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Atmospheric data and disturbance wind estimation method based on flight data

A technology of atmospheric data and flight data, applied in computing, civil aviation safety technology and flight data application, reckoning or counting field, can solve the problem of not reflecting the real characteristics of disturbance wind, and achieve the effect of improving state estimation accuracy and modeling accuracy

Pending Publication Date: 2021-07-13
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

On the other hand, in terms of disturbance wind estimation, models such as gust and wind shear are generally established, and turbulent wind is regarded as random noise. This modeling method cannot reflect the real characteristics of disturbance wind

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  • Atmospheric data and disturbance wind estimation method based on flight data
  • Atmospheric data and disturbance wind estimation method based on flight data
  • Atmospheric data and disturbance wind estimation method based on flight data

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Embodiment Construction

[0017] The technical solution of the invention will be described in detail below in conjunction with the accompanying drawings.

[0018] The atmospheric data and disturbance wind estimation method based on flight data disclosed in this application, such as figure 1 As shown, there are three major steps.

[0019] Step 1: Preprocess the flight record data, and preliminarily estimate the true airspeed, angle of attack, prevailing wind and turbulence parameters. Selecting the time series of flight data includes: triaxial acceleration a=[a x ,a y ,a z ] T ;Three-axis angular velocity [p,q,r] T ;Roll, pitch and yaw angles [φ,θ,ψ] T ; Ground speed V G =[V Gx ,V Gy ,V Gz ] T ;recorded value of angle of attack Mach number M; ambient temperature T. The process of preliminarily estimating the true airspeed, angle of attack, prevailing wind and turbulence parameters includes three steps from step 1-A to step 1-C.

[0020] Step 1-A: Estimate the initial value of the true air...

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Abstract

The invention discloses an atmospheric data and disturbance wind estimation method based on flight data, and belongs to the technical field of calculation, reckoning or counting. The method comprises the following steps: firstly, preprocessing flight record data, and preliminarily estimating vacuum speed, incidence angle, prevailing wind and turbulence parameters; thirdly, dividing disturbance wind into prevailing wind and turbulent flow, establishing a prevailing wind state equation based on an index correlation model, establishing a turbulent flow state equation based on a von Karman model, establishing a state equation containing atmospheric data, prevailing wind and turbulent flow by utilizing recorded inertial data, and combining with an established measurement equation to form a Kalman filtering system; and finally, for flight record data with a certain length, adopting a method of combining forward filtering and backward smooth filtering to obtain state estimation of atmosphere data and disturbance wind at any moment, and improving disturbance wind estimation precision on the premise of not establishing an aircraft pneumatic and thrust model.

Description

technical field [0001] The invention relates to the fields of civil aviation safety technology and flight data application, in particular to a method for estimating atmospheric data and disturbance wind based on flight data, and belongs to the technical field of calculation, calculation or counting. Background technique [0002] Atmospheric disturbances such as wind shear and turbulence seriously affect the flight quality, ride quality and flight safety of civil aviation aircraft. The flight data recorder obtains recording parameters from the air data system, inertial navigation system and other systems from the onboard bus, and can record the aircraft flight status, engine status, flight management and various working status of the flight control system in real time. In the analysis of flight accidents induced by atmospheric disturbances, it is of great significance to analyze the true airspeed, angle of attack, sideslip angle, and instantaneous disturbance wind direction a...

Claims

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Application Information

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IPC IPC(8): G06F30/28G06F17/12G06F17/16
CPCG06F30/28G06F17/12G06F17/16
Inventor 高振兴曾丽君向志伟王得宝
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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