Abstract: A system of a multi-rotor aircraft that capitalizes on the advantages of fixed wing elements combined with rotary wing structures. The fixed wing elements can help to generate lift once the aircraft is airborne and can thus reduce the need for larger lifting rotors which can allow for longer flight times and distances. Additionally, the systems disclosed herein take advantage of a partial in-wing configuration with a number of rotors to reduce the overall footprint of the vehicle while maintaining the flight efficiency that comes with combining features of fixed and rotary wing elements, and increasing operator safety by shrouding rotating parts. The unique configurations allow for a decoupling of the pitch, yaw and roll authority to reduce the complexity in control systems and improve the flight efficiency of the aircraft. Additional configurations implement the use of smaller thrust rotors that can be used to generate thrust as well as control yaw and thus counteract any remaining unbalanced torque.

Abstract: An airship comprises a plurality of electric power generators; a plurality of electrical buses; and a plurality of propulsion points each equipped with a propellant bundle formed from a plurality of thrusters of the electric-motor-driven propeller type. For each of the propulsion points, a thruster is electrically connected to one of the generators by way of one of the electrical buses, and another thruster of the propulsion point is electrically connected to another of the generators by way of another of the electrical buses.

Abstract: A plurality of propellers generates vertical thrust at least some of the time. An attachment sub-system detachably couples to a vertical connector, where a plurality of vertically-stacked multicopters are configured to detachably couple to the vertical connector in order to transport a load at a bottom end of the vertical connector. There is an opening in a vehicle frame that is configured to: (1) receive the vertical connector prior to the attachment sub-system detachably coupling to the vertical connector and (2) hold the vertical connector while the attachment sub-system is detachably coupled to the vertical connector.

Abstract: A method is provided. An airship is maneuvered to a desired location and oriented with the thruster such that ambient wind is traveling in a direction that is substantially parallel to the longitudinal axis of the fuselage. The airflow from the ambient wind is straightened with the flow straightener to generate a substantially laminar flow. The turbine is engaged with the airflow generated by the ambient wind to generate electricity, and the electricity generated by the turbine is rectified with the rectifier and stored in the storage array.

Abstract: A craft having a source of deuterium-containing micro-fusion fuel particles is operable above a planetary, lunar or asteroid surface in the presence of ambient cosmic rays. The fuel particles are dispersible from a set of ports, where at least some of the ports are in an underside of the craft body and others are in lateral sides of the craft body. Dispersed fuel particles interact with ambient cosmic rays and muons to generate energetic reaction products, at least some which are then received by the underside of the craft to generate lift and also selected lateral sides of the craft to generate propulsive thrust in a desired lateral direction. The craft can carry tethers and winches to carry a payload above the surface from location to another. In another embodiment, a balloon-based design, such as a dirigible, provides primary buoyant lift, while the micro-fusion particles provide at least lateral thrust, and supplemental lift where needed.

Abstract: The technology relates to managing power of an aerial vehicle. The system may include an aerial vehicle having a power storage module and one or more components, as well as a computing device communicatively coupled to the aerial vehicle. The computing device may include a processor and a memory storing instructions which, when executed by the processor, may cause the computing device to receive data indicating a state of charge of the power storage module, receive data indicating a rate of power consumption of the at least one component, generate a power command based on at least one of the state of charge of the power storage module or the rate of power consumption of the at least one component, and transmit the power command to the aerial vehicle.

Abstract: Systems, devices, and methods for a transformable aerial vehicle are provided. In one aspect, a transformable aerial vehicle includes: a central body and at least two transformable frames assemblies respectively disposed on the central body, each of the at least two transformable frame assemblies having a proximal portion pivotally coupled to the central body and a distal portion; an actuation assembly mounted on the central body and configured to pivot the at least two frame assemblies to a plurality of different vertical angles relative to the central body; and a plurality of propulsion units mounted on the at least two transformable frame assemblies and operable to move the transformable aerial vehicle.

