GB1291271A - Improvements in or relating to power transmitting mechanisms, and applications thereof, notably to helicopters - Google Patents

Improvements in or relating to power transmitting mechanisms, and applications thereof, notably to helicopters

Info

Publication number
GB1291271A
GB1291271A GB48884/69A GB4888469A GB1291271A GB 1291271 A GB1291271 A GB 1291271A GB 48884/69 A GB48884/69 A GB 48884/69A GB 4888469 A GB4888469 A GB 4888469A GB 1291271 A GB1291271 A GB 1291271A
Authority
GB
United Kingdom
Prior art keywords
lever
engine
levers
rotor
shaft
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
GB48884/69A
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Sud Aviation Societe Nationale de Constructions Aerdnaettiques
Original Assignee
Sud Aviation Societe Nationale de Constructions Aerdnaettiques
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Sud Aviation Societe Nationale de Constructions Aerdnaettiques filed Critical Sud Aviation Societe Nationale de Constructions Aerdnaettiques
Publication of GB1291271A publication Critical patent/GB1291271A/en
Expired legal-status Critical Current

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/54Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/56Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/32Rotors
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Throttle Valves Provided In The Intake System Or In The Exhaust System (AREA)
  • Toys (AREA)

Abstract

1291271 Controlling aircraft power plant SUD AVIATION SOC NATIONALE DE CONSTRUCTIONS AERONAUTIQUES 6 Oct 1969 [7 Oct 1968 8 Oct 1968] 48884/69 Addition to 1085453 Heading B7G [Also in Division F2] An improvement in the invention disclosed in parent Specification, wherein two engines are selectively clutched into driving connection with a helicopter rotor and/or ancillary systems (not shown) by a manually operated lever 9, Fig. 2, comprises the provision of further levers 23, 24 to which lever 9 is selectively connected to control the power output of the two engines during the clutching operations. The lever 9 is connected through linkage 2 to lever 51 of a selector unit 3, Fig. 5, which comprises a shaft 38 connected to the clutch operating mechanism and secured by a pin 20 to a tubular extension 37 within which is positioned diametrically a shaft 47. Extension 37 is slidably mounted in a reduction gear cover 35 forming part of one engine and carries at its free end a hollow sleeve 51a fast with arm 51, the sleeve having a cam slot 52 co-operating with shaft 47 so that upon movement of arm 51 by lever 9, shaft 38 is moved to the right (Fig. 5) against a compression spring which provides a return motion. A head 47b on shaft 47 actuates a mioroswitch 54 to provide an indication in the cockpit that the ancillary systems are being driven. The levers 9, 23, 24 pass through a slotted gate plate 5 (viewed from the rear in Fig. 7) and lever 9, which carries transverse pins 22, is mounted on a pivot common with levers 23, 24 for rotary and bodily sideways sliding movement. Levers 23, 24 are apertured at 25, 26 and 27 respectively for selective engagement by pins 22. In Fig. 7, lever 9 is in " rotor coupled " position and both engine throttle levers 23, 24 are at " full throttle "; to uncouple the rotor from an engine, lever 9 is moved to the left to pick up lever 23 and then downwards to reduce fuel flow to the engine controlled by lever 23. Lever 9 is then moved across the central transverse slot to pick up lever 24 and then moved down both to uncouple the engine from the rotor and to reduce the fuel flow to the other engine. Lever 9 is finally moved to the left, to reengage lever 23, and upward, with the result that sufficient fuel is supplied to the first engine to cause it to drive the ancillary equipment with the rotor uncoupled. In an alternative embodiment (Figs. 16-23, not shown) the assembly of Fig. 5 is replaced by a rotary electric actuator (101) driven by a reversible motor connected by means of a linkage of reciprocating rods to the clutch apparatus of the parent Specification. The actuator is connected to the lever block 1 via an electric circuit (Fig. 23) which incorporates safety devices and indicator lamps. A bi-stable mechanical flipflop ensures reversal of the actuator motor at the appropriate moment, and a magnetically operated locking device (Figs. 18-22) prevents movement of the throttles during reversal. A time-delayer is incorporated in the circuit, and means are provided for preventing coupling or decoupling if one of the engines is stopped while the helicopter is in flight.
GB48884/69A 1968-10-07 1969-10-06 Improvements in or relating to power transmitting mechanisms, and applications thereof, notably to helicopters Expired GB1291271A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR168928 1968-10-07
FR169098 1968-10-08

Publications (1)

Publication Number Publication Date
GB1291271A true GB1291271A (en) 1972-10-04

Family

ID=26182249

Family Applications (1)

Application Number Title Priority Date Filing Date
GB48884/69A Expired GB1291271A (en) 1968-10-07 1969-10-06 Improvements in or relating to power transmitting mechanisms, and applications thereof, notably to helicopters

Country Status (2)

Country Link
US (1) US3617017A (en)
GB (1) GB1291271A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2410995B (en) * 2002-10-15 2007-05-09 Immersion Corp Products and processes for providing force sensations in a user interface

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5154835A (en) * 1991-12-10 1992-10-13 Environmental Systems & Services, Inc. Collection and separation of liquids of different densities utilizing fluid pressure level control
DE10301978A1 (en) * 2003-01-20 2004-08-05 Eurocopter Deutschland Gmbh Device and method for transmitting and providing the energy of capacitive actuators

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2973661A (en) * 1957-06-17 1961-03-07 Omega Aircraft Corp Selective adjustment control mechanism
CA650897A (en) * 1958-07-15 1962-10-23 Haworth Lionel Single lever aircraft engine control mechanisms
US2967436A (en) * 1959-03-04 1961-01-10 Eric J Steinlein Throttle and clutch control head
US3135234A (en) * 1962-07-30 1964-06-02 Leslie A Turnidge Device for controlling engine and transmission
US3250494A (en) * 1963-03-25 1966-05-10 Ronald T Peterson Control mechanism for variable sweep wing aircraft
FR1422328A (en) * 1964-11-13 1965-12-24 Sud Aviation Improvements in power transmission mechanisms and their applications, particularly in helicopters
DE1234533B (en) * 1965-06-24 1967-02-16 M A N Turbo Ges Mit Beschraenk Control device for combination helicopter with a gas turbine generated pressure gases driven hub rotor

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2410995B (en) * 2002-10-15 2007-05-09 Immersion Corp Products and processes for providing force sensations in a user interface
US8917234B2 (en) 2002-10-15 2014-12-23 Immersion Corporation Products and processes for providing force sensations in a user interface

Also Published As

Publication number Publication date
US3617017A (en) 1971-11-02

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PCNP Patent ceased through non-payment of renewal fee