| 20090146002 | INITIATING FLIGHT OF A FLYING STRUCTURE - In example embodiments described herein, techniques are described for launching flying structures such as a plank wings or a gliders, canards, or any other flying structures. In some example embodiments, a rotational arrangement facilitates such launches. In operation, a rotational arrangement couples with the flying structure and is configured to allow a user to impart rotational movement to the flying structure. In imparting the rotational movement, the rotational mechanism allows an automatic variation of a radius of the associated radius of curvature. | 06-11-2009 |
| 20090212157 | MICRO-ROTORCRAFT SURVEILLANCE SYSTEM - A flying micro-rotorcraft unit is provided for remote tactical and operational missions. The unit includes an elongated body having an upper and a lower end. The body defines a vertical axis. The unit further includes a navigation module including means for determining a global position of the elongated body during flight of the unit. Rotor means of the unit is coupled to the upper end of the elongated body for generating a thrust force that acts in a direction parallel to the vertical axis to lift the elongated body into the air. The rotor means is located between the elongated body and the navigation module. | 08-27-2009 |
| 20090242693 | SYSTEM FOR SHIPBOARD LAUNCH AND RECOVERY OF UNMANNED AERIAL VEHICLE (UAV) AIRCRAFT AND METHOD THEREFOR - A system to launch and recover an Unmanned Aerial Vehicle (UAV) aircraft has a pole member attached to a deck of a ship. An arm member is attached to the pole member and extends away from the pole member in an approximately horizontal direction. The arm member is able to move rotationally and vertically on the pole member. An attachment mechanism is attached to a distal end of the arm member for holding and capturing the UAV aircraft. Momentum of the UAV aircraft causes the arm member to move rotationally around and vertically on the pole member when the UAV aircraft is coupled to the attachment mechanism. | 10-01-2009 |
| 20090250550 | METHOD OF LAUNCHING A CATAPULT, CATAPULT, AND LOCKING DEVICE - A method of launching a catapult, a catapult and a locking device for a catapult. The catapult comprises a carriage for fastening an aircraft. The carriage can be provided with a high acceleration by directing a launching force generated by a launching device thereto. The carriage can be held at a launching position by means of the locking device. The catapult further comprises a takeoff damper that generates a damping force having a direction opposite relative to the launching force. Accordingly, the takeoff damper restricts the acceleration of the carriage at the initial launching moments. | 10-08-2009 |
| 20090314882 | MICRO AIR-VEHICLE TRANSPORT CONTAINER AND LAUNCH SYSTEM - 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. | 12-24-2009 |
| 20090314883 | UAV LAUNCH AND RECOVERY SYSTEM - An unmanned aerial vehicle (UAV) is launched and recovered using a UAV management system. The UAV is stored in a magazine and moved from the magazine during a launch operation and to the magazine during a recovery operation. | 12-24-2009 |
| 20100096496 | SLIDING FRAME AIRCRAFT LAUNCHER AND RELATED METHOD - An aircraft launcher includes a base frame, a first sliding frame that slides with respect to the base frame, a second sliding frame that slides with respect to the first sliding frame, an aircraft support located on the second sliding frame, and a drive apparatus adapted to slide at least one of the first sliding frame and the second sliding frame with respect to the base frame. | 04-22-2010 |
| 20100123041 | GAS GENERATOR LAUNCHER FOR SMALL UNMANNED AERIAL VEHICLES (UAVS) - The launching of an unmanned projectile includes pre-packaging a barrel with a projectile, a pusher cup, and a gas generator. The gas generator generates gas to propel the projectile out of the barrel. A pressure chamber increases a pressure of the gas in the barrel. The pressure chamber comprises a front body portion connected to the gas generator; an aft body portion connected to the front body portion and the gas generator; and a vent sleeve positioned around the front body portion and adapted to provide an aperture through which the gas exits the barrel in order to control a level of gas pressure in the barrel. A triggering of the gas generator causes the pusher cup to push the projectile out of the barrel at a predetermined launch velocity in order to attain a predetermined self-propelled flight trajectory, wherein the triggering causes the pusher cup to exit the barrel. | 05-20-2010 |
