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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 19 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS1973

Space tug.

The reusable space tug is a major system being planned for use with the space shuttle to augment its capability to deliver, retrieve, and support automated payloads. The reusable space tug will be designed to support all the planned missions beyond low earth orbit including geosynchronous orbit. Tug missions and requirements are discussed together with tug options, giving attention to existing transfer stages and growth stages. System studies for an interim tug concept are planned to begin in February 1973. Three independent studies will be conducted: two on cryogenic tugs and one on storable propellant tugs.-

Huber, W. G.↗
NASA NTRS1973

Earth-orbit mission considerations and Space Tug requirements.

The reusable Space Tug is a major system planned to augment the Space Shuttle's capability to deliver, retrieve, and support automated payloads. The Space Tug will be designed to perform round-trip missions from low earth orbit to geosynchronous orbit. Space Tug goals and requirements are discussed together with the characteristics of the full capability Tug. The Tug is to be operated in an unmanned 'teleoperator' fashion. Details of potential teleoperator applications are considered, giving attention to related systems studies, candidate Tug mission applications, Tug 'end-effector' alternatives, technical issues associated with Tug payload retrieval, and Tug/payload accommodations.

Huber, W. G.↗
NASA NTRS1970

Space tug

Versatility of space tug structural design relating to its mission planning and energy requirements

Culbertson, P. E.↗
NASA NTRS1972

Performance of recoverable single and multiple space tugs for missions beyond earth escape

A recoverable space tug launched by the space shuttle to provide the required post-orbital propulsion needed for placement of unmanned satellites is described. The space tug will also be used to launch interplanetary spacecraft from low earth orbit. The performance of single and multiple space tugs (in tandem) for launching spacecraft beyond earth escape is summarized. Trajectories are developed that allow recovery of the tugs whenever practical. The effects of important tug and trajectory parameters on performance are presented. It is concluded that a single tug can inject spacecraft to Mars or Venus and still be recovered. The use of several tugs in tandem can provide a significant increase in capability over the use of a single tug. The more difficult missions involve a mix of recovered and expended tugs.

Zimmerman, A. V.↗
NASA NTRS1972

Performance of recoverable single and multiple Space Tugs for missions beyond earth escape.

A recoverable Space Tug launched by the Space Shuttle can provide the required post-orbital propulsion needed for placement of unmanned satellites. The Space Tug will also be used to launch interplanetary spacecraft from low earth orbit. This study summarizes the performance of single and multiple Space Tugs (in tandem) for launching spacecraft beyond earth escape. Trajectories are developed that allow recovery of the Tugs whenever practical. The effects of important Tug and trajectory parameters on performance are presented. It is concluded that a single Tug can inject spacecraft to Mars or Venus and still be recovered. The use of several Tugs in tandem can provide a significant increase in capability over the use of a single Tug. The more difficult missions involve a mix of recovered and expended Tugs.

Zimmerman, A. V.↗
NASA NTRS1975

Space tug thermal control

The future development of full capability Space Tug will impose strict requirements upon the thermal design. While requiring a reliable and reusable design, Space Tug must be capable of steady-state and transient thermal operation during any given mission for mission durations of up to seven days and potentially longer periods of time. Maximum flexibility and adaptability of Space Tug to the mission model requires that the vehicle operate within attitude constraints throughout any specific mission. These requirements were translated into a preliminary design study for a geostationary deploy and retrieve mission definition for Space Tug to determine the thermal control design requirements. Results of the study are discussed with emphasis given to some of the unique avenues pursued during the study, as well as the recommended thermal design configuration.

Ward, T. L.↗
NASA NTRS1975

Space Tug thermal control

Future development of full capability of the Space Tug will impose strict requirements upon the thermal design. Space Tug must be capable of steady-state and transient thermal operation during any given mission for durations of up to seven days and potentially longer periods of time. Maximum flexibility and adaptability of Space Tug to the mission model requires that the vehicle operate without attitude constraints throughout any specific mission. These requirements were translated into a preliminary design study for a geostationary deploy and retrieve mission definition for Space Tug to determine the thermal control design requirements. Results of the study are discussed with emphasis on some of the unique avenues pursued during the study, as well as the recommended thermal design configuration.

Ward, T. L.↗
NASA NTRS1975

Space tug thermal control follow-on

The Space Tug Thermal Control Follow-On program was conducted to further explore some of the thermal control concepts proposed for use in space tug in a breadboard test program. The objectives were to demonstrate the thermal control capabilities of a louver/battery configuration and a thermal conditioning panel/heat pipe radiator configuration. An additional objective was added to model the header pipe and radiator of the second test and correlate the analysis with the test results. These three objectives were achieved and are discussed within this report.

