Subsystem trade-off environmental control and life support for orbiter phase B contractor
Environmental control and life support subsystem for space shuttle orbiter
Jasin, J.↗
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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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Computer requirements analysis and trade-offs for on-board space guidance and control systems
Computer requirements of self contained guidance, navigation and control system onboard manned orbital space station
Jurison, J.↗
Space shuttle booster wing geometry trade studies
Canard space shuttle reusable launch vehicle wing geometry variations effect on flyback systems weight, noting influence of aspect ratio and wing area
Butsko, J. E.↗
Northwest passage: Trade route for large air cushion vehicles
A conceptual vehicle and powerplant (10,000-ton) nuclear-powered air-cushion vehicle (ACV) that could open the Northwest Passage and other Arctic passages to commercial traffic is identified. The report contains a description of the conceptual vehicle, including the powerplant and operations, an assessment of technical feasibility, estimates of capital and operating costs, and identification of eligible cargo and markets. A comparison of the nuclear ACV freighter with nuclear container ships shows that for containerized or roll-on/roll-off cargo the ACV would provide greatly reduced transit time between North Atlantic and North Pacific ports at a competitive cost.
Anderson, J. L.↗
Astronomy sortie missions definition study. Volume 3, book 1: Design analysis and trade studies
A study to define the astronomy sortie missions was conducted. The design analyses and tradeoff studies conducted for candidate concepts are presented. The subjects discussed are: (1) system and subsystem requirements, (2) space shuttle interfaces, (3) infrared telescope development, and (4) experiments to be conducted during the mission.
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Candidate configuration trade study, Stellar-Inertial Measurement System (SIMS) for an Earth Observation Satellite (EOS), addendum
Results are given of an investigation of the effects of spacecraft orbital ephemeris and attitude errors on the ability to determine the locations of unknown landmarks with respect to known landmarks in the payload sensor imagery.
White, R.↗
Spacecraft systems design trade-offs for the Earth Resources Technology Satellite.
The Earth Resources Technology Satellite Program's use of flight proven hardware in the design of a satellite for earth sensor payload support and data handling is discussed. The use of an existing satellite as the building block around which additional support systems such as the orbit adjust system, the redundant wideband telemetry systems, the second regulated power system, and the quad redundant command system is analyzed. System performance seen in orbit vs design objectives are discussed to point up the success of the design approach chosen. Also discussed are the schedule and cost benefits derived from the use of previously developed hardware with additional subsystems as required to meet program requirements.
Branchflower, G. A.↗
Comparative aerodynamic study of two hypersonic cruise aircraft configurations derived from trade-off studies
Explore the source record for details and available documents.
Penland, J. A.↗
Definition and trade-off study of reconfigurable airborne digital computer system organizations
A highly-reliable, fault-tolerant reconfigurable computer system for aircraft applications was developed. The development and application reliability and fault-tolerance assessment techniques are described. Particular emphasis is placed on the needs of an all-digital, fly-by-wire control system appropriate for a passenger-carrying airplane.
Conn, R. B.↗
Earth Observatory Satellite system definition study. Report 1: Orbit/launch vehicle trade-off studies and recommendations
A summary of the constraints and requirements on the Earth Observatory Satellite (EOS-A) orbit and launch vehicle analysis is presented. The propulsion system (hydrazine) and the launch vehicle (Delta 2910) selected for EOS-A are examined. The rationale for the selection of the recommended orbital altitude of 418 nautical miles is explained. The original analysis was based on the EOS-A mission with the Thematic Mapper and the High Resolution Pointable Imager. The impact of the revised mission model is analyzed to show how the new mission model affects the previously defined propulsion system, launch vehicle, and orbit. A table is provided to show all aspects of the EOS multiple mission concepts. The subjects considered include the following: (1) mission orbit analysis, (2) spacecraft parametric performance analysis, (3) launch system performance analysis, and (4) orbits/launch vehicle selection.
