FR2334942A1 - Control of approach of aircraft during landing - regulates deceleration in accordance with total slope compared with reference slope - Google Patents

Control of approach of aircraft during landing - regulates deceleration in accordance with total slope compared with reference slope

Info

Publication number
FR2334942A1
FR2334942A1 FR7537861A FR7537861A FR2334942A1 FR 2334942 A1 FR2334942 A1 FR 2334942A1 FR 7537861 A FR7537861 A FR 7537861A FR 7537861 A FR7537861 A FR 7537861A FR 2334942 A1 FR2334942 A1 FR 2334942A1
Authority
FR
France
Prior art keywords
slope
total
approach
accordance
altitude
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
FR7537861A
Other languages
French (fr)
Other versions
FR2334942B1 (en
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 Francaise dEquipements pour la Navigation Aerienne SFENA SA
Original Assignee
Societe Francaise dEquipements pour la Navigation Aerienne SFENA 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 Francaise dEquipements pour la Navigation Aerienne SFENA SA filed Critical Societe Francaise dEquipements pour la Navigation Aerienne SFENA SA
Priority to FR7537861A priority Critical patent/FR2334942A1/en
Publication of FR2334942A1 publication Critical patent/FR2334942A1/en
Application granted granted Critical
Publication of FR2334942B1 publication Critical patent/FR2334942B1/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
    • G01C23/00—Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
    • G05D1/00—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot
    • 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

Abstract

A control system is described for controlling the decelerated approach of an aerodyne on the "glide". Use is made of the properties of the total shape or gradient, s. The altitude (ho) and thus the instant at which it is necessary to reduce the motorisation and bring out the flap-shutters at the landing position are determined. In this way, at an altitude of hf it is possible to attain the velocity (Vref + 10) knots. At regular intervals, the deceleration of the aircraft is controlled, and also the total slop (S). Thus the pilot knows whether ho must momentarily start up the engines to compensate for deviations between S and a calculated reference slope (S)D. The velocity Vref is attained progressively below the altitude hf by re-establishly the thrust of the engine.
FR7537861A 1975-12-10 1975-12-10 Control of approach of aircraft during landing - regulates deceleration in accordance with total slope compared with reference slope Granted FR2334942A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR7537861A FR2334942A1 (en) 1975-12-10 1975-12-10 Control of approach of aircraft during landing - regulates deceleration in accordance with total slope compared with reference slope

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7537861A FR2334942A1 (en) 1975-12-10 1975-12-10 Control of approach of aircraft during landing - regulates deceleration in accordance with total slope compared with reference slope

Publications (2)

Publication Number Publication Date
FR2334942A1 true FR2334942A1 (en) 1977-07-08
FR2334942B1 FR2334942B1 (en) 1980-04-25

Family

ID=9163592

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7537861A Granted FR2334942A1 (en) 1975-12-10 1975-12-10 Control of approach of aircraft during landing - regulates deceleration in accordance with total slope compared with reference slope

Country Status (1)

Country Link
FR (1) FR2334942A1 (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2958050A1 (en) * 2010-03-24 2011-09-30 Dassault Aviat METHOD AND SYSTEM FOR MANAGING THE ENERGY VARIATION OF AN AIRCRAFT
US8706324B2 (en) 2010-03-24 2014-04-22 Dassault Aviation Device for displaying the energy variation of an aircraft, corresponding method and system for displaying the energy variation
CN111580552A (en) * 2020-05-09 2020-08-25 陕西飞机工业（集团）有限公司 Automatic flight control method for circular flight path of airplane
US11358733B2 (en) 2020-01-21 2022-06-14 Rockwell Collins, Inc. Optimum idle descent start point display based on current conditions

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2958050A1 (en) * 2010-03-24 2011-09-30 Dassault Aviat METHOD AND SYSTEM FOR MANAGING THE ENERGY VARIATION OF AN AIRCRAFT
US8527173B2 (en) 2010-03-24 2013-09-03 Dassault Aviation Method and system for managing the energy variation of an aircraft
US8706324B2 (en) 2010-03-24 2014-04-22 Dassault Aviation Device for displaying the energy variation of an aircraft, corresponding method and system for displaying the energy variation
US11358733B2 (en) 2020-01-21 2022-06-14 Rockwell Collins, Inc. Optimum idle descent start point display based on current conditions
CN111580552A (en) * 2020-05-09 2020-08-25 陕西飞机工业（集团）有限公司 Automatic flight control method for circular flight path of airplane
CN111580552B (en) * 2020-05-09 2023-08-04 陕西飞机工业（集团）有限公司 Automatic flight control method for circular flight path of airplane

Also Published As

Publication number Publication date
FR2334942B1 (en) 1980-04-25

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Legal Events

Date Code Title Description
ST Notification of lapse