AIRCRAFT MODELS - Storming Media

Linear Modeling of Tiltrotor Aircraft (In Helicopter and Airplane Modes) for Stability Analysis and Preliminary Design

JUN 96

222 pages

Authors: Gary D. Klein; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

The full text of this report is available for sale.

This thesis investigates the linear state space modeling of a tiltrotor aircraft by modifying an existing MATLAB routine which is used for preliminary (helicopter) stability and control analysis. The modifications consist of changing existing script files along with adding new ones. The modifications result in having a routine that allows the input of tiltrotor characteristics and subsequently generates a state space model along with other stability and control characteristics. The ...

Gain-Scheduled Aircraft Control Using Linear Parameter-Varying Feedback

JUN 96

218 pages

Authors: Martin R. Breton; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH

Systems which vary significantly over an operating envelope, such as fighter aircraft, generally cannot be controlled by a single linear time- invariant controller. As a result, gain-scheduling methods are employed to design control laws which can provide the desired performance. This thesis examines a relatively new approach to gain-scheduling, in which the varying controller is designed from the outset to guarantee robust performance, thereby avoiding the disadvantages of point designs. ...

Application of Multivariable Control Theory to Aircraft Control Laws. Final Report: Multivariable Control Design Guidelines

MAY 1996

286 pages

Authors: HONEYWELL INC MINNEAPOLIS MN

THE RESEARCH COVERED IN THIS REPORT IS A RESULT OF THE TASKS IN THE CONTROL APPLICATION OF MULTIVARIABLE CONTROL THEORY TO AIRCRAFT CONTROL LAWS. THE REPORT IS WRITTEN TO PROVIDE GUIDELINES TO HELP CONTROL LAW DESIGNERS USE MULTIVARIABLE CONTROL THEORY FOR AIRCRAFT CONTROLS. THE REPORT IS ORGANIZED INTO THREE PARTS. THE FIRST INCLUDES DISCUSSIONS ON VARIOUS CONTROL METHODOLOGIES AND PRESENTATION OF FUNDAMENTALS OF CONTROL. THE SECOND DISCUSSES THE DESIGN AND ...

RTPS Telemetry-Simulator Link at the Naval Air Warfare Center

17 APR 96

10 pages

Authors: William G. McNamara; Jay Nichols; Page Stanley; NAVAL AIR WARFARE CENTER AIRCRAFT DIV PATUXENT RIVER MD

Over the last 3 years the Naval Air Warfare Center Aircraft Division (NAWCAD), Patuxent River, MD, has been in the process of developing a link between its secure Manned Flight Simulator (MFS) and Real Time Processing System (RTPS) facilities. The MFS hosts a wide variety of high fidelity fixed and rotary wing aircraft simulation models. The RTPS is used as a telemetry ground station for conduct of Navy flight testing ...

The 'Hybrid' of Taiwan's Airspace -- Close Up on Taiwan's IDF Fighter

04 APR 96

20 pages

Authors: S. A. Daoming; NATIONAL AIR INTELLIGENCE CENTER WRIGHT-PATTERSON AFB OH

On the basis of introductions in the recent Taiwan press, the 8th flight squadron of the Taizhong Qingquangang KMT air force base held a delivery ceremony on 28 December 1994 for the first batch of 20 IDF fighters. Beginning New Year's Day 1995, they begin formal utilization to carry out combat readiness missions. As far as the Taiwan air force IDF, that is, in English--Indigenous Defense Fighter, as it is ...

An Investigation of Learning Curves and Their Use in Simulation

APR 1996

163 pages

Authors: Jennie H. Lommel; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH

In 1995, the C-17 Factory Simulation Model (FSM) was developed to enable analysts to address 'what-if' questions about the resources required to build future aircraft, and is based on learning curve models that are used to both portray and simulate future aircraft production. In this thesis, we examine and develop alternate learning curve models that also utilize a small amount of initial production data to portray the relationship between the ...

