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Jet Aircraft. Rotor-Craft. Air-Balloon. Airship. Blimp and Dirigibles. Rotor Craft

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Jet Aircraft. Rotor-Craft. Air-Balloon. Airship. Blimp and Dirigibles. Rotor Craft ELECTRIC AIRBALOON, AEROSTAT. [2275] AT LEAST ONE: Jet aircraft. Rotor-craft. Air-balloon. Airship. Blimp and dirigibles. Rotor craft. Auto Gyro. Gyro plane. Helicopter. Monoplane. Bi-plane. Supersonic lifting body. Civil airplane. 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 wing aircraft orbit copter. gyro plane helicopter amphibian land plane. Sea- plane. float plane. flying boat. Airships (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 ornithopter 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 helicopters 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 rotorcraft 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 tail rotor 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 airplanes 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 wings (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 helicopter rotor 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 autorotation, 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.
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