FR2388252A1 - Generateur de signal d'angle de tangage pour avion - Google Patents

Generateur de signal d'angle de tangage pour avion

Info

Publication number
FR2388252A1
FR2388252A1 FR7807286A FR7807286A FR2388252A1 FR 2388252 A1 FR2388252 A1 FR 2388252A1 FR 7807286 A FR7807286 A FR 7807286A FR 7807286 A FR7807286 A FR 7807286A FR 2388252 A1 FR2388252 A1 FR 2388252A1
Authority
FR
France
Prior art keywords
signal generator
angle signal
plane
air
tangle
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.)
Granted
Application number
FR7807286A
Other languages
English (en)
Other versions
FR2388252B1 (fr
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.)
Sundstrand Data Control Inc
Original Assignee
Sundstrand Data Control Inc
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 Sundstrand Data Control Inc filed Critical Sundstrand Data Control Inc
Publication of FR2388252A1 publication Critical patent/FR2388252A1/fr
Application granted granted Critical
Publication of FR2388252B1 publication Critical patent/FR2388252B1/fr
Granted legal-status Critical Current

Links

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
    • G01C9/00—Measuring inclination, e.g. by clinometers, by levels
    • G01C9/005—Measuring inclination, e.g. by clinometers, by levels specially adapted for use in aircraft
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
    • G01C19/00—Gyroscopes; Turn-sensitive devices using vibrating masses; Turn-sensitive devices without moving masses; Measuring angular rate using gyroscopic effects
    • G01C19/02—Rotary gyroscopes
    • G01C19/44—Rotary gyroscopes for indicating the vertical
    • 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
    • G05D1/04—Control of altitude or depth
    • G05D1/06—Rate of change of altitude or depth
    • G05D1/0607—Rate of change of altitude or depth specially adapted for aircraft
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06G—ANALOGUE COMPUTERS
    • G06G7/00—Devices in which the computing operation is performed by varying electric or magnetic quantities
    • G06G7/48—Analogue computers for specific processes, systems or devices, e.g. simulators
    • G06G7/78—Analogue computers for specific processes, systems or devices, e.g. simulators for direction-finding, locating, distance or velocity measuring, or navigation systems

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Computer Hardware Design (AREA)
  • Theoretical Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mathematical Physics (AREA)
  • Automation & Control Theory (AREA)
  • Navigation (AREA)

Abstract

L'invention concerne les dispositifs d'aide à la navigation aérienne. A partir des signaux fournis par un accéléromètre longitudinal 12, un gyroscope vertical 14, et un capteur de vitesse air 24, le générateur de signal de l'invention fournit un signal d'angle de tangage theta * qui est corrigé pour tenir compte des variations de vitesse de la masse d'air dans laquelle se déplace l'avion. Application aux dispositifs d'atterrissage tête haute.
FR7807286A 1977-04-20 1978-03-14 Generateur de signal d'angle de tangage pour avion Granted FR2388252A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US05/789,153 US4095271A (en) 1977-04-20 1977-04-20 Aircraft pitch attitude signal generator

Publications (2)

Publication Number Publication Date
FR2388252A1 true FR2388252A1 (fr) 1978-11-17
FR2388252B1 FR2388252B1 (fr) 1982-10-22

Family

ID=25146745

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7807286A Granted FR2388252A1 (fr) 1977-04-20 1978-03-14 Generateur de signal d'angle de tangage pour avion

Country Status (8)

Country Link
US (1) US4095271A (fr)
JP (1) JPS53131699A (fr)
CA (1) CA1101123A (fr)
DE (1) DE2803029C2 (fr)
FR (1) FR2388252A1 (fr)
GB (1) GB1574270A (fr)
IT (1) IT1102169B (fr)
SE (2) SE435321B (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2418445A1 (fr) * 1978-02-22 1979-09-21 Bofors Ab Appareil determinant la verticale d'un systeme monte sur une base en mouvement, tel qu'un vehicule terrestre ou aerien