F-111C Longitudinal and Lateral Aerodynamic Flight Data Analysis for Take-off and Landing Configurations

APR 96

Authors: A. D. Snowden; J. S. Drobik; DEFENCE SCIENCE AND TECHNOLOGY ORGANIZATION CANBERRA (AUSTRALIA)

The full text of this report is not available and therefore is not for sale. This information is provided for reference purposes only.

A series of flight trials was performed on an F-111C aircraft, tail number A8-132, at the RAAF's Aircraft Research and Development Unit. Data obtained from the tests has been analysed in Air Operations Division to determine the aircraft aerodynamic and control derivatives. In this report the longitudinal and lateral derivatives for the take-off and landing configurations are presented and compared with wind tunnel results.

Evaluation of the Boeing Pan Air Technologies Code (A502i) Through Prediction of Separation Forces on the GBU-24

MAR 96

116 pages

Authors: Matthew A. LeTourneau; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

The Boeing PAN AIR Technologies code (A502i) is investigated to explore its suitability for determination of separation forces on ordnance. To this end, A502i is first assessed by applying it to three problems for which other solutions and experimental data are available, i.e. steady flow past a rectangular, parabolic arc wing and a delta wing at both subsonic and supersonic conditions. Good agreement is found in all cases. A502i is ...

Simulation Support of a 17.5 percent Scale F/A-18E/F Remotely Piloted Vehicle

27 FEB 96

2 pages

Authors: Timothy R. Fitzgerald; NAVAL AIR WARFARE CENTER AIRCRAFT DIV PATUXENT RIVER MD

As defense budgets continue to shrink, cost-effective methods for the accurate and timely acquisition of aerodynamic data must be developed. Traditionally, wind tunnels have fulfilled this role at both the conceptual and developmental stages, as well as, throughout the service life of an aircraft. However, although wind tunnels are a trusted and valuable data source that provide consistent, repeatable data upon which to construct aerodynamic models, they also have inherent ...

Enhanced Aircraft Design Capability for the Automated Structural Optimization System. Phase 1

31 JAN 96

119 pages

Authors: Timothy K. Hasselman; Xiaoguang Chen; David L. Herendeen; Douglas J. Neill; Mark S. Ewing; ACTA INC TORRANCE CA

This report documents the results of an STTR Phase 1 feasibility study to investigate potential enhancements to the 'Automated Structural Optimization System (ASTROS).' The scope of this feasibility study included (1) developing a robust design capability through probabilistic design optimization, (2) expanding the multidisciplinary optimization (MDO) capabilities of ASTROS, and (3) lining the three primary design stages, i.e., conceptual, preliminary, and detail design. A new method for reliability-based optimization was ...

Geophysics Technology Area Plan. FY96

JAN 96

39 pages

Authors: PHILLIPS LAB KIRTLAND AFB NM

The FY 96 Geophysics Technology Area Plan describes Phillips Laboratory's exploratory and advanced technology development in the field of geophysics. The document addresses user needs, goals, major accomplishments, and changes from last year for each geophysics thrust. Thrust 1 describes geophysics for space operations and communications. Thrust 2 covers geophysics for air and combat operations. Finally, thrust 3 addresses geophysics with corporate applications. (AN)

U.S. Navy T-45A Departure and Spin Evaluation (Videorecording).

06 DEC 1995

Authors: NAVAL AIR WARFARE CENTER AIRCRAFT DIV PATUXENT RIVER MD

Physical description: 1 VHS video; 1/2 in.; col.; sd.; mono; 5 mins.; standard playback sp.

Optimal Formation Flight Control

DEC 95

182 pages

Authors: Shawn B. McCamish; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Automatic formation flight involves controlling multiple wing aircraft equipped with standard Mach-hold, altitude-hold, and heading-hold autopilots in order to maintain a desired position relative to a lead aircraft throughout formation maneuvers. Changes in the lead aircraft's states, including formation heading, velocity, altitude, and geometry changes, are treated as disturbance and are rejected by the formation flight control system. The work in this thesis is a continuation of five previous theses, ...

