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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 181 records · Page 10
All sourcesNASA NTRSDOE OSTI
NASA NTRS1981

Fourier spectroscopy on planetary missions including Voyager

In the last dozen years spaceborne Fourier transform spectrometers have obtained infrared emission spectra of Earth, Mars, Jupiter, Saturn and Titan as well as of the Galilean and other Saturnian satellites and Saturn's rings. Intercomparisons of the properties of planetary atmospheres and of the characteristics of solid surfaces are now feasible. The principles of remotely sensing the environment on a planetary body are dicussed. Special consideration is given to the most recent results obtained by the Voyager infrared investigation on the Saturn system.

Hanel, R. A.↗
NASA NTRS1976

Planetary mission planning for the next decade

This paper reflects NASA's philosophy in the further exploration of the solar system. The philosophy entails the continuing reconnaissance of unexplored bodies in the solar system, while at the same time performing in-depth science investigations with respect to those bodies where the major science issues can be annunciated. The tactic in implementing this strategy will of necessity vary from year to year as a consequence of the varying budget restraints imposed on planetary exploration. However, the strategy will yield the greatest increment of knowledge in a given time frame.

Herman, D. H.↗
NASA NTRS1977

Quasi-microscope concept for planetary missions

Viking lander cameras have returned stereo and multispectral views of the Martian surface with a resolution that approaches 2 mm/lp in the near field. A two-orders-of-magnitude increase in resolution could be obtained for collected surface samples by augmenting these cameras with auxiliary optics that would neither impose special camera design requirements nor limit the cameras field of view of the terrain. Quasi-microscope images would provide valuable data on the physical and chemical characteristics of planetary regoliths.

Huck, F. O.↗
NASA NTRS2009

A Simulation Study of Multi-Beam Altimetry for Lunar Reconnaissance Orbiter and Other Planetary Missions

The combined use of altimetry, Earth-based Doppler and Earth-based range measurements in the lunar reconnaissance orbiter (LRO) mission (Chin et al. in Space Sci Rev 129:391-419, 2007) has been examined in a simulation study. It is found that in the initial phases of the mission orbit and altimeter geolocation accuracies should be better than 10m in the radial component and 60m overall. It is demonstrated that LRO's precise 1-way laser range measurement from Earth-based stations (Smith et al. in Proceedings of the 15th International Laser Ranging Workshop, Canberra, Australia, October 15-20, 2006) will be useful for gravity recovery. The advantages of multiple laser beams are demonstrated for altimeter calibration, orbit determination and gravity recovery in general planetary settings as well as for LRO.

Rowlands, D. D.↗
NASA NTRS2012

MgB2 Thin-Film Bolometer for Applications in Far-Infrared Instruments on Future Planetary Missions

A SiN membrane based MgB2 thin-film bolometer, with a non-optimized absorber, has been fabricated that shows an electrical noise equivalent power of 256 fW/square root Hz operating at 30 Hz in the 8.5 - 12.35 micron spectral bandpass. This value corresponds to an electrical specific detectivity of 7.6 x 10(exp 10) cm square root Hz/W. The bolometer shows a measured blackbody (optical) specific detectivity of 8.8 x 10(exp 9) cm square root Hz/W, with a responsivity of 701.5 kV/W and a first-order time constant of 5.2 ms. It is predicted that with the inclusion of a gold black absorber that a blackbody specific detectivity of 6.4 x 10(exp 10) cm/square root Hz/W at an operational frequency of 10 Hz, can be realized for integration into future planetary exploration instrumentation where high sensitivity is required in the 17 - 250 micron spectral wavelength range.

Lakew, B.↗
NASA NTRS2012

Compact Two-step Laser Time-of-Flight Mass Spectrometer for in Situ Analyses of Aromatic Organics on Planetary Missions

RATIONALE A miniature time-of-flight mass spectrometer has been adapted to demonstrate two-step laser desorption-ionization (LOI) in a compact instrument package for enhanced organics detection. Two-step LDI decouples the desorption and ionization processes, relative to traditional laser ionization-desorption, in order to produce low-fragmentation conditions for complex organic analytes. Tuning UV ionization laser energy allowed control ofthe degree of fragmentation, which may enable better identification of constituent species. METHODS A reflectron time-of-flight mass spectrometer prototype measuring 20 cm in length was adapted to a two-laser configuration, with IR (1064 nm) desorption followed by UV (266 nm) postionization. A relatively low ion extraction voltage of 5 kV was applied at the sample inlet. Instrument capabilities and performance were demonstrated with analysis of a model polycyclic aromatic hydrocarbon, representing a class of compounds important to the fields of Earth and planetary science. RESULTS L2MS analysis of a model PAH standard, pyrene, has been demonstrated, including parent mass identification and the onset o(tunable fragmentation as a function of ionizing laser energy. Mass resolution m/llm = 380 at full width at half-maximum was achieved which is notable for gas-phase ionization of desorbed neutrals in a highly-compact mass analyzer. CONCLUSIONS Achieving two-step laser mass spectrometry (L2MS) in a highly-miniature instrument enables a powerful approach to the detection and characterization of aromatic organics in remote terrestrial and planetary applications. Tunable detection of parent and fragment ions with high mass resolution, diagnostic of molecular structure, is possible on such a compact L2MS instrument. Selectivity of L2MS against low-mass inorganic salt interferences is a key advantage when working with unprocessed, natural samples, and a mechanism for the observed selectivity is presented.

