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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 307 records · Page 17
All sourcesNASA NTRSDOE OSTI
NASA NTRS1983

On-board estimation technology for space station - Current status and future developments.

Design considerations and projected solutions to on-board automated estimation techniques for advanced technology controls on a space station are described, with emphasis on the state estimator. The space station is modelled as a collection of rigid and flexible bodies connected at a finite number of hinges. The systems dynamics are characterized by angular velocities of the base body, gimbal angles, and deflections of the flexible appendages. The state estimator evolution is projected to occur in four generations, with the first being control logic in the Viking and Voyager spacecraft, the second in the Shuttle and Galileo probe, the third being large antennas and the prototype space station, the last, around the year 2000, for the actual space station. Considerations for attitude, ephemeris, shape determination, and position estimation through each generation are discussed.

Rodriguez, G.↗
NASA NTRS1985

Edge Labels for Multilayer Circuit Boards

Quick visual inspection identifies out-of-place layers. Small copper pads or other labels on layers present regular pattern if multilayer circuit board properly assembled and irregular pattern if one or more layers in wrong place. New method faster, cheaper, and more reliable than earlier methods.

Rossi, P. J.↗
NASA NTRS1982

Flexible composite film for printed circuit board

A flexible printed circuit for a printed circuit board in which layers of reaction product composed of a combination of phenoxy resin - polyisocyanate - brominated epoxy resin, and in which the equivalent ratio of those functional groups is hydroxyl group: isocyanate group: epoxy group - 1 : 0.2 to 2 : 0.5 to 3 are laminated on at least one side of saturated polyester film is discussed.

Yabe, K.↗
NASA NTRS1983

A small and light weight heat exchanger for on-board helium refrigerator

A small and light weight heat exchanger used for small helium refrigerator has been developed by Sumitomo Heavy Industries, Ltd. This heat exchanger is a laminated metal heat exchanger which consists of perforated aluminum metal plates and glassfiber reinforced plastic separators. The size is from 100 mm to 28 mm in diameter and about 300 mm in length. The weight is from 2.5 kg to 0.6 kg. Also it can be used between room temperature and liquid helium temperature. The thermal efficiency obtained has been more than 96%. The heat exchanger has been practically used for on-board helium refrigerator in Japanese National Railways' superconducting magnetic levitated trains.

Koizumi, T.↗
NASA NTRS1984

BRESEX: On board supervision, basic architecture and preliminary aspects for payload and space shuttle interface

Data relative to the on board supervision subsystem are presented which were considered in a conference between INPE and NASA personnel, with the purpose of initiating a joint effort leading to the implementation of the Brazilian remote sensing experiment - (BRESEX). The BRESEX should consist, basically, of a multispectral camera for Earth observation, to be tested in a future space shuttle flight.

Bergamini, E. W.↗
NASA NTRS1984

Wind shear measuring on board an airliner

A measurement technique which continuously determines the wind vector on board an airliner during takeoff and landing is introduced. Its implementation is intended to deliver sufficient statistical background concerning low frequency wind changes in the atmospheric boundary layer and extended knowledge about deterministic wind shear modeling. The wind measurement scheme is described and the adaptation of apparatus onboard an A300 airbus is shown. Preliminary measurements made during level flight demonstrate the validity of the method.

Krauspe, P.↗
NASA NTRS1986

Controlled impact demonstration on-board (interior) photographic system

Langley Research Center (LaRC) was responsible for the design, manufacture, and integration of all hardware required for the photographic system used to film the interior of the controlled impact demonstration (CID) B-720 aircraft during actual crash conditions. Four independent power supplies were constructed to operate the ten high-speed 16 mm cameras and twenty-four floodlights. An up-link command system, furnished by Ames Dryden Flight Research Facility (ADFRF), was necessary to activate the power supplies and start the cameras. These events were accomplished by initiation of relays located on each of the photo power pallets. The photographic system performed beyond expectations. All four power distribution pallets with their 20 year old Minuteman batteries performed flawlessly. All 24 lamps worked. All ten on-board high speed (400 fps) 16 mm cameras containing good resolution film data were recovered.

May, C. J.↗
NASA NTRS1986

Chemical analysis of aerosol in the Venusian cloud layer by reaction gas chromatography on board the Vega landers

The experiment on sulfuric acid aerosol determination in the Venusian cloud layer on board the Vega landers is described. An average content of sulfuric acid of approximately 1 mg/cu m was found for the samples taken from the atmosphere at heights from 63 to 48 km and analyzed with the SIGMA-3 chromatograph. Sulfur dioxide (SO2) was revealed in the gaseous sample at the height of 48 km. From the experimental results and blank run measurements, a suggestion is made that the Venusian cloud layer aerosol consists of more complicated particles than the sulfuric acid water solution does.

