ELECTRIC AIRBALOON, .

[2275] AT LEAST ONE: Jet . Rotor-craft. Air-. . Blimp and dirigibles. Rotor craft. Auto Gyro. Gyro plane. . Monoplane. Bi-plane. Supersonic lifting body. Civil . Freight airplane. Passenger airplane. Business jet. Private Jet. Cargo plane. Unmanned autonomous cargo aircrafts. Drone, autonomous aerial vehicle. Solar plane. Electric battery powered planes. Airship. Solar hybrid Plane. Solar hybrid amphibian aerial vehicle. Sail Plane. airplane rotary aircraft orbit copter. gyro plane helicopter amphibian land plane. Sea- plane. float plane. flying boat. (Blimps & Dirigibles): Like balloons, airships use hot air and/or lighter-than- air gases to generate lift. But unlike balloons, they also carry one or more engines and propellers to generate thrust and have aerodynamic control surfaces. Hang gliding, sport of flying in lightweight nonpowered aircraft. heavier than air (aerodyne) engine driven airplane rotary wing aircraft gyro plane helicopter amphibian land plane, seaplane float plane flying boat.

ELECTRIC ROTARY WING AIRCRFTS.

[2276] Field of invention This invention relates to vertical propulsion turbine rotor and electric generator including electric machines and manual navigation controllers for and rotary wing aircraft and more particularly to helicopters with reduced blade length and increased speed and maneuverability including new possibilities and features. Helicopter in which in-plane Description of the prior art Sustainable and Zero emission helicopter with new means for navigating and power generating for electric flying vehicles.

BACKGROUND OF THE INVENTION

[2277] A helicopter, or chopper, is a type of in which lift and thrust are supplied by rotors. This allows the helicopter to take off and land vertically, to hover, and to fly forward, backward, and laterally. These attributes allow helicopters to be used in congested or isolated areas where fixed-wing aircraft and many forms of VTOL (Vertical Takeoff and Landing) aircraft cannot perform. The Electric aircraft is navigated by the main rotor and and turbine engines and boosters comprising electric generators for power supply.

[2278] Turbine rotor applicable generating thrust is applicable for airborne and flying objects, and tethered unmanned aircraft. Radio controlled and autonomous and drones having a physical link with the ground by means of satellite connection and radio transmitters, comprising A turbine rotor with at least one blade, Pitch adjustable mounted to the hub, rotor blade horizontal and vertical angle adjustable turbine rotor. Tilt able roto hub with swash mechanism and unit operable mounted with the disturbed drive shaft. Manual controller having a stick made on the upper Centre of the controller sphere and digital automated controllers. An example of application of the turbine machines for generating electric current and for propulsion of the aircraft.

[2279] A helicopter main rotor or rotor system is the combination of several rotary (rotor blades) and a control system that generates the aerodynamic lift force that supports the airborne weight of the helicopter, and the thrust that counteracts aerodynamic drag in forward flight. Each main rotor is mounted on a vertical mast over the top of the helicopter, as opposed to a helicopter tail rotor, which connects through a combination of drive shaft(s) and gearboxes along the tail boom. The blade pitch is typically controlled by a swashplate connected to the helicopter flight controls. Helicopters are one example of rotary-wing aircraft (rotorcraft).

[2280] The tail rotor is a smaller rotor mounted so that it rotates vertically or near-vertically at the end of the tail of a traditional single-rotor helicopter. The tail rotor's position and distance from the center of gravity allow it to develop thrust in the same direction as the main rotor's rotation, to counter the torque effect created by the main rotor. Tail rotors are simpler than main rotors since they require only collective changes in pitch to vary thrust. The pitch of the tail rotor blades is adjustable by the pilot via the anti-torque pedals, which also provide directional control by allowing the pilot to rotate the helicopter around its vertical axis. The tail rotor is made open besides the tailfin and tail rotor arranged operable in the tail between the vertical fins. A helicopter may comprise horizontal tail wings and vertical tail wings upward end below the tail rotor.

[2281] The common helicopter tail rotor drive system consists of a shaft powered from the main transmission and a gearbox mounted at the end of the tail boom. The drive shaft may consist of one long shaft or a series of shorter shafts connected at both ends with flexible couplings, that allow the drive shaft to flex with the tail boom. The gearbox at the end of the tail boom provides an angled drive for the tail rotor and may also include gearing to adjust the output to the optimum rotational speed for the tail rotor, measured in rotations per minute (RPM). On larger helicopters with a tail pylon, intermediate gearboxes are used to transition the tail rotor drive shaft from along the tail boom to the top of the pylon. The tail rotor pylon may also serve as a vertical stabilizing airfoil, to alleviate the power requirement for the tail rotor in forward flight. The tail rotor pylon may also serve to provide limited antitorque within certain airspeed ranges, in the event of the tail rotor flight controls fail. About 10% of the engine power goes to the tail rotor.

[2282] The is blade adjustable by means of a collective pitch mechanism or cyclic pitch are both applied for the digital helicopter and rotor hub mounted pitch system. The swash plates with a stationary member and rotating mechanisms titling angular with respect to the mast is adjustable in force and aft plane and in the lateral plane. The blade is connected members are operable connected to the plurality of rotor blades and control horn operable connected with the blade connecting member. With at least one hydraulic, pneumatic or electro mechanical actuator connected with the control horn. At least one actuator is operable connected to the swashplate assembly to the actuators. The rotor and airframe is suspended with a kinematic connection for stabilization of the airframe. The rotor head and blades include harmonic vibration.

[2283] The aircraft may comprise flexible and retractable lifting rotor blades and open core rotor head. With bladelets arranged perpendicular that can be retracted in the center cavity. The retractable propellers comprise, a telescopic actuator mounted shaft. Pivoting and locking blade and rotor head.

[2284] Helicopter with manual folding rotor blades for reducing the blade surface and parking multiple helicopters adjacent. Folding the plurality of blades in a group along the tail boom. The blade connecting mechanism such as a knuckle joint or universal joint mounted with the hub and shaft operable in a guiding ring in which the blade holder is movable by sliding the blade holder with the blade toward the tail.

