WO2020053868A1 - Appareil et procédé de propulsion par réaction à travers un conduit de tunnel d'inhalation d'air pour un engin volant - Google Patents

Appareil et procédé de propulsion par réaction à travers un conduit de tunnel d'inhalation d'air pour un engin volant Download PDF

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Publication number
WO2020053868A1
WO2020053868A1 PCT/IN2018/000050 IN2018000050W WO2020053868A1 WO 2020053868 A1 WO2020053868 A1 WO 2020053868A1 IN 2018000050 W IN2018000050 W IN 2018000050W WO 2020053868 A1 WO2020053868 A1 WO 2020053868A1
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Prior art keywords
air
fuselage
jet
impeller
inhale
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Ceased
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PCT/IN2018/000050
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English (en)
Inventor
Meruva RAVIBABU
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Individual
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C15/00—Attitude, flight direction, or altitude control by jet reaction
    • B64C15/02—Attitude, flight direction, or altitude control by jet reaction the jets being propulsion jets
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/30—Aircraft characterised by electric power plants
    • B64D27/33—Hybrid electric aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/30—Aircraft characterised by electric power plants
    • B64D27/35—Arrangements for on-board electric energy production, distribution, recovery or storage
    • B64D27/353—Arrangements for on-board electric energy production, distribution, recovery or storage using solar cells
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/30—Aircraft characterised by electric power plants
    • B64D27/35—Arrangements for on-board electric energy production, distribution, recovery or storage
    • B64D27/357—Arrangements for on-board electric energy production, distribution, recovery or storage using batteries
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/04—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/04—Aircraft characterised by the type or position of power plants of piston type
    • B64D27/08—Aircraft characterised by the type or position of power plants of piston type within, or attached to, fuselages
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/10—Aircraft characterised by the type or position of power plants of gas-turbine type 
    • B64D27/14—Aircraft characterised by the type or position of power plants of gas-turbine type  within, or attached to, fuselages
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/20—Vertical take-off and landing [VTOL] aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/10—Wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/11—Propulsion using internal combustion piston engines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/19—Propulsion using electrically powered motors

Definitions

  • This invention relates to an air inhale tunnel conduit jet propulsion apparatus and method for flying craft.
  • the present invention relates to a method of air-jet-propulsion for flying craft by following the steps of 1) inhalation of air through fore and/or upper part of the flying craft in to a tunnel conduit path, 2) compression of said air inside the tunnel conduit and /or along the flying craft and 3) delivering the pressurised and/or fast moving said air through air- jet nozzle thereby said flying-craft is propelled.
  • the invention relates to a novel application of thrusting and propulsion means and method for aeronautic vehicles, comprising fuel engine, electrical and/or solar power source with rechargeable batteries, mechanical power transmission system, electrical power supply, air compressor, AC and/or DC motor, air- jet nozzle and control mechanism.
  • the invention provides improved thrusting and propulsion apparatus and method for flying crafts includes shapes of fuselages of Drone, helicopter, UAV (unmanned aerial vehicle) aircraft and VTOL and jet plane.
  • the present invention generally relates to aeronautical engineering and applications of aerodynamic.
  • Propulsion apparatus and method of present day aircrafts are taken as prior art as they are approximately related to this invention.
  • Prior art aircraft vehicles achieves lift and thrust by pushing air down words and/or back words respectively using propulsion device.
  • Types of devices for propulsion is divided into two methods. Online engine devices where engine is a part of the propulsion apparatus.
  • engine is an independent component and its mechanical power is delivered to propulsion apparatus on same shaft and/or with additional power transmission mechanism.
  • Drag Drag coefficient x density of air x velocity 2 x reference area of fuselage
  • Drag is increased exponential to the speed of the vehicles is one of the problem. Air hitting at reference area of fuselage is another problem to be attended.
  • Various methods have been used to reduce drag coefficient by improving aerodynamic designs of the fuselage of the vehicle. This invention provides improved solution to reduce the drag coefficient as described in brief description. In prior art vehicles there is a need to reduce the fuel consumption and energy further. Number of aero dynamic designs have been evolved to reduce the high aerodynamic drag and high air resistance at high speeds, still need is that to reduce aerodynamic drag further.
