To the Moon and Beyond Back
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Return to the Moon Mission Overview
Return to the Moon Mission Overview The new millennium is still young, but humans using the lastest in transport technology to are preparing to Return to the Moon, reduce the travel time. In addition to verifying spurred on by the verification of ice water on the best site for the establishment of the the lunar surface by Lunar Prospector in lunar base, during the course of the mission, 1998. Composed of hydrogen and oxygen – the crew will recover a probe that is the elements that make up water – the lunar stranded in space and access the damage to ice provides a core resource for long-term the probe, and then build and launch an human presence on the lunar surface. equipment module to the lunar surface. Lunar Prospector was followed by a series of Some information has been previously successful robotic missions designed to obtained from the potential lunar base sites. probe the concept that the ice water could A detailed study has determined that the be harvested. Once collected, the ice water base site must contain solid, metals, and can be turned into drinking water, oxygen for potentially useful resources such as helium-3. life support of a lunar base, nutrients as the Rock and soil samples, soil composition, and basis for agriculture, components needed for seismic information have been gathered by rocket fuel, or when combined with lunar soil, previous missions from a portion of the the basics for construction materials. Not potential sites. Experiments on soil and rock only did those robotic missions successfully samples from other possible sites must be prove that concept, but since then, additional performed in order to determine the best robotic staging missions have landed and site for the lunar base. -
Conceptual Human-System Interface Design for a Lunar Access Vehicle
Conceptual Human-System Interface Design for a Lunar Access Vehicle Mary Cummings Enlie Wang Cristin Smith Jessica Marquez Mark Duppen Stephane Essama Massachusetts Institute of Technology* Prepared For Draper Labs Award #: SC001-018 PI: Dava Newman HAL2005-04 September, 2005 http://halab.mit.edu e-mail: [email protected] *MIT Department of Aeronautics and Astronautics, Cambridge, MA 02139 TABLE OF CONTENTS 1 INTRODUCTION..................................................................................................... 1 1.1 THE GENERAL FRAMEWORK................................................................................ 1 1.2 ORGANIZATION.................................................................................................... 2 2 H-SI BACKGROUND AND MOTIVATION ........................................................ 3 2.1 APOLLO VS. LAV H-SI........................................................................................ 3 2.2 APOLLO VS. LUNAR ACCESS REQUIREMENTS ...................................................... 4 3 THE LAV CONCEPTUAL PROTOTYPE............................................................ 5 3.1 HS-I DESIGN ASSUMPTIONS ................................................................................ 5 3.2 THE CONCEPTUAL PROTOTYPE ............................................................................ 6 3.3 LANDING ZONE (LZ) DISPLAY............................................................................. 8 3.3.1 LZ Display Introduction................................................................................. -
Project Horizon Report
Volume I · SUMMARY AND SUPPORTING CONSIDERATIONS UNITED STATES · ARMY CRD/I ( S) Proposal t c• Establish a Lunar Outpost (C) Chief of Ordnance ·cRD 20 Mar 1 95 9 1. (U) Reference letter to Chief of Ordnance from Chief of Research and Devel opment, subject as above. 2. (C) Subsequent t o approval by t he Chief of Staff of reference, repre sentatives of the Army Ballistic ~tissiles Agency indicat e d that supplementar y guidance would· be r equired concerning the scope of the preliminary investigation s pecified in the reference. In particular these r epresentatives requested guidance concerning the source of funds required to conduct the investigation. 