[2285] The tail rotor system rotates airfoils, small wings called blades, that vary in pitch to vary the amount of thrust they produce. The blades most often utilize a composite material construction, such as a core made of aluminum honeycomb or plasticized paper honeycomb, covered in a skin made of aluminum or carbon fiber composite. Tail rotor blades are made with both symmetrical and asymmetrical airfoil construction. The pitch change mechanism uses a cable control system or control tubes that run from the anti-torque pedals in the cockpit to a mechanism mounted on the tail rotor gearbox. In larger helicopters, the pitch change mechanism is augmented by a hydraulic power control servo. In the event of a hydraulic system failure, the mechanical system is still able to control the tail rotor pitch, though the control resistance felt by the pilot will be considerably greater.

[2286] The digital helicopter electric driven tail rotor turbine machine is powered by the helicopter's main electric power supply comprises electric regulative circuits and semiconductor components including converters and charging units, on circuit boards in a isolated cage and connected by cable wiring with the rechargeable batteries and electric generators, and rotates at a speed proportional to that of the main rotor. In both piston and turbine powered helicopters, the main rotor and the tail rotor are mechanically connected through a freewheeling clutch system, which allows the rotors to keep turning in the event of an engine failure by mechanically de-linking the engine from both the main and tail rotors. During , the momentum of the main rotor continues to power the tail rotor and allow directional control. To optimize its function for forward flight, the blades of a tail rotor have no twist to reduce the profile drag, because the tail rotor is mounted with its axis of rotation perpendicular to the direction of flight.

[2287] Cable ducts are electrically isolated for emotion and radiation penetrating the data wiring and cables. The dusts comprise hinged lids that are screwed and closed by antivibration washers and screws. The duct accommodates kilometers of electric with supplement insulated folly of electric whirring.

[2288] Helicopters also apply conventional anti-torque controls instead of the tail rotor, such as the ducted fan (called Fenestron or FANTAIL) and NOTAR. NOTAR provides anti-torque similar to the way a wing develops lift through the use of the Coandă effect on the tail boom. And the Gyroscopic rotor applied for the tattered rotary wing turbine generator.

[2289] The use of two or more horizontal rotors turning in opposite directions is another configuration used to counteract the effects of torque on the aircraft without relying on an anti-torque tail rotor. This allows the power normally required to drive the tail rotor to be applied to the main rotors, increasing the aircraft's lifting capacity. There are several common configurations that use the counter-rotating effect to benefit the rotorcraft:

[2290] Tandem rotors are differently arranged then regarding the coaxial dual rotor. The tandem rotors consists of two counter-rotating rotors with one mounted behind the other.

[2291] are two counter-rotating rotors mounted one above the other with the same axis.

[2292] Intermeshing rotors are two counter-rotating rotors mounted close to each other at a sufficient angle to let the rotors intermesh over the top of the aircraft without colliding.

[2293] Transverse rotors are pair of counter-rotating rotors mounted at each end of the wings or outrigger structures. Now used on , some early model helicopters had used them.

[2294] Quadcopters have four rotors often with parallel axes (sometimes rotating in the same direction with tilted axes) which are commonly used on model aircraft.

[2295] designs let the rotor push itself through the air and avoid generating torque.

AIRCRAFT ENGINE AND TURBOSHAFT.

[2296] The number, size and type of engine(s) used on a helicopter determines the size, function and capability of that helicopter design. The electric radial engine is a reciprocating type of electric engine configuration in which the cylinders "radiate" outward from a central crankcase like the spokes of a wheel. It resembles a stylized star when viewed from the front, and is called a "star engine". Other electric engines with a plurality of electric linear pistons motors and the coaxial geared machines including the Electromagnetic machine.

[2297] Turbine engine, Turboshafts are also more reliable than piston engines, especially when producing the sustained high levels of power required by a helicopter. The turboshaft engine is able to be scaled to the size of the helicopter being designed, so that all but the lightest of helicopter models are powered by turbine engines today.

[2298] Special jet combustion engines developed to drive the rotor from the rotor tips are referred to as tip jets. Tip jets powered by a remote compressor are referred to as cold tip jets, while those powered by combustion exhaust are referred to as hot tip jets.

[2299] Horizontal propulsion turbines are made beside the fuselage oriented in traveling direction with extending wing or mounted on short pilons to the fuselage which may resemble a wale shaped fuselage. The turbine machine can be made with the turbine machine in figure 3. With a single turbine rotor or figure 4. With dual rotors displacing large volumes of air for generating horizontal propulsive forces. The turbine can be made with a combustion section as jet boosters. The boosters are applied after takeoff and are electrically driven by the generators of the aircraft. The engine turbines are electromagnetically driven by the stator solenoids of coil wiring for creating a traveling magnetic field that propels the copper ring on the inner rotor hub for rotation at very high velocities.

[2300] Some radio-controlled helicopters and smaller, helicopter-type unmanned aerial vehicles, use electric motors. Radio-controlled helicopters may also have piston engines that use fuels other than gasoline, such as nitromethane. Some turbine engines commonly used in helicopters can also use biodiesel instead of jet fuel. These devices are battery powered and electric generative aerial vehicles like drones etc.

{2301] Human-powered helicopters are also available that can be motorized with the turbine machines and equipped with electric generator.

NAVIGATION AND FLIGHT CONTROLERS.

[2302] Existing helicopter has four flight control inputs. These are the cyclic, the collective, the anti-torque pedals, and the throttle. The cyclic control is usually located between the pilot's legs and is commonly called the cyclic stick or just cyclic. On most helicopters, the cyclic is like a joystick. However, the some helicopters have a unique teetering bar cyclic control system and a few helicopters have a cyclic control that descends into the cockpit from overhead.

[2303] The control is called the cyclic because it changes the pitch of the rotor blades cyclically. The result is to tilt the rotor disk in a particular direction, resulting in the helicopter moving in that direction. If the pilot pushes the cyclic forward, the rotor disk tilts forward, and the rotor produces a thrust in the forward direction. If the pilot pushes the cyclic to the side, the rotor disk tilts to that side and produces thrust in that direction, causing the helicopter to hover sideways.

[2304] The collective pitch control or collective is located on the left side of the pilot's seat with a settable friction control to prevent inadvertent movement. The collective changes the pitch angle of all the main rotor blades collectively (i.e. all at the same time) and independently of their position. Therefore, if a collective input is made, all the blades change equally, and the result is the helicopter increasing or decreasing in altitude.