| 20100252676 | METHOD AND APPARATUS FOR RAM DECELERATION IN A LAUNCH SYSTEM - One embodiment includes a launch vessel defining an elongate, linear interior extending from a bottom portion to an exit opening. The embodiment includes a ram slidably disposed in the launch vessel, the ram sealed to the vessel. The embodiment also includes one or more wedges coupled to the launch vessel along the interior proximal the exit opening, with each wedge shape sized to increasingly narrow a cross section of the interior along an exit vector extending from the bottom portion toward the exit opening. In the embodiment, the vessel is to house a charge proximal the bottom portion, the charge to propel the ram along the exit vector, with the one or more wedges sized to stop be ram inside the interior. | 10-07-2010 |
| 20110062281 | LAUNCH SYSTEM - The present disclosure relates to a launch system for air vehicles. More specifically, the present disclosure relates to launching unmanned air vehicles (UAVs) that are unable to be launched by hand. The present disclosure provides a system for launching a winged vehicle, including: a projectile launching device; and a device for converting projectile momentum into acceleration of a winged vehicle. | 03-17-2011 |
| 20110073707 | METHODS AND APPARATUS FOR MARINE DEPLOYMENT - Methods and apparatus for marine deployment according to various aspects of the present invention may operate in conjunction with a floatable housing adapted to be deployed by a marine vehicle. The floatable housing may be adapted to be launched from a marine vehicle and rise to the surface. Assets, such as an unmanned aerial vehicle, may be deployed from the surfaced floatable housing. | 03-31-2011 |
| 20110133024 | METHOD AND APPARATUS FOR RETRIEVING A HOVERING AIRCRAFT - For retrieval of a hovering aircraft, a cable, bar, or similar fixture is suspended in an approximately horizontal orientation across the retrieval area between two well-separated supports. The aircraft slowly flies into this fixture, which then slides along the aircraft in a direction approximately parallel with the aircraft's thrust line. This leads to the aircraft becoming fastened to the fixture by an interceptor or aircraft capturer, which in alternative embodiments are respectively on the aircraft or the fixture or both. Thrust is then reduced, and the aircraft comes to rest hanging from the fixture for subsequent removal. Retrieval is thus accomplished with simple and economical apparatus, light and unobtrusive elements on the aircraft, low risk of damage, and only moderate piloting accuracy. | 06-09-2011 |
| 20110147515 | HAND LAUNCHABLE UNMANNED AERIAL VEHICLE - An unmanned aerial vehicle including a controller operating in a search mode of operation where a receiver of an acquisition sensor searches for a target and causes flight control surfaces to guide the vehicle in a downward spiral path, a terminal mode of operation where the acquisition sensor detects a target and causes flight control surfaces to direct the vehicle toward the target, and an activation mode of operation where a trigger sensor detects a target within a predetermined distance to the vehicle and the controller activates a responder. | 06-23-2011 |
| 20110147516 | COLD-LAUNCH DEVICE AND METHOD USING THE SAME - A cold-launch device, including a high-energy gas resource, a gas cylinder, a control valve, a gas-liquid mixing cylinder having a cylinder body, the high-energy gas resource is connected to the gas cylinder whereby supplying energy thereto, and the gas cylinder is connected to an terminal of the gas-liquid mixing cylinder via the control valve and a connecting pipe. | 06-23-2011 |
| 20110168838 | Launch tube deployable surveillance and reconnaissance system - An unmanned aerial surveillance and reconnaissance system are disclosed wherein an unmanned aerial vehicle is launchable from a launch tube, for instance, the bore of an existing weapons system mounted on a mobile vehicle, such as a weapon barrel of a tank or armored combat vehicle and which the launch may be remotely initiated from the protected armored compartment of the mobile vehicle. | 07-14-2011 |
| 20110204180 | Ground-based apparatuts for take off, landing and taxiing of aircraft - An apparatus for the take-off, landing and taxiing of an aircraft without undercarriage system or with retracted undercarriage, wherein the apparatus comprises a ground-based undercarriage, the speed of which can be matched to the speed of the aircraft when landing, the ground-based undercarriage ( | 08-25-2011 |
| 20110315817 | SYSTEMS AND DEVICES FOR REMOTELY OPERATED UNMANNED AERIAL VEHICLE REPORT-SUPPRESSING LAUNCHER WITH PORTABLE RF TRANSPARENT LAUNCH TUBE - An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node. | 12-29-2011 |
| 20120001020 | SYSTEMS AND DEVICES FOR REMOTELY OPERATED UNMANNED AERIAL VEHICLE REPORT-SUPPRESSING LAUNCHER WITH PORTABLE RF TRANSPARENT LAUNCH TUBE - An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node. | 01-05-2012 |