A Comparison of Aircraft Icing Forecast Models

DEC 95

39 pages

Authors: Daniel Cornell; Christopher A. Donahue; Chan Keith; AIR FORCE COMBAT CLIMATOLOGY CENTER SCOTT AFB IL

This report documents the results of a study comparing forecasted aircraft icing conditions to pilot reports (PIREPs) of aircraft icing. Of the three operational forecast algorithms validated (AF Global Weather Central's RAOB routine, icing routines in the Navy's NODDS, and TESS software), RAOB had the overall best comparison to the PIREPs and 67 percent of the type forecasts and 42 percent of the intensity forecasts agreeing with the reported icing. ...

A Quantitative Feedback Theory FCS Design for the Subsonic Envelope of the Vista F-16 Including Configuration Variation and Aerodynamic Control Effector Failures

DEC 95

228 pages

Authors: Vicent J. Cacciatore; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Fault tolerant flight control systems for combat aircraft are an alternative to excessively redundant aircraft designs or reconfigurable control laws. However, due to the range of flight conditions within a combat aircraft's operational flight envelope, the variety of its configurations, and the unavailability of an aerodynamic data base for damaged aircraft, designing fault tolerant systems is a complicated endeavor. Quantitative Feedback Theory is a robust control design technique especially well ...

Optimal Solution Selection for Sensitivity-Based Finite Element Model Updating and Structural Damage Detection

DEC 95

215 pages

Authors: Jay A. Renken; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

The finite element model has become the standard way in which complex structural systems are modeled, analyzed, and the effects of loading simulated. A new method is developed for comparing the finite element simulation to experimental data, so the model can be validated, which is a critical step before a model can be used to simulate the system. An optimization process for finite element structural dynamic models utilizing sensitivity based ...

Report of Study on Airlines' Anticipated Near Future Cockpit Control and Display Capabilities and Plans for Data Link Communication. Part 2

OCT 95

41 pages

Authors: Albert J. Rehmann; S. L. Townsend; G. Yastrop; CTA INC MCKEE CITY NJ

This report reviews the findings of a study conducted by CTA incorporated for the Federal Aviation Administration

Full Envelope Control of Nonlinear Plants with Parameter Uncertainty by Fuzzy Controller Scheduling

SEP 95

210 pages

Authors: Thomas J. Kobylarz; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH

A full envelope controller synthesis technique is developed for multiple-input single-output (MISO) nonlinear systems with structured parameter uncertainty. The technique maximizes the controller's valid region of operation, while guaranteeing pre-specified transient performance. The resulting controller does not require on-line adaptation, estimation, prediction or model identification. Fuzzy Logic (FL) is used to smoothly schedule independently designed point controllers over the operational envelope and parameter space of the system's model. These point ...

A Comparison of Flight Input Techniques for Parameter Estimation of Highly-Augmented Aircraft

SEP 95

118 pages

Authors: Russell J. Gates; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Parameter estimation is an inverse process in which stability derivatives are determined from time history flight data by matching the aircraft mathematical model's computed response with the measured response of the aircraft. Accurate parameter estimation depends mainly on instrumentation and input technique. Input technique is the focus of this thesis in which both classical inputs and optimal inputs were applied under the same flight conditions to the High Angle of ...

Aircraft Drawing-Die Design CAD Expert System Based on Engineering Graph

21 AUG 95

14 pages

Authors: Xiangyang Fu; Guangdao Gao; Peng Yang; NATIONAL AIR INTELLIGENCE CENTER WRIGHT-PATTERSON AFB OH

The features of engineering CAD expert systems are discussed and an ADDES system Aircraft Drawing-Die Design CAD Expert System) is built. Based on the construction of the DIE coding system, such methods as the feature-based code system are used to establish a customer model. The agents in the system have the ability to solve partial problems, and the system is organized into distributed and hierarchical ...

Prediction and Control of Heat Treat Distortion of Helicopter Gears

AUG 95

194 pages

Authors: R. Stingfellow; LITTLE (ARTHUR D) INC CAMBRIDGE MA

A helicopter gear heat treatment distortion modelling approach was developed using a commercially available finite element program. The model. predicts distortion and residual stresses resulting from carburization, harden/ quench and temper processes performed on gears fabricated from 9310 steel. Accurate prediction of heat treatment distortion could aid in the design of gears, heat treatment processes and quench dies to reduce distortion. This would result in a significant reduction in scrap ...

