| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244110000 | Snares | 20 |
| 20080308673 | Secure System and Method for Aircraft Emergency Landing - A secure system and method for aircraft emergency landing are provided. The system includes a movable board, a detecting device, a controlling system and a buffering device. The detecting device detects the landing location and speed, and transmits the information to the controlling system, which moves the board and makes the moving speed and position of the board match with those of landing aircraft according to the detected information. The aircraft will land on the movable board. The buffering device includes plural independent gas capsules full of antiflaming gas provided on the top surface of the movable board. The gas capsules counteract the aircraft's inertia and absorb the impact force quickly. Plural gas capsules are provided independently from each other. Thus, even though the gas capsules hit aircraft first are broken, remain gas capsules still can perform the function of buffering. | 12-18-2008 |
| 20090166469 | Aircraft arrestor system and method of decelerating an aircraft - An arrestor system and method of decelerating an aircraft. The arrestor system has a base with at least one tile made of a plurality of particles being arranged such that the particles form a plurality of water drainage passageways and wherein the at least one tile has a compressive strength which will fatigue upon a force being imparted thereto which is greater than the compressive strength of the tile. | 07-02-2009 |
| 20090189016 | SYSTEMS AND METHODS FOR RECOVERING AND CONTROLLING POST-RECOVERY MOTION OF UNMANNED AIRCRAFT - Systems and methods for recovering unmanned aircraft and controlling post-recovery motion of the aircraft are disclosed herein. An aircraft recovery system for recovering an unmanned aircraft in flight in accordance with one embodiment of the disclosure, for example, can include an inflatable aircraft recovery system having an inflatable portion with a generally vertical orientation. The inflatable portion can also include a landing pocket extending at least partially therethrough. The landing pocket is sized to receive at least a portion of a fuselage of the aircraft. The aircraft recovery system can also include a guidance system at least proximate to the landing pocket and positioned to guide the aircraft toward the landing pocket. | 07-30-2009 |
| 20100044507 | Crash Attenuation System for Aircraft - A crash attenuation system for an aircraft, the system having an airbag carried by the aircraft and inflatable generally adjacent an exterior of the aircraft. The airbag has at least one vent for releasing gas from the interior of the airbag. A first gas source is in fluid communication with the interior of the airbag for inflating the airbag with gas generated provided by the first gas source. A vent valve is provided for controlling a flow of gas through each vent, each vent valve being selectively configurable between an open state, in which gas can pass through the associated vent from the interior of the airbag, and a closed state, in which gas is retained within the interior of the airbag. A second gas source is provided for at least partially re-inflating the airbag after venting of gas through the at least one vent. | 02-25-2010 |
| 20110011974 | LAUNCH AND RECOVERY SYSTEM FOR UNMANNED AERIAL VEHICLES - A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) ( | 01-20-2011 |
| 20120091272 | HARPON D'ANCRAGE PAR EXEMPLE D'UN AERONEF ET SYSTEME D'ANCRAGE COMPORTANT UN TEL HARPON - An anchoring harpoon ( | 04-19-2012 |
| 20130020437 | STABILIZED AGGREGATES AND OTHER MATERIALS AND STRUCTURES FOR PURPOSES INCLUDING, BUT NOT LIMITED TO, ENERGY ABSORPTION - Described are materials and structures for absorbing energy. The materials and structures are well suited for arresting aircraft and other vehicles, although their purposes need not be so limited. Also detailed are packaging and other solutions for maintaining system integrity, especially (but not exclusively) when foam glass or other aggregate is employed. | 01-24-2013 |
| 20130341462 | Apparatus and Method for Retrieving Unmanned Aerial Vehicles - A system and method for recovering unmanned aerial vehicles (UAVs) uses the fact that many small UAVs can hover in a vertical or near-vertical attitude. An exemplary system includes two or more rollers rotatable about respective axes of rotation, a mechanism to capture a UAV, and a support to which the rollers are mounted in such a way as to place the axes of rotation in parallel in a common plane. When the plane is in a vertical orientation, the capture mechanism is enabled to capture a UAV positioned adjacent the rollers. By hovering the UAV in the vertical position there is no forward velocity or momentum, and hence the craft can more easily be captured and the motor can be shut down without damaging the UAV. Misalignment during recovery is mitigated by cushioning in the rollers and the ability of the capture mechanism to compensate for imperfect alignment. | 12-26-2013 |
| 20140367514 | HOLDING CONTAINER FOR SHOCK ABSORBING SELF-DEPLOYABLE DEVICE - A device for absorbing impacts of a parachutist or airdropped package upon landing, which can equip a harness, and/or a skydiver or dropping pallet for performing the aircraft jump without any risk of interferences, allows, during the aircraft exit and free fall, to hold, neutralized in a reduced volume, an air-inflatable airbag, for deployment during the canopy descent. It includes a container back pad hooked to the harness and/or to the user or to the dropping pallet, which can be made removable by straps and bridles, in which an airbag is arranged such that its air scoop is closed by flaps locked by a cutaway cable. When the user exerts an action on the opening handle or when the parachute opens, the cable separates the flaps, allowing to unballast the airbag and open the air scoop to the air flow from the movement of the harness during the descent. | 12-18-2014 |
