Stability & Performance Characteristics Of A Jaguar Aircraft From Post Flight Data Analysis (Revised)

The Aeronautical Development Agency Brought Together Aircraft Systems And Testing Establishment, The HAL Flight Test Centre And The Flight Mechanics & Controls Group Of NAL To Perform Planned Flight Tests On A Jaguar Aircraft Of Indian Airforce . The Aim Of The Programme Was To Generate The Drag Polar Type Performance 'Data, Stability And Control Derivatives For The Aircraft And To Make A Handling Quality Assessment Of The Aircraft . This Document Presents A Comprehensive Analysis Of The Preprocessed Flight Test Data At The Flight Mechanics And Controls Division.By Properly Exciting The Necessary Modalities And Analysing The Responses Using Nonlinear Maximum Likelihood Estimation Method With Appropriate Mathematical Models, Consistent Aircraft Parameters Are Generated . It Is Shown That The Maneuvers Such As The Roller Coaster, Windup Turns And Low Speed Slow Down Provide The Aircraft Drag Polar Covering Full Angle Of Attack Range And Full Range Of Load Factors. The Document Provides The Jaguar Drag Polars , The Longitudinal/ Lateral Stability And Control Derivatives And .A Handling Quality Assessment Of The Short Period Mode Generated From Response Analysis . The Results Are Compared With Data From The Aircraft Manufacturer And Are Found To Match Reasonably Well . This Programme Also Demonstrates The Ability Of The Bangalore Aeronautical Community In Addressing Comprehensive Flight Test Programmes Of Future Aircraft Like The Light Combat Aircraft . The Results Presented In This Document Supersede Those Reported In NAL PD-SE-891

View the PDF document PC Based Flight Path Reconstruction Using UD Factorisation Filtering Algorithm .

The results of flight path reconstruction using UD factorisation-based Kalman filtering algorithm are presented. The algorithm was implemented using PC-MATLAB functions and validated for simulated as well as real flight data. It is of considerable relevance to analysis of aircraft accident data and general flight data for aerospace vehicles

Graphics for interactive PC based parameter estimation package

This document describes the capabilities package developed in Turbo-C for flight data analysis using maximum of Graphics use {h interactive likelihood estimation metho

Aerodynamic parameter estimation from dynamic maneuvers by two step methodology

In this document two step methodology to estimate aerodynamic derivatives of a transport aircraft from dynamic maneuvers is thoroughly described. The results of parameter with maximum likelihood method and different types of dynamic maneuvers or their combination are presented. The approach enhances confidence in the methods as well as in the result