Census U.S. Civil Aircraft, Calendar Year 1994

31 DEC 94

438 pages

Authors: FEDERAL AVIATION ADMINISTRATION WASHINGTON DC OFFICE OF AVIATION POLICY AND P LANS

This report presents information about the U.S. Civil Aircraft Fleet. It includes detailed tables of air carrier aircraft and an inventory of inventory of registered aircraft by manufacturer model, and general aviation aircraft by state and county of the owner.

Piloted Evaluation of an Integrated Methodology for Propulsion and Airframe Control Design

SEP 94

13 pages

Authors: Michelle M. Bright; Donald L. Simon; Sanjay Garg; Duane L. Mattern; Richard J. Ranaudo; NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH LEWIS RESEARCH CEN TER

An integrated methodology for propulsion and airframe control has been developed and evaluated for a Short Take-Off Vertical Landing (STOVL) aircraft using a fixed base flight simulator at NASA Lewis Research Center. For this evaluation the flight simulator is configured for transition flight using a STOVL aircraft model, a full nonlinear turbofan engine model, simulated cockpit and displays, and pilot effectors. The paper provides a brief description of the simulation ...

Design and Evaluation of a LQR Controller for the Bluebird Unmanned Air Vehicle

SEP 1994

86 pages

Authors: Brian T. Foley; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

The modern aerospace controls engineer is provided with a variety of powerful tools to aid in the design and testing of digital flight control systems. The current fiscal environment requires extensive validation of all aerospace based systems through simulation and hardware-in-the-loop testing prior to implementation. This work explores the design and evaluation of an Automatic Flight Control System (AFCS) for the Bluebird Unmanned Aerial Vehicle (UAV). Software tools such as ...

Comparison of Fixed Wing Aircraft Algorithms for JANUS

SEP 94

85 pages

Authors: Charles L. Daniels Ii; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

This research compares the fixed wing altitude algorithms utilized in the United States and the Australian versions of the combat modeling tool, JANUS(A). The Australian Army Battle Simulation Group has recently developed a new algorithm that more realistically models aircraft flight profiles within JANUS(A). A Low-High-Low strike profile was simulated, using both algorithms, against low level, littoral anti-aircraft weaponry. The simulated aircraft were flown in a weapons hold environment and ...

Virtual Prototyping as an Aid for Control System Analysis

SEP 94

49 pages

Authors: Arnold P. Selnick; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Virtual Prototyping provides an opportunity for control engineers to observe and evaluate their designs in a "real world" setting without the costs or risks associated with flight test. Designers Workbench is a computer aided design tool that allows a user to create, view, modify and animate three- dimensional databases. These may include instruments, avionics displays and any out-the-window applications such as runways or terrain. The dynamic behavior of specific elements ...

Pressure Measurements on an F/A-18 Twin Vertical Tail in Buffeting Flow. Volume 1. Wind Tunnel Test Summary

31 AUG 94

105 pages

Authors: Chris Pettit; Michael Banford; Dansen Brown; Ed Pendleton; WRIGHT LAB WRIGHT-PATTERSON AFB OH

Buffeting pressure measurements were made on the vertical tail surface of a full scale F/A-18 aircraft model in the National Full Scale Aerodynamics Complex at NASA Ames Research Center. Test variables included aircraft angle-of-attack, aircraft sideslip angle, and dynamic pressure. Accelerometers were used to obtain vertical tail accelerations. Pressure transducers were mounted on the starboard vertical tail. Steady and unsteady pressures were obtained. Unsteady pressure data were reduced to PSD ...

