Method and device for the monitoring and guidance of an aircraft

Communications: electrical – Aircraft alarm or indicating systems – Nonalarm flight indicator

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340974, 345 7, G01C 2100

Patent

active

056661118

ABSTRACT:
Disclosed is an improvement to the guidance, during the approach and landing stages, of aircraft operating in the categories 2 or 3A of the certification system used by recognized civilian organizations such as the DGAC, the FAA or the JAA, this improvement being designed to render the aircraft capable of working in the immediately lower category, namely the 3A or 3B category, at lower cost. The improvement consists of the addition of a head-up display visor HUD to the attitude heading reference system AHRS and to the air data computer ADC and of the displaying, on the head-up display visor HUD, of the flight path vector whose angular coordinates are drawn from information on east-west and north-south horizontal ground speed delivered by a global positioning receiver GPS according to the avionics standard furthermore used for the localization and navigation of the aircraft. This improvement has the advantage of enabling passage to the immediately lower certification category without requiring the on-board carriage of an inertial platform which is a device that is costly to purchase as well as to maintain.

REFERENCES:
patent: 3967799 (1976-07-01), Muller
patent: 4104612 (1978-08-01), Lowe
patent: 4247843 (1981-01-01), Miller et al.
patent: 4368517 (1983-01-01), Lovering
patent: 4419079 (1983-12-01), Georges et al.
patent: 4454496 (1984-06-01), Lowe
patent: 5357263 (1994-10-01), Fischer et al.
patent: 5406489 (1995-04-01), Timothy et al.
Patent Abstracts Of Japan, vol. 014 No. 235 (M-0975), May 18, 1990 & JP-A-02 060897 (Mitsubishi Heavy Ind Ltd), Mar. 1, 1990, abridged.

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