3. (S) I envision expeditious development o! the proposal to establish a lunar outpost to be of critical innportance t o the p. S . Army of the future. This eva luation i s appar ently shar ed by the Chief of Staff in view of his expeditious a pproval and enthusiastic endorsement of initiation of the study. Therefore, the detail to be covered by the investigation and the subs equent plan should be as com plete a s is feas ible in the tin1e limits a llowed and within the funds currently a vailable within t he office of t he Chief of Ordnance. I n this time of limited budget , additional monies are unavailable. Current. programs have been scrutinized r igidly and identifiable "fat'' trimmed awa y. Thus high study costs are prohibitive at this time , 4. (C) I leave it to your discretion t o determine the source and the amount of money to be devoted to this purpose. -
II. Causes of Tides III. Tidal Variations IV. Lunar Day and Frequency of Tides V
Tides I. What are Tides? II. Causes of Tides III. Tidal Variations IV. Lunar Day and Frequency of Tides V. Monitoring Tides Wikimedia FoxyOrange [CC BY-SA 3.0 Tides are not explicitly included in the NGSS PerFormance Expectations. From the NGSS Framework (M.S. Space Science): “There is a strong emphasis on a systems approach, using models oF the solar system to explain astronomical and other observations oF the cyclic patterns oF eclipses, tides, and seasons.” From the NGSS Crosscutting Concepts: Observed patterns in nature guide organization and classiFication and prompt questions about relationships and causes underlying them. For Elementary School: • Similarities and diFFerences in patterns can be used to sort, classiFy, communicate and analyze simple rates oF change For natural phenomena and designed products. • Patterns oF change can be used to make predictions • Patterns can be used as evidence to support an explanation. For Middle School: • Graphs, charts, and images can be used to identiFy patterns in data. • Patterns can be used to identiFy cause-and-eFFect relationships. The topic oF tides have an important connection to global change since spring tides and king tides are causing coastal Flooding as sea level has been rising. I. What are Tides? Tides are one oF the most reliable phenomena on Earth - they occur on a regular and predictable cycle. Along with death and taxes, tides are a certainty oF liFe. Tides are apparent changes in local sea level that are the result of long-period waves that move through the oceans. Photos oF low and high tide on the coast oF the Bay oF Fundy in Canada. -
Go for Lunar Landing Conference Report
CONFERENCE REPORT Sponsored by: REPORT OF THE GO FOR LUNAR LANDING: FROM TERMINAL DESCENT TO TOUCHDOWN CONFERENCE March 4-5, 2008 Fiesta Inn, Tempe, AZ Sponsors: Arizona State University Lunar and Planetary Institute University of Arizona Report Editors: William Gregory Wayne Ottinger Mark Robinson Harrison Schmitt Samuel J. Lawrence, Executive Editor Organizing Committee: William Gregory, Co-Chair, Honeywell International Wayne Ottinger, Co-Chair, NASA and Bell Aerosystems, retired Roberto Fufaro, University of Arizona Kip Hodges, Arizona State University Samuel J. Lawrence, Arizona State University Wendell Mendell, NASA Lyndon B. Johnson Space Center Clive Neal, University of Notre Dame Charles Oman, Massachusetts Institute of Technology James Rice, Arizona State University Mark Robinson, Arizona State University Cindy Ryan, Arizona State University Harrison H. Schmitt, NASA, retired Rick Shangraw, Arizona State University Camelia Skiba, Arizona State University Nicolé A. Staab, Arizona State University i Table of Contents EXECUTIVE SUMMARY..................................................................................................1 INTRODUCTION...............................................................................................................2 Notes...............................................................................................................................3 THE APOLLO EXPERIENCE............................................................................................4 Panelists...........................................................................................................................4 -
