ARTIFICIAL GRAVITY RESEARCH to ENABLE HUMAN SPACE EXPLORATION International Academy of Astronautics
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An Instrumented Centrifuge for Studying Mouse Locomotion and Behaviour Under Hypergravity Benjamin J
© 2019. Published by The Company of Biologists Ltd | Biology Open (2019) 8, bio043018. doi:10.1242/bio.043018 METHODS AND TECHNIQUES An instrumented centrifuge for studying mouse locomotion and behaviour under hypergravity Benjamin J. H. Smith* and James R. Usherwood ABSTRACT (Alexander, 1984). Investigating the limitations of inverted Gravity may influence multiple aspects of legged locomotion, from the pendulum models of locomotion may lead to advances in robotics periods of limbs moving as pendulums to the muscle forces required and treatment of gait pathologies, as well as our fundamental to support the body. We present a system for exposing mice to understanding of legged locomotion. hypergravity using a centrifuge and studying their locomotion and The motion of an inverted pendulum can be described using u€ ¼ g u u€ activity during exposure. Centrifuge-induced hypergravity has the the equation L sin , where is angular acceleration, g is θ advantages that it both allows animals to move freely, and it affects gravitational acceleration, L is length, and is angular displacement both body and limbs. The centrifuge can impose two levels of from the equilibrium point; testing the predictions of inverted hypergravity concurrently, using two sets of arms of different lengths, pendulum-based models therefore requires the manipulation of either each carrying a mouse cage outfitted with a force and speed L or g. Differences in L are usually studied by comparing similar measuring exercise wheel and an infrared high-speed camera; both animals of different sizes (Gatesy and Biewener, 1991; Daley and triggered automatically when a mouse begins running on the wheel. -
PHYSICS of ARTIFICIAL GRAVITY Angie Bukley1, William Paloski,2 and Gilles Clément1,3
Chapter 2 PHYSICS OF ARTIFICIAL GRAVITY Angie Bukley1, William Paloski,2 and Gilles Clément1,3 1 Ohio University, Athens, Ohio, USA 2 NASA Johnson Space Center, Houston, Texas, USA 3 Centre National de la Recherche Scientifique, Toulouse, France This chapter discusses potential technologies for achieving artificial gravity in a space vehicle. We begin with a series of definitions and a general description of the rotational dynamics behind the forces ultimately exerted on the human body during centrifugation, such as gravity level, gravity gradient, and Coriolis force. Human factors considerations and comfort limits associated with a rotating environment are then discussed. Finally, engineering options for designing space vehicles with artificial gravity are presented. Figure 2-01. Artist's concept of one of NASA early (1962) concepts for a manned space station with artificial gravity: a self- inflating 22-m-diameter rotating hexagon. Photo courtesy of NASA. 1 ARTIFICIAL GRAVITY: WHAT IS IT? 1.1 Definition Artificial gravity is defined in this book as the simulation of gravitational forces aboard a space vehicle in free fall (in orbit) or in transit to another planet. Throughout this book, the term artificial gravity is reserved for a spinning spacecraft or a centrifuge within the spacecraft such that a gravity-like force results. One should understand that artificial gravity is not gravity at all. Rather, it is an inertial force that is indistinguishable from normal gravity experience on Earth in terms of its action on any mass. A centrifugal force proportional to the mass that is being accelerated centripetally in a rotating device is experienced rather than a gravitational pull. -
An Assessment of Aerocapture and Applications to Future Missions
