| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244002000 | COMPOSITE AIRCRAFT | 52 |
| 20110192931 | AIRCRAFT SYSTEM THAT ENABLES GROUND TRAVELING - Disclosed is a flying object system performing ground traveling, which travels on the ground and flies in the air. The flying object system travels with three or more wheels connected to a main body, generates flying force through wings symmetrically installed at both sides of the main body, and is provided with plural propellers, operated by a control lever and installed on the wings and at least a part of the main body, each of the wings being divided into a plurality of compartments to be folded or be changed in shape by pressure of gas or air. Therefore, the flying object system travels on a road on the ground and takes off and flies in the air in traffic congestion, and flies in the air and lands and travels on a road on the ground if necessary, thus rapidly moving to a destination without the effects of traffic congestion. | 08-11-2011 |
| 20130037650 | Systems and Methods for Long Endurance Airship Operations - In one example, a long endurance airship system includes a payload airship and a first logistics airship mechanically joined to the payload airship to form a first combined airship, the payload airship and the logistics airship having design capabilities differing by at least a factor of two with regard to at least one of: power generation capability, propulsion capability, endurance capability, and lift capability, in which the first combined airship is free flying, lighter-than-air, and configured to maintain aloft for greater than 30 days without physical connection to the ground. Illustrative methods for long endurance airship operations are also provided. | 02-14-2013 |
| 20090302149 | COMPOSITE AIR VEHICLE HAVING A HEAVIER-THAN-AIR VEHICLE TETHERED TO A LIGHTER-THAN-AIR VEHICLE - A system including a heavier-than-air vehicle (HTA), a lighter-than-air vehicle (LTA), and a tether is disclosed. The tether is coupled between the HTA and the LTA such that the LTA supports the HTA. The system may be further configured to suit the needs of the particular application. For example, the system may be configured to be controllable from a remote location or capable of autonomous operations. The system may also be configured such that the HTA comprises a mission payload and communications equipment. In an exemplary embodiment of the invention, the LTA is configured to provide lift for the system and the HTA is configured to provide station-keeping propulsion, the advantage being reduced fuel consumption and increased mission endurance. | 12-10-2009 |
| 20100044494 | Space launcher - A space vehicle and its launcher are capable of low-cost launch, safe maneuvering, plus powered go-around for landing. | 02-25-2010 |
| 20130112804 | Multi-Modal Vehicle - A multi-modal vehicle (“MMV”) | 05-09-2013 |
| 20130068876 | Flying Vehicle - A vehicle has a roadable configuration similar to an automobile in which multiple rotors are stowed within the vehicle, and a flying configuration in which the rotors are deployed from the vehicle, allowing it to fly like a VTOL/STOL aircraft or a helicopter. | 03-21-2013 |
| 20100294877 | VTOL lifting body flying automobile - This apparatus is a new VTOL roadable aircraft having fore and aft sections joined by a seating midsection; with compact inlets built into its fuselage, also pairs of flight stabilizing surfaces and tail fins; the fuselage structure being a Lifting Body that provides aerodynamic lift during both forward flight and vertical descent; provided with intake chambers containing propelling surfaces rotating on longitudinal axis in opposite senses, and external pairs of swiveled nozzles producing thrust vectoring; these nozzles using conventional devices and having spins directed by original controls of corresponding identical movement directions; with standard automobile equipment integrated with the vehicle compact design and dimensions, making it compatible for road transport and enabling direct transitions to flight mode; and safe landing systems for emergencies are provided with half the technology being off the shelf devices as those in use by NASA and the US Airforce. | 11-25-2010 |
