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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 73 records · Page 4
All sourcesNASA NTRSDOE OSTI
NASA NTRS2004

Mechanical Design of a Performance Test Rig for the Turbine Air-Flow Task (TAFT)

To support development of the Boeing-Rocketdyne RS84 rocket engine, a full-flow, reaction turbine geometry was integrated into the NASA-MSFC turbine air-flow test facility. A mechanical design was generated which minimized the amount of new hardware while incorporating all test and instrumentation requirements. This paper provides details of the mechanical design for this Turbine Air-Flow Task (TAFT) test rig. The mechanical design process utilized for this task included the following basic stages: Conceptual Design. Preliminary Design. Detailed Design. Baseline of Design (including Configuration Control and Drawing Revision). Fabrication. Assembly. During the design process, many lessons were learned that should benefit future test rig design projects. Of primary importance are well-defined requirements early in the design process, a thorough detailed design package, and effective communication with both the customer and the fabrication contractors.

Forbes, John C.↗
NASA NTRS2004

Modeling of a Variable Focal Length Flat Lens Using Left Handed Metamaterials

Left Handed Metamaterials (LHM) were originally purposed by Victor Veselago in1968. These substances would allow a flat structure to focus electromagnetic (EM) waves because they have a negative index of refraction. A similar structure made from conventional materials, those with a positive index of refraction, would disperse the waves. But until recently, these structures have been purely theoretical because substances with both a negative permittivity and negative permeability, material properties necessary for a negative index of refraction, do not naturally exist, Recent developments have produced a structure composed of an array of thin wires and split ring resonators that shows a negative index of refraction. area smaller than a square wavelength. How small the area is can be determined by how perfectly the lens is polished and how pure the substance is that composes the lens. These lenses must also be curved for focusing to occur. The focal length is determined by the curvature of the lens and the material. On the other hand, a flat structure made from LHM would focus light because of the effect of a negative index of refraction in Snell s law. The focal length could also be varied by simply adjusting the distance of the lens from the source of radiation. This could create many devices that are adjustable to different situations in fields such as biomedical imaging and communication. the software package XFDTD which solves Maxwell s equations in the frequency domain as well as the time domain. The program used Drude models of materials to simulate the effect of negative permittivity and negative permeability. Because of this, a LHM can be simulated as a solid block of material instead of an array of wires and split ring resonators. After a flat lens is formed, I am to examine the focusing effect of the lens and determine if a higher resolution flat lens can be developed. Traditional lenses made from conventional materials cannot focus an EM wave onto an My goal was to model LHMs and create a flat lens from them. This was to be done using

Reinert, Jason↗
NASA NTRS2019

Space Communications and Navigation (SCaN) Tool Capabilities Updates for Antenna Pattern and Jitter

The ability to accurately simulate the dynamic misalignment of pointing across a communications link is critical to determining the link performance between/across spacecraft and/or ground stations. The communication system antenna pattern and dynamic misalignment are key components to understanding the pointing loss induced on the communications link. Currently, projects performing these analyses use a variety of simulation tools and packages. NASA's Space Communications and Navigation (SCaN) office aims to provide a unified tool set for these functions. However, the analysis tool to calculate antenna patterns is currently static, two-dimensional, and approximated based on limited input. Steps were taken to change the inputs used by the tool to create a more accurate approximation of the antenna's far field pattern as well as create a three-dimensional pattern. An additional tool was also developed to calculate time-dynamic pointing loss from the antenna pattern generated or observed antenna pattern data given dynamic pointing errors.

SCaN↗
NASA NTRS1983

User manual of the CATSS system (version 1.0) communication analysis tool for space station

The Communication Analysis Tool for the Space Station (CATSS) is a FORTRAN language software package capable of predicting the communications links performance for the Space Station (SS) communication and tracking (C & T) system. An interactive software package was currently developed to run on the DEC/VAX computers. The CATSS models and evaluates the various C & T links of the SS, which includes the modulation schemes such as Binary-Phase-Shift-Keying (BPSK), BPSK with Direct Sequence Spread Spectrum (PN/BPSK), and M-ary Frequency-Shift-Keying with Frequency Hopping (FH/MFSK). Optical Space Communication link is also included. CATSS is a C & T system engineering tool used to predict and analyze the system performance for different link environment. Identification of system weaknesses is achieved through evaluation of performance with varying system parameters. System tradeoff for different values of system parameters are made based on the performance prediction.

