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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 433 records · Page 24
All sourcesNASA NTRSDOE OSTI
NASA NTRS1972

Life sciences payload definition and integration study. Volume 1: Management summary

The objectives of a study program to determine the life sciences payloads required for conducting biomedical experiments during space missions are presented. The objectives are defined as: (1) to identify the research functions which must be performed aboard life sciences spacecraft laboratories and the equipment needed to support these functions and (2) to develop layouts and preliminary conceptual designs of several potential baseline payloads for the accomplishment of life research in space. Payload configurations and subsystems are described and illustrated. Tables of data are included to identify the material requirements for the space missions.

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NASA NTRS1972

A preliminary investigation of the environmental Control and Life Support Subsystems (EC/LSS) for animal and plant experiment payloads

A preliminary study of the environmental control and life support subsystems (EC/LSS) necessary for an earth orbital spacecraft to conduct biological experiments is presented. The primary spacecraft models available for conducting these biological experiments are the space shuttle and modular space station. The experiments would be housed in a separate module that would be contained in either the shuttle payload bay or attached to the modular space station. This module would be manned only for experiment-related tasks, and would contain a separate EC/LSS for the crew and animals. Metabolic data were tabulated on various animals that are considered useful for a typical experiment program. The minimum payload for the 30-day space shuttle module was found to require about the equivalent of a one-man EC/LSS; however, the selected two-man shuttle assemblies will give a growth and contingency factor of about 50 percent. The maximum payloads for the space station mission will require at least a seven-man EC/LSS for the laboratory colony and a nine-man EC/LSS for the centrifuge colony. There is practically no room for growth or contingencies in these areas.

Wells, H. B.↗
NASA NTRS1973

Effects of ascent trajectory mode and tank disposal method on shuttle payload accommodation

The effects of external tank disposal by retrorocket versus passive tank drop, and targeting the main engine burn for high apogee versus the baseline parking orbit ascent method on shuttle payload accommodation capability were investigated. Missions launched from Eastern Test Range were investigated over a range of orbit altitudes to determine tank disposal requirements including footprint dispersions and alternate impact locations, performance, and orbital maneuvering system requirements. Passive tank drop also proved to be advantageous from a payload accommodation standpoint. Direct insertion was shown to be a means of accommodating long payloads at higher altitudes than permitted by the baseline ascent method.

Blair, J. C.↗
NASA NTRS1973

Two concepts for the reduction of payload attitude slewing times.

The concepts presented are particularly valuable in sounding rocket applications, where experiment data-gathering time above the atmosphere is measured in minutes per flight. One concept is a practical nonlinear control law for slewing a payload in one axis, with performance that approaches time-optimal as the uncertainty in angular acceleration approaches zero. The second concept is a practical transformation-of-coordinates system allowing slewing about an axis not coincident with any of the three control axes of the payload, so that the payload experiment axis may move along the great circle arc containing the initial and terminal target points. Implementation of both concepts is facilitated by the availability of variable-thrust cold-gas thrustors. Both concepts can result in significant reductions in slewing times compared with more conventional systems.

Riley, D. C.↗
NASA NTRS1973

Payloads.

Approaches to payload definition, design, and planning adopted in the Space Shuttle Program are described. The Space Shuttle offers many new modes of operation featuring reuse of spacecraft, on-orbit checkout and maintenance, sortie experiment missions, and opportunities to trade launch weight and volume for cost savings. In order to take advantage of these new approaches and to accommodate the varying missions, new payload elements have been identified, and new low-cost design approaches are being developed to utilize standardized components and modularized subassemblies that reduce spacecraft buildup and maintenance costs. A new payload planning technique makes use of the computer to provide large-scale planning, scheduling, and costing required for various program options.