Ward, T. L.↗
NASA NTRSDate not supplied

Maneuverable Automated Tethered Space Tug Simulator

This TIP will develop autonomous capabilities for the space tugs in the Flat Floor Robotics Laboratory (FFRL) for use in support of In-Space Servicing, Assembly, and Manufacturing (ISAM) and future vehicles in the FFRL. The space tugs would be housed on larger spacecraft, such as ISS or Gateway, and deployed for various ISAM activities. When these activities are complete, the space tug can be reeled back to its host spacecraft.

Flat Floor Robotics Lab↗
NASA NTRS1973

Natural environment design requirements for the space tug

The natural environment design requirements for the space tug are presented. Since the Space Tug is carried as cargo to orbital altitudes in the space shuttle bay, orbital environmental impacts and short-period atmospheric density variations are the main concerns. The subjects discussed are: (1) natural environment, (2) neutral environment, (3) charged particles, (4) radiation, and (5) meteoroid hazards.

West, G. S., Jr.↗
NASA NTRS1972

Space tug economic analysis study. Volume 1: Executive summary

An economic analysis of space tug operations is presented. The space tug is defined as any liquid propulsion stage under 100,000 pounds propellant loading that is flown from the space shuttle cargo bay. Two classes of vehicles are the orbit injection stages and reusable space tugs. The vehicle configurations, propellant combinations, and operating modes used for the study are reported. The summary contains data on the study approach, results, conclusions, and recommendations.

Source record↗
NASA NTRS1990

Requirements for a near-earth space tug vehicle

The requirement for a small but powerful space tug, which will be capable of autonomous orbital rendezvous, docking and translating cargos between near-earth orbits by the end of this decade to support the growing national and international space infrastructure focused near the Space Station Freedom, is described. An aggregate of missions drives the need for a space tug including reboosting decaying satellites back to their operational altitudes, retrieving failed or exhausted satellites to Shuttle or SSF for on-orbit refueling or repair, and transporting a satellite servicer system with an FTS to ailing satellites for supervised in-place repair. It is shown that the development and operation of a space tug to perform such numerous missions is more cost effective than separate module and satellite systems to perform the same tasks.

Gunn, Charles R.↗
NASA NTRS1974

Space Tug systems study. Volume 2: Compendium

Possible storable propellant configurations and program plans are evaluated for the space tug. Alternatives examined include: use of existing expendable stages modified for use with shuttle, followed by a space tug at a later date; use of a modified growth version of existing expendable stages for greater performance and potential reuse, followed by a space tug at a later date; use of a low development cost, reusable, interim space tug available at shuttle initial operational capability (IOC) that could be evolved to greater system capabilities at a later date; and use a direct developed tug with maximum potential to be available at some specified time after space shuttle IOC. The capability options were narrowed down to three final options for detailed program definition.

Source record↗
NASA NTRS1975

IUS/TUG orbital operations and mission support study. Volume 3: Space tug operations

A study was conducted to develop space tug operational concepts and baseline operations plan, and to provide cost estimates for space tug operations. Background data and study results are presented along with a transition phase analysis (the transition from interim upper state to tug operations). A summary is given of the tug operational and interface requirements with emphasis on the on-orbit checkout requirements, external interface operational requirements, safety requirements, and system operational interface requirements. Other topics discussed include reference missions baselined for the tug and details for the mission functional flows and timelines derived for the tug mission, tug subsystems, tug on-orbit operations prior to the tug first burn, spacecraft deployment and retrieval by the tug, operations centers, mission planning, potential problem areas, and cost data.

Source record↗
NASA NTRS1975

Space Tug baseline description and status

The baseline definition of the Space Tug discussed herein is the one necessary to meet current payload mission model requirements in the mid-1980's for the least risk and development investment. This baseline Space Tug is a nominal 15-ft diameter, 30-ft long, LOX/LH2 stage with a main propellant capacity of about 50,000 lbs. Once deployed from the Space Shuttle in orbit, it is designed to automatically deliver spacecraft to a predetermined position and velocity and/or rendezvous and dock with prepositioned spacecraft for servicing or retrieval. The Tug would normally be returned to the vicinity of the Shuttle Orbiter, with or without spacecraft, to be retrieved and returned to earth in the Shuttle. Design characteristics, performance requirements, projected activities, and subsystems features are described.

Teir, W.↗