| 20160033245 | Missile for Implanting Actuator in a Room or Building - A new form of missile, for implantation of an actuator within a wall or building, is provided. In some aspects of the invention, the missile comprises an enclosed actuator, deployed upon successful implantation of the missile in a target wall. Preferably, the missile comprises stops and piercing grips to secure the missile within the target wall, and encourage the proper degree of penetration and a mounting position enabling the deployment of the actuator(s) comprised within the missile. In some embodiments, the actuator can be remotely actuated by control system and user commands. | 02-04-2016 |
| 20160097170 | FOAMED GLASS COMPOSITE ARRESTOR BEDS AND METHODS FOR MAKING AND USING THE SAME - A method of making a foamed glass composite engineered material arresting system for aircraft arrest, including heating glass frit to a temperature of between about 1500 degrees Fahrenheit and about 1900 degrees Fahrenheit, softening the frit to define a viscous glass material, and foaming the viscous glass material to yield a foamed glass body. The foamed glass body is then cooled, positioned in a bed located adjacent an airport runway, and at least partially surrounded with a structural matrix material to define a composite bed portion. The foamed glass body is incompressible and fails with a crushing failure mode. | 04-07-2016 |
| 20150102166 | SYSTEM AND METHOD FOR REDUCING THE STOPPING DISTANCE OF AN AIRCRAFT - A system for reducing a stopping distance of an aircraft may include an edge control system configured to control a leading edge device mounted to a wing of an aircraft. The edge control system may be configured to automatically command extension of the leading edge device from a first position to a second position in response to deployment of a spoiler if a ground speed of the aircraft is greater than a threshold ground speed. | 04-16-2015 |
| 20150321748 | SPEED BRAKE ALERTING SYSTEM AND METHOD - A system and method is provided for controlling the speed of an aircraft with a speed brake during landing. The system includes a speed brake control system and a speed brake controller coupled to the speed brake control system for arming the speed brake. An alert generator is coupled to the speed brake controller for generating an alert when the speed brake is not armed. | 11-12-2015 |
| 20110147519 | BRAKE DISC PACK FOR AIRCRAFT - An inert gas system is provided, particularly for aircrafts. The inert gas system comprises an inert gas reservoir, provided in a wing or a fuselage, for supplying inert gas to the at least one fuel tank. Inert gas is supplied via a piping system to at least one brake disc pack of at least one landing gear. Inert gas supplied generates an oxygen reduced atmosphere at the at least one brake disc pack. | 06-23-2011 |
| 20130146707 | METHOD AND APPARATUS FOR PROVIDING POWER IN AN AIRCRAFT TO ONE OR MORE AIRCRAFT SYSTEMS - A method and apparatus is disclosed in which an aircraft system such as the landing gear system or braking system is operated at least partially under power provided by a generator driven by the wheels of the landing gear. | 06-13-2013 |
| 20080203225 | Multiple support disc loader - The present invention is a portable engine powered horizontal action aircraft landing barrier arresting cable disc loading apparatus which includes an engine powered hydraulic pump; manual hydraulic pump; an elongated frame; a transverse axle having a reservoir for hydraulic fluid; a hydraulic cylinder and ram/piston secured to one end of the frame and a system of staves comprised partially of the elongated frame and slotted plates affixed at regular intervals along the longitudinal length opposite the hydraulic cylinder. The ram/piston is configured with a chain attachment hook which is movable toward and away from the staves and provides a longitudinal pulling force with respect to the staves. Multiple staves are provided to divide the pulling force between groups of the total number of discs to be loaded. The present invention has internal power redundancy and has a means of accessing external power for secondary redundancy. | 08-28-2008 |
| 20100019085 | DEVICE AND METHOD FOR RECOVERING UNMANNED AIRBORNE VEHICLES - The invention relates to a device for recovering unmanned airborne vehicles comprising support means connected to the ground and retention means connected to the support means, it being possible for the device to occupy a non-operational position and an operational position in which the retention means are interposed in the path of the unmanned airborne vehicle. The support means consist of at least one inflatable element ( | 01-28-2010 |
| 20100038479 | EMERGRNCY LANDING APPARATUS - The present invention discloses an apparatus for emergency landing comprising: an extraction vehicle ( | 02-18-2010 |
| 20100102166 | MISSILE INTERCEPTOR WITH NET BODY - The invention describes and claims an apparatus and method of missile interception. The missile interceptor comprises a net body with a plurality of sections and at least one missile trajectory effector. In the preferred variant, the missile trajectory effector is embodied as an exploding ring. A missile, passing through the net body, picks up a ring, which explodes once the missile passes a sufficient distance away from the missile interceptor. Preferred embodiments of the missile interceptor further comprise one or more vertically-positioned poles. Claimed method involves the use of such interceptor and positioning the interceptor on the likely trajectory of incoming missiles. | 04-29-2010 |
| 20100243799 | INTERCEPT SYSTEM FOR FALLING BOMBS - An intercept system for destroying a falling bomb includes a packable structure including a compressed expandable net of break resistant cords, a radio altimeter and a deployment mechanism for expanding and deploying the net below a falling bomb. The system also includes an explosive charge and a detonator for detonating the explosive charge when the detonator comes into contact with a bomb. A shoulder fired missile launcher propels the packable structure into the air below a falling bomb. The structure also includes a timer, responsive to the radio altimeter to detonate the explosive charge if a bomb is not encountered within a pre-selected amount of time. | 09-30-2010 |
