Abstract: Certain aspects relate to a blended wing body aircraft with a fuel cell and methods of use. An exemplary aircraft includes a blended wing body, at least a propulsor mechanically affixed to the aircraft and configured to propel the aircraft, at least a first fuel store configured to store a first fuel, and at least a fuel cell configured to combine the first fuel with oxygen to produce electricity.

Abstract: To use launchpad based laser beam generators to stream 50+ kilowatt laser beams up through clear fused quartz discs located in the base of the rocket to super heat the steam in the rocket's pressure chamber for the purpose of increasing the thrusting power of the rocket. This rocket does not use fossil fuel, but rather it uses 99% pure hydrogen peroxide fuel, (H2O2) which flashes into steam without the use of combustion.

Abstract: An unmanned aerial vehicle includes a fuselage, a battery accommodation cavity, a battery pack, a battery circuit board, and a functional module. The battery accommodation cavity is disposed on the fuselage. The battery pack includes at least two battery blocks which are mounted inside the battery accommodation cavity. The battery circuit board is electrically connected to the battery blocks in the battery pack. The functional module is electrically connected to the battery circuit board, and the battery blocks in the battery pack supply power to the functional module via the battery circuit board at the same time.

Abstract: A high efficiency hydrogen fuel system for an aircraft at high altitude which utilizes compressors to compress air to a sufficiently high pressure for the fuel cell. Liquid hydrogen is compressed and then utilized in heat exchangers to cool the compressed air, maintaining the air at a temperature low enough for the fuel cell. The hydrogen is also used to cool the fuel cell as it is also depressurized prior to its entry in the fuel cell cycle. A water condensation system allows for water removal from the airstream to reduce impacts to the atmosphere. The hydrogen fuel system may be used with VTOL aircraft, which may allow them to fly at higher elevations. The hydrogen fuel system may be used with other subsonic and supersonic aircraft, such as with asymmetric wing aircraft.

Abstract: A propulsion system according to an exemplary embodiment of this disclosure, among other possible things includes a fuel storage tank that is configured to store a fuel in a compressed state, a power generation device that is configured to consume the fuel and generate an output, a fuel system that is configured to provide the fuel from the fuel storage tank to the power generation device, and an electrochemical compressor that is in communication with the fuel system. The electrochemical compressor is configured to gather residual fuel from the fuel system and communicate the gathered residual fuel to at least one of the power generation device and the fuel storage tank.

Abstract: Drive system for an aircraft, including: a propeller; electric motor; transmission system for transmitting positive torque from the motor to drive the propeller and negative torque from the propeller in windmill braking state to drive the motor; interface for inputting an input; first unit for controlling torque acting on the motor; second unit for detecting rotational speed of the motor; selection unit to select an active mode from propulsion mode and recovery mode, wherein the motor generates recovery energy in the recovery mode; and management system to control energy flow in an electrical system of the aircraft, the electrical system including the motor, is controlled according to the active mode; wherein the selection unit is configured to select the active mode according to the input, rotational speed, and predefined envelope, wherein the envelope indicates a maximum positive torque and minimum negative torque that depends on the rotational speed.

Abstract: The present invention discloses an unmanned aerial vehicle, including: a fuselage; a battery accommodation cavity, disposed on the fuselage; a battery pack, including at least two battery blocks and mounted inside the battery accommodation cavity; a battery circuit board, electrically connected to the battery blocks in the battery pack; and a functional module, electrically connected to the battery circuit board, the battery blocks in the battery pack supplying power to the functional module via the battery circuit board at the same time. By using the solution of the present invention, endurance of the unmanned aerial vehicle is increased.

Abstract: A payload module of a stratospheric drone including a casing (10), and payload equipment contained in the casing (10), wherein the casing includes a support structure (12) and a cover (15), the support structure being suitable for attachment to the drone at the front end thereof, relative to the direction of movement of the drone, and for extending forward from said front end, and in that the cover (15) and the payload equipment are supported by the support structure (12).

Abstract: A self-localization method and system to estimate the position of a tethered quadcopter using only the onboard sensors. Embodiments of the invention are based on the dynamics of the tethered quadcopter and the principles of an accelerometer. The estimated orientation angles of the tether were used to estimate the location of the quadcopter with respect to the connecting point of the tether, which can be a ground vehicle. The results generated by both the software simulation and actual experiments reveal the effectiveness and accuracy of embodiments of the present invention.

