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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 505 records · Page 28
All sourcesNASA NTRSDOE OSTI
NASA NTRS1986

Composition and stability of the condensate observed at the Viking Lander 2 site on Mars

Surface energy balance and near-surface temperature data from the Viking Lander 2 site taken during the first winter that condensated were observed and analyzed to determine the relative stability of CO2 and H2O frosts. The CO2 frost stability is calculated with an equilibrium surface energy balance model, i.e., the total energy incident on a frost surface is compared with the blackbody energy emitted by the surface. The energy sources considered were IR emission from the atmosphere, sunlight, and the sensible heat flux from the atmosphere. H2O stability was examined as a function of buoyant diffusion and turbulent mixing processes which could remove saturated near-surface gases. The CO2 frost is found to be sufficiently unstable at the time the condensate was observed on the ground, so all CO2 ice deposited at night would boil away in a few hours of sunlight. CO2 ice would not form during a dust storm. Water frost would be stable during the condensate observations, since sublimation would occur at a rate below 1 micron/day. A stable winter thickness of 10 microns is projected for the water ice.

Hart, H. M.↗
NASA NTRS1987

Viking Landers and remote sensing

Thermal and radar remote sensing signatures of the materials in the lander sample fields can be crudely estimated from evaluations of their physical-mechanical properties, laboratory data on thermal conductivities and dielectric constants, and theory. The estimated thermal inertias and dielectric constants of some of the materials in the sample field are close to modal values estimated from orbital and earth-based observations. This suggests that the mechanical properties of the surface materials of much of Mars will not be significantly different that those of the landing sites.

Moore, H. J.↗
NASA NTRS1987

Further information on structure of the atmosphere of Venus derived from the Vega Venus balloon and lander mission

Continued analysis of the pressure and temperature data returned by the two Vega mission balloons has revealed an apparently significant difference in mean atmospheric static stability between the two data sets. Furthermore, the stability is time dependent within each data set. The 6.5 K temperature contrast between the two balloons remains, and appears to have a counterpart in the contrast between two of the Pioneer Venus probes at these levels, which has been attributed to planetary scale waves. Comparisons of the Vega 2 lander data with those of the Pioneer Venus Large Probe shows relatively close agreement in the state properties and in the atmospheric static stability profiles as well.

Seiff, A.↗
NASA NTRS1988

Phobos lander coding system: Software and analysis

The software developed for the decoding system used in the telemetry link of the Phobos Lander mission is described. Encoders and decoders are provided to cover the three possible telemetry configurations. The software can be used to decode actual data or to simulate the performance of the telemetry system. The theoretical properties of the codes chosen for this mission are analyzed and discussed.

Cheung, K.-M.↗
NASA NTRS1989

Historical perspective - Viking Mars Lander propulsion

This paper discusses the Viking 1 and 2 missions to Mars in 1975-1976 and describes the design evolution of the Viking Terminal Descent Rocket Engines responsible for decelerating the Viking Mars Landers during the final portion of their descent from orbit. The Viking Terminal Descent Rocket Engines have twice the thrust of the largest monopropellant hydrazine engine developed previously but weigh considerably less. The engine has 18 nozzles, the capability of 10:1 throttling, is totally sealed until fired, employs no organic unsealed materials, is 100 percent germ free, utilized hydrazine STM-20 as the propellant, and starts at a temperature more than 45 F below the propellant's freezing point.

Morrisey, Donald C.↗
NASA NTRS1989

Icarus lander

Icarus is one of the earth-crossing asteroids. It has a semi-major axis of 1.078 AU, giving it a period of 1.12 years, and an eccentricity of 0.827. The perihelion distance is thus 0.187 AU. The inclination of Icarus's orbit is 23 deg. Although it is a small body, it is still massive enough to be essentially immune to non-gravitational forces. These orbital and physical qualities make it an attractive target for testing General Relativity. The close passage to the sun means that it will be subject to a large relativistic perihelion precession; the high eccentricity makes the precession easy to measure; the high inclination allows the solar quadrupole moment (J sub 2) to be simultaneously determined via the nodal precession it predicts. The degeneracy between the relativistic effect and the effect of J sub 2 in the perihelion precession may thus be broken. Results are presented from a preliminary study of a possible trajectory design for an Icarus lander and from a covariance study of the scientific return to be expected from such a mission.

Hellings, Ronald W.↗
NASA NTRS1990

Lunar Polar Coring Lander

Plans to build a lunar base are presently being studied with a number of considerations. One of the most important considerations is qualifying the presence of water on the Moon. The existence of water on the Moon implies that future lunar settlements may be able to use this resource to produce things such as drinking water and rocket fuel. Due to the very high cost of transporting these materials to the Moon, in situ production could save billions of dollars in operating costs of the lunar base. Scientists have suggested that the polar regions of the Moon may contain some amounts of water ice in the regolith. Six possible mission scenarios are suggested which would allow lunar polar soil samples to be collected for analysis. The options presented are: remote sensing satellite, two unmanned robotic lunar coring missions (one is a sample return and one is a data return only), two combined manned and robotic polar coring missions, and one fully manned core retrieval mission. One of the combined manned and robotic missions has been singled out for detailed analysis. This mission proposes sending at least three unmanned robotic landers to the lunar pole to take core samples as deep as 15 meters. Upon successful completion of the coring operations, a manned mission would be sent to retrieve the samples and perform extensive experiments of the polar region. Man's first step in returning to the Moon is recommended to investigate the issue of lunar polar water. The potential benefits of lunar water more than warrant sending either astronauts, robots or both to the Moon before any permanent facility is constructed.