| 20110303789 | MOBILE AIRCRAFT RECOVERY SYSTEM - An apparatus for the recovery of an aircraft includes a capture device and first and second pole pairs. The first pole pair includes first top and bottom poles respectively placed near first top and bottom portions of the capture device. The first pole pair is configured to move from a first position, in which the pole pair holds the capture device in an open position to capture the aircraft, to a second position, in which the pole pair holds the capture device in a closed position to contain the captured aircraft after impact of the aircraft on the capture device. The second pole pair includes second top and bottom poles respectively placed near second top and bottom portions of the capture device. The second pole pair is also configured to move from the first position to the second position. Further, energy elements are coupled on one end to a respective top or bottom portion of the capture device and on another end to a respective top or bottom pole. The energy elements are disposed to absorb the force of the impact of the aircraft. | 12-15-2011 |
| 20120032025 | UAV RECOVERY SYSTEM - An unmanned aerial vehicle (UAV) recovery system comprises a base and a pneumatic capture net, including a set of upwardly extending, flexible, inflatable tubes, supported by a capture net support assembly. Drag forces are exerted on a UAV by the set of tubes when the UAV flies into them. In some examples the recovery system includes a plurality of decelerators, each decelerator having a supply of a restraint strap, connected to the pneumatic net, which can be pulled from the decelerator upon the application of a sufficient force so that movement of the pneumatic net is resistible by forces exertable by the decelerators on the pneumatic net. | 02-09-2012 |
| 20120187243 | Unmanned aerial vehicle(UAV) recovery system - A UAV recovery system including a recovery cart; a guide mechanism for defining the path of the cart; a base station for capturing a UAV tailhook; a momentum transfer system driven by the inertia of the UAV through the arresting member to move the recovery cart along the guide mechanism away from the base station in the same direction as the UAV; an acceleration control device for converging the speeds and positions of the UAV and cart for enabling engagement of the cart and UAV as their relative speeds approach zero; and a brake system for stopping the recovery cart when the cart and UAV are engaged. Also disclosed is a UAV having a tailhook pivotably mounted on the UAV at the center of gravity of the UAV. | 07-26-2012 |
| 20130082137 | RAIL RECOVERY SYSTEM FOR AIRCRAFT - The present invention's side-arm recovery system enables large Unmanned Aircraft Systems (UASs) to operate from small vessels or from ground sites with a minimal footprint. The side-arm recovery system allows arresting an UAS independent of a runway. On the ground or on a ship, the system makes use of a specialized crane system that includes capture and energy absorption devices. A fuselage-mounted top hook snags a horizontal cable and the arresting forces act in the plane of symmetry through the central structure of the UAS. After the capture energy is absorbed, the recovery system safely lowers the aerial vehicle to a ground handling cart. The same system can be combined into a launcher and retriever system which further reduces the footprint by eliminating the need for a separate launcher. | 04-04-2013 |
| 20140231585 | LAUNCH AND RECOVERY SYSTEM FOR UNMANNED AERIAL VEHICLES - A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) ( | 08-21-2014 |
| 20150129716 | Point Take-Off and Landing of Unmanned Flying Objects - Point take-off and landing systems for an unmanned flying object. In one embodiment, the flying object is guided along a flight trajectory and approaches a landing body such that a latching element, coupled with a suspension cable suspended from the flying body, latches with a receiving latch, coupled with an extendable retractable beam projecting horizontally from a landing body side surface. A cable release/retraction mechanism engages and then releases/retracts the suspension cable. The beam is as maneuvered to haul the flying object onto a landing surface. In another embodiment, the flying object is guided along a flight trajectory and approaches a landing body such that a latching element, coupled with a suspension cable suspended from the flying body, latches with a receiving cable, supported by cable supports projecting vertically from a landing body top surface. A cable release/retraction mechanism releases/retracts the suspension cable, hauling the flying object onto the landing surface. | 05-14-2015 |
| 20150360797 | UNMANNED AIR VEHICLE RECOVERY SYSTEM - Embodiments of the present disclosure relate generally to safe arrestment and recovery of an airborne unmanned air vehicle (UAV). Specific embodiments provide a 360 degree capture engagement cage that can recover a UAV approaching from any direction. The systems described herein may be used regardless of wind direction. The systems described herein may also be used as an air-only based system. Other embodiments may be used as including both an upper and lower tether for the engagement cage. | 12-17-2015 |
| 20150375873 | Drive Mechanisms for Use in Controlling Rotation and Twist of a Tether - A system may include a tether, a tether gimbal assembly, a drive mechanism, and a control system. The tether may include a distal end, a proximate end, and at least one conductor. The tether gimbal assembly may be connected to the tether. The drive mechanism may be coupled to the tether gimbal assembly and may include a housing, a spindle, and a motor. The housing may be fixed to the tether gimbal assembly. The spindle may be rotatably coupled to the housing, and the tether may be coupled to the spindle and rotate in conjunction with the spindle. The motor may be coupled to the spindle and configured to rotate the spindle and the tether. And the control system may be configured to operate the drive mechanism to control twist in the tether. | 12-31-2015 |
