Abstract: A technique of operating an unmanned aerial vehicle (UAV) adapted for a package delivery mission includes: powering distributed propulsion units during takeoff and landing segments of the package delivery mission and idling at least a portion of the distributed propulsion units while powering a pair of outboard propulsion units during a cruise segment of the package delivery mission. The distributed propulsion units are mounted below fixed wings of the UAV and have first propellers mounted fore of the fixed wings. The outboard propulsion units are each mounted to a corresponding one of the fixed wings outboard of the distributed propulsion units. The outboard propulsion units include outboard propellers having a larger diameter than the first propellers.

Abstract: A landing apparatus for a reusable launch vehicle is provided, including a landing leg pivotably mounted at one end to the reusable launch vehicle, for example, to a propellant tank part, and mounted at the other end to the propellant tank part by a detaching means such as a pyro bolt for example, a cover mounted to an outside of the landing leg along a longitudinal direction of the landing leg, and a leg landing plate mounted to a distal end of the landing leg and relatively pivotable with respect to the landing leg by its own weight when the other end of the landing leg is separated from the propellant tank part.

Abstract: The main fuselage 12 and the pair of left and right auxiliary fuselage 14, 16 are connected by three wings, the front wing 30, the main wing 26, and the horizontal stabilizer 32. At the connecting portion between the main fuselage 12 and the main wing 26, a narrow portion 28 is provided in the chord of the main wing 26 that is narrower than the other portions of the main wing 26. The narrow portion 28 of the main wing 26 is connected to the side surface of the main fuselage 12 or the narrow portion 28 penetrates the main fuselage 12. The main wing 26 and the pair of left and right auxiliary fuselage 14 and 16 were connected by interposing a flat columnar support 48. The aircraft can fly stably with less turbulence of airflow and is suitable for aerial refueling and the like.

Abstract: Methods, systems, and apparatus, including computer programs encoded on computer storage media, for controlling spraying of chemicals by an unmanned aerial vehicle (UAV). An unmanned aerial vehicle system includes one or more processors configured to perform operations of autonomously performing a flight path by the UAV and dispersing a chemical by the UAV along portions of the flight path. The UAV may include a chemical spray system having one or more spray booms with multiple nozzles for dispersing a chemical. The chemical spray system may include one or more tanks attached to the body of the UAV and a pump fluidly connected to the tanks to disperse chemical via the spray booms.

Abstract: Aspects relate to systems and methods for folding wings on an aircraft. An exemplary system includes a blended wing body, where the blended wing body includes a main body and at least a wing, a hinge located on the at least a wing and configured to allow folding of the at least a wing, an actuation system configured to fold the at least a wing, and a controller configured to control the at least an actuation system.

Abstract: Aspects related to aircraft for commercial air travel and methods of manufacture. An aircraft includes a blended wing body, a single deck located within the blended wing body, wherein the single deck additionally includes a passenger compartment located in a lateral middle portion of the blended wing body and at least a cargo store located laterally outside the passenger compartment, and a landing gear, wherein the landing gear includes at least a nose gear located substantially forward of the single deck and at least a main gear located substantially aft of the single deck, wherein one or more of the at least a nose gear and the at least a main gear occupies a gear housing that overlaps with a plane coincident with at least a portion of the single deck.

Abstract: A marine seismic acquisition system includes a frame that includes a central longitudinal axis and members that define orthogonal planes that intersect along the central longitudinal axis; a data interface operatively coupled to the frame; hydrophones operatively coupled to the frame; a buoyancy engine operatively coupled to the frame where the buoyancy engine includes at least one mechanism that controls buoyancy of at least the frame, the hydrophones and the buoyancy engine; and at least one inertial motion sensor operatively coupled to the frame that generates frame orientation data, where the hydrophones, the buoyancy engine and the at least one inertial motion sensor are operatively coupled to the data interface.

Abstract: In one aspect the present subject matter is directed to a gas-electric propulsion system for an aircraft. The system may include a turbofan jet engine, an electric powered boundary layer ingestion fan that is coupled to a fuselage portion of the aircraft aft of the turbofan jet engine, and an electric generator that is electronically coupled to the turbofan jet engine and to the boundary layer ingestion fan. The electric generator converts rotational energy from the turbofan jet engine to electrical energy and provides at least a portion of the electrical energy to the boundary layer ingestion fan. In another aspect of the present subject matter, a method for propelling an aircraft via the gas-electric propulsion system is disclosed.