Angell, David↗
NASA NTRS1990

Winter frost at Viking Lander 2 site

This paper presents quantitative evidence for cold trapping (frost redeposition) at the Viking Lander 2 site. This evidence consists of the frost surface coverage and color transition, the timing of this transition, and the limited vertical mixing and horizontal water transport. It is argued that cold trapping must be a general property of seasonal frost and, therefore, must be considered in order to understand the evolution of the surface environment of Mars.

Svitek, Thomas↗
NASA NTRS1990

Observations of Martian surface winds at the Viking Lander 1 site

Martian surface winds at the Viking Lander 1 have been reconstructed using signals from partially failed wind instrumentation. Winds during early summer were controlled by regional topography, and then underwent a transition to a regime controlled by the Hadley circulation. Diurnal wind oscillations were controlled primarily by regional topography and boundary layer forcing, although a global mode may have been influencing them during two brief episodes. Semidiurnal wind oscillations were controlled by the westward-propagating semidiurnal tide from sol 210 onward. Comparison of the synoptic variations at the two sites suggests that the same eastward propagating wave trains were present at both sites.

Murphy, James R.↗
NASA NTRS1991

Common Lunar Lander (CLL) Engineering Study Results

Information is given in viewgraph form on the Common Lunar Lander (CLL) engineering study results. The mission is to provide a delivery system to soft-land a 200 kg payload set at any given lunar latitude and longitude. Topics covered include the study schedule, mission goals and requirements, the CLL reference mission, costs, CLL options, and two stage performance analysis.

Stecklein, Jonette↗
NASA NTRS1991

Common Lunar Lander (CLL) trajectory analysis

Common Lunar Lander trajectory analysis is presented in viewgraph format. Trajectory requirements, trajectory characteristics, trajectory timeline, and alternate trajectory advantages and disadvantages are given.

Wagner, Lynn A., Jr.↗
NASA NTRS1991

Common Lunar Lander (CLL) Conceptual Design and Mass Properties

The conceptual design and mass properties are presented for the CLL in viewgraph format. The spacecraft structural mass is given for orbital assembly, thermal insulation, integrated propulsion, power generation, avionics, environment control, and pyrotechnics and landing system. The mass is given of the lander as well as the transfer stage.

Lawson, Shelby↗
NASA NTRS1991

Common Lunar Lander (CLL) Propulsion System

A description of the Common Lunar Lander (CLL) propulsion system is given. Among the topics discussed are the following: system characteristics, system mission requirements, key drivers to subsystem selection, system readiness level, and point design output. Additionally, a schematic of the system is provided.

Hyatt, Don↗
NASA NTRS1991

Tracking Systems to Support the Common Lunar Lander (CLL)

A discussion of the tracking system for Artemis (the Common Lunar Lander) is presented. Among the topics presented are the following: major drivers for system definition, results of vendor survey, baseline system properties, program considerations, and mission phases requiring tracking.

Culpepper, William X.↗
NASA NTRS1992

Simulations of surface winds at the Viking Lander sites using a one-level model

The one-level model developed by Mass and Dempsey for use in predicting surface flows in regions of complex terrain was adapted to simulate surface flows at the Viking lander sites on Mars. In the one-level model, prediction equations for surface winds and temperatures are formulated and solved. Surface temperatures change with time in response to diabatic heating, horizontal advection, adiabatic heating and cooling effects, and horizontal diffusion. Surface winds can change in response to horizontal advection, pressure gradient forces, Coriolis forces, surface drag, and horizontal diffusion. Surface pressures are determined by integration of the hydrostatic equation from the surface to some reference level. The model has successfully simulated surface flows under a variety of conditions in complex-terrain regions on Earth.

Bridger, Alison F. C.↗
NASA NTRS1991

Logistics impacts on lunar and Mars lander design

The results of trade studies and evaluations done to determine the impact of accommodation and unloading of cargo on spacecraft design are reviewed. It is concluded that the effectiveness of the surface mission to moon or Mars is best accomplished by providing for undivided cargo delivery and for cargo unloading indirectly to earth surface without the aid of a surface system unloader, for immediate cargo drop during descent abort to orbit, for immediate cargo drop in case of need for an emergency ascent from the surface, and for contiguous placement of cab and surface habitat modules. For exploration architectures that include multiple site visits within as much as several hundred km of each other, use of excursion vehicles capable of short suborbital hops to secondary sites is much less expensive in terms of IMLEO than a strategy of using multiple landers or multiple missions.

Donahue, Benjamin↗
NASA NTRS1991

Mars boundary layer simulations - Comparison with Viking lander and entry observations

Diurnal variations of wind and temperature in the lower Martian atmosphere are simulated with a boundary layer model that includes radiative heating in a dusty CO2 atmosphere, turbulence generated by convection and/or shear stresses, a surface heat budget, and time varying pressure forces due to sloping terrain. Model results for early northern summer are compared with Viking lander observations to determine the model's strengths and weaknesses, and suitability as an engineering model.

Haberle, R. M.↗
NASA NTRS1991

The design of a common lunar lander

The Austin Cynthesis Corporation was formed to respond to a Request for Proposal for the design of a Common Lunar Lander (CLL) capable of carrying lightweight (less than 500 kg), unspecified payload to the moon. This Final Design Report Document includes information on the requirements for the design project; the ideas proposed as solutions to the design problem; the work which has been completed in support of the design effort; justifications, validations, and verifications of decisions made during the project; and suggestions for future work to be done in support of the project. A project schedule, including current status of the items included on the schedule, as well as cost and management summaries is also included.

Driggers, Dan↗