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: A helicopter system has multiple rotors and methods of operation. The helicopter has a fuselage with four rotors and an engine operably connected to the four rotors for powered rotation of a rotor shaft with a set of rotor blades attached for each of the four rotors. Each of the rotor shafts is positioned in a housing with each housing attached at a lower end to a distal end of a beam with beams attached at a proximal end on the right side and on the left side adjacent to the nose end of the fuselage, and on the right side and on the left side adjacent to the tail end of the fuselage. All four rotor shafts are inclined from a lower end to an upper end toward the fuselage. All four rotor shafts may be inclined toward the nose end or the tail end of the fuselage.

Abstract: An apparatus is described comprising: at least one processor; and memory storing instructions that, when executed by the at least one processor, cause the apparatus to: regulate an operation of a motor based at least in part on a control imposed on an output torque of the motor and a rate of change of a speed of the motor.

Abstract: An airship is disclosed. The airship may include a plurality of frame members defining a support structure for a hull of the airship. The airship may further include a plurality of bladders disposed within the hull, and retaining a volume of a lighter-than-air gas. The airship may also include a plurality of valves operatively coupled to at least one of the bladders. The airship may additionally include a computer configured to operate the valves to vary aerostatic buoyancy of the airship to achieve a desired lift force.

Abstract: A solar-powered airship with a hull configured to contain a gas and at least one propulsion assembly with a propulsion device and electric motors configured to drive the propulsion device. The airship may also include a power supply system including solar panels operatively coupled to the electric motors and configured to supply power to the electric motors. The power supply system may also include batteries operatively coupled to the solar panels and configured to receive and store electrical energy supplied by the solar panels, the batteries being further operatively coupled to the electric motors and configured to supply power to the electric motors. The batteries may each be located within an outer envelope of the airship defined by the hull of the airship in a position selected to provide ballast. The solar-powered airship may also include a cargo system configured to contain passengers or freight.

Abstract: An apparatus includes a lighter than air platform, a reversible propulsive/wind turbine, a deployable anchor to constrain movement of the lighter than air platform with respect to an anchor point allowing wind to drive the turbine, and a generator/motor coupled to the turbine to produce electrical power when movement of the lighter than air platform is constrained. A method performed by the apparatus is also provided.

Abstract: Embodiments according to the methods and systems provide for the selection, assembly, deployment, exploitation of data collected, redeployment, retrieval and stowage of a remotely operated lighter than air (LTA) network of vehicles. From modular components stowed with a mobile platform, one or more LTA vehicles can be assembled, deployed and retrieved. Determining the desirable number of LTA vehicles and the modular components to be assembled for each vehicle can be performed through a computer recommending modular components based on mission parameters. A remote controller device can be used for pre-deployment setup, in-flight mission management and analysis of data gathered by a plurality of possible sensing devise operably attached to the one or more LTA vehicles.

Abstract: An airship is disclosed in the form of a spherical hull having a venting duct extending diagonally therethrough from an entrance end at the forward facing surface of the hull to an exit end at the rearward facing surface of the hull. A propeller is disposed in the duct to direct an air flow through the duct for expulsion at the exit end and the exiting flow is vectored by a set of controllable louvers at the exit end. The expulsed airflow reduces drag normally associated with a spherical airship by disturbing the wake at the trailing surface of the airship. A mooring method and apparatus also is disclosed for minimizing wind induced loads on the airship, or indeed on any body such as a gas storage tank, by supporting the airship or other body a predetermined distance above the ground.