Pressure Measurements on an F/A-18 Twin Vertical Tail in Buffeting Flow. Volume 2: Steady and Unsteady RMS Pressure Data

01 AUG 94

383 pages

Authors: Chris Pettit; Dansen Brown; Michael Banford; Ed Pendleton; WRIGHT LAB WRIGHT-PATTERSON AFB OH

Buffeting pressure measurements were made on the vertical tail surface of a full scale F/A- 18 aircraft model in the National Full Scale Aerodynamics Complex at NASA Ames Research Center. Test variables included aircraft angle-of-attack, aircraft sideslip angle, and dynamic pressure. Accelerometers were used to obtain vertical tail accelerations. Pressure transducers were mounted on the starboard vertical tail. Steady and unsteady pressures were obtained. Unsteady pressure data were reduced to ...

Pressure Measurements on an F/A-18 Twin Vertical Tail in Buffeting Flow. Volume 3. Buffet Power Spectral Densities

AUG 94

705 pages

Authors: Chris Pettit; Dansen Brown; Michael Banford; Ed Pendleton; WRIGHT LAB WRIGHT-PATTERSON AFB OH

Pressure Measurements on An F/A-18 Twin Vertical Tail in Buffeting Flow. Volume 4. Buffet Cross Spectral Densities. Part 1

AUG 94

695 pages

Authors: Chris Pettit; Dansen Brown; Michael Banford; Ed Pendleton; WRIGHT LAB WRIGHT-PATTERSON AFB OH

Helicopter Performance Evaluation (HELPE) Computer Model

JUL 94

54 pages

Authors: Abdul R. Kiwan; ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD

A HELicopter Performance Evaluation (HELPE) computer model has been developed. The model is empirically based on the energy balance method. For a helicopter at a given mission, the model computes for a helicopter at given weight and flight conditions, the maximum possible level speed, its maneuverability in a turn, and its hover and climb capabilities in the in-ground and out-of-ground effects modes. The code also computes the speeds of maximum ...

Turbomachinery Design Using CFD (La Conception des Turbomachines par L'Aerodynamique Numerique)

MAY 94

Authors: ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT NEUILLY-SUR-SEINE (FRAN CE)

Computational Fluid Dynamics (CFD) has become a major design tool for designers of turbomachinery. The progress in this area is fast, and the use of 3-D methods is becoming increasingly applicable to the design process. This Lecture Series will improve the knowledge in the NATO nations on how to utilize the modern tools of CFD to increase the efficiency, reduce the fuel consumption, and increase the affordability of aircraft engines. ...

Course Module for AA201: Wing Structural Design Project

MAR 94

132 pages

Authors: Stephen A. Burris; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

This thesis defined a fundamental approach for aircraft wingbox design appropriate for an introductory course in aircraft structures based upon material strength and stiffness requirements. The process developed sought to encompass major conceptual engineering design considerations that ranged from load estimation at various points in the subsonic flight envelope, to initial structural sizing and layout. The goal was to present a process that could be readily conducted via hand calculations ...

Information Requirements in Support of Accreditation: Volume II: Of the Accreditation Requirements Study Report

FEB 1994

42 pages

Authors: COMPUTER SCIENCES CORP CAMARILLO CA

The goals of the Susceptibility Model Assessment and Range Test (SMART) Project are to develop an efficient process for the verification and validation (V&V) and configuration management (C/M) of aircraft susceptibility models and to facilitate their quick and cost effective accreditation by applying this new approach to five models frequently used in survivability analyses supporting acquisition decisions. The credibility assessment process thus defined generates various reports that provide a model ...

A Computer Program to Obtain Time-Correlated Gust Loads for Nonlinear Aircraft Using the Matched-Filter-Based Method

FEB 94

46 pages

Authors: Robert C. Scott; Anthony S. Pototzky; Boyd Perry III; NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CEN TER

NASA Langley Research Center has, for several years, conducted research in the area of time-correlated gust loads for linear and nonlinear aircraft. The results of this work led NASA to recommend that the Matched- Filter-Based One-Dimensional Search Method be used for gust load analyses of nonlinear aircraft. This manual describes this method, describes a FORTRAN code which performs this method, and presents example calculations for a sample nonlinear aircraft model. ...