Marshall, W. R.↗
NASA NTRS1973

The space shuttle payload planning working groups. Volume 7: Earth observations

The findings of the Earth Observations working group of the space shuttle payload planning activity are presented. The objectives of the Earth Observation experiments are: (1) establishment of quantitative relationships between observable parameters and geophysical variables, (2) development, test, calibration, and evaluation of eventual flight instruments in experimental space flight missions, (3) demonstration of the operational utility of specific observation concepts or techniques as information inputs needed for taking actions, and (4) deployment of prototype and follow-on operational Earth Observation systems. The basic payload capability, mission duration, launch sites, inclinations, and payload limitations are defined.

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NASA NTRS1974

Space processing payloads for Spacelab

Discussed are the definitions of facilities which will serve the research needs of a large group of users. These facilities (payloads) are derived by several combinations of items from a large inventory of modular, reusable, research equipment which enables ready response to many flight opportunities. Workable concepts have been prepared and submitted to the Spacelab design activity. These designs permit the flying of either partial or dedicated payloads. The technical integrity of the modular approach to payload design/integration and the utility of commercial-equipment technology are also addressed in this paper.

Taylor, K. R.↗
NASA NTRS1973

The Space Shuttle System description, operations, and payload capabilities

General characteristics of the Space Shuttle System are presented with overall capabilities and operating characteristics detailed. Mission operations and performance baselines are presented. The relationships between orbital parameters and payload capabilities are highlighted. On-orbit scientific and applications operating modes are briefly reviewed and methods of achieving a versatile payloads program using standard payload carriers are discussed.

Heberlig, J. C.↗
NASA NTRS1974

Space processing payloads for the Space Shuttle era

This paper discusses the definition of facilities which will serve the research needs of a large group of users. These facilities (payloads) are derived by several combinations of items from a large inventory of modular, reusable research equipment, enabling us to respond to many flight opportunities. Workable concepts have been laid out and inputted into the Spacelab design activity. These designs permit the flying of either partial or dedicated payloads. Also addressed in this paper are the technical integrity of the modular approach to payload design and integration, and the utility of commercial equipment technology.

Taylor, K. R.↗
NASA NTRS1974

Requirements and concepts for space-processing payloads

The definition of facilities which will serve the research needs of a large group of users is given. These facilities (payloads) are derived by several combinations of items from a large inventory of modular, reusable, research equipment which enables ready response to many flight opportunities. Workable concepts were prepared and submitted to the Spacelab design activity. These designs permit the flying of either partial or dedicated payloads. The technical integrity of the modular approach to payload design/integration and the utility of commercial equipment technology are also discussed.

Taylor, K. R.↗
NASA NTRS1975

Prediction of payload vibration environments by mechanical admittance test techniques

A series of experiments was conducted with simple beam and mass launch vehicle and payload models in order to determine the validity of mechanical admittance/impedance techniques applied to development of improved payload vibration tests. Admittances and impedances were measured from tests of the individual components to form matrices which were combined analytically to allow prediction of responses for the complete system. Results were computed for a transmission matrix approach and an admittance matrix approach. Both a rigid body and a flexible payload model were considered. The results clearly demonstrate that the transmission matrix method is too sensitive to measurement error to be practical for this application, while the pure admittance matrix method produces quite satisfactory results. The effects of various errors on the final results are demonstrated.

Kana, D. D.↗
NASA NTRS1975

Simulation of man-machine interaction on shuttle payload manipulator

The main objective of this simulation was to evaluate the feasibility of a simplified control system for a remote manipulator for space shuttle payloads. The motion commanded by the operator through the control system to the six degree of freedom manipulator approximates that of a backhoe. Compatibility of low arm damping, heavy payloads, small clearances in the shuttle cargo bay and stringent mission timelines were evaluated. The effects of various devices to enhance visual cues were evaluated. Phase I of the simulation was capture of a payload flying free in space relative to the shuttle. Phase II was simulation of cargo stowage into a mockup of the space shuttle cargo bay. A shuttle remote manipulator control station mockup including TV monitors and hand controllers is used in the simulation. Results evaluating various parameters of the control system and the task, including arm flexibility, are presented.