Abstract: A hybrid lift air vehicle for carrying and transporting a load, comprising an envelope having a generally ellipsoidal shape adapted to receive a volume of lighter-than-air gas, at least two variable thrust vertical thrusters in secure engagement with the envelope and at least two variable thrust lateral thrusters in secure engagement with the envelope, means for temporarily securely engaging the load to the envelope wherein the volume of lighter-than-air gas has a buoyancy that offsets at least 25% of the weight of the air vehicle when unloaded, wherein the thrust from the at least two vertical thrusters may be varied to raise and lower the air vehicle and the load when engaged, and wherein the thrust from the at least two lateral thrusters may be varied to maneuver and transport the raised air vehicle and the load when engaged.

Abstract: A propulsion unit for an airship comprises a driveshaft, having a gimbal mount to a mounting frame attachable to a fuselage, the gimbal being mounted in the mounting frame and comprising an inner ring and an outer ring having orthogonal rotational axes, the inner ring including a propeller unit having a conical housing pivotable on trunnions with the gimbal and a propeller affixed to a propeller shaft coaxial with the axis of the conical housing. The outer ring includes a toroidal Orientation of the conical housing and propeller shaft is accomplished by actuators, a first actuator controlling the angle of the outer ring relative to the framework and a second actuator controlling the angle of the conical housing relative to the outer ring.

Abstract: The method for generating an integrated guidance law for aerodynamic missiles uses a strength Pareto evolutionary algorithm (SPEA)-based approach for generating an integrated fuzzy guidance law, which includes three separate fuzzy controllers. Each of these fuzzy controllers is activated in a unique region of missile interception. The distribution of membership functions and the associated rules are obtained by solving a nonlinear constrained multi-objective optimization problem in which final time, energy consumption, and miss distance are treated as competing objectives. A Tabu search is utilized to build a library of initial feasible solutions for the multi-objective optimization algorithm. Additionally, a hierarchical clustering technique is utilized to provide the decision maker with a representative and manageable Pareto-optimal set without destroying the characteristics of the trade-off front. A fuzzy-based system is employed to extract the best compromise solution over the trade-off curve.

Abstract: The control optimization method for helicopters carrying suspended loads during hover flight utilizes a controller based on time-delayed feedback of the load swing angles. The controller outputs include additional displacements, which are added to the helicopter trajectory in the longitudinal and lateral directions. This simple implementation requires only a small modification to the software of the helicopter position controller. Moreover, the implementation of this controller does not need rates of the swing angles. The parameters of the controllers are optimized using the method of particle swarms by minimizing an index that is a function of the history of the load swing. Simulation results show the effectiveness of the controller in suppressing the swing of the slung load while stabilizing the helicopter.

Abstract: The fuzzy logic-based control method for helicopters carrying suspended loads utilizes a controller based on fuzzy logic membership distributions of sets of load swing angles. The anti-swing controller is fuzzy-based and has controller outputs that include additional displacements added to the helicopter trajectory in the longitudinal and lateral directions. This simple implementation requires only a small modification to the software of the helicopter position controller. The membership functions govern control parameters that are optimized using a particle swarm algorithm. The rules of the anti-swing controller are derived to mimic the performance of a time-delayed feedback controller. A tracking controller stabilizes the helicopter and tracks the trajectory generated by the anti-swing controller.

Abstract: This invention performs relative positioning, predictive control, and ballast control to achieve very heavy-lifting tasks on land or sea. Such tasks allow station keeping and precise transfer of very heavy payloads between ships underway. This scalable multibody system features three subcomponents: Airship, Skycrane and Loadframe. This semi-autonomous system combines aerodynamic (kinetic) and aerostatic (buoyancy force) lift with efficient power and propulsion. During low-speed flight, the Airship and Skycrane are decoupled but linked via a reelable Tether Control Line. Beneath the Skycrane, centered on its hull, a patented NIST (National Institute of Standards and Technology) RoboCrane, featuring a computer controlled six degrees of freedom (DoF) cabling system, is attached, to precisely suspend and control a Loadframe, with or without payload. During subsonic forward flight, these Airship and Skycrane are coupled as a single airframe: fuselage and delta wing.

Abstract: 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.

Abstract: 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.

