Lunar Flashlight: Mapping Lunar Surface Volatiles Using a Cubesat
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
Volcanic History of the Imbrium Basin: a Close-Up View from the Lunar Rover Yutu
Volcanic history of the Imbrium basin: A close-up view from the lunar rover Yutu Jinhai Zhanga, Wei Yanga, Sen Hua, Yangting Lina,1, Guangyou Fangb, Chunlai Lic, Wenxi Pengd, Sanyuan Zhue, Zhiping Hef, Bin Zhoub, Hongyu Ling, Jianfeng Yangh, Enhai Liui, Yuchen Xua, Jianyu Wangf, Zhenxing Yaoa, Yongliao Zouc, Jun Yanc, and Ziyuan Ouyangj aKey Laboratory of Earth and Planetary Physics, Institute of Geology and Geophysics, Chinese Academy of Sciences, Beijing 100029, China; bInstitute of Electronics, Chinese Academy of Sciences, Beijing 100190, China; cNational Astronomical Observatories, Chinese Academy of Sciences, Beijing 100012, China; dInstitute of High Energy Physics, Chinese Academy of Sciences, Beijing 100049, China; eKey Laboratory of Mineralogy and Metallogeny, Guangzhou Institute of Geochemistry, Chinese Academy of Sciences, Guangzhou 510640, China; fKey Laboratory of Space Active Opto-Electronics Technology, Shanghai Institute of Technical Physics, Chinese Academy of Sciences, Shanghai 200083, China; gThe Fifth Laboratory, Beijing Institute of Space Mechanics & Electricity, Beijing 100076, China; hXi’an Institute of Optics and Precision Mechanics, Chinese Academy of Sciences, Xi’an 710119, China; iInstitute of Optics and Electronics, Chinese Academy of Sciences, Chengdu 610209, China; and jInstitute of Geochemistry, Chinese Academy of Science, Guiyang 550002, China Edited by Mark H. Thiemens, University of California, San Diego, La Jolla, CA, and approved March 24, 2015 (received for review February 13, 2015) We report the surface exploration by the lunar rover Yutu that flows in Mare Imbrium was obtained only by remote sensing from landed on the young lava flow in the northeastern part of the orbit. On December 14, 2013, Chang’e-3 successfully landed on the Mare Imbrium, which is the largest basin on the nearside of the young and high-Ti lava flow in the northeastern Mare Imbrium, Moon and is filled with several basalt units estimated to date from about 10 km south from the old low-Ti basalt unit (Fig. -
The Cubesat Mission to Study Solar Particles (Cusp) Walt Downing IEEE Life Senior Member Aerospace and Electronic Systems Society President (2020-2021)
The CubeSat Mission to Study Solar Particles (CuSP) Walt Downing IEEE Life Senior Member Aerospace and Electronic Systems Society President (2020-2021) Acknowledgements – National Aeronautics and Space Administration (NASA) and CuSP Principal Investigator, Dr. Mihir Desai, Southwest Research Institute (SwRI) Feature Articles in SYSTEMS Magazine Three-part special series on Artemis I CubeSats - April 2019 (CuSP, IceCube, ArgoMoon, EQUULEUS/OMOTENASHI, & DSN) ▸ - September 2019 (CisLunar Explorers, OMOTENASHI & Iris Transponder) - March 2020 (BioSentinnel, Near-Earth Asteroid Scout, EQUULEUS, Lunar Flashlight, Lunar Polar Hydrogen Mapper, & Δ-Differential One-Way Range) Available in the AESS Resource Center https://resourcecenter.aess.ieee.org/ ▸Free for AESS members ▸ What are CubeSats? A class of small research spacecraft Built to standard dimensions (Units or “U”) ▸ - 1U = 10 cm x 10 cm x 11 cm (Roughly “cube-shaped”) ▸ - Modular: 1U, 2U, 3U, 6U or 12U in size - Weigh less than 1.33 kg per U NASA's CubeSats are dispensed from a deployer such as a Poly-Picosatellite Orbital Deployer (P-POD) ▸NASA’s CubeSat Launch initiative (CSLI) provides opportunities for small satellite payloads to fly on rockets ▸planned for upcoming launches. These CubeSats are flown as secondary payloads on previously planned missions. https://www.nasa.gov/directorates/heo/home/CubeSats_initiative What is CuSP? NASA Science Mission Directorate sponsored Heliospheric Science Mission selected in June 2015 to be launched on Artemis I. ▸ https://www.nasa.gov/feature/goddard/2016/heliophys ics-cubesat-to-launch-on-nasa-s-sls Support space weather research by determining proton radiation levels during solar energetic particle events and identifying suprathermal properties that could help ▸ predict geomagnetic storms. -
A Summary of the Unified Lunar Control Network 2005 and Lunar Topographic Model B. A. Archinal, M. R. Rosiek, R. L. Kirk, and B