Hookway, R. O.↗
NASA NTRS1975

The Concept Verification Testing of a materials science payload

The Concept Verification Testing (CVT) project at the Marshall Space Flight Center, Alabama is a developmental activity that supports Shuttle Payload projects such as Spacelab. It provides an operational one-g environment for testing NASA and other agency experiment and support systems concepts that may be used in Shuttle. A dedicated Materials Science Payload was tested in the General Purpose Laboratory (GPL) in December 1974 in order to assess the requirements of a Space Processing payload on a Spacelab type facility. Physical and functional integration of the experiments into the facility was studied, and the impact of the experiments on the facility (and vice versa) was evaluated. The Principal Investigators (PI) who had proposed experiments were onboard and in a consulting status on the ground. The significant results of the week-long simulation will be discussed.

Griner, C. S.↗
NASA NTRS1975

Future payload technology requirements study

Technology advances needed for an overall mission model standpoint as well as those for individual shuttle payloads are defined. The technology advances relate to the mission scientific equipment, spacecraft subsystems that functionally support this equipment, and other payload-related equipment, software, and environment necessary to meet broad program objectives. In the interest of obtaining commonality of requirements, the study was structured according to technology categories rather than in terms of individual payloads.

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NASA NTRS1975

STS payloads mission control study, executive summary briefing

The following study objectives were investigated and results are briefly discussed: (1) identify flight control ground functions for representative STS payloads, (2) investigate present/planned NASA-wide facilities for STS payload control, (3) determine feasible, cost effective system concept options for flight control of STS payloads, and (4) development of implementation guidelines for proposed concept option(s).

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NASA NTRS1976

The concept verification testing of materials science payloads

The concept Verification Testing (CVT) project at the Marshall Space Flight Center, Alabama, is a developmental activity that supports Shuttle Payload Projects such as Spacelab. It provides an operational 1-g environment for testing NASA and other agency experiment and support systems concepts that may be used in shuttle. A dedicated Materials Science Payload was tested in the General Purpose Laboratory to assess the requirements of a space processing payload on a Spacelab type facility. Physical and functional integration of the experiments into the facility was studied, and the impact of the experiments on the facility (and vice versa) was evaluated. A follow-up test designated CVT Test IVA was also held. The purpose of this test was to repeat Test IV experiments with a crew composed of selected and trained scientists. These personnel were not required to have prior knowledge of the materials science disciplines, but were required to have a basic knowledge of science and the scientific method.

Griner, C. S.↗
NASA NTRS1976

Space shuttle engineering and operations support. Isolation between the S-band quad antenna and the S-band payload antenna. Engineering systems analysis

The isolation between the upper S-band quad antenna and the S-band payload antenna on the shuttle orbiter is calculated using a combination of plane surface and curved surface theories along with worst case values. A minimum value of 60 db isolation is predicted based on recent antenna pattern data, antenna locations on the orbiter, curvature effects, dielectric covering effects and edge effects of the payload bay. The calculated value of 60 db is significantly greater than the baseline value of 40 db. Use of the new value will result in the design of smaller, lighter weight and less expensive filters for S-band transponder and the S-band payload interrogator.

Lindsey, J. F.↗
NASA NTRS1976

A cost and utility analysis of NIM/CAMAC standards and equipment for shuttle payload data acquisition and control systems. Volume 1: Summary

The cost effectiveness of utilizing the Nuclear Instrumentation Modular (NIM) and the Computer Automated Measurement Control (CAMAC) equipment for Spacelab payload instrumentation was determined. Representative shuttle sortie payloads were analyzed for applicability and commonality. Modification of NIM/CAMAC equipment was analyzed for its suitability in Spacelab environments and to determine the cost. NIM/CAMAC equipment usage requirements for Spacelab payloads were converted to pool size requirements and time-phased equipment procurement requirements. A programmatic estimate of the pool equipment costs and a management plan were prepared for the pool concept. The implementation and impact of CAMAC software were assessed.

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