Communications and tracking on the apollo lunar exploration mission
Apollo project lunar exploration communications and tracking
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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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Solar Mesosphere Explorer mission
The Solar Mesosphere Explorer (SME) satellite experiments will provide a comprehensive study of atmospheric ozone and the processes which form and destroy it. Five instruments to be carried on the spacecraft will measure the ozone density and altitude distribution, monitor the incoming solar radiation, and measure other atmospheric constituents which affect ozone. The first objective of the SME satellite experiments is to determine what changes occur in the ozone distribution as a result of changes in the incoming solar radiation. A second objective is to measure all changes in the ozone density distribution in the altitude range of 30 to 80 km and to determine the causes of these changes.
Stuart, J. R.↗
Parametric Evaluation of Interstellar Exploration Mission Concepts
One persistent difficulty in evaluating the myriad advanced propulsion concepts proposed over the last 60 years is a true apples to apples comparison of the expected gain in performance. This analysis is complicated by numerous factors including, multiple missions of interest to the advanced propulsion community, the lack of a credible closed form solution to 'medium thrust' trajectories, and lack of detailed design data for most proposed concepts that lend credibility to engine performance estimates. This paper describes a process on how to make fair comparisons of different propulsion concepts for multiple missions over a wide range of performance values. The figure below illustrates this process. This paper describes in detail the process and outlines the status so far in compiling the required data. Parametric data for several missions are calculated and plotted against specific power-specific impulse scatter plots of expected propulsion system performance. The overlay between required performance as defined by the trajectory parametrics and expected performance as defined in the literature for major categories of propulsion systems clearly defines which propulsion systems are the most apt for a given mission. The application of the Buckingham Pi theorem to general parameters for interstellar exploration ( mission time, mass, specific impulse, specific power, distance, propulsion source energy/mass, etc.) yields a number of dimensionless variables. The relationships of these variables can then be explored before application to a particular mission. Like in the fields of fluid mechanics and heat transfer, the use of the Buckingham Pi theorem results in new variables to make apples to apples comparisons.
Adams, Robert B.↗
Developing Advanced Support Technologies for Planetary Exploration Missions
The United States Vision for Space Exploration calls for sending robots and humans to explore the Earth s moon, the planet Mars, and beyond. The National Aeronautics and Space Administration (NASA) is developing a set of design reference missions that will provide further detail to these plans. Lunar missions are expected to provide a stepping stone, through operational research and evaluation, in developing the knowledge base necessary to send crews on long duration missions to Mars and other distant destinations. The NASA Exploration Systems Directorate (ExSD), in its program of bioastronautics research, manages the development of technologies that maintain human life, health, and performance in space. Using a systems engineering process and risk management methods, ExSD s Human Support Systems (HSS) Program selects and performs research and technology development in several critical areas and transfers the results of its efforts to NASA exploration mission/systems development programs in the form of developed technologies and new knowledge about the capabilities and constraints of systems required to support human existence beyond Low Earth Orbit. HSS efforts include the areas of advanced environmental monitoring and control, extravehicular activity, food technologies, life support systems, space human factors engineering, and systems integration of all these elements. The HSS Program provides a structured set of deliverable products to meet the needs of exploration programs. these products reduce the gaps that exist in our knowledge of and capabilities for human support for long duration, remote space missions. They also reduce the performance gap between the efficiency of current space systems and the greater efficiency that must be achieved to make human planetary exploration missions economically and logistically feasible. In conducting this research and technology development program, it is necessary for HSS technologists and program managers to develop a common currency for decision making and the allocation of funding. A high level assessment is made of both the knowledge gaps and the system performance gaps across the program s technical project portfolio. This allows decision making that assures proper emphasis areas and provides a key measure of annual technological progress, as exploration mission plans continue to mature.
Berdich, Debra P.↗
Developing Advanced Human Support Technologies for Planetary Exploration Missions
The United States Vision for Space Exploration calls for sending robots and humans to explore the Earth's moon, the planet Mars, and beyond. The National Aeronautics and Space Administration (NASA) is developing a set of design reference missions that will provide further detail to these plans. Lunar missions are expected to provide a stepping stone, through operational research and evaluation, in developing the knowledge base necessary to send crews on long duration missions to Mars and other distant destinations. The NASA Exploration Systems Directorate (ExSD), in its program of bioastronautics research, manages the development of technologies that maintain human life, health, and performance in space. Using a system engineering process and risk management methods, ExSD's Human Support Systems (HSS) Program selects and performs research and technology development in several critical areas and transfers the results of its efforts to NASA exploration mission/systems development programs in the form of developed technologies and new knowledge about the capabilities and constraints of systems required to support human existence beyond Low Earth Orbit. HSS efforts include the areas of advanced environmental monitoring and control, extravehicular activity, food technologies, life support systems, space human factors engineering, and systems integration of all these elements. The HSS Program provides a structured set of deliverable products to meet the needs of exploration programs. These products reduce the gaps that exist in our knowledge of and capabilities for human support for long duration, remote space missions. They also reduce the performance gap between the efficiency of current space systems and the greater efficiency that must be achieved to make human planetary exploration missions economically and logistically feasible. In conducting this research and technology development program, it is necessary for HSS technologists and program managers to develop a common currency for decision making and the allocation of funding. A high level assessment is made of both the knowledge gaps and the system performance gaps across the program s technical project portfolio. This allows decision making that assures proper emphasis areas and provides a key measure of annual technological progress, as exploration mission plans continue to mature.
