Abstract: A vehicle which can travel on land, in water, or through air has a body like that of an automobile with powered wheels for providing propulsion on land. The vehicle also has rotors for providing propulsion in air and wings for providing lift. Storage compartments conceal the rotors during land operation, and in this mode the wings are folded down against the body, over the compartments. The wings and the rotors can be deployed to convert the vehicle to flight mode.

Abstract: An inflight connection system for aircraft having at least one wing with a wingtip includes, for each aircraft, a primary connector selectively extendable from the wingtip, an alignment connector selectively extendable from the wingtip and a male and female connector assembly disposed proximate the wingtip. The primary connectors extend a greater distance from the wingtips than the alignment connectors such that the primary connectors form a first connection between the aircraft when the aircraft are flying in a connection pattern. Thereafter, retraction of the primary connectors reduces wingtip separation of the aircraft such that the alignment connectors form a second connection between the aircraft establishing coarse alignment therebetween. Thereafter, retraction of the primary and alignment connectors further reduces wingtip separation of the aircraft such that the male and female connector assemblies form a third connection between the aircraft establishing fine alignment therebetween.

Abstract: The disclosed inventory systems and methods can be used to retrieve and transport items from one location in an inventory system to another. Specifically, an unmanned aerial vehicle (UAV) including passive buoyancy element, a thrust unit, and a retention feature, can be controlled by a management component to retrieve one or more items, transport the item or items, and deposit the item or items. For example, a UAV can be controlled to obtain an item at one location in a warehouse such as a first floor and lift said item to a second location in the warehouse such as a second floor, and deposit the item at the second location.

Abstract: Apparatus, methods, and systems for adjusting a center of mass of a drone may include a balance track and a repositionable weight. The balance track may be configured to extend outwardly from a central region of the drone. The balance track may include a plurality of weight-balance fixation positions. The repositionable weight may be configured to be secured at any one of the plurality of weight-balance fixation positions. In various embodiments the repositionable weight may include an electronic component. Various embodiments may include a another balance track configured to extend outwardly from the central region along a second axis that is different from a first axis of the other balance track.

Abstract: A method and apparatus for reducing a force. An apparatus comprises a multi-directional joint assembly and a damper associated with the multi-directional joint assembly. The multi-directional joint assembly has a first end and a second end. The first end and the second end move relative to each other. The damper is comprised of a number of elastomeric layers and a number of rigid layers interspersed with each other reducing at least one of a force and a moment.

Abstract: The present disclosure reveals a drone deployment system for use from an airborne aircraft such that the drone deployment system is capable of moving through the aircraft, picking up a drone with a grappling means attached to an extendable arm, moving to an opening in the aircraft, extending and deploying the drone. The drone deployment system is further capable of retrieving a drone by having the extendable arm extended out the opening in the aircraft, having the drone fly into the grappling means which then engages, holding the drone, and the extendable arm is then retractable so that the opening can be closed and the drone placed in storage.

Abstract: An airborne drone delivery network and method of operating same that provides an effective system to deliver items to a set number of delivery locations using drones in which the drone flight path is minimized and wherein the drones may be easily retrieved and reused for delivery of additional items.

Abstract: Described is a system and method for utilizing unmanned aerial vehicles (“UAV”) to facilitate delivery of ordered items to user specified delivery destinations. In one implementation, the UAV may be configured as a one-way UAV that is designed to transport ordered items to the user specified delivery destination but not return to a materials handling facility under its own power. Instead, the one-way UAV may remain at the delivery destination for later retrieval by a retrieval unit (e.g., truck).

Abstract: An apparatus for detecting skew in a slat of an aircraft wing includes an elongated track moveably supported in the wing for longitudinal movement toward and away from a leading edge of the wing. The slat is coupled to a forward end of the track for conjoint movement therewith. An actuator is configured to selectably drive the track and slat between retracted and extended positions relative to the leading edge of the wing. A pinion gear is rotatably mounted in the wing and disposed in rolling engagement with a rack gear disposed on the track, and a sensor is coupled to the pinion gear and configured to sense the longitudinal position of the slat as a function of a rotational position of the pinion gear.

Abstract: A method and system for evaluating and loading unmanned aerial vehicles (UAVs) are described. The UAVs are moved by a conveyance device. It may be determined whether the UAV passes at least one of a structural integrity test or a functionality test. The UAV may be removed from the conveyance device in the event the UAV fails at least one of the structural integrity test or the functionality test. A package may be loaded into a compartment of the UAV in the event the UAV passes the structural integrity test and the functionality test.