JAXA's Space Exploration Activities
JAXA’s Space Exploration Activities Jun Gomi, Deputy Director General, JAXA Hayabusa 2 ✓ Asteroid Explorer of the C-type asteroid ✓ Launched in December, 2014 ✓ Reached target asteroid “Ryugu” in 2018 ✓ First successful touchdown to Ryugu on February 22, 2019 ✓ Return to Earth in 2020 (162173) Ryugu 2 Hayabusa 2 (c) JAXA, University of Tokyo, Kochi University, Rikkyo University, (c) JAXA, University of Tokyo, Kochi University, Rikkyo University, Nagoya University, Chiba Institute of Technology, Meiji University, Nagoya University, Chiba Institute of Technology, Meiji University, University of Aizu and AIST. University of Aizu, AIST Asteroid Ryugu photographed from a Asteroid Ryugu from an altitude of 6km. distance of about 20 km. The image Image was captured with the Optical was taken on June 30, 2018. Navigation Camera on July 20, 2018. Hayabusa 2 4 JAXA’s Plan for Space Exploration International • Utilization of ISS/Kibo • Cis-Lunar Platform (Gateway) Cooperation • Lunar exploration and beyond Industry & • JAXA Space Exploration Innovation Academia Hub Partnerships • Science Community discussions JAXA’s Overall Scenario for International Space Exploration Mars, others ★ Initial Exploration ★ Full Fledge Exploration MMX: JFY2024 • Science and search for life • Utilization feasibility exam. Kaguya Moon ©JAXA ©JAXA ©JAXA ©JAXA ©JAXA Full-fledged Exploration & SLIM Traversing exploration(2023- ) Sample Return(2026- ) Utilization (JFY2021) • Science exploration • S/R from far side • Cooperative science/resource • Water prospecting • Technology demo for human mission exploration by robotic and human HTV-X der.(2026- ) • Small probe deploy, data relay etc. Gateway Phase 1 Gateway (2022-) Phase 2 • Support for Lunar science Earth • Science using deep space Promote Commercialization International Space Station 6 SLIM (Smart Lander for Investigating Moon) ✓ Demonstrate pin-point landing on the moon. -
Building Structures on the Moon and Mars: Engineering Challenges and Structural Design Parameters for Proposed Habitats
Building Structures on the Moon and Mars: Engineering Challenges and Structural Design Parameters for Proposed Habitats Ramesh B. Malla, Ph.D., F. ASCE, A.F. AIAA Professor Department of Civil and Environmental Engineering University of Connecticut, Storrs, CT 06269 (E-Mail: [email protected]) Presented at the Breakout Panel Session- Theme C - Habitats (Preparation and Architecture) RETH Workshop- Grand Challenges and Key Research Questions to Achieve Resilient Long-Term Extraterrestrial Habitats Purdue University; October 22-23, 2018 What is Structural Resiliency? Characterized by four traits: Robustness Ability to maintain critical functions in crisis Minimization of direct and indirect Resourcefulness losses from hazards through enhanced Ability to effectively manage crisis as it resistance and robustness to extreme unfolds events, as well as more effective Rapid Recovery recovery strategies. Reconstitute normal operations quickly and effectively Redundancy Backup resources to support originals Per: National Infrastructure Advisory Council, 2009 Hazard Sources & Potential Lunar Habitats Potential Hazard Sources Available Habitat Types Impact (Micrometeorite, Debris) Inflatable Hard Vacuum Membrane Extreme Temperature Rigid-Frame Structure Seismic Activity Hybrid Frame- Low Gravity “Bessel Crater” - https://www.lpi.usra.edu/science/kiefer/Education/SSRG2- Craters/craterstructure.html Membrane Radiation Structure Galactic Cosmic Rays (GCR) Subsurface Solar-Emitted Particles (SEP) Variants Malla, et al. (1995) -
Reviewing the Contribution of GRAIL to Lunar Science and Planetary Missions Maria T