Tsang, C. S.↗
NASA NTRSDate not supplied

Design Considerations for Aerocapture Delivery of Uranus Orbiter and Probe

This paper presents an aerocapture system design for delivering the Uranus Orbiter and Probe (UOP) subsystems to their science orbit using the Mars Science Laboratory architecture. A packaging and integration scheme are presented for UOP subsystems, with careful consideration of large components required for outer planet science missions (RTG power generation, RF communications). The implication of packaging multiple RTG’s inside an aeroshell during a multiple year cruise phase will be explained, with possible thermal design solutions to mitigate RTG waste heat analyzed. Mass properties and margins for the system are discussed and an overall mass risk assessment is presented for the entry system and total flight system at launch. Alternative vehicle configurations are explored to include multiple probes and enable science objectives during transit to Uranus. Aerocapture mass savings when compared to the baseline UOP design are presented.

Andrew J. Gomez-Delrio↗
NASA NTRSDate not supplied

Design Considerations for Aerocapture Delivery of Uranus Orbiter and Probe

This paper presents an aerocapture system design for delivering the Uranus Orbiter and Probe (UOP) subsystems to their science orbit using the Mars Science Laboratory architecture. A packaging and integration scheme are presented for UOP subsystems, with careful consideration of large components required for outer planet science missions (RTG power generation, RF communications). The implication of packaging multiple RTG’s inside an aeroshell during a multiple year cruise phase will be explained, with possible thermal design solutions to mitigate RTG waste heat analyzed. Mass properties and margins for the system are discussed and an overall mass risk assessment is presented for the entry system and total flight system at launch. Alternative vehicle configurations are explored to include multiple probes and enable science objectives during transit to Uranus. Aerocapture mass savings when compared to the baseline UOP design are presented.

Aerocapture↗
NASA NTRS1972

Integration of safety engineering into a cost optimized development program.

A six-segment management model is presented, each segment of which represents a major area in a new product development program. The first segment of the model covers integration of specialist engineers into 'systems requirement definition' or the system engineering documentation process. The second covers preparation of five basic types of 'development program plans.' The third segment covers integration of system requirements, scheduling, and funding of specialist engineering activities into 'work breakdown structures,' 'cost accounts,' and 'work packages.' The fourth covers 'requirement communication' by line organizations. The fifth covers 'performance measurement' based on work package data. The sixth covers 'baseline requirements achievement tracking.'

Ball, L. W.↗
NASA NTRS1986

Switches, lasers and electronically-hopped beam antennas in space - NASA's advanced communications technology satellite

The proposed design and operation of the Advanced Communications Technology Satellite (ACTS) are described. The ACTS is a three-axis stabilized spacecraft with an in-orbit weight of 2300 lbs and a beginning-of-life power of 1770 W; it is composed of a 20 GHz 2.2 m downlink antenna, a 30 GHz 3.3 m uplink antenna, a 1 m steerable antenna, and a laser package. The space segment communications payload uses high and low burst rate modes; the operations of these modes are discussed. The components of the laser intersatellite link instrument package are examined. Consideration is given to the ACTS's antennas, RF matrix switch system, and the base band processor. Diagrams of the ACTs systems are presented.

Lovell, Robert R.↗
NASA NTRS1976

Space shuttle Ku-band integrated rendezvous radar/communications system study

The results are presented of work performed on the Space Shuttle Ku-Band Integrated Rendezvous Radar/Communications System Study. The recommendations and conclusions are included as well as the details explaining the results. The requirements upon which the study was based are presented along with the predicted performance of the recommended system configuration. In addition, shuttle orbiter vehicle constraints (e.g., size, weight, power, stowage space) are discussed. The tradeoffs considered and the operation of the recommended configuration are described for an optimized, integrated Ku-band radar/communications system. Basic system tradeoffs, communication design, radar design, antenna tradeoffs, antenna gimbal and drive design, antenna servo design, and deployed assembly packaging design are discussed. The communications and radar performance analyses necessary to support the system design effort are presented. Detailed derivations of the communications thermal noise error, the radar range, range rate, and angle tracking errors, and the communications transmitter distortion parameter effect on crosstalk between the unbalanced quadriphase signals are included.

Source record↗
NASA NTRS1985

Modeling techniques used in the communications link analysis and simulation system (CLASS)

CLASS (Communications Link Analysis and Simulation System) is a software package developed for NASA to predict the communication and tracking performance of the Tracking and Data Relay Satellite System (TDRSS) services. The modeling techniques used in CLASS are described. The components of TDRSS and the performance parameters to be computed by CLASS are too diverse to permit the use of a single technique to evaluate all performance measures. Hence, each CLASS module applies the modeling approach best suited for a particular subsystem and/or performance parameter in terms of model accuracy and computational speed.