  • jet type prior art vehicles can’t fly at low speeds and needs huge space is required for runways to acquire high speed to take off. Further reduction of fuel consumption to be achieved, and reduction of operating temperature of engine to generate the required thrust force, is another expensive issue in Jet engines.
  • the helicopter and drone propellers pushes air from top to down and front to back angularly to enable lift and thrust.
  • These prior art devices consumes huge fuel, needs to improve fuel efficiency.
  • Fan type prior art vehicle difficult to reach high altitudes and very high speeds and difficult to face bad weather conditions. This invention over rides the problems of fan propellers and jet propellers.
  • Drones have speed limitation, they fly by utilising power from charged batteries, limitation of travel distance are the issues to be attended and these are prone to risk if battery fails due to sudden drop of voltage. Topmost limitation is the flying time and possibility of sudden fall of battery charge. It is problematic to fly drones in rain, snow, or even in drizzle to prevent against physical effects on the fuselage and propeller apparatus. Improvement of flying time without increasing the capacity of battery is achieved in this invention and enables more speed. Issue is to develop a drone operable with fuel engine at economic cost.
  • the principal object of the invention is to provide air inhale tunnel conduit jet propulsion apparatus and method having a tunnel conduit inside and/or along the flying craft that minimises drag force to achieve maximum fuel efficiency.
  • Another object of this invention is to provide air inhale tunnel conduit jet propulsion apparatus and method wherein power source applies torque via torque transfer mechanism to the driving shaft of the air-impellers and air-compressors, thereby air at fore of the fuselage and/or wings is inhaled through tunnel conduit to realise substantial reduction of drag of the flying craft.
  • a further object of this invention is to provide air inhale tunnel conduit jet propulsion apparatus and method for flying crafts that eliminates exponential increase as mentioned in the mathematical equation of the drag with respect to speed of the vehicle.
  • a further object of this invention is to provide air inhale tunnel conduit jet propulsion apparatus and method that minimises drag force against the fuselage by air inhale, by creating low pressure in front and top of the fuselage compared to prior art helicopters and drones as briefed in the description, resulting more fuel efficient for vertical take-off and landing.
  • a further object of this invention is to provide air inhale tunnel conduit jet propulsion apparatus and method that utilises internal combustion engine, provides improved safety without loss of velocity to the flying craft compared to prior art jet-craft wherein jet-craft engine operates at 2000 degree Celsius, said jet-engine parts will melt at 1300 degree Celsius. Safety is realised as the said IC engine of this invention is operable at 600 degree Celsius.
  • a further object of this invention is to provide air inhale tunnel conduit jet propulsion apparatus and method for flying crafts includes shapes of fuselages of Drone, helicopter, UAV (unmanned aerial vehicle) aircraft and VTOL and jet plane.
  • Another object of the this invention is to provide improved jet propulsion apparatus for aviation having improvement in simplified drive engine making shorter runway suitable for landing/take off flying craft to house airports in small towns.
  • a further object of this invention is to provide air inhale tunnel conduit jet propulsion apparatus and method to build different payload capacity flying crafts.
  • Invention articulates inhalation of air through fore of the fuselage, enables low pressure at fore and angularly at top of the fuselage.
  • the inhaled air is accelerated and/or compression by additional air compressors inside the fuselage through tunnel conduit before release through the air-jet-outlet.
  • the invention apparatus and method minimises drag due to the air attack on fuselage, and creates low pressure at fore of the fuselage generates pulling force results the solution to the problems of prior art, reduction of drag provides solution to achieve all the problems listed in the prior art i.e fuel efficiency, higher speeds, simplified machinery, vertical take-off and landing, improved safety, attaining higher speed and thereby increase of fuel efficiency, easy handling, acceleration, and improved performance characteristics.
  • An inhale tunnel conduit jet-apparatus and method is provided for propulsion of flying crafts in natural atmospheric conditions where said flying crafts means all types of air-born vehicles. Fundamental novel feature of this invention is nullification of drag due to head on collision of air at fore and top of the fuselage by inhaling the air through the fore and top of the fuselage.