| 20150375874 | Systems and Methods for Controlling Rotation and Twist of a Tether - A system may include a tether, a slip ring, a tether gimbal assembly, a drive mechanism, a control system. The tether may include a distal tether end coupled to an aerial vehicle, a proximate tether end, and at least one insulated electrical conductor coupled to the aerial vehicle. The slip ring may include a fixed portion and a rotatable portion, where the rotatable portion is coupled to the tether. The tether gimbal assembly may be rotatable about at least one axis and is coupled to the fixed portion of the slip ring. The drive mechanism may be coupled to the slip ring and configured to rotate the rotatable portion of the slip ring. And the control system may be configured to operate the drive mechanism to control twist in the tether. | 12-31-2015 |
| 20160005159 | Enhanced Accuracy for Tracking Tethered Airborne Vehicles - Wind energy systems, such as an Airborne Wind Turbine (“AWT”), may be used to facilitate conversion of kinetic energy to electrical energy. An AWT may include an aerial vehicle that flies in a path to convert kinetic wind energy to electrical energy. The aerial vehicle may be tethered to a ground station with a tether that terminates at a tether termination mount system. In one aspect, the tether termination mount system may include a tether termination unit configured in one or more gimbals that allow for the tether termination unit to rotate about one or more axes while tracking the aerial vehicle in flight. In a further aspect, the tether termination mount system may include an imaging device configured for imaging the aerial vehicle during flight in order to enhance tracking accuracy over that which is performed by angular motion of the tether termination unit. | 01-07-2016 |
| 20160016675 | SMALL UNMANNED AERIAL VEHICLE (SUAV) SHIPBOARD RECOVERY 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. | 01-21-2016 |
| 20160137311 | AERIAL SYSTEM AND VEHICLE FOR CONTINUOUS OPERATION - An aerial vehicle system for gathering data may comprise a Waypoint Location, wherein the Waypoint Location comprises an arresting cable; a Ground Control Station, wherein the Ground Control Station comprises a charging cable; and an aerial vehicle, wherein the aerial vehicle comprises an onboard battery, a capturing hook and a sensor payload for generating surveillance data. The aerial vehicle may be configured to autonomously travel between the Waypoint Location and the Ground Control Station. The aerial vehicle may be configured to couple with the arresting cable via the capturing hook. The aerial vehicle may be configured to electronically couple with the charging cable via the capturing hook to facilitate charging the aerial vehicle's onboard battery. | 05-19-2016 |
| 20160144980 | CAPTURE DEVICES FOR UNMANNED AERIAL VEHICLES, INCLUDING TRACK-BORNE CAPTURE LINES, AND ASSOCIATED SYSTEMS AND METHODS - Capture devices for unmanned aerial vehicles, including track borne capture lines, and associated systems and methods are disclosed. A representative system includes at least one support having an upright portion and at least one boom portion, a carriage track carried by the at least one boom portion, and a carriage carried by, and movable along, the carriage track. The system can further include a capture line carried by and extending downwardly from the at least one boom portion, or the carriage, or both the at least one boom portion and the carriage. | 05-26-2016 |
| 20160251088 | UNMANNED AIR VEHICLE RECOVERY SYSTEM | 09-01-2016 |
| 20220135259 | ROCKET LANDING SYSTEMS - A rocket landing stabilization system can include one or more upright support structures such as posts, columns, or walls, from which one or more stabilizing elements can be supported. The stabilizing elements can be used to stabilize a rocket as it lands at a landing site. The rocket landing stabilization system can also include a cradle, funnel, or cone to catch or otherwise support a rocket as it lands at the landing site. The rocket landing stabilization system can be located on land or at sea. | 05-05-2022 |
| 20100102167 | LANDING WHEEL GEAR - A Separate and mobile landing gear which substitutes the existing fixed landing gear in aircrafts. This innovated landing gear locks on the landing aircraft in the manner described in the detailed description. | 04-29-2010 |
| 20130068886 | PLATFORM FOR THE LANDING OF AN AIRCRAFT ON AN ACCESS FACILITY - A platform ( | 03-21-2013 |
| 20130099054 | ACTIVE PLATFORM FOR THE LANDING OF AN AIRCRAFT ON AN ACCESS FACILITY - An active platform ( | 04-25-2013 |
| 20130134260 | REDUCED DIMENSIONS PLATFORM FOR THE LANDING OF AN AIRCRAFT ON AN ACCESS FACILITY - A reduced dimensions platform ( | 05-30-2013 |
| 20140124621 | INTELLIGENT SELF-LEVELING DOCKING SYSTEM - A docking system for an unmanned aerial vehicle (UAV) is described that provides a stable landing and take-off area as well as, in some embodiments, refueling and/or data transfer capabilities. The docking system may be portable to provide a ready docking area for a UAV in areas that may not otherwise be suitable for UAV operation. The docking system may include a landing surface, an orientation mechanism that adjusts the landing surface to provide a level landing area, and an alignment mechanism coupled with the landing surface that moves a UAV resting on the landing surface to a predetermined location on the landing surface for automated refueling of the UAV. A latching mechanism may secure the UAV to the landing surface when the UAV is located at the predetermined location. | 05-08-2014 |
| 20140284423 | METHOD FOR LANDING AN AIRSHIP ON A LANDING DEVICE PLACED ON THE GROUND - A method for landing an airship on a landing device placed on the ground by: aligning, in particular horizontally aligning, the airship relative to the landing device with the aid of driving mechanisms arranged on the airship; lowering the airship onto a landing platform element of the landing device; arresting the airship on the landing platform element, wherein at least one electric magnet arranged in the landing device magnetically pulls the airship towards the landing device; and fastening the airship to the ground. | 09-25-2014 |
| 20140319272 | DEVICE AND METHOD FOR USE WITH UNMANNED AERIAL VEHICLES - An autonomous battery replacement station for an unmanned aerial vehicle (UAV) is provided. The UAV includes a replaceable battery. The station includes (a) a landing platform configured to receive the UAV, (b) a storage location configured to store a replacement battery for the UAV, and (c) a means for swapping the replaceable battery on the UAV with a replacement battery from the storage location. | 10-30-2014 |
