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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 883 records · Page 49

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NASA NTRS1991

Next generation solid boosters

Space transportation solid rocket motor systems; Shuttle derived heavy lift launch vehicles; advanced launch system (ALS) derived heavy lift launch vehicles; large launch solid booster vehicles are outlined. Performance capabilities and concept objectives are presented. Small launch vehicle concepts; enabling technologies; reusable flyback booster system; and high-performance solid motors for space are briefly described. This presentation is represented by viewgraphs.

Lund, R. K.↗

NASA NTRS1991

Conceptual design of a next-generation, fully reusable manned launch system

The conceptual design of a rocket-powered, two-stage fully reusable launch vehicle has been performed as a part of the Advanced Manned Launch System (AMLS) study at the NASA Langley Research Center. The main goals of the AMLS study are to provide routine, low-cost manned access to space. Technologies and system approaches have been studied that would contribute to significant reductions in operating costs relative to current systems. System and operational characteristics of the two-stage fully reusable vehicle are presented, and the various tools and methods used in the design process are summarized. The results of a series of trade studies performed to examine the effect of varying major vehicle parameters on the reference two-stage fully reusable vehicle are also summarized.

Stanley, Douglas O.↗

NASA NTRS1992

Study report recommendations for the next generation Range Safety System (RSS) Integrated Receiver/Decoder (IRD)

The Integrated Receiver/Decoder (IRD) currently used on the Space Shuttle was designed in the 1980 and prior time frame. Over the past 12 years, several parts have become obsolete or difficult to obtain. As directed by the Marshall Space Flight Center, a primary objective is to investigate updating the IRD design using the latest technology subsystems. To take advantage of experience with the current designs, an analysis of failures and a review of discrepancy reports, material review board actions, scrap, etc. are given. A recommended new design designated as the Advanced Receiver/Decoder (ARD) is presented. This design uses the latest technology components to simplify circuits, improve performance, reduce size and cost, and improve reliability. A self-test command is recommended that can improve and simplify operational procedures. Here, the new design is contrasted with the old. Possible simplification of the total Range Safety System is discussed, as is a single-step crypto technique that can improve and simplify operational procedures.

Crosby, Robert H.↗

NASA NTRS1992

Retrievable payload carrier: Next generation Long Duration Exposure Facility

This paper describes the Retrievable Payload Carrier (RPC), which is a multi-experiment, free flyer spacecraft being privately developed to make in-space experimentation more accessible and economically feasible for research and development organizations. The carrier concept was derived from NASA's highly successful and flight proven Long Duration Exposure Facility (LDEF). The LDEF capabilities have been enhanced to meet new customer requirements. This reusable payload carrier is planned for launch and retrieval by the space shuttle on a regular basis. The RPC's flexible design will facilitate manifesting of the shuttle cargo bay space. The vehicle is designed so that either the entire vehicle or only individual experiments can be removed and replaced. A fully operational RPC program consists of: (1) a carrier spacecraft; (2) a ground control station; (3) a ground processing facility; and (4) the personnel required to support both the development and operational phases of the program.

Perry, Arthur T.↗

NASA NTRS1992

Retrievable payload carrier. Next generation Long Duration Exposure Facility: Update 1992

Perry, A. T.↗

NASA NTRS1992

Next generation optical instruments and space experiments based on the LDEF thermal control surfaces experiment (S0069)

The Thermal Control Surfaces Experiment (TCSE) on the Long Duration Exposure Facility (LDEF) was a very effective experiment to study the effects of the space environment on thermal control surfaces. Three current programs have benefitted from the TCSE experiment and are the: Optical Properties Monitor (OPM); Laboratory Portable Spectroreflectometer (LPSR); and Space Portable Spectroreflectometer. The OPM expands the TCSE optical measurement and environmental monitoring capability. The LPSR is a hand held instrument developed to measure the spectral total hemispherical reflectance of small and larger surfaces in the field. The SPSR is a space application of the LPSR and TCSE technologies with the same measurement capabilities. The SPSR will be able to characterize the external surfaces of operational spacecraft such as Space Station Freedom.

Wilkes, Donald R.↗

NASA NTRS1991

Optical design considerations for next-generation space and lunar telescopes

The paper discusses the optical requirements for future large space or lunar telescopes and their influence upon the fundamental system parameters. Two telescope concepts, a four-reflection three-mirror telescope, and a spherical-primary four-mirror telescope are introduced. Both have the potential for extreme high performance, and both use four reflections to accomplish this. Considering the present available coating capabilities, the reflectivity loss in the lower UV region due to the additional reflections, compared to a two-mirror system, seriously affects the utility of four-mirror telescopes for this part of the spectrum. Separate telescopes for the UV and for longer wavelengths may therefore be a practical solution, unless significant advances in coating technology are made in the foreseeable future.