[2305] The anti-torque pedals are located in the same position as the rudder pedals in a fixed-wing aircraft, and serve a similar purpose, namely to control the direction in which the nose of the aircraft is pointed. Application of the pedal in each direction changes the pitch of the tail rotor blades, increasing or reducing the thrust produced by the tail rotor and causing the nose to yaw in the direction of the applied pedal. The pedals mechanically change the pitch of the tail rotor altering the amount of thrust produced. In the digital electric helicopter this feature is controlled by the automated system and digital gyro sensing system units whereby the paddles are omitted and the copter vertical pitch is controlled by the ball rotated to the left or to the right by means of the tail rotor or turbines. The extension on the navigational sphere is a joystick.

[2306] Helicopter rotors are designed to operate in a narrow range of RPM. The throttle controls the power produced by the engine, which is connected to the rotor by a fixed ratio transmission. The purpose of the throttle is to maintain enough engine power to keep the rotor RPM within allowable limits so that the rotor produces enough lift for flight. In single-engine helicopters, the throttle control is a motorcycle-style twist grip mounted on the collective control, while dual-engine helicopters have a power lever for each engine.

[2307] A swashplate controls the collective and cyclic pitch of the main blades. The swashplate moves up and down, along the main shaft, to change the pitch of both blades. This causes the helicopter to push air downward or upward, depending on the angle of attack. The swashplate can also change its angle to move the blades angle forwards or backwards, or left and right, to make the helicopter move in those directions. The turbine machines have different types of swash mechanisms whereby not excluding existing swash mechanisms for tilting the rotor hub.

[2308] A aircraft or personal flying vehicle with a plurality of rotary turbine rotors mounted in a partial shroud or concentrator of circular shape wherein rotatable mounted with respect to the shroud. The turbines are equipped with an electric motor in the hub and electrically connected. The turbine rotors are mounted tillable with the shroud and mounted rods and actuators. The shroud is mounted on a pylon, on a wing extension or in the wing, in a corresponding diameter aperture of the rotor with a minimum spatial gap. Navigation is obtained by tilting the blades collectively in equal direction and 360*, by means of the gyroscopic manual controllers. The turbine rotor can navigate the craft by alternating rotating velocities individually and in assembly depending on the plurality of electric turbine rotors. An Accelerometer and unit are made in the hub and around the axis. Electric wiring and optical cables are harnessed and ducted trough conduits and mated with the power supply and control unit.

VIBRATION.

[2309] Helicopters also vibrate; an unadjusted helicopter can easily vibrate so much that it will shake itself apart. To reduce vibration, all helicopters have rotor adjustments for height and weight. Blade height is adjusted by changing the pitch of the blade. Weight is adjusted by adding or removing weights on the rotor head and/or at the blade end caps. Most also have vibration dampers for height and pitch. Some also use mechanical feedback systems to sense and counter vibration. Usually the feedback system uses a mass as a "stable reference" and a linkage from the mass operates a flap to adjust the rotor's angle of attack to counter the vibration. Adjustment is difficult in part because measurement of the vibration is hard, usually requiring sophisticated accelerometers mounted throughout the airframe and gearboxes. The most common blade vibration adjustment measurement system is to use a stroboscopic flash lamp, and observe painted markings or colored reflectors on the underside of the rotor blades. The traditional low-tech system is to mount colored chalk on the rotor tips, and see how they mark a linen sheet. Gearbox vibration most often requires a gearbox overhaul or replacement. Gearbox or drive train vibrations can be extremely harmful to a pilot. The most severe being pain, numbness, loss of tactile discrimination and dexterity.

Maximum speed limit [2310] The main limitation of the helicopter is its low speed. The reasons a helicopter cannot fly as fast as a fixed- wing aircraft is simply because it generates a vertical propulsion while speeding horizontally whereby horizontal and vertical air collides. When the helicopter is hovering, the outer tips of the rotor travel at a speed determined by the length of the blade and the rotational speed. In a moving helicopter, however, the speed of the blades relative to the air depends on the speed of the helicopter as well as on their rotational speed. The airspeed of the advancing rotor blade is much higher than that of the helicopter itself. It is possible for this blade to exceed the speed of sound, and thus produce vastly increased drag and vibration.

[2311] At the same time, the advancing blade creates more lift traveling forward, the retreating blade produces less lift. If the aircraft were to accelerate to the air speed that the blade tips are spinning, the retreating blade passes through air moving at the same speed of the blade and produces no lift at all, resulting in very high torque stresses on the central shaft that can tip down the retreating-blade side of the vehicle, and cause a loss of control. Dual counter-rotating blades prevent this situation due to having two advancing and two retreating blades with balanced forces.

[2312] Because the advancing blade has higher airspeed than the retreating blade and generates a dissymmetry of lift, rotor blades are designed to "flap" – lift and twist in such a way that the advancing blade flaps up and develops a smaller angle of attack. Conversely, the retreating blade flaps down, develops a higher angle of attack, and generates more lift. At high speeds, the force on the rotors is such that they "flap" excessively, and the retreating blade can reach too high an angle and . For this reason, the maximum safe forward airspeed of a helicopter is given a design rating called VNE, velocity, never exceed. In addition, it is possible for the helicopter to fly at an airspeed where an excessive amount of the retreating blade stalls, which results in high vibration, pitch-up, and roll into the retreating blade.

ROTORY WING AIRCRAFT APPLICATIONS.

[2313] Due to the operating characteristics of the helicopter, its ability to take off and land vertically, and to hover for extended periods of time, as well as the aircraft's handling properties under low airspeed conditions, it has been chosen to conduct tasks that were previously not possible with other aircraft, or were time- or work- intensive to accomplish on the ground. Today, helicopter uses include transportation of people and cargo, military uses, construction, firefighting, search and rescue, tourism, medical transport, law enforcement, agriculture, news and media, and aerial observation, among others. They can be used for Reflection seismology or recreation.

[2314] A helicopter used to carry loads connected to long cables or slings is called an aerial crane. Aerial cranes are used to place heavy equipment, like radio transmission towers and large air conditioning units, on the tops of tall buildings, or when an item must be raised up in a remote area, such as a radio tower raised on the top of a hill or mountain. Helicopters are used as aerial cranes in the logging industry to lift trees out of terrain where vehicles cannot travel and where environmental concerns prohibit the building of roads. These operations are referred to as longline because of the long, single sling line used to carry the load.

