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  • 1
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    Experimental measurement of passive material and structural damping for flexible space structures (1983)
    Elsevier
    Details
    Publication Date: 1983-05-01
    Print ISSN: 0094-5765
    Electronic ISSN: 1879-2030
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Elsevier
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    PAPER CURRENT
  • 2
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    A Mars environmental SURvey (MESUR) - Feasibility of a low cost global approach (1993)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Space Technology - Industrial and Commercial Applications (ISSN 0892-9270); 13; 4; p. 363-370.
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Starting small on the road to Mars (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: Three small inexpensive mission concepts for Mars landing and exploration are described emphasizing expected scientific returns that can lead to human exploration. The Mars Explorer mission prepares for human missions by means of landing-site reconnaissance and characterization, while the Surface Lander Investigation of Mars mission uses a single probe and robotics to image the surface and analyze samples. The Mars Environmental Survey experiment is reported in which robotics are employed to study the soil, atmosphere, weather and seismic activity on the red planet.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Planetary Report (ISSN 0736-3680); 12; 4, Ju; 10
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Mars Environmental Survey (MESUR): Science objectives and mission description (1992)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: In-situ observations and measurements of Mars are objectives of a feasibility study beginning at the Ames Research Center for a mission called the Mars Environmental SURvey (MESUR). The purpose of the MESUR mission is to emplace a pole-to-pole global distribution of landers on the Martian surface to make both short- and long-term observations of the atmosphere and surface. The basic concept is to deploy probes which would directly enter the Mars atmosphere, provide measurements of the upper atmospheric structure, image the local terrain before landing, and survive landing to perform meteorology, seismology, surface imaging, and soil chemistry measurements. MESUR is intended to be a relatively low-cost mission to advance both Mars science and human presence objectives. Mission philosophy is to: (1) 'grow' a network over a period of years using a series of launch opportunities, thereby minimizing the peak annual costs; (2) develop a level-of-effort which is flexible and responsive to a broad set of objectives; (3) focus on science while providing a solid basis for human exploration; and (4) minimize project cost and complexity wherever possible. In order to meet the diverse scientific objectives, each MESUR lander will carry the following strawman instrument payload consisting of: (1) Atmospheric structure experiment, (2) Descent and surface imagers, (3) Meteorology package, (4) Elemental composition instrument, (5) 3-axis seismometer, and (6) Thermal analyzer/evolved gas analyzer. The feasibility study is primarily to show a practical way to design an early capability for characterizing Mars' surface and atmospheric environment on a global scale. The goals are to answer some of the most urgent questions to advance significantly our scientific knowledge about Mars, and for planning eventual exploration of the planet by robots and humans.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Lunar and Planetary Inst., Workshop on the Martian Surface and Atmosphere Through Time; p 74-75
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    A Mars environmental survey (MESUR) - Feasibility of a low cost global approach (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: In situ measurements of Mars' surface and atmosphere are the objectives of a novel network mission concept called the Mars Environmental SURvey (MESUR). As envisioned, the MESUR mission will emplace a pole-to-pole global distribution of 16 landers on the Martian surface over three launch opportunites using medium-lift (Delta-class) launch vehicles. The basic concept is to deploy small free-flying probes which would directly enter the Martian atmosphere, measure the upper atmospheric structure, image the local terrain before landing, and survive landing to perform meteorology, seismology, surface imaging, and soil chemistry measurements. Data will be returned via dedicated relay orbiter or direct-to-earth transmission. The mission philosophy is to: (1) 'grow' a network over a period of years using a series of launch opportunities; (2) develop a level-of-effort which is flexible and responsive to a broad set of objectives; (3) focus on Mars science while providing a solid basis for future human presence; and (4) minimize overall project cost and complexity wherever possible.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: IAF PAPER 91-432