  • An Inhale tunnel conduit jet apparatus and method are provided for propulsion of flying craft includes the following elements at least one each: 1 ) Engine means to deliver energy to drive shaft of air impeller and/or air-compressor to operate aircraft and to operate control mechanism of the aircraft. Said Engine means also delivers energy to drive shaft of electrical generator to generate power to drive electrical motor to operate said air impeller and/or said air-compressor and to operate control mechanism of the aircraft.
  • Further Engine means also delivers energy to charge the rechargeable battery power source to drive said electrical motor to operate said air impeller and/or said air-compressor to operate aircraft and to operate said control mechanism of the aircraft 2) air-input-port for air-suction into inhale- tunnel-conduit and said air-input-port is fixed and/or swivel-able at fore or/and top of the fuselage 3) inhale tunnel conduit comprises air-input-port at the beginning, air-impeller and/or air-compressor along and terminated at input of the air-jet-outlet. Said inhale tunnel conduit is configured inside and/or along fuselage and/or to wings/arms.
  • air-jet- outlet is configured to air-input-port via said inhale tunnel conduit and to said air-impeller and/or said air-compressor to energize the air, to pass fast moving air from said air-input-port to said air-jet-outlet.
  • Said air-jet-outlet is configured swivel-able and/or fixed and/or pivotably at aft and/or bottom of the fuselage to release pressurised and/or fast moving air to give thrust to the flying craft.
  • Control mechanism is configured with means to regulate quantity and direction of air inhale, control over the direction and rate of speed of air released through said air-jet-outlet to manoeuvre of aircraft and for control the speed, yaw, pitch, rolling.
  • Said inhale tunnel conduit propulsion apparatus and method provides lifting and thrusting mechanism for aircrafts including fuselage shapes of jet plane, VTOL crafts, Drones and UAVs.
  • the method of this invention provides propulsion for aircraft by following method steps comprises 1 ) air inhaling through swivel/fixed air-input-port from fore and/or top of the fuselage/wings/arms thereby air enters inhale tunnel conduit 2) air compression through said air impeller and/or air-compressor which are placed in series of said inhale tunnel conduit, compressed/accelerated air reaches air-jet-outlet in said tunnel conduit along the fuselage/wings/arms 3) delivering thrust to the flying craft by means of releasing the said pressurised/accelerated air through said air-jet outlet which is configured at the aft/bottom of the flying craft. 4) Angle of air input port, air jet outlet and quantity of fast moving air is controlled by control-mechanism to manoeuvre the speed, yaw, pitch, rolling of the aircraft.
  • Very first feature of this invention is minimising the drag/drag coefficient than the drag of the present day vehicles.
  • Feature of this invention is that apparatus enables air craft with presently used internal combustion engines to drive at the speed of jet-crafts by reducing overall power requirements.
  • This jet-apparatus invention and method is configured for varied pay load capacities of aircraft in varied possible shapes by suitably modifying size and shape of the said elements of the invention.
  • the invention enables the manoeuvring of flying craft by controlling the rate of air inhalation, angle of air inhalation, air release rate, air release direction and angle by which accelerated air released though air-jet out let.
  • Additional feature is that in case of emergency air craft can be grounded by bringing to zero speed to make safe emergency landing by utilising pressurised air stocked in cylinders provided in series with tunnel air conduit by releasing air through said air-jet out let.
  • This inhale tunnel conduit propulsion jet-apparatus and method is configurable to ail kinds of present day air born vehicles.
  • embodiments of this invention operates with improved safety for drones and helicopter shaped fuselages.
  • Another feature is that possible explosion of prior art jet engine due to its high operating temperature is eliminated because the engine used in the invention operates at temperatures of internal combustion engine.
  • Function feature of this invention is simplified driving controls and making pilot friendly to avoid risk as in case of helicopters where response time is noticeably more.
  • Invention fits to suite wide range of vehicle to suite the customer needs.
  • Another function of the invention is reduced costs of aeronautical vehicle without loss of quality, for large scale production and to reduce maintenance cost of the vehicle.
  • Another function of the invention is to develop aircrafts suitable to use on shorter runways, compact air ports for accessibility to general public. It is functional to simplify the vehicles to house airports in small towns and for landings on roof tops.
  • Another function is to provide a provision for safe and emergency landing in case of engine failure.
