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  • Other Sources  (303)
  • SPACECRAFT PROPULSION AND POWER  (281)
  • Chemical Engineering
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  • 1990-1994  (286)
  • 1955-1959  (17)
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  • 1
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    On protection of Freedom's solar dynamic radiator from the orbital debris environment. II - Further testing and analyses (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: Presented here are results of a test program undertaken to further define the response of the solar dynamic radiator to hypervelocity impact (HVI). Tests were conducted on representative radiator panels (under ambient, nonoperating conditions) over a range of velocity. Target parameters are also varied. Data indicate that analytical penetration predictions are conservative (i.e., pessimistic) for the specific configuration of the solar dynamic radiator. Test results are used to define the solar dynamic radiator reliability with respect to HVI more rigorously than previous studies. Test data, reliability, and survivability results are presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: ASME, Transactions, Journal of Solar Energy Engineering (ISSN 0199-6231); p. 142-149.
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    On protection of Freedom's solar dynamic radiator from the orbital debris environment. I - Preliminary analysis and testing (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: A great deal of experimentation and analysis was performed to quantify penetration thresholds of components which will experience orbital debris impacts. Penetration was found to depend upon mission specific parameters such as orbital altitude, inclination, and orientation of the component; and upon component specific parameters such as material, density and the geometry particular to its shielding. Experimental results are highly dependent upon shield configuration and cannot be extrapolated with confidence to alternate shield configurations. Also, current experimental capabilities are limited to velocities which only approach the lower limit of predicted orbital debris velocities. Therefore, prediction of the penetrating particle size for a particular component having a complex geometry remains highly uncertain. An approach is described which was developed to assess on-orbit survivability of the solar dynamic radiator due to micrometeoroid and space debris impacts. Preliminary analyses are presented to quantify the solar dynamic radiator survivability, and include the type of particle and particle population expected to defeat the radiator bumpering (i.e., penetrate a fluid flow tube). Results of preliminary hypervelocity impact testing performed on radiator panel samples (in the 6 to 7 km/sec velocity range) are also presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: ASME, Transactions, Journal of Solar Energy Engineering (ISSN 0199-6231); p. 135-141.
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Advanced Main Combustion Chamber structural jacket strength analysis (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The structural analysis of the Advanced Main Combustion Chamber (AMCC) is presented. The AMCC is an advanced fabrication concept of the Space Shuttle Main Engine main combustion chamber (MCC). Reduced cost and fabrication time of up to 75 percent were the goals of the AMCC with cast jacket with vacuum plasma sprayed or platelet liner. Since the cast material for the AMCC is much weaker than the wrought material for the MCC, the AMCC is heavier and strength margins much lower in some areas. Proven hand solutions were used to size the manifolds cutout tee areas for combined pressure and applied loads. Detailed finite element strength analyses were used to size the manifolds, longitudinal ribs, and jacket for combined pressure and applied local loads. The design of the gimbal actuator strut attachment lugs were determined by finite element analyses and hand solutions.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 93-1395 , In: AIAA(ASME)ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 34th and AIAA/ASME Adaptive Structures Forum, La Jolla, CA, Apr. 19-22, 1993, Technical Papers. Pt. 2 (A93-33876 1; p. 833-836.
    Format: text
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  • 4
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    Finite element analysis of the Space Shuttle Main Engine (SSME) alternate turbopump development (ATD) high pressure oxydizer turbopump (HPOTP) (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A 3D model of all stationary components of the ATD HPOTP is analyzed using a superelement solution technique to obtain a better understanding of the pump behavior and to support pump testing. Emphasis is place on the methods used for determining deflections. As part of the model verification, analyses were conducted on the main housing model under proof-pressure and push-test loading conditions. The analysis at 109 percent rate power level resulted in asymmetric deformation patterns which were used to calculate operating and rub clearances. The present analysis is considered to provide the most realistic representation of the ATD HPOTP to date.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 93-1396 , In: AIAA(ASME)ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 34th and AIAA/ASME Adaptive Structures Forum, La Jolla, CA, Apr. 19-22, 1993, Technical Papers. Pt. 2 (A93-33876 1; p. 837-846.
