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Airborne safe landing power control system and method

a technology of power control system and safe landing, which is applied in the direction of vehicle position/course/altitude control, process and machine control, instruments, etc., can solve the problems of system failure to provide the flexibility, reliability and rapid response time that are needed, and the system has not enjoyed widespread commercial success

Inactive Publication Date: 2002-09-05
SAFE FLIGHT INSTR
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Notwithstanding past developments and the need for reliable automatic landing system, such systems have not enjoyed widespread commercial success.
It is believed that such systems fail to provide the needed flexibility, reliability and rapid response time to accommodate rough air, head and tail wind oscillations and other weather related problems.

Method used

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  • Airborne safe landing power control system and method
  • Airborne safe landing power control system and method
  • Airborne safe landing power control system and method

Examples

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Embodiment Construction

[0014] An aircraft safe landing power control system in accordance with the present invention incorporates an improved means for adjusting the thrust by using an automatic throttle system during landings.

[0015] As illustrated in FIG. 1, an aircraft 2 is controlled by conventional means to capture an ILS glide path means or center line 4 as for example disclosed in the U.S. Pat. No. 3,892,373 of Doniger which is incorporated herein in its entirety by reference. At a point A from either level flight below the centerline or from descending flight above the centerline 4, the aircraft 2 tracks the beam centerline 4 from point A to point B. At point B, the flare altitude of about 50 feet above a runway 6, a flare maneuver is engaged to control the aircraft to touch down at point C. It is during the flare maneuver, i.e. from point B to point C that the present invention is applicable.

[0016] FIG. 2 illustrates a prior art automatic landing system which utilizes the sum of altitude rate and ...

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PUM

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Abstract

An airborne power control system for automatically controlling the power of an aircraft during landing is disclssed. The system includes a computer and a minimum airspeed program as a function of altitude. A radio altimeter or the like senses the instantaneous altitude of the aircraft while a pitot tube or the like measures indicated airspeed. A computer and program compare programmed airspeed with actual airspeed for a given altitude. And, a servomotor is provided for decreasing engine thrust where the actual airspeed exceeds the programmed airspeed at any given altitude. An inhibitor inhibits the decrease in engine thrust if the airspeed drops below the programmed airspeed.

Description

[0001] This invention relates to an airborne power control system and method and more particularly to a power control system and method for automatically controlling power during the landing of an aircraft.BACKGROUND FOR THE INVENTION[0002] The need for a highly reliable and safe automatic landing system for aircraft has been recognized. It has also been recognized that any such system should be fully operable under adverse weather conditions with reliability. Such systems must automatically land an aircraft safely in fog or rain, at night, with heavy payloads and produce a smooth landing under any such conditions.[0003] In order to meet the requirements for reliability and to provide for smooth landings under adverse conditions, an automatic landing system must contain control equipment which is insensitive to outside disturbances normally encountered in landings.[0004] In the past, various control systems have been used to control aircraft in-flight. For example, glide slope syste...

Claims

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Application Information

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IPC IPC(8): G05D1/06G05D1/08
CPCG05D1/0676G05D1/0833
Inventor GREENE, LEONARD M.
Owner SAFE FLIGHT INSTR