Now showing items 1-20 of 144

    • AdVISE - Advanced Vehicle Integration and Synthesis Environment (AdVISE) 

      Ferlemann, Shelly; Rehder, J. Joseph (Georgia Institute of Technology, 2005-11-09)
      Describes a collaborative design and analysis environment for the aerospace community including industry and academia in order to: develop and maintain a knowledge base as an agency resource ; assist in decisions concerning ...
    • Aerobraking Cost/Risk Decisions 

      Spencer, David A.; Tolson, Robert (Georgia Institute of Technology, 2005-11-10)
      Three missions have successfully used aerobraking to reduce the spacecraft orbit period and achieve the desired orbit geometry. A fourth, Mars Reconnaissance Orbiter, will employ aerobraking following its orbit insertion ...
    • 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 ...
    • Analysis of JPL Mission Cost Estimate Drivers 

      Sebastian, Tommy (Georgia Institute of Technology, 2005-11-10)
      An analysis of JPL cost estimate drivers. To give a better idea of true costs, all values were converted to fiscal year 2005 ; the NASA New Start Inflation Index (2005) was used. The context was generated primarily from ...
    • The Apollo Lunar Orbit Rendezvous Architecture Decision Revisited 

      Reeves, David M.; Scher, Michael D.; Wilhite, Alan W.; Stanley, Douglas O. (Georgia Institute of Technology, 2005-11-09)
      The 1962 Apollo architecture mode decision process was revisited with modern analysis and systems engineer tools to determine driving selection criteria and technology/operational mode design decisions that may be used ...
    • 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 ...
    • An Auction Algorithm for Optimal Satellite Refueling 

      Salazar, Alexandros; Tsiotras, Panagiotis (Georgia Institute of Technology, 2005-11-10)
      Satellite refueling can extend the lifetime of satellite constellations. Peer-to-peer satellite refueling in particular has the potential to make the most efficient use of the fuel contained in the constellation by ...
    • Automated Hypersonic Launch Vehicle Design Using ModelCenter® 

      Bradford, John Edward; Eklund, Dean (Georgia Institute of Technology, 2005-11-10)
      Over the course of the last two years and with funding from the AFRL, SEI has been performing the conceptual design of two Military Space Plane concepts called Quicksat and Sentinel. Quicksat is a Two Stage to Orbit ...
    • 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 ...