Interplanetary monitoring platform, imp i - explorer xviii second interim status report
Performance summary of IMP-1 - instrumentation power supply, telemetry, and thermal systems
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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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Wireless power-receiving assembly for a telemetry system in a high-temperature environment of a combustion turbine engine
In a telemetry system (100) in a high-temperature environment of a combustion turbine engine (10), a wireless power-receiving coil assembly (116) may be affixed to a movable component (104) of the turbine engine. Power-receiving coil assembly (116) may include a radio-frequency transparent housing (130) having an opening (132). A lid (134) may be provided to close the opening of the housing. Lid (134) may be positioned to provide support against a surface (120) of the movable component. An induction coil (133) is disposed in the housing distally away from the lid and encased between a first layer (136) and a last layer (140) of a potting adhesive. Lid (134) is arranged to provide vibrational buffering between the surface (120) of the movable component (104) and the layers encasing the induction coil.
33 ADVANCED PROPULSION SYSTEMS↗
Implementation and Initial Validation of a 100-Kilowatt Class Nested-Channel Hall Thruster
The X3 is a 100-kilowatt class nested-channel Hall thruster developed by the Plasmadynamics and Electric Propulsion Laboratory at the University of Michigan in collaboration with the Air Force Research Laboratory and NASA. The cathode, magnetic circuit, boron nitride channel rings, and anodes all required specific design considerations during thruster development, and thermal modeling was used to properly account for thermal growth in material selection and component design. A number of facility upgrades were required at the University of Michigan to facilitate operation of the X3. These upgrades included a re-worked propellant feed system, a completely redesigned power and telemetry break-out box, and numerous updates to thruster handling equipment. The X3 was tested on xenon propellant at two current densities, 37% and 73% of the nominal design value. It was operated to a maximum steady-state discharge power of 60.8 kilowatts. The tests presented here served as an initial validation of thruster operation. Thruster behavior was monitored with telemetry, photography and high-speed current probes. The photography showed a uniform plume throughout testing. At constant current density, reductions in mass flow rate of 18% and 26% were observed in the three-channel operating configuration as compared to the superposition of each channel running individually. The high-speed current probes showed that the thruster was stable at all operating points and that the channels influence each other when more than one is operating simultaneously. Additionally, the ratio of peak-to-peak AC-coupled discharge current oscillations to mean discharge current did not exceed 51% for any operating points reported here, and did not exceed 17% at the higher current density.
High Power↗
Effect of RF Filtering on the Performance of Uncoded PCM/PM Telemetry Channels
A method for calculating the increase in received telemetry signal power required to compensate for the use of a radio frequency interference (RFI) filter in front of the DSN receiving system low-noise amplifier is described. The telemetry system for which the degradation is calculated is an uncoded PCM/PM system in which the NRZ data directly modulates the carrier at a modulation level which leaves a discrete carrier. A phase-locked loop in the RF receiver tracks the discrete carrier and coherently demodulates the PCM data. The RFI filter may be a series of Butterworth, Tchebychev, or Bessel low-pass, high-pass, band-pass, or band-reject filters, each with arbitrary bandwidth, number of poles, and, for band-pass or band-reject filters, resonant frequency. The only restriction is that the RFI filter must have only simple poles. Numerical results are presented for the RFI filters the DSN plans to place in front of the S-band FET, S-band maser, and X-band maser low noise amplifiers. The main conclusion is that the filters will produce negligible degradation at data rates below 4 Mbps.
Koerner, M. A.↗
Fault Diagnosis of Power Systems Using Intelligent Systems
The power system operator's need for a reliable power delivery system calls for a real-time or near-real-time Al-based fault diagnosis tool. Such a tool will allow NASA ground controllers to re-establish a normal or near-normal degraded operating state of the EPS (a DC power system) for Space Station Alpha by isolating the faulted branches and loads of the system. And after isolation, re-energizing those branches and loads that have been found not to have any faults in them. A proposed solution involves using the Fault Diagnosis Intelligent System (FDIS) to perform near-real time fault diagnosis of Alpha's EPS by downloading power transient telemetry at fault-time from onboard data loggers. The FDIS uses an ANN clustering algorithm augmented with a wavelet transform feature extractor. This combination enables this system to perform pattern recognition of the power transient signatures to diagnose the fault type and its location down to the orbital replaceable unit. FDIS has been tested using a simulation of the LeRC Testbed Space Station Freedom configuration including the topology from the DDCU's to the electrical loads attached to the TPDU's. FDIS will work in conjunction with the Power Management Load Scheduler to determine what the state of the system was at the time of the fault condition. This information is used to activate the appropriate diagnostic section, and to refine if necessary the solution obtained. In the latter case, if the FDIS reports back that it is equally likely that the faulty device as 'start tracker #1' and 'time generation unit,' then based on a priori knowledge of the system's state, the refined solution would be 'star tracker #1' located in cabinet ITAS2. It is concluded from the present studies that artificial intelligence diagnostic abilities are improved with the addition of the wavelet transform, and that when such a system such as FDIS is coupled to the Power Management Load Scheduler, a faulty device can be located and isolated from the rest of the system. The benefit of these studies provides NASA with the ability to quickly restore the operating status of a space station from a critical state to a safe degraded mode, thereby saving costs in experimentation rescheduling, fault diagnostics, and prevention of loss-of-life.
