Power system configuration study and reliability analysis. Spacecraft power system configuration reference manual
Preliminary power system configuration tradeoffs to select optimized systems with respect to reliability and weight - manual
MANUAL↗
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Buoyant Venus station mission feasibility study for 1972 and 1973 launch opportunities. Volume 3 - Configuration definition. Part 1 - Configuration Final report
Configuration definitions for buoyant Venus station missions for 1972 - 1973 launch period
Carroll, P. C.↗
Configuration interaction matrix elements for d sup n configurations
Configuration interaction matrix elements for weak interactions
Barnes, J. A.↗
Tracking and data relay satellite system configuration and tradeoff study. Volume 3: TDRSS configuration and data summary, part 1
A reference handbook of configuration data and design information is presented. It treats the overall system definition, operations and control, and telecommunication service system including link budgets. A brief description of the user transceiver and ground station is presented. A final section includes a summary description of the TDR spacecraft and all the subsystems. The data presented are largely in tabular form for easy reference.
Source record↗
Triple balance test of the PRR baseline space shuttle configuration on a .004 scale model of the MCR 0074 orbiter configuration in the MSFC 14 x 14 inch Trisonic Wind Tunnel (TWT 570) IA31F(B), volume 1
A wind tunnel force and moment test of the space shuttle launch vehicle was conducted. The wind tunnel model utilized a triple balance such that component aerodynamics of the orbiter, external tank, and solid rocket booster was obtained. The test was conducted at an angle of attack range from -10 deg to 10 deg, and angle of sideslip range from -10 deg to 10 deg, and a Mach number range from 0.6 to 4.96. Simulation parameters to be used in future launch vehicle wind tunnel tests were investigated. The following were included: (1) effect of orbiter -ET attach hardware; (2) model attachment (spacer) effects; (3) effects of grit on model leading surfaces; and (4) model misalignment effects. The effects of external tank nose shape was studied by investigating five different nose configurations. Plotted and tabulated data is reported.
Ramsey, P. E.↗
Earth Observatory Satellite system definition study. Report no. 3: Design/cost tradeoff studies. Appendix D: EOS configuration design data. Part 2: Data management system configuration
The Earth Observatory Satellite (EOS) data management system (DMS) is discussed. The DMS is composed of several subsystems or system elements which have basic purposes and are connected together so that the DMS can support the EOS program by providing the following: (1) payload data acquisition and recording, (2) data processing and product generation, (3) spacecraft and processing management and control, and (4) data user services. The configuration and purposes of the primary or high-data rate system and the secondary or local user system are explained. Diagrams of the systems are provided to support the systems analysis.
Source record↗
THE ORIGIN AND DISTRIBUTION OF SUPERSONIC STORE INTERFERENCE FROM MEASUREMENT OF INDIVIDUAL FORCES ON SEVERAL WING-FUSELAGESTORE CONFIGURATIONS. 1.-SWEPT-WING HEAVY-BOMBER CONFIGURATION WITH LARGE STORE NACELLE . LIFT AND DRAG, MACH NUMBER, 1.61
Supersonic store interference - 1, swept-wing heavy bomber with large stores - lift & drag at mach 1.61
EXTERNAL STORE↗
THE ORIGIN AND DISTRIBUTION OF SUPERSONIC STORE INTERFERENCE FROM MEASUREMENT OF INDIVIDUAL FORCES ON SEVERAL WING-FUSELAGE-STORE CONFIGURATIONS. II - SWEPT-WING HEAVY-BOMBER CONFIGURATION WITH LARGE STORE NACELLE. LATERAL FORCES AND PITCHING MOMENTS, MACH NUMBER, 1.61
Effect of large store /nacelle/ on a swept-wing heavy bomber - lateral force and pitching moments
SWEPT WING↗
THE ORIGIN AND DISTRIBUTION OF SUPSONIC STORE INTERFERENCE FROM MEASUREMENT OF INDIVIDUAL FORCES ON SEVERAL WING-FUSELAGESTORE CONFIGURATIONS. V - SWEPT-WING HEAVY-BOMBER CONFIGURATION WITH LARGE STORE NACELLE. MACH NUMBER 2.01
Origin & distribution of supersonic store interference/measurement of individual forces - swept-wing heavy bomber with large store figure
EXTERNAL STORE↗
THE ORIGIN AND DISTRIBUTION OF SUPERSONIC STORE INTERFERENCE FROM MEASUREMENT OF INDIVIDUAL FORCES ON SEVERAL WING-FUSELAGESTORE CONFIGURATIONS. III - SWEPT-WING FIGHTER-BOMBER CONFIGURATION WITH LARGE AND SMALL STORES. MACH NUMBER, 1.61
Origin of supersonic store interference from measurements of individual forces - swept-wing fighter-bomber with large & small stores
EXTERNAL STORE↗
Excitation cross sections for some of the states of 2p4-3p configuration of neon and 4p4-5p configuration of krypton
Excitation cross sections for proton upper laser states of neon and proton states of krypton
NEON↗
Excitation cross sections for some of the states of 2p super 4 -3p configuration of neon 4p super 4 -5p configuration of krypton.
Excitation cross sections for upper electron states of neon and krypton lasers, obtaining wave functions
Koozekanani, S.↗
Lee-side flow phenomena on space shuttle configurations at hypersonic speeds. Part 1: Flow separation and flow field viscous phenomena of a delta-wing shuttle orbiter configuration
Results of a pitot pressure investigation of the flow field on the lee side of a delta wing shuttle orbiter are presented. The results delineate the extent of the lee side separated flow and give a tentative cross sectional definition to the shock wave structure for angles of attack of 15 deg and 30 deg. It is shown that while, in general, the effects of Reynolds number on the flow field are not large, detailed effects are observed that may have significant bearing on the heating estimate. Two examples are cited for an angle of attack of 15 deg; these are: (1) The scope of the vertical tail exposed to the unseparated flow increases with increasing Reynolds number and (2) the depth of the separated flow adjacent ot where the bow wave crosses the wing appears to decrease with increasing Reynolds number. In addition, it is shown that at a spanwise station outboard of the wing-fuselage juncture, increasing Reynolds number decreased the pitot pressure in the unseparated flow. This defect of pitot pressure appears associated with the flow over the wing-fillet-fuselage juncture.
Cleary, J. W.↗