| 20080296428 | Air Freight Transport Method, Transport Aeroplane and Air Freight Transport System - An air cargo transportation method, a transport plane and an air cargo transport system. In the air cargo transportation method for the transport of various cargoes to different destinations, a transport plane is provided first that flies through at least three air regions respectively associated to a station. The transport plane does not land at one of the stations. Instead, the cargo is transported between the transport plane and one of the stations by an airworthy feeders, the cargo being transferred between the feeder and the transport plane while in the air. The transport plane and two feeders form the air cargo transport system, wherein the transport plane may comprise two interconnected feeders. With the air cargo transportation method, the utilization of the transport plane is enhanced. Further, the transport ways for individual cargo items can be shortened so that the efficiency is improved. | 12-04-2008 |
| 20120025006 | IN-LINE STAGED HORIZONTAL TAKEOFF AND LANDING SPACE PLANE - A vehicle includes a first sub-vehicle, and a second sub-vehicle which is repeatably moveable between coupled and uncoupled conditions with the first sub-vehicle. The first and second sub-vehicles each include a landing system and propulsion system. The first and second sub-vehicles are in the coupled condition during take-off. The first and second sub-vehicles are separately flyable in the uncoupled condition. Both vehicles are launched horizontally, by a ramp, or vertically, using atmospheric lift to achieve atmospheric flight, orbital, or sub-orbital launch. | 02-02-2012 |
| 20080308669 | COMPOSITE AIRCRAFT COMPONENT - This invention relates to improving the tolerance of composite laminate structures to damage and/or delamination, resulting in weakening of the structure and/or to reducing the possibility of such damage and/or delamination. In particular, but not exclusively the invention relates to protecting the end surfaces of composite laminate structures present on aircraft from impact damage. The invention provides an aircraft component comprising a composite laminate structure, the composite laminate structure including an end surface at which a multiplicity of the layers of the laminate structure terminate, wherein the aircraft component further comprises a deformable strip mounted to protect the end surface of the composite laminate structure from direct impacts. | 12-18-2008 |
| 20090121071 | FLYING WING BOAT - A flying wing boat is provided, which comprising a fuselage provided with a cockpit at a bow thereof; a pair of main wings, each of which being pivotably connected to one side of the fuselage respectively and being provided with a flap; a pair of pontoons, each of which being provided at a tip of each main wings; at least one propeller provided at a fore part of the fuselage; and a driving system supplying power to the at least one propeller. The flying wing boat of the present invention could improve the safety and comfortabilty of navigation. | 05-14-2009 |
| 20100096490 | Remote engine/electric helicopter industrial plat form - The invention is an unmanned flying helicopter aircraft platform (“aircraft platform”) that can be powered by either interchangeable electric motors or by fuel powered internal combustion engines. The aircraft platform is surrounded by a lightweight exoskeleton cage that protects the rotor blades from coming into contact with external objects. The aircraft platform uses a weight located on the bottom side of the aircraft platform that can be remotely moved to adjust the center of gravity in order to navigate in any direction. The aircraft platform has a place on its bottom side where attachments can be added or removed which allows the aircraft platform to be used for multiple different purposes. The aircraft platform can be flown and operated either remotely using a hand held control unit or it can be flown and operated by an onboard pilot located in the human carrying attachment. | 04-22-2010 |
| 20100025523 | RECONFIGURABLE AIRCRAFT AND ASSOCIATED METHODS - A reconfigurable aircraft and associated methods. In one embodiment the reconfigurable aircraft comprises a plurality of payload retainers. The payload retainers are configured to receive and retain payloads, including fuel, armaments and sensors. The aircraft is configured to cooperate in flight with an airborne supply vehicle to receive the payloads from the supply vehicle. | 02-04-2010 |
| 20110139923 | Miniature Robotic Vehicle with Ground and Flight Capability - Miniature robotic vehicles suitable for a variety of tasks including covert surveillance, reconnaissance, and recreation are provided. Embodiments of the invention may include vehicles having a hybrid transportation system that incorporates a rotary-wing flight mode in conjunction with a wheeled ground transport mode. As a result, exemplary vehicles provide efficient ground-mode travel, with the added ability to fly over large obstacles and rough terrain. | 06-16-2011 |
