Simulation Modeling Of A Transport Aircraft Using Flight Test Data

The Mathematical Models Using Flight Test Data With Respect To A Transport. Aircraft For The Offline Simulation Are Described In This Document. For The Purpose Of Simulation Validation Process, Representative Flight Data Sets Are Selected From A Data Bank Which Was Created Previously Using Data From Actual Flight Maneuvers

Estimation of Horizontal Tail loads of MTC-21 Aircraft

In the maneuvering flight of an aircraft, horizontal tail experiences heavy loads which is a factor of the fatigue life of the aircraft. This report contains the estimated values of the horizontal tail loads of MiG-21BIS aircraft for different flight conditions. These results are used to generate the tail load spectrum for the full scale fatigue testing of aircraft at NAL. The method used is based on a simple procedure which uses the load factor time history and the time to reach peak normal acceleration as design parameters in the estimation of horizontal tail loads

A Scheme For Packing And Unpacking Data

An Encryption Algorithm For Converting Aerodynamic Data set To A Form Which Meets The Twin Goals Of Secrecy And Optimal Storage Is Proposed. Algorithm For Packing And Unpacking Of The Data Items Along With Software Is Discussed Using Actual Aerodynamic Data

Post Flight Missile Parameter Identification for aeroballistic range

This document is a detailed project proposal for estimation of aerodynamic parameters of missile models from ballistic range data

Flight Simulation of HS - 748 with and without rotodome Part 3- Aerostatic Model Formulation

The mathematical models and data used in the off-line flight simulation of the rotodomed aircraft have been described in detail in Part 1 . The issues related to the Rolls Royce Engine simulation studies have been presented in Part 2 . In this document, static wind tunnel test data generated at H .A .L and considered as acceptable by BAE has been used as a reference data for verifying and formulating the aero-static model and associated data for HS-748 and AEW configurations . The resulting static model has been combined with dynamic model to arrive at an overall representative Aero model for use in flight simulation studies . This procedure is vital for unusual aircraft configurations as most of the data at design stage is available only from static wind tunnel tests

On the use of modal sensitivity measures in flight control applications

One of the primary objectives of feadback control is to ensure that system response remain well behaved even under parameter uncertainty. Depending on the mathematical formulation of the problem and/or the synthesis approach employed, various measures can be postulated to ascertain system sensitivity properties. If role(eigenvalue) assignment criterion forms the basis of controller design the associated problem is clearly that of eigenvalue/eigenvector perturbation. Since system response is fully characterized by its eigenvalues and eignvectors their sensitivities form a national basis to analyse trajectory sensitivities of dynamic system in the present paper a set of modal sensitivity measures are derived using classical linear perturbation theory of the eigenvalue problem. Their utility is illustrated by designing minimum sensitivity controllers for an aircraft

Flight Simulation Of HS-748 With And Without Rotodome Part-4 : Handling Qualities And Dynamic Responses

The Mathematical And Data Used In Off-Line Simulation Of The Rotodomed Aircraft Have Been Described In Detail In Part-1 . The Issue Related To The Rolls Royce Engine Simulation Studies Have Been Presented In Part-2 . The Formulation Of The Aerostatic 'Model And Its Verification Has Been Discussed In Part-3 . In This Report, The Results Of The Handling Qualities And Dynamic .Responses Of Both The Basic And The Aew Are Presented. The Results Are Discussed Within The Proposed Restricted C.G. Envelope And Speed Limits Of AEW

Non-linear maximum likelihood estimation of stability derivatives from range data

A parameter identification technique of extracting nondimensional stability derivatives for the AGARD standard ballistic correlation model HB-2 from supersonic free-flight data is investigated. Based on the Maximum Likelihood criterion, the identification technique used is a modified Newton-Raphson quasi-linearization minimization procedure with certain extensions for handling general nonlinear systems without involved program changes. A hybrid type formulation for the 6 degrees of freedom nonlinear equations of motion is employed wherein aerodynamic force and moment representations are in wind-axis and body-axis coordinate systems respectively. Results for both the longitudinal and lateral stability derivatives of the AGARD model demonstrate, as borne out by the excellent fit to the measured motions of a typical flight and accuracy of the parameter estimates, the suitability and power of the maximum likelihood method and functional adequacy of the mathematical model used

Knowledge based sensor failure management using observers

An expert system was developed for sensor failure management for control systems. Keeping the basic structure intact, the expert system can be used in real time environment with suitable modifications. A new strategy has been presented which is useful to investigate in situations with many alternatives providing almost immediate solutions for corrective measures.13

Failure management scheme for use in a flush air data system

This paper concerns the development of a failure management software for use in a Flush Air Data System (FADS).FADS is used for the online computation of air data parameters namely, Mach number, angle of attack and angle of side slip.Failure management, an essential requirement for FADS, especially in the context of aircraft flight control applications, has been addressed using a novel concept called failure indicator vector.This new methodology ensures the selection of correct values out of a number of redundant values of a computed air data parameter.This method leads to symbolic processing techniques, which is found to be very effective in terms of programming efficiency and simple procedure for logical13; reasoning.The method and the software have been successfully tested using the wind tunnel data generated13; at NAL