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Accession Number:
ADA288610
Title:
Development of a Nonlinear Simulation for the McDonnell Douglas F-15 Eagle with a Longitudinal TECS Control-Law.
Descriptive Note:
Master's thesis,
Corporate Author:
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH
Report Date:
1994-09-01
Pagination or Media Count:
158.0
Abstract:
The purpose of this report is to develop using SIMULINK an aircraft simulation that couples the nonlinear equations of motion with the nonlinear aerodynamic and engine performance data. The simulation has been designed using data from actual flight testing of the McDonnell Douglas E-15 Eagle. The ultimate objective is to provide a generic framework for the development of nonlinear simulations of other aircraft with minimal required changes. Design of a longitudinal autopilot using the Total Energy Control System TECS concept is accomplished using the linearized model and later validated with the nonlinear model. 1.2 Analysis of Data Provided The following sections summarize the model characteristics and the relevant support modules for the F-15 described in 5. The numerical data were provided in the format of a Genesis simulation used at Wright-Patterson and the coding was subsequently converted from EORTRAN to MATLAB. A detailed description of the model follows in Chapter 2. The evaluation of the open-loop nonlinear model and the design of the TECS control law will be accomplished at the two flight points shown in Table 1.1. Other flight conditions throughout the flight envelope will also be investigated.
Distribution Statement:
APPROVED FOR PUBLIC RELEASE
