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Dale L Johnson - One of the best experts on this subject based on the ideXlab platform.

  • terrestrial environment climatic criteria guidelines for use in Aerospace Vehicle development
    2018
    Co-Authors: Dale L Johnson
    Abstract:

    This document provides guidelines for the terrestrial environment that are specifically applicable in the development of design requirements/specifications for NASA Aerospace Vehicles, payloads, and associated ground support equipment. The primary geographic areas encompassed are the John F. Kennedy Space Center, FL; Vandenberg AFB, CA; Edwards AFB, CA; Michoud Assembly Facility, New Orleans, LA; John C. Stennis Space Center, MS; Lyndon B. Johnson Space Center, Houston, TX; George C. Marshall Space Flight Center, Huntsville, AL; and the White Sands Missile Range, NM. This document presents the latest available information on the terrestrial environment applicable to the design and operations of Aerospace Vehicles and supersedes information presented in NASA-HDBK-1001 and TM X-64589, TM X-64757, TM-78118, TM-82473, and TM-4511. Information is included on winds, atmospheric thermodynamic models, radiation, humidity, precipitation, severe weather, sea state, lightning, atmospheric chemistry, seismic criteria, and a model to predict atmospheric dispersion of Aerospace engine exhaust cloud rise and growth. In addition, a section has been included to provide information on the general distribution of natural environmental extremes in the conterminous United States, and world-wide, that may be needed to specify design criteria in the transportation of space Vehicle subsystems and components. A section on atmospheric attenuation has been added since measurements by sensors on certain Earth orbital experiment missions are influenced by the Earth s atmosphere. There is also a section on mission analysis, prelaunch monitoring, and flight evaluation as related to the terrestrial environment inputs. The information in these guidelines is recommended for use in the development of Aerospace Vehicle and related equipment design and associated operational criteria, unless otherwise stated in contract work specifications. The terrestrial environmental data in these guidelines are primarily limited to information below 90 km altitude.

  • terrestrial environment climatic criteria guidelines for use in Aerospace Vehicle development 2008 revision
    2008
    Co-Authors: Dale L Johnson
    Abstract:

    This document provides guidelines for the terrestrial environment that are specifically applicable in the development of design requirements/specifications for NASA Aerospace Vehicles, payloads, and associated ground support equipment. The primary geographic areas encompassed are the John F. Kennedy Space Center, FL; Vandenberg AFB, CA; Edwards AFB, CA; Michoud Assembly Facility, New Orleans, LA; John C. Stennis Space Center, MS; Lyndon B. Johnson Space Center, Houston, TX; George C. Marshall Space Flight Center, Huntsville, AL; and the White Sands Missile Range, NM. This document presents the latest available information on the terrestrial environment applicable to the design and operations of Aerospace Vehicles and supersedes information presented in NASA-HDBK-1001 and TM X-64589, TM X-64757, TM-78118, TM-82473, and TM-4511. Information is included on winds, atmospheric thermodynamic models, radiation, humidity, precipitation, severe weather, sea state, lightning, atmospheric chemistry, seismic criteria, and a model to predict atmospheric dispersion of Aerospace engine exhaust cloud rise and growth. In addition, a section has been included to provide information on the general distribution of natural environmental extremes in the conterminous United States, and world-wide, that may be needed to specify design criteria in the transportation of space Vehicle subsystems and components. A section on atmospheric attenuation has been added since measurements by sensors on certain Earth orbital experiment missions are influenced by the Earth s atmosphere. There is also a section on mission analysis, prelaunch monitoring, and flight evaluation as related to the terrestrial environment inputs. The information in these guidelines is recommended for use in the development of Aerospace Vehicle and related equipment design and associated operational criteria, unless otherwise stated in contract work specifications. The terrestrial environmental data in these guidelines are primarily limited to information below 90 km altitude.

