Now showing items 1-20 of 108

    • Analysis of Human-System Interaction For Landing Point Redesignation 

      Chua, Zarrin K. (Georgia Institute of Technology, 2009-05-26)
      Despite two decades of manned spaceflight development, the recent thrust for increased human exploration places significant demands on current technology. More information is needed in understanding how human control affects ...
    • Application of a New Economic Analysis Tool to a Two-Stage-to-Orbit RBCC Launch Vehicle Design 

      Olds, John R.; Lee, Hosung (Georgia Institute of Technology, 1996-09)
      As aerospace industries are forced to compete in an environment of declining federal budgets and increased competition, 'design for performance' is quickly giving way to 'design for cost.' Many modern launch vehicle ...
    • An Approach for Calculating the Cost of Launch Vehicle Reliability 

      Krevor, Zachary C.; Wilhite, Alan W. (Georgia Institute of Technology, 2007-09)
      The goal of this paper is to determine the cost of increasing launch vehicle reliability during conceptual design. The launch vehicle mission requirements are held constant while various reliability strategies are evaluated ...
    • An Approximate Ablative Thermal Protection System Sizing Tool for Entry System Design 

      Dec, John A.; Braun, Robert D. (Georgia Institute of Technology, 2006-01)
      A computer tool to perform entry vehicle ablative thermal protection systems sizing has been developed. Two options for calculating the thermal response are incorporated into the tool. One, an industry-standard, high-fidelity ...
    • Approximation of Probabilistic Distributions Using Selected Discrete Simulations 

      McCormick, David Jeremy; Olds, John R. (Georgia Institute of Technology, 2000-09)
      The goal of this research is to find a computationally efficient and easy to use alternative to current approximation of direct Monte Carlo methods for robust design. More specifically, a new technique is sought to use ...
    • Architecture Options for Propellant Re-supply of Lunar Exploration Elements 

      Young, James J.; Thompson, Robert W.; Wilhite, Alan W. (Georgia Institute of Technology, 2006-09)
    • Argus, a Highly Reusable SSTO Rocket-Based Combined Cycle Launch Vehicle with Maglifter Launch Assist 

      Olds, John R.; Bellini, Peter X. (Georgia Institute of Technology, 1998-04)
      This paper summarized the results of a conceptual design study that was performed in support of NASA's recent Highly Reusable Space Transportation study. The Argus concept uses a Maglifter magnetic-levitation sled launch ...
    • Artemis: A Reusable Excursion Vehicle Concept for Lunar Exploration 

      Young, David Anthony; Olds, John R.; Hutchinson, Virgil L., Jr.; Krevor, Zachary C.; Young, James J. (Georgia Institute of Technology, 2005-07)
      Artemis is a reusable excursion vehicle for lunar landing missions. It is intended to transport a notional CEV vehicle from low lunar orbit (LLO) to the lunar surface. It can be reused by refueling the vehicle in LLO. ...
    • ASPEN Revisited: The Challenge of Nuclear Propulsion for ETO 

      Weglian, John E.; Olds, John R.; Marcus, Leland R.; McIntire, James; Nelson, Douglas K.; Blevins, John (Georgia Institute of Technology, 2001-07)
      ASPEN was a study conducted by Los Alamos National Labs in the early 1960s to examine the benefits of using a Nuclear Thermal Rocket (NTR) for Earth-to-Orbit (ETO) single-stage launch vehicle applications. Using the analysis ...
    • Aztec: A TSTO Hypersonic Vehicle Concept Utilizing TBCC and HEDM Propulsion Technologies 

      Kokan, Timothy Salim; Hutchinson, Virgil L., Jr.; Reeves, John Daniel; Olds, John R. (Georgia Institute of Technology, 2004-07)
      The Aztec reusable launch vehicle (RLV) concept is a two-stage-to-orbit (TSTO) horizontal takeoff, horizontal landing (HTHL) vehicle. The first stage is powered by ten JP- 5 fueled turbine-based combined-cycle (TBCC) ...
    • Cadmus: A Europa Lander Mission Concept 