  • Object of this invention is to create improvement in response time for flight control and give better provision to move against wind flow and at very high altitudes and low pressures and in most environmental conditions. All components of the invention acts over the inhaled air til! it leaves through nozzle to energise the said air. A part of the said inhaled air is used to burn the fuel of the internal combustion engine.
  • Another application of the invention is to configure the air input ports at the fore of the fuselage in a suitable manner to the prior art propeller or jet flying craft model there by using the said inhaled air to generate thrust through air-jet-nozzle.
  • Purpose of the invention is to obtain advantages of fuel efficiency, improved safety, high speed travel and economical propulsion apparatus.for propulsion of flying crafts.
  • This air inhale tunnel conduit propulsion apparatus and method of this invention centres on the innovative concept of air inhaling through fore and/or angularly from top of the fuselage/wings/arms, compressing and/or accelerating the said air through and/or along the fuselage/wings/arms and diffusing the said pressurised and/or accelerated air through jet- nozzle there by obtains thrust.
  • This invention cruises the aircraft with much less power than the above mentioned power by minimizing drag of the fuselage and utilizing air cushions under fuselage and low pressure above fuselage while cruising.
  • the propulsion apparatus and method of the invention provides improved lifting and thrusting mechanism for jet plane, VTOL crafts, Drones, UAVs and airborne vehicles of varied sizes in open air atmosphere in most open environmental conditions.
  • the apparatus includes the following components at least one each: 1) air suction fixed/swivel input port at fore and/or at top of the fuselage through which air is inhaled.
  • air- impeller and/or air-compressor configured in series with air suction input port is driven by power source and said power source operates control system of said aircraft and/or to power the electrical-generator to charge rechargeable power source 3)
  • a motor is operated by said power source and/or by rechargeable power source to drive said air-impeller and/or said air- compressor 4)
  • swivel/fixed nozzle at aft and/or bottom of the fuselage of said jet-aircraft is configured in series with air-impeller and/or air-compressor to release pressurised air to give thrust 5)
  • said air impeller and/or compressor are operated by power transfer gear mechanism by power from power source.
  • air-jet-out!et is configured to said-air-input- port via said air tunnel conduit and to air-impeller and/or air-compressor are configured to energize air to pass fast from said air-input-port to said air-jet-outlet.
  • Said control system is configured to lift and control the speed, yaw, pitch, rolling.
  • the method of this invention provides propulsion for flying craft by the steps comprising 1 ) air inhaling through fore and/or top of the fuselage/wings/arms by means of impeller 2) said inhaled air is compression and/or accelerated in a closed tunnel conduit through and/or along the fuselage/wings/arms and 3) delivering said accelerated air through nozzles at aft of the fuselage and/or ends and/or bottom of the wings delivers thrust.
  • Said control system is configured to lift and control of the speed, pitch, yaw, and rolling of the aircraft in desired manner by controlling the quantum of inhaled air, releasing angle and position of said accelerated air in addition to the conventional control methods of prior art vehicles.
  • Said air impeller, said air compressor, and a tunnel conduit is configured to energises said inhaled air and holds and/or passes the said air through diffusion output-nozzle at aft of the fuselage, said nozzle is swivel able angularly at the bottom and/or at aft of the fuselage by the control of said control mechanism for cruise of the vehicle in desired direction.
  • the present invention providing air inhale tunnel conduit propulsion apparatus and method for propulsion of aircraft, the apparatus configured with at least one impeller and /or compressor module operated by torque power of internal combustion engine or electrical motor.
  • the input of the impeller/compressor module is connected to the output of said fixed/swivel air inhale port at fore/top of the fuselage through impeller element and the output of the impeller/compressor module is connected to a fixed/swivel diffusion nozzle element at aft/bottom of the fuselage through tunnel conduit and with/without a pressurised air container attached in series of said tunnel conduct.
  • the present invention providing air inhale tunnel conduit propulsion apparatus and method for propulsion of aircraft, the apparatus configured with one or multiples of fuel engine elements, electrical generator elements, and a chargeable battery power apparatus elements to drive the compressor elements and/or impeller elements and to power the control module of the fixed/swivel input-port and fixed/swivel nozzle/output-port elements.
