Person:

Mavris, Dimitri N.

Permanent Link

https://hdl.handle.net/1853/71501

Associated Organization(s)

Organizational Unit

Daniel Guggenheim School of Aerospace Engineering

Organizational Unit

Aerospace Systems Design Laboratory (ASDL)

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Publication Search Results

Now showing 1 - 10 of 73

Use of a Conceptual Sizing Tool for Conceptual Design of Tactical Missiles (U)

(Georgia Institute of Technology, 2002-11) Frits, Andrew P. ; Fleeman, Eugene L. ; Mavris, Dimitri N.

This paper illustrates the use of a conceptual sizing tool for the design of tactical missiles. The sizing tool, called the Tactical Missile Design (TMD) spreadsheet, was developed to allow the user to quickly generate estimates of a missile configuration?s performance and other measures of merit such as lethality. This capability allows the user to get a first order estimate of a missile?s ability to meet a set of requirements and allows for fast trade-studies to quickly identify the performance drivers of a system. In order to generate reasonable estimates for missile range and speed, a sizing tool must have analysis methods for aerodynamics, propulsion, weight, and trajectory. In order for the sizing tool to remain useful for conceptual tradeoffs, these analyses must be robust enough to handle a wide range of inputs, yet simple enough to be executed quickly. The analysis methods were constructed with these requirements in mind. The aerodynamics analysis is based upon several physics-derived analytical expressions as outlined in the text ?Tactical Missile Design? by Eugene Fleeman. Propulsion uses a simplified cycle analysis to relate engine parameters (maximum inlet temperature, fuel heating value, expansion ratio) to overall specific impulse (Isp). The propulsion analysis can handle either air-breathing and solid-rocket systems, or a combination thereof. For trajectory, a constant flight path is assumed, with a boost, cruise, and coast phase. These straightforward analysis methods combine to produce a very powerful, yet robust, conceptual missile design tool. The paper first lays out the analysis methods, assumptions, and limitations in the Tactical Missile Design spreadsheet. Next, a comparison is made between the results of the TMD spreadsheet and the performance of historical missile systems. In addition, the paper explores some example trade studies to identify the drivers of a rocket and a ramjet missile system. Finally, the TMD spreadsheet is used to show how easily a tactical missile can be optimized at the conceptual level.
A Probabilistic Approach to the Conceptual Design of a Ship-Launched High Speed Standoff Missile

(Georgia Institute of Technology, 2002-11) Ender, Tommer Rafael ; McClure, Erin Kathleen ; Mavris, Dimitri N.

This paper focuses on the application of advanced design methodologies developed by Georgia Tech's Aerospace Systems Design Laboratory (ASDL) to the conceptual design of a hypersonic air-breathing ship-to-surface cruise missile. This approach uses an integrated, parametric environment, that brings more physics based knowledge into early phases of design, thus allowing the designer to have a thorough understanding of the entire design space. Response Surface Methodology (RSM) and probabilistic methods allow the designer to then generate a field of designs, instead of just one point design. A High Speed Standoff Missile (HSSM) was required to deliver a 250-lb warhead to time critical targets with a stationary dwell time between five and fifteen minutes, at a range of up to 1,500 km. The primary drivers for a successful design were shown to be minimum time to target, affordability, and compatibility with the Vertical Launch System (VLS) currently used on many of the United States Navy's cruisers and destroyers. Included is an explanation of the physics based tools used to perform the various disciplinary analyses, and their use to construct metamodels allowing for design space exploration and robust design simulation, as well as a quantification of the uncertainty in the design parameters.
Formulation of an Integrating Framework for Conceptual Object-Oriented Systems Design

(Georgia Institute of Technology, 2002-11) De Baets, Peter Wilfried Gaston ; Zentner, John Marc ; Mavris, Dimitri N.

