Reflection coefficients of planetary surfaces from unmanned spacecraft.
Radar type instrument for measuring reflection coefficients of planetary surfaces from unmanned spacecraft
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Radar type instrument for measuring reflection coefficients of planetary surfaces from unmanned spacecraft
Bladders, diaphragms and pistons used for earth- storable liquid rocket propellant expulsion in unmanned spacecraft
High-power microwave transmitters for deep-space communication with unmanned spacecraft
Magnetic unloading system provides torque to unload wheel momentum in presence of nonzero average disturbance torques for stabilizing unmanned spacecraft
Design of thermionic reactor power systems for nuclear electric propelled unmanned spacecraft
Design calculations for magnetohydrodynamic power conversion system for nuclear electric propelled unmanned spacecraft
Analytic procedures and computer codes for predicting weight optimized radioisotope thermal generator shields for unmanned spacecraft
Analytic procedures and computer codes for prediction of weight optimized radioisotope thermoelectric generator shields for unmanned spacecraft
Analysis of propellant sensitivity, secondary propulsion, and ground operations for unmanned spacecraft propulsion systems
Feasibility of common stage for alternate space missions and attitude control systems for unmanned spacecraft propulsion system
This handbook is approved for use by NASA Headquarters and all NASA Centers and is intended to provide a common framework for consistent practices across NASA programs. This handbook was developed to describe electrical grounding design architecture options for unmanned spacecraft. This handbook is written for spacecraft system engineers, power engineers, and electromagnetic compatibility (EMC) engineers. Spacecraft grounding architecture is a system-level decision which must be established at the earliest point in spacecraft design. All other grounding design must be coordinated with and be consistent with the system-level architecture. This handbook assumes that there is no one single 'correct' design for spacecraft grounding architecture. There have been many successful satellite and spacecraft programs from NASA, using a variety of grounding architectures with different levels of complexity. However, some design principles learned over the years apply to all types of spacecraft development. This handbook summarizes those principles to help guide spacecraft grounding architecture design for NASA and others.
As a NASA center, the Jet Propulsion Laboratory (JPL) is committed to the concept of developing and launching a continuously improving series of smaller robotic space exploration missions in shorter intervals of time (faster, better, cheaper).
Mission and planetary vehicles characteristics affecting design of solid propellant motors and thrust vector control systems in planetary orbiters and landers
Storability, thermodynamic properties, and performance of high energy liquid propellants
Mission and planetary vehicles characteristics affecting design of solid propellant motors and thrust vector control systems in planetary orbiters and landers
Conical radiator configuration requiring minimum parasitic launch support for thermionic reactor power system for a nuclear electric propelled Titan 3c/7
Design and weight summary for baseline magnetohydrodynamic power system of nuclear electric propulsion spacecraft
Weight factors and cycle efficiency for nuclear electric propelled spacecraft using MHD power system