  • the present invention providing air inhale tunnel conduit apparatus and method for driving aeronautical vehicle, the method is to inhale/suck the air through swivel suction input- port at fore/top of the fuselage by impeller and/or compress the said air and release the said air through swivel/fixed diffusion nozzle element at aft/bottom of the fuselage.
  • the developed low pressure in front of the fuselage by inhaled air actuates lifting, traction, and drag reduction to the aircraft.
  • the method of releasing high pressure/fast moving air through swivel diffusion nozzle module at aft/bottom of the fuselage gives thrusting force and jet propulsion.
  • Pressurised air containers are provided in the path of the said air to operate diffusion nozzles for emergency landing without application of power. These Pressurised air containers are connected to tunnel conduit and nozzles and these are operated by valves which are controlled by control mechanism to cruise.
  • Fuel efficiency and safety is improved in this method of invention in steps of doing air inhaling and compressing and jetting pressurised/fast moving air through a separate tunnel conduit without passing through combustion chamber of the engine.
  • a part of the inhaled air from the tunnel conduit air is configured for burning the fuel in the internal combustion engine or jet engine to provide torque force to drive alternator, compressors, impellers, control system and power for battery charging.
  • Temperature of the fuel engine is normal as engine used is any of the specialised automobile engine because power requirement and fuel burnt is not very high.
  • Block schematic diagram of air inhale tunnel conduit jet propulsion apparatus and method for thrusting of flying craft is embedded in all the three embodiments, said embedded block diagram represents the apparatus of the invention which comprises hardware inter connections to move hassle free air movement from inhalation port, impeller and/or compressor and to output nozzle port.
  • air inhale tunnel conduit jet propulsion apparatus is configured into aircraft shaped fuselage, said air suction input ports are configured at fore and top of the fuselage and at fore of the wings through which air flow is sucked into the tunnel conduit inside the vehicle fuselage, sucked air is compressed by compressor and released through exit nozzles configured at aft of the fuselage and at aft of the wings.
  • An air compression chamber is provided in the path of the tunnel conduit with multiple valve members which are operable to regulate flow of the air through the multiple input pots and exit nozzles.
  • high pressure air tunnel conduit is also defined as air conduit circuit that comprises inhalation port, impeller and/or compressor and output nozzle port configured with inter connections.
  • air inhale tunnel conduit jet propulsion apparatus is configured into helicopter shaped fuselage, said air suction input ports are configured at fore and top of the fuselage through which air flow is sucked into the air tunnel conduit circuit inside the vehicle fuselage and multiple exit nozzles configured at the tail of the fuselage and at bottom of the of the fuselage through which fast moving and/or pressurized air flow is released.
  • An air compression chamber is provided with multiple valve members inside the air conduit circuit which are operable to regulate flow of the air through the multiple input ports and exit nozzles.
  • the modules of the apparatus and method of the invention is incorporated inside the helicopter shaped body of the vehicle, in which, the fixed/swivel suction port modules are configured at fore of the fuselage angularly upwards.
  • Fixed/swivel diffusion nozzle members are configured at aft/end of the fuselage angularly downwards.
  • air inhale tunnel conduit jet propulsion apparatus is configured into drone shaped fuselage, said air suction input ports are configured at top of the wings and top of the fuselage through which air flow is sucked into the air tunnel conduit circuit of the vehicle fuselage and multiple exit nozzles configured at bottom of the wings/arms and at bottom of the fuselage through which air flow is released.
  • An air compression chamber is provided with multiple valve members which are operable to regulate flow of the air through the multiple input pots and exit nozzles.
  • the module of the apparatus and method of the invention is incorporated inside the drone shaped body of the vehicle, in which, the fixed/swivel suction port modules are configured above the arms of the drone and Fixed/swivel diffusion nozzle members are configured at the bottom of the arm of the drone right below the suction port.
  • the fixed/swivel suction port modules are configured above the fuselage of the drone and fixed/swivel diffusion nozzle members are configured at the bottom of the fuselage of the drone.
  • apparatus is configured with air compression for jet propulsion with a cow! around the impeller and compressor, energy loses are minimum, thereby problems of prior art devices are solved and improvements are achieved.
  • Suction ports through which air flow is sucked into the tunnel conduit inside the fuselage and multiple exit nozzles through which air flow is released from the vehicle.
