Classifications

• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C27/00—Rotorcraft; Rotors peculiar thereto
  • B64C27/02—Gyroplanes
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C27/00—Rotorcraft; Rotors peculiar thereto
  • B64C27/02—Gyroplanes
  • B64C27/021—Rotor or rotor head construction
  • B64C27/025—Rotor drives, in particular for taking off; Combination of autorotation rotors and driven rotors

Definitions

• the transport model of tomorrow is an enigma, both on the problem of consumption, pollution and security, for everyone who travels.
• the displacement is an obligation for the active people who do not sell that virtual but also concrete benefits, which requires a certain reactivity, which by the speed restrictions lengthens the operations and the decision-making.
• the autogyro is a particular aircraft that needs to be developed, generally towards flight safety, and respect for the environment. Several factors of noise and pollution have opened us to a translation on the ground, to a transport at a low cost.
• the present application takes various known processes that we assemble in a particular way and which in this application is the integration of a double rotary wing which itself is coupled to a launch engine, which exempts us from a propeller against couple that presents many dangers. This device is put in place, the time that the natural effect of self-lift is sufficient.
• a specific compilation introduces new technologies assembled for the first time in the principle of a self-gyrating technology, which represents the eCRT technology which brings a complement of security.
• Fig. 1 autogyra consisting of two helices (1, 2), rotating wings whose blades turn in opposite directions to obtain a balance of levitation forces not requiring a helix active counter-torque.
• the engine (5) to launch the light propellers (1, 2) before the auto-levitation takes effect, which strongly secures the takeoff.
• This device also allows with a low wind, less than 20 knots, to take off virtually in vertical without damage and loss of balance, or rolling too long.
• the torque converter controlled from the pilot cell activates in reverse mechanical rotation (6) the propellers (1.2) until the autorotation suspends the aircraft. This converter makes it possible to transmit the minimum useful energy of the motor (5) to ensure the lift.
• the engine (5) translates its power to the propeller (4) of horizontal thrust, which gives the speed of translation and allows to advance the autogyra which takes its lift without the need for energy input on its pale which naturally underlie the aircraft (1, 2).
• the blades are constant pitch, which tends to create a drag decreasing the speed of flight, but provides significant security.
• the step could be variable but identical for the two pale constituting dynamic wing, like fixed-wing aircraft propellers, with variable pitch propeller. Obviously both propellers (1,2) are concerned. From cell (3) commands allow actions for the right flight with high visibility. This stability by providing integration of two propellers constituting the rotary wing constitutes an important stability and with the engine connection in relatively low speed of advancement provides lift without autorotating the aircraft.
• This device is a safety assurance by self stabilization of the aircraft on the spot of its flight. This characteristic is not the regime nor the function but a momentary temporary solution of flight safety, that the autogyrists do not have for the moment, and which certainly requires energy.
• the mechanical noise and propellers are reduced by the contribution of eCRT technology which is one of the claimed applications on mechanical parts, constituting a mechanical organ, of flight, linking the engine, the structure of the cell, the axes propellers of the dynamic wing and the power converter to pale which are regulated at launch of the aircraft.
• the noise gain is at least 5 decibels and the power output with a traditional piston engine or type Wanckel or turbine, a non-limiting example of possibilities will be very effective with 110 horsepower to launch the set of propellers effortlessly.
• the mechanical friction is extremely reduced, which brings a reliability and an available power gain very important given this multi-axis mechanical organization assisted by intelligent eCRT technology which regulates the voltages, the stresses of the mechanical parts.
• the aerial activity of the machines is extremely sensitive and the dynamic wing becomes "more bearing" by the eCRT realization which orders the polarities and the electromagnetic fluxes managed even canceled, which eliminates the inconveniences of the electromagnetic incompatibilities generated by the effects of mechanical stresses, influencing the flight characteristics, increasing the flight performance and leaving the mechanical powers free without effort.
• the eCRT probes erase these incidences of fluctuating electromagnetic charges contrary to the ideal stable conditions for the flight of an aircraft, without parasite and without fluctuating counterforce, equipped with at least one dynamic rotary wing, in this case of example non-exhaustive realization.

Landscapes

• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• Aviation & Aerospace Engineering (AREA)
• Toys (AREA)
• Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)

Applications Claiming Priority (2)

Publications (1)

Family

ID=43587046

Family Applications (1)

Country Status (8)

Cited By (1)

Families Citing this family (1)

Family Cites Families (11)

• 2009
  • 2009-08-20 EP EP09740163A patent/EP2464566A2/de not_active Withdrawn
  • 2009-08-20 KR KR1020127003866A patent/KR20120040713A/ko not_active Withdrawn
  • 2009-08-20 RU RU2012109561/11A patent/RU2012109561A/ru not_active Application Discontinuation
  • 2009-08-20 WO PCT/FR2009/001017 patent/WO2011018559A2/fr not_active Ceased
  • 2009-08-20 CN CN2009801608717A patent/CN102811904A/zh active Pending
  • 2009-08-20 BR BR112012003387A patent/BR112012003387A2/pt not_active Application Discontinuation
  • 2009-08-20 CA CA2770944A patent/CA2770944A1/fr not_active Abandoned
  • 2009-08-20 JP JP2012524256A patent/JP2013501675A/ja active Pending

Non-Patent Citations (1)

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