| 20120012695 | UAV Launch Attachment Assembly and Launch System - A UAV attachment assembly, used with a UAV launch assembly comprising a frame and a launch driver, comprises a base, a UAV support, a biasing element, a coupler, and a retainer. The base is operably coupled to the launch driver. The UAV support is mounted to the base and is placeable in vertically collapsed and vertically extended orientations. The biasing element biases the UAV support towards the collapsed orientation. The coupler releasably couples the UAV support to a UAV when the UAV support is in the extended orientation, the UAV support being free of the UAV when in the collapsed orientation. The retainer maintains the UAV support in the vertically extended orientation prior to launch and releases the UAV support at launch so that the biasing element can cause the UAV support to move towards the collapsed orientation and to disengage from the UAV. | 01-19-2012 |
| 20120068009 | SUBMERSIBLE TRANSPORT AND LAUNCH CANISTER - Embodiments of a submersible transport and launch canister are provided for use by a diver in the deployment of an airborne object. In one embodiment, the submersible transport and launch canister includes a pressure vessel having an open end portion and a storage cavity configured to receive the airborne object therein. A diver-actuated cap is movable between an open position and a closed position in which the diver-actuated cap sealingly engages the open end portion. A propellant device is fluidly coupled to the storage cavity and is configured to propel the airborne object from the storage cavity and through the open end portion when the propellant device is actuated by the diver. | 03-22-2012 |
| 20120068010 | SUBMERSIBLE TRANSPORT AND LAUNCH CANISTER AND METHODS FOR THE USE THEREOF - Embodiments of a method for deploying an airborne object are provided utilizing a submersible transport and launch canister of the type that includes a pressure vessel in which the airborne object is stored and a cap which sealingly engages the pressure vessel. In one embodiment, the method includes the steps of positioning an end portion of the pressure vessel above the surface level of a body of water, opening the cap, and launching the airborne object from the pressure vessel while in the body of water. | 03-22-2012 |
| 20120080556 | Systems and Methods for Autonomous Operations of Unmanned Aerial Vehicles - Systems and methods are disclosed for autonomous or remote-controlled operation of unmanned aerial vehicles (“UAVs”). An integrated mechanical and electrical system is capable of launching, controlling, snagging, recovering, securing, parking, and servicing UAVs without human intervention at the site of the system. The illustrative embodiment comprises a boom and a container that houses the boom and UAV(s). The boom rotates about its longitudinal axis to operationally orient a plurality of faces thereof. Each face is associated with certain system operations, including but not limited to: launching a UAV, snagging a UAV from the air, and securing a UAV to the boom. | 04-05-2012 |
| 20120205488 | UNMANNED AERIAL VEHICLE LAUNCH SYSTEM - A system for launching an unmanned aerial vehicle (UAV) payload includes a launch tube, liquid rocket, and launch control assembly. The rocket is positioned in the launch tube and contains the UAV payload. A booster assembly may include a canister partially filled with liquid. A gas cylinder is filled with compressed gas. The liquid is pre-pressurized by the gas or mixed with the gas right before launch such that, upon launch, liquid and gaseous thrust stages launch the rocket to a threshold altitude. The UAV payload deploys after reaching the threshold altitude. Optional stability tubes may be connected to the launch tube, which may be buoyant for water-based operations. An optional tether may be connected to the liquid rocket for arresting its flight prior to reaching apogee. The UAV payload is not launched directly by the gas/liquid mix. A method of launching the UAV payload is also disclosed. | 08-16-2012 |
| 20120205489 | INITIATING FLIGHT OF A FLYING STRUCTURE - In example embodiments described herein, techniques are described for launching flying structures such as a plank wings or a gliders, canards, or any other flying structures. In some example embodiments, a rotational arrangement facilitates such launches. In operation, a rotational arrangement couples with the flying structure and is configured to allow a user to impart rotational movement to the flying structure. In imparting the rotational movement, the rotational mechanism allows an automatic variation of a radius of the associated radius of curvature. | 08-16-2012 |