Abstract: An electric powered paraglider is provided. An electric powered paraglider includes a frame which includes a plurality of connector points. The electric powered paraglider also includes a propulsion unit mechanically coupled to the frame. The propulsion unit includes at least one propeller and configured to generate a predefined amount of thrust using at least one electric motor. The electric powered paraglider also includes a throttle controller unit physically or wirelessly connected to the flight control unit. The throttle controller unit includes at least three switches. The at least three switches are configured to operate one or more parameters of the paraglider. The electric powered paraglider also includes a power latching unit mechanically coupled to the frame. The power latching unit includes a plurality of batteries. The power latching unit is configured to allow a user to swap the plurality of batteries by implementing a power latching mechanism.

Abstract: An aerial vehicle (10) has an aerial platform (12) that supports lift elements (11), an engine (14) and a fuel supply (15) and that has a coupling mechanism (16) adapted for coupling to a removable load (17). The lift elements include a soft or flexible wing (11) flexibly coupled to the aerial platform at points of suspension on opposite sides of the aerial platform whose location (A, B) relative to a longitudinal axis of the platform is such that the aerial platform and the attached load has a center of gravity (C.G.) which maintains balance of the aerial platform. An adjustment system (18) is coupled to the points of suspension and is operative for moving the points of suspension relative to the longitudinal axis of the platform when cargo is unloaded from the flying platform to preserve balance.

Abstract: An aircraft has a fuselage, a wing assembly coupleable to the fuselage, and an empennage including a pair of tail booms configured to be removably coupled to the wing assembly. The wing assembly includes a pair of boom interfaces located on laterally opposite sides of the fuselage. Each tail boom has a boom forward end configured to be mechanically attached to one of the boom interfaces using an externally-accessible mechanical fastener.

Abstract: A multi-boom aircraft with an adjustable wing geometric twist includes at least one wing, and at least three booms arranged transversely to at least one of the wings. Each of the booms includes at least one actuator, and the at least one wing is mounted on the booms so as at least a portion of the corresponding wing can be pivoted by means of the actuators about an axis extending substantially along the corresponding wing.

Abstract: There is provided a system including: a control device mounted on an aircraft and configured to control the aircraft, the aircraft having a battery, and a wireless device configured to use power stored in the battery to provide a wireless communication service to a user terminal; and a module that is physically attachable to and detachable from the control device, in which the control device has a housing that includes a module attachment and detachment unit, and an electrical connection unit configured to electrically connect the module to the battery when the module is attached to the module attachment and detachment unit, and the module has, a power receiving unit configured to receive power from the battery, and a communication processing unit configured to use the power received by the power receiving unit to communicate with the wireless device.

Abstract: The aircraft (10) comprises a fuselage (11) and a rhombohedral wing structure (12) comprising front wings (13, 14) mounted on a front wing-root support (17) and rear wings (15, 16) mounted on a rear wing-root support (18). One end of each front wing is articulated to one end of a rear wing and at least one of the wing-root supports is able to move along the fuselage. The wing-root supports (17, 18) are positioned respectively underneath and on top of the fuselage (11). The length (41) of the rear wings (15, 16) is strictly less than the length (48) of the front wings (13, 14). The aircraft (10) comprises an adaptor for adapting the position of each wing root (17, 18) to suit the flight conditions.

Abstract: A flight vehicle including a frame having a bottom side configured to receive a user harness, port and starboard wings extend from port and starboard sides of the frame. Each wing may include at least one helium wing bag. The flight vehicle also includes a helium backpack secured to a top side of the frame, the helium backpack including an inflatable main helium bag configured for holding a main volume of helium. Each of the at least one helium wing bag may be fluidically isolated from the main helium bag. The flight vehicle may include a rigid base member, the inflatable main helium bag joined to an upper surface of the rigid base member via an elastic expansion member.

Abstract: An aerial vehicle includes an airframe, a canopy capable of adjusting a speed of falling during falling, a brake cord having one end connected to the canopy, a wind-up apparatus provided in the airframe and being capable of winding up the other end of the brake cord, a sensor unit that detects a distance to an external object, and a controller that controls an operation of the wind-up apparatus based on a result of detection by the sensor unit. The wind-up apparatus includes a gas generator as a drive source. The controller has the wind-up apparatus operate to wind up the other end of the brake cord by activating the gas generator when the distance detected by the sensor unit is equal to or smaller than a prescribed value.

