FR2389171A1 - Polarisation de reaction a la vitesse d'inclinaison longitudinale d'un helicoptere pour assurer la stabilite de manoeuvre dans l'axe d'inclinaison longitudinale et le palpage de la charge - Google Patents

Polarisation de reaction a la vitesse d'inclinaison longitudinale d'un helicoptere pour assurer la stabilite de manoeuvre dans l'axe d'inclinaison longitudinale et le palpage de la charge

Info

Publication number
FR2389171A1
FR2389171A1 FR7811983A FR7811983A FR2389171A1 FR 2389171 A1 FR2389171 A1 FR 2389171A1 FR 7811983 A FR7811983 A FR 7811983A FR 7811983 A FR7811983 A FR 7811983A FR 2389171 A1 FR2389171 A1 FR 2389171A1
Authority
FR
France
Prior art keywords
longitudinal tilt
helicopter
polarization
longitudinal
maneuvering
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.)
Pending
Application number
FR7811983A
Other languages
English (en)
Inventor
Franklin Amos Tefft
Don Luis Adams
Lou Saxon Cotton
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 Technologies 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 Technologies Corp filed Critical United Technologies Corp
Publication of FR2389171A1 publication Critical patent/FR2389171A1/fr
Pending 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
    • 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
    • G05D1/08—Control of attitude, i.e. control of roll, pitch, or yaw
    • G05D1/0808—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft
    • G05D1/0858—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft specially adapted for vertical take-off of aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Automation & Control Theory (AREA)
  • Toys (AREA)
  • Catching Or Destruction (AREA)

Abstract

L'invention concerne la polarisation de réaction à la vitesse d'inclinaison longitudinale d'un hélicoptère. L'hélicoptère comporte un rotor principal 2 et des éléments de commande prévus pour ce dernier et réagissant à une manette de commande de pas cyclique 16, un gyroscope de commande de vitesse d'inclinaison longitudinale 42 comportant une sortie 40, ainsi qu'un dispositif de polarisation 38 réagissant à la sortie 40 du gyroscope 42 pour modifier le signal de commande de pas cyclique d'une valeur proportionnelle à la sortie 40 du gyroscope 42 dans une direction s'opposant à la vitesse d'inclinaison longitudinale détectée. L'invention est utilisée pour assurer la stabilité de manoeuvre d'un hélicoptère dans l'axe d'inclinaison longitudinale et le palpage de la charge.
FR7811983A 1977-04-27 1978-04-24 Polarisation de reaction a la vitesse d'inclinaison longitudinale d'un helicoptere pour assurer la stabilite de manoeuvre dans l'axe d'inclinaison longitudinale et le palpage de la charge Pending FR2389171A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US05/791,622 US4127245A (en) 1977-04-27 1977-04-27 Helicopter pitch rate feedback bias for pitch axis maneuvering stability and load feel

Publications (1)

Publication Number Publication Date
FR2389171A1 true FR2389171A1 (fr) 1978-11-24

Family

ID=25154274

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7811983A Pending FR2389171A1 (fr) 1977-04-27 1978-04-24 Polarisation de reaction a la vitesse d'inclinaison longitudinale d'un helicoptere pour assurer la stabilite de manoeuvre dans l'axe d'inclinaison longitudinale et le palpage de la charge

Country Status (12)

Country Link
US (1) US4127245A (fr)
JP (1) JPS53136297A (fr)
BE (1) BE866342A (fr)
CA (1) CA1085368A (fr)
DE (1) DE2817323A1 (fr)
DK (1) DK149678A (fr)
FR (1) FR2389171A1 (fr)
GB (1) GB1587088A (fr)
IL (1) IL54526A (fr)
IT (1) IT1095328B (fr)
NL (1) NL7804334A (fr)
NO (1) NO145053C (fr)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4168045A (en) * 1978-02-28 1979-09-18 United Technologies Corporation Speed and collective pitch bias of helicopter longitudinal cyclic pitch
US4279391A (en) * 1979-01-24 1981-07-21 United Technologies Corporation Desensitizing helicopter control response to inadvertent pilot inputs
US4330829A (en) * 1979-01-24 1982-05-18 United Technologies Corporation Helicopter flight stability control induced oscillation suppression
US4528628A (en) * 1982-12-06 1985-07-09 United Technologies Corporation Shutdown monitor for a helicopter pitch bias actuator
CA1246717A (fr) * 1983-08-01 1988-12-13 James J. Howlett Rehausseur de facteur de charge pour aeronef a voilure tournante
US4930988A (en) * 1989-01-02 1990-06-05 Honeywell Inc Individual blade control system for helicopters
US5395077A (en) * 1991-07-19 1995-03-07 Wolford; Thomas A. Multi-axial hand-operated aircraft control and method
US6149527A (en) * 1991-07-19 2000-11-21 Wolford; Thomas A. Apparatus for imparting rotary motion through a flex point
US5499785A (en) * 1994-09-15 1996-03-19 The Boeing Company Autojettison method and apparatus for dual-point suspension systems
US6254037B1 (en) 1999-08-06 2001-07-03 Bell Helicopter Textron Inc. Variable gradient control stick force feel adjustment system
DE102010023228B4 (de) * 2010-06-09 2012-07-12 Deutsches Zentrum für Luft- und Raumfahrt e.V. Stabilisierungseinrichtung
US9266608B2 (en) 2013-03-18 2016-02-23 Sikorsky Aircraft Corporation Compensating for lead-lag in rotor system

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3920966A (en) * 1974-04-29 1975-11-18 Us Air Force Blended manual-automatic control system

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3482805A (en) * 1967-11-14 1969-12-09 Siegfried Knemeyer System for stabilizing the collective control of a helicopter or the corresponding control of other vtol aircraft
US3711042A (en) * 1970-07-13 1973-01-16 Na Sa Aircraft control system
US3733039A (en) * 1971-05-20 1973-05-15 United Aircraft Corp Feel augmentation control system for helicopters
US3833189A (en) * 1971-08-05 1974-09-03 United Aircraft Corp Load stability system

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3920966A (en) * 1974-04-29 1975-11-18 Us Air Force Blended manual-automatic control system

Also Published As

Publication number Publication date
US4127245A (en) 1978-11-28
IL54526A (en) 1982-07-30
DK149678A (da) 1978-10-28
IT7822699A0 (it) 1978-04-26
CA1085368A (fr) 1980-09-09
DE2817323A1 (de) 1978-11-02
JPS53136297A (en) 1978-11-28
NO145053B (no) 1981-09-21
NO781453L (no) 1978-10-30
NO145053C (no) 1982-01-04
BE866342A (fr) 1978-08-14
IT1095328B (it) 1985-08-10
GB1587088A (en) 1981-03-25
NL7804334A (nl) 1978-10-31

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