| 20130026286 | Systems And Methods For Launching A Folding Aircraft - A canister system for a folding aircraft may include a canister housing and a launch mechanism powered by one or more compression springs. A hand-operated drive mechanism may rotate a plurality of threaded rods to drive the launch mechanism from a released position to a cocked position, in which mechanical energy is stored in the springs. A latch mechanism may capture the launch mechanism in the cocked position. The canister may include a housing for receiving and storing the aircraft when the launch mechanism is in the cocked position. A trigger mechanism may release the latch mechanism, permitting the energy stored in the compressed springs to drive the launch mechanism toward the released position and propel the aircraft from the housing at launch velocity. | 01-31-2013 |
| 20130068881 | SOLAR CONCENTRATOR AND ASSOCIATED ENERGY CONVERSION APPARATUS - One embodiment includes a launch vessel defining an elongate, linear interior extending from a bottom portion to an exit opening. The embodiment includes a ram slidably disposed in the launch vessel, the ram sealed to the vessel. The embodiment also includes one or more wedges coupled to the launch vessel along the interior proximal the exit opening, with each wedge shape sized to increasingly narrow a cross section of the interior along an exit vector extending from the bottom portion toward the exit opening. In the embodiment, the vessel is to house a charge proximal the bottom portion, the charge to propel the ram along the exit vector, with the one or more wedges sized to stop be ram inside the interior. | 03-21-2013 |
| 20130264416 | THREE-STRING STUNT KITE - A stunt kite is attached to three lines that are attached to a single handle. Moving the handle will change the angle of the kite by pulling on the desired line or lines. By changing the angle of the kite, the user can direct the wind that is pushing on its sail, causing the kite to go off on a different direction. By doing this, the user is able to perform controlled aerial, ground, underwater and partially submerged stunts. | 10-10-2013 |
| 20130277497 | MAN-PORTABLE, MULTI-MODE UNMANNED AERIAL SYSTEM LAUNCHER - A man-portable unmanned aerial system launcher (UAS) launcher includes a rail assembly having an internal track and a carriage assembly having a base configured to translate within the internal track. The carriage assembly also includes a cradle configured to support a UAS and a bracket configured to support the cradle above the base. The UAS launcher includes a launch control system configured to secure the carriage assembly in the launch-ready position until the launch control system receives a launch signal. The UAS launcher also includes one or more elastic members configured to engage the carriage assembly and the rail assembly. Once the carriage assembly is translated to the launch-ready position, strain is applied to the carriage assembly by the one or more elastic members. Release of the carriage assembly enables force generated by strain of the elastic members to propel the carriage assembly toward a launch position. | 10-24-2013 |
| 20130306791 | METHOD AND APPARATUS FOR AUTOMATED LAUNCH, RETRIEVAL, AND SERVICING OF A HOVERING AIRCRAFT - Various embodiments of the present disclosure provide an apparatus configured to automatically retrieve, service, and launch an aircraft. For retrieval, the aircraft drops a weighted cable, and pulls it at low relative speed into a broad aperture of the apparatus. In certain instances, the cable is dragged along guiding surfaces of the apparatus into and through a slot until its free end is captured. The aircraft becomes anchored to the apparatus, and is pulled downward by the cable into a receptacle. Guiding surfaces of the receptacle adjust the position and orientation of a probe on the aircraft, directing the probe to mate with a docking fixture of the apparatus. Once mated, the aircraft is automatically shut down and serviced. When desired, the aircraft is automatically started and tested in preparation for launch, and then released into free flight. A full ground-handling cycle is thus accomplished with a simple, economical apparatus. | 11-21-2013 |
| 20130313357 | UAV Launch Attachment Assembly and Launch System - A UAV attachment assembly, used with a UAV launch assembly comprising a frame and a launch driver, comprises a base, a UAV support, a biasing element, a coupler, and a retainer. The base is operably coupled to the launch driver. The UAV support is mounted to the base and is placeable in vertically collapsed and vertically extended orientations. The biasing element biases the UAV support towards the collapsed orientation. The coupler releasably couples the UAV support to a UAV when the UAV support is in the extended orientation, the UAV support being free of the UAV when in the collapsed orientation. The retainer maintains the UAV support in the vertically extended orientation prior to launch and releases the UAV support at launch so that the biasing element can cause the UAV support to move towards the collapsed orientation and to disengage from the UAV. | 11-28-2013 |
