ALBERT

All Library Books, journals and Electronic Records Telegrafenberg

X
feed icon rss

Your email was sent successfully. Check your inbox.

An error occurred while sending the email. Please try again.

Proceed reservation?

Export
Filter
  • SPACECRAFT PROPULSION AND POWER  (3)
  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (2)
  • LAUNCH VEHICLES AND SPACE VEHICLES  (1)
Collection
Keywords
Years
  • 1
    facet.materialart.
    Unknown
    SRB ascent aerodynamic heating design criteria reduction study, volume 2 (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Data are presented for the wind tunnel interference heating factor data base, the timewise tabulated ascent design environments, and the timewise plotted environments comparing the REMTECH results to the Rockwell RI-IVBC-3 results.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-183569 , NAS 1.26:183569 , RTR-090-01-VOL-2
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 2
    facet.materialart.
    Unknown
    SRB thermal environments (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The objective was to utilize and expand the Solid Rocket Booster (SRB) orbital flight test data base for better predictions of future flight environments. There were five tasks associated with this effort: analyze the internal aft skirt wind tunnel data and incorporate it into a data base for generating design and preflight reeentry thermal environments; generate reentry design thermal environments for the SRB steel case with the nozzle extension off; generate reentry design thermal environments for the SRB Filament Wound Case with the nozzle extension off; develop an engineering tool to analyze the 3-D flowfield around the SRB aft skirt during reentry for the purpose of obtaining the frequency and severity of the belching gas intrusion internal to the aft skirt; and perform SRM transient joint flow analysis for subscale and full scale motor firing as well as determine the effects of debonds of the insulation on the fill time and heating within the field joint insulation. In addition, this work was extended to provide support for the 51L Shuttle SRB failure analysis.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-183801 , NAS 1.26:183801 , RTR-142-03
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 3
    facet.materialart.
    Unknown
    SRB ascent aerodynamic heating design criteria reduction study, volume 1 (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An independent set of solid rocket booster (SRB) convective ascent design environments were produced which would serve as a check on the Rockwell IVBC-3 environments used to design the ascent phase of flight. In addition, support was provided for lowering the design environments such that Thermal Protection System (TPS), based on conservative estimates, could be removed leading to a reduction in SRB refurbishment time and cost. Ascent convective heating rates and loads were generated at locations in the SRB where lowering the thermal environment would impact the TPS design. The ascent thermal environments are documented along with the wind tunnel/flight test data base used as well as the trajectory and environment generation methodology. Methodology, as well as, environment summaries compared to the 1980 Design and Rockwell IVBC-3 Design Environment are presented in this volume, 1.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-183580 , NAS 1.26:183580 , RTR-090-01
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 4
    facet.materialart.
    Unknown
    AOTV Low L/D Preliminary Aeroheating Design Environment (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The aerothermal environment to a configuration with a brake face which exhibits a low lift to drag ratio (L/D) of below 0.75 is emphasized. The five times geosynchronous (5 x Geo) orbit entry was selected as the design trajectory. The available data base and math model is discussed. The resulting preliminary design environment is documented. Recommendations as to how the design environment may be improved through technological advances are given.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-170877 , NAS 1.26:170877 , RTR-069-2
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 5
    facet.materialart.
    Unknown
    Initial Shuttle external tank flight evaluation (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The objective of this paper is to evaluate aerothermal flight measurements made on the Space Shuttle External Tank (ET) during its initial flights. The ETs have been adequately instrumented to measure various quantities during flight including heat transfer, pressure, and structural temperature. The flight data have been compared with mathematical models based on an extensive wind tunnel data base, realistic flowfields, and empirical heat-transfer relationships. An analysis of the results points out the validity of the current aeroheating methodology and existing data base, and identifies problem areas in the methodology as indicated by the flight data.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: AIAA PAPER 82-0843 , Joint Thermophysics, Fluids, Plasma and Heat Transfer Conference; Jun 07, 1982 - Jun 11, 1982; St. Louis, MO
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 6
    facet.materialart.
    Unknown
    External tank laminar and rarefied aeroheating (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A practical method has been developed for calculation of laminar and rarefied aerodynamic heating to the external tank of the Space Shuttle during the ascent phase of flight. A modification of laminar boundary theory is used as the basis for the heating relation. This relation is used in conjunction with a correlation for surface pressures to obtain undisturbed aerodynamic heating. Interference effects on the external tank due to the orbiter are correlated using the rarefaction parameter which was developed as part of the heating relation. The effects of rarefaction on the undisturbed and interference heating are illustrated with test data.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 79-0377 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 15, 1979 - Jan 17, 1979; New Orleans, LA
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
Close ⊗
This website uses cookies and the analysis tool Matomo. More information can be found here...