[2315] The largest single non-combat helicopter operation in history was the disaster management operation following the 1986 Chernobyl nuclear disaster. Hundreds of pilots were involved in airdrop and observation missions, making dozens of sorties a day for several months.

[2316] "Heli tack" is the use of helicopters to combat wildland fires. The helicopters are used for aerial firefighting (water bombing) and may be fitted with tanks or carry Heli buckets. Heli buckets, such as the Bambi bucket, are usually filled by submerging the bucket into lakes, rivers, reservoirs, or portable tanks. Tanks fitted onto helicopters are filled from a hose while the helicopter is on the ground or water is siphoned from lakes or reservoirs through a hanging snorkel as the helicopter hovers over the water source. Heli-tack helicopters are also used to deliver firefighters, who rappel down to inaccessible areas, and to resupply firefighters. Common firefighting helicopters include variants of the Bell 205 and the Erickson S-64 Aircrane helitanker.

[2317] Helicopters are used as air ambulances for emergency medical assistance in situations when an ambulance cannot easily or quickly reach the scene, or cannot transport the patient to a medical facility in time. Helicopters are also used when patients need to be transported between medical facilities and air transportation is the most practical method. An air ambulance helicopter is equipped to stabilize and provide limited medical treatment to a patient while in flight. The use of helicopters as air ambulances is often referred to as "MEDEVAC", and patients are referred to as being "airlifted", or "medevaced".

[2318] An autogiro (sometimes called gyrocopter, gyroplane, or rotor-plane) utilizes an unpowered rotor, driven by aerodynamic forces in a state of autorotation to develop lift, and an engine-powered , like that of a fixed- wing aircraft having the same, to provide thrust. While similar to a helicopter rotor in appearance, the autogiro’s rotor must have air flowing up and through the rotor disk in order to generate rotation. Early autogiros resembled the fixed-wing aircraft of the day, with wings and a front-mounted engine and propeller in a tractor configuration to pull the aircraft through the air. Late-model autogiros feature a rear-mounted engine and propeller in a pusher configuration.

[2319] The rotor of a is normally driven by its engine for takeoff and landing – hovering like a helicopter with anti-torque and propulsion for forward flight provided by one or more propellers mounted on short or stub wings. As power is increased to the propeller, less power is required by the rotor to provide forward thrust resulting in reduced pitch angles and rotor blade flapping. At cruise speeds with most or all of the thrust being provided by the propellers, the rotor receives power only sufficient to overcome the profile drag and maintain lift. The effect is a rotorcraft operating in a more efficient manner than the freewheeling rotor of an autogiro in autorotation, minimizing the adverse effects of of helicopters at higher airspeeds.

[2320] A rotor or gyro is an unpowered rotary-wing aircraft. Like an autogiro or helicopter, it relies on lift created by one or more sets of rotors in order to fly. Unlike a helicopter, autogiro’s and rotor do not have an engine powering their rotors, but while an autogiro has an engine providing forward thrust that keeps the rotor turning, a has no engine at all, and relies on either being carried aloft and dropped from another aircraft, or by being towed into the air behind a car or boat. The turbine rotor of figure two can also be applied for propulsion wherein the hub the electric magnetic motor is arranged with electromagnets and a copper cylinder rightly mounted in the inner hub circumferential, comprising rotary electric connecting carbon brushes with copper rings for electric supply.

[2321] Tandem rotor helicopters have two large horizontal rotor assemblies mounted one in front of the other. Currently this configuration is mainly used for large cargo helicopters.

[2322] Transverse rotor rotorcraft have two large horizontal rotor assemblies mounted on the wing ends of both wings.

[2323] A is an aircraft which generates lift and propulsion by way of one or more powered rotors (sometimes called proprotors) mounted on rotating engine pods or nacelles usually at the ends of a fixed wing or an engine mounted in the fuselage with drive shafts transferring power to rotor assemblies mounted on the wingtips. It combines the vertical lift capability of a helicopter with the speed and range of a conventional fixed- wing aircraft. For vertical flight, the rotors are angled so the plane of rotation is horizontal, lifting the way a helicopter rotor does. As the aircraft gains speed, the rotors are progressively tilted forward, with the plane of rotation eventually becoming vertical. In this mode, the wing provides the lift, and the rotor provides thrust as a propeller. Since the rotors can be configured to be more efficient for propulsion (e.g. with root-tip twist) and it avoids a helicopter's issues of retreating blade stall, the tiltrotor can achieve higher speeds than helicopters.

[2324] A tiltrotor aircraft differs from a in that only the rotor pivots rather than the entire wing. This method trades off efficiency in vertical flight for efficiency in STOL/STOVL operation.

[2325] The present invention relates to a Horizontal blade adjustable and Pitch Adjustable Tilting turbine rotor. Applicable for vertical and horizontal propulsion for flying rotary wing aircrafts and fixed wind aircrafts and for marine vessels including submarines. The rotor comprising a rotor hub, the cylindrical hub has a closed top cover with a bore for a counter rotating mass, or an antenna at the exact center of the top cover. In this embodiment bolted with the main shaft by a swivel joint, and an open lower part wherein the drive shaft is mounted by flexible metal iron plate bend in the form of a “V” for tilting the rotor without interrupting the driveshaft. The hub is coupled with the drive shaft by means of a bend iron metal plate, bend in a circular and “V” shape, whereby the two ends are flattened having bores holes made around the flattened ends and corresponding holes on the rotor hub and the shaft and bolted with the bend plate in between the hub and the drive shaft with sunken anti vibration bolts and nuts of corresponding length of the plate and hub and with the shaft. The hub having three bores in delta alignment wherein the three rotor blades are rigidly mounted by universal joints in the bore of the rotor hub, at the upper peripheries of the rotor hub. The cyclic pitch is mounted on the first rotor blade part, and the horizontal pitch on the lower first blade part and pivoted on the rotor hub.

