Flight Path Reconstruction and Wind Estimation Using Flight Test Data from Crash Data Recorder (CDR)

Reduction of Flight Test Data From Linear Accelerometers

Journal of the Royal Aeronautical Society ◽

10.1017/s0368393100125271 ◽

1953 ◽

Vol 57 (510) ◽

pp. 415-415

Author(s):

Andrew Mokrzycki

Keyword(s):

Test Data ◽

Vertical Plane ◽

Flight Test ◽

Flight Path ◽

The Body ◽

Body Axis ◽

List Type ◽

Type Number ◽

Arbitrary Body

The problems discussed in this note refer to the simplest case of the use of linear accelerometers, in which the flight path is in the vertical plane of symmetry of the aeroplane, and the acceleration normal to the path is to be determined.Generally two facts are neglected:– (i)That the accelerometer senses along an arbitrary body axis ZB (Fig. 1), instead of along the wind axis Z (normal to the path).(ii)That the accelerometer is not placed exactly at the e.g. of the aeroplane but at some point A, having co-ordinates xA and zA in the body axes.

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Wind Profile Estimation during Flight Path Reconstruction

Defence Science Journal ◽

10.14429/dsj.70.13596 ◽

2020 ◽

Vol 70 (3) ◽

pp. 231-239

Author(s):

T.K. Nusrath Khadeeja ◽

Jatinder Singh

Keyword(s):

High Performance ◽

Flight Test ◽

Flight Path ◽

Flow Angle ◽

Wind Estimation ◽

Wind Velocities ◽

Profile Estimation ◽

The Impact ◽

Excellent Tool ◽

Data Calibration

Accuracy of flow angles measurements becomes crucial as the aircraft approaches higher angle of attack. Flight path reconstruction (FPR) is an excellent tool for air data calibration. An important element of air data calibration is the estimation of wind velocities. The objective of this paper is to evaluate different approaches of wind estimation within the framework of FPR. Flight test data of a high performance aircraft is subjected to FPR and the estimated wind velocities and flow angle trajectories are presented and discussed to demonstrate the impact of wind estimation on aircraft flow angles. Results clearly show that accuracy of reconstructed flow angles improves when time varying wind models are used. The proposed analytical wind model is found to be as effective as augmented parameters in Extended Kalman filter and computationally less intensive.

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Flight Path Reconstruction and Parameter Estimation Using Output-Error Method

Shock and Vibration ◽

10.1155/2006/960391 ◽

2006 ◽

Vol 13 (4-5) ◽

pp. 379-392 ◽

Cited By ~ 3

Author(s):

Benedito Carlos de Oliveira Maciel ◽

Luiz Carlos Sandoval Góes ◽

Elder Moreira Hemerly ◽

Nei Salis Brasil Neto

Keyword(s):

Test Data ◽

Inertial Sensors ◽

Flight Test ◽

Flight Path ◽

Positioning Systems ◽

Output Error ◽

Control Derivatives ◽

And Control ◽

Derivatives Of ◽

Error Method

This work describes the application of the output-error method using the Levenberg-Marquardt optimization algorithm to the Flight Path Reconstruction (FPR) problem, which constitutes an important preliminary step towards the aircraft parameter identification. This method is also applied to obtain the aerodynamic and control derivatives of a regional jet aircraft from flight test data with measurement noise and bias. Experimental results are reported, employing a real jet aircraft, with flight test data acquired by smart probes, inertial sensors (gyrometers and accelerometers) and Global Positioning Systems (GPS) receivers.

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