| 20090294573 | Dual-Use Modular Propulsion surveillance Vehicle with Detachable Unmanned Airborne Vehicles - The present invention provides a system for reconnaissance using autonomous unmanned airborne vehicles (UAV). The system comprises a mothership, which is generally a fixed wing fuel tank capable of providing a suitable surface for flight (lift) and one or more elements for attachment of individual UAVs. The system further comprises one or more UAVs that are detachably connected to the mothership, and which are independently controllable for reconnaissance and tracking. The system and its individual parts are reusable and independently controllable, permitting low cost reconnaissance over wide areas of geography. | 12-03-2009 |
| 20090283626 | METHODS AND APPARATUS FOR AERIAL RECOVERY OF FLYING APPARATUS - Methods and systems are provided which may allow a first vehicle to recover a second air vehicle while both are moving. The first vehicle and the second air vehicle may be traveling at different velocities. An attachment member of the second air vehicle may attach to a recovery member of the first vehicle while the first vehicle and the second air vehicle are traveling at different velocities. The recovery member attached to the second air vehicle may move relative to and along an exterior surface of the first vehicle in a direction substantially parallel to a direction of travel of the first vehicle. | 11-19-2009 |
| 20110198434 | Aero-assisted pre-stage for ballistic rockets and aero-assisted flight vehicles - An aero-assisted pre-stage ( | 08-18-2011 |
| 20120292430 | DEVICE FOR LAUNCHING AND RECOVERING A DRONE, AND AN ASSOCIATED AIRCRAFT | 11-22-2012 |
| 20120292429 | Discoidal Seaplane - A flying vehicle, comprising a discoidal secondary wing and two airfoil primary wings. The airfoil primary wings provide out-of-surface-effect lift that acts as the main lift force for the vehicle. The discoidal secondary wing provides lift via the surface effect, stabilizes the vehicle, provides a mounting surface for solar panels, and acts as a pontoon for water landings. The vehicle can also include a retractable toroidal or round balloon to provide additional lift. The vehicle is fully scalable, from children's toys to passenger vehicles. | 11-22-2012 |
| 20080283659 | Buoyancy launch vehicle - A launching vehicle that is lighter than air and capable of lifting a space bound payload to the upper atmosphere, reducing the energy required for spaceflight. Several possible configurations include but are not limited to. First, a single conventional balloon comparable to a large weather balloon for small payload or low orbit launches. Second, a layered configuration of several balloons stacked one on top of another increasing payload capacity. Third, a grouped configuration utilizing a structure lifted with the payload to accommodate more balloons and provide a stable structure from which to launch. Fourth a ring or doughnut shaped balloon could be used to carry the payload allowing fully vertical launch. Fifth, the ring shaped balloons could be stacked vertically and or grouped concentrically to allow for large payloads. Sixth, one or more umbilical attachments could be attached to the spacecraft allowing it to siphon the lifting gas for fuel when optimal balloon altitude assuming a fuel capable gas is utilized in the balloon. | 11-20-2008 |
| 20090179106 | Non-powered, aero-assisted pre-stage for ballistic rockets and aero-assisted flight vehicles - A non-powered pre-stage ( | 07-16-2009 |
| 20100200689 | AIRCRAFT WITH A PRESSURIZED VESSEL - An aircraft comprising a fuselage, a vessel associated with the fuselage, a propulsion system associated with the fuselage, and a lift system. The vessel is capable of storing a pressurized gas compressed to a density that allows the aircraft to operate under water. The lift system is capable of providing the aircraft lift to fly in air. | 08-12-2010 |
| 20110000999 | Foldable swan-wings aircraft - An aircraft structure is provide, an aircraft structure for an aircraft. Including front wings And rear wings of the Swan-Wings, vertical winglets and the first level floor body. The Fuselage has a cross-section of substantially flat fuselage shape being is wide enough to Provide lifting force. The front wings of the Swan-Wings are disposed horizontally in Front portion of the fuselage. The rear wings of the Swan-Wings are disposed Horizontally in rear portion of the fuselage. | 01-06-2011 |