Post-Exit Atmospheric Flight Cruise Approach An Assessment of Aerocapture and Applications to Future Missions February 13, 2016 National Aeronautics and Space Administration An Assessment of Aerocapture Jet Propulsion Laboratory California Institute of Technology Pasadena, California and Applications to Future Missions Jet Propulsion Laboratory, California Institute of Technology for Planetary Science Division Science Mission Directorate NASA Work Performed under the Planetary Science Program Support Task ©2016. All rights reserved. D-97058 February 13, 2016 Authors Thomas R. Spilker, Independent Consultant Mark Hofstadter Chester S. Borden, JPL/Caltech Jessie M. Kawata Mark Adler, JPL/Caltech Damon Landau Michelle M. Munk, LaRC Daniel T. Lyons Richard W. Powell, LaRC Kim R. Reh Robert D. Braun, GIT Randii R. Wessen Patricia M. Beauchamp, JPL/Caltech NASA Ames Research Center James A. Cutts, JPL/Caltech Parul Agrawal Paul F. Wercinski, ARC Helen H. Hwang and the A-Team Paul F. Wercinski NASA Langley Research Center F. McNeil Cheatwood A-Team Study Participants Jeffrey A. Herath Jet Propulsion Laboratory, Caltech Michelle M. Munk Mark Adler Richard W. Powell Nitin Arora Johnson Space Center Patricia M. Beauchamp Ronald R. Sostaric Chester S. Borden Independent Consultant James A. Cutts Thomas R. Spilker Gregory L. Davis Georgia Institute of Technology John O. Elliott Prof. Robert D. Braun – External Reviewer Jefferey L. Hall Engineering and Science Directorate JPL D-97058 Foreword Aerocapture has been proposed for several missions over the last couple of decades, and the technologies have matured over time. This study was initiated because the NASA Planetary Science Division (PSD) had not revisited Aerocapture technologies for about a decade and with the upcoming study to send a mission to Uranus/Neptune initiated by the PSD we needed to determine the status of the technologies and assess their readiness for such a mission. -
Up, Up, and Away by James J
www.astrosociety.org/uitc No. 34 - Spring 1996 © 1996, Astronomical Society of the Pacific, 390 Ashton Avenue, San Francisco, CA 94112. Up, Up, and Away by James J. Secosky, Bloomfield Central School and George Musser, Astronomical Society of the Pacific Want to take a tour of space? Then just flip around the channels on cable TV. Weather Channel forecasts, CNN newscasts, ESPN sportscasts: They all depend on satellites in Earth orbit. Or call your friends on Mauritius, Madagascar, or Maui: A satellite will relay your voice. Worried about the ozone hole over Antarctica or mass graves in Bosnia? Orbital outposts are keeping watch. The challenge these days is finding something that doesn't involve satellites in one way or other. And satellites are just one perk of the Space Age. Farther afield, robotic space probes have examined all the planets except Pluto, leading to a revolution in the Earth sciences -- from studies of plate tectonics to models of global warming -- now that scientists can compare our world to its planetary siblings. Over 300 people from 26 countries have gone into space, including the 24 astronauts who went on or near the Moon. Who knows how many will go in the next hundred years? In short, space travel has become a part of our lives. But what goes on behind the scenes? It turns out that satellites and spaceships depend on some of the most basic concepts of physics. So space travel isn't just fun to think about; it is a firm grounding in many of the principles that govern our world and our universe. -
Magnetoshell Aerocapture: Advances Toward Concept Feasibility
Magnetoshell Aerocapture: Advances Toward Concept Feasibility Charles L. Kelly A thesis submitted in partial fulfillment of the requirements for the degree of Master of Science in Aeronautics & Astronautics University of Washington 2018 Committee: Uri Shumlak, Chair Justin Little Program Authorized to Offer Degree: Aeronautics & Astronautics c Copyright 2018 Charles L. Kelly University of Washington Abstract Magnetoshell Aerocapture: Advances Toward Concept Feasibility Charles L. Kelly Chair of the Supervisory Committee: Professor Uri Shumlak Aeronautics & Astronautics Magnetoshell Aerocapture (MAC) is a novel technology that proposes to use drag on a dipole plasma in planetary atmospheres as an orbit insertion technique. It aims to augment the benefits of traditional aerocapture by trapping particles over a much larger area than physical structures can reach. This enables aerocapture at higher altitudes, greatly reducing the heat load and dynamic pressure on spacecraft surfaces. The technology is in its early stages of development, and has yet to demonstrate feasibility in an orbit-representative envi- ronment. The lack of a proof-of-concept stems mainly from the unavailability of large-scale, high-velocity test facilities that can accurately simulate the aerocapture environment. In this thesis, several avenues are identified that can bring MAC closer to a successful demonstration of concept feasibility. A custom orbit code that dynamically couples magnetoshell physics with trajectory prop- agation is developed and benchmarked. The code is used to simulate MAC maneuvers for a 60 ton payload at Mars and a 1 ton payload at Neptune, both proposed NASA mis- sions that are not possible with modern flight-ready technology. In both simulations, MAC successfully completes the maneuver and is shown to produce low dynamic pressures and continuously-variable drag characteristics. -