Momoh, James A.↗
AI-enabled, implantable, multichannel wireless telemetry for photodynamic therapy
Photodynamic therapy (PDT) offers several advantages for treating cancers, but its efficacy is highly dependent on light delivery to activate a photosensitizer. Advances in wireless technologies enable remote delivery of light to tumors, but suffer from key limitations, including low levels of tissue penetration and photosensitizer activation. Here, we introduce DeepLabCut (DLC)-informed low-power wireless telemetry with an integrated thermal/light simulation platform that overcomes the above constraints. The simulator produces an optimized combination of wavelengths and light sources, and DLC-assisted wireless telemetry uses the parameters from the simulator to enable adequate illumination of tumors through high-throughput (<20 mice) and multi-wavelength operation. Together, they establish a range of guidelines for effective PDT regimen design. In vivo Hypericin and Foscan mediated PDT, using cancer xenograft models, demonstrates substantial suppression of tumor growth, warranting further investigation in research and/or clinical settings.
60 APPLIED LIFE SCIENCES↗
Prototype Software for Future Spaceflight Tested at Mars Desert Research Station
NASA scientists in MDRS Crew 49 (April 23-May 7, 2006) field tested and significantly extended a prototype monitoring and advising system that integrates power system telemetry with a voice commanding interface. A distributed, wireless network of functionally specialized agents interacted with the crew to provide alerts (e.g., impending shut-down of inverter due to low battery voltage), access md interpret historical data, and display troubleshooting procedures. In practical application during two weeks, the system generated speech over loudspeakers and headsets lo alert the crew about the need to investigate power system problems. The prototype system adapts the Brahms/Mobile Agents toolkit to receive data from the OneMeter (Brand Electronics) electric metering system deployed by Crew 47. A computer on the upper deck was connected to loudspeakers, four others were paired with wireless (Bluetooth) headsets that enabled crew members to interact with their personal agents from anywhere in the hab. Voice commands and inquiries included: 1. What is the {battery | generator} {volts | amps | volts and amps}? 2. What is the status of the {generator | inverter | battery | solar panel}? 3. What is the hab{itat} {power usage | volts | voltage | amps | volts and amps}? 4. What was the average hab{itat} {amps | volts | voltage} since <#> {AM | PM)? 5. When did the {generator | batteries} change status? 6. Tell {me I | everyone} when{ ever} the generator goes offline. 7. Tell {me | | everyone} when the hab{itat} {amps | volts | voltage} {exceeds | drops brelow} <#>. 8. {Send | Take | Record} {a} voice note {(for | to} } {at }. This research demonstrates the principles of design in the context of use, investigating requirements through experimental use of prototype systems in an analog setting, and use of MDRS as a research facility for designing and implementing new systems.
Clancey, William J.↗
The Relay spacecraft
Structure, power, communications, telemetry, tracking, and command for Relay I spacecraft
COMMAND SYSTEM↗
The Small Astronomy Satellite /SAS/ program.
Small astronomy satellite /SAS/ design, power, command, telemetry and control systems
Townsend, M. R.↗
Television Broadcast Satellite study, TVBS system. Volume 4 - Appendices
Power conditioning, telemetry and command, cost of up-link ground terminal, and up-link receiver for television broadcast satellite system - Vol. 4
Source record↗
Two early missions to the comets.