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Earth Observatory Satellite system definition study. Report 3: Design cost trade-off studies and recommendations
An analysis of the design and cost tradeoff aspects of the Earth Observatory Satellite (EOS) development is presented. The design/cost factors that affect a series of mission/system level concepts are discussed. The subjects considered are as follows: (1) spacecraft subsystem cost tradeoffs, (2) ground system cost tradeoffs, and (3) program cost summary. Tables of data are provided to summarize the results of the analyses. Illustrations of the various spacecraft configurations are included.
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Earth Observatory Satellite system definition study. Report no. 3: Design/cost tradeoff studies. Appendix E: EOS program supporting system. Part 1: System trade studies no. 1 through 8
The design requirements and associated cost impacts for using the space shuttle to deliver the Earth Observatory Satellite (EOS) are identified. The additional impact of achieving full compatibility for resupply and retrieval is considered. Based on the results of the analysis, it is concluded that the EOS-Shuttle compatibility can be realized with reasonable spacecraft weight and cost penalties. Inherent space shuttle capabilities are adequate to meet the requirements of all missions except E and F. Mission E (Tiros 0) may be accommodated by either an EOS orbit transfer capability or a tug. The tug appears to be the only viable approach to satisfying the mission F (SEOS) requirements.
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High-lift aerodynamics: Trends, trades, and options
The trend toward the utilization of higher maximum lift coefficient with increased aircraft size and cruise velocities is discussed. The impact of this trend on the need for tradeoffs between cruise performance and takeoff, climb, and landing performance is examined. Theoretical methods for the analysis of the two-dimensional characteristics of flap systems are described and compared with experimental data. Four powered-lift concepts are described to outline some of the options currently being developed. Two jet-flap theories are described which provide analytical methods for estimation of the three-dimensional aerodynamic high-lift performance characteristics of powered lift systems.
Margason, R. J.↗
Analysis of commercial equipment and instrumentation for Spacelab payloads. Volume 3: Design analysis and trade studies
A detailed analysis is presented of each selected equipment item, and suitability and cost analyses were documented by equipment item. Tradeoffs of alternative specification requirements are presented which include possible relaxation of vibration, material control, fungus and corrosion requirements for experiment equipment. An additional tradeoff was performed to determine whether it is cost effective to modify experiment equipment to be compatible with a 28-volt dc power source rather than the conventional 110-volt ac source. Programmatic analysis data are given which were used as the basis for the extension of results from the analyses of specific equipment items to the entire spacelab experiment program.
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Trade-off analysis of modes of data handling for earth resources (ERS), volume 1
Data handling requirements are reviewed for earth observation missions along with likely technology advances. Parametric techniques for synthesizing potential systems are developed. Major tasks include: (1) review of the sensors under development and extensions of or improvements in these sensors; (2) development of mission models for missions spanning land, ocean, and atmosphere observations; (3) summary of data handling requirements including the frequency of coverage, timeliness of dissemination, and geographic relationships between points of collection and points of dissemination; (4) review of data routing to establish ways of getting data from the collection point to the user; (5) on-board data processing; (6) communications link; and (7) ground data processing. A detailed synthesis of three specific missions is included.
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Trade-off analysis of modes of data handling for earth resources (ERS), volume 2
For abstract, see N75-26470.
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Coding/modulation trade-offs for Shuttle wideband data links
This paper describes various modulation and coding schemes which are potentially applicable to the Shuttle wideband data relay communications link. This link will be capable of accommodating up to 50 Mbps of scientific data and will be subject to a power constraint which forces the use of channel coding. Although convolutionally encoded coherent binary PSK is the tentative signal design choice for the wideband data relay link, FM techniques are of interest because of the associated hardware simplicity and because an FM system is already planned to be available for transmission of television via relay satellite to the ground. Binary and M-ary FSK are considered as candidate modulation techniques, and both coherent and noncoherent ground station detection schemes are examined. The potential use of convolutional coding is considered in conjunction with each of the candidate modulation techniques.
Batson, B. H.↗