Orbital Fueling Architectures Leveraging Commercial Launch Vehicles for More Affordable Human Exploration
ORBITAL FUELING ARCHITECTURES LEVERAGING COMMERCIAL LAUNCH VEHICLES FOR MORE AFFORDABLE HUMAN EXPLORATION by DANIEL J TIFFIN Submitted in partial fulfillment of the requirements for the degree of: Master of Science Department of Mechanical and Aerospace Engineering CASE WESTERN RESERVE UNIVERSITY January, 2020 CASE WESTERN RESERVE UNIVERSITY SCHOOL OF GRADUATE STUDIES We hereby approve the thesis of DANIEL JOSEPH TIFFIN Candidate for the degree of Master of Science*. Committee Chair Paul Barnhart, PhD Committee Member Sunniva Collins, PhD Committee Member Yasuhiro Kamotani, PhD Date of Defense 21 November, 2019 *We also certify that written approval has been obtained for any proprietary material contained therein. 2 Table of Contents List of Tables................................................................................................................... 5 List of Figures ................................................................................................................. 6 List of Abbreviations ....................................................................................................... 8 1. Introduction and Background.................................................................................. 14 1.1 Human Exploration Campaigns ....................................................................... 21 1.1.1. Previous Mars Architectures ..................................................................... 21 1.1.2. Latest Mars Architecture ......................................................................... -
Continuous-Flow Centrifugation to Collect Suspended Sediment for Chemical Analysis
1 Table 6. Compounds detected in both equipment blank samples and not in corresponding source blank samples or at concentrations greater than two times the corresponding source blank sample concentration. Prepared in cooperation with the National Water Quality Monitoring Council and [Source data: Appendix A, table A1; Conn and Black (2014, table A4); and Conn and others (2015, table A11). CAS Registry Number: Chemical Abstracts Service Washington State Department of(CAS) Ecology Registry Number® (RN) is a registered trademark of the American Chemical Society. CAS recommends the verifi cation of CASRNs through CAS Client ServicesSM. Method: EPA, U.S. Environmental Protection Agency’s SW 846; SIM, select ion monitoring. Unit: µg/kg, microgram per kilogram; ng/kg, nanogram per kilogram. Sample type: River samples were from the Puyallup River, Washington. Q, qualifi er (blank cells indicate an unqualifi ed detection). J, estimated, result between the Continuous-Flow Centrifugationdetection level and reporting level; toNJ, result Collect did not meet all quantitation Suspended criteria (an estimated maxiumum possible concentration is reported in Result column) U, not detected above the reporting level (reported in the Result column); UJ, not detected above the detection level (reported in the Result column). Abbreviations: na, not Sediment for Chemicalapplicable; Analysis PCBs, polychlorinated biphenyls] Sample type Chapter 6 of CAS River River Commercial Commercial Section D, Water Quality Parameter name Registry Method Unit source equipment -
Gas Centrifuge Technology: Proliferation Concerns and International Safeguards Brian D
