Planetary benchmarks

Design criteria and technology requirements for a system of radar reference devices to be fixed to the surfaces of the inner planets are discussed. Offshoot applications include the use of radar corner reflectors as landing beacons on the planetary surfaces and some deep space applications that may yield a greatly enhanced knowledge of the gravitational and electromagnetic structure of the solar system. Passive retroreflectors with dimensions of about 4 meters and weighing about 10 kg are feasible for use with orbiting radar at Venus and Mars. Earth-based observation of passive reflectors, however, would require very large and complex structures to be delivered to the surfaces. For Earth-based measurements, surface transponders offer a distinct advantage in accuracy over passive reflectors. A conceptual design for a high temperature transponder is presented. The design appears feasible for the Venus surface using existing electronics and power components

Innovative Schematic Concept Analysis for a Space Suit Portable Life Support Subsystem

Conceptual designs for a space suit Personal Life Support Subsystem (PLSS) were developed and assessed to determine if upgrading the system using new, emerging, or projected technologies to fulfill basic functions would result in mass, volume, or performance improvements. Technologies were identified to satisfy each of the functions of the PLSS in three environments (zero-g, Lunar, and Martian) and in three time frames (2006, 2010, and 2020). The viability of candidate technologies was evaluated using evaluation criteria such as safety, technology readiness, and reliability. System concepts (schematics) were developed for combinations of time frame and environment by assigning specific technologies to each of four key functions of the PLSS -- oxygen supply, waste removal, thermal control, and power. The PLSS concepts were evaluated using the ExtraVehicular Activity System Sizing Analysis Tool, software created by NASA to analyze integrated system mass, volume, power and thermal loads. The assessment resulted in the Texas Engineering Experiment Station recommending to NASA an evolution path from the existing PLSS to a long duration, low mass PLSS suitable for Martian missions

Space Suit Concepts and Vehicle Interfaces for the Constellation Program

In carrying out NASA’s Vision for Space Exploration, a number of different environments will be encountered that will require the crew to wear a protective space suit. Specifically, four suited mission phases are identified as Launch, Entry & Abort profiles, Contingency 0g (orbital) Extravehicular Activity (EVA), Lunar Surface EVA and Martian Surface EVA. This study presents conceptual design solutions based on a previous architecture assessment that defined space suit operational requirements for four proposed space suit configuration options. In addition, a subset of vehicle interface requirements are defined for enabling umbilical and physical connections between the suits and the various Constellation spacecraft in which they will be used. A summary of the resultant suit and component concepts and vehicle interface definitions is presented. This work was conducted during the fall semester of 2006 as part of a graduate aerospace engineering design class at the University of Colorado

Innovative Schematic Concept Analysis for a Space Suit Portable Life Support Subsystem

Conceptual designs for a space suit Personal Life Support Subsystem (PLSS) were developed and assessed to determine if upgrading the system using new, emerging, or projected technologies to fulfill basic functions would result in mass, volume, or performance improvements. Technologies were identified to satisfy each of the functions of the PLSS in three environments (zero-g, Lunar, and Martian) and in three time frames (2006, 2010, and 2020). The viability of candidate technologies was evaluated using evaluation criteria such as safety, technology readiness, and reliability. System concepts (schematics) were developed for combinations of time frame and environment by assigning specific technologies to each of four key functions of the PLSS -- oxygen supply, waste removal, thermal control, and power. The PLSS concepts were evaluated using the ExtraVehicular Activity System Sizing Analysis Tool, software created by NASA to analyze integrated system mass, volume, power and thermal loads. The assessment resulted in the Texas Engineering Experiment Station recommending to NASA an evolution path from the existing PLSS to a long duration, low mass PLSS suitable for Martian missions

No Borders: Bridging Cultures Through Yuri\u27s Night

Yuri’s Night is a non-profit organization that has facilitated a global celebration of humanity’s past, present, and future in space since 2001. Events are held annually in commemoration and celebration of the day of the first human spaceflight (12 April 1961), and the inaugural launch of the Space Shuttle twenty years later. In alignment with our mission statement, we aim to bridge cultures, be they geographic, social, or technical, as we are all learning to speak each other’s languages.Museum and science centers have celebrated a range of activities from dance parties with Stormtroopers to TweetUps with Astronauts. Locations have included: Powerhouse Discovery Centre (Australia); Rothney Astrophysical Observatory (Canada); University of Barcelona (Spain); Museum of Science and Technology (Sweden); Fiske Planetarium (USA); Great Lakes Science Center (USA); California Academy of Sciences (USA); and even the International Spaceflight Museum (Second Life).Yuri’s Night has reached the far corners of our planet on a variety of remote research platforms, where mission crews have recorded messages to share with events across the globe. Events have occurred in extreme places such as the Amundsen-Scott South Pole Station, in Mars simulations at the Mars Desert Research Station (USA) and Mars500 (Russia), and in orbit aboard the International Space Station. The upcoming ‘Explore with Yuri’ project aims to bring more attention to the initiative by encouraging people to submit photos and stories sporting Yuri’s Night t-shirts, stickers, and patches, in esoteric locations.Yuri’s Night has become more than an annual cultural space event and has reached the summit of Mt. Everest (patch with Astronaut Parazynski), SpaceUp Houston (USA), SpaceUp India, the set of the Big Bang Theory (flyer on Raj’s fridge), EndlessBBQ (barbeque celebrations with Space Tweeps), and the International Space Development Conference. Yuri’s Night contributed the event registration solution for the GetCurious campaign, which targeted landing parties for the Mars Science Laboratory, Curiosity. More than 25,000 people celebrated the landing at events from The Planetary Society’s PlanetFest in Pasadena, USA, to ~13,000 people gathering in Algiers, Algeria.For Yuri’s Night 2013 and beyond, our team has launched new campaigns with outreach partners including increased K12 activity and the ‘We Want Our Future’ initiative. Yuri’s Night is breaking down borders to traditional space outreach and will continue to enter into popular culture by creating opportunities for anyone to celebrate human spaceflight in their own cultural context

