A preliminary control net of Mars
Mars surface areodetic control net from Mariner 6 and 7 TV pictures, determining initial coordinate points and far and near encounter frames
Berg, R. A.↗
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Digital processing of the Mariner 6 and 7 pictures
Digital computer techniques for Mars surface imagery systematic video data distortions quantification and correction onboard Mariner 6 and 7
Dunne, J. A.↗
Selection of bands for multispectral imaging of Mars
Bands and gray levels number selection for Mars surface multispectral imaging
Klemas, V.↗
Colorimetry of Martian features by means of area scanning
Colorimetry of Mars surface from dual beam area scanner, considering light and dark areas contrast during 1969 opposition
Boyce, P. B.↗
Relative elevation differences revealed by near infrared CO2 bands on Mars
Relative elevation differences on Mars surface revealed by near IR carbon dioxide bands spectroscopic observations
Woszczyk, A.↗
Urease reaction rates at low water activity
Urea hydrolysis reaction rates by urease at low water activity, noting use for Mars surface bioassay
Mclaren, A. D.↗
Sheet plastic filters for solar cells
Poly(vinylidene fluoride) (PVF) film protects solar cells on Mars surface from radiation and prevents degradation of solar cell surfaces by Martian dust storms. PVF films may replace glass or quartz windows on solar cell arrays used to generate power on earth.
Wizenick, R. J.↗
An optimal system design process for a Mars roving vehicle
The problem of determining the optimal design for a Mars roving vehicle is considered. A system model is generated by consideration of the physical constraints on the design parameters and the requirement that the system be deliverable to the Mars surface. An expression which evaluates system performance relative to mission goals as a function of the design parameters only is developed. The use of nonlinear programming techniques to optimize the design is proposed and an example considering only two of the vehicle subsystems is formulated and solved.
Pavarini, C.↗
System modeling and optimal design of a Mars-roving vehicle.
The problem of systematically determining the optimal design for an unmanned Mars-roving vehicle is considered. A system model, identifying all feasible designs, is generated by consideration of the physical constraints on the design parameters, and the requirement that the system be deliverable to the Mars surface. An expression which evaluates system performance relative to mission goals is developed. The model and objective function together allow simulation of the effects of design trade-offs upon system performance for all feasible designs. Nonlinear programming techniques are utilized to identify the optimal design.
Smith, E. J.↗
The development of sine vibration test requirements for Viking lander capsule components
In connection with the Viking project for exploring the planet Mars, two identical spacecraft, each consisting of an orbiter and a lander, will be launched in the third quarter of 1975. Upon arrival at the planet, the Viking lander will separate from the Viking orbiter and descend to a soft landing at a selected site on the Mars surface. It was decided to perform a sine vibration test on the Viking spacecraft, in its launch configuration, to qualify it for the booster-induced transient-dynamic environment. It is shown that component-level testing is a cost- and schedule-effective prerequisite to the system-level, sine-vibration test sequences.
Barrett, S.↗
Personnel techniques necessary to maximize bio-barrier integrity at a Martian receiving laboratory
The planning of biological isolation measures for the Mars Surface Sample Return Mission is discussed in terms of personnel and organizational management. Deficiencies in past operation of the Lunar Receiving Laborator are analyzed. It was found that the failure to clearly define relationship among the government agencies involved and to effectively integrate their objectives and responsibilities was a major cause of Laboratory deficiencies. Possible solutions to these problems are presented for application to future missions.
Michaelson, G. S.↗
The effect of sterilization on biological, organic geochemical and morphological information in natural samples
The loss of biological, organic geochemical, and morphological science information that may occur should a Mars surface sample be sterilized prior to return to earth is examined. Results of experimental studies are summarized.
Hochstein, L. I.↗
Unmanned solar systems exploration - An arena for international cooperation
Mission profiles for a Mars Surface Sample Return (MSSR) mission are considered. A profile using separate launches for a lander/ascent module and an orbiter/return system could use present technology and is appropriate for international cooperation. The achievement of clean interfaces between major building blocks and ease of controlling back contamination are advantages offered by the concept. A spatially distributed surface sample could be obtained by using multiple landers delivering samples to a common orbiter. The Pioneer Venus program, originally planned as a cooperative NASA-ESRO project, resulted in development of a standardized spacecraft bus yielding benefits at minimized cost. The first joint US-European planetary mission now planned is the launch of a Pioneer class orbiter to Jupiter in 1980. Feasibility studies are being conducted.
Herman, D. H.↗
Methodology for back-contamination risk assessment for a Mars sample return mission
The risk of back-contamination from Mars Surface Sample Return (MSSR) missions is assessed. The methodology is designed to provide an assessment of the probability that a given mission design and strategy will result in accidental release of Martian organisms acquired as a result of MSSR. This is accomplished through the construction of risk models describing the mission risk elements and their impact on back-contamination probability. A conceptual framework is presented for using the risk model to evaluate mission design decisions that require a trade-off between science and planetary protection considerations.
Merkhofer, M. W.↗
The future impact of computation on planetary exploration
Informed speculations are advanced on plausible candidates for space exploration missions in decades ahead; while none are approved NASA projects, they are deemed accessible to current technology. A Venus radar mapper, a minirover system (several rovers) for Mars surface exploration (geology, areochemistry, meteorology, detection of biota), investigation of Halley's comet (1986 apparition) with the aid of a solar sail vehicle, flybys of Jovian (Galilean) satellites and a landing on Ganymede, and a soft landing on the Saturnian large satellite Titan for examination of its atmosphere and surface are sketched. Anticipated data rates, software, mission reliability, and spacecraft autonomy are discussed, along with anticipated improvements in information transmission hardware and software, and some conjectures beyond the turn of the century.
Whitney, W. M.↗
The role of automatic control in future interplanetary spaceflight
The paper reviews the guidance and automatic control techniques used in previous U.S. and Soviet lunar and planetary exploration spacecraft, and examines the objectives and requirements of potential future interplanetary missions from the viewpoint of their further demands on automatic control technology. These missions include the Venus orbital imaging radar mission, the Pioneer Mars penetrator mission, the Mars surface sample return mission, Pioneer Saturn/Uranus/Titan probe missions, the Mariner Jupiter orbiter with daughter satellite, and comet and asteroid missions.
Scull, J. R.↗
NASA Electric Propulsion Program
The described NASA program is to provide the technology base to meet the U.S. future needs in the area of low thrust, high specific impulse propulsion. An electric propulsion system will be needed to augment the Shuttle-IUS Space Transportation System for space missions involving the exploration of the solar system. Plans exist in this connection for comet and asteroid rendezvous, a Saturn and a Mercury orbiter, and a Mars surface sample return. An analysis has shown that electric propulsion can be used to obtain larger payloads, shorter trip times, more mission flexibility, and less complicated trajectories. In addition, electric propulsion has also potential uses for earth orbital missions. Attention is given to the auxiliary propulsion technology program which is to develop a one millipound electron bombardment thrust system, a baseline program concerned with a 3 kilowatt thrust system, ion thruster research, magnetoplasmadynamic thruster research and evaluation, and the use of a mass driver as a reaction mass propulsion system.
Hudson, W. R.↗
Mars penetrator umbilical
The device proposed to gather subsurface data on the planet Mars is a ballistic probe which penetrates the soil after a free fall through the Martian atmosphere. Highlights of the design, development, and testing of several features of the Mars Surface Penetration Probe are outlined.
Barns, C. E.↗