CA951409A - Trim reference for helicopter feel augmentation system - Google Patents

Trim reference for helicopter feel augmentation system

Info

Publication number
CA951409A
CA951409A CA132,306,A CA132306A CA951409A CA 951409 A CA951409 A CA 951409A CA 132306 A CA132306 A CA 132306A CA 951409 A CA951409 A CA 951409A
Authority
CA
Canada
Prior art keywords
helicopter
augmentation system
trim reference
feel augmentation
feel
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
CA132,306,A
Other languages
English (en)
Other versions
CA132306S (en
Inventor
Gerald W. Parkinson
Jack R. Cutting
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.)
RTX Corp
Original Assignee
United Aircraft Corp
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 United Aircraft Corp filed Critical United Aircraft Corp
Application granted granted Critical
Publication of CA951409A publication Critical patent/CA951409A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/56—Mechanisms 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
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
    • G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
    • G05D1/0055—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots with safety arrangements
    • G05D1/0061—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots with safety arrangements for transition from automatic pilot to manual pilot and vice versa

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Automation & Control Theory (AREA)
  • Mechanical Engineering (AREA)
  • Toys (AREA)
  • Control Of Position Or Direction (AREA)
CA132,306,A 1971-05-20 1972-01-12 Trim reference for helicopter feel augmentation system Expired CA951409A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US14657071A 1971-05-20 1971-05-20

Publications (1)

Publication Number Publication Date
CA951409A true CA951409A (en) 1974-07-16

Family

ID=22517996

Family Applications (1)

Application Number Title Priority Date Filing Date
CA132,306,A Expired CA951409A (en) 1971-05-20 1972-01-12 Trim reference for helicopter feel augmentation system

Country Status (6)

Country Link
US (1) US3700995A (enExample)
CA (1) CA951409A (enExample)
DE (1) DE2224029A1 (enExample)
FR (1) FR2139095B1 (enExample)
GB (1) GB1336975A (enExample)
IT (1) IT955656B (enExample)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4313165A (en) * 1979-10-23 1982-01-26 United Technologies Corporation Force feel actuator with limited proportional/integral error feedback
US4398242A (en) * 1980-02-25 1983-08-09 The Boeing Company Electronic controller
DE3200839C1 (de) * 1982-01-14 1983-08-25 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Vorrichtung zum Trimmen von Flugzeugen
DE3416969A1 (de) * 1984-05-08 1985-11-14 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Verfahren und vorrichtung zur steuerkraftstabilisierung bei einem drehfluegelflugzeug
DE3431583A1 (de) * 1984-08-28 1986-03-13 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Vorrichtung zur automatischen beseitigung von steuerkraftfehlern bei luftfahrzeugen, insbesondere hubschraubern
US5522568A (en) * 1993-11-09 1996-06-04 Deka Products Limited Partnership Position stick with automatic trim control
FR2787763B1 (fr) * 1998-12-24 2001-02-23 Eurocopter France Dispositif d'aide au recentrage d'un organe de commande d'un aeronef
US11560225B2 (en) 2020-07-15 2023-01-24 Beta Air, Llc Hover and thrust control assembly for dual-mode aircraft
US11518497B2 (en) 2020-07-15 2022-12-06 Beta Air, Llc Hover and thrust control assembly for dual-mode aircraft

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2850251A (en) * 1954-04-08 1958-09-02 Wilbur A Joerndt Roll compensator for guided missiles
US3136698A (en) * 1962-08-24 1964-06-09 Estle R Mann Servo-controlled regulator for neutronic reactors
US3360755A (en) * 1967-02-23 1967-12-26 Stackpole Carbon Co Manually and electrically operated potentiometer
US3585561A (en) * 1969-07-15 1971-06-15 Danfoss As Restoring potentiometer for a servomotor

Also Published As

Publication number Publication date
FR2139095A1 (enExample) 1973-01-05
DE2224029A1 (de) 1972-12-07
IT955656B (it) 1973-09-29
US3700995A (en) 1972-10-24
GB1336975A (en) 1973-11-14
FR2139095B1 (enExample) 1977-12-23

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