  • terrestrial environment climatic criteria handbook for use in Aerospace Vehicle development
    11th Conference on Aviation Range and Aerospace and the 22nd Conference on Severe Local Storms, 2004
    Co-Authors: Dale L Johnson, William W Vaughan
    Abstract:

    An update of the NASA 'Terrestrial Environment (Climatic) Criteria Handbook for Use in Aerospace Vehicle Development' (NASA-HDBK-1001) is currently in the final process of completion for release in late-2004 or early 2005. The current version of the Handbook was approved by the NASA Chief Engineer in 2000 as a NASA Preferred Technical Standard. However, it was based on natural environment criteria developed mostly in the early 1990's. Therefore, a task was approved to completely update the Handbook in order to reflect the current state-of-the-art in the various terrestrial environmental climatic criteria areas. The technical areas include: Winds, atmospheric constituents, thermodynamic parameters/models/extremes, humidity, electricity, precipitation/fog/icing, cloud phenomena/cover, diffusion/toxic release, severe weather/tornado/hurricane, solar/thermal radiation, geologic hazards, and sea state. A summary of this extensive update will be presented along with some key examples of the new contents. Earlier versions of this publication have been extensively used by the Aerospace community, especially program managers and design engineers for required natural terrestrial environment inputs to use in mission planning, development studies and trades, plus by those concerned with terrestrial environment descriptions for the major test ranges within the United States.

  • terrestrial environment climatic criteria handbook for use in Aerospace Vehicle development
    11th Conference on Aviation Range and Aerospace and the 22nd Conference on Severe Local Storms, 2004
    Co-Authors: Dale L Johnson, William W Vaughan
    Abstract:

    Aerospace Meteorology provides the identification of that aspect of meteorology that is concerned with the definition and modeling of atmospheric parameters for use in Aerospace Vehicle development, mission planning and operational capability assessments. One of the principal sources of this information is the NASA-HDBK-1001 "Terrestrial Environment (Climatic) Criteria Handbook for Use in Aerospace Vehicle Development'. This handbook was approved by the NASA Chief Engineer in 2000 as a NASA Preferred Technical Standard . Its technical contents were based on natural environment statistics/models and criteria developed mostly in the early 1990's. A task was approved to completely update the handbook to reflect the current state-of-the-art in the various terrestrial environment climatic areas.

William W Vaughan - One of the best experts on this subject based on the ideXlab platform.

  • terrestrial environment climatic criteria handbook for use in Aerospace Vehicle development
    11th Conference on Aviation Range and Aerospace and the 22nd Conference on Severe Local Storms, 2004
    Co-Authors: Dale L Johnson, William W Vaughan
    Abstract:

    An update of the NASA 'Terrestrial Environment (Climatic) Criteria Handbook for Use in Aerospace Vehicle Development' (NASA-HDBK-1001) is currently in the final process of completion for release in late-2004 or early 2005. The current version of the Handbook was approved by the NASA Chief Engineer in 2000 as a NASA Preferred Technical Standard. However, it was based on natural environment criteria developed mostly in the early 1990's. Therefore, a task was approved to completely update the Handbook in order to reflect the current state-of-the-art in the various terrestrial environmental climatic criteria areas. The technical areas include: Winds, atmospheric constituents, thermodynamic parameters/models/extremes, humidity, electricity, precipitation/fog/icing, cloud phenomena/cover, diffusion/toxic release, severe weather/tornado/hurricane, solar/thermal radiation, geologic hazards, and sea state. A summary of this extensive update will be presented along with some key examples of the new contents. Earlier versions of this publication have been extensively used by the Aerospace community, especially program managers and design engineers for required natural terrestrial environment inputs to use in mission planning, development studies and trades, plus by those concerned with terrestrial environment descriptions for the major test ranges within the United States.

  • terrestrial environment climatic criteria handbook for use in Aerospace Vehicle development
    11th Conference on Aviation Range and Aerospace and the 22nd Conference on Severe Local Storms, 2004
    Co-Authors: Dale L Johnson, William W Vaughan
    Abstract:

    Aerospace Meteorology provides the identification of that aspect of meteorology that is concerned with the definition and modeling of atmospheric parameters for use in Aerospace Vehicle development, mission planning and operational capability assessments. One of the principal sources of this information is the NASA-HDBK-1001 "Terrestrial Environment (Climatic) Criteria Handbook for Use in Aerospace Vehicle Development'. This handbook was approved by the NASA Chief Engineer in 2000 as a NASA Preferred Technical Standard . Its technical contents were based on natural environment statistics/models and criteria developed mostly in the early 1990's. A task was approved to completely update the handbook to reflect the current state-of-the-art in the various terrestrial environment climatic areas.

Jian Guo - One of the best experts on this subject based on the ideXlab platform.