Abstract: An unmanned aerial vehicle for mounting a clamp to a line includes a body, a first propeller attached to the body, a second propeller attached to the body, and a third propeller attached to the body. The body is between at least one of the first propeller and the second propeller, the first propeller and the third propeller, or the second propeller and the third propeller. A guide is attached to the body and is configured to support the clamp for mounting to the line by flying the unmanned aerial vehicle toward the line. The guide is configured to support the clamp such that an imaginary clamp line between a first jaw of the clamp and a second jaw of the clamp when the clamp is in an arrested position is non-parallel to a plane intersecting the first propeller, the second propeller, and the third propeller.

Abstract: A gas turbine engine arrangement includes an accessory gearbox which is mounted so as to be aligned in an axial direction along the engine. The accessory gearbox may be recessed at least partly into a casing of the engine.

Abstract: The present invention discloses an unmanned aerial vehicle, including: a fuselage; a battery accommodation cavity, disposed on the fuselage; a battery pack, including at least two battery blocks and mounted inside the battery accommodation cavity; a battery circuit board, electrically connected to the battery blocks in the battery pack; and a functional module, electrically connected to the battery circuit board, the battery blocks in the battery pack supplying power to the functional module via the battery circuit board at the same time. By using the solution of the present invention, endurance of the unmanned aerial vehicle is increased.

Abstract: According to the present invention there is provided an aerial vehicle that is operable to fly, the aerial vehicle having at least a first and second subsystem that are operably connected, wherein the first subsystem comprises a first flight module, first one or more effectors that are selectively operable to generate a first force sufficient to cause the aerial vehicle to fly; and the second subsystem comprises a second flight module, second one or more effectors that are selectively operable to generate a second force sufficient to cause the aerial vehicle to fly; such that the first or second subsystem can be selectively used to fly the aerial vehicle not relying on the one or more effectors of the other subsystem. There is further provided a corresponding method for controlling an aerial vehicle.

Abstract: A counter rotating propeller system comprises a structure configured to control the front propeller outer slipstream and prop wash. Specifically disclosed is a structure configured to vary the effective hub-tip radius ratio of the rear propeller.

Abstract: The invention relates to a propeller ring (10) of a turbomachine (1), with variable-pitch blades (P), the propeller ring (10) comprising a substantially coaxial annular body (11) with a main axis (A) and a plurality of radial housings (12) uniformly distributed around the main axis (A), each radial housing (12) being designed to receive a bearing (13) for a root (14) of a blade (P) so as to allow the variable pitch of the blade (P), the radial housings (12) having a substantially ovoid cross-section in a plane (T) tangential to the annular body (11).

Abstract: The present invention extends to methods, systems, devices, and apparatus for remotely operated aerial vehicle with reduced cross-section area during forward flight. In one aspect, a remotely operated aerial vehicle is a rotor based Unmanned Aerial Vehicle (UAV) having a plurality of rotors. A remotely operated aerial vehicle includes a frame, a power source, a plurality of motors, and a corresponding plurality of fixed rotors. The frame includes a top surface. Each fixed rotor in the plurality of fixed rotors is mounted to a corresponding motor from among the plurality of motors. The corresponding motor controls the rotation of the fixed rotor. Each of the plurality of fixed rotors is mounted at a specified angle relative to the top surface. Mounting the fixed rotors at the specified angle minimizes the cross-sectional area of the frame when the remotely operated aerial vehicle flies in a specified direction.

Abstract: The present invention discloses an unmanned aerial vehicle, including: a fuselage; a battery accommodation cavity, disposed on the fuselage; a battery pack, including at least two battery blocks and mounted inside the battery accommodation cavity; a battery circuit board, electrically connected to the battery blocks in the battery pack; and a functional module, electrically connected to the battery circuit board, the battery blocks in the battery pack supplying power to the functional module via the battery circuit board at the same time. By using the solution of the present invention, endurance of the unmanned aerial vehicle is increased.