Space Suit Concepts and Vehicle Interfaces for the Constellation Program

In carrying out NASA’s Vision for Space Exploration, a number of different environments will be encountered that will require the crew to wear a protective space suit. Specifically, four suited mission phases are identified as Launch, Entry & Abort profiles, Contingency 0g (orbital) Extravehicular Activity (EVA), Lunar Surface EVA and Martian Surface EVA. This study presents conceptual design solutions based on a previous architecture assessment that defined space suit operational requirements for four proposed space suit configuration options. In addition, a subset of vehicle interface requirements are defined for enabling umbilical and physical connections between the suits and the various Constellation spacecraft in which they will be used. A summary of the resultant suit and component concepts and vehicle interface definitions is presented. This work was conducted during the fall semester of 2006 as part of a graduate aerospace engineering design class at the University of Colorado

Using Inertial Measurement Units for Measuring Spacesuit Mobility and Work Envelope Capability for Intravehicular and Extravehicular Activities

Human spaceflight destinations are expanding to include a multitude of environments that will offer different mobility challenges to explorers due to varying gravity levels and surface operations. Intravehicular Activities (IVA) suits might include a basic “get-me-down” suit for suborbital spaceflight, or a high performance pressurized pilot suit where arm mobility and field of vision are particularly important. Extravehicular Activities (EVA) could require different spacesuit architectures including: a zero-gravity station/craft maintenance suit where hand dexterity is critical; a close proximity operation suit to asteroids where maneuverability and visibility are critical; and a surface suit for the Moon or Mars where leg mobility would be a key requirement. Spacesuit kinematics are currently measured using motion capture data or photo and video analysis. Although these methods retain great detail of the external motion of the suit, they do not capture the physical body motions within the suit and in the case of motion capture, they are restricted to a laboratory setting. Inertial Measurement Units (IMUs) use accelerometers and gyroscopes to estimate relative translation and rotation. IMUs systems exist that are mobile, low-powered, and economical solutions that can be used in a laboratory setting or in the field. In this paper a range of commercially available IMUs are presented, from which the Man-Vehicle Laboratory has selected APDM, Inc.’s Opal (TM) devices for research. A preliminary analysis was conducted of a subject’s knee bend angle while walking comparing the IMUs to a Vicon motion capture system, which is considered the industry gold standard for data acquisition. The IMU knee joint angle mapped within 3 degrees of the Vicon data showing the potential of the new system. At the David Clark Company, the IMUs were used with the Contingency Hypobaric Astronaut Protective Suit (CHAPS) to measure elbow flexion/extension, shoulder flexion/extension, and shoulder abduction/adduction in the scenarios of unsuited, suited and unpressurized, and pressurized. Results from testing are presented in the paper showing the system’s ability to capture range of motion in any environment. A brief discussion summarizes key findings in the study and identifies limitations in the IMU test configuration. Recommendations for future testing are outlined and conclusions are drawn on the usability of IMUs for exploration investigations of astronaut mobility and work envelope

Four-Month Moon and Mars Crew Water Utilization Study Conducted at the Flashline Mars Arctic Research Station, Devon Island, Nunavut

A categorized water usage study was undertaken at the Flashline Mars Arctic Research Station on Devon Island, Nunavut in the High Canadian Arctic. This study was conducted as part of a long duration four-month Mars mission simulation during the summer of 2007. The study determined that the crew of seven averaged 82.07 L/day over the expedition (standard deviation 22.58 L/day). The study also incorporated a Mars Time Study phase which determined that an average of 12.12 L/sol of water was required for each crewmember. Drinking, food preparation, hand/face, oral, dish wash, clothes wash, shower, shaving, cleaning, engineering, science, plant growth and medical water were each individually monitored throughout the detailed study phases. It was determined that implementing the monitoring program itself resulted in an approximate water savings of 1.5 L/day per crewmember. The seven person crew averaged 202 distinct water draws a day (standard deviation 34) with high water use periods focusing around meal times. No statistically significant correlation was established between total water use and EVA or exercise duration. Study results suggest that current crew water utilization estimates for long duration planetary surface stays are more than two times greater than that required