Abstract: An aircraft with an airframe and at least one thrust producing unit the at least one thrust producing unit being electrically powered by an associated electrical engine that is electrically connected to an electrical energy source via an electrical energy distribution system, wherein the airframe comprises at least one load carrying section and at least one propulsion system carrying section, wherein the at least one load carrying section and the at least one propulsion system carrying section are segregated from each other, wherein the at least one load carrying section is provided for transportation of passengers and/or cargo, and wherein the at least one propulsion system carrying section is provided for carrying at least essentially the electrical energy source and the electrical energy distribution system.

Abstract: An aircraft includes a fuselage having a tail section and an engine core coupled via an external pylon to the fuselage. The aircraft further includes a boundary layer ingestion (BLI) fan coupled to the tail section of the fuselage and coupled via a shaft to the engine core.

Abstract: Method comprises receiving, by at least one memory, from at least one imaging system, at least two input images. The method includes comparing, by a processor, the at least two input images to each other such that nonstationary portions of the at least two input images are determined by either separating, by the at least one processor, each of the two input images into multiple pixel regions, and generating an error matrix for each of said multiple pixel regions. If an error value in the error matrix falls within a predetermined range, the pixel region is a nonstationary portion of the input images; or identifying, by a machine learning system, nonstationary portions of the input images. The pixels from nonstationary portions are removed from the at least two input images.

Abstract: A method to control folding of a wing tip section about a fixed base wing section by a control system that automatically determines whether: (i) a command signal is received to fold the wing tip section, (ii) a first condition indicating signal indicates that the aircraft is on the ground; (iii) the current speed of the aircraft is no greater than a preset maximum speed, and (iv) the aircraft is not at gate in an airport.

Abstract: Systems and methods to improve stability and control of an aerial vehicle are described. For an aerial vehicle having a ring wing around a fuselage and a plurality of propulsion mechanisms, one or more sections of the ring wing may be pivotable to reduce vibrations and forces transferred to the aerial vehicle, and to prevent stall and minimize turbulence experienced by the aerial vehicle. The pivotable sections of the ring wing may be freely pivotable, may include locking elements to prevent or allow pivoting, may include bias elements or dampening elements to partially control the free pivoting, or may include actuators to effect desired pivoting.

Abstract: An example method of manufacturing a wing includes providing a wing frame. The wing frame includes a primary spar, a drag spar, a plurality of transverse frame elements having at least one spar joiner, and a plurality of mounting elements. The primary spar is coupled to the drag spar via the at least one spar joiner. The method further includes placing the wing frame into a mold, wherein the mold defines a shape of the wing. The method also includes injecting the mold with an air-filled matrix material, such that the air-filled matrix material substantially encases the wing frame and fills the defined shape of the wing, and such that the plurality of transverse frame elements provide torsional rigidity to the wing.

Abstract: A system and method for monitoring the intensification and weakening of tropical cyclones, including tropical storms and hurricanes. The method includes flying a UAV above the tropical cyclone for an extended period of time and detecting transitions in structure. Intensification to hurricane stage is indicated by core structure transition of the tropical cyclone to include the presence of an eye within an eyewall. The UAV can be a Global Hawk aircraft and include a number of sensors and detectors, such as a camera for providing images of the tropical cyclone, an infrared detector for detecting temperature changes in the eye structure, a radar detector for detecting wind magnitude and direction in the tropical cyclone, dropsonde sensors for measuring temperature, pressure, humidity, and wind speed/direction in the tropical cyclone, etc. The UAV can relay the vortex parameter data in real time to a satellite for subsequent downlinking to receiving stations.

Abstract: An aircraft is disclosed having a lifting body housing a passenger cabin including a forward portion bounded laterally by at least one portion of a leading edge of the lifting body. The passenger cabin includes at least one lateral luggage storage device housed in the concavity formed by the leading edge portion and includes an opening towards the interior of the passenger cabin.

Abstract: Disclosed herein is a modular aerial vehicle system having a fuselage module configured to couple with a plurality of lift generation modules. The modular aerial vehicle system may comprise a fuselage module and a lift generation module. The fuselage module can include a first attachment interface, an avionics system operatively coupled with a power unit (e.g., via an ESC), and a communications system operatively coupled with the flight controller. The lift generation module can include a second attachment interface and a plurality of propulsors. The fuselage module may be configured to removably couple with the lift generation module via the first and second attachment interfaces. The first and second attachment interfaces may comprise (1) a plurality of electrical contacts to facilitate electrical communication between the fuselage module and the lift generation module and/or (2) one or more retention devices to couple structurally the lift generation module with said fuselage module.