    Format: text
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  • 5
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    On protection of Freedom's solar dynamic radiator from the orbital debris environment. Part 2: Further testing and analyses (1991)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Presented here are results of a test program undertaken to further define the response of the solar dynamic radiator to hypervelocity impact (HVI). Tests were conducted on representative radiator panels (under ambient, nonoperating conditions) over a range of velocity. Target parameters are also varied. Data indicate that analytical penetration predictions are conservative (i.e., pessimistic) for the specific configuration of the solar dynamic radiator. Test results are used to define the solar dynamic radiator reliability with respect to HVI more rigorously than previous studies. Test data, reliability, and survivability results are presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-104514 , E-6335 , NAS 1.15:104514 , International Solar Energy Conference; Apr 04, 1992 - Apr 08, 1992; Lahaina, Maui, HI; United States
    Format: application/pdf
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  • 6
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    On protection of Freedom's solar dynamic radiator from the orbital debris environment. Part 1: Preliminary analyses and testing (1990)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A great deal of experimentation and analysis was performed to quantify penetration thresholds of components which will experience orbital debris impacts. Penetration was found to depend upon mission specific parameters such as orbital altitude, inclination, and orientation of the component; and upon component specific parameters such as material, density and the geometry particular to its shielding. Experimental results are highly dependent upon shield configuration and cannot be extrapolated with confidence to alternate shield configurations. Also, current experimental capabilities are limited to velocities which only approach the lower limit of predicted orbital debris velocities. Therefore, prediction of the penetrating particle size for a particular component having a complex geometry remains highly uncertain. An approach is described which was developed to assess on-orbit survivability of the solar dynamic radiator due to micrometeoroid and space debris impacts. Preliminary analyses are presented to quantify the solar dynamic radiator survivability, and include the type of particle and particle population expected to defeat the radiator bumpering (i.e., penetrate a fluid flow tube). Results of preliminary hypervelocity impact testing performed on radiator panel samples (in the 6 to 7 km/sec velocity range) are also presented. Plans for further analyses and testing are discussed. These efforts are expected to lead to a radiator design which will perform to requirements over the expected lifetime.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-102458 , E-5245 , NAS 1.15:102458 , International Solar Energy Conference; Apr 01, 1990 - Apr 04, 1990; Miami, FL; United States
    Format: application/pdf
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  • 7
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    Effect of idealized asymmetric inhibitor stubs on circumferential flow in the Space Shuttle SRM (1990)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 6; 5-10
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  • 8
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    Numerical propulsion system simulation (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: The approach currently being developed at the NASA Lewis Research Center to address the issues of high-fidelity propulsion systems computational simulations is discussed. The approach focuses on interdisciplinary analysis, system simulation, simulation environment, and parallel computing. The Numerical Propulsion System Simulation is a long range program with the ultimate goal of developing the capability to reduce the cost and time of developing advanced technology propulsion systems.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Computing Systems in Engineering (ISSN 0956-0521); 2; 4, 19
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  • 9
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    External-store drag reduction at transonic and low supersonic Mach numbers by application of Baldwin's moment-of-area rule (1955)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Keywords: GENERAL
    Type: NACA Conf. on Aerodyn. of High Speed Aircraft; p 93-103
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  • 10
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    Space Shuttle main engine OPAD: The search for a hardware enhanced plume (1993)
    In:  Other Sources
    Details
    Publication Date: 2013-08-29
    Description: The process of applying spectroscopy to the Space Shuttle Main Engine (SSME) for plume diagnostics, as it exists today, originated at Marshall Space Flight Center in Huntsville, Alabama, and its implementation was assured largely through the efforts of Sverdrup AEDC, in Tullahoma, Tennessee. This team continues to lead and guide efforts in the plume diagnostics arena. The process, Optical Plume Anomaly Detection (OPAD), formed the basis for various activities in the development of ground-based systems as well as the development of in-flight plume spectroscopy. OPAD currently provides and will continue to provide valuable information relative to future systems definitions, instrumentation development, code validation, and data diagnostic processing. OPAD is based on the detection of anomalous atomic and molecular species in the SSME plume using two complete, stand-alone optical spectrometers. To-date OPAD has acquired data on 44 test firings of the SSME at the Technology Test Bed (TTB) at MSFC. The purpose of this paper will be to provide an introduction to the OPAD system by discussing the process of obtaining data as well as the methods of examining and interpreting the data. It will encompass such issues as selection of instrumentation correlation of data to nominal engine operation, investigation of SSME component erosion via OPAD spectral data, necessity and benefits of plume seeding, application of artificial intelligence (AI) techniques to data analysis, and the present status of efforts to quantify specie erosion utilizing standard plume and chemistry codes as well as radiative models currently under development.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: JHU, The 1993 JANNAF Propulsion Meeting, Volume 2; p 79-92
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