Abstract: An air vehicle includes a body having a top and a bottom and a support platform for carrying cargo such a people or equipment. An impeller mounted on the body is powered, such as by a motor, for rotating so as to create low pressure on the top of the body relative to the pressure on the bottom of the body so as to create lift. The body may contain buoyant gas sufficient to aid in lift. Air from the impeller may be directed to directionally control the vehicle. A plurality of impellers may be used.

Abstract: A multi-purpose airship usable for multi-purposes with less maintenance cost is provided. The multi-purpose airship comprises an operator cabin (1) to which a work device of agricultural chemical scattering device (10) or the like is fittable, a rotor (4) fitted to a top of the operator cabin (1) and having rotor blades of plural stages (or coaxial rotors) of which fitting angle (or pitch) is adjustable to generate a lifting force and propulsive force, a balloon (5) detachably fitted to a top of the rotor (4) and filled with gas lighter than air to generate a lifting force, a stabilizing wing (2) elongating horizontally from each side of the operator cabin (1) and a propulsion device (3) comprising a propeller device or jet engine fitted to a distal end of the stabilizing wing (2) to vary a thrust direction between the horizontal direction and the vertical direction.

Abstract: The present invention comprises an inflatable balloon of sufficient volume and buoyancy to allow a human pilot to float above the ground and to glide over the ground within an enclosed area. The balloon incorporates several safety features that permit it to be used for recreation, including a prop-bike to enable the user to propel the balloon.

Abstract: An aircraft has a flying wing and two wingtip hulls installed on the wingtips of the flying wing. Both of the wingtip hulls contain lighter-than-air gas to generate static lift. These wingtip hulls not only contribute to lift-generating but also help the aircraft achieve roll stability and control. Forward propulsion systems are installed at the upper-front positions of the flying wing. When vertical and/or short take-off and landing (V/STOL) capability is required, one or more lift-fan propulsion systems can be installed on the flying wing. The lift-fan propulsion systems can either be driven by their own engines or by the power transmitted from the forward propulsion systems. Payload can be carried inside the flying wing or be hung under or held above the flying wing.

Abstract: A vertical lift aircraft comprises a cabin mounted to an enclosed rotary wing which provides vertical lift for the aircraft. The rotary wing includes an annular housing and a main rotor blade rotatable within a space circumscribed by the housing. The main rotor blade is rotatable about a rotation axis that is tilted forwardly from a vertical axis of the aircraft. A horizontal directional control for the aircraft includes a plurality of control slides disposed at spaced locations along the housing and being movable inwardly and outwardly in a radial direction between a neutral position in which the control slides are retracted from the downdraft area and an operational position in which the control slides are extended into the downdraft area. Selective deployment of one or more control slides in the operational position effects horizontal directional turning of the aircraft in the direction of the one or more deployed control slides.

Abstract: A vertical lift aircraft comprises a cabin mounted to an enclosed rotary wing which provides vertical lift for the aircraft. The rotary wing includes an annular housing and a main rotor blade rotatable within a space circumscribed by the housing. The main rotor blade is rotatable about a rotation axis that is tilted forwardly from a vertical axis of the aircraft. A horizontal directional control for the aircraft includes a plurality of control slides disposed at spaced locations along the housing and being movable inwardly and outwardly in a radial direction between a neutral position in which the control slides are retracted from the downdraft area and an operational position in which the control slides are extended into the downdraft area. Selective deployment of one or more control slides in the operational position effects horizontal directional turning of the aircraft in the direction of the one or more deployed control slides.