Berdich, Debra P.↗
Storyboard for the Medical System Concept of Operations for Mars Exploration Missions
This storyboard conceptualizes one scenario of an integrated medical system during a Mars exploration mission. All content is for illustrative purposes only and neither defines nor implies system design requirement.
Antonsen, Eric↗
NASA Alternate Fecal Canister On-orbit Performance and Applicability to Exploration Missions
NASA developed a collapsible canister for the collection and containment of fecal deposits on long range exploration missions as well as on space stations where mass and volume are of great impact on spacecraft and propulsion designs. Developed as an alternative to the exploration toilet hard-sided canister, the container is a smaller volume for stowage in the unfilled state which allows better use of constrained volume on smaller vehicles for longer missions while still providing the important features of odor and solid/liquid contents containment when in the filled state. A reduction in mass was also achieved for the alternate fecal canister itself, although weight of the lid and contents are common to both the hard-side canister, and the alternate fecal canister. Details of the design, flight build and certification, and technology demonstration on ISS will be discussed. The discussion will include interface requirements and design solutions for use with the Universal Waste Management System (UWMS) as well as future extensibility for other toilet systems.
toilet↗
Definition ofthe Design Trajectory and Entry Flight Corridor for the NASA Orion Exploration Mission 1 Entry Trajectory Using an Integrated Approach and Optimization
One of the key design objectives of NASA's Orion Exploration Mission 1 (EM- 1) is to execute a guided entry trajectory demonstrating GN&C capability. The focus of this paper is defining the flyable entry corridor for EM-1 taking into account multiple subsystem constraints such as complex aerothermal heating constraints, aerothermal heating objectives, landing accuracy constraints, structural load limits, Human-System-Integration-Requirements, Service Module debris disposal limits and other flight test objectives. During the EM-1 Design Analysis Cycle 1 design challenges came up that made defining the flyable entry corridor for the EM-1 mission critical to mission success. This document details the optimization techniques that were explored to use with the 6-DOF ANTARES simulation to assist in defining the design entry interface state and entry corridor with respect to key flight test constraints and objectives.
McNamara, Luke W.↗
Nutrition Requirements, Standards, and Operating Bands for Exploration Missions
The challenge was brought forward in early 2005 to define the nutritional requirements for Exploration missions, and to define the relevant standards and associated operating bands related to nutrition. This document is the result of this charge. An extensive review of existing knowledge was conducted with participation of intramural and extramural experts, and the findings are summarized herein. In short, the approach taken was to define the nutrient intake requirements, that is, the amount of each nutrient expected to be available in the food system. The standards are defined as markers of nutritional status, with optimal (green), sub-optimal (yellow), and critical (red) levels for each. For many of the nutrient requirements, it is not known if they are altered during space flight. Furthermore, in many cases the intake of a nutrient may act as a countermeasure to one or more negative effects of space flight, but these potential countermeasures, too, are not well defined. Thus, we have also documented herein the areas where further research is required. Accordingly, while this document is intended as a comprehensive summary of our knowledge to date, it is expected that this is the first edition of these requirements and standards. As we learn more about space-flight nutrition, and as relationships between disease and nutrients are further defined in Earth-based populations, this document, and the approach to nutrition in the space rogram, will need to be updated accordingly.
Neubek, Deborah J.↗
An Open Avionics and Software Architecture to Support Future NASA Exploration Missions
The presentation describes an avionics and software architecture that has been developed through NASAs Advanced Exploration Systems (AES) division. The architecture is open-source, highly reliable with fault tolerance, and utilizes standard capabilities and interfaces, which are scalable and customizable to support future exploration missions. Specific focus areas of discussion will include command and data handling, software, human interfaces, communication and wireless systems, and systems engineering and integration.
AE↗
The Gravity and Extreme Magnetism Small Explorer Mission (GEMS)
Polarization is an inherently geometric quantity and provides information on source geometry inaccessible via spectroscopy or timing. To date, there have been reliable detections of X-ray polarization from only one object outside the solar system (the Crab nebula). Recent development of photoelectric polarimetry makes it possible to perform sensitive X-ray polarimetry with a modest mission. GEMS was selected by NASA to be the 13th Small Explorer mission with launch planned for 2014. GEMS will be approximately 100 times more sensitive than any previously flown X-ray polarimeter and will provide useful polarization measurements for dozens of cosmic X-ray sources. GEMS will lead to new insights into the nature of accreting black holes, magnetized neutron stars, and supernova remnants. In this talk I will review the science motivation for GEMS and describe the status of the mission implementation.