A Summary of the Unified Lunar Control Network 2005 and Lunar Topographic Model B. A. Archinal, M. R. Rosiek, R. L. Kirk, and B. L. Redding U. S. Geological Survey, 2255 N. Gemini Drive, Flagstaff, AZ 86001, USA, [email protected] Introduction: We have completed a new general unified lunar control network and lunar topographic model based on Clementine images. This photogrammetric network solution is the largest planetary control network ever completed. It includes the determination of the 3-D positions of 272,931 points on the lunar surface and the correction of the camera angles for 43,866 Clementine images, using 546,126 tie point measurements. The solution RMS is 20 µm (= 0.9 pixels) in the image plane, with the largest residual of 6.4 pixels. We are now documenting our solution [1] and plan to release the solution results soon [2]. Previous Networks: In recent years there have been two generally accepted lunar control networks. These are the Unified Lunar Control Network (ULCN) and the Clementine Lunar Control Network (CLCN), both derived by M. Davies and T. Colvin at RAND. The original ULCN was described in the last major publication about a lunar control network [3]. Images for this network are from the Apollo, Mariner 10, and Galileo missions, and Earth-based photographs. The CLCN was derived from Clementine images and measurements on Clementine 750-nm images. The purpose of this network was to determine the geometry for the Clementine Base Map [4]. The geometry of that mosaic was used to produce the Clementine UVVIS digital image model [5] and the Near-Infrared Global Multispectral Map of the Moon from Clementine [6]. -
Lunar Flashlight & NEA Scout
National Aeronautics and Space Administration Lunar Flashlight & NEA Scout A NanoSat Architecture for Deep Space Exploration Payam Banazadeh (JPL/Caltech) Andreas Frick (JPL/Caltech) EM-1 Secondary Payload Selection • 19 NASA center-led concepts were evaluated and 3 were down-selected for further refinement by AES toward a Mission Concept Review (MCR) planned for August 2014 • Primary selection criteria: - Relevance to Space Exploration Strategic Knowledge Gaps (SKGs) - Life cycle cost - Synergistic use of previously demonstrated technologies - Optimal use of available civil servant workforce Payload Strategic Knowledge Gaps Mission Concept NASA Centers Addressed BioSentinel Human health/performance in high- Study radiation-induced DNA ARC/JSC radiation space environments damage of live organisms in cis- • Fundamental effects on biological systems lunar space; correlate with of ionizing radiation in space environments measurements on ISS and Earth Lunar Flashlight Lunar resource potential Locate ice deposits in the Moon’s JPL/MSFC/MHS • Quantity and distribution of water and other permanently shadowed craters volatiles in lunar cold traps Near Earth Asteroid (NEA) NEA Characterization Slow flyby/rendezvous and Scout • NEA size, rotation state (rate/pole position) characterize one NEA in a way MSFC/JPL How to work on and interact with NEA that is relevant to human surface exploration • NEA surface mechanical properties 2 EM-1: Near Earth Asteroid (NEA) Scout concept WHY NEA Scout? – Characterize a NEA with an imager to address key Strategic -
Modeling and Adjustment of THEMIS IR Line Scanner Camera Image Measurements
Modeling and Adjustment of THEMIS IR Line Scanner Camera Image Measurements by Brent Archinal USGS Astrogeology Team 2255 N. Gemini Drive Flagstaff, AZ 86001 [email protected] As of 2004 December 9 Version 1.0 Table of Contents 1. Introduction 1.1. General 1.2. Conventions 2. Observations Equations and Their Partials 2.1. Line Scanner Camera Specific Modeling 2.2. Partials for New Parameters 2.2.1. Orientation Partials 2.2.2. Spatial Partials 2.2.3. Partials of the observations with respect to the parameters 2.2.4. Parameter Weighting 3. Adjustment Model 4. Implementation 4.1. Input/Output Changes 4.1.1. Image Measurements 4.1.2. SPICE Data 4.1.3. Program Control (Parameters) Information 4.2. Computational Changes 4.2.1. Generation of A priori Information 4.2.2. Partial derivatives 4.2.3. Solution Output 5. Testing and Near Term Work 6. Future Work Acknowledgements References Useful web sites Appendix I - Partial Transcription of Colvin (1992) Documentation Appendix II - HiRISE Sensor Model Information 1. Introduction 1.1 General The overall problem we’re solving is that we want to be able to set up the relationships between the coordinates of arbitrary physical points in space (e.g. ground points) and their coordinates on line scanner (or “pushbroom”) camera images. We then want to do a least squares solution in order to come up with consistent camera orientation and position information that represents these relationships accurately. For now, supported by funding from the NASA Critical Data Products initiative (for 2003 September to 2005 August), we will concentrate on handling the THEMIS IR camera system (Christensen et al., 2003). -