Abstract: The present airship-shaped space craft has a middle fuselage extending in a fore-and-aft direction, and a pair of two outer fuselages extending in the fore-and-aft direction located symmetrically on both sides of the middle fuselage. In the above fuselages, gas of a specific gravity of which is smaller than that of air is filled, and the middle fuselage is connected with the outer fuselages by a horizontal wing. The horizontal wing is provided with propelling devices supported in a gimbal fashion for generating thrust in any optional direction, jet engines with backwards directed nozzles to be controlled within a range from a slantwise upward direction to a slantwise downward direction, and rocket engines with ejection nozzles to be controlled in right-and-left and up-and-down directions. During ascent of the space craft, at first the propelling devices, then the jet engines and at last the rocket engines are actuated so as to make the space craft reach and fly along a satellite orbit.

Abstract: An aircraft has a fuselage designed essentially as an aerostatic lift body and combined lift and propulsion devices which are articulated on the fuselage, are provided with propellers and form propulsion units and which in each case are tiltable between a lift position, in which the respective propeller rotation plane is essentially horizontal and the output shaft of the associated drive, said output shaft acting on the respective propeller shaft, is essentially vertical, and a propulsion position, in which the respective propeller rotation plane is essentially vertical and the output shaft of the associated drive, said output shaft acting on the respective propeller shaft, is essentially horizontal. The propeller rotation plane has all-round inclinability relative to the output shaft of the associated drive, said output shaft acting on the propeller shaft.

Abstract: A method for altitude control of airships in all the speed ranges which occur during operation has the following features:

Abstract: An aircraft has a fuselage designed essentially as an aerostatic lift body and combined lift and propulsion devices which are articulated on the fuselage, are provided with propellers and form propulsion units and which in each case are tiltable between a lift position, in which the respective propeller rotation plane is essentially horizontal and the output shaft of the associated drive, said output shaft acting on the respective propeller shaft, is essentially vertical, and a propulsion position, in which the respective propeller rotation plane is essentially vertical and the output shaft of the associated drive, said output shaft acting on the respective propeller shaft, is essentially horizontal. The propeller rotation plane has all-round inclinability relative to the output shaft of the associated drive, said output shaft acting on the propeller shaft.

Abstract: An aircraft has a fuselage designed essentially as an aerostatic lift body. Combined lift and propulsion devices are articulated on the fuselage, are provided with propellers and form propulsion units and which in each case can tilt between a lift position, in which the respective propeller rotation plane is essentially horizontal and a propulsion position, in which the respective propeller rotation plane is essentially vertical. Additionally the propeller rotation plane has all-round inclination relative to the output shaft of the associated drive device.

Abstract: In a novel hovering aircraft, an airfoil blade structure rotatable about a vertical axis comprises a set of upper blades and a set of lower blades, all having variable lift, the upper blades converging toward the lower blades from root to tip. Struts, located inboard of the blade tips, keep the tips of the upper and lower blades separate from each other to reduce interference effects, and also support motors and propellers.

Abstract: A hybrid aircraft is taught having VTOL, R-VTOL and S-STOL capabilities. The aircraft has a lifting body hull and four wing sections arranged in tandem which are pivotally moveable about their neutral axis. Each wing section has mounted thereon a pivotal propeller-rotor assembly for providing thrust substantially in a range between horizontal and vertical. The wings and propellers are integrated to the hull by an outrigger designed to be very stiff and to distribute forces from the wings and propellers to the hull. The hull is shaped to provide aerodynamic lift in an airstream and to facilitate construction by minimizing the number of panels of differing curvature required. The hull is formed of a pressure tensioned frame covered with semi-rigid panels, a lower cladding frame and bow and stem cladding nose cones. The semi-rigid panels covering the frame are formed of gas-tight and abrasion resistant laminate material and are connected to the frame by means of an interface rib and latch system.

Abstract: A stable and highly maneuverable lighter-than-air aircraft is provided. The aircraft includes a body portion which is supported beneath a balloon portion by a stem or axle. The balloon is fillable with a lighter-than-air gas and is sized to accept sufficient amounts of gas to make the aircraft buoyant. The balloon portion is rotationally fixed to the axle and the axle is rotationally journaled in the body. Thus, the balloon portion can rotate relative to the body portion and the body can selectively be rotated relative to the axle. A motor is housed in the body portion and is operable to propel the aircraft in a desired direction. The aircraft is operated such that the balloon portion rotates above the body portion without rotating the body portion. The rotation of the balloon portion provides stability to the aircraft and the ability for the body portion to rotate about the axle enables the aircraft to be highly maneuverable.

