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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 217 records · Page 12
All sourcesNASA NTRSDOE OSTI
NASA NTRS1973

Payload design requirements analysis (study 2.2). Volume 3. Guideline analysis

Payloads to be launched on the space shuttle/space tug/sortie lab combinations are discussed. The payloads are of four types: (1) expendable, (2) ground refurbishable, (3) on-orbit maintainable, and (4) sortie. Economic comparisons are limited to the four types of payloads described. Additional system guidelines were developed by analyzing two payloads parameterically and demonstrating the results on an example satellite. In addition to analyzing the selected guidelines, emphasis was placed on providing economic tradeoff data and identifying payload parameters influencing the low cost approaches.

Shiokari, T.↗
NASA NTRS1973

Low cost payload studies

Low cost payload studies aimed at the reduction of Space Shuttle cost, with the emphasis on mission support subsystem equipment, are reviewed. Spacecraft design, manufacturing and operational approaches are specified and quantified to demonstrate the feasibility of reductions of cost from present-day estimates. Space Shuttle design capabilities for retrieval, repair, and reuse of future payloads are indicated as cost reduction possibilities. It is also pointed out that an increased volume and weight carrying capability of the Space Shuttle can alter the design approach to future payloads to reduce cost. Details are given on some specific subsystem component design alterations integrated in an overall low-cost payload design. Refurbishment is discussed as the final area of interest for low cost payload design. Total program savings of up to 50% are found to be possible in the studies.

Moore, W. F.↗
NASA NTRS1973

Space shuttle sortie payload crew safety and systems compatibility criteria. Volume 1: Executive summary

As part of the effort to reduce the costs of shuttle payloads, this study was performed to determine the minimum, mandatory design and verification criteria necessary to insure that sortie payloads are compatible with the space shuttle system; distinguishing them from those criteria related primarily to mission success, configuration choices, management prerogatives, or other cost-benefit variables which are, therefore, discretionary to payload project management. It was concluded that utilization of the mandatory design criteria, presented in this report, as the basis for sortie payload specifications will produce basic systems compatibility between the orbiter and its sortie payloads at reduced costs. Also, when additional criteria are generated due to changes in subsystems, designs, or guidelines, the categorization methodology developed can aid managerial decision-making concerning these criteria. To a limited degree, the compatibility criteria as defined in this study reflect a portion of the total system safety effort involved in a manned space program.

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NASA NTRS1974

Operations planning simulation model extension study. Volume 1: Long duration exposure facility ST-01-A automated payload

Ground processing and operation activities for selected automated and sortie payloads are evaluated. Functional flow activities are expanded to identify payload launch site facility and support requirements. Payload definitions are analyzed from the launch site ground processing viewpoint and then processed through the expanded functional flow activities. The requirements generated from the evaluation are compared with those contained in the data sheets. The following payloads were included in the evaluation: Long Duration Exposure Facility; Life Sciences Shuttle Laboratory; Biomedical Experiments Scientific Satellite; Dedicated Solar Sortie Mission; Magnetic Spectrometer; and Mariner Jupiter Orbiter. The expanded functional flow activities and descriptions for the automated and sortie payloads at the launch site are presented.

Marks, D. A.↗
NASA NTRS1975

Automated Space Processing Payloads Study. Volume 1: Executive Summary

An investigation is described which examined the extent to which the experiment hardware and operational requirements can be met by automatic control and material handling devices; payload and system concepts are defined which make extensive use of automation technology. Topics covered include experiment requirements and hardware data, capabilities and characteristics of industrial automation equipment and controls, payload grouping, automated payload conceptual design, space processing payload preliminary design, automated space processing payloads for early shuttle missions, and cost and scheduling.

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NASA NTRS1974

Space payload dynamic testing

More cost effective methods for insuring payload reliability are required to efficiently utilize the projected payload capacity of future space systems such as the Space Shuttle. Studies are needed to better define the vibration environment of space vehicles to develop improved and more routine methods of testing and to develop better dynamic protection systems. Such improvements in environment definition, testing, and isolation will lead to less stringent design specification, improved payload reliability, fewer and more realistic qualification and flight acceptance tests. This paper presents current payload test philosophies, effectiveness of testing, and research needed to achieve more cost effective payload reliability for future applications.