Active Control of Instabilities in Jet Engines

31 pages

Authors: John C. Doyle; CALIFORNIA INST OF TECH PASADENA

Advances in several areas of robust control theory and its applications were made during the extension of this program. Our emphasis has been in the development of computable measures of performance robustness for both linear and nonlinear systems, and in the development of computationally sound identification algorithms. In the following paragraphs we briefly discuss the main areas of our program. A detailed description of the results obtained and the future ...

Evaluation of Moderate Angle of Attack Roll of a Dual Engine, Thrust Vectoring Aircraft Using Quantitative Feedback Theory

DEC 93

207 pages

Authors: Kevin E. Boyum; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

This thesis develops an innovative approach to the design of a flight control system for performing the large-amplitude velocity vector roll maneuver at high angles of attack (AOAs). A six degree of freedom aircraft model is developed from the fundamental nine-state equations of motion using a modified linearization technique. The MIMO (multiple-input multiple-output) Quantitative Feedback Theory (QFT) robust control design technique is then used to jointly address the system nonlinearities ...

Neural Networks for Dynamic Flight Control

DEC 93

140 pages

Authors: Ronald E. Setzer; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

This thesis examines the application of artificial neural networks (NNs) to the problem of dynamic flight control. The specific application is the control of a flying model helicopter. The control interface is provided through a hardware and software test bed called the Fast Adaptive Maneuvering Experiment (FAME). The NN design approach uses two NNs: one trained as an emulator of the plant and the other trained to control the emulator. ...

Flight Controller Design Using Mixed H2/H Infinity Optimization with a singular H Infinity Constraint

DEC 93

Authors: James P. Luke; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH

This thesis explores the effectiveness of mixed H2/H Infinity optimal control design applied to a realistic flight control problem. The application used by this thesis is a single input single output problem dealing with a normal acceleration command following model of the AFTI F-16. The mixed H2/H infinity control problem is broken into its component H2 and H Infinity parts; the H2 part is formulated as an LQG problem, and ...

Fault Detection and Isolation for the Bluebird Test Bed Aircraft

DEC 93

117 pages

Authors: Mario J. Levesque; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

A Fault Detection and isolation (FDI) algorithm design is presented using the Multiple Model algorithm technique for the Bluebird aircraft being developed at the Naval Postgraduate School. The requirement to maintain high performance in the dynamic system of the aircraft necessitates the use of FDI techniques to detect and isolate malfunctions in the sensors and actuators of the aircraft without using hardware redundancy. The solution presented makes use of analytical ...

Procedural Guide for Modelling and Analyzing the Flight Characteristics of a Helicopter Design Using Flightlab

23 SEP 93

150 pages

Authors: Gary P. McVaney; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

This thesis presents one method for modelling and analyzing a helicopter design using Flightlab. Flightlab is a computer program that provides for engineering design, analysis and simulation of aircraft using non-linear dynamic modeling techniques. The procedure to model a single main rotor helicopter is outlined using the sample helicopter design in the book 'Helicopter Performance, Stability, and Control' by Ray Prouty. The analysis procedure contains computer program scripts for determining ...

Application of Tiltrotor Technology to U.S. Coast Guard Missions

SEP 93

165 pages

Authors: J. Casler; T. Cooney; D. Hall; A. Roe; J. Whitacker; VEDA INC LEXINGTON PARK MD

The Congress of the United States has directed the U.S. Coast Guard to determine the potential offered by tiltrotor aircraft technology, more specifically the V-22, for three Coast Guard functions; Search and Rescue (SAR), Law Enforcement/Maritime Interdiction (LE/MI), and Marine Environmental Protection (MEP). This study examines potential employment scenarios of the V- 22 in the identified mission components, measures the operational effectiveness of the V-22, and determines the manpower and ...

A Non-Linear Simulation for an Autonomous Unmanned Air Vehicle

SEP 93

123 pages

Authors: David R. Kuechenmeister; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Unmanned Air Vehicles have become increasingly important on the modern battlefield. The restrictive requirement for runways and special equipment to take off and land was partially solved by the vertical take off and landing Airborne Remotely Operated Device, AROD. Work done at the Naval Postgraduate School has modified the AROD to not only land and launch vertically, but to fly horizontally for the majority of the mission. To realize these ...

