Electrostatic measurement experiment, Scout Vehicle 131-R /S.E.V./
Scout vehicle electrostatic sensor performance
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Scout vehicle electrostatic sensor performance
Scout vehicle flight experiment to determine performance of phenolic nylon spacecraft heat shield material under reentry conditions
Feasibility study of long term storing of Scout and other solid propellant launch vehicles in assembled, flightworthy configuration and facility requirements
Program considerations and results of feasibility study for small, recoverable lifting reentry vehicle test bed launched by Scout 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
This presentation give an overview of a proposed series of Mars Scouts Missions.
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.
Thermodynamic and physical properties of solid propellant for MARC 36Al spin rocket motor for Scout vehicles - static test firing of rocket motors
Low-density phenolic nylon charring ablator nose cones for Scout reentry project
Design feasibility of Scout launched recoverable lifting reentry vehicle test bed
Feasibility of Scout launched small lifting reentry vehicle for testing materials and thermostructures of full scale reentry vehicles
Vehicle instrumention and ground support equipment development to improve vertical and roll alignment of Scout launch vehicle
Error sources and their magnitudes in Scout launch vehicle data
Electrostatic potential sensors for use on NASA Scout vehicle S-131R
Modified BE-3 engine for fifth stage of Scout launch vehicle
Tabulated results of error analysis for reentry and escape missions of Scout launch vehicle
Rocket motor integration into Scout vehicle to improve performance
Scout missile destruct charge system premature operational response to high temperature environment caused by combustion gas leak during stage separation