Pinson, L. D.↗
NASA NTRS1975

Preliminary Shuttle payload contamination assessment

The paper discusses the molecular induced atmosphere of the Shuttle Orbiter and a payload carrier (Spacelab) configuration - long module and a 3-m pallet) in the Shuttle Orbiter payload bay and compares it to the ambient atmosphere at various orbital altitudes. The density and flux of the contaminants are expressed as a function of distance out of the payload bay for a line-of-sight perpendicular to the payload bay and payload carrier. Isodensity plots about the Shuttle Orbiter for a side and end view for each major source are presented. The major sources considered are the external surface materials mass loss, pressurized habitation area leakage, attitude control engines, and supplemental flash evaporator venting. The resulting plots provide an insight into the extent and spatial variation of the on-orbit contaminant-induced environment.

Ress, E. B.↗
NASA NTRS1976

Optical tools and techniques for aligning solar payloads with the SPARCS control system

The success of a rocket-borne experiment depends not only on the pointing of the attitude control system, but on the alignment of the attitude control system to the payload. To ensure proper alignment, special optical tools and alignment techniques are required. Those that were used in the SPARCS program are described and discussed herein. These tools include theodolites, autocollimators, a 38-cm diameter solar simulator, a high-performance 1-m heliostat to provide a stable solar source during the integration of the rocket payload, a portable 75-cm sun tracker for use at the launch site, and an innovation called the Solar Alignment Prism. Using the real sun as the primary reference under field conditions, the Solar Alignment Prism facilitates the coalignment of the attitude sun sensor with the payload. The alignment techniques were developed to ensure the precise alignment of the solar payloads to the SPARCS attitude sensors during payload integration and to verify the required alignment under field conditions just prior to launch.

Thomas, N. L.↗
NASA NTRS1976

STS payloads mission control study (continuation phase)

User oriented space transportation system-payload mission control concepts are developed for optimum contribution of ground flight control support to onboard capability to meet STS payload objectives in a cost effective manner. Flight control ground functions are identified for representative payloads. Present and planned NASA facilities for payload control are investigated. Cost effective system concept options are determined for flight control of the payloads. Implementation guidelines are developed for proposed system concept options. Joint preflight activities are identified. Composite joint resources are identified.

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NASA NTRS1976

Spacelab payload accommodation handbook. Preliminary issue

The main characteristics of the Spacelab system are described. Sufficient information on Spacelab capabilities is provided to enable individual experimenters or payload planning groups to determine how their payload equipment can be accomodated by Spacelab topics discussed include major spacelab/experiment interfaces; Spacelab payload support systems and requirements the experiments must comply with to allow experiment design; and development and integration up to a level where a group of individual experiments are integrated into a complete Spacelab payload using Spacelab racks/floors and pallet segments. Integration of a complete Spacelab payload with Spacelab subsystems, primary module structure etc., integration of Spacelab with the Orbiter and basic operational aspects are also covered in this preliminary edition of the handbook which reflects the current Spacelab baseline design and is for information only.

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NASA NTRS1977

Development of shuttle payloads

The development of payloads for the Shuttle is described in terms of two activities - one is oriented towards development of payload hardware, while the other is oriented towards the development of payload/Space Transportation System (STS) planning, scheduling, and integration techniques. This second activity is called STS Utilization Planning (SUP). In addition to describing the major aspects of SUP, a discussion of development activities on three payloads that typify direct Shuttle placement missions is included. These payloads are the First Spacelab Mission, the Atmospheric, Magnetospheric, and Plasmas in Space (AMPS) payload, and the Large Space Telescope (LST).

Murphy, J. T.↗
NASA NTRS1979

Payload installation and deployment aid for Space Shuttle Orbiter spacecraft remote manipulator system

An aid concept known as the PIDA (Payload Installation and Deployment Aid) is presented as a way to assist the RMS (Remote Manipulator System) by relaxing the accuracy required during payload handling in the payload bay. The aid concept was designed and developed to move payloads through a prescribed path between the confined quarters of the payload bay and a position outside the critical maneuvering area of the Orbiter. A description of the design requirements and the modes of operation of the various functions of the deployment and the docking mechanisms are covered.

Ross, T. O.↗
NASA NTRS1978

Efficient payload processing - The opposite side of frequent Space Shuttle launches

An overview is presented of the processing cycles of horizontally integrated and vertically integrated Shuttle payloads at the Kennedy Space Center. Attention is given to the integration of these payloads into Shuttle-ready cargos and the installation of the cargo into the Orbiter. Diagrams are presented of: (1) Shuttle processing flow at KSC, (2) payload processing flow, (3) typical items of multimission support equipment, (4) primary items of checkout equipment, (5) payload ready for transfer into the canister for vertical processing, and (6) the rotating service structure retracted to receive the payload canister.