| 20160159442 | PLATFORM FOR THE LANDING OF AN AIRCRAFT ON A BOAT - A platform ( | 06-09-2016 |
| 20160159496 | Drone Docking Station and Delivery System - Disclosed herein is a system and device for a drone docking station for deposit of items delivered by drone. Items may include food items, groceries, parcels and others. A secure porch, roof, window or otherwise building mounted box may be secured through to an existing edifice or may be configured to mount to an existing mailbox post or actually take the place of the mailbox. The basic elements making up the components of the box enable it to carry out efficient and secure delivery of goods to a container box located at a specific address, and to securely hold those goods until they are picked up; regardless of duration, weather, or otherwise. The drone dock may employ different technological devices to provide for communication between the drone dock and a drone, to provide for security and for the preservation of the delivered goods before during and after delivery. | 06-09-2016 |
| 20180022477 | SUPPORT EQUIPMENT FOR COLLECTING REUSABLE ROCKET | 01-25-2018 |
| 20090294584 | Stabilized UAV recovery system - A stabilized UAV recovery system is disclosed. In the illustrative embodiment for UAV recovery over water, the system includes ship-based elements and UAV-based elements. The ship-based elements include a robot arm that holds a capture mechanism over the side of the ship while compensating for wave-induced ship motion. The UAV-based elements include a hook mounted to the top of the UAV fuselage. With the capture mechanism held stable from the perspective of a UAV approaching from behind or in front of the mechanism, the UAV is flown under it, snagging an arresting line with the hook. With continued forward motion of the UAV, the arresting line pulls out of a winch drum that is coupled to a brake, bringing the UAV to rest. | 12-03-2009 |
| 20100025528 | SYSTEMS AND METHODS FOR CAPTURING AND CONTROLLING POST-RECOVERY MOTION OF UNMANNED AIRCRAFT - Systems and methods for capturing and controlling post-recovery motion of an unmanned aircraft are disclosed herein. An aircraft system in accordance with one embodiment of the invention, for example, can include a line capture assembly carried by an unmanned aircraft having a fuselage and a lifting surface. The line capture assembly can include a flexible support line having a first portion attached to an attachment point on the fuselage and a second portion extending from the attachment point spanwise along the lifting surface of the aircraft. The line capture assembly can also include an engagement device coupled to the second portion of the support line. The engagement device is releasably secured to the lifting surface. | 02-04-2010 |
| 20100181424 | CATCH AND SNARE SYSTEM FOR AN UNMANNED AERIAL VEHICLE - 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. | 07-22-2010 |
| 20110024559 | METHOD AND APPARATUS FOR AUTOMATED LAUNCH, RETRIEVAL, AND SERVICING OF A HOVERING AIRCRAFT - An aircraft capable of thrust-borne flight can be automatically retrieved, serviced, and launched using equipment suitable for use on a small vessel, or a base with similarly limited space or irregular motion. For retrieval, the aircraft drops a weighted cable, and pulls it at low relative speed into a broad aperture of a base apparatus. Continued translation of the aircraft may pull the cable clear of the apparatus, in which case it can continue in free flight and return for another retrieval attempt. Alternatively, the cable will be dragged along guiding surfaces of the apparatus into and through a slot or similar channel, until its free end is captured. The aircraft, having thus become anchored to the base station, is then pulled down by the cable into a receptacle. Guiding surfaces of the receptacle adjust the position and orientation of a probe on the aircraft, while directing the probe to mate with a docking fixture. Once mated to the fixture, the cable can be released and stored aboard the aircraft; the aircraft can be automatically shut down; and fueling or other servicing can be completed through appropriate connectors in the docking fixture. The aircraft can remain docked as needed, and when desired, be automatically started and tested in preparation for launch. It can then be released into free flight. A full ground-handling cycle can thus accomplished with simple and economical apparatus. It can be used with low risk of damage, and only moderate piloting accuracy. | 02-03-2011 |
| 20110127378 | LAUNCH AND RECOVERY SYSTEM FOR UNMANNED AERIAL VEHICLES - A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) ( | 06-02-2011 |
| 20110233329 | METHOD AND APPARATUS FOR AUTOMATED LAUNCH, RETRIEVAL, AND SERVICING OF A HOVERING AIRCRAFT - An aircraft capable of thrust-borne flight can be automatically retrieved, serviced, and launched using equipment suitable for use on a small vessel, or at a base with similarly limited space or irregular motion. For retrieval, the aircraft drops a tether, and pulls the tether at low relative speed into contact with a horizontal guide. The tether is pulled across the guide until the guide is captured by a hook or other end effector. The tether length is then adjusted as necessary, and the aircraft swings on the guide to hang in an inverted position. Translation of the tether along the guide then brings the aircraft to a docking carriage, in which the aircraft parks for servicing. For launch the carriage is swung upright, the end effector is released from the guide, and the aircraft thrusts into free flight. A full ground-handling cycle can thus be accomplished automatically with simple and economical apparatus. It can be used with low risk of damage, and requires only moderate accuracy in manual or automatic flight control. | 09-29-2011 |
