NL16887C - - Google Patents

Info

Publication number
NL16887C
NL16887C NL16887DA NL16887C NL 16887 C NL16887 C NL 16887C NL 16887D A NL16887D A NL 16887DA NL 16887 C NL16887 C NL 16887C
Authority
NL
Netherlands
Application number
Publication of NL16887C publication Critical patent/NL16887C/xx

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/82Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
NL16887D NL16887C (en)

Publications (1)

Publication Number Publication Date
NL16887C true NL16887C (en)

Family

ID=1784653

Family Applications (1)

Application Number Title Priority Date Filing Date
NL16887D NL16887C (en)

Country Status (1)

Country Link
NL (1) NL16887C (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2409917A1 (en) * 2010-07-20 2012-01-25 Eurocopter Method and rotary-wing aircraft provided with a stabilisation means minimising the attitude hump phenomenon
EP2878536A1 (en) * 2013-11-29 2015-06-03 AIRBUS HELICOPTERS DEUTSCHLAND GmbH Advanced pitch stabilizer

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2409917A1 (en) * 2010-07-20 2012-01-25 Eurocopter Method and rotary-wing aircraft provided with a stabilisation means minimising the attitude hump phenomenon
FR2962972A1 (en) * 2010-07-20 2012-01-27 Eurocopter France METHOD AND AIRCRAFT WITH ROTATING WING WITH STABILIZING MEANS MINIMIZING THE DAMPER PHENOMENON
EP2878536A1 (en) * 2013-11-29 2015-06-03 AIRBUS HELICOPTERS DEUTSCHLAND GmbH Advanced pitch stabilizer
US9381995B2 (en) 2013-11-29 2016-07-05 Airbus Helicopters Deutschland GmbH Advanced pitch stabilizer

Similar Documents

Publication Publication Date Title
AR222664A1 (en) IMPROVEMENTS IN HELICOPTER COUPLING
AT283826B (en) Method for reducing the intensity of shock waves
AR197031A1 (en) AIRCRAFT TIRE
AT329973B (en) AIRCRAFT OR WATER VEHICLE DRIVEN BY ROTATING WINGS, IN PARTICULAR HELICOPTERS
AR240737A1 (en) Rotor arrangement for a rotorcraft
AR224118A1 (en) A METHOD FOR MANUFACTURING A HELICOPTER MAIN ROTOR PALLET AND A PALLET OBTAINED BY SUCH METHOD
AT370049B (en) MISSILE
AT370690B (en) ARTIFICIAL PLANE
AR248246A1 (en) An ultralight aircraft, in particular a helicopter
AR226884A1 (en) STRUCTURE TO IMPROVE THE PERFORMANCE OF A HELICOPTER MOTOR
AT357045B (en) DISC SHAPED MISSILE
AT345671B (en) ARRANGEMENT FOR DELAYING OR PREVENTING A SHOCKWAVE FORMATION
AT318398B (en) Device for controlling the setting angle of two-blade rotors for rotary wing aircraft
AT304273B (en) helicopter
AR198047A1 (en) IMPROVEMENTS IN HUBS FOR VARIABLE PITCH PROPELLERS
AR195795A1 (en) A STRUCTURE TO REDUCE VIBRATIONS IN A HELICOPTER AND A METHOD TO SUPPORT A CHARGE IN SUCH HELICOPTER USING SUCH STRUCTURE
AT299718B (en) Water sports kites
AT101094B (en) Airplane deck with adjustable curvature.
AT386173B (en) AIRCRAFT
AT334215B (en) PLANE, PREFERABLY MOTOR GLIDER
AT334214B (en) KITE FLIGHT DEVICE
AT358398B (en) ADJUSTING SCREW
AR226172A1 (en) A DEVICE TO INTERCONNECT THE FUSELAGE AND THE PYLON OF A HELICOPTER
AT232871B (en) Airfoil for an extremely high-speed missile
AR226171A1 (en) IMPROVEMENTS IN A HELICOPTER TRANSMISSION, INTENDED TO ISOLATE THE FUSELAGE OF THE VIBRATIONS INDUCED BY THE ROTOR