WO1992015975A1 - Instrument destine a detecter des trajectoires de vol manquant de securite lorsque le systeme de guidage automatique est en fonction - Google Patents

Instrument destine a detecter des trajectoires de vol manquant de securite lorsque le systeme de guidage automatique est en fonction Download PDF

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Publication number
WO1992015975A1
WO1992015975A1 PCT/US1992/000896 US9200896W WO9215975A1 WO 1992015975 A1 WO1992015975 A1 WO 1992015975A1 US 9200896 W US9200896 W US 9200896W WO 9215975 A1 WO9215975 A1 WO 9215975A1
Authority
WO
WIPO (PCT)
Prior art keywords
aircraft
altitude
armed
warning
ground
Prior art date
Application number
PCT/US1992/000896
Other languages
English (en)
Inventor
Charles D. Bateman
Original Assignee
Sundstrand Corporation
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 Corporation filed Critical Sundstrand Corporation
Publication of WO1992015975A1 publication Critical patent/WO1992015975A1/fr

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Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
    • G01C5/00—Measuring height; Measuring distances transverse to line of sight; Levelling between separated points; Surveyors' levels
    • G01C5/06—Measuring height; Measuring distances transverse to line of sight; Levelling between separated points; Surveyors' levels by using barometric means
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
    • G01S13/88—Radar or analogous systems specially adapted for specific applications
    • G01S13/93—Radar or analogous systems specially adapted for specific applications for anti-collision purposes
    • G01S13/933—Radar or analogous systems specially adapted for specific applications for anti-collision purposes of aircraft or spacecraft
    • G01S13/935—Radar or analogous systems specially adapted for specific applications for anti-collision purposes of aircraft or spacecraft for terrain-avoidance
    • 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

Definitions

  • This invention relates generally to ground proximity warning systems, and more particularly to a ground proximity warning system usable with automated guidance systems such as flight directors, flight management systems, auto pilots and flight guidance systems for the purpose of warning the pilot when the automated guidance system is guiding the aircraft along an unsafe flight path.
  • Various ground proximity warning systems that warn the pilot of an aircraft of an unsafe flight condi ⁇ tion are known. These systems generally monitor various flight parameters, such as radio altitude and rate, barometric altitude and rate and deviation from the glideslope and generate warnings in the event of in- sufficient terrain clearance, excessive closure rate, excessive barometric sink rate and deviation below the glideslope beam.
  • Various automated guidance systems such as flight directors, flight management systems, auto pilots and flight guidance systems are also known. These devices employ gyros to provide heading and pitch infor ⁇ mation and an artificial horizon. In addition, these devices receive glideslope and localizer beams that they couple onto in order to guide the aircraft to the touch ⁇ down point on the runway.
  • the single figure is a block diagram of the warning system according to the invention.
  • DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT Referring now to the drawing, the system according to the invention is generally designated by the reference numeral 10 and contains a ground proximity warning system 12 that may be a relatively sophisticated ground proximity warning system such as the Mark VII ground proximity warning system manufactured by Sundstrand Data Control, Inc. of Redmond, Washington, or a system as disclosed in, for example. United States Patent No. 3,946,358, incorporated herein by reference.
  • a multiple mode ground proximity warning system When a multiple mode ground proximity warning system is used as the ground proximity warning system 12, it receives a radio altitude and a radio altitude rate signal from a radio altitude source 14, a baro ⁇ metric altitude and rate signal from a barometric source 16 and a glideslope deviation signal from a glideslope receiver 18.
  • a Z-velocity signal from an inertial navigation system may be used instead of the barometric altitude rate to provide vertical velocity information.
  • the ground proximity warning system 12 receives a signal from an automated guidance system such as a flight director or a flight guidance system or other similar device 20. The ground proximity warning system 12 receives signals representative of the status of the flight director or flight guidance system.
  • the status signals may take the form of arming logic outputs that are normally used for flight deck annuncia ⁇ tion of status during the approach process. These signals indicate whether the flight director or flight guidance system is armed, and also indicates the par- ticular modes of operation of the flight director or flight guidance system 20 that have been armed.
  • the ground proximity warning system 12 receives signals from a localizer receiver 22 that pro ⁇ vides an indication of the deviation of the aircraft from the localizer beam.
  • An annunciator 24 receives advisory and warning messages generated by the ground proximity warning system 12 and relays them to the pilot.
  • the annunciator 24 may be either a visual or an aural annunciator, but an aural annunciator is prefer- able because it is able to provide specific voice messages generated by the ground proximity warning system 12 to the pilot in order to provide him with specific information defining the problem.
  • a modern automated guidance system such as the flight director or flight guidance system 20 has many modes of operations, among them a glide path mode, a localizer mode and an altitude mode.
  • the glide path mode When the glide path mode is armed, the flight director or flight guid ⁇ ance system 20 captures the glideslope beam and guides the aircraft along the glideslope beam at approximately a 3' angle toward the end of the runway.
  • the localizer mode When the localizer mode is armed, the flight director or flight guidance system 20 acquires the localizer beam that pro ⁇ vides azimuth information and guides the aircraft along a path in line with the runway center line.
  • a pre ⁇ determined altitude is selected and the flight director or flight guidance system maintains the aircraft at the preselected altitude.
  • the status signals from the flight director or flight guidance system 20 are received by the ground proximity warning system 12 and compared with signals from the radio altitude signal source 14 to determine whether there is sufficient terrain clearance when the flight director or flight guidance system 20 is being used by the pilot. For example, when the glide path mode is armed, but the flight director or flight guid ⁇ ance system has not coupled or captured the beam, i.e., is not on track with the beam, and the aircraft is at less than a predetermined altitude, for example, 1000 feet above the ground, something is wrong. In such an event, an appropriate advisory message could be given to the pilot.
  • a predetermined altitude for example, 1000 feet above the ground
  • Examples of such messages are "TOO LOW, TERRAIN”, “GLIDESLOPE”, “GLIDESLOPE NOT COUPLED”, and a readout of the altitude, for example 1000 feet could also be given.
  • a readout of the altitude for example 1000 feet could also be given.
  • another condition specific advisory message would be given.
  • An example of such a message is "TOO LOW, TERRAIN”, “LOCALIZER, LOCALIZER NOT COUPLED”.
  • An announcement of the altitude could also be made.
  • the deviation signal from the localizer 22 can also be monitored.

