NASA Space Systems Technology ModelNational Aeronautics and Space Administration, Office of Aeronautics and Space Technology, 1984 - Astronautics |
Common terms and phrases
Aerobraking aerocapture analysis antennas applications areas attitude control automation battery Breakdown Structure capability components composite concepts configuration cooler cooling cost cryogenic cycle density devices diameter Earth orbit efficiency electric propulsion energy engine environment Figure flight fluid forecast fuel cell gimbal gyros heat pipe heat rejection hydrazine improved increase insulation integrated interaction ion thruster large space launch lifetime liquid loads Low Earth Orbit magnetic materials mirror missions modules momentum wheels NASA nuclear on-orbit operating optical payload performance planetary plasma potential power levels power systems processing propellant propulsion systems radiation reactor reduce rocket satellite sensors shown in Fig Shuttle solar array solar cells solid space station space systems spacecraft specific impulse specific modulus specific power stability storage subsystem superconductors surface SYSTEMS TECHNOLOGY techniques TECHNOLOGY READINESS DATE temperature testing thermal control thermal management thrust thruster torques voltage W/kg weight
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Page 7-65 - Remote power controllers (RPCs) are solid state devices that combine in one unit the capability to perform all the needed functions of load switching, overload protection, and a direct indication of whether the load is on or off.
Page 3-46 - The lifetime of such heat exchangers in space is not known at present. Refrigeration is accomplished either by thermoelectric cooling, in which the cold zone is produced electrically without moving parts, or by mechanically implemented thermodynamic cycles. The mechanical processes have a coefficient of performance (COP) equal to 2, which is about four times the value obtained with the thermoelectric process. Mechanical refrigeration has not been demonstrated in space. Temperature control is achieved...
Page 7-66 - E-9231) Avail: NTIS HC A02/MF A01 CSCL 09C Solid state remote power controllers (RPC's) are now available to control and protect all types of loads in both ac and dc power distribution systems. RPC's possess many outstanding qualities that make them attractive for most system applications. A review is given of the present state-of-the-art and applications for solid state RPC's for both aerospace and terrestrial systems. Author N77-27307*jj!
Page 3-32 - ... consumption and coolant for use in thermal control systems. Electrical power production through fuel cells can be utilized to reduce both the space station solar array and battery requirements. Compounding effects result. Reduced solar array area reduces both the drag force and resultant orbit makeup propellant requirements, while reduction in battery mass further lowers the propellant requirement. Monopropellant and bipropellant auxiliary propulsion systems meet the moderate stationkeeping requirements...
Page 8-35 - A solidcryogen system is used in conjunction with an insulated container, an evaporation path to space, and a conduction path from the coolant to the focal plane being cooled. Advantages over the use of cryogenic liquids include a higher heat content per mass and volume, lower operating temperatures, and no valves for pressure control. Solid cryogens provide a reliable refrigeration system for 3 to 5 years or longer in space cooling applications.
Page 8-31 - JT expansion valve, cryogenic liquids in either the subcritical or supercritical state, and, for special applications, cryogenic solids. The advantages of these systems are simplicity, reliability, relative economy, and negligible power requirements. In most cases, the technology is developed. The basic disadvantages of cryogenic storage systems are their limited life due to heat leakage and the rapid increase in weight and volume for extended durations of use. Although high-pressure-gas storage...
Page 3-28 - Operations Space Station operations will be characterized by reduced cost and increased use of man's capability in space. This will be achieved through philosophical, programmatic, and technological developments that reduce the number and cost of ground support personnel and take advantage of the unique ability of human involvement in on-board operations. Previous manned programs required large ground crews during pre-launch, launch, and on-orbit operational phases. Early development of computer...
Page 6-17 - YEAR 1990 2000 The A curve, showing a 30% reduction in structural weight by the year 2000, is based on the use of composites and structural concepts which will evolve naturally. The 50% reduction in structural weight shown in the B curve depends not only on the full utilization of the unique properties of composites, but also on development of structural concepts using new and different structural analysis and design techniques. FC 5-30. Thermal Expansion Control Capability...
Page 3-29 - ... functions, reduced level of real-time monitoring, and increased reliance on the crew to schedule and structure crew activities. All of these changes will allow a dramatic decrease in ground personnel and cost. Man's ability to function in space will also be enhanced. In addition to decoupling most of the crew activity from ground control, crew productivity will be increased by better utilization of crew time and augmentation of crew capability. Crew time will be better used by implementing technologies...
Page 13 - LEVEL 1 BASIC PRINCIPLES OBSERVED AND REPORTED LEVEL 2 CONCEPTUAL DESIGN FORMULATED LEVEL 3 CONCEPTUAL DESIGN TESTED ANALYTICALLY OR EXPERIMENTALLY LEVEL 4 CRITICAL...