[2326] The servo will pull and push the second blade parts for angle adjustment of the blades in the horizontal plane. The first rotor blade part is the small part of the blade which is mounted with the stationary cyclic pitch mechanism. The second blade part is mounted in with the first blade part by the pitch mechanism of the cyclic pith wherein the locking mechanism is provided. The lower first blade part is mated pivoting with the linear motor rod pivot mounted on the rotor hub and electrical connected by a lower ring and upper ring of electric conductive material ducted through grooves connecting all electrical components’ in a simple matrix. The electric motors on the hub is closed in a jacket having a rounded leading edge and trailing edge whereby the leading edge is in rotating direction of the rotor. The jacket can be equipped with at least on airfoil, like small blades pressing air downward, compensating the turbulence created by the lower piston rod.

[2327] In different embodiment refers to a turbo machine helicopter rotor which can reach faster cruising speed. By augmenting rotational velocity or RPM. The flying object becomes superior in performance and maneuverability requires concise rotor blades, neither requisite of a larger horizontal plain.

[2328] The three lower electric motors are linear motors with gears and locking mechanism provided in the motor casing. The electric motor is made between two rods having racks or gear keys along the rod mashing with the cogwheel and enclose with a minimum air gap and raped in a metal jacket. The two rods move outward when rotating in one direction and inward when moving in the opposite direction and adjusting the horizontal blade angle. portraying from both sides of the electric machine connected with the first blade part and the hub. Electric motor packed in a metal jacket and blade surface material and pivoting connected with the hub having pivoting hollow rings extending from the hub wherein the motor casing is mounted by a rod and locked in place by washers and nuts. The motor two linear moving rods are connected under the first blade part also with pivot connection, and the other with the hub. wherein the rod is placed in the connecting saddle with eyes of the saddle corresponding to the rod bore wherein a metal pin is inserted connecting both parts. The blade and rod connection is under the first blade part before the pitch connection mechanism which is mounted in bearing for rotation. On the drive shaft two electric insulated flattened tracks of copper are made in a slight carved groove vertically extending with the shaft and continued in the rotor hub where interconnected cables continue in slight grooves and portraying the hub to the exterior isolated along the joints for mating with the electric motors. on the blades connected with the servo motors.

[2329] The first rotor blade part consists of titanium plats whereon the pitch system is mounted or welded and the blade is covered with the blade material and enclosed as one blade piece, including the lower electric machines, the harnessed jacket is closed with the corresponding blade material looking as one body. The swash plate is mounted on the lower hub wherein the carved circular track is provided for the swash ring to be mounted in ball bearings The swash ring having three rods mated by pivots and bend downward mated with a ring rigid metal or aluminum which is actuated by three linear piston rods of the linear electric machine connected to the opposing ring surface. which are electrically mated with the internal power supply of the Helicopter and mated with the servo controller. The motor are programmed and have a unique ID for communication with the control system individually or assembly. The two electric conductive flat tracks are connected with two slip rings on the lower drive shaft and electrically mated with carbon spring loaded pins which are mated with the servo power supply.

[2330] AT LEAST ONE: Rotor blade consists of a first blade part with determined size for installing the cyclic blade pitch thereupon which is mounted in a casing and suited in a steel metal jacket including its gear casing and locking mechanism, mounted on the first rotor blade part. The second blade part is connected to the fist blade part by the rotary cyclic pith system mechanism whereby the second blade part is rotated by the servo of the cyclic pitch on the first blade. In different embodiment, the electric motor is made in the rotor and stator of the pitch magnesium and the locking mechanism made on the stator of the first blade part for locking the second blade part. In this embodiment, a more rigid method is required for different tasks. The rotating mechanism couples the blades whereby an axis from the second blade inner frame protrudes through the circular pitch mount and extend through the gear casing of the servo wherein mounted in bearing parallel with the second axis and mated by means of gears to reduce rotational servo speed. The axis entering the gear casing contains a solid iron metal disc equipped with bores whereby edges between the bores are slightly conic made and corresponding bores in the opposing casing, made of a solid peace having a spatial gap with the inner wall having equal diameter for rotation therein. The solenoid piston is mounted in the inner casing, mounted therein in longitudinal direction opposing the disc of bores and entering the bores in locking position which is the first piston position. The unlock position is the second position. The servo motor is placed in an angle of 90 degree with a bevel gear on the drive shaft which mash with the gear of the fist axis in the gear casing. The rotor is mounted on the upper part of the hub and the lower hub comprising three servos motors for the horizontal blade pitch and the swash ring is mounted underneath the motor connection. The cyclic blade pitch contains solenoid locking mechanism which lock the metal disc with the metal iron casing through bores in the casing body and corresponding bores provided on the disc from which the solenoid is electrically connected with the servo circuit board which electronically unlocks the solenoid piston to engage the servo motor for adjusting the blade pitch.

[2331] AT LEAST ONE: Or Three lower electric motors are rotary electric machines. with gears and locking mechanism in the motor casing. The electric motor is parallel between the two rods having helical or spiral gear keys along the rod mashing with the two-bevel gear at both motor sides. The bevel gears comprising corresponding gear keys connected in an angle of 180degree and supported in a casing and suited in a metal jacket. The two rods move outward in opposing direction when rotating in one direction and inward in opposing direction when moving in the opposite direction of the first direction for adjusting the horizontal blade pitch angle. Portraying from both sides of the electric machine connected with the first blade part and the hub. Electric motor and rods is packed in a frame with guides, a casing, and metal jacket and blade surface material and pivoting connected with the hub having pivoting hollow saddles extending from the hub wherein the motor casing is mounted by a rod and locked in place by washers and nuts. The motor two linear moving rods are connected under the first blade part also with pivot connection, and the other with the hub. wherein the rod is placed in the connecting saddle with eyes on the saddle side extension corresponding to the rod bore wherein a metal pin is inserted connecting both parts and bolted by locking nuts and a secured pin. The blade and rod connection is under the first blade part before the pitch connection mechanism which is mounted in bearing for rotation. On the drive shaft two electric insulated flattened tracks of copper are made in a slight carved groove vertically extending with the shaft and continued in the rotor hub where interconnected cables continue in slight grooves and portraying the hub to the exterior isolated along the joints for mating with the electric motors. on the blades connected with the servo motors. The first rotor blade part consists of titanium plats whereon the pitch system is mounted or welded, and the blade is covered with the blade material and enclosed as one blade piece, including the lower electric machines, the harnessed jacket is closed with the corresponding blade material looking as one body. The swash plate is mounted on the lower hub wherein the carved circular track is provided for the swash ring to be mounted in ball bearings The swash ring having three rods mated by pivots and bend downward mated with a ring rigid metal or aluminum which is actuated by three linear piston rods of the linear electric machine connected to the opposing ring surface. which are electrically mated with the internal power supply of the Helicopter and mated with the servo controller. The motor are programmed and have a unique ID for communication with the control system individually or assembly. The two electric conductive flat tracks are connected with two slip rings on the lower drive shaft and electrically mated with carbon spring loaded pins which are mated with the servo power supply.