| 20140061377 | Spear Tactical RFID Unmanned Aircraft System (UAS) - This disclosure relates generally to the field of unmanned aircraft systems (UAS), specifically to launch, fly and land unmanned aerial vehicles (UAV). This disclosure describes a system comprised of a UAV, a portable launch pad, a telescoping landing net and an integrated RFID system. This system provides a unique combination of UAV performance and payload capabilities with integrated Radio Frequency Identification Device (RFID) electronic systems capable of withstanding extreme weather conditions including high winds in remote locations. | 03-06-2014 |
| 20140061378 | METHOD AND APPARATUS FOR RETRIEVING A HOVERING AIRCRAFT - For retrieval of a hovering aircraft, a cable, bar, or similar fixture is suspended in an approximately horizontal orientation across the retrieval area between two well-separated supports. The aircraft slowly flies into this fixture, which then slides along the aircraft in a direction approximately parallel with the aircraft's thrust line. This leads to the aircraft becoming fastened to the fixture by an interceptor or aircraft capturer, which in alternative embodiments are respectively on the aircraft or the fixture or both. Thrust is then reduced, and the aircraft comes to rest hanging from the fixture for subsequent removal. Retrieval is thus accomplished with simple and economical apparatus, light and unobtrusive elements on the aircraft, low risk of damage, and only moderate piloting accuracy. | 03-06-2014 |
| 20140077028 | METHOD AND APPARATUS FOR RETRIEVING A HOVERING AIRCRAFT - For retrieval of a hovering aircraft, a cable bar, or similar fixture is suspended in an approximately horizontal orientation across the retrieval area between two well-separatod supports. The aircraft slowly flies into this fixture, which then sides along the aircraft in a direction approximately parallel with the aircraft's thrust. line.. This leads to the aircraft becoming fastened to the fixture by an interceptor or aircraft capturer, which in alternative embodiments are respectively on the aircraft or the fixture or both. Thrust is then reduced, and the aircraft comes to rest hanging from the fixture for subsequent removal. Retrieval is thus accomplished with simple and economical apparatus, light unobtrusive elements on the aircraft, low risk of damage, and only moderate piloting accuracy. | 03-20-2014 |
| 20140117153 | SYSTEMS AND METHODS TO LAUNCH AIRCRAFT - Systems and methods to launch an aircraft are disclosed. In one embodiment, a system to launch an aircraft comprises a launch arm comprising at least one load cell, an aircraft coupled to the launch arm, and a release mechanism in communication with the at least one load cell, wherein the release mechanism releases the aircraft when the at least one load cell indicates that a load on the launch arm is below a predetermined threshold. Other embodiments may be described. | 05-01-2014 |
| 20140124619 | METHOD AND APPARATUS FOR AUTOMATED LAUNCH, RETRIEVAL, AND SERVICING OF A HOVERING AIRCRAFT - Various embodiments of the present disclosure provide an apparatus configured to automatically retrieve, service, and launch an aircraft. For retrieval, the aircraft drops a weighted cable, and pulls it at low relative speed into a broad aperture of the apparatus. In certain instances, the cable is dragged along guiding surfaces of the apparatus into and through a slot until its free end is captured. The aircraft becomes anchored to the apparatus, and is pulled downward by the cable into a receptacle. Guiding surfaces of the receptacle adjust the position and orientation of a probe on the aircraft, directing the probe to mate with a docking fixture of the apparatus. Once mated, the aircraft is automatically shut down and serviced. When desired, the aircraft is automatically started and tested in preparation for launch, and then released into free flight. A full ground-handling cycle is thus accomplished with a simple, economical apparatus. | 05-08-2014 |
| 20140203137 | AIRCRAFT THRUST, ASSEMBLY, AND METHODS - Systems and methods for ground-based aircraft thrust systems are provided. In particular, some embodiments use an electromechanical thrust assembly to accelerate aircraft using ground-based energy for takeoff. The assembly can include one or more sleds, one or more maglev tracks, and/or one or more linear motors. Airplanes are loaded onto a sled (e.g., a saddle-shaped sled) that supports and balances the airplane instead of the landing gear aboard the aircraft. The sled levitates above the ground using high-density permanent magnet arrays. Magnetic levitation forces are varied along the assembly to account for lift provided by airflow over the wings. An aircraft thrust system includes a magnetically levitated saddle-shaped sled with airbags that support an aircraft during takeoff acceleration coupled with a linear motor that spans the length of the distance needed for takeoff. | 07-24-2014 |