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Arcjet exploratory tests of ARC optical window design for the AFE vehicle (1991)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Tests were made in the 20 MW arc jet facility at the NASA ARC to determine the suitability of sapphire and fused silica as window materials for the Aeroassist Flight Experiment (AFE) entry vehicle. Twenty nine tests were made; 25 at a heating rate about 80 percent of that expected during the AFE entry and 4 at approximately the full, 100 percent AFE heating rate profile, that produces a temperature of about 2900 F on the surface of the tiles that protect the vehicle. These tests show that a conductively cooled window design using mechanical thermal contacts and sapphire is probably not practical. Cooling the window using mechanical thermal contacts produces thermal stresses in the sapphire that cause the window to crack. An insulated design using sapphire, that cools the window as little as possible, appears promising although some spectral data in the vacuum-ultra-violet (VUV) will be lost due to the high temperature reached by the sapphire. The surface of the insulated sapphire windows, tested at the 100 percent AFE heating rate, showed some slight ablation, and cracks appeared in two of three test windows. One small group of cracks were obviously caused by mechanical binding of the window in the assembly, which can be eliminated with improved design. Other cracks were long, straight, thin crystallographic cracks that have very little effect on the optical transmission of the window. Also, the windows did not fall apart along these crystallographic cracks when the windows were removed from their assemblies. Theoretical results from the thermal analysis computer program SINDA indicate that increasing the window thickness from 4 to 8 mm may enable surface ablation to be avoided. An insulated design using a fused silica window tested at the nominal AFE heating rate experienced severe ablation, thus fused silica is not considered to be an acceptable window material.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: NASA-CR-192655 , NAS 1.26:192655 , AFE-9004-003
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    SOFIA Platform Available for Ride-Along Research (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Presentation at NASA Ames Instrumentation Workshop describing the availability of SOFIA for ride-along research.
    Keywords: Research and Support Facilities (Air)
    Type: ARC-E-DAA-TN26351 , NASA Ames Instrumentation Workshop; Sep 16, 2015; Moffett Field, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    SIRTF high earth orbit mission conceptual structural design and analysis (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The Space Infrared Telescope Facility (SIRTF) is a cryogenically cooled, space based, one meter class telescope for infrared astronomy. A recent mission option study has moved SIRTF from a previous low earth orbit (900 km) shuttle launched design to a high earth orbit (100,000 km) Titan IV/Centaur launched design. The mission option study requirements and trades relating to the structural configuration and the chosen SIRTF design are described. Also discussed is a dynamic stress analysis of the new SIRTF baseline structural design which has been performed using finite element modeling and simulated launch interface loads.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Cryogenic Optical Systems and Instruments IV; Jul 10, 1990 - Jul 12, 1990; San Diego, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    SIRTF primary mirror design, analysis, and testing (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The primary mirror assembly (PMA) requirements and concepts for the Space Infrared Telescope Facility (SIRTF) program are discussed. The PMA studies at NASA/ARC resulted in the design of two engineering test articles, the development of a mirror mount cryogenic static load testing system, and the procurement and partial testing of a full scale spherical mirror mounting system. Preliminary analysis and testing of the single arch mirror with conical mount design and the structured mirror with the spherical mount design indicate that the designs will meet all figure and environmental requirements of the SIRTF program.
    Keywords: ENGINEERING (GENERAL)
    Type: Cryogenic Optical Systems and Instruments IV; Jul 10, 1990 - Jul 12, 1990; San Diego, CA; United States
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    NASA TECHNICAL REPORTS
  • 10
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    Mission optimization of the Space Infrared Telescope Facility (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The Space Infrared Telescope Facility (SIRTF) mission based on a cryogenically cooled telescope is described. The SIRTF makes it possible to perform background limited measurements with three focal plane instruments in the wavelength range 2-700 microns over the entire celestial sphere for at least five years. A telescope performance limited by the natural astrophysical background between 2 to 300 microns is achieved by using a superfluid helium cryogenic system for maintaining the forebaffle temperature below 8 K. The attitude control system based on Extreme Ultra-Violet Explorer reaction wheels meets the large and small angle slew requirements and provides 0.15 arc sec pointing stability. The present HEO baseline configuration has a mass of 4370 kg. The future Titan IV/Centaur launch capability to 100,000 km for a SIRTF-sized payload is at least 5770 kg.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Cryogenic Optical Systems and Instruments IV; Jul 10, 1990 - Jul 12, 1990; San Diego, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
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