EPSC Abstracts Vol. 12, EPSC2018-575, 2018 European Planetary Science Congress 2018 EEuropeaPn PlanetarSy Science CCongress c Author(s) 2018 Reviewing the contribution of GRAIL to lunar science and planetary missions Maria T. Zuber and David E. Smith Department of Earth, Atmospheric and Planetary Sciences, Massachusetts Institute of Technology, Cambridge, MA 02139- 4307, USA. ([email protected], [email protected]) Abstract Q of the Moon determined to be 41±4 at the monthly frequency. The GRAIL Discovery mission to the Moon in 2011 provided an unprecedentedly accurate gravity field model for the Moon. The goal of the mission was to provide insight into the structure of the Moon from its interior to the surface but it also made significant contributions to lunar spacecraft operations for all future lunar missions to the Moon. We discuss the science and the broader contributions from this mission that completed its objectives in December 2012 when the spacecraft impacted the lunar surface. 1. Introduction Figure 1: Free-air gravity of the Moon from GRAIL. GRAIL was a mission designed to measure the Full uniform resolution spherical harmonic models gravity field of the Moon with both high accuracy were obtained out to degree & order 1200 with and high resolution. The measurement goal was to special fields with higher resolutions over certain obtain the gravity at resolutions that would enable areas to degree and order 1800. interpretation of the crust at fractions of its thickness, estimated at the time of launch to be about 45 km. To 3. Mission Operations obtain a surface resolution of less than 10 km required the spacecraft to orbit the Moon at less than The significant improvement in our knowledge of the 20 km, an altitude that was considered dangerous at gravity field of the Moon by GRAIL enabled the re- that time without an accurate gravity field model. -
The Calendars of India
The Calendars of India By Vinod K. Mishra, Ph.D. 1 Preface. 4 1. Introduction 5 2. Basic Astronomy behind the Calendars 8 2.1 Different Kinds of Days 8 2.2 Different Kinds of Months 9 2.2.1 Synodic Month 9 2.2.2 Sidereal Month 11 2.2.3 Anomalistic Month 12 2.2.4 Draconic Month 13 2.2.5 Tropical Month 15 2.2.6 Other Lunar Periodicities 15 2.3 Different Kinds of Years 16 2.3.1 Lunar Year 17 2.3.2 Tropical Year 18 2.3.3 Siderial Year 19 2.3.4 Anomalistic Year 19 2.4 Precession of Equinoxes 19 2.5 Nutation 21 2.6 Planetary Motions 22 3. Types of Calendars 22 3.1 Lunar Calendar: Structure 23 3.2 Lunar Calendar: Example 24 3.3 Solar Calendar: Structure 26 3.4 Solar Calendar: Examples 27 3.4.1 Julian Calendar 27 3.4.2 Gregorian Calendar 28 3.4.3 Pre-Islamic Egyptian Calendar 30 3.4.4 Iranian Calendar 31 3.5 Lunisolar calendars: Structure 32 3.5.1 Method of Cycles 32 3.5.2 Improvements over Metonic Cycle 34 3.5.3 A Mathematical Model for Intercalation 34 3.5.3 Intercalation in India 35 3.6 Lunisolar Calendars: Examples 36 3.6.1 Chinese Lunisolar Year 36 3.6.2 Pre-Christian Greek Lunisolar Year 37 3.6.3 Jewish Lunisolar Year 38 3.7 Non-Astronomical Calendars 38 4. Indian Calendars 42 4.1 Traditional (Siderial Solar) 42 4.2 National Reformed (Tropical Solar) 49 4.3 The Nānakshāhī Calendar (Tropical Solar) 51 4.5 Traditional Lunisolar Year 52 4.5 Traditional Lunisolar Year (vaisnava) 58 5. -
Robotic Asteroid Prospector
Robotic Asteroid Prospector Marc M. Cohen1 Marc M. Cohen Architect P.C. – Astrotecture™, Palo Alto, CA, USA 94306-3864 Warren W. James2 V Infinity Research LLC. – Altadena, CA, USA Kris Zacny,3 Philip Chu, Jack Craft Honeybee Robotics Spacecraft Mechanisms Corporation – Pasadena, CA, USA This paper presents the results from the nine-month, Phase 1 investigation for the Robotic Asteroid Prospector (RAP). This project investigated several aspects of developing an asteroid mining mission. It conceived a Space Infrastructure Framework that would create a demand for in space-produced resources. The resources identified as potentially feasible in the near-term were water and platinum group metals. The project’s mission design stages spacecraft from an Earth Moon Lagrange (EML) point and returns them to an EML. The spacecraft’s distinguishing design feature is its solar thermal propulsion system (STP) that provides two functions: propulsive thrust and process heat for mining and mineral processing. The preferred propellant is water since this would allow the spacecraft to refuel at an asteroid for its return voyage to Cis- Lunar space thus reducing the mass that must be launched from the EML point. The spacecraft will rendezvous with an asteroid at its pole, match rotation rate, and attach to begin mining operations. The team conducted an experiment in extracting and distilling water from frozen regolith simulant. Nomenclature C-Type = Carbonaceous Asteroid EML = Earth-Moon Lagrange Point ESL = Earth-Sun Lagrange Point IPV = Interplanetary Vehicle M-Type = Metallic Asteroid NEA = Near Earth Asteroid NEO = Near Earth Object PGM = Platinum Group Metal STP = Solar Thermal Propulsion S-Type = Stony Asteroid I. -