| 20100065676 | Balloon kite - To fly kite requires wind and skill. Balloon kite can fly high with no wind. To fly balloon kite requires no skill. You do not have to be an expert to fly balloon kite. In a year only windy season is suitable for flying kite. With balloon kite every day is a flying kite day and every child can fly it. Children can enjoy flying balloon kite all year round. | 03-18-2010 |
| 20110049288 | UNMANNED AIRCRAFT SYSTEM AND OPERATION METHOD THEREOF - An unmanned aircraft system includes a manned aircraft and an unmanned aircraft. The manned aircraft includes a manned aircraft main wing, a manned aircraft fuselage, a manned aircraft landing system, and a manned aircraft joining mechanism provided at a bottom portion of the manned aircraft fuselage. The unmanned aircraft includes an unmanned aircraft main wing, an unmanned aircraft fuselage, an unmanned aircraft landing system, and an unmanned aircraft joining mechanism provided at a roof portion of the unmanned aircraft fuselage. The manned aircraft joining mechanism and the unmanned aircraft joining mechanism are detachably joined. The unmanned aircraft system can take off or land in a state that the unmanned aircraft and the manned aircraft are joined. | 03-03-2011 |
| 20110042507 | Convertible Vehicle For Road, Air, and Water Usage - A convertible combined road, water, and aircraft vehicle has a road form, a water form, and an aircraft form. The vehicle includes a vehicle body having a passenger compartment and wheels supporting the vehicle body on the ground when in the road form. A wing assembly is attached to each side of the vehicle body. Each wing assembly includes a wing and at least one propelling device attached to the wing. The propelling devices may be jet engines, or ducted fans or in-wing propellers. A wing assembly rotating mechanism rotates the wing assembly 360 degrees when the vehicle is in the aircraft form so that thrust is provided in 360 degrees, allowing for vertical takeoff and landing and mid air hovering. A wing assembly positioning mechanism positions the wing assembly between an open-winged flying position and a folded or closed-winged non-flying position. A rear propelling assembly is provided to propel the vehicle in the air, and a tail assembly is provided which includes elements for maneuvering the vehicle in the air and water. The rear propelling assembly includes a rear propelling device and a propelling device positioning mechanism capable of positioning the rear propelling device through a range of at least 90 degrees between a position for providing the vehicle with vertical lift or thrust and a position for providing the vehicle with forward thrust. The rear propelling device may be a jet engine or a propeller. An operator's control unit is disposed in the passenger compartment with which an operator controls vehicle. | 02-24-2011 |
| 20090127376 | WING TIP DOCKING SYSTEM FOR AIRCRAFT - A system and method for docking various types of aircraft is disclosed. An aerodynamic lifting structure docking mechanism for docking two or more aircraft is provided comprising an aerodynamic lifting structure. The aerodynamic lifting structure includes a first and second airflow adjustment mechanism. The aerodynamic lifting structure further includes a first hard docking mechanism, and a second hard docking mechanism, and still further includes a soft docking mechanism. The first and second airflow adjustment mechanisms are configured to substantially remove any aerodynamic lifting structure vortices around each of the aerodynamic lifting structure tip areas. The soft docking mechanism is configured to soft dock a first aerodynamic lifting structure with a second aerodynamic lifting structure. The first hard docking mechanism is configured to hard dock with the second hard docking mechanism, thereby temporarily attaching the first aerodynamic lifting structure with the second aerodynamic lifting structure. | 05-21-2009 |
| 20080272226 | Ducted Fan Air Vehicle with Deployable Wings - A ducted fan air vehicle and method of operation is disclosed for obtaining aerodynamic lift and efficiency in forward flight operation without significantly impacting hover stability. One or more retractable wings are included on the ducted fan air vehicle and are deployed during forward flight to provide aerodynamic lift. The wing or wings are retracted when the vehicle hovers to reduce the impact the wings have on stability in a wind. Each wing may conform to the curvature or profile of the vehicle when retracted, and may be constructed in one or more wing sections. The wing or wings may be deployed and retracted automatically or at the command of an operator. Each wing and related components may be integrated into the vehicle or may be detachable. | 11-06-2008 |