Abstract: The present invention discloses an unmanned aerial vehicle, including: a fuselage; a battery accommodation cavity, disposed on the fuselage; a battery pack, including at least two battery blocks and mounted inside the battery accommodation cavity; a battery circuit board, electrically connected to the battery blocks in the battery pack; and a functional module, electrically connected to the battery circuit board, the battery blocks in the battery pack supplying power to the functional module via the battery circuit board at the same time. By using the solution of the present invention, endurance of the unmanned aerial vehicle is increased.

Abstract: An Electro Hydro Dynamic, EHD, thruster (105) comprising a first set of electrodes (210), a second set of electrodes (220) and a supporting structure (103) for supporting the first set of electrodes (210) and the second set of electrodes (220). The EHD thruster (105) is configured to generate airflow of ionized air for cooling a heat sink (101). Further, the EHD thruster (105) is electrically isolated from the heat sink (101).

Abstract: Electrokinetic methods are described with the purpose of collecting assayable agents directed by creation of an electrokinetic potential well. Environmental agents such as biowarfare agents, pathogens, allergens or pollutants are collected autonomously. The dielectric fluid medium, such as air, is sampled by electrokinetic propulsion. A further embodiment for collection of pathogen samples entails exposing the sample to an electric plasma in the neighborhood of a high voltage electrode or electrodes, further transported through a potential well created at a sample collection device conductive liquids, such as oils may be sampled for the presence of contaminants, contaminating organisms or bio-degrading organisms.

Abstract: A method of producing accelerations without ejecting any material exhaust which relies on inducing mass fluctuations in conventional electrical circuit components and combining them with a mechanically coupled periodic thrust to produce propulsive forces without the ejection of any propellant. Ferroelectric force transducers, in particular, piezoelectric transducers, are driven by at least two phase-locked voltage waveforms so that the rest mass fluctuation and mechanical excursion needed to produce a stationary thrust are both produced in the transducer itself. Parametric amplification is used to achieve high amplitude, correctly phase-locked voltages of correct frequencies to activate the transducer by the simple addition of a DC voltage to the AC voltage of a single frequency driving signal. The driving voltage waveforms may be pulsed to maximize the thrust and reduce the duty cycle of the active components of the system.

Abstract: An aircraft (40). The aircraft (40) comprises a propulsion system comprising a pair of internal combustion engines (10) each driving an electrical power generator (56), each electrical power generator (56) being electrically coupled to a plurality of electrically driven propulsors (46). The propulsors (46) are located forward of a leading edge (45) of the wings (44) such that an airstream generated by the propulsors flows over the wings (44) in use. Each internal combustion engine (10) and electrical generator (56) is mounted on a respective wing (44) outboard of a centre of thrust (70) of the propulsors (46) on that wing (44).

Abstract: An aircraft with an electric propulsion arrangement which includes a fuselage, a wing system attached to the fuselage, and a tail unit attached to a rear part of the fuselage. The electric propulsion arrangement is arranged on each side of the fuselage, an electrical energy generator and electricity storage and supply devices are arranged substantially along a longitudinal axis of symmetry of the fuselage. The aircraft thus incorporates a hybrid motorization.

Abstract: A landing gear for an aircraft has a pair of spaced wheels, and a drive and steering arrangement operable to drive each of the wheels in either rotational direction. The drive and steering arrangement includes two permanent magnet rotors, with each of the permanent magnet rotors connected to rotate with one of the wheels. A single stator is positioned to drive both of the rotors. The drive and steering arrangement is mounted between the pair of wheels.

Abstract: A quadrotor UAV including ruggedized, integral-battery, load-bearing body, two arms on the load-bearing body, each arm having two rotors, a control module mounted on the load-bearing body, a payload module mounted on the control module, and skids configured as landing gear. The two arms are replaceable with arms having wheels for ground vehicle use, with arms having floats and props for water-surface use, and with arms having pitch-controlled props for underwater use. The control module is configured to operate as an unmanned aerial vehicle, an unmanned ground vehicle, an unmanned (water) surface vehicle, and an unmanned underwater vehicle, depending on the type of arms that are attached.