Getty, Stephanie↗
NASA NTRSDate not supplied

Restricted by A Historical Review of Strategies and Organization for Restricted Earth Return of Samples from NASA Planetary Missions

Return of samples from the Moon via the Apollo 11, 12 and 14 missions represented NASA's first attempts into conducting what is now known as Restricted Earth Return. When Apollo returned samples from the moon, there were few of the agencies, legal and organizational structures that exist now. A half a century later, the U.S system has seen changes in legal and organizational structures with the appearance of different agencies and legal requirements. During the Apollo era, U.S. legal and organizational structures, assessed threats to the Earth’s biosphere with a priority towards the risks of effects from extraterrestrial pathogens on humans, though the guiding document, the Baylor Protocol, also considered animal and plant models. This presentation focuses on a review of two main questions: Did the return of samples from the Moon happen at a “sweet spot” in time, where the number of requirements and conservatism was commensurate with the scientific knowns and unknowns? Could the emphasis of risk mitigation on human pathogens during the return of extraterrestrial samples be more about human solipsism, leaving us with a blind spot to sources of pathogens, such as fungi, which could lead to an impact to our biosphere, and we humans, via our food chains and agricultural pathways?

planetary protection↗
NASA NTRS1971

Support requirements for remote sensor systems on unmanned planetary missions. Appendix A: Support requirement summary tables, phase 3

An appendix containing one page summary tables of sensor observation objectives, measurement capabilities, support requirments, and worth values is presented. Tables are arranged according to (1) sensor type number, (2) flyby mission number, (3) for multi-planet missions, in order of increasing distance from the sun, (4) for orbiter mission, by planets in order of increasing distance from the sun, and (5) by orbit number.

Source record↗
NASA NTRS1971

Stagnation region heating of a phenolic-nylon ablator during return from planetary missions

The results of a stagnation-line analysis of the radiative heating of a phenolic-nylon ablator are reported. The analysis includes flowfield coupling with the ablator surface, equilibrium chemistry, multicomponent or binary diffusion and a coupled line and continuum radiation calculations. Users manual and operating instructions for the computer programs listed in the report are included.

Esch, D. D.↗
NASA NTRS1972

Planetary mission handbook. Appendix A: Graphical trajectory data

Graphical data is presented for Type 1 ballistic transfers to Jupiter (1974 to 1986), Saturn (1976 to 1986) and Uranus (1985). There are four graphs for each launch opportunity, namely the hyperbolic excess speed at earth departure, the hyperbolic excess speed at planet arrival, the declination of the hyperbolic departure asymptote, and the declination of the hyperbolic approach asymptote.

Source record↗
NASA NTRS1972

Planetary missions handbook, first edition

A consistent source of payload performance data for missions to the outer planets is provided. The payload data for both flybys and orbiters is presented graphically as a function of flight time for various launch years, launch vehicles, and orbit sizes. All the relevant parameters have been combined to produce useful data on a single graph to make advanced mission planning much easier. The limitation of this mode of presentation is that only a reasonable number of payload vs. flight time curves can be drawn. Thus it is necessary to select parameters carefully to reflect frequently used values.

Source record↗
NASA NTRS1972

Sealed silver oxide zinc cells for orbiting and planetary missions.

Several test programs were carried out to determine the performance and limitations of sealed, silver oxide zinc cells for (1) 24-hr synchronous orbits, (2) orbits that would require a maximum of six cycles per day, and (3) missions to other planets requiring maintenance of maximum capacity for probe operations during planet encounter. The results are summarized to provide power system designers with guidelines bearing on capacity maintenance during cycling, cycle life, charged stand effects, and internal pressure characteristics. The life of zinc silver oxide cells is shown to be limited to one to two years over the temperature range of 0 to 24 C.

Hennigan, T. J.↗