Gas Centrifuge Technology: Proliferation Concerns and International Safeguards Brian D. Boyer Los Alamos National Laboratory Trinity Section American Nuclear Society Santa Fe, NM November 7, 2014 Acknowledgment to M. Rosenthal (BNL), J.M. Whitaker (ORNL), H. Wood (UVA), O. Heinonen (Harvard Belfer School), B. Bush (IAEA-Ret.), C. Bathke (LANL) for sources of ideas, information, and knowledge UNCLASSIFIED Operated by Los Alamos National Security, LLC for the U.S. Department of Energy's NNSA Enrichment / Proliferation / Safeguards . Enrichment technology – The centrifuge story . Proliferation of technology – Global Networks . IAEA Safeguards – The NPT Bargain Enrichment Proliferation Safeguards U.S. DOE Centrifuges – DOE / Pres. George W. Bush at ORNL B. Boyer and K. Akilimali - IAEA Zippe Centrifuge – Deutsches Museum (Munich) briefed on seized Libyan nuclear Safeguards Verifying Spent Fuel in www.deutsches-museum.de/en/exhibitions/energy/energy-technology/nuclear-energy/ equipment (ORNL) Training in Sweden (Ski-1999) UNCLASSIFIED 2 Operated by Los Alamos National Security, LLC for the U.S. Department of Energy's NNSA The Nuclear Fuel Cycle and Proliferation Paths to WMDs IAEA Safeguards On URANIUM Path Weapon Assembly Convert UF6 to U Metal Pre-Safeguards Natural Enriched DIVERSION Material (INFCIRC/153) Uranium Uranium PATH “Open” Cycle WEAPONS PATHS Fuel – Natural Uranium or LEU In closed cycle – MOX Fuel (U and Pu) “Closed” Cycle IAEA Safeguards On PLUTONIUM Path Convert Pu Plutonium Compounds to Pu Metal DIVERSION PATH To Repository -
Basics in Centrifugation - Eppendorf Handling Solutions Page 1 of 5
Basics in Centrifugation - Eppendorf Handling Solutions Page 1 of 5 Menu • Home • Sample Handling • Centrifugation • Safe Use of Centrifuges • Basics in Centrifugation Basics in Centrifugation • Biosafety • Safe Use of Centrifuges • Centrifugation Applications • This and That • Braking Ramps • Thermal Conductivity • Centrifuge Maintenance • Ergonomics • share • tweet • share • mail Basics in Centrifugation Centrifugation is a technique that helps to separate mixtures by applying centrifugal force. A centrifuge is a device, generally driven by an electric motor, that puts an object, e.g., a rotor, in a rotational movement around a fixed axis. A centrifuge works by using the principle of sedimentation: Under the influence of gravitational force (g-force), substances separate according to their density. Different types of separation are known, including isopycnic, ultrafiltration, density gradient, phase separation, and pelleting. https://handling-solutions.eppendorf.com/sample-handling/centrifugation/safe-use-of-cent... 10/24/2018 Basics in Centrifugation - Eppendorf Handling Solutions Page 2 of 5 Pelleting is the most common application for centrifuges. Here, particles are concentrated as a pellet at the bottom of the centrifuge tube and separated from the remaining solution, called supernatant. During phase separation, chemicals are converted from a matrix or an aqueous medium to a solvent (for additional chemical or molecular biological analysis). In ultrafiltration, macromolecules are purified, separated, and concentrated by using a membrane. Isopycnic centrifugation is carried out using a "self- generating" density gradient established through equilibrium sedimentation. This method concentrates the analysis matches with those of the surrounding solution. Protocols for centrifugation typically specify the relative centrifugal force (rcf) and the degree of acceleration in multiples of g (g-force). -
Human Adaptation to Space
Human Adaptation to Space From Wikipedia, the free encyclopedia Human physiological adaptation to the conditions of space is a challenge faced in the development of human spaceflight. The fundamental engineering problems of escaping Earth's gravity well and developing systems for in space propulsion have been examined for well over a century, and millions of man-hours of research have been spent on them. In recent years there has been an increase in research into the issue of how humans can actually stay in space and will actually survive and work in space for long periods of time. This question requires input from the whole gamut of physical and biological sciences and has now become the greatest challenge, other than funding, to human space exploration. A fundamental step in overcoming this challenge is trying to understand the effects and the impact long space travel has on the human body. Contents [hide] 1 Importance 2 Public perception 3 Effects on humans o 3.1 Unprotected effects 4 Protected effects o 4.1 Gravity receptors o 4.2 Fluids o 4.3 Weight bearing structures o 4.4 Effects of radiation o 4.5 Sense of taste o 4.6 Other physical effects 5 Psychological effects 6 Future prospects 7 See also 8 References 9 Sources Importance Space colonization efforts must take into account the effects of space on the body The sum of mankind's experience has resulted in the accumulation of 58 solar years in space and a much better understanding of how the human body adapts. However, in the future, industrialization of space and exploration of inner and outer planets will require humans to endure longer and longer periods in space. -
