GB1398905A - Erection of gyroscopes - Google Patents

Erection of gyroscopes

Info

Publication number
GB1398905A
GB1398905A GB3202172A GB3202172A GB1398905A GB 1398905 A GB1398905 A GB 1398905A GB 3202172 A GB3202172 A GB 3202172A GB 3202172 A GB3202172 A GB 3202172A GB 1398905 A GB1398905 A GB 1398905A
Authority
GB
United Kingdom
Prior art keywords
signal
amplifier
circuit
aircraft
accelerometer
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
GB3202172A
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.)
Societe de Fabrication dInstruments de Mesure SFIM SA
Original Assignee
Societe de Fabrication dInstruments de Mesure SFIM SA
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 Societe de Fabrication dInstruments de Mesure SFIM SA filed Critical Societe de Fabrication dInstruments de Mesure SFIM SA
Publication of GB1398905A publication Critical patent/GB1398905A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • G01C19/46—Erection devices for restoring rotor axis to a desired position
    • G01C19/48—Erection devices for restoring rotor axis to a desired position operating by electrical means
    • 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
    • G01C19/46—Erection devices for restoring rotor axis to a desired position

Landscapes

  • Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • General Physics & Mathematics (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Gyroscopes (AREA)
  • Navigation (AREA)

Abstract

1398905 Gyroscopes SOC DE FABRICATION D'INSTRUMENTS DE MESURE 7 July 1972 [8 July 1971] 32021/72 Heading G1C Apparatus for erecting a gyrovertical on an aircraft so as to compensate for the effects of gravity comprises an accelerometer 3 which provides a signal indicative of both the acceleration of the aircraft and the effect of gravity in a vertical longitudinal plane of the aircraft, a speed detector 4 providing a signal corresponding to the speed of the aircraft in the longitudinal plane, and a differential amplifier 9 which provides a signal proportional to the difference of the signals supplied on the one hand by the accelerometer 3 and on the other hand by a circuit 6 which differentiates the speed signal from the detector 4 to provide an acceleration signal, the output from the amplifier 9 being arranged to actuate a torque motor 2 in driving connection with the gyroscope but preferably only when the accelerometer signal is below a predetermined value. This predetermined value is set by a threshold circuit 12 which opens a switch 11 in the circuit between the amplifier 9 and torque motor 2 when the predetermined value is exceeded. The accelerometer 3 may be of the electrolytic type, the speed detector 4 may be an altitude compensated anemometer, the input signals to the amplifier 9 may be controlled by low pass filters 7,8 and the output signal from the amplifier 9 may be supplied to the torque motor 2 through a clipping circuit 10 which controls the maximum torque which can be applied. A demodulator 5 for converting sinusoidal signals from the speed detector 4 to direct current signals may be arranged at the input to the differentiating circuit 6.
GB3202172A 1971-07-08 1972-07-07 Erection of gyroscopes Expired GB1398905A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7124984A FR2145067A5 (en) 1971-07-08 1971-07-08

Publications (1)

Publication Number Publication Date
GB1398905A true GB1398905A (en) 1975-06-25

Family

ID=9080022

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3202172A Expired GB1398905A (en) 1971-07-08 1972-07-07 Erection of gyroscopes

Country Status (3)

Country Link
DE (1) DE2233601A1 (en)
FR (1) FR2145067A5 (en)
GB (1) GB1398905A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2951125A1 (en) * 1979-12-19 1981-07-02 Messerschmitt-Bölkow-Blohm GmbH, 8000 München METHOD FOR DETERMINING THE TRUE SOLAR DIRECTION OF AIRCRAFT AND SPACE VEHICLES

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4255979A (en) * 1978-01-16 1981-03-17 The Singer Company Pulse width modulated binary rebalance rate capture loop control for two-degree-of-freedom dry tuned gyro

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2951125A1 (en) * 1979-12-19 1981-07-02 Messerschmitt-Bölkow-Blohm GmbH, 8000 München METHOD FOR DETERMINING THE TRUE SOLAR DIRECTION OF AIRCRAFT AND SPACE VEHICLES

Also Published As

Publication number Publication date
DE2233601A1 (en) 1973-01-25
FR2145067A5 (en) 1973-02-16

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Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee