SEARCH · Search NASA
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.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
The functional elements of payload operations and support are discussed together with some of the features of the operational concept. The existence of clear and simple lines of responsibility and authority is an important factor in a simplification of the decision process. A high orbiter utilization rate is a key to the economic advantage of the reusable transportation system.
A complete description is given of the IVE physical and performance design requirements as evolved in this study. The data are presented in a format to facilitate the development of an item specification. Data were used to support the development of the project plan data (schedules, cost, etc.) contained in Volume 4 of this report.
A representative set of payloads for both science and applications disciplines were selected that would ensure a realistic and statistically significant estimate of equipment utilization. The selected payloads were analyzed to determine the applicability of Nuclear Instrumentation Modular (NIM)/Computer Automated Measurement Control (CAMAC) equipment in satisfying their data acquisition and control requirements. The analyses results were combined with the comparable results from related studies to arrive at an overall assessment of the applicability and commonality of NIM/CAMAC equipment usage across the spectrum of payloads.
The modifications for the Nuclear Instrumentation Modular (NIM) and Computer Automated Measurement Control (CAMAC) equipment, designed for ground based laboratory use, that would be required to permit its use in the Spacelab environments were determined. The cost of these modifications were estimated and the most cost effective approach to implementing them were identified. A shared equipment implementation in which the various Spacelab users draw their required complement of standard NIM and CAMAC equipment for a given flight from a common equipment pool was considered. The alternative approach studied was a dedicated equipment implementation in which each of the users is responsible for procuring either their own NIM/CAMAC equipment or its custom built equivalent.
A preliminary assessment of vibroacoustic test plan optimization for free flyer STS payloads is presented and the effects on alternate test plans for Spacelab sortie payloads number of missions are also examined. The component vibration failure probability and the number of components in the housekeeping subassemblies are provided. Decision models are used to evaluate the cost effectiveness of seven alternate test plans using protoflight hardware.
The paper gives a detailed description of the Multimission Modular Spacecraft. Attention is given to the structural system, the electrical system, the thermal control system, the power system, attitude control, the propulsion module, and mission considerations.
An investigation of all payloads in the IBM disciplines and the selection of driver payloads within each discipline are described. The driver payloads were selected on the basis of their data processing requirements. These requirements are measured by a weighting scheme. The total requirements for each discipline are estimated by use of the technology payload model. The driver selection process which was both a payload by payload comparison and a comparison of expected groupings of payloads was examined.
Explore the source record for details and available documents.
A payload change-out room developed to provide a controlled environment and the structural platform for a payload ground handling mechanism (PGHM), which performs the actual installation or removal of the payload is described. Design efforts to develop a PGHM compatible with the free-standing launch vehicle and the payload change-out room housing are discussed. Requirements of the PGHM considered include compensation for structural deflections resulting from wind forces and the transfer of the payload weight and protection for the payload, the orbiter, and the PGHM itself against damaging impacts that could occur during such deflections.
Payload safety guidelines and implementation procedures which were revised to include updated sections on energy storage batteries are presented.
The paper describes four separate advanced space radiator concepts that have been pursued in an integrated effort to develop multipayload use, low-cost heat rejection systems which can overcome the limitations of current radar systems. These four concepts are the following: (1) a wide heat load range, modularized space radiation system; (2) a heat rejection subsystem designed as a compact self-contained heat rejection module which provides a refrigeration cycle to accomodate a wide variation in payload heat loads and cooling temperature requirements; (3) a lightweight flexible fin radiator system with heat rejection capability; and (4) a radiator which does not require a circulating coolant on the radiator panel with heat pipes and thus particularly applies to very-long-duration free-flying payloads where long life reliability is an overriding design parameter. The Orbiter active thermal control system is briefly described.
It is pointed out that if the difference between the nodal crossing time of the Shuttle parking orbit and the final orbit of a spacecraft is more than about half an hour, current design spacecraft may have to carry a prohibitively large propulsion system to meet its requirements. Various solutions to this problem are discussed.
Data are presented covering (1) scheduled launch month and orbiter vehicle, (2) the inclination of the orbit and the altitude in nautical miles, (3) the number of crew members and the duration of the mission, (4) the payload, and (5) the carrier.
Previously cited in issue 24, p. 3746, Accession no. A82-48063
The Office of Space and Terrestrial Applications-3 payload, scheduled for flight on STS Mission 17, consists of four earth-observation experiments. The Feature Identification and Location Experiment-1 will spectrally sense and numerically classify the earth's surface into water, vegetation, bare earth, and ice/snow/cloud-cover, by means of spectra ratio techniques. The Measurement of Atmospheric Pollution from Satellite experiment will measure CO distribution in the middle and upper troposphere. The Imaging Camera-B uses side-looking SAR to create two-dimensional images of the earth's surface. The Large Format Camera/Attitude Reference System will collect metric quality color, color-IR, and black-and-white photographs for topographic mapping.
Report describes Space Flight 80C86 microcomputer board, a configurable general-purpose microcomputer board designed specifically for near-Earth space-flight applications. Architecture of microcomputer board supports dual-bus structure. Local bus provides essential elements for stand-alone computer operations, and system bus provides for communication with subsystems unique to specific application.
Explore the source record for details and available documents.
An interface verification test (IFVT) in the free-free condition was conducted to verify that the constrained modes of a mass simulator had the same frequencies as the Hubble Space Telescope, for which it was designed. Landing tests were performed in which the mass simulator was mounted on its trunnions inside a container onboard an aircraft. Its acceleration response was adequately measured, and the anticipated constrained natural frequencies based on the IFVT were confirmed. The first test updated the model to predict the fixed based modes, and the second verified the test's capacity to characterize the structure. The IFVT is shown to generate information which permits accurate modeling of the constrained structure, without requiring the traditional fixed-based modal test.