Now showing items 29-48 of 108

    • Daedalon: A Revolutionary Morphing Spacecraft Design for Planetary Exploration 

      Lafleur, Jarret M.; Olds, John R.; Braun, Robert D. (Georgia Institute of Technology, 2005-01)
      The product of a study sponsored by the NASA Institute for Advanced Concepts (NIAC), Daedalon is a spacecraft design baselined for Mars which utilizes morphing wing technology to achieve the design objective of a standard, ...
    • Demonstration of CLIPS as an Intelligent Front-End for POST 

      Budianto, Irene Arianti; Olds, John R.; Baker, Nelson C. (Georgia Institute of Technology, 1999-01)
      Most of the analysis codes used in the design of aerospace systems are complex, requiring some expertise to set up and execute. Usually the Program to Optimize Simulated Trajectories (POST) fails to converge when its control ...
    • Design of a Long Endurance Titan VTOL Vehicle 

      Prakash, Ravi; Braun, Robert D.; Colby, Luke S.; Francis, Scott R.; Gündüz, Mustafa E.; Flaherty, Kevin W.; Lafleur, Jarret M.; Wright, Henry S. (Georgia Institute of Technology, 2006-03)
      Saturn's moon Titan promises insight into many key scientific questions, many of which can be investigated only by in situ exploration of the surface and atmosphere of the moon. This research presents a vertical takeoff ...
    • A Design of Experiments-Based Method for Point Selection in Approximating Output Distributions 

      McCormick, David Jeremy; Olds, John R. (Georgia Institute of Technology, 2002-09)
      The goal of this research is to find a computationally efficient and easy-to-use alternative to current approximation or direct Monte Carlo methods for robust design. More specifically, a technique is sought to use selected ...
    • Design Space Pruning Techniques for Low-Thrust, Multiple Asteroid Rendezvous Trajectory Design 

      Alemany, Kristina; Braun, Robert D. (Georgia Institute of Technology, 2007-09)
      In 2006, the 2nd Global Trajectory Optimization Competition (GTOC2) posed a “Grand Asteroid Tour” trajectory optimization problem, where participants were required to find the best possible low-thrust trajectory that ...
    • Development of a Multipurpose Low Thrust Interplanetary Trajectory Calculation Code 

      Sakai, Tadashi; Olds, John R. (Georgia Institute of Technology, 2003-08)
      A multipurpose low thrust interplanetary trajectory calculation code has been developed. This code integrates the equations of motion along the trajectory assuming that the spacecraft is subject to a single attracting body ...
    • Development of a Planetary Entry System Synthesis Tool for Conceptual Design and Analysis 

      Kipp, Devin M.; Dec, John A.; Wells, Grant William; Braun, Robert D. (Georgia Institute of Technology, 2005-06)
      A Planetary Entry Systems Synthesis Tool, with applications to conceptual design and modeling of entry systems has been developed. This tool is applicable to exploration missions that employ entry, descent and landing or ...
    • Development of SAMURAI - Simulation and Animation Model Used for Rockets with Adjustable Isp. 

      Sakai, Tadashi; Olds, John R.; Alemany, Kristina (Georgia Institute of Technology, 2005-01)
      An interplanetary trajectory calculation application SAMURAI - Simulation and Animation Model Used for Rockets with Adjustable Isp - has been developed. SAMURAI is written in C++ and calculates transfer trajectories with ...
    • A Distributed Framework for Probabilistic Analysis 

      McCormick, David Jeremy; Olds, John R. (Georgia Institute of Technology, 2002-09)
      Probabilistic multidisciplinary design optimization promises to incorporate critical design uncertainty in order to create optimal products with a high probability of meeting design constraints under a wide variety of ...
    • Economic Uncertainty of Weight and Market Parameters for Advanced Space Launch Vehicles 

      Whitfield, Jeff A.; Olds, John R. (Georgia Institute of Technology, 1998-10)
      This paper reports the results of a study that evaluated the economic risk inherent in market variability and the uncertainty of developing weight estimates for an advanced space launch vehicle program. The purpose of this ...
    • Entry Descent and Landing Challenges of Human Mars Exploration 