[2332] AT LEAST ONE: Lower fuselage of the of the helicopter comprises a level for generating electric current with horizontal aligned turbine rotors. In the lower floor beneath the cabin at the lower level of the fuselage, a squire intake ramp is installed in the wide in the lower fuselage which expending from the lower front nose to the rear end of the fuselage. The front ramp may be equipped with a grill or adjustable shutters that can be set as diffusers. The inner intake comprising movable horizontally mounted vanes or screens which can alter the inner flow of the turbine machines to prevent saturation or damage. Screens can be provided in the generator cowl of the fuselage wherein the turbine machines are installed. For the horizontal turbine rotor are provided in the upper and lower cowl casing, vanes or screens made on the wind conducting surface equal as part of that surface made before the turbine rotors at a predetermined distance in front of the first turbine rotor.

[2333] The deflector is adjustable mounted with pivots from the intake side and pushed upward from the turbine rotor side by means of a hydraulic piston. The deflector is adjusted to deflect flowing air from the turbine to the upper horizontal plain. The first turbine rotor lower half is descended in the hollow cowl lower body with an air gap. The second horizontal axis aligned turbine rotor is made in the squire ramp with a minimum spatial gap with the surrounding cowl or nacelle body. The turbine rotor axis is suspended in the cowl side frame located in the hollow body operable mounted in bearings. The second turbine rotor shaft can be lowered equally with the first rotor or adjusted by the electronic controller. This feature enables air circulation when reaching higher travel velocity and regulated by the vanes. The first and second horizontal turbine rotor are a ring generator with horizontal blades, wherein the midpoint resides the stator. The turbine machine can generate current and sustain the craft at modest speed. Thea turbine machine can be made with a rotor, rotor combination for a supplement amount of electric current. The turbine rotor can be divided in smaller horizontal parts.

[2334] AT LEAST ONE: Fly by wire digital electric sustainable helicopter is manually navigated by means of the gyroscope controllers. More particularly, the invention relates to an electric aircraft, helicopter comprising adjustable rotor combined with the control System for controlling the direction of flight of a helicopter and vertical tilting, horizontal adjustable and tilting in the direction of travel of the helicopter rotary electric machines and speed which can be combined as motor and generator. And automated gearbox for providing a set of gear ratios for stepping up RPM. The helicopter comprises a fuselage, which has a fixed tail structure, a tail fin, tail flaps, a cabin. A rotor with at least one blade, the at least one blade is individually pitched in 360degrees, horizontal adjustable or bending blades, a tillable rotor, rotatable mounted on top of the cabin of the fuselage extending from the mast. The mast whereon the stationary mast body is provided a circular gap, for the ring turbine machine to be mounted with its casing, mounted in the fuselage gap and electrically connected by provided connectors and bolted with the fuselage. Whereon the fuselage the stationary swash ring components are mounted in a circular casing around the shaft. Airfoils extend perpendicular from the ring turbine outer hub. the ring turbine blades are extended in a predetermined length, not to disturb the generated trust. A motor for rotating the at least one blade. Electric engine or rotary electric machine, rechargeable means. Fast charging means. The manual, gyroscopic, flight controller is digitally mated with the electronic components of the manual controls. The ball contains an extra mass at its inner lowest point by which it may returns to its central position. The rotary ball is made in the side console combined, the throttle, tail turbine throttle, front flaps, back flaps, tail fin, and main rotor controls are provided including voice control and automatic pilot which requires a navigational input.

[2335] AT LEST ONE: Digital cockpit, digital touchscreen controls, autonomous operable, semi-autonomous engaging auto pilot, gyroscopic manual controllers, by controller balls and rings is electronically supported and controlled. The helicopter containing an upper incasing frame of carbon fiber with large window screens or of transparent acryl screens made in window frames around the cabin, having digital displays in a between the layer where a layer is provided for coloration or a tinted screen for sunlight cover. Voice control integrated with digital displays and voice control AD converters of all analog signals to digital and optical mated units. Having wireless communication devices. Typically, the aircraft further includes limiters for limiting pivoting of the collar about the rotor mast to between +20 degrees and -20 degrees which is adjustable. The horizontal adjustment is also secured for downward adjustment with respect to the fuselage. The helicopter control of the present invention is simple in structure but, sturdy and reliable safe and efficient and effective in operation. The rotor is driven by an electric traction motor type machine. Or combined electric piston engine. Or the geared coaxial machine in different combination.

[2336] In Certain Embodiment for a Helicopter for example. The manual gyroscope controller fly by wire system translated electronically and/or mechanically, combined motion to electronic signals processors which are converted and digitalized and processed and executed. The ball made rotatable in its lower casing comprising circular horizontal strips of magnet film of neodymium magnets poled N and S in blocks. provided on the lower part of the ball mated in the casing wherein the opposing casing the opposing strips of solenoids are provided which may be printed or SMD electromagnets. A switching system like a commutator with altered parts, or electronic processor and microcontrollers reading motion and assisting the pilot by electric and magnetic means. The magnet and solenoids opposing track are the sensors mated with the MEM-HRS base sensors in the ball and the tracks in dictating direction of the ball. Each horizontal and vertical track is connected to a switching unit or commutator and processed by a computer processor whereon all switching units are mated on a circuit board provided in the lower casing. The ball is magnetically levitated by the magnetic track and a center magnet in the lower body and in the lowest point of the ball. In Certain embodiment the rotary ball is supported on rolling supports like a mouse ball having the same. A ring is mounted on its horizontal plane around the ball, rings or rollers controllers are mounted operating vertically. Controllers and levers switches are also digital on screen and can be altered digitally by a touch of the screen whereby the physical component is also altered which are all electronically mated with the automated system. A commutator is electrically connected to each track and moves electrically with the ball. The units are mated on a circuit board enclosed unit and mounted in the lower casing and connected with optical cables the automated system and associating units.