Gelman, B. G.↗
NASA NTRS1985

X-ray observations of GX 1 + 4 with the monitor proportional counter on board the Einstein Observatory

The results of X-ray observations of GX 1 + 4 with the monitor proportional counter on board the Einstein Observatory (HEAO 2) are presented. Using data from the time interval processor, the value of the approximately 2 minute pulse period at the time of the observations was determined. Previous determinations are discussed, along with evidence for a suggested value of approximately 4 minutes for the pulse period. The phase of first harmonic of the Fourier decomposition of pulse profile is stable within its errors but the phases of higher harmonics are not. The spin-up time scale is determined to be approximately 40 years.

Elsner, R. F.↗
NASA NTRS1986

A single-board preprocessor and pulse generator

The Aeronomy Lab. of NOAA has designed and built a single board, programmable radar controller for use with VHF ST (stratosphere troposphere) radars. The controller consists of a coherent integrator preprocessor and a radar pulse generator, both of which are described, as well as interfaces to an antenna beam switch and a receiver bandwidth switch. The controller occupies a single slot in a Data General Nova of Eclipse computer. The integrator and pulse generator take advantage of high density, dual port FIFO chips such as the 512 x 9 Mostek MK 4501. These FIFOs have separate input and output ports and independent read and write cycles with cycle times of less than 200 ns, making them very fast and easy to interface. A simple block diagram of the coherent integrator is shown. The integrator is designed to handle inputs from one receiver (2 channels) with 1 sec sample spacing. The pulse generator is based on controllers designed by R. F. Woodman for the Arecibo and SOUSY radars us a recirculating memory scheme.

Carter, D. A.↗
NASA NTRS1987

Knowledge representation by connection matrices: A method for the on-board implementation of large expert systems

Extremely large knowledge sources and efficient knowledge access characterizing future real-life artificial intelligence applications represent crucial requirements for on-board artificial intelligence systems due to obvious computer time and storage constraints on spacecraft. A type of knowledge representation and corresponding reasoning mechanism is proposed which is particularly suited for the efficient processing of such large knowledge bases in expert systems.

Kellner, A.↗
NASA NTRS1988

A flexible on-board demultiplexer/demodulator

Optimization of satellite communications system performance from the point of view of reduced overall system cost per unit of service delivered, requires that economies be exercised at all levels. Introduction of onboard regeneration which necessarily involves on-board demultiplexing and demodulation is an essential ingredient in meeting this goal. To achieve maximum benefit from this approach, the uplink transmission data rate and bandwidth from each earth terminal and consequently uplink EIRP needs to be minimized. This necessarily introduces multiple carriers of different bandwidths on the uplinks and creates an attending need onboard for simultaneous demodulation of many carriers. This paper addresses a digitally implemented bulk demultiplexer/demodulator that processes a large number of carriers having differing carrier bandwidths, bit rates and center rrequencies. The device is programmable from the ground to accommodate changes in the complexion of the carriers.

Campanella, S. Joseph↗
NASA NTRS1989

Removing Bonded Integrated Circuits From Boards

Small resistance heater makes it easier, faster, and cheaper to remove integrated circuit from hybrid-circuit board, package, or other substrate for rework. Heater, located directly in polymeric bond interface or on substrate under integrated-circuit chip, energized when necessary to remove chip. Heat generated softens adhesive or solder that bonds chip to substrate. Chip then lifted easily from substrate.

Rice, John T.↗
NASA NTRS1989

On-board data analysis techniques for space plasma particle instruments

This article describes the on-board data analysis techniques used on two recent space plasma particle instruments to compute meaningful parameters of three-dimensional plasma distributions in real time. These parameters may be transmitted with much higher time resolution than the full distribution within the limited telemetry. In addition, they greatly reduce the ground processing requirements.

Curtis, D. W.↗
NASA NTRS1989

On-board attitude determination for the Topex satellite

This paper presents an overall technical description of the on-board attitude determination system for The Ocean Topography Experiment (Topex) satellite. The stellar-inertial attitude determination system being designed for the Topex satellite utilizes data from a three-axis NASA Standard DRIRU-II as well as data from an Advanced Star Tracer (ASTRA) and a Digital Fine Sun Sensor (DFSS). This system is a modified version of the baseline Multimission Modular Spacecraft (MMS) concept used on the Landsat missions. Extensive simulation and analysis of the MMS attitude determination approach was performed to verify suitability for the Topex application. The modifications to this baseline attitude determination scheme were identified to satisfy the unique Topex mission requirements.

Dennehy, C. J.↗