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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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At least 523 records · Page 29
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NASA NTRS1981

Aerodynamic enhancement of space transportation systems

The results of a number of recent investigations are reviewed and used to demonstrate gains in launch, orbital transfer, and planetary vehicle performance and economy that can result from the proper exploitation of aerodynamic phenomena. For launch vehicles, application of control-configured design is shown to allow substantial reduction in wing and vertical fin area (and hence, weight) while maintaining acceptable vehicle performance and control. For orbital transfer and planetary vehicles, the use of aerodynamic lift and drag to reduce retropropulsion requirements is shown to produce payload increases of up to 100 percent and to enable some planetary missions that are not feasible with all-propulsive vehicles. Finally, the application of various advanced technologies to a complete set of launch and orbit transfer vehicles in an early space industrialization mission scenario is considered.

Walberg, G. D.↗
NASA NTRS1981

The Inertial Upper Stage - A space transportation system element nearing first flight

The Inertial Upper Stage (IUS) developed by the USAF and NASA is a highly reliable, cost-effective solid propellant upper stage, with inherent flexibility and adaptability for integration with the Space Shuttle. The propulsion system is simple, utilizing safe, solid rocket motors with extremely light-weight nonmetallic cases and nozzles. The IUS can deliver 2268 kg from the Shuttle to geosynchronous altitude; it consists of a 9700 kg propellant weight first stage, an interstage structure, a 2720 kg propellant weight second stage, and an equipment support section. The avionics system includes the electronic and electrical hardware used to perform all signal conditioning, data processing, and software formatting associated with navigation, guidance, control, data management, and redundancy management. The generic thermal design of the IUS is suited to a wide range of thermal environments; the software design provides for selectable thermal maneuvers (rotisserie, reciprocating, toasting, space facing, sun facing) to satisfy different payload thermal requirements. A 1982 launch with the Titan 34D and a 1983 launch with the Shuttle Orbiter are planned.

Rohrbaugh, D. J.↗
NASA NTRS1981

Satellite services - An added benefit of the space transportation system

It is argued that the greatest economic benefit can be achieved by the Space Shuttle Orbiter's use as a satellite servicing platform if the following conditions are fulfilled: (1) the international user community must build serviceability features into its satellite and orbital platform designs, based on a common set of guidelines; (2) the various tools required for satellite servicing must be developed in a timely manner; and (3) servicing costs must be kept as low as possible, in order to appeal to the greatest number and variety of satellite operators. A three-part program development schedule is proposed, beginning with near-Orbiter servicing in low earth orbit, continuing with servicing at orbital heights between the low and geosynchronous at greater distances from the Orbiter, and culminating in the early 1990's with the use of the Space Operations Center (SOC) platform for servicing at all orbital heights.

Herardian, M. M.↗
NASA NTRS1981

Space Transportation System Cargo projects: inertial stage/spacecraft integration plan. Volume 1: Management plan

The Kennedy Space Center (KSC) Management System for the Inertial Upper Stage (IUS) - spacecraft processing from KSC arrival through launch is described. The roles and responsibilities of the agencies and test team organizations involved in IUS-S/C processing at KSC for non-Department of Defense missions are described. Working relationships are defined with respect to documentation preparation, coordination and approval, schedule development and maintenance, test conduct and control, configuration management, quality control and safety. The policy regarding the use of spacecraft contractor test procedures, IUS contractor detailed operating procedures and KSC operations and maintenance instructions is defined. Review and approval requirements for each documentation system are described.

Source record↗
NASA NTRS1982

High temperature composites for advanced missile and space transportation systems

A study has been conducted to characterize a state-of-the-art graphite/polyimide composite system by determining mechanical and thermophysical properties of selected laminates over a temperature range of -250 F to 600 F. The material studied was Celion 3000/PMR-15. Material property data obtained from testing included tension, compression and shear strengths, and coefficient of thermal expansion. Environmental conditions examined were: as cured/post-cured, isothermal aged at 600 F, thermal cycled from -250 F to 600 F, and moisture conditioned. This study has provided an initial data base on a graphite/polyimide composite system capable of operating in 500/600 F applications.

Mccleskey, S. F.↗
NASA NTRS1982

Stability and control flight test results of the space transportation system's orbiter

Flight testing of the Space Shuttle Orbiter is in progress and current results of the post-flight aerodynamic analyses are discussed. The purpose of these analyses is to reduce the pre-flight aerodynamic uncertainties, thereby leading to operational certification of the Orbiter flight envelope relative to the integrated airframe and flight control system. Primary data reduction is accomplished with a well documented maximum likelihood system identification techniques.