Abstract: A fixed-wing flying apparatus, aircraft, airplane or device is provided which is capable of stably gliding in more than one direction such as backwards, frontward or sideways. The device comprises a plurality of wings arranged around the center of area and defining a space therebetween. Each wing includes an outwardly protruding wall along an outer edge of the wing, which disrupts airflow over the wing flying in front so it is less effective than the wing flying behind, facilitating temporary or long term sustainable speed-seeking glide stability in more than one forward direction without any trim or center of gravity adjustment. The plurality of wings can include two wings, three wings forming a triangle, or four wings forming a square or rectangle. The aircraft can be unpowered, powered, free-flight or controlled. A one-front airplane can also be constructed with very relaxed yaw stability.

Abstract: An aircraft propulsion assembly, comprising a gas generator and two fans rotated by the gas generator and offset on either side of a vertical plane passing through the axis of said gas generator. The propulsion assembly comprises an air inlet sleeve comprising an inlet pipe oriented along a first axis that is substantially parallel and offset with respect to a longitudinal axis of the gas generator, the inlet pipe dividing into a supply pipe that is connected to an inlet opening of the gas generator and a discharge pipe configured such that particles ingested by the inlet pipe are discharged without entering the gas generator.

Abstract: A solar powered aircraft including a modular main wing and a pair of relatively large modular winglets attached to the transverse end portions of the main wing. To collect solar radiation, including relatively low-angle radiation, solar panels are mounted to both the main wing and the winglets. In some embodiments, the aspect ratio of the main wing is relatively low, such as between 9 and 15, i.e., the main wing is relatively deep compared to its wing span. In some embodiments, the winglets are relatively long, such as in the range of 0.2 to 0.7 times the length of the main wing semi-span. In some embodiments, a truss-like spar passes through and helps support the wing and the winglets.

Abstract: An aircraft that comprises a body, a wing, and a strut. The wing is coupled to and extends from the body. The wing comprises a wing inboard end portion, a wing outboard end portion, opposite the wing inboard end portion, and an intermediate portion between the wing inboard end portion and the wing outboard end portion. The strut comprises a strut inboard end portion and a strut outboard end portion. The strut inboard end portion is coupled to and extends from the body and the strut outboard end portion is coupled to and extends from the intermediate portion of the wing. The strut outboard end portion of the strut is configured to generate a download acting on the strut outboard end portion of the strut when the aircraft is in flight.

Abstract: An oblique wing aircraft designed for reduced surface area to volume ratio. The aircraft has an oblique wing comprising a forward swept wing segment and an aft swept wing segment. A center oblique airfoil section connects the forward and aft swept wing segments. The center oblique airfoil section has a larger chord near its centerline than the chords of either of the forward or aft swept wing segments. The chord of the center oblique airfoil section tapers down more rapidly than the forward or aft wing segments as the center oblique airfoil section extends outboard toward the forward and aft swept wings. Preferably, the aircraft is an all-wing aircraft.

Abstract: Various embodiments include methods and aerial robotic vehicles that adjust a flight control parameter based on whether propeller guards are installed. An aerial robotic vehicle processor may determine whether a propeller guard is installed, set a flight parameter based on the determination, and control one or more motors of the aerial robotic vehicle using the flight parameter. When propeller guards are installed, the flight parameter may be set to a value appropriate for controlling the aerial robotic vehicle when the propeller guard is installed. The flight parameter may be one or more of control gains, drag profile control settings, a maximum rotor speed, maximum speed of the aerial robotic vehicle, maximum power usage, restrictions to select modes of operation, visual algorithm settings, or a flight plan. Data from one or more sensors and/or motor controllers may be used to determine the presence of a propeller guard.

Abstract: A hang glider control device may include a cross bar having a first end, a second end, a central region, a first central arm, and a second central arm. The first central arm and the second central arm may be coupled opposingly to the central region. The first end may be formed by a portion of the first central arm distal to the central region, and the second end may be formed by a portion of the second central arm distal to the central region. The first end of the cross bar may be configured to couple the cross bar to the first upright above the base tube, and the second end of the cross bar may be configured to couple the cross bar to the second upright above the base tube so that the crossbar may be generally parallel to the base tube.