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5031102A (en) * 1979-12-03 1991-07-09 The Boeing Company Method and apparatus for aircraft pitch and thrust axes control
US4382283A (en) * 1980-08-08 1983-05-03 United Technologies Corporation Helicopter attitude and airspeed acquisition and retention system
US4390950A (en) * 1980-11-28 1983-06-28 Sundstrand Corporation Angle of attack based pitch generator and head up display
US4405986A (en) * 1981-04-17 1983-09-20 The United States Of America As Represented By The Secretary Of The Army GSP/Doppler sensor velocity derived attitude reference system
FR2511146B1 (fr) * 1981-08-07 1986-07-25 British Aerospace Instrument de navigation
US4481586A (en) * 1982-03-09 1984-11-06 Sperry Corporation Adaptive washout circuit for use in a stability augmentation system
US4583030A (en) * 1982-08-03 1986-04-15 Century Flight Systems, Inc. Pitch/trim control
US4646243A (en) * 1983-01-13 1987-02-24 The Boeing Company Apparatus for determining the groundspeed rate of an aircraft
US4675822A (en) * 1985-10-31 1987-06-23 The Singer Company Doppler-inertial data loop for navigation system
US4725811A (en) * 1986-02-13 1988-02-16 Sundstrand Data Control, Inc. Wind shear detection and alerting system
FR2614694B1 (fr) * 1987-04-28 1989-06-30 Equip Navigation Aerienne Centrale d'attitude integree pour aerodyne
US5396425A (en) * 1993-08-27 1995-03-07 The United States Of America As Represented By The Secretary Of The Air Force Vertical velocity indicator
US5841018A (en) * 1996-12-13 1998-11-24 B. F. Goodrich Avionics Systems, Inc. Method of compensating for installation orientation of an attitude determining device onboard a craft
FR3008499B1 (fr) * 2013-07-12 2015-08-07 Airbus Operations Sas Procede et dispositif d'affichage en temps reel d'une consigne d'assiette sur un aeronef lors d'un pilotage manuel.
GB2534417B (en) * 2015-01-26 2019-06-12 Atlantic Inertial Systems Ltd Multiple sensor integration
US10532741B2 (en) 2017-10-02 2020-01-14 Deere & Company Method of using predicted vehicle accelerations to improve roll and pitch measurement accuracy in a tracked machine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3467799A (en) * 1965-12-08 1969-09-16 Murray Mfg Corp Elimination of arcing effects in circuit breakers
US3691356A (en) * 1970-12-10 1972-09-12 Sperry Rand Corp Speed command and throttle control system for aircraft
US3948096A (en) * 1971-03-16 1976-04-06 Sperry Rand Corporation Apparatus for computing the acceleration of an aircraft along its flight path
US4012713A (en) * 1975-11-05 1977-03-15 Safe Flight Instrument Corporation System for providing an indication of wind shear

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3215374A (en) * 1962-01-10 1965-11-02 North American Aviation Inc Vehicle control system
US3686626A (en) * 1970-06-03 1972-08-22 United Control Corp Aircraft instrument
US3654806A (en) * 1970-06-18 1972-04-11 Sundstrand Data Controls Inc Aircraft instrument
US3816005A (en) * 1970-06-22 1974-06-11 Sundstrand Data Control Head-up display
US3744309A (en) * 1970-07-20 1973-07-10 United Control Corp Pitch signal calculator for aircraft
US3851303A (en) * 1972-11-17 1974-11-26 Sundstrand Data Control Head up display and pitch generator

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3467799A (en) * 1965-12-08 1969-09-16 Murray Mfg Corp Elimination of arcing effects in circuit breakers
US3691356A (en) * 1970-12-10 1972-09-12 Sperry Rand Corp Speed command and throttle control system for aircraft
US3948096A (en) * 1971-03-16 1976-04-06 Sperry Rand Corporation Apparatus for computing the acceleration of an aircraft along its flight path
US4012713A (en) * 1975-11-05 1977-03-15 Safe Flight Instrument Corporation System for providing an indication of wind shear

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2418445A1 (fr) * 1978-02-22 1979-09-21 Bofors Ab Appareil determinant la verticale d'un systeme monte sur une base en mouvement, tel qu'un vehicule terrestre ou aerien

Also Published As

Publication number Publication date
FR2388252B1 (fr) 1982-10-22
CA1101123A (fr) 1981-05-12
JPS621880B2 (fr) 1987-01-16
SE8400588L (sv) 1984-02-06
IT1102169B (it) 1985-10-07
GB1574270A (en) 1980-09-03
SE8400588D0 (sv) 1984-02-06
DE2803029C2 (de) 1982-12-16
IT7848966A0 (it) 1978-04-19
DE2803029A1 (de) 1978-10-26
SE435321B (sv) 1984-09-17
SE435322B (sv) 1984-09-17
JPS53131699A (en) 1978-11-16
US4095271A (en) 1978-06-13
SE7803524L (sv) 1978-10-21

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Legal Events

Date Code Title Description
ST Notification of lapse