Scherer, L. R.↗
NASA NTRS1979

Determination of ASPS performance for large payloads in the shuttle orbiter disturbance environment

A high fidelity simulation of the annular suspension and pointing system (ASPS), its payload, and the shuttle orbiter was used to define the worst case orientations of the ASPS and its payload for the various vehicle disturbances, and to determine the performance capability of the ASPS under these conditions. The most demanding and largest proposed payload, the Solar Optical Telescope was selected for study. It was found that, in all cases, the ASPS more than satisfied the payload's requirements. It is concluded that, to satisfy facility class payload requirements, the ASPS or a shuttle orbiter free-drift mode (control system off) should be utilized.

Keckler, C. R.↗
NASA NTRS1981

STS-2 second space shuttle mission: Shuttle to carry scientific payload on second flight

The STS-2 flight seeks to (1) fly the vehicle with a heavier payload than the first flight; (2) test Columbia's ability to hold steady attitude for Earth-viewing payloads; (3) measure the range of payload environment during launch and entry; (4) further test the payload bay doors and space radiators; and (5) operate the Canadian-built remote manipulator arm. The seven experiments which comprise the OSTA-1 payload are described as well as experiments designed to assess shuttle orbiter performance during launch, boost, orbit, atmospheric entry and landing. The menu for the seven-day flight and crew biographies, are included with mission profiles and overviews of ground support operations.

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NASA NTRS1980

The payload connection - Approaches to onboard data processing for scientific systems on the Space Shuttle

The integration of payload instruments into the Command and Data Management Subsystem (CDMS) of the Space Shuttle Spacelab is discussed. Specific emphasis is on the distributed (self-contained processor) vs centralized (Spacelab Computer) approach to science payload utilization of these control and data handling capabilities. An overview of the Spacelab CDMS is first given. A synopsis of the integration process for Spacelab Missions 1, 2, and 3 is discussed. Three different hardware approaches to payload command and data handling are then categorized from which Spacelab implementations to date are derived. The different types of Spacelab Mission 3 payload CDMS hardware and software being used are discussed, including examples of microprocessors and data acquisition systems. Preliminary costs for Spacelab application software vs other flight software approaches are compared. A standard RAU interface that would permit a range of ECOS services to be provided, yet be implemented as a mass-produceable unit for incorporation into payloads, is proposed, in keeping with the trend toward simplifying the integration effort, standardizing CDMS interfaces, and ultimately lowering cost.

Konkel, C. R.↗
NASA NTRS1981

The Shuttle environment from a payload viewpoint

The paper describes the basis for current estimates of Shuttle environments. It considers available predictions of environments, uncertainties, worst-case conditions and discusses how this data base is used to derive the environmental design requirements. These requirements are assessed from a payload viewpoint, i.e., how they affect payload type, design, mission, location in Shuttle and payload classification. Finally, typical future Shuttle payloads (a pallet-mounted instrument and a spacecraft) are discussed relative to how the Shuttle environments influenced the payload design and test approach.

Divita, E. L.↗
NASA NTRS1981

Payload carrier systems for conducting sortie mode science

The capabilities and characteristics of the payload carriers developed to provide structural and operational interfaces between the Space Shuttle and the various types of experiments designed to operate in the sortie mode are discussed. The Spacelab is a flexible laboratory system composed of interchangeable elements that can be put together in eight different combinations of pallets and pressurized modules, and provides considerable standard services to users in such areas as equipment installation, power distribution, thermal control, command and data management, software, pointing systems and crew participation. A modular three-axis pointing control system designated the Annular Suspension and Pointing System, is being developed to provide additional pointing capabilities to those payloads that require capabilities not provided by the Spacelab instrument pointing system. Two engineering models of the Spacelab pallet have been designated Orbital Flight Test Pallets which, together with a special experiment support structure, are intended for initial and operational payloads that do not constitute a complete Spacelab mission. The simplest and smallest payload carriers are the Getaway Special cans, intended for small, self-contained, self-sufficient payloads, and the orbiter middeck lockers. In this way, most of the user requirements for Shuttle sortie missions identified to date can be fulfilled.

Jean, O. C.↗