Abstract: The present invention relates to an automatic system suitable for reducing the speed of rotation of one or more suspended loads, preferably where said rotation is originated by the flow tube located downstream preferably of the blades of the helicopter whereto said loads are attached, or by any other cause, and whose mechanical operation is based on the use of at least one aerodynamic surface, which automatically positions so as to exert, through the actual interaction with this flow tube, an aerodynamic moment, with respect to the center of mass of these suspended loads, appropriately contrary to said speed of rotation, so as to determine the slowing and therefore the progressive stabilization thereof. The automation of this deceleration is obtained through the use of a cycle of automatic control which is based primarily on the interaction, obtained with a processor, between an element responsive to said speed of rotation and an actuator capable of rotating said aerodynamic surface.

Abstract: A boom extension and contraction mechanism for a crane apparatus includes: a flow passage switching mechanism that switches a flow passage of the hydraulic oil between the cylinder-to-boom connection switching cylinder side and the boom member connection switching cylinder side; a hose reel configured to reel out a hydraulic hose as a telescopic cylinder is extending, and to reel off the hydraulic hose as the telescopic cylinder is contracting; a cable used to supply power and transmit a signal between a swivel base and a boom; and a cord reel configured to reel out the cable as the telescopic cylinder is extending and to reel off the cable as the telescopic cylinder is contracting. The code reel and the hose reel are arranged on the base in a direction in which the boom extends and contracts.

Abstract: A motionless skew detection system for an aircraft is disclosed, and includes a flight control surface of an aircraft wing, two drive mechanisms for operating the flight control surface, a first load sensor and a second load sensor for each of the two drive mechanisms, and a control module. Each of the two drive mechanisms are located on opposing sides of the flight control surface and each of the two drive mechanisms include at least a first linkage including a first outer surface and a second linkage including a second outer surface. The first load sensor is disposed along the first outer surface of the first linkage and the second load sensor is disposed along the second outer surface of the second linkage. The control module is in signal communication with the first load sensor and the second load sensor of each drive mechanism.

Abstract: An aircraft is provided and includes a mission vehicle configured to follow vertical take-off and landing (VTOL) operations and to execute forward flight, hover/loiter and landing operations and a launch vehicle configured to drive the mission vehicle through at least vertical take-off (VTO) operations. The launch vehicle is umbilically coupled to the mission vehicle during the VTO operations and releasable from the mission vehicle thereafter.

Abstract: This disclosure describes an unmanned aerial vehicle that may be configured during flight to optimize for agility or efficiency.

Abstract: Innovative new methods in connection with lighter-than-air (LTA) free floating platforms, of facilitating legal transmitter operation, platform flight termination when appropriate, environmentally acceptable landing, and recovery of these devices are provided. The new systems and methods relate to rise rate control, geo-location from a LTA platform including landed payload and ground-based vehicle locations, and steerable recovery systems.

Abstract: Ground vehicles that may include flight capability are described. In some examples, a vehicle frame may include a fuel tank with a main tank and at least two auxiliary tanks, with the main tank disposed substantially along the centerline of the vehicle, and the at least two auxiliary tanks extending upward and outward from the main tank. In some examples, vehicles may include a chassis, a cage attached to the chassis, a front wheelbase attached to the chassis and/or cage, a rear wheelbase attached to the chassis and/or cage, a ground steering mechanism connected to the front wheelbase and/or the rear wheelbase, a motor connected to a propeller, and a propeller shroud at least partially encircling the propeller.

Abstract: A vehicle capable of being converted between a flying condition and an automotive riding condition. The vehicle has a telescopically extendable tail having a first tubular tail segment and a second tail segment disposed axially slideable within the first tubular tail segment. The tail is provided with at least two form-closing coupling members located at an axial distance from each other for providing a force-transferring coupling between the second tail segment and the first tubular tail segment in the extended state of the second tail segment, each of the form-closing coupling members capable of transferring torque and transverse forces, and each of the form-closing coupling members coming into engagement by axial displacement of the second tail segment in the outward direction.

Abstract: A computer-implemented method of controlling an aircraft including, determining whether a change in altitude at a predetermined thrust-setting can be performed, the determination including: determining a climb-requirement including initial and final altitudes and a required range of airspeeds at the final altitude; determining aircraft performance data including a thrust at the final altitude at the thrust-setting, an initial airspeed at the initial altitude and an aircraft total mass at the initial altitude; using the aircraft performance data to determine a final airspeed and drag at the final altitude if a change in altitude at the predetermined setting were performed; determining whether thrust at the final altitude at the thrust-settings and airspeed is greater than drag; and providing a signal indicating whether the calculated final airspeed falls within the required range of airspeeds, and whether the thrust at the final altitude and airspeed at the cruise thrust-setting is greater than drag.