In this paper, an overview is given of the different alternatives to an integrating computational framework. A new framework will be introduced, which incorporates the latest computational techniques and more importantly a mind-set emphasizing flexibility, modularity, portability and re-usability. Distributed object computing extends an object oriented system which allows objects to interact across heterogenous networks and interoperate as a unified whole. Integrated computing frameworks are discussed, together with data transport techniques such as Extensible Markup Language (XML) and Simple Object Access Protocol (SOAP) to achieve platform, code and meta-model independent integration. In addition, the paper will illustrate through an air vehicle example that using open-source tools are a valid alternative to commercial packages. Added advantages are the access to source code which is extremely useful in a conceptual systems-of-systems research environment.
Quiet Supersonic Jet Engine Performance Tradeoff Analysis Using a Response Surface Methodology Approach

(Georgia Institute of Technology, 2002-11) Briceño, Simón Ignacio ; Mavris, Dimitri N.

Recent market studies indicate a renewed interest for a quiet Supersonic Business Jet (SBJ). The success of such a program will be strongly dependent upon the achievement of stringent engine noise, emissions and fuel consumption goals. This paper demonstrates the use of advanced design methods to develop a parametric design space exploration environment which will be ultimately used for the identification of an engine concept capable of satisfying acoustic levels imposed by FAR part 36 (stage IV) and NOx and CO2 standards as stated in the 1996 ICAO. The engine performance is modeled through the use of Response Surface and Design of Experiments Techniques, enabling the designer/decision-maker to change initial engine parameter values to detect the effects of the responses in a time efficient manner. Engine performance and engine weight results are obtained through physics-based engine analysis codes developed by NASA. An SBJ airframe baseline model is used in conjunction with the engine performance data and executed through a synthesis and sizing code to simulate a supersonic mission. This paper focuses on the tradeoffs associated with noise, emissions and specific fuel consumption of the supersonic engine by employing design parameters such as overall pressure ratio, fan pressure ratio, turbine inlet temperature and throttle ratio. Finally, an optimal engine combination is created to satisfy all the constraints imposed by the aforementioned regulations for a particular mission configuration. Using a statistical analysis package, the designer has the ability to analyze tradeoffs that allows adjustments to be made to certain parameters that, although may compromise others, will still allow the system to fall within engine regulatory limits.
A Quality Engineering Approach to the Determination of the Space Launch Capability of the Peacekeeper ICBM Utilizing Probabilistic Methods

(Georgia Institute of Technology, 2002-11) Kumpel, Amy E. ; Barros, Peter. A., Jr. ; Mavris, Dimitri N.

This paper outlines the use of a comprehensive and robust methodology for the conceptual design of an expendable launch vehicle employing the existing Peacekeeper ICBM. This methodology includes an Integrated Product and Process Development (IPPD) approach, coupled with response surface techniques and probabilistic assessments. IPPD aids the decision-maker in accurately projecting performance and economic metric values. It also provides a probabilistic framework to address the inherent uncertainty in vehicle requirements in an analytical manner by representing payload, mission, and design requirements as distributions instead of point values. In short, the methodology utilized in this study is a combination of traditional missile and rocket design and quality engineering techniques. The main goal of this method is to design for the most affordable system possible while ensuring technical feasibility and economic viability. This paper shows how these methods were applied to a proof of concept investigation of the space launch vehicle (SLV) capability of the Peacekeeper ICBM.
Personal air vehicle exploration tool and modeling

(Georgia Institute of Technology, 2002-10-31) Mavris, Dimitri N.
Probabilistic Modeling of Technology Development for use in Project Planning and Management

(Georgia Institute of Technology, 2002-10) Largent, Matthew Clinton ; Mavris, Dimitri N.

From the dawn of human flight, the use of new technology has been necessary for aircraft to fly faster, further, and higher. That need continues today, making technology development a critical factor in new aerospace systems development. This study introduces some of the detailed formulation behind a process developed to assist the planning and management of a development project for a new technology. The process is based on risk management and uses probabilistic analysis, project network techniques, and Bayesian statistics in order to provide information useful for decision making. The six steps in the process focus on identification and reduction of performance uncertainty, as well as identification of cost and schedule risk and uncertainty. The process introduces some ways in which analysis can interact with expert opinion in order to produce meaningful system-level comparisons of technologies. The iterative nature of the process helps to deal with uncertainty in the technology and outside influences which affect the technology?s development.
Using Response Surface Metamodels to Optimize the Aerodynamic Performance of a High Speed Standoff Missile within a Multi-Disciplinary Environment

