The Engineering Analysis and Design of the Aircraft Dynamics Model for the FAA Target Generation Facility - Prepared Report

Oct 24, 2026

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Engineering analysis and design of an aircraft dynamics model developed for the FAA Target Generation Facility. Covers the formulation of six degrees of freedom equations of motion, modal properties for key aircraft motion modes, and model reduction to four degrees of freedom with wind additions. Extends dynamics to trajectory propagation over an Earth model with coordinate transformations, derives state variables, and presents airframe, engine, and standard atmosphere modeling plus numerical integration techniques. Includes longitudinal dynamics examination and feedback control system foundations.

LanguageEnglish

CategoryResearch & Report

FormatPDF

Pages321

Reading Time13 h 29 min

AccessFree to download

INTRODUCTION

BACKGROUND

SCOPE

ORGANIZATION

THE AIRCRAFT EQUATIONS OF MOTION

THE DEFINITION OF THE BODY FRAME AND THE INERTIAL FRAME

DEFINITION OF FLIGHT MECHANICS NOMENCLATURE

THE WIND AND STABILITY REFERENCE FRAMES

THE DERIVATION OF THE SIX DEGREE OF FREEDOM EQUATIONS OF MOTION

THE MODAL PROPERTIES OF THE SIX DEGREE OF FREEDOM MODEL

SIMPLIFYING THE EQUATIONS OF MOTION TO FOUR DEGREES OF FREEDOM

THE ADDITION OF WINDS

TRAJECTORY PROPAGATION OVER AN EARTH MODEL

THE DERIVED STATE VARIABLES

THE AIRFRAME MODEL

THE ENGINE MODEL

THE STANDARD ATMOSPHERE MODEL

INTEGRATION TECHNIQUES

THE INTEGRATION OF THE ROLL EQUATION

DESIGN OF THE LATERAL CONTROL SYSTEM

THE EXAMINATION OF THE LONGITUDINAL DYNAMICS

THE LINEAR MODEL OF THE LONGITUDINAL DYNAMICS

THE ANALYSIS OF LONGITUDINAL AIRCRAFT MODAL PROPERTIES

TRANSFER FUNCTION ANALYSIS OF THE LONGITUDINAL DYNAMICS

THE FEEDBACK CONTROL SYSTEM FOR LONGITUDINAL CONTROL

99162-01 The Engineering Analysis and Design of the Aircraft Dynamics Model For the FAA Target Generation Facility Mark Peters Michael A. Konyak Prepared for: Scott Doucett ANG-E161 Simulation Branch, Laboratory Services Division Federal Aviation Administration William J. Hughes Technical Center Atlantic City, NJ 08405 Under: Air Traffic Engineering Co., LLC 1027 Route 9 South Palermo, NJ 08223 FAA Prime Contract No. DTFAWA-10A-00020 October 2012 Acknowledgments This project was supported under contract No. DTFA03-94-C-0042 (CADSS) with the Federal Aviation Administration William J. Hughes Technical Center, Atlantic City, NJ, under subcontract to System Resources Corporation (SRC) . The author acknowledges the insightful project direction provided by Mr. Dan Warburton of the FAA and Mr. George Chachis of SRC, during the course of this work. The author also wishes to acknowledge the various technical contributions and reviews from the members of the Seagull team. Specifically, the author acknowledges Dr. John Sorensen and Tysen Mueller for their contributions to the error modeling sections of the Navigator development, and George Hunter and JC Gillmore for their leadership and guidance throughout the project. Mark Peters September, 1999 THIS PAGE INTENTIONALLY LEFT BLANK ii Table of Contents 1. INTRODUCTION....................................................................................................1 1.1 BACKGROUND .........................................................................................................1 1.2 SCOPE ......................................................................................................................2 1.3 ORGANIZATION .......................................................................................................2 2. THE AIRCRAFT EQUATIONS OF MOTION ...................................................5 2.1 THE DEFINITION OF THE BODY FRAME AND THE INERTIAL FRAME .........................5 2.2 DEFINITION OF FLIGHT MECHANICS NOMENCLATURE.............................................8 2.3 THE WIND AND STABILITY REFERENCE FRAMES .....................................................9 2.4 THE DERIVATION OF THE SIX DEGREE OF FREEDOM EQUATIONS OF MOTION .......12 2.5 THE MODAL PROPERTIES OF THE SIX DEGREE OF FREEDOM MODEL .....................16 2.5.1 The Short Period Mode .................................................................................. 18 2.5.2 The Phugoid Mode ......................................................................................... 18 2.5.3 The Dutch Roll Mode ..................................................................................... 18 2.5.4 The Roll Mode ................................................................................................ 19 2.5.5 The Spiral Mode ............................................................................................. 19 2.6 SIMPLIFYING THE EQUATIONS OF MOTION TO FOUR DEGREES OF FREEDOM .........20 2.7 THE ADDITION OF WINDS ......................................................................................27 2.8 TRAJECTORY PROPAGATION OVER AN EARTH MODEL ..........................................31 2.8.1 Elliptic Earth Reference Frames ................................................................... 31 2.8.2 The Earth Model and its Kinematic Parameters ........................................... 35 2.8.3 Kinematics Relating the Coordinate Frames................................................. 39 2.8.4 Transforming DIS to Lat/Lon ........................................................................ 43 2.9 THE DERIVED STATE VARIABLES ..........................................................................45 2.10 THE AIRFRAME MODEL......................................................................................47 2.11 THE ENGINE MODEL ..........................................

FAQs

What is the purpose of the aircraft dynamics model in this report?

It provides an engineering analysis and design of an aircraft dynamics model specifically for the FAA Target Generation Facility.

How does the report structure the aircraft motion modeling?

It derives six degrees of freedom equations of motion, analyzes modal properties, then simplifies the model to four degrees of freedom and adds wind effects.

What numerical and system components are included for simulation?

The report includes airframe and engine models, a standard atmosphere model, numerical integration techniques, and the integration of roll dynamics.

Oct 24, 2026

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