| 20120223182 | SYSTEMS AND METHODS FOR RECOVERING AND CONTROLLING POST-RECOVERY MOTION OF UNMANNED AIRCRAFT - Systems and methods for recovering unmanned aircraft and controlling post-recovery motion of the aircraft are disclosed herein. An aircraft recovery system for handling an unmanned aircraft in accordance with one embodiment of the disclosure includes a base portion and an elongated aircraft capture member having a first end movably coupled to the base portion and a second, free end opposite the first end. The aircraft capture member includes a first portion and a second portion at a distal end of the first portion and positioned to intercept an unmanned aircraft in flight. The first and/or second portions are generally flexible. The system further includes an energy capture and dissipation assembly operably coupled to the aircraft capture member and positioned to receive at least a portion of the landing forces from the aircraft. | 09-06-2012 |
| 20120273612 | 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. | 11-01-2012 |
| 20130161447 | METHOD AND APPARATUS FOR AUTOMATED LAUNCH, RETRIEVAL, AND SERVICING OF A HOVERING AIRCRAFT - An aircraft capable of thrust-borne flight can be automatically retrieved, serviced, and launched using equipment suitable for a small vessel. For retrieval, the aircraft hovers over a base apparatus having one or more rails which bound a space into which the aircraft can safely descend. When the aircraft's measured position and velocity are appropriate, the aircraft descends promptly such that a spanwise component on the aircraft engages the rails. The teeth restrain the aircraft in position and orientation, while the rails bring the aircraft to rest. Articulation of the rails is used to park the aircraft in a servicing station. Connections for refueling, recharging, and/or functional checks are made in preparation for launch. Launch is effected by removing connections and restraints and articulating the rails to put the aircraft in an appropriate position and orientation. The aircraft uses its own thrust to climb out of the apparatus into free flight. | 06-27-2013 |
| 20130299634 | AERODYNAMICALLY CONTROLLED GRAPPLE ASSEMBLY - A grapple assembly suspended as an external load from an associated flying vehicle includes a frame member secured to an associated load line suspended from the associated vehicle. The frame member includes a first section, a second section, and a hinge joint connecting the first section to the second section. A grapple mechanism is mounted to the frame member second section. If desired, an aerodynamic body can be mounted to the frame member so as to encase at least a portion of the frame member. A release mechanism can be provided for jettisoning at least a portion of the aerodynamic body. The release mechanism can be triggered by an operator who can be stationed in the flying vehicle. | 11-14-2013 |
| 20130320138 | LINE CAPTURE DEVICES FOR UNMANNED AIRCRAFT, AND ASSOCIATED SYSTEMS AND METHODS - Line capture devices for unmanned aircraft, and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes a line capture device body having a line slot with an open end and a closed end. A retainer is positioned proximate to the line slot and has a rotor with a plurality of rotor arms positioned to extend at least partially across the line slot as the rotor rotates relative to the body. A joint rotatably couples the rotor to the body, and a ratchet device is operably coupled to the rotor to allow the rotor to rotate in a first direction and at least restrict the rotor arm from rotating in a second direction opposite the first. In other embodiments, the retainer can include other arrangements, for example, one or more wire-shaped elements. | 12-05-2013 |
| 20140008490 | AERIAL RECOVERY OF SMALL AND MICRO AIR VEHICLES - A method, apparatus, system, and computer system to facilitate aerial recovery of an air vehicle are disclosed. In various embodiments, a drogue is established in a drogue recovery orbit and an air vehicle is recovered with the drogue. Establishment of the drogue in a drogue recovery orbit may include establishment of a mothership in a mothership recovery orbit or actuating control surfaces on the drogue. Recovering the air vehicle may include maneuvering the drogue and the air vehicle in a cooperative manner to facilitate recovery of the air vehicle or utilizing a homing device on the drogue to guide the air vehicle. The various techniques disclosed may be modified to compensate for wind. | 01-09-2014 |
| 20140054415 | METHOD AND APPARATUS FOR AUTOMATED LAUNCH, RETRIEVAL, AND SERVICING OF A HOVERING AIRCRAFT - An aircraft capable of thrust-borne flight can be automatically retrieved, serviced, and launched. In one embodiment, for retrieval, the aircraft drops a tether and pulls the tether at low relative speed into contact with a horizontal guide. The tether is pulled across the guide until the guide is captured b an end effector. The tether length is adjusted as necessary, and the aircraft swings on the guide to hang in an inverted position. Translation of the tether along the guide then brings the aircraft to a docking carriage, in which the aircraft parks for servicing. For launch, the carriage is swung upright, the end effector is released from the guide, and the aircraft thrusts into free flight. A full ground-handling cycle can thus be accomplished automatically with a simple, economical apparatus. It can be used with low risk of damage and requires moderate accuracy in manual or automatic flight control. | 02-27-2014 |
| 20140091176 | 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. | 04-03-2014 |
| 20140091177 | 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. | 04-03-2014 |
| 20140203140 | 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. | 07-24-2014 |
| 20140203141 | 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. | 07-24-2014 |
| 20150307209 | LINE CAPTURE DEVICES FOR UNMANNED AIRCRAFT, AND ASSOCIATED SYSTEMS AND METHODS - Line capture devices for unmanned aircraft, and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes a line capture device body having a line slot with an open end and a closed end. A retainer is positioned proximate to the line slot and has a rotor with a plurality of rotor arms positioned to extend at least partially across the line slot as the rotor rotates relative to the body. A joint rotatably couples the rotor to the body, and a ratchet device is operably coupled to the rotor to allow the rotor to rotate in a first direction and at least restrict the rotor arm from rotating in a second direction opposite the first. In other embodiments, the retainer can include other arrangements, for example, one or more wire-shaped elements. | 10-29-2015 |
