Method for correcting height error of static pressure source of medium-sized aircraft

A technology of height error and source error, applied in the direction of aircraft component testing, etc., to achieve the effect of correcting static pressure source error, low use cost, and improving accuracy

Pending Publication Date: 2020-06-12
SHAANXI AIRCRAFT CORPORATION
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  • Abstract
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  • Application Information

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Problems solved by technology

Through the patent website query, the current domestic patents are to correct the error of the static pressure source through the selection and positioning of the pressure source, which is very different from the present invention

Method used

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  • Method for correcting height error of static pressure source of medium-sized aircraft
  • Method for correcting height error of static pressure source of medium-sized aircraft
  • Method for correcting height error of static pressure source of medium-sized aircraft

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Embodiment Construction

[0038] Below in conjunction with the accompanying drawings and specific examples the calculation method is further described in detail:

[0039] This method is a method for determining the altitude error of the static pressure source based on the airspeed calibration of a medium-sized aircraft. It considers the flight quality in the landing configuration, the landing performance, and the stall alarm in the landing configuration. The solution method is used to correct the position error of the static pressure source and improve the accuracy of the indicated speed and altitude. The basic flow of the air data system altitude and velocity measurement is as follows: figure 1 shown.

[0040] 1. Obtain the airspeed calibration curve ΔV=f(V c ),like figure 2 shown.

[0041] 2. Determine the static pressure source error correction curve C according to the speed calibration curve obtained in step 1 * P .

[0042] Static pressure source error coefficient is C P =(P Si -P S ) / q ...

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Abstract

The invention belongs to the field of aviation aircraft design, and relates to a method for correcting a height error of a static pressure source of a medium-sized aircraft. Specifically, through a testing flight speed and an optimized atmospheric engine resolving method, the position error of the static pressure source is corrected, and the accuracy of the indication speed and height of an aircraft atmospheric data system is improved. The method is simple and fast, saves the cost of traditional tests, and is suitable for four-engine propeller type medium and large airplanes, transporters andrelated platform airplanes.

Description

technical field [0001] The invention belongs to the field of aviation aircraft design, and is a method for determining the height error of a static pressure source based on the airspeed calibration of a medium-sized aircraft. Specifically, the position error of the static pressure source is corrected through the flight test speed and the calculation method of the optimized atmospheric machine, and the improvement is improved. The Aircraft Air Data System indicates speed and altitude accuracy. Background technique [0002] Since the altitude and speed of the aircraft are converted from information such as static pressure, the error of altitude and speed affects the measurement accuracy of the flight parameters of the aircraft, and the position error of the static pressure source is the main factor affecting the static pressure error. It is affected by factors such as the installation position, installation angle, and aircraft configuration of the sensor on the aircraft, inclu...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/60
CPCB64F5/60
Inventor 马江李昌凡刘建平刘丽江王卓吕莉莉王超孟永良龚莎莎宁超
Owner SHAANXI AIRCRAFT CORPORATION
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