New Views of the Moon Enabled by Combined Remotely Sensed and Lunar Sample Data Sets, a Lunar Initiative
New Views of the Moon Enabled by Combined Remotely Sensed and Lunar Sample Data Sets, A Lunar Initiative Using the hand tool on your Reader, click on the links below to view that particular section of the proposal. Proposal Summary Scientific/Technical/Management Objectives and Expected Significance Background and Impact Approach and Methodology: The Role of Integration in Fundamental Problems of Lunar Geoscience Workshop 2: New Views of the Moon II: Understanding the Moon Through the Integration of Diverse Datasets. Abstract Volume and Subsequent Publications Statement of Relevance Work Plan Potential Workshop (2000): Thermal and Magmatic Evolution of the Moon Potential Workshop (2001): Early Lunar Differentiation, Core Formation, Effects of Early Planetesimal Impacts, and the Origin of the Moon’s Global Asymmetry Potential Workshop (2002): Selection of Sites for Future Sample Return Capstone Publication Timeline for the New Views of the Moon Initiative Personnel: Initiative Management and Proposal Management References Facilities: The LPI Appendix 1. Workshop on New Views of the Moon: Integrated Remotely Sensed, Geophysical, and Sample Datasets. List of presentations Appendix 2. LPSC 30 (1999) special sessions related to the Lunar Initiative. List of presentations (oral and poster) Appendix 3. Lunar Initiative Steering Committee Web Note: This is the text of a proposal submitted on behalf of the Lunar Science Community to support ongoing workshops and activities associated with the CAPTEM Lunar Initiative. It was submitted in May, 1999, in response to the ROSS 99 NRA, which solicits such proposals to be submitted to the relevant research programs. This proposal was submitted jointly to Cosmo- chemistry and Planetary Geology and Geophysics. -
Atlas V Launches LRO/LCROSS Mission Overview
Atlas V Launches LRO/LCROSS Mission Overview Atlas V 401 Cape Canaveral Air Force Station, FL Space Launch Complex-41 AV-020/LRO/LCROSS United Launch Alliance is proud to be a part of the Lunar Reconnaissance Orbiter (LRO) and the Lunar Crater Observation and Sensing Satellite (LCROSS) mission with the National Aeronautics and Space Administration (NASA). The LRO/LCROSS mission marks the sixteenth Atlas V launch and the seventh flight of an Atlas V 401 configuration. LRO/LCROSS is a dual-spacecraft (SC) launch. LRO is a lunar orbiter that will investigate resources, landing sites, and the lunar radiation environment in preparation for future human missions to the Moon. LCROSS will search for the presence of water ice that may exist on the permanently shadowed floors of lunar polar craters. The LCROSS mission will use two Lunar Kinetic Impactors, the inert Centaur upper stage and the LCROSS SC itself, to produce debris plumes that may reveal the presence of water ice under spectroscopic analysis. My thanks to the entire Atlas team for its dedication in bringing LRO/LCROSS to launch, and to NASA for selecting Atlas for this ground-breaking mission. Go Atlas, Go Centaur, Go LRO/LCROSS! Mark Wilkins Vice President, Atlas Product Line Atlas V Launch History Flight Config. Mission Mission Date AV-001 401 Eutelsat Hotbird 6 21 Aug 2002 AV-002 401 HellasSat 13 May 2003 AV-003 521 Rainbow 1 17 Jul 2003 AV-005 521 AMC-16 17 Dec 2004 AV-004 431 Inmarsat 4-F1 11 Mar 2005 AV-007 401 Mars Reconnaissance Orbiter 12 Aug 2005 AV-010 551 Pluto New Horizons 19 Jan 2006 AV-008 411 Astra 1KR 20 Apr 2006 AV-013 401 STP-1 08 Mar 2007 AV-009 401 NROL-30 15 Jun 2007 AV-011 421 WGS SV-1 10 Oct 2007 AV-015 401 NROL-24 10 Dec 2007 AV-006 411 NROL-28 13 Mar 2008 AV-014 421 ICO G1 14 Apr 2008 AV-016 421 WGS-2 03 Apr 2009 Payload Fairing Number of Solid Atlas V Size (meters) Rocket Boosters Flight/Configuration Key AV-XXX ### Number of Centaur Engines 3-digit Tail Number 3-digit Configuration Number LRO Overview LRO is the first mission in NASA’s planned return to the Moon. -