Kallman, Tim↗
Lunar campsite concept: Space transfer concepts and analysis for exploration missions
The lunar Campsite concept responds to a perceived need to identify early manned science and exploration missions that require minimal initial funding. The Campsite concept defers the build-up of many infrastructure components without escalating total program costs. The lunar Campsite has been sized nominally for four crew for 42 days (1 lunar night and 2 lunar days), but can be modified to span two lunar nights up to 60 days. Total mission fulfillment requires five Earth-to-LEO launches, four (100 mt class launch vehicle) for the two vehicle assemblies and one (PLS or NSTS) for the crew. The lunar Campsite mission mode is tandem direct using a booster stage and a lander stage. The booster is separated from the lander after the TLI burn and is expended into the Earth's atmosphere. In the Campsite mode, the lander lands on the surface not to be returned. In the crew delivery mode, the lander is guided to a precision landing about 500 m from the Campsite, and with enough propellant to return the crew to Earth. The Campsite consists of a habitat and airlock, body mounted radiators with a surface shield, sun tracking solar arrays, and an Earth-tracking high-gain antenna. The CV is very similar to the campsite delivery vehicle. The CV does not, however, have radiators or solar arrays. The vehicle stacks are essentially common in that they utilize the same structure system and engines, the same propellant tanks, the same 'cut-out' in which the CRV and payloads are incorporated, and the same RCS locations. The booster and lander stage propellant tank propellant capacities are identical and have margins which would allow additional fueling for propulsive capture of the boost stage into Earth orbit. This contractual study was performed to identify Campsite and vehicle interfaces and vehicle requirements, and to surface issues related to the integration of the Campsite and LTV's.
Source record↗
Europa Geophysical Explorer Mission Concept Studies
This slide presentation discusses the studies done to outline the concept of a explorer mission to the Jovian Moon, Europa, that would allow a further understanding of the Geophysics of that moon. Included in the presentation are an outline of the possible trajectory, including flyby assists, a listing of the science objectives and the scientific instruments that would be used in the completion of the objectives.
lander↗
Sustainable and Autonomic Space Exploration Missions
Visions for future space exploration have long term science missions in sight, resulting in the need for sustainable missions. Survivability is a critical property of sustainable systems and may be addressed through autonomicity, an emerging paradigm for self-management of future computer-based systems based on inspiration from the human autonomic nervous system. This paper examines some of the ongoing research efforts to realize these survivable systems visions, with specific emphasis on developments in Autonomic Policies.
Hinchey, Michael G.↗
A methodology to determine impact of robotic technologies on space exploration missions
This paper presents a new method for evaluating relative strengths and impact of robotic technologies utilized for space exploration missions.
robotics↗
Development of a Mechanical Trash Compactor (Mpactor) for Exploration Missions
NASA is developing a mechanical trash compactor (Mpactor), a pneumatically driven trash compaction system, for human space exploration missions to manage trash items such as food packaging, sanitary wipes, clothing, tape, and other types of waste. The compaction system that is under development does not involve heating, water removal, or water recovery which eliminates the need for complex ancillary hardware required to manage gaseous effluents, as well as condense the water vapor. A system called the Crew Exploration Vehicle (CEV) Compactor, intended for use in the micro-gravity environment, was developed at NASA Ames Research Center for the Constellation Program 2007. This CEV Compactor is being further developed and renamed the Mpactor (short for mechanical trash compactor). The Mpactor is being used to gather engineering data that will allow engineers and planners to scale a future design for different mission scenarios and to evaluate different bag materials and designs that help retain compaction.
transit vehicle↗
Exploration Mission Particulate Matter Filtration Technology Performance Testing in a Simulated Spacecraft Cabin Ventilation System
Human deep space exploration missions will require advances in long-life, low maintenance airborne particulate matter filtration technology. As one of the National Aeronautics and Space Administrations (NASA) developments in this area, a prototype of a new regenerable, multi-stage particulate matter filtration technology was tested in an International Space Station (ISS) module simulation facility. As previously reported, the key features of the filter system include inertial and media filtration with regeneration and in-place media replacement techniques. The testing facility can simulate aspects of the cabin environment aboard the ISS and contains flight-like cabin ventilation system components. The filtration technology test article was installed at the inlet of the central ventilation system duct and instrumented to provide performance data under nominal flow conditions. In-place regeneration operations were also evaluated. The real-time data included pressure drop across the filter stages, process air flow rate, ambient pressure, humidity and temperature. In addition, two video cameras positioned at the filtration technology test articles inlet and outlet were used to capture the mechanical performance of the filter media indexing operation under varying air flow rates. Recent test results are presented and future design recommendations are discussed.
particulate matter filtration↗
Lithium Ion Batteries for Mars Exploration Missions
The upcoming NASA's missions aimed at exploring our Planetary system require batteries that can operate at extreme operating temperatures, with high specific energy and energy densities. Conventional aerospace rechargeable battery systems are inadequate to meet the demands.
extreme↗