Abstract: A system for launching an unmanned aerial vehicle (UAV) payload includes a launch tube, liquid rocket, and launch control assembly. The rocket is positioned in the launch tube and contains the UAV payload. A booster assembly may include a canister partially filled with liquid. A gas cylinder is filled with compressed gas. The liquid is pre-pressurized by the gas or mixed with the gas right before launch such that, upon launch, liquid and gaseous thrust stages launch the rocket to a threshold altitude. The UAV payload deploys after reaching the threshold altitude. Optional stability tubes may be connected to the launch tube, which may be buoyant for water-based operations. An optional tether may be connected to the liquid rocket for arresting its flight prior to reaching apogee. The UAV payload is not launched directly by the gas/liquid mix. A method of launching the UAV payload is also disclosed.

Abstract: A method is presented for controlling thrust generated by aircraft engines. Engine thrust is controlled based on aircraft groundspeed and airspeed during the initial part of takeoff. Limiting thrust at low groundspeed during the initial phase of takeoff has significant benefits that reduce engine stress during this brief but critical phase leading to flight. Logical elements combine both groundspeed and airspeed in such a way that the operator perceives a smooth progressive thrust increase consistent with normal engine operation.

Abstract: An aircraft comprises an airframe, an electric propulsion system, a number of battery pods, and an engagement system. The number of battery pods has a physical connector system. The engagement system is attached to the airframe and is capable of engaging the physical connector system to connect the number of battery pods to the airframe.

Abstract: An aircraft comprises an airframe, an electric propulsion system, a number of battery pods, and an engagement system. The number of battery pods has a physical connector system. The engagement system is attached to the airframe and is capable of engaging the physical connector system to connect the number of battery pods to the airframe.

Abstract: A system and methods for reducing flow field velocity into a propeller is disclosed. An aerodynamic structure is enhanced to provide a reduced velocity flow field region, and a propeller is positioned in the reduced velocity flow field region.

Abstract: Flexible and resilient masts are connected by flexible and resilient inner and outer spars, and flexible cords radially connect the spars. A flexible material is attached to the cords. The assembly is wrapped around a rotatable cylindrical drum in the structure's stored configuration. Each mast is flexible only about an axis lying parallel to the axis of rotation of the drum, and is otherwise rigid. Each mast is linear when extended and has a bending stress when deformed into a non-linear configuration, such as when wrapped around the drum. When the structure is in its stored configuration, a restraining device opposes the bending stress and another prevents the drum from rotating. Upon disengagement of the restraining devices, the stored bending strain energy forces the drum to rotate and the masts to extend into the deployed configuration and thereby unfurl the flexible material.

Abstract: A method for assembling a gas turbine engine to prevent rotor over-speeding is described. The method includes serially coupling a first fuel system interface to a second fuel system interface, such that at least one of the first fuel system interface and the second fuel system interface is coupled to the gas turbine engine. The method also includes coupling a control system to the first fuel system interface and to the second fuel system interface. The control system is configured to identify an occurrence of an over-speed condition. The method also includes programming the control system to discontinue fuel flow to the engine when both the first fuel system interface and the second fuel system interface indicate an over-speed condition has occurred.

Abstract: A vehicle is described having an engine to provide motive transportation and a work producing device used to provide power and thermal conditioning to a payload aboard the vehicle. In one form the work producing device provides power to the payload separate from a network powered by the engine that provides motive transportation. The payload can be a directed energy device in one embodiment. The vehicle can take the form of an aircraft which can be configured to receive the work producing device in a cargo bay/payload bay and/or a pod.

Abstract: A communication system for supporting communications with a target market area. The system includes one or more solar-powered aircraft maintained in, or successively passing through, flight stations or flight patterns around the market area. Each of the aircraft targets limited beamwidth communication antennas on a substantial portion of the target market area. The control system is configured to fly selective flight patterns depending on the aircraft characteristics and the flight conditions. The flight patterns may emphasize high-power-generation patterns such as flying away from the sun for aircraft with wing-mounted solar cells.

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: A propeller or propeller drive, the propeller being carried by a support shaft (3) which projects from the body (53) of the missile or vehicle and about which the propeller rotates, the drive unit for the propeller being situated in front of the propeller (23) in the propulsion direction or in the propeller spinner (1). According to the invention it is provided that the drive unit has at least one gas turbine (55), optionally a multiple-stage gas turbine, which is secured to the drive shaft and which drives it or jointly rotates with it, and that the drive shaft (6) is traversed by the support shaft (3) or is mounted thereon in a rotating manner and drives the propeller (23), optionally by way of a gear mechanism (14) situated between the turbine (55) and the propeller (23).