[2337] The electromagnetic controlled and operating controller in the shape of a sphere is placed operable in bearings in its lower holder or casing wherein electro magnetically connected by the magnetic track of solenoids on the lower section of the sphere and opposing tracks of solenoids permanent magnet can also be applied in the lower body section of ball and casing with a spatial gap for motion of the sphere. The sphere is leveled by a mass provided in the sphere made on the lowest point inside the sphere. A digital signal generator provides a digital controller signal to the processing unit which is electrically connected referred to as flyby wire system with the swash mechanism and tail rotors, rudder and horizontal flaps by means of actuators.

[2338] In Certain embodiment the rotary ball is supported supports in bearings like a mouse having the same Roller mechanism and sensing system. The at least one controller ring is provided around the sphere with a spatial gap rotating in the horizontal plane around the ball and a function is digitally assigned and programmed to the controller ring. Rings or rollers controllers are mounted operating vertically. Controllers and throttle levers, switches are also digital on screen and can be altered digitally by voice command, a keypad, a computer mouse or on the smaller controller touchscreen whereby the physical component is also altered which are all electronically mated with the automated system. A commutator is electrically connected to each track and moves electrically with the ball. The units are mated on a circuit board enclosed unit and mounted in the lower casing and connected with optical cables the automated system and associating units.

[2339] AT LEAST ONE: High speed and excellent maneuverable single or concentric rotor Helicopter with increased rotor blades. Concentric propeller rotors are made with increased blade length whereby the first upper rotor and the second lower coaxial rotors can be made in different length of rotor blades. The first blade can be made larger than the second rotor blade assembly comprising two rotor blades or more blades. The second smaller rotor is rotated with increased velocity regarding the first rotor to provide equal propulsion as the first larger rotor and anti-torque. The rotor can be swapped of lengths and position.

[2340] The Tilting rotorcraft is suspended by a ball and socket joint with the lower body such to maintain the stability and position of the helicopter fuselage or capsulated cabin. Cyclic blade pitch unit is mounted in the rotor Hub mounted in pitch bearing with the blades. The Blades are operable in bearing mounted with the hub and the pitch mechanism.

[2341] With Horizontal and vertical adjustable turbine rotors. Perpendicular rotors with horizontal and vertical propulsion. With single turbine rotor or a plurality of turbine rotors. With axial and perpendicular flow and coreless turbine engines.

[2342] The turbine rotor comprises airfoils extending perpendicular and axial from the rotor hub with a predetermined Hight and longitude operable in its nacelle, whereby the aero foils blades curvature and rotation generate vertical thrust by the rotor pitch setting.

[2343] Generators are provided in the fuselage containing air ducts and ramps as air passage from the nose to the tail, from the bow to the stern. Made partially in the fuselage or wings. Mounted extending from the fuselage like the turbine engines. The fuselage or hull wherein the horizontal air duct is provided, Horizontal and/or Vertical turbine generators are mounted operable in bearing with the side wall of the sheet metal duct or composite or fiber duct, solid plastic air-duct and frame with electronic diverting panels and vanes, having geared electric generators in the hub, whereby the second turbine rotor push blades are elevated the inner duct comprises inner adjustable panels actuated for conducting wind on the rotor or deflecting wind in case of maximum speed and saturation. The turbine rotor is motorized and adjustable mounted. Tail skid. 45degree gearbox. Synchronized elevators. The horizontal duct comprises horizontal propulsion turbines motors made at the exhaust nozzle. The generators and turbine motors can be combined arranged in the horizontal air duct.

[2344] The lower fuselage containing an air passage from the nose to the rear fuselage wherein the horizontal fuselage. Horizontal turbine generators are mounted in side wall bearings having geared electric generators in the hub, whereby the second turbine rotor push blades are elevated the inner duct comprises inner adjustable panels actuated for conducting wind on the rotor or deflecting wind in case of maximum speed and saturation. The turbine rotor is motorized and adjustable mounted. Tail skid. 45-degree gearbox. Synchronized elevators. Horizontal sonic Engine cowling on the upper fuselage. Mast and transmission. Engine mount. Landing Skids. Landing floats. One propeller rotor. Helicopter rotor. Helicopter lower fuselage air passage way. Adjustable inner vans. Wind turbine generators. Automated geared Hub generator. 400Hz power supply. Voltage converter and regulator. Digital cockpit and cabin. Manual gyroscopic controller and digital controls and screen. Digital screen in the windscreen. fiber optical cable and connectors and connecting panel. PCM unit. AD-DA converter unit. DC-DC converter unit. AC-AC converter unit. Bridge rectifier. Rechargeable battery. Current Accumulators. Backup system. Helicopter rotor. Rotor mast.

[2345] Horizontal sonic Engine cowling on the upper fuselage. Mast and transmission. Engine mount. Landing Skids. Landing floats. One propeller rotor. Helicopter rotor. Helicopter lower fuselage air passage way. Adjustable inner vans. Wind turbine generators. Automated geared Hub generator. 400Hz power supply. Voltage converter and regulator. Digital cockpit and cabin. Manual gyroscopic controller and digital controls and screen. Digital screen in the windscreen. fiber optical cable and connectors and connecting panel. PCM unit. AD-DA converter unit. DC-DC converter unit. AC-AC converter unit. Bridge rectifier. Rechargeable battery. Current Accumulators. Backup system. Helicopter rotor. Rotor mast. Upper and lower swash plates mated in turbo bearing. rotor hub. . Rotor blade. Blade grip. Control rod connected swash unit and rotor(s). Rotor Stabilizer bar. Wide body Fuselage.

[2346] Transmission. Engine cowling and engine. engine mount. Cabin. Cabin door. Tail boom. horizontal tail rotor. tail fin. tail rotary machine and gearbox. tail skid. Landing skid. rotor drive 45-degree gearbox. Tail rotor. Dual horizontal jet propulsion engines mounted on the fuselage. Dual shaft driven by dual rotary electric machine and dual shaft coupling. Helicopter equipped with a front rotor and a back helicopter rotor. Second rotor mounted on the first rotor rotating in opposing direction. Tilting hub with small telescopic pistons in the swash mechanism stator. Having GPS. And navigational autopilot for flying autonomous. Remote sensing. Radar system. Additional generators. A lower duct traversing the lower fuselage with inner adjustable defectors and deflectors, intake ramp and exhaust with one or more horizontal or vertical turbines or combined generating electric current by ram air and bleed air.