| 20140231583 | Launch Device for Tube-Launched Projectile - A device for launching a projectile from the bore of a tube. A launch frame having a longitudinal axis is configured for being received within the bore of the tube with a shuttle assembly configured for urging a projectile alone the tube's longitudinal axis. A shuttle assembly tensioning means is configured to urge the shuttle assembly along the longitudinal axis and a shuttle assembly retention means is configured for the selective retention and release of the shuttle assembly at a predetermined position along the longitudinal axis. | 08-21-2014 |
| 20140252162 | UAV LAUNCHING FROM MOVING PLATFORM - A system for launching an unmanned aerial vehicle (UAV) from a moving platform, the system comprising: a platform configured to carry the UAV; one or more sensors configured to measure forces acting between said platform and said UAV in one or more directions; a mooring mechanism configured to moor said UAV to said platform; and a controller configured to: transmit at least one trimming command to said UAV based on measurements of said one or more sensors, and cause said mooring mechanism to release said UAV from said platform following the transmitting of the at least one trimming command, when the measurements of said one or more sensors indicate that a lift force is sufficiently close to a weight of the UAV. | 09-11-2014 |
| 20150008280 | LAUNCHED AIR VEHICLE SYSTEM - A launch canister for ejection from a submerged launch platform, the launch canister being adapted for ejection in a direction substantially along a first axis of the launch canister and comprising: an enclosure for carrying a UAV; a nose cap releasably located in a launch opening at a forward end of the launch canister; a launch mechanism for driving a UAV carried in the enclosure out of the launch canister through the launch opening in a direction substantially along said first axis; and a water surface sensor for detecting when the nose cap of the canister broaches the surface of the water; wherein the launch canister is configured to, on the water surface sensor detecting that the nose cap of the canister has broached the surface of the water, immediately release the nose cap and initiate the launch mechanism to drive a UAV carried in the enclosure out of the launch canister through the launch opening. | 01-08-2015 |
| 20150060600 | ELECTRIC UNMANNED AERIAL VEHICLE LAUNCHER - Embodiments of the present invention provide improvements to UAV launching systems. The disclosed launching system eliminates the use of hydraulic fluid and compressed nitrogen or air by providing an electric motor-driven tape that causes movement of a shuttle along a launcher rail. | 03-05-2015 |
| 20150321758 | UAV deployment and control system - A system of software and hardware components is disclosed comprising a system designed to deploy, manage, and control unmanned aerial vehicles (UAVs). The integrated UAVs can be deployed from vehicles, buildings, and other types of fixed locations. The present disclosure enables users to deploy UAVs to perform pre-defined flight maneuvers and fly to pre-designated locations. The present disclosure also and affords the ability for users to maintain the UAVs flight control locally or transfer control of a deployed UAV to remotely located system operators. | 11-12-2015 |
| 20150329205 | AIRCRAFT DEPLOYMENT AND RETRIEVAL OF UNMANNED AERIAL VEHICLES - An aircraft system incorporates a first aircraft having a grappling device including a first gripper with a first actuator and a second gripper with a second actuator. The first gripper and the second gripper are movable between an open and a closed position to engage a hooking device and pivot together to change a capture angle. A first controller receives a command and operates the actuators in response to open and close the first and second grippers of the grappling device. The controller also receives a second command and operates the first and second actuators to pivot the grippers and provide grappling at a range of capture angles. A second aircraft, which may be a UAV, incorporates the hooking device. The hooking device includes a ring rotatable from the surface and a third actuator to rotate the ring between a stowed and an extended position. | 11-19-2015 |
| 20160009412 | LAUNCHING AN UNMANNED AERIAL VEHICLE USING A HAND-HELD WEAPON | 01-14-2016 |
| 20160039536 | SYSTEMS AND DEVICES FOR REMOTELY OPERATED UNMANNED AERIAL VEHICLE REPORT-SUPPRESSING LAUNCHER WITH PORTABLE RF TRANSPARENT LAUNCH TUBE - An unmanned aerial vehicle (UAV) launch tube ( | 02-11-2016 |
| 20160083112 | UAV Take-Off Method and Apparatus - A method and apparatus for launching unmanned air vehicles (UAVs) includes supporting the unmanned air vehicle on a surface vehicle, such as a dolly cart, for riding along a surface such as ground or water. A towline is connected to the surface vehicle and the towline is pulled to force the unmanned air vehicle in a forward direction at a speed sufficient for take-off. The towline may be pulled by a winch system. In some embodiments the UAV is positioned with a nose down angle on the surface vehicle. The nose down angle permits overspeed of the UAV and cart as it is pulled along the ground, as well as controlled take-off. | 03-24-2016 |