Multi-Lunar Day Polar Missions with a Solar-Only Rover. A. Colaprete1, R
Survive the Lunar Night Workshop 2018 (LPI Contrib. No. 2106) 7007.pdf Multi-Lunar Day Polar Missions with a Solar-Only Rover. A. Colaprete1, R. C. Elphic1, M. Shirley1, M. Siegler2, 1NASA Ames Research Center, Moffett Field, CA, 2Planetary Science Institute, Tucson, AZ Introduction: Resource Prospector (RP) was a lu- Polar Solar “Oases”: Numerous studies have nar HEOMD/Advanced Exploration Systems volatiles identified regions near the lunar poles that have sus- prospecting mission developed for potential flight in tained periods of solar illumination. In some places the early 2020s. The mission includes a rover-borne these periods of sustained sunlight extend across sever- payload that (1) can locate surface and near-subsurface al lunations, while others have very short (24-48 hours) volatiles, (2) excavate and analyze samples of the vola- nights. A study was conducted to evaluate if the RP tile-bearing regolith, and (3) demonstrate the form, rover system could take advantage of these “oases” to extractability and usefulness of the materials. The pri- survive the lunar night. While the Earth would set, as mary mission goal for RP is to evaluate the In-Situ seen by the rover, every approximately 2-weeks, these Resource Utilization (ISRU) potential of the lunar “oases” could provide sufficient power, and have lu- poles, to determine their utility within future NASA nar-nights short enough, for the rover system to sur- and commercial spaceflight architectures. While the vive. current RP rover design did not require a system that Results: The study focused in the area surrounding could survive lunar nights, it has been demonstrated the north pole crater Hermite-A (primarily due to the that the current design could conduct multi-lunar day fidelity of existing traverse planner data sets in this missions by taking advantage of areas that receive pro- area). -
Extending NASA™S Exploration Systems Architecture Towards Long
SpaceOps 2006 Conference AIAA 2006-5746 Extending NASA’s Exploration Systems Architecture towards Long - term Crewed Moon and Mars Operations Wilfried K. Hofstetter *, Paul D. Wooster †, Edward F. Crawley ‡ Massac husetts Institute of Technology 77 Massachusetts Avenue , Cambridge, MA, 02139 This pape r presents a baseline strategy for extending lunar crew transportation system operations as outlined in NASA’s Exploration Systems Architecture Study (ESAS) report towards longer -stay lunar surface operations and conjunction class Mars missions. The analys is of options for commonality between initial lunar sortie operations and later Moon and Mars exploration missions is essential for reducing life -cycle cost and pr oviding low - investment / high -return options for extending exploration capabilities soon afte r the 7 th human lunar landing . The analysis is also intended to inform the development of the human lunar lander and other exploration system elements by identifying enabling requirements for extension of the lunar crew tr ansportation system. The baseline strategy outlined in this paper was generated using a three -step process : the analysis of exploration objectives and scenarios, identification of functional and operational extension options , and the conceptual design of a set of preferred extension option s. Extension options include (but are not limited to) the use of the human lunar lander as outpost for extended stays, and Mars crew transportation using evolved Crew Exploration Vehicle ( CEV ) and human lander crew compartments. Although t he results presen ted in this paper are based on the ES AS elements , the conclusions drawn in this paper are generally applicable provided the same l unar transportation mode (lunar orbit rendezvous) is used .