| 20110163197 | FLIGHT UNIT THAT CAN BE COUPLED TO A ROAD VEHICLE HAVING SINGLE-FILE SEATING - A vehicle suitable as both a road vehicle and an aircraft, which includes two units that can be coupled to one another; a first unit embodies a road vehicle with least single-file seating, and a second unit is embodied as a flight unit. | 07-07-2011 |
| 20100193626 | TRANSFORMING UNMANNED AERIAL-TO-GROUND VEHICLE - A transforming unmanned aerial-to-ground vehicle assembly comprising: an aerodynamic flying assembly comprising an unmanned aerial vehicle integrated with an unmanned ground vehicle, a power unit shared by the unmanned aerial vehicle and the unmanned ground vehicle, vehicle controls shared by the unmanned aerial vehicle and the unmanned ground vehicle, a disengagement mechanism to separate the unmanned ground vehicle from the unmanned aerial vehicle, one or more manipulator arms located on either the unmanned aerial vehicle or the unmanned ground vehicle, and landing gear. | 08-05-2010 |
| 20100193625 | MODULAR ARTICULATED-WING AIRCRAFT - Systems and/or methods for forming a multiple-articulated flying system (skybase) having a high aspect ratio wing platform, operable to loiter over an area of interest at a high altitude are provided. In certain exemplary embodiments, autonomous modular flyers join together in a wingtip-to-wingtip manner. Such modular flyers may derive their power from insolation. The autonomous flyers may include sensors which operate individually, or collectively after a skybase is formed. The skybase preferably may be aggregated, disaggregated, and/or re-aggregated as called for by the prevailing conditions. Thus, it may be possible to provide a “forever-on-station” aircraft. | 08-05-2010 |
| 20120037748 | AIRSHIP - An airship system having a flexible envelope and at least one bladder positioned therein is described. The bladder(s) provide an impervious barrier between the gas within the bladder(s) and the air exterior to the bladder(s). The envelope includes longitudinal and hoops straps weaved together in a criss-cross manner. The envelope also includes rings positioned thereon that include truss members for receiving struts for removably coupling the airship to another airship. A tri-hull delta dirigible system is also described, comprising three airships coupled together using struts and arranged in an equilateral triangle formation. The tri-hull delta dirigible system has a similar lift capacity (volume) as a conventional large mono-hull dirigible, while minimizing the detrimental bending in the center of the conventional mono-hull dirigible. | 02-16-2012 |
| 20110315806 | Modular and morphable air vehicle - An unmanned air module includes one or more rotors, engines, a transmission and avionics. Any of several different ground modules may be attached to the air module. The air module may fly with and without the ground module attached. The ground module may be a vehicle ground module and may be manned. The vehicle ground module may transport the attached air module across the ground. The air module may have two rotors, which may be ducted fans, and three different configurations: a tandem rotor configuration, a side-by-side configuration, and a tilted-rotor configuration. | 12-29-2011 |
| 20120061506 | WING TIP DOCKING SYSTEM FOR AIRCRAFT - A system and method for docking various types of aircraft is disclosed. An aerodynamic lifting structure docking mechanism for docking two or more aircraft is provided comprising an aerodynamic lifting structure. The aerodynamic lifting structure includes a first and second airflow adjustment mechanism. The aerodynamic lifting structure further includes a first hard docking mechanism, and a second hard docking mechanism, and still further includes a soft docking mechanism. The first and second airflow adjustment mechanisms are configured to substantially remove any aerodynamic lifting structure vortices around each of the aerodynamic lifting structure tip areas. The soft docking mechanism is configured to soft dock a first aerodynamic lifting structure with a second aerodynamic lifting structure. The first hard docking mechanism is configured to hard dock with the second hard docking mechanism, thereby temporarily attaching the first aerodynamic lifting structure with the second aerodynamic lifting structure. | 03-15-2012 |