  • review of uncertainty based multidisciplinary design optimization methods for Aerospace Vehicles
    Progress in Aerospace Sciences, 2011
    Co-Authors: Wen Yao, Xiaoqian Chen, Wencai Luo, Michel Van Tooren, Jian Guo
    Abstract:

    Abstract This paper presents a comprehensive review of Uncertainty-Based Multidisciplinary Design Optimization (UMDO) theory and the state of the art in UMDO methods for Aerospace Vehicles. UMDO has been widely acknowledged as an advanced methodology to address competing objectives of Aerospace Vehicle design, such as performance, cost, reliability and robustness. However the major challenges of UMDO, namely the computational complexity and organizational complexity caused by both time-consuming disciplinary analysis models and UMDO algorithms, still greatly hamper its application in Aerospace engineering. In recent years there is a surge of research in this field aiming at solving these problems. The purpose of this paper is to review these existing approaches systematically, highlight research challenges and opportunities, and help guide future efforts. Firstly, the UMDO theory preliminaries are introduced to clarify the basic UMDO concepts and mathematical formulations, as well as provide a panoramic view of the general UMDO solving process. Then following the UMDO solving process, research progress of each key step is separately surveyed and discussed, specifically including uncertainty modeling, uncertainty propagation and analysis, optimization under uncertainty, and UMDO procedure. Finally some conclusions are given, and future research trends and prospects are discussed.

Jafar Roshanian - One of the best experts on this subject based on the ideXlab platform.

  • multidisciplinary design optimization of a small solid propellant launch Vehicle using system sensitivity analysis
    Structural and Multidisciplinary Optimization, 2009
    Co-Authors: Jahangir Jodei, Masoud Ebrahimi, Jafar Roshanian
    Abstract:

    Multidisciplinary design optimization approaches have significant effects on Aerospace Vehicle design methodology. In designing next generation of space launch systems, MDO processes will face new and greater challenges. This study develops a system sensitivity analysis method to optimize multidisciplinary design of a two-stage small solid propellant launch Vehicle. Suitable design variables, technological, and functional constraints are considered. Appropriate combinations of disciplines such as propulsion, weight, geometry, and trajectory simulation are used. A generalized sensitivity equation is developed and solved. These results are basis for optimization. Comparison of the developed approach with gradient optimization methods reveals that developed approach requires less computation time.

Roberto Da Cunha Follador - One of the best experts on this subject based on the ideXlab platform.

  • experimental results of a mach 10 conical flow derived waverider to 14 x hypersonic Aerospace Vehicle
    Journal of Aerospace Technology and Management, 2011
    Co-Authors: Tiago Rolim, Marco Antonio Sala Minucci, Paulo Toro, Antonio Carlos De Oliveira, Roberto Da Cunha Follador
    Abstract:

    Resumen en: This paper presents a research in the development of the 14-X hypersonic airspace Vehicle at Institute for Advanced Studies (IEAv) from Department of Sci...

  • Experimental results of a Mach 10 conical-flow derived waverider to 14-X hypersonic Aerospace Vehicle
    Departamento de Ciência e Tecnologia Aeroespacial, 2011
    Co-Authors: Tiago Cavalcanti Rolim, Marco Antonio Sala Minucci, Paulo Gilberto De Paula Toro, Antônio De Carlos De Oliveira, Roberto Da Cunha Follador
    Abstract:

    This paper presents a research in the development of the 14-X hypersonic airspace Vehicle at Institute for Advanced Studies (IEAv) from Department of Science and Aerospace Technology (DCTA) of the Brazilian Air Force (FAB). The 14-X project objective is to develop a higher efficient satellite launch alternative, using a Supersonic Combustion Ramjet (SCRAMJET) engine and waverider aerodynamics. For this development, the waverider technology is under investigation in Prof. Henry T. Nagamatsu Aerothermodynamics and Hypersonics Laboratory (LHTN), in IEAv/DCTA. The investigation has been conducted through ground test campaigns in Hypersonic Shock Tunnel T3. The 14-X Waverider Vehicle characteristic was verified in shock tunnel T3 where surface static pressures and pitot pressure for Mach number 10 were measured and, using Schlieren photographs Diagnostic Method, it was possible to identify a leading-edge attached shock wave in 14-X lower surface