A Cost Model for USAF Acquisition of Commercial Aircraft for Service in the Special Air Mission Fleet

04 JUN 93

102 pages

Authors: C. G. McVicker III; Michael T. Roche; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH

The purpose of this research was to develop a cost estimating model which would allow cost estimators the ability to quickly and accurately estimate the acquisition of Air Force Special Air Mission fleet aircraft. The literature review revealed studies, government contracts, and trade publications which served as source data. This information was supplemented by interviews with acquisition specialists and contractors and incorporated into a database. Several estimating techniques were created ...

Development of an Air-to-Air Refueling Automatic Flight Control System Using Quantitative Feedback Theory

JUN 93

127 pages

Authors: Dennis W. Trosen; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Quantitative Feedback Theory and the improved method Quantitative Feedback Theory are enhanced to include the rejection of disturbance at the system output. The enhanced Quantitative Feedback Theory and improved method Quantitative Feedback Theory processes are applied to the design of an automatic flight control system to regulate position of the C-135B fuel receiving aircraft relative to the tanker during air-to-air refueling. A simple feedback control system is developed that will ...

Solution of Euler Equations for Forebody-Inlet Ensemble of Aircraft at High Angle of Attack

27 APR 93

Authors: Zheng Xiaoqing; Shen Huili; FOREIGN AEROSPACE SCIENCE AND TECHNOLOGY CENTER WRIGHT- PATTERSON AFB OH

A computational procedure was developed to simulate inviscid flows over integrated forebody-inlet ensemble of an aircraft model. The analysis, which includes the effect of Mach number, angle of attack and engine mass flow, is based on the solution of three-dimensional Euler equations. A finite-volume spatial discretization and a Runge-Kutta time stepping scheme are employed in solving the equations. To achieve the required geometric flexibility, a multizone mesh is used. The ...

ADST Operation Manual for the Management Command and Control. Volume 1. AIRNET/MIPS Host MCC

31 MAR 93

70 pages

Authors: Dinh Nguyen; Lynn Thompson; Rick Bright; Gerry Mitchell; Mary Kruck; LORAL SYSTEMS CO ORLANDO FL ADST PROGRAM OFFICE

This manual describes the MIPS Management Command and Control (MCC) system operational procedures to be used for initializing the AIRNET Battle Simulation and for conducting battle exercises at the AIRNET facility (Ft. Rucker)

Estimating Test Range Capacity

05 MAR 93

160 pages

Authors: Paul A. McDaniel; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH

The main focus of this thesis effort was to develop a means to estimate the capacity of the test range complex at Eglin AFB, Florida. For the purposes of this study, test range capacity was defined as the maximum number of missions, of a given set, that could possibly be supported by range resources on any given day. In trying to determine this number, the complexities of the overall multi-resource ...

ModSAF Software Architecture Design and Overview Document

20 JAN 93

111 pages

Authors: Andy Ceranowicz; Carol Ladd; Joshua Smith; Robert Vrablik; LORAL SYSTEMS CO ORLANDO FL ADST PROGRAM OFFICE

This document provides information regarding architectural features of the ModSAF application. Various sections discuss the basic concepts of ModSAF, the physical and behavioral models, architectural support, functional components, design methodology, and the procedures for extending ModSAF with new objects or behaviors. The last chapter steps the reader through the process of defining, building, and executing new capabilities in ModSAF. Modular Semi- Automated Forces, DIS, ADST, BDS-D.

Piloted Evaluation of an Integrated Propulsion and Flight Control Simulator

AUG 92

13 pages

Authors: Michelle M. Bright; Donald L. Simon; NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH LEWIS RESEARCH CEN TER

This paper describes a piloted evaluation of the integrated flight and propulsion control simulator at NASA Lewis Research Center. The purpose of this evaluation is to demonstrate the suitability and effectiveness of this fixed base simulator for advanced integrated propulsion and airframe control design. The evaluation will cover control effector gains and deadbands, control effectiveness and control authority, and heads up display functionality. For this evaluation the flight simulator is ...