Protons in the Near Lunar Wake Observed by the SARA Instrument on Board Chandrayaan-1
FUTAANA ET AL. PROTONS IN DEEP WAKE NEAR MOON 1 Protons in the Near Lunar Wake Observed by the SARA 2 Instrument on Board Chandrayaan-1 3 Y. Futaana, 1 S. Barabash, 1 M. Wieser, 1 M. Holmström, 1 A. Bhardwaj, 2 M. B. Dhanya, 2 R. 4 Sridharan, 2 P. Wurz, 3 A. Schaufelberger, 3 K. Asamura 4 5 --- 6 Y. Futaana, Swedish Institute of Space Physics, Box 812, Kiruna, SE-98128, Sweden. 7 ([email protected]) 8 9 10 1 Swedish Institute of Space Physics, Box 812, Kiruna, SE-98128, Sweden 11 2 Space Physics Laboratory, Vikram Sarabhai Space Center, Trivandrum 695 022, India 12 3 Physikalisches Institut, University of Bern, Sidlerstrasse 5, CH-3012 Bern, Switzerland 13 4 Institute of Space and Astronautical Science, 3-1-1 Yoshinodai, Sagamihara, Japan 14 Index Terms 15 6250 Moon 16 5421 Interactions with particles and fields 17 2780 Magnetospheric Physics: Solar wind interactions with unmagnetized bodies 18 7807 Space Plasma Physics: Charged particle motion and acceleration 19 Abstract 20 Significant proton fluxes were detected in the near wake region of the Moon by an ion mass 21 spectrometer on board Chandrayaan-1. The energy of these nightside protons is slightly higher than 22 the energy of the solar wind protons. The protons are detected close to the lunar equatorial plane at 23 a 140˚ solar zenith angle, i.e., ~50˚ behind the terminator at a height of 100 km. The protons come 24 from just above the local horizon, and move along the magnetic field in the solar wind reference 25 frame. -
Global Mapping of Elemental Abundance on Lunar Surface by SELENE Gamma-Ray Spectrometer
Lunar and Planetary Science XXXVI (2005) 2092.pdf Global Mapping of elemental abundance on lunar surface by SELENE gamma-ray spectrometer. 1M. -N. Kobayashi, 1A. A. Berezhnoy, 6C. d’Uston, 1M. Fujii, 1N. Hasebe, 3T. Hiroishi, 4H. Kaneko, 1T. Miyachi, 5K. Mori, 6S. Maurice, 4M. Nakazawa, 3K. Narasaki, 1O. Okudaira, 1E. Shibamura, 2T. Takashima, 1N. Yamashita, 1Advanced Research Institute of Sci.& Eng., Waseda Univ., 3-4-1, Okubo, Shinjuku-ku, Tokyo, 169-8555, Japan, (masa- [email protected]), 2Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, 3-1-1 Yoshinodai, Sagamihara, Kanagawa, 229-8510, 3Niihama Works, Sumitomo Heavy Industry Ltd., Niihama, Ehime, Japan, Moriya Works, 4Meisei Electric Co., Ltd., 3-249-1, Yuri-ga-oka, Moriya-shi, Ibaraki, 302-0192, 5Clear Pulse Co., 6-25-17, Chuo, Ohta-ku, Tokyo, Japan, 143-0024, 6Centre d’Etude Spatiale des Rayonnements, CNRS/UPS, Colonel Roche, B.P 4346, France. Introduction: Elemental composition on the sur- face of a planet is very important information for solv- ing the origin and the evolution of the planet and also very necessary for understanding the origin and the evolution of solar system. Planetary gamma-ray spec- troscopy is extremely powerful approach for the ele- mental composition measurement. Gamma-ray spec- trometer (GRS) will be on board SELENE, advanced lunar polar orbiter, and employ a large-volume Ge detector of 252cc as the main detector [1]. SELENE GRS is, therefore, approximately twice more sensitiv- ity than Lunar Prospector GRS, four times more sensi- Figure 1: The schematic drawing of SELENE Gamma- tive than APOLLO GRS. -
Mission Design for the Lunar Reconnaissance Orbiter
AAS 07-057 Mission Design for the Lunar Reconnaissance Orbiter Mark Beckman Goddard Space Flight Center, Code 595 29th ANNUAL AAS GUIDANCE AND CONTROL CONFERENCE February 4-8, 2006 Sponsored by Breckenridge, Colorado Rocky Mountain Section AAS Publications Office, P.O. Box 28130 - San Diego, California 92198 AAS-07-057 MISSION DESIGN FOR THE LUNAR RECONNAISSANCE ORBITER † Mark Beckman The Lunar Reconnaissance Orbiter (LRO) will be the first mission under NASA’s Vision for Space Exploration. LRO will fly in a low 50 km mean altitude lunar polar orbit. LRO will utilize a direct minimum energy lunar transfer and have a launch window of three days every two weeks. The launch window is defined by lunar orbit beta angle at times of extreme