| 20160090179 | APPARATUS, SYSTEM, AND METHOD FOR FLYING AN AIRCRAFT - Described herein is an aircraft launch system that includes a riser coupleable to an aircraft. The riser includes an actuator and a tether coupled to the actuator. The aircraft launch system further includes a sky anchor coupled to the tether. The actuator is operable to retract the tether and draw together the sky anchor and the aircraft. | 03-31-2016 |
| 20160096636 | Electromagnetic Tow System For Nonpowered Ultralight Aircraft - An electromagnetic tow system for towing nonpowered ultralight aircraft that allows for towing under constant and controlled tow line tension using both pay-in and pay-out tow methods. An electric motor is mechanically connected to a winch holding the tow line and electrically connected to a power supply. When the line is paid out on tow, the motor is disconnected from its power supply and its non-field windings are shorted outright or connected through a resistor. As the motor's rotor rotates inside the motor's magnetic field (created by the motor's permanent magnets or powered stator windings) under the mechanical load of the towed aircraft, current is generated in the non-field windings of the motor, which creates braking torque opposing the mechanical rotation of the rotor and provides tow line tension. In a preferred configuration, a hub motor is used, with the winch drum side plates mounted directly onto the sides of the hub motor to serve as heat sinks cooling the motor; variable resistor is used to control the braking torque, plugging is available to increase braking torque when necessary, and the electromagnetic-braking-generated voltage and current are used to recharge the motor's portable power supply. The same motor is also used to rewind the tow line onto the spool as needed. | 04-07-2016 |
| 20160114906 | APPARATUS AND METHOD FOR AUTOMATED LAUNCH, RETRIEVAL, AND SERVICING OF A HOVERING AIRCRAFT - An apparatus and method for automated launch, retrieval, and servicing of a hovering aircraft is provided. The apparatus includes a line which is elevatable while maintaining a principally horizontal axis. For retrieval, the aircraft translates principally spanwise over the line, following a path which is principally horizontal and normal to the line. At an appropriate moment, the line is elevated and contacts the aircraft's wing. As the aircraft continues translating, the line slides along the wing until captured in a cleat. The aircraft is then stably tethered in hover, and its position can be manipulated by articulating the line, such as to guide the aircraft into a docking station. For launch the aircraft lifts itself into hover while tethered to the line. Articulation of the line guides the aircraft into a launch position, at which point the line is disconnected from the cleat, thereby releasing the aircraft. | 04-28-2016 |
| 20160137313 | TECHNIQUES FOR EMPLACING AN UNMANNED AERIAL VEHICLE LAUNCHER PRIOR TO LAUNCHING AN UNMANNED AERIAL VEHICLE - A technique is directed to launching an unmanned aerial vehicle (UAV). The technique involves positioning a UAV launcher over a ground location. The technique further involves installing, after the UAV launcher is positioned over the ground location and prior to launching the UAV, an anchor into the ground location to anchor the UAV launcher to the ground location. The technique further involves operating, after the UAV launcher is anchored to the ground location, the UAV launcher to impart launching force onto the UAV to launch the UAV, the anchor holding the UAV launcher substantially in place at the ground location to minimize energy loss as the UAV launcher imparts launching force onto the UAV. In some arrangements, the UAV launcher is capable of pivoting while remaining anchored between launches to accommodate changes in wind direction while maintaining substantial connection to the ground location for enhanced consistency and performance. | 05-19-2016 |
| 20160144956 | SYSTEM AND METHOD FOR IMPROVING TRANSITION LIFT-FAN PERFORMANCE - A system and method enabled to increase efficiency during a VTOL aircraft's transition. A VTOL aircraft enabled to operate multiple lift fans arranged into separately controllable groups, wherein the VTOL aircraft initially has vertical flight but transitions to horizontal flight. A first group of lift fans may be kept at full throttle, a second group of lift fans may be throttled to balance thrust and/or weight, and a third group of lift fans may be shut off. | 05-26-2016 |
| 20160152347 | LAUNCH DEVICE FOR REMOTELY CONTROLLED AIRCRAFT | 06-02-2016 |