Abstract: The invention relates to an electrolysis system. Said system can be utilized in a nuclear fusion process, on roof of a ferromagnetic aircraft in preferred embodiment. Said electrolysis system will utilize electric energy produced by said aircraft at no cost. Said energy will be provided to an array of electrodes to electrolyze water or seawater to produce protons and electrons, and with B-11 isotope ions, vaporized out of source on board craft, a fusion spherical plasma can be produced on roof of said aircraft, for a nuclear fusion reaction. Stored energy produced by electrolysis system, can also be used for other purposes. Said fusion spherical plasma is produced at essentially no cost, other than cost of electrolysis system and aircraft. Three aircraft will be utilized in preferred embodiment, all three craft utilizing an electrolysis system, though only one craft, the ferromagnetic craft alone, producing the B-11 isotope ion.

Abstract: An aircraft in the form of multi-stage missile 1 with a spiral inducing assembly 2 which is capable of inducing the missile to travel in a continuous spiraling motion without the missile rolling. A ramjet 6b is attached to a tube 3 that is able to rotate around the encircled part of the fuselage. The ramjet 6b is able to rotate in a pivoting manner on the rotate-able tube 3 with respect to the rotate-able tube 3, thereby changing their pitch relative to the longitudinal axis of the rotate-able tube 3. Ramjet 6b is rotated to a greater than another ramjet on the right side of the tube 3. The difference in degree of rotation between the ramjets makes the ramjet 6b exert a greater force on the rotate-able tube 3 than the ramjet on the right side when the ramjets are rotated in the same direction. The imbalance between the rotational forces thus causes the rotate-able tube 3 to rotate. When rotated, the ramjets would exert a lateral force on the rotate-able tube 3.

Abstract: An aircraft in the form of multi-stage missile 1 with a spiral inducing assembly 2 which is capable of inducing the missile to travel in a continuous spiraling motion without the missile rolling. A ramjet 6b is attached to a tube 3 that is able to rotate around the encircled part of the fuselage. The ramjet 6b is able to rotate in a pivoting manner on the rotate-able tube 3 with respect to the rotate-able tube 3, thereby changing their pitch relative to the longitudinal axis of the rotate-able tube 3. Ramjet 6b is rotated to a greater than another ramjet on the right side of the tube 3. The difference in degree of rotation between the ramjets makes the ramjet 6b exert a greater force on the rotate-able tube 3 than the ramjet on the right side when the ramjets are rotated in the same direction. The imbalance between the rotational forces thus causes the rotate-able tube 3 to rotate. When rotated, the ramjets would exert a lateral force on the rotate-able tube 3.

Abstract: This invention relates to a plasma gun utilized in a plasma based aircraft maintained in a flight mode by rotating plasma vortices located above and beneath said aircraft. Plasma produced by aircraft is utilized by said plasma gun to facilitate initial take off of craft, and also to accelerate aircraft speed, or, within an emergency, as needed. Said aircraft can also eject plasma through aircraft central shaft or within any direction from sides of said craft, for escape, evasion or normal accelerated flight. Preferred embodiment for said plasma gun, is a coaxial plasma gun, utilizing the large capacitance potential of aircraft, the large supply of aircraft produced plasma off said capacitors, or from uninsulated conducting wires, and also utilizing the strong Lorentz force existing within craft. The plasma produced by ionization within craft strong magnetic field, will enable this craft to rapidly avoid impediments to flight, or oncoming dangers.

Abstract: An air vehicle propulsion system incorporates an engine core with a power shaft to drive an outer blade row. The power shaft is extends through and is supported by a counter rotation transmission unit which drives an inner blade row in counter rotational motion to the outer blade row. The counter rotation transmission unit exchanges power from the engine core with the shaft. An actuator engages the shaft for translation from a first retracted position to a second extended position.

Abstract: A propulsion method employing gyroscopes (1,2) with electric motors (4) which are being moved along a closed path in the spacecraft. Rotation axis of the gyroscopes are rotated periodically relative to movement direction so that gyroscopic effect is only obtained during movement in one direction. Thereby a gyroscopic resistance difference is obtained and used as a propulsion force. Another application is to use gyroscopes connected to generators in order to decelerate a spacecraft, transforming the moment created in gyroscope during deceleration into the electrical energy, distribute it to the space as heat transfer by means of radiation through the heat resistant panels.