Landscapes

  • Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Automation & Control Theory (AREA)
  • Electromagnetism (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Traffic Control Systems (AREA)

Abstract

Système d'alarme de proximité au sol (12) destiné à être utilisé conjointement avec un système de guidage automatique (20), qui transmet un signal d'alarme (24) au pilote d'un avion se préparant à atterrir si le système de guidage automatique (20) n'est pas enclenché ou n'est pas sur la trajectoire. Ledit système d'alarme détermine si le système de guidage automatique est enclenché, et surveille les paramètres de vol tels que l'altitude (14, 16) et la déviation du faisceau directeur (22) et produit un signal d'alarme si l'avion est trop bas ou présente une déviation excessive par rapport au faisceau de radioalignement.
PCT/US1992/000896 1991-03-07 1992-02-04 Instrument destine a detecter des trajectoires de vol manquant de securite lorsque le systeme de guidage automatique est en fonction WO1992015975A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US666,119 1984-10-29
US66611991A 1991-03-07 1991-03-07

Publications (1)

Publication Number Publication Date
WO1992015975A1 true WO1992015975A1 (fr) 1992-09-17

Family

ID=24672913

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US1992/000896 WO1992015975A1 (fr) 1991-03-07 1992-02-04 Instrument destine a detecter des trajectoires de vol manquant de securite lorsque le systeme de guidage automatique est en fonction

Country Status (1)

Country Link
WO (1) WO1992015975A1 (fr)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2890442A (en) * 1951-05-11 1959-06-09 Sperry Gyroscope Co Ltd Failure warning systems for navigational apparatus
US3382498A (en) * 1965-10-04 1968-05-07 Csf I.l.s. air-borne receiver
US3521229A (en) * 1966-09-02 1970-07-21 Sud Aviat Soc Nationale De Con Safety device for use in aircraft during automatic landing
US3936796A (en) * 1974-06-19 1976-02-03 Sundstrand Data Control, Inc. Aircraft ground proximity warning instrument
US3947809A (en) * 1975-01-13 1976-03-30 Sundstrand Data Control, Inc. Below glide slope advisory warning system for aircraft
US4684948A (en) * 1983-07-08 1987-08-04 Sundstrand Data Control, Inc. Ground proximity warning system having modified terrain closure rate warning on glide slope approach

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2890442A (en) * 1951-05-11 1959-06-09 Sperry Gyroscope Co Ltd Failure warning systems for navigational apparatus
US3382498A (en) * 1965-10-04 1968-05-07 Csf I.l.s. air-borne receiver
US3521229A (en) * 1966-09-02 1970-07-21 Sud Aviat Soc Nationale De Con Safety device for use in aircraft during automatic landing
US3936796A (en) * 1974-06-19 1976-02-03 Sundstrand Data Control, Inc. Aircraft ground proximity warning instrument
US3947809A (en) * 1975-01-13 1976-03-30 Sundstrand Data Control, Inc. Below glide slope advisory warning system for aircraft
US4684948A (en) * 1983-07-08 1987-08-04 Sundstrand Data Control, Inc. Ground proximity warning system having modified terrain closure rate warning on glide slope approach

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