Early missions to the comets Grigg-Skjellerup in 1977 and Encke in 1980 are suggested as precursors to more ambitious missions to Encke rendezvous in 1984 and Halley intercept in 1986. The spacecraft structures, power systems, telemetry, configurations, and launch vehicles considered appropriate for these two missions are actual equipments ready for applications. The mission objectives would be exploration of the nature of the solar wind interaction with comets, the composition of the gaseous cometary atmosphere, and possibly the details of the trailing portion of a comet (ion and dust tails).
Farquhar, R. W.↗
Telemetry link for an automatic salmon migration monitor
The antenna and transmitter described in this report were designed for integration into the remote acoustic assessment system for detection of sockeye salmon in the Bristol Bay region of the Bering Sea. The assessment system configuration consists of an upward directed sonar buoy anchored 150 ft below the surface and attached by cable to a spar buoy tethered some 300 ft laterally. The spar buoy contains a telemetry transmitter, power supply, data processing electronics, an antenna and a beacon light.
Baldwin, H. A.↗
Microelectronic bioinstrumentation system
The progess made from April 1973 to June 1974 on a microelectronics bioinstrumentation system is reported and includes data for the following three individual projects: (1) a radio frequency powered implant telemetry system; (2) an ingestible temperature telemeter; and (3) development of pO2 and pH sensors. Proposed activities for continuation of the research for the period September 1, 1974 to August 31, 1975 are also discussed.
Ko, W. H.↗
Control and telemetry transducer requirements for nuclear powered vehicles
Explore the source record for details and available documents.
Johnson, M. C.↗
Science on Spacelab
Spacelab was developed by the European Space Agency for the conduction of scientific and technological experiments in space. Spacelab can be taken into earth orbit by the Space Shuttle and returned to earth after a period of 1-3 weeks. The Spacelab modular system of pallets, pressurized modules, and racks can contain large payloads with high power and telemetry requirements. A working group has defined the 'Atmospheres, Magnetospheres, and Plasmas-in-Space' project. The project objectives include the absolute measurement of solar flux in a number of carefully selected bands at the same time at which atmospheric measurements are made. NASA is committed to the concept that the scientist is to play a key role in its scientific programs.
Schmerling, E. R.↗
Design of a Solar Sail Mission to Mars
An evaluation of the design of the solar sail includes key areas such as structures, sail deployment, space environmental effects, materials, power systems, telemetry, communications, attitude control, thermal control, and trajectory analysis. Deployment and material constraints determine the basic structure of the sail, while the trajectory of the sail influences the choice of telemetry, communications, and attitude control systems. The thermal control system of the sail for the structures and electronics takes into account the effects of the space environment. Included also are a cost and weight estimate for the sail.
Eastridge, Richard↗
High-Latitude Communications Satellite (HILACS)
The Naval Postgraduate School in the AE 4871 Advanced Spacecraft Design course designed a communications satellite (HILACS) that will provide a continuous UHF communications link between stations located north of the region covered by geosynchronous communications satellites. The communications payload will operate only for that portion of the orbit necessary to provide specific coverage. The satellite orbit is elliptic with perigee at 1204 km in the Southern Hemisphere and an apogee at 14,930 km with 63.4 degrees inclination. Analysis and design of each of the subsystems was done to the extent possible within the constraints of an eleven week quarter and the design and analysis tools available. Work was completed in orbital analysis, the reaction control system, attitude control subsystem, electric power subsystem, telemetry, tracking, and control, thermal control subsystem, and the structures subsystem. The design team consisted of 12 students. Additional support was provided by the Jet Propulsion Laboratory and the Naval Research Laboratory.
Source record↗
The Inner Magnetospheric Imager (IMI): Instrument heritage and orbit viewing analysis
For the last two years an engineering team in the Program Development Office at MSFC has been doing design studies for the proposed Inner Magnetospheric Imager (IMI) mission. This team had a need for more information about the instruments that this mission would carry so that they could get a better handle on instrument volume, mass, power, and telemetry needs as well as information to help assess the possible cost of such instruments and what technology development they would need. To get this information, an extensive literature search was conducted as well as interviews with several members of the IMI science working group. The results of this heritage survey are summarized below. There was also a need to evaluate the orbits proposed for this mission from the stand point of their suitability for viewing the various magnetospheric features that are planned for this mission. This was accomplished by first, identifying the factors which need to be considered in selecting an orbit, second, translating these considerations into specific criteria, and third, evaluating the proposed orbits against these criteria. The specifics of these criteria and the results of the orbit analysis are contained in the last section of this report.
Wilson, Gordon R.↗