Korsch, Dietrich↗

NASA NTRS1991

Computational aerodynamics - The next generation

Continued advances in the various elements that comprise the field of computational fluid dynamics (CFD) are promoting a radically different approach to the aerodynamic design and analysis of aerospace vehicles and systems. The elements of CFD generally include numerical algorithm development, transition and turbulence modeling, surface modeling, and grid generation, scientific visualization and validation methodologies. This paper discusses the research progress and prospects for the future in each of these elements within NASA's CFD and Experimental Validation Program. The applicability of computational methods for the purposes of understanding complex flow phenomena, exploring aerodynamic concepts, and providing vehicle-design input is also addressed.

Hessenius, Kristin A.↗

NASA NTRS1991

Next generation functional components for space telemetry data processing

The use of new design methodologies to continue the evolution of telemetry data systems to higher levels of integration is discussed. In particular, hardware description languages and automated logic synthesis tools are used to create very dense Application Specific Integrated Circuits (ASICs) that generically implement telemetry processing functions. The use of the ASICs will make it possible to develop a new generation of functional components, each of the components integrating several telemetry processing subsystems into a single card.

Bennett, Toby↗

NASA NTRS1993

Next generation system modeling of NTR systems

The topics are presented in viewgraph form and include the following: nuclear thermal rocket (NTR) modeling challenges; current approaches; shortcomings of current analysis method; future needs; and present steps to these goals.

Buksa, John J.↗

NASA NTRS1993

Retrievable payload carrier, next generation Long Duration Exposure Facility: Update 1992

Access to space and cost have been two major inhibitors of low Earth orbit research. The Retrievable Payload Carrier (RPC) Program is a commercial space program which strives to overcome these two barriers to space experimentation. The RPC Program's fleet of spacecraft, ground communications station, payload processing facility, and experienced integration and operations team will provide a convenient 'one-stop shop' for investigators seeking to use the unique vantage point and environment of low Earth orbit for research. The RPC is a regularly launched and retrieved, free-flying spacecraft providing resources adequate to meet modest payload/experiment requirements, and presenting ample surface area, volume, mass, and growth capacity for investigator usage. Enhanced capabilities of ground communications, solar-array-supplied electrical power, central computing, and on-board data storage pick up on the path where NASA's Long Duration Exposure Facility (LDEF) blazed the original technology trail. Mission lengths of 6-18 months, or longer, are envisioned. The year 1992 was designated as the 'International Space Year' and coincides with the 500th anniversary of Christopher Columbus's voyage to the New World. This is a fitting year in which to launch the full scale development of our unique shop of discovery whose intent is to facilitate retrieving technological rewards from another new world: space. Presented is an update on progress made on the RPC Program's development since the November 1991 LDEF Materials Workshop.

Perry, A. T.↗

NASA NTRS1993

Next generation optical instruments and space experiment based on the LDEF thermal control surfaces experiment (S0069)

The Thermal Control Surfaces Experiment (TCSE) was a successful experiment to study the effects of the space environment on thermal control surfaces using in-space optical properties measurements combined with post-flight analyses. The TCSE reflectometer performed well on the LDEF mission demonstrating that a portable compact integrating sphere spectroreflectometer can be built that is rugged and space rated. Since the retrieval of the TCSE package from space, several other instruments have evolved from its pioneering technologies. These are the Optical Properties Monitor (OPM), the Laboratory Portable SpectroReflectometer (LPSR), and the Space Portable SpectroReflectometer (SPSR). These instruments and experiment packages are described.

Wilkes, Donald R.↗

NASA NTRS1992

Edison - The next generation infrared space observatory

Edison, a large-aperture, radiatively-cooled telescope, is proposed as the major international mission to follow the current generation of cryogenically-cooled infrared space telescopes. It is being studied at present as a 2.5-3.5 m mixed radiatively- and mechanically-cooled facility optimized to investigate the wavelength range 3-100+ microns. This paper outlines the status of the project, discusses some aspects of a smaller-aperture 'precursor' mission, and describes a portion of the baseline science mission.

Thronson, H. A., Jr.↗

NASA NTRS1992

Doppler global velocimetry - The next generation?