| 20120061505 | WING TIP DOCKING SYSTEM FOR AIRCRAFT - A system and method for docking various types of aircraft is disclosed. An aerodynamic lifting structure docking mechanism for docking two or more aircraft is provided comprising an aerodynamic lifting structure. The aerodynamic lifting structure includes a first and second airflow adjustment mechanism. The aerodynamic lifting structure further includes a first hard docking mechanism, and a second hard docking mechanism, and still further includes a soft docking mechanism. The first and second airflow adjustment mechanisms are configured to substantially remove any aerodynamic lifting structure vortices around each of the aerodynamic lifting structure tip areas. The soft docking mechanism is configured to soft dock a first aerodynamic lifting structure with a second aerodynamic lifting structure. The first hard docking mechanism is configured to hard dock with the second hard docking mechanism, thereby temporarily attaching the first aerodynamic lifting structure with the second aerodynamic lifting structure. | 03-15-2012 |
| 20090134268 | LIGHTER-THAN-AIR VERTICAL LOAD LIFTING SYSTEM - An aerial load lifting system features a non-rigid or blimp-type dirigible providing a lighter-than-air envelope that is placed within a structural shell. The system is designed so that the envelope provides essentially neutral buoyancy for the structure, leaving only the cargo weight to be lifted by the rotors. The structural shell supports the engine, fuel tank, rotors, and transmission system that power the lift and vectoring of the aircraft, in addition to supporting the cargo load. The structural shell transfers the weight of the load directly to the location of the rotors, thus avoiding stress on the envelope. | 05-28-2009 |
| 20120168555 | AUTONOMOUS STRATOSPHERIC LIGHTER-THAN-AIR AIRCRAFT AND METHOD FOR PROVIDING RADIO AND OPTICAL COMMUNICATION, TELEVISION BROADCASTING AND MONITORING - The invention relates to an autonomous stratospheric aircraft which is lighter than air, and to a method for providing radio and optical communication, television broadcasting and monitoring with the aid of communication equipment arranged on the aircraft. The present invention can be used for producing lighter-than-air aircraft as well as global and regional communication and television broadcasting and multi-aspect monitoring systems and networks. | 07-05-2012 |
| 20120211588 | Methods and Apparatus for Aerial Recovery of Flying Apparatus - Methods and systems are provided which may allow a first vehicle to recover a second air vehicle while both are moving. The first vehicle and the second air vehicle may be traveling at different velocities. An attachment member of the second air vehicle may attach to a recovery member of the first vehicle while the first vehicle and the second air vehicle are traveling at different velocities. The recovery member attached to the second air vehicle may move relative to and along an exterior surface of the first vehicle in a direction substantially parallel to a direction of travel of the first vehicle. | 08-23-2012 |
| 20100051739 | Method for controlling lifting force of an aerovane fan and a helicar - The invention discloses a new method for controlling lifting force of an aerovane fan and a helicar utilizing this method. The method directly controls airflow rate enter a duct (Collar, culvert pipe, in which has the aerovanes fans), using an airflow valve that can be opening or closed by a rotating operation, so to control lifting force. The airflow valve has double layer perforated the hemisphere hulls or hemi-ellipsoid hulls in shape. A simple and practical helicar is designed on the basis of this method. At the center part of the helicar, a duct (Collar) placed upright, in which double aerovane fans rotating in opposite directions with each other; some spouts and grid slices for adjusting airflow are arranged at bottom plate; setting the auxiliary wings that can be foldable and retractable on two sides; a double fins (and rudderpistons); a horizontal empennage (and a elevator); and some tail spouts are provided at the tail part of helicar; an engine is placed at the rear part of the helicar; a cab or passenger chamber are placed at fore of helicar; and furthermore, a series of operate mechanisms is included. The blades of the aerovane fans are fixed at an angle of attack connect with hub fixedly, strong as a whole, the aerovanes fans rotating at a high speed and has small diameter. Therefore, the structure of the helicar is simple and compact. After the wings be retracted and folded, the helicar width may be about 2 meters, which is suitable for driving on the road of ground or flying in the air. When an inflatable rubber gasbag is attached to the bottom plate underside, this helicar also may land on the surface of water and drive on it. | 03-04-2010 |