Abstract: An apparatus and method for transmitting a rotary input into counter-rotating outputs is disclosed herein. An exemplary apparatus for performing the method includes a planetary gear set having a sun gear rotatable by a rotary input, a plurality of planet gears in meshed engagement with the sun gear, a carrier coupling the plurality of planet gears together, and a ring gear encircling and in meshed engagement with the plurality of planet gears. The exemplary apparatus also includes a first shaft member coupled to the carrier for transmitting motion in a first rotational direction. The exemplary apparatus also includes a second shaft member coupled to the ring gear for transmitting motion in a second rotational direction opposite the first rotational direction. The first shaft member at least partially encircles the second shaft member.

Abstract: In order to provide noise suppression, bumps or undulations are provided on a nozzle surface in order to vary the convergent-divergent ratio between that surface and an opposed nozzle surface. By such an approach, a circumferential variation in the shock cell pattern is created and the flow is deflected so as to enhance turbulent mixing thereby suppressing noise.

Abstract: The present invention pertains to a solar cell module comprising at least one photovoltaic element encapsulated between a front layer on its light receiving surface side and a back layer, said front layer comprising at least one layer comprising a tetrafluoroethylene (TFE) polymer [polymer (F)], said polymer (F) comprising: recurring units derived from TFE; and from 15 to 25% wt of recurring units derived from at least one perfluoromonomer [monomer (CM)] chosen among: (i) perfluoroalkylvinylethers complying with formula CF2?CFORf1, in which Rf1 is a C1-C6 perfluoroalkyl, e.g. —CF3, —C2F5, —C3F7; and/or (ii) perfluoro-oxyalkylvinylethers complying with formula CF2?CFOX0, in which X0 is a C1-C12 perfluorooxyalkyl having one or more ether groups, like perfluoro-2-propoxy-propyl; and (iii) mixtures thereof. Still objects of the invention are a process for the manufacture of the solar cell module as above defined and its use for producing current to external sources, e.g. for powering a fixed-wing aircraft.

Abstract: An apparatus which exhibits properties allowing it to levitate and travel utilizing magnetic energy.

Abstract: An aircraft including a longitudinal fuselage, at least two lateral wings connected symmetrically one on each side of the fuselage and at least one engine pod fixed to each lateral wing via an engine support pylon. At least one profiled bearing rod is positioned on each of the engine support pylons so as to generate a propulsive resultant force under action of an oblique air flow.

Abstract: An exemplary embodiment of the present invention sets forth an exemplary bi-plane air vehicle. The air vehicle may include, a plurality of wings coupled to one another in substantially a box configuration, wherein the bi-plane air vehicle has no tail.

Abstract: Integrated propulsion systems and methods for blended wing aircraft are disclosed. In one embodiment, a propulsion system at least one engine operatively disposed within an engine flow duct having an engine inlet and an engine exhaust aperture, and at least one fan operatively disposed within a fan flow duct having a fan inlet and a fan exhaust aperture. The engine and fan rotational axes extending at least approximately along a lengthwise direction of the aircraft, the fan flow duct being separate from the engine flow duct. A transmission assembly is operatively coupled between the at least one engine and the at least one fan, the transmission assembly being configured to transmit a rotary output from the at least one engine to rotate the at least one fan.

Abstract: A flying craft has an aerodynamic aircraft fuselage structure preferably disc shaped. A pair of coaxial electrokinetic motor-generators are mounted concentrically, and preferably centered within the disc shaped structure of the craft. Each of the motors is toroidal in configuration, providing a ring-shaped stator and rotor portions. The rotor portions of the motors drive counter rotating fans which are electro-magnetically levitated. The structure is open to the fans so that air may be drawn into the structure and expelled downward providing vertical lift to the aircraft. By use of auxiliary air braking flaps and electrokinetic thrusters, the craft may be tilted so as to develop a desired horizontal thrust. By impulse breaking one of the fans through tracking solenoids at different points around the stator, the aircraft may be made to rotate about its own vertical axis for changing direction. By a series of sudden braking of the motors the craft may be made to move by inertial reaction.