Abstract: The invention is a propulsion system for a lighter-than-air vehicle, the vehicle having a longitudinal, lateral and vertical axis. In detail, the propulsion system includes a thrust producing assembly rotatably mounted on the vehicle, the assembly rotatable about an axis of rotation in a plane at an acute angle to the vertical axis of the vehicle, the assembly rotatable in the plane from a position wherein the thrust axis of the assembly is aligned with the longitudinal axis to a position at least plus or minus ninety degrees thereto. A powerplant assembly is coupled to the thrust producing assembly to provide power thereto. The powerplant assembly includes a fuel efficient powerplant assembly mounted within the vehicle having sufficient power for cruise conditions, the fuel efficient powerplant having a output drive shaft coupled to the thrust producing assembly. A light weight, high power powerplant assembly is mounted directly to the thrust producing assembly having sufficient power for docking conditions.

Abstract: An omnidirectional propelling type of airship can be propelled in any direction in three-dimensions. The airship includes an airtight gas chamber, gas having a specific gravity smaller than that of air and filling the gas chamber, a section capable of accommodating men, cargo and the like, and propellers supported by gimbals and capable of propelling the airship in any spacial direction.

Abstract: The invention is a propulsion system for a lighter-than-air vehicle. In detail the propulsion system includes a pylon having a longitudinal axis and first and second ends, the first end of the pylon rotatably mounted to the vehicle and the second end extending outward from the vehicle. The pylon is rotatable about the first end in a plane perpendicular to the longitudinal axis of the vehicle. A thrust producing assembly is mounted on the second end of the pylon and is rotatable about an axis of rotation in a plane perpendicular to the longitudinal axis of the pylon. A powerplant assembly is coupled to the thrust producing assemblies to provide power thereto. An actuation system is provided for rotating the assembly about the axis of rotation. A second actuation system is provided for rotating the pylon about the first end.

Abstract: An acrobatic airship capable of making a perfect somersault, and a 360 degree roll in a limited small air space, without utilizing high-powered thrusters or sophisticated automatic control mechanisms. The airship has a rather thick and round axi-symmetrically shaped hull equipped with a pair of reversible thrusters on each side of the hull's nose area. Each thruster is also equipped with a tilting mechanism, which enables the thrust vector orientation to be changed independently. The airship has a set of tail fins as attitude stabilizers which do not have movable control surfaces. This acrobatic airship can be designed as a manned or unmanned craft, and is ideal for use in advertising and also as a camera platform, an observation vehicle for hazardous environments, and in various other industrial applications.

Abstract: An unmanned flight vehicle wherein two counter-rotating rotors are positioned within a toroidal fuselage and in which rotor pitch solely is utilized to generate all required lift, pitch, roll, yaw and vibration and stress control for the vehicle.

Abstract: A hybrid aircraft with a large non-rotating balloon chamber containing a lighter-than-air gas which provides a large static lifting force having a magnitude substantially greater than the weight of the aircraft with a support structure system which is substantially longer in length than in width which is encased by the balloon chamber the support structure system having two ends which protrude from the balloon chamber at opposite sides along the center line of the balloon chamber with a rotatable rotor frame suspended from the ends of the support structure system about the non-rotating balloon chamber. The craft has a plurality of blade airfoils connected to the rotor frame and oriented radially relative to the balloon chamber and which the angle of attack of each blade can be varied. A thrust means is mounted at or near the outboard end of the blade airfoils.