Reusable Rocket Upper Stage Development of a Multidisciplinary Design Optimisation Tool to Determine the Feasibility of Upper Stage Reusability L
Reusable Rocket Upper Stage Development of a Multidisciplinary Design Optimisation Tool to Determine the Feasibility of Upper Stage Reusability L. Pepermans Technische Universiteit Delft Reusable Rocket Upper Stage Development of a Multidisciplinary Design Optimisation Tool to Determine the Feasibility of Upper Stage Reusability by L. Pepermans to obtain the degree of Master of Science at the Delft University of Technology, to be defended publicly on Wednesday October 30, 2019 at 14:30 AM. Student number: 4144538 Project duration: September 1, 2018 – October 30, 2019 Thesis committee: Ir. B.T.C Zandbergen , TU Delft, supervisor Prof. E.K.A Gill, TU Delft Dr.ir. D. Dirkx, TU Delft This thesis is confidential and cannot be made public until October 30, 2019. An electronic version of this thesis is available at http://repository.tudelft.nl/. Cover image: S-IVB upper stage of Skylab 3 mission in orbit [23] Preface Before you lies my thesis to graduate from Delft University of Technology on the feasibility and cost-effectiveness of reusable upper stages. During the accompanying literature study, it was determined that the technology readiness level is sufficiently high for upper stage reusability. However, it was unsure whether a cost-effective system could be build. I have been interested in the field of Entry, Descent, and Landing ever since I joined the Capsule Team of Delft Aerospace Rocket Engineering (DARE). During my time within the team, it split up in the Structures Team and Recovery Team. In September 2016, I became Chief Recovery for the Stratos III student-built sounding rocket. During this time, I realised that there was a lack of fundamental knowledge in aerodynamic decelerators within DARE. -
Smallsat Aerocapture to Enable a New Paradigm of Planetary Missions
SmallSat Aerocapture to Enable a New Paradigm of Planetary Missions Alex Austin, Adam Nelessen, Bill Ethiraj Venkatapathy, Robin Beck, Robert Braun, Michael Werner, Evan Strauss, Joshua Ravich, Mark Jesick Paul Wercinski, Michael Aftosmis, Roelke Jet Propulsion Laboratory, California Michael Wilder, Gary Allen CU Boulder Institute of Technology NASA Ames Research Center Boulder, CO 80309 Pasadena, CA 91109 Moffett Field, CA 94035 [email protected] 818-393-7521 [email protected] [email protected] Abstract— This paper presents a technology development system requirements, which concluded that mature TPS initiative focused on delivering SmallSats to orbit a variety of materials are adequate for this mission. CFD simulations were bodies using aerocapture. Aerocapture uses the drag of a single used to assess the risk of recontact by the drag skirt during the pass through the atmosphere to capture into orbit instead of jettison event. relying on large quantities of rocket fuel. Using drag modulation flight control, an aerocapture vehicle adjusts its drag area This study has concluded that aerocapture for SmallSats could during atmospheric flight through a single-stage jettison of a be a viable way to increase the delivered mass to Venus and can drag skirt, allowing it to target a particular science orbit in the also be used at other destinations. With increasing interest in presence of atmospheric uncertainties. A team from JPL, NASA SmallSats and the challenges associated with performing orbit Ames, and CU Boulder has worked to address the key insertion burns on small platforms, this technology could enable challenges and determine the feasibility of an aerocapture a new paradigm of planetary science missions.