      Thompson, Robert W.; Francis, Scott R.; Olsen, Randy; Coffman, Robbie; Braun, Robert D.; Parsons, Michael (Georgia Institute of Technology, 2005-03)
      The Cadmus mission responds to the need for a Europa surface exploration mission in the 2021 time frame that complements and extends the science performed by the Jupiter Icy Moons Orbiter (JIMO) and Galileo spacecraft. ...
    • Centurion: A Heavy-Lift Launch Vehicle Family for Cis-Lunar Exploration 

      Young, David Anthony; Olds, John R.; Hutchinson, Virgil L., Jr.; Krevor, Zachary C.; Pimentel, Janssen; Reeves, John Daniel; Sakai, Tadashi; Young, James J. (Georgia Institute of Technology, 2004-07)
      Centurion is an expendable heavy lift launch vehicle (HLLV) family for launching lunar exploration missions. Each vehicle in the family is built around a common two-stage core. The first stage of the core uses kerosene ...
    • Challenges of Mars Entry, Descent and Landing 

      Braun, Robert D.; Manning, Robert M. (Georgia Institute of Technology, 2006-03)
      The United States has successfully landed five robotic systems on the surface of Mars. These systems all had landed mass below 0.6 metric tons (t), had landed footprints on the order of hundreds of km and landed at ...
    • Characterizing High-Energy-Density Propellants for Space Propulsion Apllications 

      Kokan, Timothy Salim; Olds, John R. (Georgia Institute of Technology, 2006-10)
      A technique for determining the thermophysical properties of high-energy-density matter (HEDM) propellants is presented. HEDM compounds are of interest in the liquid rocket engine industry due to their high density and ...
    • Chimera: A Low Cost Solution to Small Satellite Space Access 

      Crowley, John; Hutchinson, Virgil L., Jr.; Keisner, Alex; Young, David Anthony; Curry, Mike; Jackson, Jonathan; Maatsch, John; Piletsky, Pavel; Olds, John R. (Georgia Institute of Technology, 2003-08)
      The Chimera rocket was designed to enter the small satellite market by offering an affordable and flexible alternative to the Pegasus launch vehicle. A number of design concepts were evaluated, and one was selected to ...
    • A Collaborative Optimization Approach to Design and Deployment of a Space Based Infrared System Constellation 

      Budianto, Irene Arianti; Olds, John R. (Georgia Institute of Technology, 2000-03)
      Collaborative optimization, as a design architecture, has been used successfully in solving large-scale multidisciplinary optimization problems related to aircraft and space vehicle designs. The study presented in this ...
    • Comparison of Collaborative Optimization to Conventional Design Techniques for a Conceptual RLV 

      Cormier, Timothy A.; Scott, Andrew; Ledsinger, Laura Anne; McCormick, David Jeremy; Way, David Wesley; Olds, John R. (Georgia Institute of Technology, 2000-09)
      Initial results are reported from an ongoing investigation into optimization techniques applicable to multidisciplinary reusable launch vehicle (RLV) design. The test problem chosen for investigation is neither particularly ...
    • A Comparison of Modern and Historic Mass Estimating Relationships on a Two-Stage to Orbit Launch Vehicle 

      Rohrschneider, Reuben R.; Olds, John R. (Georgia Institute of Technology, 2001-08)
      Traditionally mass estimation for conceptual design of advanced launch vehicles has depended on historically based mass estimating relationships (MERs). This paper compares the modern MERs used in the Space Systems Design ...
    • Component-Level Weight Analysis for RBCC Engines 

      Olds, John R.; McCormick, David Jeremy (Georgia Institute of Technology, 1997-09)
      Rocket-based combined-cycle engines (RBCC) engines have recently received increased attention for use on advanced, reusable space launch vehicles. By combining convention rocket and airbreathing operating modes into an ...
    • Computational Fluid Dynamics Validation of a Single, Central Nozzle Supersonic Retropropulsion Configuration 

      Cordell, Christopher E., Jr.; Braun, Robert D. (Georgia Institute of Technology, 2009-05)
      Supersonic retropropulsion provides an option that can potentially enhance drag characteristics of high mass entry, descent, and landing systems. Preliminary flow field and vehicle aerodynamic characteristics have been ...