[2347] A helicopter comprising a dual rotor electric machine with at least one stator dual arranged coils or electric magnets mechanically connected by a coaxial shaft for driving two helicopter main rotors in contra direction for eliminating centrifugal forces. The coaxial shafts consist of a first external drive shaft and a second inner drive shafts mounted on bearings on the third stationary barrel. The hollow barrel is the cable conduit for electric and data cables conducted through the barrel in insulated harnessed cable cover and electrically connected by to pitch and sensing system in the rotor hub. The tail rotor for contra rotation is omitted. A helicopter may consist of two rotors one at the front of the fuselage and one at the back of the fuselage. The helicopter may comprise a tail rotor for horizontal propulsion or a dual turbine booster provided on the tail boom. The electric motor and bearing provided rotation without vibration and are mounted with the craft body on antivibration material that absorb vibration.

[2348] The Fly by wire digital electric sustainable energy generating helicopter is manually navigated by means of the gyroscopic controllers. More particularly, the invention relates to an electric aircraft, helicopter comprising pitch adjustable rotors combined with the control System for controlling the direction of flight of a helicopter and vertical tilting or horizontal adjustable and tilting for the direction of travel of the helicopter rotary electric with rotor, rotor, stator, stator arrangement. With Electric machines combined as motor and generator. And automated gearbox for providing a set of gear ratios for stepping up RPM. Magnetic motor and electromagnetic motor, induction motor etc. The helicopter comprises a fuselage, which has a fixed tail structure, a tail fin, tail flaps, a cabin. A rotor with at least one blade, the at least one blade is individually pitched in 360-degrees, horizontal adjustable or bending blades, a tillable rotor, rotatable mounted on top of the cabin of the fuselage extending from the mast.

[2349] The mast whereon the stationary mast body is provided a circular gap, for the ring turbine machine to be mounted with its casing, mounted in the fuselage gap and electrically connected by provided connectors and bolted with the fuselage. Whereon the fuselage the stationary swash ring components are mounted in a circular casing around the shaft. Airfoils extend perpendicular from the ring turbine outer hub. the ring turbine blades are extended in a predetermined length, not to disturb the generated trust. A motor for rotating the at least one blade. Electric engine or rotary electric machine, rechargeable means. Fast charging means. The manual, gyroscopic, flight controller is digitally mated with the electronic components of the manual controls. The ball contains an extra mass at its inner lowest point by which it may returns to its central position. The rotary ball is made in the side console combined, the throttle, tail turbine throttle, front flaps, back flaps, tail fin, and main rotor controls are provided including voice control and automatic pilot which requires a navigational input.

[2350] A Horizontal and Vertical pitch adjustable turbine rotor is applied for a fixed wing aircrafts, rotary wing aircrafts and marine vessels for augmented speed and maneuverability instead of using large and heavy screw propeller, and crafts including an electric engine with at least one rotor placed at the center of stern or two placed besides or a plurality mounted rotatable on its axis for steering in each degree of the circular plane. The turbine machine at the bow is also rotatable mounted, whereby the vessel is maneuverable in all preferred angles. The ship is extreme maneuverable that can rotate around its center axis. By means of the extension the rotor can be tilted vertically to steer the vessel, and to lift the vessel partially when speeding, while the axis is aligned horizontal Having a drive shaft which can be driven by the reciprocating engine or a rotary electric machine. And a gear for adjusting the rotational speed. The horizontal aligned shaft driving the rotary.

[2351] Upper and lower swash plates mated in turbo bearing. rotor hub. Jesus Nut. Rotor blade. Blade grip. Control rod connected swash unit and rotor(s). Rotor Stabilizer bar. Wide body Fuselage. Transmission. Engine cowling and engine. engine mount. Cabin. Cabin door. Tail boom. horizontal tail rotor. tail fin. tail rotary engine and gearbox. tail skid. Landing skid. rotor drive 45-degree gearbox. Tail rotor. Dual horizontal jet propulsion engines mounted on the fuselage. Dual shaft driven by dual rotary electric machine and dual shaft coupling. Helicopter equipped with a front rotor and a back-helicopter rotor. Second rotor mounted on the first rotor rotating in opposing direction. Tilting hub with small telescopic pistons in the swash mechanism stator. Having GPS. And navigational autopilot for flying autonomous. Remote sensing. Radar system. Additional generators. A lower duct traversing the lower fuselage with inner adjustable defectors and deflectors, intake ramp and exhaust with one or more horizontal or vertical turbines or combined generating electric current by ram air and bleed air.

[2352] A helicopter comprise different types of landing gears extending in pair from the lower fuselage or retractable lading gears with wheels. The craft can also land on a body a water with floats mounted on the lower extending lading gears.

[2353] AT LEAST ONE, Civil transport helicopters. Light observation helicopter. Firefighting/rescue. . Multipurpose light helicopter. Cargo helicopter. Transport. SAR/utility helicopter. ASW/SAR/utility helicopter. Medium-lift transport/SAR helicopter. Heavy-lift cargo helicopter. Multipurpose Utility helicopter. Observation/scout helicopter. Search and Rescue helicopter. Light multi-role helicopter. Multi-mission maritime helicopter. V/STOL transport Tilting engine for horizontal trust and vertical thrust. Reconnaissance and . high-speed compound helicopter. UAVs. HALE ISR UAV. Carrier-based UAV. Passenger and Cargo Transportation helicopter. Autonomous flying Helicopter, manned or unmanned. Gyrocopter. Rotary wing craft. ROV. Large cargo aircraft with front load by opening nose, rear loader. Hang glider. Powered Parachute. Aerial tanker. Trainers. Transport aircraft Utility aircraft. UAVs. HALE ISR UAV. Carrier-based UAV. Motorized glider and sailplanes.

[2354] A personal flying aircraft for one or two individual with one main rotor or a plurality of turbine rotors providing vertical trust.