  • An air compression chamber is provided along with multiple valve members which are operable to regulate flow of the air through the multiple exit nozzles.
  • the exit ports are configured in an array inclined in the opposite direction of the cruise of the vehicle.
  • the modules of the apparatus and method of the invention is incorporated inside the fuselage of oval shaped body with extended wings, in which, the fixed/swivel suction port modules are configured at fore of the fuselage and to fore side of the both the extended wings of this body.
  • Fixed/swivel diffusion nozzle members are configured at aft/end of the fuselage and aft side of the extended wings.
  • the modules of the apparatus and method of the invention is incorporated inside the airplane shaped body of the vehicle, in which, the fixed/swivel suction port modules are configured at fore of the fuselage and to fore side of the both the wings of the aeroplane.
  • Fixed/swivel diffusion nozzle members are configured at aft/end of the fuselage and aft side of the wings.
  • jet engine has tunnel conduit connectivity for air supply to burn fuel from the tunnel conduit from air input ports.
  • drag coefficient becomes bear minimum in comparison with prior art vehicles because air is sucked at forefront of the fuselage angularly towards up, there by developing low pressure at foreface of the fuselage to minimize the drag coefficient, there by all the problems mentioned in the prior art are solved.
  • All embodiments of this invention has low pressure above the fuselage due to air suction, atmospheric pressure under the fuselage, and nozzles releases accelerated air gives thrust as per Newton third law, aircraft takes-off vertically with less power than the prior art vehicles there by solves problems of the prior art vehicles.
  • Thrust required to move floating body in the air is too minimum because drag is only air resistance which is minimized in these embodiment of the invention because of the developed low pressure due to suction at forefront and angularly above the fuselage.
  • Newton 3 rd conveys that there is equal reaction against action, applies to this invention that vehicle moves forward when air is sucked inside. Also due to suction, low pressure at front of the fuselage pulls vehicle forward there by drag becomes further less than the drag of prior art vehicles.
  • the invention solves the major problems/improvements and also applicable to the newton 3 rd law.
  • the Newton 3 rd law reaction also applicable to this invention at fore and aft of the fuselage compared the prior art vehicles there by it gets doubled benefits in improving/solving the problems. Because Drag is minimised, forward pull and lift of the vehicle is improved, this invention is advantageous than all air vehicles used presently hence this invention is novel with subject matter, non-obvious and useful for industrial application.
  • FAICJ apparatus means Fuselage Air Inhaling Acceleration, and Jet (FAIAJ) apparatus and method for vehicles of aeronautics to generate lifting, traction, drag reduction, thrusting and propulsion.
  • Fig. 1 is an illustration of the apparatus and method of the invention showing simplified functional and schematic block diagram.
  • Fig. 2 a prospective view diagram illustrating a preferred embodiment of the apparatus and method of this invention when it is made to function inside the fuselage of aeroplane.
  • Fig. 3 a prospective view diagram illustrating a preferred embodiment of the apparatus and method of this invention when it is made to function inside and over fuselage of Helicopter.
  • Fig. 4 a prospective view diagram illustrating a preferred embodiment of the apparatus and method of this invention when it is made to function inside the Drone shaped fuselage.
  • present invention is applicable for power source and motor mounted bellow the wings or in the cockpit.
  • the configured position of the components are anywhere with the flying craft except for air-input- ports and nozzle output ports which have specific places as mentioned in the description to suite architecture of vehicle.
  • motor means AC motor or DC motor or BLDC motor.
  • Fig 1 articulates the simplified functional and schematic block diagram of the invention“air inhale tunnel conduit jet propulsion apparatus and method for flying craftto generate lifting, traction, drag reduction, thrusting and propulsion.
  • the apparatus shown in Fig1 comprises air suction/impelling swivel inlet ports components 111 and 112 at fore of the fuselage of flying vehicle, configured to air impeller/compressor components 121 and 122 which are operated by torque generating engine 101 or by motor 161.
  • the developed low pressure at fore of the fuselage generates drag reduction and develops traction.
  • the apparatus comprises air suction/impelling swivel inlet ports components 1 13 and 114 on top of the fuselage connected to air compressor components 123 and 124 which are operated by torque generating machine 101 or by motor 161.