Abstract: Apparatus, methods, and systems for adjusting a center of mass of a drone may include a balance track and a repositionable weight. The balance track may extend outwardly from a central region of the drone. The balance track may include a plurality of weight-balance fixation positions. The repositionable weight may be configured to be secured at any one of the plurality of weight-balance fixation positions. Various embodiments may include receiving a weight-distribution input relating to balancing the drone. A weight-distribution balance profile may be determined, based on the weight-distribution input, for determining whether a repositionable weight should be repositioned among a plurality of weight-balance fixation positions on a balance track extending outwardly from a central region of the drone. The repositionable weight may be repositioned according to the weight-distribution balance profile.

Abstract: The present invention discloses a vehicle (1) capable of being converted between a flying condition and an automotive riding condition. The vehicle has a telescopically extendable tail (10) comprising a first tubular tail segment (11) and a second tail segment (12) disposed axially slideable within the first tubular tail segment. The tail is provided with at least two form-closing coupling members (21, 35; 31, 36) located at an axial distance (LI) from each other for providing a force-transferring coupling between the second tail segment (12) and the first tubular tail segment (11) in the extended state of the second tail segment (12), each of said form-closing coupling members (21, 35; 31, 36) capable of transferring torque and transverse forces, and each of said form-closing coupling members (21, 35; 31, 36) coming into engagement by axial displacement of the second tail segment (12) in the outward direction.

Abstract: A distributed payload attachment system includes a payload suspension cable coupled to a payload, a distributed attachment cable having a first anchor point coupled to a first arm of an aerial platform and a second anchor point coupled to a second arm of the aerial platform, and a pulley system operably coupled between the payload suspension cable and the distributed attachment cable, the pulley system generating equal tension across the distributed attachment cable to enable the payload to shift and balance the tension forces in the distributed attachment cable. A method of operating the distributed payload attachment system and an aerial platform including the distributed payload attachment system are also described herein.

Abstract: An air-to-surface surveillance and/or weapons system includes a base aircraft and an unmanned slave aircraft that can be uncoupled from a base aircraft and coupled back to it again. The base aircraft and slave aircraft are equipped with coupling equipment designed to work together. The base aircraft is equipped with surveillance and monitoring equipment. The slave aircraft is equipped with monitoring equipment and/or weapons. The slave aircraft can be connected to a control station via a data link for data exchange and can be controlled from this control station.

Abstract: 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.

Abstract: A span-loaded, highly flexible flying wing, having horizontal control surfaces mounted aft of the wing on extended beams to form local pitch-control devices. Each of five spanwise wing segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other wing segments, to minimize inter-segment loads. Wing dihedral is controlled by separately controlling the local pitch-control devices consisting of a control surface on a boom, such that inboard and outboard wing segment pitch changes relative to each other, and thus relative inboard and outboard lift is varied.

Abstract: A cargo lift system employs multiple unmanned lift vehicles acting as vertical lift generating machines. An autonomous control system controls coordinated movements of the cooperating unmanned vertical lift generating machines. A coupling system connects the cargo load to each of the plurality of unmanned vertical lift generating machines. The plurality of unmanned vertical lift generating machines are separated from each other by a distance through spacing by individual onboard flight computers in the lift generating machines or by rigid or semi-rigid connections between the lift generating machines.

Abstract: Methods and apparatus for an adaptable solar airframe are provided herein. In some embodiments, an adaptable solar airframe includes an expandable body having an aerodynamic cross-section that reduces parasitic air drag at any given thickness of the body, further being able to change its shape in flight in response to changes in the relative position of the sun; and a flexible solar PV system attached to the surface of the expandable body.

Abstract: A harness is provided comprising a body having a series of electrical conductors embedded therein and substantially running along the length thereof. The body may be part of a structural component such as stringer.

Abstract: A compound rotorcraft including a rotary wing aircraft having a fuselage and at least one rotor and a fixed-wing aircraft coupled to the rotary wing aircraft, wherein the rotary wing aircraft can fly on the rotor or the fixed-wing aircraft, and wherein the fixed-wing aircraft is detachable from the rotary wing aircraft to fly independently.

Abstract: A vehicle which is adaptable for both flight and water travel includes: a body; a wing, a stabilizer, or a first propelling member; and at least one attachment member. The body is configured to fly through air and to move through water. The at least one attachment member attaches the wing, the stabilizer, or the first propelling member to the body while the body is in flight. The at least one attachment member detaches at least a portion of the wing, at least a portion of the stabilizer, or at least a portion of the first propelling member from the body when the body is in the water.