Abstract: An air vehicle configured to augment effective drag to change the rate of descent of the air vehicle in flight via propeller shaft rotation direction reversal, i.e., thrust reversal.

Abstract: A cross flow fan to be incorporated into an aircraft fuselage comprises an ingestion fan rotor to be positioned in a tail section of an aircraft fuselage to reduce boundary layer air from a top surface of the fuselage and to drive the air away from the top surface, and a drive arrangement for the ingestion fan rotor. An aircraft is also disclosed.

Abstract: Systems and methods for countering an unmanned air vehicle are disclosed. Representative methods include directing an interceptor UAV toward a target UAV, and directing the interceptor UAV back to ground along a controlled flight path, for example, in response to an instruction not to engage with the target UAV, and/or in response to an unsuccessful engagement. Another representative method includes disabling the target UAV by deploying a disabling element (e.g., a net) from the interceptor UAV to contact the target UAV. Representative systems include a target acquisition system, a launch control system, and an engagement system carried by the interceptor UAV. In particular embodiments, the interceptor UAV can have a generally cylindrical fuselage, one or more fins carried by the fuselage, counter-rotating propellers carried by the fuselage, and a disabling system that is configured to disable the target UAV.

Abstract: The present invention is directed to a solar-powered aircraft comprising a fixed wing panel, a motor driven propeller, a plurality of secondary wing panels, and a tail assembly having a first tail panel and a second tail panel. Each secondary wing panel being configured to rotate about a first longitudinal pivot axis extending from a distal end of the fixed wing panel through a central transverse portion of the secondary wing panel. The secondary wing panels may comprise an array of solar panels on its surface. The first tail panel comprises a second array of solar panels located on a surface of the first tail panel, the first tail panel being configured to rotate about a second longitudinal pivot axis through a central transverse portion of the first tail panel.

Abstract: The target marking device comprises a small-size flying unit, said flying unit being configured to fly at low height and to be guided with the aid of guidance commands, said flying unit being furnished with at least one sensor able to measure at least one parameter of the environment, a data transmission unit configured to emit at least data relating to measurements carried out by the sensor from the flying unit and to receive guidance orders at the flying unit, and at least one emitter able to emit position information.

Abstract: A heavy payload, autonomous UAV able to deliver supply by way of airdrop with more precision and at a lower cost. The UAV can be equipped with a movable wing system. The UAV can include a removable storage box. The UAV can be equipped with a drogue parachute for deploying the wings upon jettison of the UAV from a mothership. The UAV can be controlled remotely or it can operate autonomously. The UAV can include canard wings. The canard wings and the movable wings can include ailerons to effectuate flight control of the UAV. The UAV can be reusable or can be an expandable UAV. The UAV's wings can be configured to automatically separate from the UAV during the landing sequence.

Abstract: A solar power system comprising a solar panel, a load, and a battery pack group. The load comprising an electric motor operatively coupled with a propeller. The battery pack group comprises one or more voltage controllable battery packs, each of said one or more voltage controllable battery packs comprising a plurality of battery cells. The voltage controllable battery packs having a rigid printed circuit board electrically coupled with the plurality of battery cells, the rigid printed circuit board including an interconnect connector to electrically couple with a corresponding interconnect connector of a second voltage controllable battery pack.

Abstract: A collapsible flying device is provided having a housing including first and second housing sections forming an enclosure, and a motorized assembly that includes a drive motor and a drive shaft driven by the drive motor. The drive shaft matingly receives the first housing section and is coupled to the second housing section, wherein operation of the drive motor drives the drive shaft to move the first housing section from a closed position adjacent the second housing section to an open position spaced from the second housing section. A rotor hub is rotatingly driven by the drive motor. At least two rotor blades are coupled thereto and positioned within the enclosure in a collapsed position when the first housing section is in the closed position, and extend beyond the enclosure in an expanded position when the first housing section is in the open position.

Abstract: Described is an airborne fulfillment center (“AFC”) and the use of unmanned aerial vehicles (“UAV”) to deliver items from the AFC to users. For example, the AFC may be an airship that remains at a high altitude (e.g., 45,000 feet) and UAVs with ordered items may be deployed from the AFC to deliver ordered items to user designated delivery locations. As the UAVs descend, they can navigate horizontally toward a user specified delivery location using little to no power, other than to stabilize the UAV and/or guide the direction of descent. Shuttles (smaller airships) may be used to replenish the AFC with inventory, UAVs, supplies, fuel, etc. Likewise, the shuttles may be utilized to transport workers to and from the AFC.