Abstract: A method and system for supporting an airborne vehicle in space over a predetermined location and for an extensive period, comprises coupling the airborne vehicle by cables to a plurality of unmanned aircraft each having its own propulsion system; controlling the unmanned aircraft to fly in circular orbits at equally-spaced angles around the airborne vehicle while coupled to the airborne vehicle, to tension the cables and thereby to support the airborne vehicle in space over the predetermined location; and supplying the unmanned aircraft with energy from an external source to maintain the unmanned aircraft in flight over an extended or indefinite period of time.

Abstract: A radio-controlled flying apparatus comprising an annular buoyant body and having an overall center of gravity below the center of buoyant force of the buoyant body. The annular buoyant body contains a gas of lighter weight than air. A main body is supported by the annular buoyant body by means of a dual-axis gimbal. The main body is provided with a pair of propellers which are rotatably supported by the main body and are driven by variable-speed motors into rotation in opposite directions. The main body is further provided with a rocking mechanism for causing said main body to rock about the dual-axis gimbal. An electric circuit resides in the main body for receiving a radio wave from an external transmitter to control the rocking mechanism and variable-speed motors. The electric components in the electric circuit are supplied their power from a battery carried on the main body.

Abstract: A lighter-than-air aircraft includes a rigid platform having cargo and passenger compartments and gas bags attached to the platform for holding a gas having a density less than air, thus imparting lift to the platform. The bags are arranged in pairs, there being a pair of spaced apart upper bags along the upper surface of the platform and a pair of spaced apart lower bags along the lower surface. While the bags cover portions of the upper and lower surfaces, both surfaces remain exposed along the longitudinal centerline of the platform, and here the platform is provided with vertical ducts and bays. The ducts house motors and propellers which drive air through the ducts and thus impart a vertically directed force to the platform. The bays hold containers which are lowered from and raised into the bays with a crane that moves along tracks extended along the upper surface of the platform.

Abstract: A flying object for collecting solar rays comprises a disk-shaped flying body equipped with floating and propelling means installed at the outer circumferential portions thereof. The flying object can detect its direction of flight and keep its position constant by means of the plural floating and propelling means. In addition, the flying object has a solar ray collecting device, equipped with solar ray collecting lenses. The solar rays collected by the solar ray collecting device are guided through an optical conductor cable into the flying object.

Abstract: An aerial load-lifting system including a lighter-than-air unit, such as a blimp, below which is suspended a powered heavier-than-air unit, such as a helicopter, for example. The latter unit produces thrust which can be directed vertically, up or down, or tilted for translational motion in any direction. The units are connected by a flexible tension member such as a cable. The upper, lighter-than-air unit is sufficiently high above the lower, heavier-than-air unit to permit the heavier-than-air-unit to freely control and maneuver itself and the payload suspended below it with minimal restraint from the lighter-than-air units.

Abstract: An aerial load-lifting system comprised of a lighter-than-air unit, such as a blimp, below which is suspended a powered heavier-than-air unit, such as a helicopter, for example. The latter unit produces thrust which can be directed vertically, up or down, or tilted for translational motion in any direction. The units are connected by a flexible tension member such as a cable. The upper, lighter-than-air unit is sufficiently high above the lower, heavier-than-air unit to permit the heavier than-air-unit to freely control and maneuver itself and the payload suspended below it with minimal restraint from the lighter-than-air units.

Abstract: An airship with provisions for vectored thrust provided by a plurality of controllable pitch rotor thrust producing units attached to the elongated aerostat hull spaced from and on opposite sides of the center of overall mass of the airship. The pitch control systems for the rotors of all thrust units include collective and cyclic pitch controls of the main, horizontally rotating lifting rotors and the control systems are interconnected to be operable by a master control which establishes both similar and differential pitch settings of the rotors of selected thrust units in a manner to establish vectored thrust in directions which establish the required amounts of vertical lift, propulsion thrust, trim and control forces to control all flight aspects of the airship.