  • the developed low pressure at top of the fuselage generates lift, traction and drag reduction.
  • Components 141 ,142 are compressed air tunnel conduits are disposed between air compressors components 121 ,122,123,124 and multilevel compressor component 131. Output of the component 131 is connected to high pressure air chamber component 181 through high pressure air tunnel conduit 143.
  • the Discharge high pressure tunnel conduit component 145 is disposed between the output of the component181 and the discharge control components 125 and 126.
  • the components 125 and 126 releases pressurised air through swivel nozzle components 191 and 192.
  • the Vehicle gets forward thrust because of the fast leaving air.
  • the Discharge high pressure tunnel conduit component 144 is disposed between the output of the component181 and the discharge control components 127 and 128.
  • the components 127 and 128 pushes pressurised air through swivel nozzle components 193 and 194. When this apparatus is operated the Vehicle gets forward thrust because of the fast leaving air.
  • Angle and direction of the swivel input ports and nozzle output ports decides direction, lift and forward movement of the vehicle.
  • the Quantity of air sucked and quantity of air released for thrust decides the speed of the vehicle.
  • the 100 represents direction of the inhaled air into air input ports.
  • the 102 represents direction of the diffused air out from air jet-nozzle nozzles.
  • the torque generating engine component 101 drives alternator component 151.
  • the output of alternator is rectified and used to charge the battery bank component 171.
  • the component 151 includes Alternator, AC to DC rectifier, inverter and flight control apparatus. Flight can be operated by battery power and/or through inverter and compressor motors without the power source from Engine.
  • Fig, 2 is a prospective view diagram illustrating a preferred embodiment of the apparatus and method of this invention when it is made to function in the Aeroplane shaped fuselage.
  • Fig 1 All components of Fig 1 are disposed inside and along the body of the aeroplane except suction inlet ports and diffusion nozzles.
  • the components 201 ,202 and 203 are shown as one of the possible representation as bunch/group of inlet ports together and this formation is not the limiting factor for actual construction of the Flight.
  • Another configuration of power engine under wings is used to drive impellers and compressors which is not shown as separate diagram for simplicity can be understood by art.
  • the Discharge high pressure tunnel conduit component 231 is disposed between the output of the component 125,126,127,128 and fixed/swivel nozzle output port components 211 ,212,213 and 214.
  • the components 125,126,127 and 128 releases pressurised airthrough fixed/swivel nozzle output port components 211 ,212,213 and 214.
  • the direction and speed of travel is decided by the angle of the swivel nozzles which are controlled by control component 151.
  • the 200 represents direction of the inhaled air into air input ports.
  • the 210 represents direction of the diffused air out from air jet-nozzle nozzles.
  • Fig. 3 a prospective view diagram illustrating a preferred embodiment of the apparatus and method of this invention when it is made to function inside the Helicopter shaped fuselage.
  • Fig 1 All components of Fig 1 are disposed inside and along the body of the helicopter shaped flying vehicle, except suction inlet ports and diffusion nozzles.
  • the developed low pressure at fore and top of the fuselage generates traction, lift and drag reduction.
  • the components 301 ,302 are shown as one of the possible representation as bunch/group of inlet ports together and this formation and location of the power source and motor is not the limiting factor for actual construction of the invention.
  • the Discharge high pressure tunnel conduit component 331 is disposed between the output of the component 125,126,127,128 and swivel nozzle output port components 311 ,312.
  • the components 125,126,127 and 128 releases pressurised air through swivel nozzle output port components 311 ,312.
  • the direction and speed of travel is decided by the angle of the swivel nozzles which are controlled by control component 151.
  • the 300 represents direction of the inhaled air into air input ports.
  • the 310 represents direction of the diffused air out from air jet-nozzle nozzles.
  • Fig. 4 a prospective view diagram illustrating a preferred embodiment of the apparatus and method of this invention when it is made to function inside a Drone shaped vehicle.
  • Fig 1 All components of Fig 1 are disposed inside and along the body of the drone shaped air vehicle, except suction inlet ports and diffusion nozzles.
  • the components 401 ,402,403,404 are shown as one of the possible representation as funnel, this formation of shape is not the limiting factor for actual construction of the Flight.