Culp, M. A.↗
NASA NTRS1982

Mission Control Center operations for the Space Transportation System

Orbital flight tests of the Space Shuttle Program involved three types of activities, including classic flight testing of the vehicle hardware and software, operational procedures evaluation and development, and performance of payload mission operations. This combination of activities required a capability of the Mission Control Center (MCC) to provide thorough support to the Orbiter and its crew across a broad spectrum of activities. Attention is given to MCC organization, the general functions performed by the MCC teams, a flight support description, the motivation for a change in MCC operations, support elements, orbit phase functions, and dynamic flight phase functions. It is pointed out that the MCC facilities for the operational mode of support will not be fully implemented until 1984.

Frank, M. P.↗
NASA NTRS1982

Evaluation of Space Transportation System (STS) OV-102 orbiter payload bay acoustic environment

This report presents the results of a statistical analysis and evaluation performed by the Mechanical Engineering Branch (Code 731) on the payload bay internal acoustic data measured on the STS-1 through STS-4 flights. The results are used as a basis for developing the required baseline acoustic environment specification to be used in establishing design and test criteria for STS payloads and components.

On, F. J.↗
NASA NTRS1983

The 1986 launch of the Galileo spacecraft via the Space Transportation System

Beginning with the Galileo spacecraft launch, deep space payloads will be launched via the Space Shuttle. This change from the previous use of expendable launch vehicles will introduce large changes in procedures and data flow configurations for both the flight project and the Deep Space Network during the launch period. The planned Galileo launch period sequence of events and telemetry and command data flow configurations are described.

Berman, A. L.↗
NASA NTRS1982

Analysis of physical exercises and exercise protocols for space transportation system operation

A quantitative evaluation of the Thornton-Whitmore treadmill was made so that informed management decisions regarding the role of this treadmill in operational flight crew exercise programs could be made. Specific tasks to be completed were: The Thornton-Whitmore passive treadmill as an exercise device at one-g was evaluated. Hardware, harness and restraint systems for use with the Thornton-Whitmore treadmill in the laboratory and in Shuttle flights were established. The quantitative and qualitative performance of human subjects on the Thorton-Whitmore treadmill with forces in excess of one-g, was evaluated. The performance of human subjects on the Thornton-Whitmore treadmill in weightlessness (onboard Shuttle flights) was also determined.

Coleman, A. E.↗
NASA NTRS1981

Space transportation system flight 2 OSTA-1 scientific payload data management plan

The Shuttle Imaging Radar-A (SIR-A), Shuttle Multispectral Infrared Radiometer (SMIRR), Future Identification and Location Experiment (FILE), Measurement of Air Pollution from Satellites (MAPS), Ocean Color Experiment (OCE), the Night/Day Optical Survey of Lightning (NOSL), and the Heflex Bioengineering Test (HBT) experiments are described.

Source record↗
NASA NTRS1983

Space Transportation System Mission STS-7

The second flight of Challenger was another exceptional flight in that 11 major objectives were accomplished. The TELESAT-F and PALAPA-B1 were deployed exactly on time. The SPAS-01 attached and detached operations went extremely well despite some heating problems with the SPAS. The OSTA-2 experiments for the Material Experiments Assembly and Material Wissenschaftliche Autone Unter Schwerelosigkeit were activated as planned with no indications of anomalies, and the MLR and CFES experiment packages in the middeck area were operated by the crew as planned. Ninety-six percent (56 of 58) of the assigned flight test objectives were completed. The turnaround time was accomplished in the least time to date (only 99.5 hours) and the return to KSC was completed with a total of only 5 days loss of program time.

Source record↗
NASA NTRS1982

KSC ground support operations and equipment for the space transportation system

A significant element of the Kennedy Space Center's ground support equipment for the Space Shuttle is the Launch Processing System, which provides a high level of automation for all operations, including the checkout of the Orbiter, Solid Rocket Boosters, and External Tank. Other direct support elements of the Ground Support Equipment accomplish environmental conditioning, provide and control power, gases, and fluids, and supply vehicle facility and personnel fire protection. Attention is given to the prelaunch functions of the Launch Control Center's Firing Rooms, which contain minicomputers, a data recording area, the Hardware Interface Modules, a Common Data Buffer, and Front End Processors.

Utsman, T. E.↗