| 20120312911 | AIRSHIP LAUNCH FROM A CARGO AIRSHIP - A method for launch of an airship includes connecting a cargo airship to a deflated second airship, launching the cargo airship, inflating the second airship with lifting gas carried by the cargo airship while aloft; and releasing the second airship from the cargo airship. A high-altitude airship launch system is also provided. | 12-13-2012 |
| 20100270417 | Winging car - A road driving and flight vehicle is able to automatically convert between two configurations to facilitate operations as an automobile and as an aircraft. In flight configuration the craft includes two jet engines at rear body part, two wings with ailerons produced by open/flap upwardly doors where the upper end is hinged to a body and bottom end raised up to place wings horizontally, and a vertical stabilizer with rudder and two horizontal stabilizers with elevators. In road driving configuration vehicle includes conventional automobile power plant in front part of the body, four wheels of which two front wheels are steerable, two doors, and a vertical and two horizontal stabilizers are stored at rear part of the body. | 10-28-2010 |
| 20120234965 | SYSTEMS AND METHODS FOR LONG ENDURANCE STRATOSPHERIC OPERATIONS - An illustrative airship system for long endurance stratospheric operations includes an upper airship and a first end of a tether attached to the upper airship. A lower airship is attached to a second end of the tether and a payload airship is reversibly mated to the lower airship. The airship system is free flying and configured to maintain long duration station keeping. Illustrative methods for long endurance stratospheric operations are also provided. | 09-20-2012 |
| 20120234964 | SYSTEMS AND METHODS FOR LONG ENDURANCE AIRSHIP OPERATIONS - In one example, a long endurance airship system includes a first combined airship with a payload airship and a first logistics airship. The first combined airship is configured for stationkeeping at a predetermined station during meteorological conditions with wind speeds below a predetermined threshold. The airship system also includes a second combined airship which is a reconfiguration of the first combined airship and includes the payload airship and a second logistics airship. The second combined airship is configured for stationkeeping at the predetermined station in all meteorological conditions, including meteorological conditions with wind speeds above the predetermined threshold. | 09-20-2012 |
| 20110036939 | RAPIDLY CONVERTIBLE HYBRID AIRCRAFT AND MANUFACTURING METHOD - A hybrid fixed wing aircraft converts into a roadworthy vehicle in a matter of seconds therefore operating efficiently in both air and ground transportation systems. The single piece wing is mounted on a skewed pivot that is on the lower portion of the fuselage and is operated by a pushbutton operating system. The aircraft includes telescopic twin boom tail design that when extended allows good pitch stability and damping. The aircraft's wing area may be increased with additional telescopic wing tip segments. This allows an increase in aspect ratio, hence improving efficiency at high loads. This feature will also creates a reduction in induced drag at cruise speed by simply retracting the tips in flight. The vehicle has a unique synchronized control system that switches from flight to ground mode without input from the operator, thereby providing a natural interface for the operator. | 02-17-2011 |
| 20110036938 | ROADABLE AIRCRAFT WITH COLLAPSIBLE WINGS AND DUCTLESS FAN - A roadable aircraft may be registered and driven as a motorcycle on the roadways, does not require that any parts be “left behind” at the airport when configuring to roadable use and does not require removing portions of the aircraft and towing them behind. A foldable and collapsible wing comprises a number of wing ribs, which are hinged to a main forward spar. To fold for road usage, the wing ribs fold about a hinge fitting to collapse against the wing spar. To maintain tension on the wing skin (to prevent flutter) tensioning bladder(s) may be used to keep the fabric taut. Once retracted and folded, the wings align with tail booms to form a compact and aerodynamic package. The ductless fan may be provided with a center-mounted extraction fan ducted to inlets along the fuselage to draw low energy air in toward the fuselage and thus prevent boundary layer separation. | 02-17-2011 |
