GB1340155A - Aircraft landing speed control apparatus - Google Patents

Aircraft landing speed control apparatus

Info

Publication number
GB1340155A
GB1340155A GB2502872A GB2502872A GB1340155A GB 1340155 A GB1340155 A GB 1340155A GB 2502872 A GB2502872 A GB 2502872A GB 2502872 A GB2502872 A GB 2502872A GB 1340155 A GB1340155 A GB 1340155A
Authority
GB
United Kingdom
Prior art keywords
aircraft
speed
signal
landing
controlling
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
GB2502872A
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.)
Bodenseewerk Geratetechnik GmbH
Original Assignee
Bodenseewerk Geratetechnik GmbH
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 Bodenseewerk Geratetechnik GmbH filed Critical Bodenseewerk Geratetechnik GmbH
Publication of GB1340155A publication Critical patent/GB1340155A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • G05D1/0653—Rate of change of altitude or depth specially adapted for aircraft during a phase of take-off or landing
    • G05D1/0661—Rate of change of altitude or depth specially adapted for aircraft during a phase of take-off or landing specially adapted for take-off
    • 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
    • G05D1/0653—Rate of change of altitude or depth specially adapted for aircraft during a phase of take-off or landing
    • G05D1/0676—Rate of change of altitude or depth specially adapted for aircraft during a phase of take-off or landing specially adapted for landing

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)
  • Control Of Velocity Or Acceleration (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Abstract

1340155 Controlling aircraft Àlanding speed BODENSEEWERK GERATETECHNIK GmbH 26 May 1972 [3 June 1971] 25028/72 Heading B7G [Also in Division G3] Apparatus for controlling the landing speed of an aircraft includes a command signal generator which includes computing means for computing, from the all-up weight of the aircraft, the aircraft speed required for landing, the computed speed signal being used in determining a control signal for controlling the landing speed of the aircraft. Aircraft all-up weight is set on a knob 22 which is coupled with a digital indicator 24 and the wiper of a potentiometer 40, the output voltage from which will be proportional to the speed V L of the aircraft with retracted flaps, associated with the set all-up weight. Since the signal V L would be reduced as the landing flaps 46 are extended a potentiometer 44 is adjusted by the flaps through link 48 to provide a flap position signal to a differential amplifier 56 to which the signal V L also is fed. The output VSI from amplifier 56, as a landing speed command signal is fed through a switch 28 to an amplifier 62 which receives also a further signal V representing actual aircraft speed, from an encapsulated sensor 30. The output #V from amplifier 62 is fed to a computer (32, Fig. 1, not shown) which receives also a signal representative of short term linear accelerations of the aircraft, the computer controlling a servomotor for controlling the aircraft landing speed by adjusting the engine throttles. In an alternative embodiment (Fig. 3, not shown) the potentiometers are replaced by synchros.
GB2502872A 1971-06-03 1972-05-26 Aircraft landing speed control apparatus Expired GB1340155A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2127535A DE2127535B2 (en) 1971-06-03 1971-06-03 Cruise control for the final landing speed of aircraft

Publications (1)

Publication Number Publication Date
GB1340155A true GB1340155A (en) 1973-12-12

Family

ID=5809705

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2502872A Expired GB1340155A (en) 1971-06-03 1972-05-26 Aircraft landing speed control apparatus

Country Status (3)

Country Link
DE (1) DE2127535B2 (en)
FR (1) FR2140241B3 (en)
GB (1) GB1340155A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2237899A (en) * 1989-11-10 1991-05-15 Fokker Aircraft Bv Automated approach speed control for an airplane
CN102183961A (en) * 2011-04-08 2011-09-14 张璞 Digital positioning landing control device
CN103144774A (en) * 2011-11-28 2013-06-12 埃姆普里萨有限公司 Flight control system mode and method providing aircraft speed control

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3640453A1 (en) * 1986-11-27 1988-06-09 Teves Gmbh Alfred BRAKE SLIP CONTROL TWO-CIRCLE VEHICLE BRAKE SYSTEM

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2237899A (en) * 1989-11-10 1991-05-15 Fokker Aircraft Bv Automated approach speed control for an airplane
US5078345A (en) * 1989-11-10 1992-01-07 Fokker Aircraft B.V. Automated approach speed control for an airplane
GB2237899B (en) * 1989-11-10 1994-05-11 Fokker Aircraft Bv Automated approach speed control for an airplane
CN102183961A (en) * 2011-04-08 2011-09-14 张璞 Digital positioning landing control device
CN103144774A (en) * 2011-11-28 2013-06-12 埃姆普里萨有限公司 Flight control system mode and method providing aircraft speed control

Also Published As

Publication number Publication date
FR2140241B3 (en) 1975-08-08
DE2127535A1 (en) 1972-12-14
DE2127535B2 (en) 1975-01-23
FR2140241A1 (en) 1973-01-12

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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