Abstract: The Road-and-air transport vehicle is intended to transport people (from 1 to 4 people] on the roads, as a light passenger vehicle, and in the air—as a small aircraft.

Abstract: A motor vehicle system includes a motor vehicle including an aircraft landing portion, and an actively propelled unmanned aircraft configured to be supported on the aircraft landing portion. The vehicle and aircraft are configured such that the vehicle can provide at least one of fuel and electrical energy to the aircraft while the aircraft is supported on the aircraft landing portion.

Abstract: A combination rotor and wheel assembly for an unmanned vehicle with ground and aerial mobility has a rotor arm adapted to be attached at an inner end thereof to a vehicle body. A rotor is rotatably connected to an outer end of the rotor arm about a rotor axis, and a rotor drive mounted on the rotor arm rotates the rotor such that the rotor exerts an upward lift force on the rotor arm. An open spoked wheel is rotatably connected about the rotor axis independent of the rotor The diameter of the wheel is greater than that of the rotor, and a bottom edge of the wheel is below the rotor. A wheel drive rotates the wheel. Vehicles can have various numbers and orientations of the rotor and wheel assembly to provide aerial and ground mobility.

Abstract: An unmanned aerial vehicle, comprising: a fuselage having a first side board and a second side board spaced apart and connected by at least one transverse board; the first side board, the second side board, and the at least one transverse board being printed circuit boards; at least one of the first side board, the second side board, and the at least one transverse board having formed and mounted thereon conductive traces and at least one component, respectively, for controlling and monitoring the unmanned aerial vehicle; first and second wings mounted to the fuselage; and, a tail mounted to the fuselage.

Abstract: The present invention is realized by apparatus and methods for placing a large utility scale photovoltaic array in the low stratosphere of earth's atmosphere at an altitude of about 20 km, above clouds, moisture, dust, and wind. This is accomplished using a large light-weight, rigid, buoyant structure to support the large photovoltaic array. Long, strong and light tethers connect the buoyant structure to the ground and hold it in position against wind forces. The electricity output from the photovoltaic array is then coupled to high voltage transmission lines which connect from the platform to the earth's surface. The electricity is then transmitted through the high voltage transmission lines to the earth's surface where it is connected to the electrical supply grid and provides lower cost, more reliable electricity.

Abstract: The present invention is realized by apparatus and methods for placing a large rigid buoyant platform in the low stratosphere of earth's atmosphere at an altitude of about 20 km, above clouds, moisture, dust, and wind. The platform can serve several uses, either individually or in any combination. These uses include uninterrupted radio and light communications, radar and optical observation including very powerful radars and solar power electricity generation. Long, strong and light tethers connect the buoyant structure to the ground which hold it in position against wind forces. The electricity output from a photovoltaic array is used to power platform uses and can also be coupled to high voltage transmission lines which transmit power from the platform to the earth's surface during daylight hours. Power can also be transmitted up to the platform during darkness to power facilities mounted on the platform ensuring continuous operation.

Abstract: 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.

Abstract: A vehicle comprises a first stage supersonic aircraft, and a second stage hypersonic aircraft. The second stage aircraft is in tandem with the first stage aircraft.

Abstract: A compound rotorcraft including a rotary wing aircraft having a fuselage and at least one rotor and a fixed-wing aircraft coupled to the rotary wing aircraft, wherein the rotary wing aircraft can fly on the rotor or the fixed-wing aircraft, and wherein the fixed-wing aircraft is detachable from the rotary wing aircraft to fly independently.

Abstract: Transformation method of hybrid transportation vehicle for ground and air includes the following transformation and reciprocal steps: Tilting the compensation cover (7) on. Expansion of both whole wings (1) from the transportation vehicle longitudinal position around two vertical axes (2) into the flying position. Expansion of rear parts of wings (1) from the top front parts of wings (1) into the spread flying position by tilting the rear of each wing (1) around a horizontal axis (3). The take-off and landing tilting of wings (1) by an angle of attack alpha=0 to 40° of the wings onset. Front wheels track (5) is reduced by axially shifting the front wheels (5) towards the fuselage. Furthermore, a corresponding hybrid transportation vehicle for ground and air is described which contains reciprocal transformation mechanisms for transformation from a sterling double or four-track automobile into a sterling aircraft for take-off and landing on the ground or water, and vice versa.

Abstract: A method for launch of an airship includes connecting a cargo airship to a second airship that is not positively buoyant at the launch site, launching the cargo airship, transferring lifting gas from the cargo airship to the second airship where said lifting gas is 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.

Abstract: A launch system and method improve the launch efficiency of a booster rocket and payload. A launch aircraft atop which the booster rocket is mounted in a cradle, is flown or towed to an elevation at which the booster rocket is released. The cradle provides for reduced structural requirements for the booster rocket by including a compressible layer, that may be provided by a plurality of gas or liquid-filled flexible chambers. The compressible layer contacts the booster rocket along most of the length of the booster rocket to distribute applied pressure, nearly eliminating bending loads. Distributing the pressure eliminates point loading conditions and bending moments that would otherwise be generated in the booster rocket structure during carrying. The chambers may be balloons distributed in rows and columns within the cradle or cylindrical chambers extending along a length of the cradle. The cradle may include a manifold communicating gas between chambers.

Abstract: A platform including two winged aircraft are tethered during flight by a single tether near their respective centers of gravity. The tether is windable about a reel, so that a distance between the aircraft can be changed during flight. The aircraft contain avionics configured to enable autonomous flight using natural wind gradients. One aircraft imposes aerodynamic forces on the other, through the tether, while flying at an altitude where wind speed is significantly different than wind speed at an altitude of the other aircraft. The two aircraft cruise back and forth within a maximum distance from a station on the ground. Cruise conditions are established using an iterative computer algorithm which utilizes flight measurements. The aircraft communicate information between each other, and the ground, and contain a payload which performs a useful function at high altitudes.

Abstract: Aircraft systems that are optimized for multiple phases of flight are disclosed. In an aspect, an in-line staged aircraft is disclosed comprising a launch vehicle and a flight vehicle which are configured to join together along a common center line and form a single air foil in the joined configuration. The flight vehicle and the launch vehicle are separable in flight. In an aspect, the flight vehicle is an unmanned aerial vehicle configured for high-altitude, long-endurance operations.

Abstract: 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.

Abstract: Apparatus, systems, and methods provide for a modular vehicle system utilized for lifting and maneuvering payloads. According to aspects of the disclosure, any number of individual lift vehicles may be connected to create a unified lift vehicle. The individual lift vehicles may be placed adjacent to one another according to a determined lifting array formation and coupled together using connection mechanisms. The connection mechanisms rigidly and communicatively connect the individual lift vehicles to create the unified lift vehicle suitable for lifting and maneuvering a payload.

Abstract: A fastener device (10) provided with attachment means (20) for attaching an external load (5) and with fastener means (30) provided with a support beam (40) and with anchor means (50) for anchoring said support beam (40). A first mechanical coupling (60) connects said support beam (40) to the anchor means (50) so as to enable the support beam (40) to pivot about a first pivot axis (AX1). In addition, coupling means (70) are hinged to the support beam (40) so as to make pivoting possible about a second pivot axis (AX2), the attachment means (20) being hinged to the coupling means (70) to make pivoting possible about a third pivot axis (AX3). This fastener device (10) includes automatic folding means (100).

Abstract: A device for launching and recovering a drone for being fastened to an aircraft is provided. The device includes a docking plate for a drone provided with a securing/releasing mechanism for the drone. The docking plate being secured to a flared guide for guiding the drone towards the docking plate.

Abstract: The present invention discloses a vehicle (1) capable of being converted between a flying condition and an automotive riding condition. The vehicle has a telescopically extendable tail (10) comprising a first tubular tail segment (11) and a second tail segment (12) disposed axially slideable within the first tubular tail segment. The tail is provided with at least two form-closing coupling members (21, 35; 31, 36) located at an axial distance (LI) from each other for providing a force-transferring coupling between the second tail segment (12) and the first tubular tail segment (11) in the extended state of the second tail segment (12), each of said form-closing coupling members (21, 35; 31, 36) capable of transferring torque and transverse forces, and each of said form-closing coupling members (21, 35; 31, 36) coming into engagement by axial displacement of the second tail segment (12) in the outward direction.

Abstract: A recoverable module for a propulsion module configured to launch a craft into space, the recoverable module including a central body, a propulsion system configured to launch the craft, systems for commanding and controlling the propulsion system, at least one propulsion engine in subsonic flight, lift surfaces for the subsonic flight and landing gear, the lift surface including two substantially flat wings fixed with respect to the central body, arranged on either side of the central body of the module, and a stabilizer mounted articulated for rotation on a downstream end of each wing, each stabilizer including at least one pair of lower wing surface and upper wing surface flaps mounted articulated on the stabilizer or any other flap fulfilling a dynamic function.