| 20150329218 | LAUNCH AND RECOVERY SYSTEM FOR UNMANNED AERIAL VEHICLES - A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) ( | 11-19-2015 |
| 20160376029 | SMALL UNMANNED AIR VEHICLE REPULSING APPARATUS - Disclosed herein is a small unmanned air vehicle repulsing apparatus including a capturing body adapted to capture a drone, a target to be captured; and a capturing body launching apparatus adapted to launch the capturing body at the drone, in which the capturing body launching apparatus can quickly capture the drone by launching the capturing body even if the suspicious drone flies into an area to be protected so as to protect the interest and safety of law-abiding people. | 12-29-2016 |
| 20090121078 | AIRCRAFT POD AND AIRCRAFT EQUIPPED WITH AT LEAST ONE SUCH POD - A pod for an aircraft including a cowling, an engine housed in the inner volume of the cowling, an annular channel circulating a secondary thrust flow arranged between the engine and the cowling, and at least one thrust reverser for forming a reverse flow from the secondary thrust flow circulating in the annular channel. The thrust reverser including a plurality of doors provided in the rear part of the cowling, so as to form a trailing edge of the cowling. The thrust reverser can include means for actuating the doors such that at lease one actuating means actuates two adjacent doors and at least one door is actuated by two actuating means. | 05-14-2009 |
| 20090127390 | Thrust Reverser for a Turbofan Gas Turbine Engine - The thrust reverser includes, in one aspect, an interior flow deflector which defines a portion of a substantially continuous and uninterrupted nozzle interior surface with the interior of a jet pipe when the door is in a stowed position, thereby reducing aerodynamic losses and improving efficiency. In another aspect, improved sealing arrangement between the jet pipe and the door provides increased performance when the doors are stowed. | 05-21-2009 |
| 20090127391 | Pivoting Fairings for a Thrust Reverser - The thrust reverser is used with a gas turbine engine and includes first and second doors pivotable between a stowed position and a deployed position. When deployed, pivoting fairings on the first door are moved so as to give room to the second door as its trailing edge moves within the first door. When stowed, the second door preferably provides the locking mechanism to the pivoting fairings of the first door. | 05-21-2009 |
| 20090314887 | THRUST REVERSER CASCADE ASSEMBLY AND AFT CASCADE RING WITH FLOW DEFLECTOR PORTION - An aircraft engine thrust reverser cascade assembly includes a plurality of circumferentially spaced cascade segments, each cascade segment including a plurality of spaced vanes including an aft-most vane, and an aft end. The cascade assembly also includes an aft cascade ring removably attached to the aft ends of the cascade segments. The aft cascade ring includes a deflector portion that at least partially extends forward of the aft ends of the cascade segments. The deflector portion is configured to at least partially redirect at least a portion of a volume of air as the air outwardly passes between the aft-most vanes and the aft ends of the cascade segments. | 12-24-2009 |
| 20090321561 | NACELLE FOR AIRCRAFT COMPRISING MEANS OF REVERSING THRUST AND AIRCRAFT COMPRISING AT LEAST ONE SUCH NACELLE - Aircraft nacelle comprising a cowling and an engine, the cowling comprising a fixed portion and a mobile portion able to slide in order to define a radial opening with the mobile portion, a thrust reverser system comprising a plurality of flaps intended to be deployed in order to seal at least partially an annular channel surrounding the engine, the mobile portion of the cowling comprising an annular housing extending longitudinally in order to receive the flaps in rest position. Each flap is linked to the fixed portion by a pivot joint and is linked to the mobile portion by a sliding-pivot joint, in such a way that a sliding of the mobile portion in separating from the fixed portion provokes a rotation of each flap around the axis of rotation of the joint with the fixed portion. | 12-31-2009 |
| 20100193632 | INTEGRAL COMPOSITE SLIDER FOR AIRCRAFTS - A slider apparatus integral with a slidable member and a method for integrating the slider apparatus with the slidable member. The slider apparatus integrated with the slidable member may be configured to slidably couple with and be structurally supported by a fixed structure. The slider apparatus may comprise a primary slider component made of composite material and at least one chamfered element bonded to the primary slider component. The slidable member may comprise the slider apparatus, a core assembly, a plurality of composite material plies wrapped around the slider apparatus and core assembly and cured therewith, and at least one low-friction slider shoe removably attached to the primary slider component outward of the plurality of composite material plies. | 08-05-2010 |
| 20100270428 | THRUST REVERSER ASSEMBLY WITH SHAPED DRAG LINKS - A thrust reverser blocker door assembly for use in turbofan engines includes an engine nacelle with an aft translating cowl that is movable from a stowed position to a deployed position. An engine case is disposed within the engine nacelle forming an airflow duct therebetween. A gap is uncovered when the translating cowl is moved into the deployed position, and a cascade vane set is positioned in the gap. A blocker door covers the cascade vane set while in the stowed position and blocks a portion of the airflow duct while in the deployed position. A geometrically shaped drag link is pivotally connected to the engine case at a first end and connected to the blocker door at a second end. While in the deployed position, the shape of the drag link provides clearance from the engine case. | 10-28-2010 |