(Georgia Institute of Technology, 2002-10) Won, Henry W. ; Levine, Simon B. ; Mavris, Dimitri N. ; Pfaender, Holger

This report summarizes the feasibility of implementing a metamodel, consisting of Response Surface Equations (RSE), in a High Speed Standoff Missile (HSSM) multi-disciplinary mission analysis. The metamodel, which is a representation of a physics based engineering tool, is used to optimize the missile aerodynamic performance for any given mission. Each mission is defined as a function of the mission parameters. The optimization schemes use flight condition information and missile requirements from the upstream mission analysis, and find the optimum missile geometry parameters for that mission. The geometry parameters are then returned to the system analysis to complete the mission evaluation under optimal aerodynamic performance. The optimization scheme allows the variation of the missile geometry without increasing the number of runs in a parametric design study, such as a Design of Experiments (DOE). Results are achieved for two modules, namely the fuselage aerodynamics and the tail fin aerodynamics. Metamodel optimization schemes were created and implemented into the modules. The transformed modules were tested to observe the behavior and accuracy of the schemes. Comparison is made between the optimal geometries found with and without the use of the metamodel. The comparison shows that the metamodel optimization returns similar results, and does so in a significantly shorter amount of time. In addition, the aerodynamic design spaces are analyzed in conjunction with the optimization behavior to predict possible problems in the optimization process. The use of the metamodel is shown to alleviate optimization problems such as multi-modal design spaces. The results indicate the usefulness and promise for the proposed metamodel optimization scheme for use in a large scale preliminary design analysis.
A Parametric Exploration of Supersonic Business Jet Concepts Utilizing Response Surfaces

(Georgia Institute of Technology, 2002-10) Mavris, Dimitri N. ; Briceño, Simón Ignacio ; Buonanno, Michael Alexander ; Fernandez, Ismael

Market forecasts predict a potentially large market for a quiet supersonic business jet provided that several technical hurdles are overcome prior to fielding such a vehicle. In order to be acceptable, the QSJ must be able to fly at supersonic speeds over land and operate from regional airports while meeting government noise and emissions requirements. Physics based analysis tools are used in conjunction with a Response Surface metamodeling approach to create an environment in which the performance, economics, and environmental impact of the aircraft can be studied as a function of design and mission parameters. Through the use of this environment, the designer is able to rapidly explore the entire concept space by dynamically modifying the configuration, engine cycle, and requirements. Results obtained using this exploration tool indicate that it may be possible to meet emissions and noise requirements, but that technology infusion will be required in order to meet all performance and economic goals. Finally, this same physics-based environment was used to assess the impact of a portfolio of technologies on the system?s acceptability.
Determination Of Revolutionary Requirements Boundaries For A High-Speed, Airbreathing Propulsion System

(Georgia Institute of Technology, 2002-10) Hollingsworth, Peter Michael ; Mavris, Dimitri N.

Modern propulsion system design and selection for future air-vehicle systems is an inherently uncertain process. The long lead-times in the development of new propulsion systems produce significant levels amount of risk for the propulsion system manufacturer. Additionally, this long lead-time allows a tremendous amount of program inertia to build up as the development process progresses. This inertia prohibits the propulsion system manufacturer from reacting to "catastrophic" changes in the system requirements. It can be shown that there exist certain regions in the system requirements hyper-space where a small change in a given requirement or requirements requires a completely different solution. Additionally, because of the inherent security associated with evolving current designs; there exists in the engineering community a reluctance to develop truly new and revolutionary technologies and systems. Therefore it is of interest to develop a method by which the location of catastrophic boundaries can be discerned. The method chosen to investigate the requirements hyper-space for supersonic cruise propulsion systems is a genetic algorithm (GA). The GA was used to determine both individual and combined technology limit boundaries and to determine the effect of technology infusion on these boundaries.