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Aircraft landing attitude alarming system and alarming control method

A technology of warning system and control method, applied in attitude control, clamping device, closing, etc.

Active Publication Date: 2015-06-03
CIVIL AVIATION UNIV OF CHINA
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

But still lack relevant device and the method that the aircraft landing attitude is warned at present

Method used

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  • Aircraft landing attitude alarming system and alarming control method
  • Aircraft landing attitude alarming system and alarming control method
  • Aircraft landing attitude alarming system and alarming control method

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Embodiment Construction

[0084] The aircraft landing attitude warning system and warning control method provided by the present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0085] The aircraft landing attitude warning system provided by the present invention is illustrated by taking the aircraft with the front three-point landing gear layout as an example, but it is not only applicable to the front three-point landing gear, but also suitable for general aviation aircraft such as aircraft and helicopters with the rear three-point landing gear layout. During the calculation, different parameter values ​​should be set according to the type of landing gear and the aircraft type.

[0086] Such as Figure 5 , figure 1 Shown, the aircraft landing attitude warning system provided by the present invention comprises:

[0087] The first distance measurement module 1, the second distance measurement module 2, the third distance measurement...

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Abstract

The invention discloses an aircraft landing attitude alarming system and an alarming control method. The system comprises a first distance measurement module, a second distance measurement module, a third distance measurement module, a calculation control component, a display component, an alarming loudspeaker and an external interface, wherein the first to third distance measurement modules are connected with the calculation control component respectively; the calculation control component is connected with the display component and the alarming loudspeaker respectively. The aircraft landing attitude alarming system and the alarming control method have the beneficial effects that the real-time distance of an aircraft to the ground and pitching and inclination attitudes in a landing process can be directly displayed, and alarming information can be provided when normal range values are exceeded, so that the dependence of the landing process on the experiences of a pilot is remedied; the descending speed is calculated and displayed, so that excessive impact on the aircraft at the landing moment of the aircraft can further be prevented, the probability of occurrence of a major safety accident such as hard landing is lowered, and the flight safety of the aircraft controlled by various pilots with various qualifications and experiences in the whole landing process is effectively improved.

Description

technical field [0001] The invention belongs to the technical field of aircraft landing attitude control, in particular to an aircraft landing attitude warning system and a warning control method. Background technique [0002] At present, the radio altitude system is usually used to measure the distance of the aircraft to the ground when the aircraft is landing. This system regards the aircraft as a particle and only detects the distance from the belly of the fuselage to the ground. In order to judge the attitude of the aircraft when it lands, the pilot should observe the pitch and tilt angles displayed by the attitude instrument and judge the proximity of each landing gear of the aircraft to the ground based on experience. This caused a heavy landing, impacting the landing gear structure. A heavy landing may have a serious impact on the structure of the aircraft. After a heavy landing, the aircraft needs to undergo multiple inspections on the structure, wings, and landing ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B65D45/00B65D47/02G05D1/08
Inventor 陈艳栗中华
Owner CIVIL AVIATION UNIV OF CHINA
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