Braun, W. R.↗
NASA NTRS1985

Validation of the communications link analysis and simulation system (CLASS)

CLASS (Communication Link Analysis and Simulation System) is a software package developed for NASA to predict the communication and tracking performance of the Tracking and Data Relay Satellite System (TDRSS) services. The methods used to verify CLASS are described. The usefulness of a software tool such as CLASS depends strongly on the reliability and accuracy of the results it produces. For this reason, considerable attention was paid to validation throughout the CLASS development.

Braun, W. R.↗
NASA NTRS1986

NASA 60 GHz intersatellite communication link definition study. Baseline document

The overall system and component concepts for a 60 GHz intersatellite communications link system (ICLS) are described. The ICLS was designed to augment the capabilities of the current Tracking and Data Relay Satellite System (TDRSS), providing a data rate capacity large enough to accommodate the expected rates for user satellites (USAT's) in the post-1995 timeframe. The use of 60 GHz for the anticipated successor to TDRSS, the Tracking and Data Acquisition System (TDAS), was selected because of current technology development that will enable multigigibit data rates. Additionally, the attenuation of the earth's atmosphere at 60 GHz means that there is virtually no possibility of terrestrially generated interference (intentional or accidental) or terrestrially based intercept. The ICLS includes the following functional areas: (1) the ICLS payload package on the GEO TDAS satellite that communicates simultaneously with up to five LEO USAT's; (2) the payload package on the USAT that communicates with the TDAS satellite; and (3) the crosslink payload package on the TDAS satellite that communicates with another TDAS satellite. Two methods of data relay on-board the TDAS spacecraft were addressed. One is a complete baseband system (demod and remod) with a bi-directional 2 Gbps data stream; the other is a channelized system wherein some of the channels are baseband and others are merely frequency translated before re-transmission. Descriptions of the TDAS antenna, transmitter, receiver, and mechanical designs are presented.

Source record↗
NASA NTRS2009

Robust Short-Pulse, High-Peak-Power Laser Transmitter for Optical Communications

We report on a pulsed fiber based master oscillator power amplifier laser at 1550 nm to support moderate data rates with high peak powers in a compact package suitable for interplanetary optical communications. To accommodate pulse position modulation, the polarization maintaining laser transmitter generates pulses from 0.1 to 1 ns with variable duty cycle over a pulse repetition frequency range of 10 to 100 MHz.

fiber amplifier↗
NASA NTRS1977

On-orbit performance of the 12 GHz, 200 watt transmitter experiment package for CTS

Performance characteristics from on-orbit tests of the transmitter experiment package (TEP) for the Communications Technology Satellite (CTS) are presented. The TEP consists of a power processing system (PPS), an output stage tube (OST) and a variable conductance heat pipe system (VCHPS), all of which are described. Test results presented include efficiencies, RF output power, frequency response, and performance with single and multiple (two) carriers, frequency-modulated by video signals.

Alexovich, R. E.↗
NASA NTRS1977

On-orbit performance of the 12 GHz, 200 watt transmitter experiment package for CTS

Performance characteristics from on-orbit tests of the Transmitter Experiment Package (TEP) for the Communications Technology Satellite (CTS) are presented. The TEP consists of a Power Processing System (PPS), an Output Stage Tube (OST), and a Variable Conductance Heat Pipe System (VCHPS), all of which are described. The OST is a coupled-cavity traveling-wave tube with a multistage depressed collector and a stepped velocity-tapered slow-wave structure for efficiency enhancement. It has an RF output power of 240 W and an overall efficiency of 51.5% at a center band frequency of 12.080 GHz. The PPS provides the required operating voltages, regulation, control, and protection for the OST. It has a measured dc-dc conversion efficiency of 86.5% to 88.5%. The VCHPS consists of a fin radiator and three dual-artery stainless steel heat pipes using methanol and a mixture of inert gases. Test results presented include efficiencies, RF output power, frequency response, and performance with single and multiple (two) carriers frequency-modulated by video signals.

Alexovich, R. E.↗
NASA NTRS1977

CTS TEP thermal anomalies: Heat pipe system performance

A part of the investigation is summarized of the thermal anomalies of the transmitter experiment package (TEP) on the Communications Technology Satellite (CTS) which were observed on four occasions in 1977. Specifically, the possible failure modes of the variable conductance heat pipe system (VCHPS) used for principal thermal control of the high-power traveling wave tube in the TEP are considered. Further, the investigation examines how those malfunctions may have given rise to the TEP thermal anomalies. Using CTS flight data information, ground test results, analysis conclusions, and other relevant information, the investigation concentrated on artery depriming as the most likely VCHPS failure mode. Included in the study as possible depriming mechanisms were freezing of the working fluid, Marangoni flow, and gas evolution within the arteries. The report concludes that while depriming of the heat pipe arteries is consistent with the bulk of the observed data, the factors which cause the arteries to deprime have yet to be identified.

Marcus, B. D.↗