| 20130008997 | COMBINATION GROUND VEHICLE AND HELICOPTER AND FIXED WING AIRCRAFT - A Combination Ground Vehicle and Helicopter and Fixed Wing Aircraft. A sideways translating tailsitter aircraft. | 01-10-2013 |
| 244003000 | Trains | 6 |
| 20100237183 | SYSTEM AND METHOD FOR THE RETRIEVAL OF A SMALLER UNMANNED AERIAL VEHICLE BY A LARGER UNMANNED AERIAL VEHICLE - A system and method are provided for using a first aircraft to retrieve a second aircraft. The first aircraft is typically larger than the second aircraft. A minimum airspeed of the first aircraft is typically greater than a maximum airspeed of the second aircraft. The first aircraft flies in a substantially circular pattern and extends a tow line, such that the tow line forms a substantially helical shape behind and below the first aircraft. Due to the helical shape, there is at least one point along the extended tow line at which the speed of the tow line is substantially equal to the speed of the second aircraft. The second aircraft can readily latch onto the tow line at that point, thereby minimizing potential damage otherwise caused by differential airspeeds. | 09-23-2010 |
| 20110006151 | 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. | 01-13-2011 |
| 20110024548 | LAUNCHING SYSTEM AND LAUNCHING APPARATUS - A flying object capable of being launched in air is detachably mounted on a wing body of a launching apparatus. The launching apparatus is towed by an aircraft through a cable so as to be run and taken off. After raising the launching apparatus to a launching height of the flying object by the aircraft, the flying object is released from the wing body in air and then the flying object is ignited and launched in air in a launching system. The system for launching in air can be developed without newly developing a platform as a mother ship so that a research cost can be remarkably reduced. In the case that a small artificial satellite is installed in a flying object, it is possible to develop an artificial satellite smoothly and quickly applicable to security matters and disaster observation. | 02-03-2011 |
| 20080223976 | Space vehicle launch system - A space vehicle launch system is proposed which utilizes a vacuum filled lighter than air vessel to lift a rocket powered vehicle to a high altitude where the vehicle can easily blast into outer space. The main advantages of this system are that, first, the rocket would not need to carry a large mass of fuel, and, therefore, this system would be much safer than the state of the art. Second, the vehicle would be lifted slowly through the atmosphere, and would not suffer any damage due to abrupt acceleration or air friction. | 09-18-2008 |
| 20100327104 | DEVICE FOR MAINTAINING THE ALTITUDE OF A PAYLOAD HAVING AN ALTITUDE-MAINTENANCE ENERGY SOURCE THAT IS PERMANENT AND EXTRACTED FROM THE SURROUNDING MEDIUM - A device for permanently maintaining the altitude of a payload the altitude-maintenance energy source of which is practically permanent and extracted from the medium includes at least two gliding bodies connected together by at least one physical link and being, in use, at different altitudes relative to the ground and for which the instantaneous winds have, practically permanently, different characteristics, and further includes a system for controlling the respective attitudes of these two bodies. | 12-30-2010 |
| 20130008998 | TOWABLE AIR VEHICLE - An unmanned, towable aerovehicle is described and includes a container to hold cargo, an autogyro assembly connected to the container and to provide flight characteristics, and a controller to control operation the autogyro assembly for unmanned flight. The container includes a connection to connect to a powered aircraft to provide forward motive force to power the autogyro assembly. In an example, the autogyro assembly includes a mast extending from the container, a rotatable hub on an end of the mast, and a plurality of blades connected to the hub for rotation to provide lift to the vehicle. In an example, an electrical motor rotates the blades prior to lift off to assist in take off. The electrical motor does not have enough power to sustain flight of the vehicle. | 01-10-2013 |