      Wells, Grant William; Lafleur, Jarret M.; Verges, Amanda; Manyapu, Kavya; Christian, John A., III; Lewis, Charity; Braun, Robert D. (Georgia Institute of Technology, 2006-02)
      Near-term capabilities for robotic spacecraft include a target of landing 1 - 2 metric ton payloads with a precision of about 10 kilometers, at moderate altitude landing sites (as high as +2 km MOLA). While challenging, ...
    • An Entry Handbook for the Conceptual Design of Mars Missions 

      Wells, Grant William; Braun, Robert D. (Georgia Institute of Technology, 2006-05)
      The purpose of this investigation is to investigate trends in Mars entry, descent and landing conceptual mission design and propose a method of presenting this information as a handbook for conceptual design. The premise ...
    • Entry System Options for Human Return from the Moon and Mars 

      Putnam, Zachary R.; Braun, Robert D.; Rohrschneider, Reuben R.; Dec, John A. (Georgia Institute of Technology, 2005-08)
      Earth entry system options for human return missions from the Moon and Mars were analyzed and compared to identify trends among the configurations and trajectory options and to facilitate informed decision making at the ...
    • Estimation of Launch Vehicle Propellant Tank Structural Weight Using Simplified Beam Approximation 

      Olds, John R.; Hutchinson, Virgil L., Jr. (Georgia Institute of Technology, 2004-07-11)
      Many conceptual launch vehicles are designed through the integration of various disciplines, such as aerodynamics, propulsion, trajectory, weights, and aeroheating. In the determination of the total vehicle weight, a ...
    • An Evaluation of Ballute Entry Systems for Lunar Return Missions 

      Clark, Ian G.; Braun, Robert D.; Theisinger, John; Wells, Grant William (Georgia Institute of Technology, 2006-08)
      This study investigates the advantages and feasibility of using ballutes for Earth entry at lunar return velocities. Using analysis methods suitable for conceptual design and assuming a CEV type entry vehicle, multiple ...
    • An Evaluation of Two Alternate Propulsion Concepts for Bantam-Argus: Deeply-Cooled Turbojet+Rocket and Pulsed Detonation Rocket+Ramjet 

      St. Germain, Brad David; Olds, John R. (Georgia Institute of Technology, 1999-06)
      The Bantam-Argus reusable launch vehicle concept is a smaller version of the original Argus single-stage-to-orbit launch vehicle design. Like the original Argus, Bantam-Argus uses a Maglifter launch assist system to provide ...
    • An Experimental and Analytical Study of High-Energy-Density propellants for Liquid Rocket Engines 

      Kokan, Timothy Salim; Olds, John R. (Georgia Institute of Technology, 2005-07)
      There exists wide ranging research interest in high-energy-density matter (HEDM) propellants as a potential replacement of existing industry standard fuels (LH2, RP-1, MMH, UDMH) for liquid rocket engines. The U.S. Air ...
    • Exploration of the Design Space for the ABLV-GT SSTO Reusable Launch Vehicle 

      Bradford, John Edward; Olds, John R.; Bechtel, Ryan S.; Cormier, Timothy A.; Messitt, Donald G. (Georgia Institute of Technology, 2000-09)
      The ABLV-GT is a conceptual design for an advanced reusable launch vehicle based on the current NASA Langley ABLV concept. It is a Vision Vehicle class, horizontal takeoff, horizontal landing singlestage-to-orbit vehicle. ...
    • Flight System Options for a Long Duration Mars Airplane 

      Rohrschneider, Reuben R.; Olds, John R.; Kuhl, Christopher A.; Braun, Robert D.; Steffes, Stephen R.; Hutchinson, Virgil L., Jr. (Georgia Institute of Technology, 2004-09)
      The goal of this study was to explore the flight system options for the design of a long endurance Mars airplane mission. The mission model was built in the design framework ModelCenter and a combination of a hybrid and ...
    • The Gryphon: A Flexible Lunar Lander Design to Support a Semi-Permanent Lunar Outpost 

      Arney, Dale; Hickman, Joseph; Tanner, Philip; Wagner, John; Wilson, Marc; Wilhite, Alan W. (Georgia Institute of Technology, 2007-09)
      A lunar lander is designed to provide safe, reliable, and continuous access to the lunar surface by the year 2020. The NASA Exploration System Architecture is used to initially define the concept of operations, architecture ...