A new measurement technique is being developed by NASA to measure off-surface flow fields. This method, Doppler global velocimetry, will allow quantification of complex three-dimensional flow fields at video camera rates. The entire flow field structure within a selected plane is measured simultaneously rather than by scanned, point-by-point measurements using conventional laser velocimetry. To assess the capability of this new technique, velocity measurements of the vortical flow field above a thin 75-degree delta wing were made in the NASA Langley Basic Aerodynamics Research Tunnel. The operation of the system is described along with the techniques developed to process the output images. The results are then compared with similar measurements obtained using a three component laser velocimeter.

Meyers, James F.↗

NASA NTRS1993

NASA's next generation all-digital deep space network breadboard receiver

This paper describes the breadboard advanced receiver (ARX) that is currently being built for future use in NASA's deep space network (DSN). This receiver has unique requirements in having to operate with very weak signals from deep space probes and provide high quality telemetry and tracking data. The hybrid analog/digital receiver performs multiple functions including carrier, subcarrier and symbol synchronization. Tracking can be achieved for either residual, suppressed or hybrid carriers and for both sinusoidal and square wave subcarriers. System requirements are specified and a functional description of the ARX is presented. The various digital signal processing algorithms used are also discussed and illustrated with block diagrams. Other functions such as time tagged Doppler extraction and monitor/control are also discussed including acquisition algorithms and lock detection schemes.

Hinedi, Sami↗

NASA NTRS1992

Performance evaluation of candidate space suit elements for the next generation orbital EMU

The AX-5 all metallic, multibearing technologies developed at the Ames Research Center and the Mk III fabric and metallic technologies developed at the Johnson Space Center were evaluated using the current Space Shuttle space suit technologies as a baseline. Manned evaluations were performed in the Weightless Environment Training Facility and KC-135 zero-gravity aircraft. Joint torque, range, cycle life, and environmental protection characteristics were analyzed during unmanned tests. Both numerical results and test subject comments on performance are presented.

West, Philip R.↗

NASA NTRS1993

Avoiding and tolerating latency in large-scale next-generation shared-memory multiprocessors

A scalable solution to the memory-latency problem is necessary to prevent the large latencies of synchronization and memory operations inherent in large-scale shared-memory multiprocessors from reducing high performance. We distinguish latency avoidance and latency tolerance. Latency is avoided when data is brought to nearby locales for future reference. Latency is tolerated when references are overlapped with other computation. Latency-avoiding locales include: processor registers, data caches used temporally, and nearby memory modules. Tolerating communication latency requires parallelism, allowing the overlap of communication and computation. Latency-tolerating techniques include: vector pipelining, data caches used spatially, prefetching in various forms, and multithreading in various forms. Relaxing the consistency model permits increased use of avoidance and tolerance techniques. Each model is a mapping from the program text to sets of partial orders on program operations; it is a convention about which temporal precedences among program operations are necessary. Information about temporal locality and parallelism constrains the use of avoidance and tolerance techniques. Suitable architectural primitives and compiler technology are required to exploit the increased freedom to reorder and overlap operations in relaxed models.

Probst, David K.↗

NASA NTRS1994

SEQ-POINTER: Next generation, planetary spacecraft remote sensing science observation design tool

Since Mariner, NASA-JPL planetary missions have been supported by ground software to plan and design remote sensing science observations. The software used by the science and sequence designers to plan and design observations has evolved with mission and technological advances. The original program, PEGASIS (Mariners 4, 6, and 7), was re-engineered as POGASIS (Mariner 9, Viking, and Mariner 10), and again later as POINTER (Voyager and Galileo). Each of these programs were developed under technological, political, and fiscal constraints which limited their adaptability to other missions and spacecraft designs. Implementation of a multi-mission tool, SEQ POINTER, under the auspices of the JPL Multimission Operations Systems Office (MOSO) is in progress. This version has been designed to address the limitations experienced on previous versions as they were being adapted to a new mission and spacecraft. The tool has been modularly designed with subroutine interface structures to support interchangeable celestial body and spacecraft definition models. The computational and graphics modules have also been designed to interface with data collected from previous spacecraft, or on-going observations, which describe the surface of each target body. These enhancements make SEQ POINTER a candidate for low-cost mission usage, when a remote sensing science observation design capability is required. The current and planned capabilities of the tool will be discussed. The presentation will also include a 5-10 minute video presentation demonstrating the capabilities of a proto-Cassini Project version that was adapted to test the tool. The work described in this abstract was performed by the Jet Propulsion Laboratory, California Institute of Technology, under contract to the National Aeronautics and Space Administration.

Boyer, Jeffrey S.↗