Abstract: According to the invention there is provided a transition arrangement (10) for an aircraft for aiding stabilization of an aircraft between substantially vertical and horizontal flight of the aircraft, the transition arrangement (10) including an aerofoil (12) and mounting means for mounting the aerofoil rotatable between a leading (18) and/or a trailing edge (20) of an aircraft wing.

Abstract: An aircraft (1), in particular a passenger or cargo aircraft, with a fuselage (2), has a tandem wing arrangement and has at least two aero engines (5, 6) disposed on the upper surface of the rear wing (4). In this way the disadvantages of the known solutions of the prior art are avoided and an improved aircraft configuration with improved aerodynamics, namely clearly reduced induced drag, is provided. Moreover, the invention creates an environmentally friendly aircraft design which conserves resources, increasing the acceptance of such aircraft among the population.

Abstract: An aerodynamically shaped, active towed body includes a fuselage curved along its vertical and horizontal longitudinal plane. The fuselage has a unit chamber and a load chamber. A transverse plane of the fuselage is triangular, two upper corners being located on an upper face of the fuselage and a lower corner being located on a lower face of the fuselage. Each of two wings is subdivided into a small and a large segment. The small segment points downwards and is attached to the fuselage in a region of the lower corner and the large segment points upwards and is attached to the small segment. Each of the small segments comprise an additional load chamber. The towed body further includes a tail fin, rudders that are each adjustable by the control device and a coupling for the towing cable.

Abstract: A method for detecting faults in a vehicle control system comprising functional units having an associated unique prime number label is provided. The method comprises calling each of the functional units, the call comprising a readable and updateable integer traversal value, and in case the functional unit is operating correctly, updating the traversal value to be the product of the value in the call and the label of the currently called functional unit, and in the case of a fault, not updating the traversal value. Further, the method comprises determining from the traversal value if any functional units are faulty by a comparison with an expected traversal value, and, in the case that the traversal value is not equivalent to the expected traversal value, determining which functional units are faulty by a unique prime factorization algorithm.

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 high-lift device includes a flap body which is provided at a rear portion of a main wing which generates a lift for the air vehicle such that the flap body is deployed with respect to the main wing and stowed in the main wing and extends along a wingspan direction of the main wing; and a gap increasing section provided at an end portion of the flap body in an extending direction of the flap body, to increase a gap between the rear portion of the main wing and a front portion of the flap body in a state in which the flap body is deployed.

Abstract: A system for controlling a high-lift device of an aircraft may include an interface for placement in a flight deck of an aircraft. The interface may include an edge control device for controlling a position of the high-lift device. The interface may be operable to select any of a plurality of control device positions. Each one of the plurality of control device positions may correspond to a different flight phase of the aircraft. The edge control device may be operable to engage, in response to a selection of a first control device position, a command mode for actuating the high-lift device in an automated manner based on the flight phase associated with the first control device position.

Abstract: An unmanned aerial vehicle (UAV) that can operate both as a conventional multicopter with no wing attached, or, it can operate as a winged multicopter. The detachable wing design used in the invention provides versatility without compromising performance; the wing attachment receptacles add no weight to the wingless multicopter configuration because they also function as the leg receptacles. In one embodiment, the base multicopter configuration is a quad-copter with four propeller drives. Four tubular receptacles, two forward and two aft, provide attachment points for the vertical struts of a detachable rectangular shaped wing, these vertical struts also function as the legs of the multicopter. The wing is fabricated using lightweight struts and rip stop nylon fabric which can be easily folded into a compact shape using quick release pins. In another embodiment, the wing is fabricated using a foam core.

Abstract: An oblique wing aircraft designed for reduced surface area to volume ratio. The aircraft has an oblique wing comprising a forward swept wing segment and an aft swept wing segment. A center oblique airfoil section connects the forward and aft swept wing segments. The center oblique airfoil section has a larger chord near its centerline than the chords of either of the forward or aft swept wing segments. The chord of the center oblique airfoil section tapers down more rapidly than the forward or aft wing segments as the center oblique airfoil section extends outboard toward the forward and aft swept wings. Preferably, the aircraft is an all-wing aircraft.