  • the Discharge high pressure tunnel conduit component 431 is disposed between the output of the component 125, 126, 127, 128 and swivel nozzle output port components 411 ,412,413,414.
  • the components 125,126,127 and 128 releases pressurised air through swivel nozzle output port components 411 ,412,413,414.
  • the direction and speed of travel is decided by the angle of the swivel nozzles which are controlled by control component 151.
  • the 400 represents direction of the inhaled air into air input ports.
  • the 410 represents direction of the diffused air out from air jet-nozzle nozzles.
  • Number of wings is not the limiting factor, as four wings only shown in this figure for diagrammatic representation only.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)

Abstract

La présente invention concerne un appareil et un procédé de propulsion par réaction à travers un conduit de tunnel d'inhalation d'air pour un appareil amélioré d'un engin volant et un procédé de propulsion d'avion. L'appareil et le procédé de l'invention fournissent un mécanisme de portance et de poussée à un avion à réaction, des engins VTOL, des drones et des UAV. L'appareil comprend les composants suivants : une source d'énergie (1) pour commander la turbine à air et un compresseur pour commander la réaction et commander l'appareil de commande de l'avion (2) un orifice fixe/pivotant d'aspiration d'air à l'avant et/ou au sommet du fuselage 3) un moteur de turbine à air et de compresseur 4) pour commander la turbine et le compresseur 6) une tuyère d'éjection fixe/pivotante à l'arrière et/ou en bas du fuselage pour libérer l'air sous pression et fournir une poussée et 7) un mécanisme à engrenages pour le transfert de puissance. Cet appareil est configuré pour assurer la portance et commander la vitesse, le mouvement de lacet, le tangage, le roulis et le couple réactif des avions. Le procédé de la présente invention assure la propulsion d'avions en suivant les étapes suivantes : 1) inhaler de l'air à travers l'avant et/ou le sommet du fuselage/des ailes/des bras, 2) comprimer l'air à travers le fuselage/les ailes/les bras et/ou le long de ces derniers et 3) fournir une poussée en libérant l'air sous pression à travers la tuyère d'éjection. L'air inhalé passe à travers un conduit de tunnel pourvu d'une turbine et/ou d'un compresseur à l'intérieur, un orifice d'entrée d'air configuré sur une extrémité et une tuyère d'éjection d'air configurée sur une autre extrémité du conduit de tunnel.
PCT/IN2018/000050 2018-09-12 2018-10-25 Appareil et procédé de propulsion par réaction à travers un conduit de tunnel d'inhalation d'air pour un engin volant Ceased WO2020053868A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
IN201841034280 2018-09-12
IN201841034280 2018-09-12

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WO2020053868A1 true WO2020053868A1 (fr) 2020-03-19

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113306702A (zh) * 2021-06-11 2021-08-27 长沙理工大学 一种喷气式无人机及其控制方法
CN115042981A (zh) * 2022-07-19 2022-09-13 南开大学 一种涡喷飞行器及其驱动方法

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3191886A (en) * 1957-01-29 1965-06-29 Bristol Siddeley Engines Ltd Gas turbine jet propulsion engine units for aircraft and also jet propelled aircraft
US6918244B2 (en) * 2001-08-17 2005-07-19 John Eugene Dickau Vertical takeoff and landing aircraft propulsion systems
WO2017151029A1 (fr) * 2016-03-04 2017-09-08 Lifeng Wang Système utilisant de l'air comprimé comme source de force et son procédé; aéronef

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3191886A (en) * 1957-01-29 1965-06-29 Bristol Siddeley Engines Ltd Gas turbine jet propulsion engine units for aircraft and also jet propelled aircraft
US6918244B2 (en) * 2001-08-17 2005-07-19 John Eugene Dickau Vertical takeoff and landing aircraft propulsion systems
WO2017151029A1 (fr) * 2016-03-04 2017-09-08 Lifeng Wang Système utilisant de l'air comprimé comme source de force et son procédé; aéronef

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113306702A (zh) * 2021-06-11 2021-08-27 长沙理工大学 一种喷气式无人机及其控制方法
CN115042981A (zh) * 2022-07-19 2022-09-13 南开大学 一种涡喷飞行器及其驱动方法

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