FIN LOADS AND TIP-CONTROL HINGE MOMENTS ON A 1 8-SCALE MODEL SIMULATING THE FIRST STAGE OF THE SCOUT RESEARCH VEHICLE AT A MACH NUMBER OF 2.01
Supersonic wind tunnel testing - scout vehicle fin load and tip control hinge moments
TIP CONTROL↗
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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Re-entry heating experiment to be flown by scout news release no. 64-202
Reentry heating experiment to be flown by scout launch vehicle to test ablating materials for use in apollo project flight
HEATING↗
Scout-vehicle aerodynamic-noise measurements.
Surface pressure measurement experiment accomplished on a scout launch vehicle, in which aerodynamic noise data at high reynolds numbers were obtained at supersonic speed range
NOISE MEASUREMENT↗
Flight performance data from the scout x-258 rocket motor
Flight performance, shock, and vibration data from Scout launch vehicle X-258 rocket engine
X-258 ROCKET ENGINE↗
Determination of trajectory and angles of attack of a scout heat-transfer spacecraft during reentry flight in the atmosphere
Unknown trajectory and angles of attack of Scout heat transfer spacecraft during reentry flight in atmosphere
ANGLE OF ATTACK↗
Scout vehicle flight loads.
Transverse flight loads produced on vertically rising Scout launch vehicle by horizontal winds and gusts
GUST LOAD↗
Scout motor performance analysis and prediction study /PAPS/
Scout motor performance analysis and prediction
SCOUT LAUNCH VEHICLE↗
Tunnel mounted auto destruct module Scout vehicle
Tunnel mounted, automatic, electronic destruction module for Scout launch vehicle first and second stages
SCOUT LAUNCH VEHICLE↗
Study to determine the effects on the Scout vehicle structure due to unconventional vehicle-spacecraft configurations
Effects on Scout launch vehicle structure due to unconventional vehicle-spacecraft configurations
SCOUT LAUNCH VEHICLE↗
Electrostatic measurement experiment, Scout Vehicle 131-R /S.E.V./
Scout vehicle electrostatic sensor performance
SCOUT LAUNCH VEHICLE↗
NASA to launch 5th Scout reentry heat experiment
Scout vehicle flight experiment to determine performance of phenolic nylon spacecraft heat shield material under reentry conditions
ABLATING MATERIAL↗
Feasibility study of storage concepts for Scout and other NASA solid propellant launch vehicles
Feasibility study of long term storing of Scout and other solid propellant launch vehicles in assembled, flightworthy configuration and facility requirements
STORAGE↗
Preliminary design study of SLAMAST Scout- launched advanced materials and structures test-bed. Volume III - Summary
Program considerations and results of feasibility study for small, recoverable lifting reentry vehicle test bed launched by Scout vehicle
LIFTING REENTRY↗
Integrated reliability program for Scout research vehicle.
Integrated reliability program for Scout launch vehicle in terms of design specification, review functions, malfunction reporting, failed parts analysis, quality control, standardization and certification
SYSTEM FAILURE↗
Mars Scouts: an overview
This presentation give an overview of a proposed series of Mars Scouts Missions.
Mars Scout Missions↗
Phoenix Mars Scout UHF Relay-Only Operations
The Phoenix Mars Scout Lander will launch in August 2007 and land on the northern plains of Mars in May of 2008. In a departure from traditional planetary surface mission operations, it will have no direct-to-Earth communications capability and will rely entirely on Mars-orbiting relays in order to facilitate command and control as well as the return of science and engineering data. The Mars Exploration Rover missions have demonstrated the robust data-return capability using this architecture, and also have demonstrated the capability of using this method for command and control. The Phoenix mission will take the next step and incorporate this as the sole communications link. Operations for 90 Sols will need to work within the constraints of Odyssey and Mars Reconnaissance Orbiter communications availability, anomalies must be diagnosed and responded to through an intermediary and on-board fault responses must be tolerant to loss of a relay. These and other issues pose interesting challenges and changes in paradigm for traditional space operations and spacecraft architecture, and the approach proposed for the Phoenix mission is detailed herein.
fault protection↗
Technology Scouting Report: Reliability Implications of Recent PV Module Technology Trends
This webinar links recent and anticipated PV module technology trends - such as the transition to n-type cells, increasing module sizes, and new encapsulants - with potential increases and reductions in reliability risk. Market trends are drawn from industry data and projections, and corresponding reliability implications are synthesized from interviews with researchers and industry experts. The webinar is an interim step toward developing a technology scouting report.
forecast↗