This minor thesis examines whether or not the Australian Defence Force (ADF) needs an indigenous aircraft structural testing program for military aircraft. Aircraft structural testing is a major test and evaluation activity currently undertaken by the DSTO to provide structural integrity information about particular aircraft for the ADF. The ADF has required this testing to be undertaken because, in general terms, testing undertaken by an aircraft's manufacturer has not been sufficient to meet the needs of the ADF. The research was divided into five sub-problems, which examined the need for aircraft structural testing, the management of these needs, what structural testing is required, how the testing should be managed and how the testing should be conducted. The research was undertaken by conducting five case studies into past, current and future aircraft structural tests being undertaken by the DSTO. The cases examined were the F/A-18 International Follow-On Structural Test Project, the P-3 service life assessment program, the F-111 wing test, the Hawk lead-in fighter full-scale fatigue test and the potential test program for the joint strike fighter (JSF). The basis of the case studies was the conduct of a series of interviews of the DSTO staff relevant to each case being examined. The information gathered through the interviews was supported by material gathered through making observations and reviewing documentation relevant to each case. The research concluded that an indigenous aircraft testing program is required by the ADF in order to maintain the structural integrity of its aircraft fleet. This minor thesis makes some recommendations for the way aircraft structural testing is conducted by the ADF, and the way general management of T & E in the Department of Defence could be improved. / Thesis (MEng(TestandEvaluation))--University of South Australia, 2004

Thesis (MEng(TestandEvaluation))--University of South Australia, 2003.

This minor thesis examines whether or not the Australian Defence Force (ADF) needs an indigenous aircraft structural testing program for military aircraft. Aircraft structural testing is a major test and evaluation activity currently undertaken by the DSTO to provide structural integrity information about particular aircraft for the ADF. The ADF has required this testing to be undertaken because, in general terms, testing undertaken by an aircraft's manufacturer has not been sufficient to meet the needs of the ADF. The research was divided into five sub-problems, which examined the need for aircraft structural testing, the management of these needs, what structural testing is required, how the testing should be managed and how the testing should be conducted. The research was undertaken by conducting five case studies into past, current and future aircraft structural tests being undertaken by the DSTO. The cases examined were the F/A-18 International Follow-On Structural Test Project, the P-3 service life assessment program, the F-111 wing test, the Hawk lead-in fighter full-scale fatigue test and the potential test program for the joint strike fighter (JSF). The basis of the case studies was the conduct of a series of interviews of the DSTO staff relevant to each case being examined. The information gathered through the interviews was supported by material gathered through making observations and reviewing documentation relevant to each case. The research concluded that an indigenous aircraft testing program is required by the ADF in order to maintain the structural integrity of its aircraft fleet. This minor thesis makes some recommendations for the way aircraft structural testing is conducted by the ADF, and the way general management of T & E in the Department of Defence could be improved. / Thesis (MEng(TestandEvaluation))--University of South Australia, 2004

MBA professional report (Master of Business Administration) Naval Postgraduate School, December 2007. / Title from reproduction cover. "December 2007." Advisor(s): Petross, Diana ; Snider, Keith. Performed by Naval Postgraduate School, Monterey, CA. "Submitted in partial fulfillment of the requirements for the degree of Master of Business Administration from the Naval Postgraduate School, December 2007."--P. iii. Includes bibliographical references (p. 91-95). Also available online from the Naval Postgraduate School (NPS), Dudley Knox Library site and the DTIC Online site.

Thesis (M.S.)--School of Advanced Air and Space Studies, 2008. / "June 2008." Vita. Includes bibliographical references (p. 91-96). Also available via the Internet.

Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, June 1990. / Thesis Advisor(s): Howard, Richard M. Second Reader: Lindsey, Gerald H. "June 1990." Description based on signature page as viewed on October 21, 2009. DTIC Identifier(s): Composite materials, ducted fan, airframes, vertical takeoff aircraft, remotely piloted vehicles. Author(s) subject terms: UAV, composites, AROD, TDF, RPV, ducted fan, vertical takeoff. Includes bibliographical references (p. 74-75). Also available online.

The purpose of this research is to apply engineering-based knowledge to the field of combat aircraft survivability, and to create scenario-specific models in order to estimate the tradeoff between aircraft survivability and lethality metrics at the encounter and sortie levels. The development of scenario-specific models serves to identify and quantify technological changes that have Ieverage on the overall performance of the aircraft from a survivability point of view. Also, the models focus on the fighter aircraft susceptibility assessment and are capable of incorporating outputs from offline studies as inputs, such as in the area of vulnerability assessment where extensive databases are available. The mission scenario models are microscopic in nature and relate important conceptual aircraft design parameters such as thrust-to-mass ratio, wing loading, empty mass, maneuverability, etc. and operational parameters (e.g., weapon payload, range, loiter time, flight profiles, etc.) to the aircraft sortie survivability and lethality under various threat scenarios. This research proposes a methodology to estimate survivability and lethality aircraft performance at the sortie level where aircraft parameters can be implemented into scenario-specific models to assess their impact upon survivability-related metrics. While the project was conceived with naval aircraft in mind, the methodology, to the extent possible, is not to be aircraft-specific and thus could be applied to any particular design at the conceptual stage. / Ph. D.

The problem of time-optimal fuselage-reorientation maneuvering of a combat aircraft, with and without thrust-vectoring capability, was analyzed. An accurate mathematical model for the reorientation maneuvers of interest was developed, to ensure practical value of the analysis. In particular, an effective method for smooth fitting of the aerodynamic data was devised. The Minimum Principle from optimal control theory was applied and the optimal control problems of interest cast into a form of numerical multipoint boundary-value problems. These are extremely difficult to solve. To alleviate their treatment, a hybrid approach was adopted. Homotopy ideas were combined with comprehensive analyses of the structure of the dynamical equations and engineering insight into the mechanics of the reorientation motions. The approach successfully yielded a number of extremal solutions for a few typical reorientation maneuvers. The nature and essential characteristics of the extremal motions were understood, as well as their domains of existence. A few parametric studies showed how aircraft design parameters should be tailored to allow for improved maneuverability. / Ph. D.

The primary purpose of this study is to develop a nonlinear feedback control law for the F / A-I8 fighter aircraft that performs a fast half-loop maneuver. This feedback law is developed using a singular perturbation approach. A secondary purpose of this study is to establish a baseline for time optimal half-loop maneuvers. The singular perturbation approach makes it possible to develop a state feedback control law which rotates the velocity vector through one hundred and eighty degrees at a maximum equilibrium pitch rate with a nearly constant angle of attack. The response of the aircraft to the control law is compared to simulations of half-loop maneuvers generated at NASA Langley Research Center. / Master of Science

System dynamics is based on principles borrowed from engineering—especially feedback concepts. It makes possible a representation of decision policies and information flow. The systems approach is a mixture of scientific approaches to conceptualizing problems and solving them through research, design and analysis. In system dynamics, differential equations are represented in the form of difference equations. There is no limit to the number that can be employed to represent the complex details of any system. The models developed here help in determining the superiority or inferiority of the Advanced Tactical Aircraft (ATA) over the baseline aircraft. The advanced tactical aircraft is a proposed replacement aircraft that can undertake any of the three missions—air superiority, fleet defense and attack/interdiction. The baseline aircraft for air superiority and fleet defense is the Tomcat Fighter, F-14 and for attack/interdiction it is Intruder, A-6. Several measures of effectiveness are presented to evaluate the superiority or inferiority of the replacement aircraft over the baseline aircraft. / Master of Science / incomplete_metadata