| 20110101158 | Thrust Reversers Including Monolithic Components - Aircraft systems including thrust reversers with monolithic components are described herein. An aircraft system in accordance with one embodiment includes a thrust reverser having a fan duct inner wall section, a fan duct outer wall section radially outward of the fan duct inner wall section, and a connecting wall section extending between the fan duct inner wall section and the fan duct outer wall section. The fan duct inner wall section, the fan duct outer wall section, and the connecting wall section form a monolithic member. | 05-05-2011 |
| 20110101159 | NESTED FAIRING THRUST REVERSER - A thrust reverser nozzle for a gas turbine engine nacelle includes opposite and asymmetrically pivoting first and second doors defining a nacelle aft section, first and second trailing edges of the first and second doors adjacent to a propulsive jet nozzle outlet of the nacelle, the doors being pivotable simultaneously between a stowed position and a deployed position such that the first trailing edge is positioned behind the second trailing edge when the doors are in the deployed position, and the first and second fairings attached to the first and second doors in relative fixed positions to the first and second doors respectively. Male contour middle portions of the first fairings may complementarily match female contour middle portions of the second fairings and are received within the female contour middle portion when the doors are in the stowed position. The fairings may be removably attached to the doors. | 05-05-2011 |
| 20110108665 | METHOD AND DEVICE FOR IMPLEMENTING THE THRUST REVERSERS OF AN AIRCRAFT - Method and device for implementing the thrust reversers of an aircraft. According to the invention, the following successive steps are carried out automatically: deployment (E | 05-12-2011 |
| 20120256051 | STUB FRAME FOR A CASCADE THRUST REVERSER STRUCTURE - The invention relates to a stub frame ( | 10-11-2012 |
| 20130009004 | INTERNAL GAS TURBINE PROPULSION THRUST REVERSER - A thrust reverser for a gas turbine engine includes a hinge, a propulsion system duct, and a kicker blocker. Bypass air and gas path air travel through the propulsion system duct and the propulsion system duct has an intake inlet and an exhaust outlet. The kicker blocker has a kicker portion and a blocker portion. The kicker blocker is rotatably attached to the hinge and is movable between a stowed position and a deployed position. The blocker portion extends into the propulsion system duct when the kicker blocker is in the deployed position to block bypass air and gas path air traveling through the propulsion system duct in a first direction prior to the exhaust outlet, thereby redirecting the bypass air and the gas path air in a second direction. | 01-10-2013 |
| 20130009005 | REVERSE THRUST DEVICE - The invention relates to a reverse thrust device including a stationary upstream structure including a front frame ( | 01-10-2013 |
| 20130146708 | CASE ASSEMBLIES WITH COMMON CONTROLS - A case assembly for an aircraft is provided. The assembly includes a thrust reverser actuation system (TRAS) configured to provide braking assistance to the aircraft; a variable area fan nozzle (VAFN) system configured to adjust an engine exhaust of the aircraft; and a common control group coupled to the TRAS and the VAFN system for controlling operation of the TRAS and the VAFN system. | 06-13-2013 |
| 20130206902 | POWER SUPPLY CIRCUIT FOR AN AIRCRAFT DE-ICING SYSTEM - An aircraft electrical supply circuit including: a power distribution network, onboard the aircraft, for electrical devices located in an engine of the aircraft or near the engine; and a power supply generator built into the engine of the aircraft to supply AC voltage power to a deicing or anti-icing system. The power supply generator is connected to a thrust reverser electromechanical actuator by a rectifier for supplying DC voltage power to the actuator. | 08-15-2013 |
| 20140131515 | AIRCRAFT TURBOJET ENGINE THRUST REVERSER WITH A REDUCED NUMBER OF LATCHES - A thrust reverser with grids includes a jet engine pylon, a one piece cowl either directly or indirectly slidably mounted on the jet engine pylon between a direct jet position and a reverse jet position, and a system for locking this cowl on a beam. The system has a single tertiary lock, which is positioned on one side of the jet engine pylon being capable of locking a corresponding upper edge of the cowl. In addition, the tertiary lock includes a locker to lock the cowl, a blocker for blocking the locker, and a position detector in order to detect the position of the locker. The system further includes another detector to detect proper closing of the other upper edge of the cowl. | 05-15-2014 |
| 20140252167 | REVERSE CORE ENGINE THRUST REVERSER FOR UNDER WING - A gas turbine engine for mounting under a wing of an aircraft has a propulsor that rotates on a first axis, and an engine core including a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section. The engine core is aerodynamically connected to the propulsor and has a second axis. A nacelle is positioned around the propulsor and engine core. The nacelle is attached to the wing of the aircraft. A downstream end of the nacelle has at least one pivoting door with an actuation mechanism to pivot the door between a stowed position and a horizontal deployed position in which the door inhibits a flow to provide a thrust reverse of the flow. | 09-11-2014 |
| 20150291289 | ASYMMETRIC THRUST REVERSERS - An aircraft includes a propulsion supported within an aft portion of a fuselage A thrust reverser is mounted in the aft portion of the fuselage proximate the propulsion system for directing thrust in a direction to slow the aircraft. The thrust reverser includes an upper blocker door movable about a first pivot axis to a deployed position and a lower blocker door movable about a second pivot axis not parallel to the first pivot axis. | 10-15-2015 |
| 20150298814 | CLOCKED THRUST REVERSERS - An aircraft includes a fuselage including a propulsion system supported within an aft portion. A thrust reverser is mounted proximate to the propulsion system for directing thrust in a direction to slow the aircraft. The thrust reverser directs thrust at an angle relative to a vertical plane to reduce interference on control surfaces and reduce generation of underbody lift. | 10-22-2015 |