lighting conditions. This paper will define the LRO launch window and the science and engineering constraints that drive it. After lunar orbit insertion, LRO will be placed into a commissioning orbit for up to 60 days. This commissioning orbit will be a low altitude quasi-frozen orbit that minimizes stationkeeping costs during commissioning phase. LRO will use a repeating stationkeeping cycle with a pair of maneuvers every lunar sidereal period. The stationkeeping algorithm will bound LRO altitude, maintain ground station contact during maneuvers, and equally distribute periselene between northern and southern hemispheres. Orbit determination for LRO will be at the 50 m level with updated lunar gravity models. This paper will address the quasi-frozen orbit design, stationkeeping algorithms and low lunar orbit determination. INTRODUCTION The Lunar Reconnaissance Orbiter (LRO) is the first of the Lunar Precursor Robotic Program’s (LPRP) missions to the moon. -
Lunar Life Sciences Payload Assessment
Lunar Surface Science Workshop 2020 (LPI Contrib. No. 2241) 5077.pdf LUNAR LIFE SCIENCES PAYLOAD ASSESSMENT. S. C. Sun1, F. Karouia2, M. P. Lera3, M. P. Parra1, H. E. Ray4, A. J. Ricco1, S. M. Spremo1. 1NASA Ames Research Center, 2Blue Marble Space Institute of Science, 3KBR, 4ASRC Federal Space and Defense, Inc. Introduction: The Moon provides a unique site to ISS, including systems that integrate into EXPRESS study living organisms. The fractional gravity and (EXpedite the PRocessing of ExperimentS for Space) unique radiation environment have similarities to Mars Racks or are external space exposure research facilities. and will help us understand how life will respond to These same systems can be the basis for future payload conditions on the red planet. Martian and lunar envi- systems for experiments to be performed beyond Low ronments can be simulated on the ground but not to high Earth Orbit. Such facilities would need to be adapted to fidelity. Altered gravity and increased radiation are dif- be compatible with the new research platforms and ficult to replicate simultaneously, which makes study- function in the harsher radiation environment found out- ing their combined effect difficult. The International side the magnetosphere. If Gateway and a lunar based- Space Station, and previously, the Space Shuttle, pro- lab could provide EXPRESS-compatible interfaces, lev- vided a microgravity environment, and could simulate eraging hardware developed for ISS would be more fea- fractional-g only via an onboard centrifuge. Because sible. the ISS and Space Shuttle orbits were within the Earth’s Gaps in Capabilities: Many of the payload systems magnetosphere, experiments on those platforms have that have been developed require human tending. -
Developing Technologies for Biological Experiments in Deep Space
Developing technologies for biological experiments in deep space Sergio R. Santa Maria Elizabeth Hawkins Ada Kanapskyte NASA Ames Research Center [email protected] NASA’s life science programs STS-1 (1981) STS-135 (2011) 1973 – 1974 1981 - 2011 2000 – 2006 – Space Shuttle International Skylab Bio CubeSats Program Space Station Microgravity effects - Nausea / vomit - Disorientation & sleep loss - Body fluid redistribution - Muscle & bone loss - Cardiovascular deconditioning - Increase pathogenicity in microbes Interplanetary space radiation What type of radiation are we going to encounter beyond low Earth orbit (LEO)? Galactic Cosmic Rays (GCRs): - Interplanetary, continuous, modulated by the 11-year solar cycle - High-energy protons and highly charged, energetic heavy particles (Fe-56, C-12) - Not effectively shielded; can break up into lighter, more penetrating pieces Challenges: biology effects poorly understood (but most hazardous) Interplanetary space radiation Solar Particle Events (SPEs) - Interplanetary, sporadic, transient (several min to days) - High proton fluxes (low and medium energy) - Largest doses occur during maximum solar activity Challenges: unpredictable; large doses in a short time Space radiation effects Space radiation is the # 1 risk to astronaut health on extended space exploration missions beyond the Earth’s magnetosphere • Immune system suppression, learning and memory impairment have been observed in animal models exposed to mission-relevant doses (Kennedy et al. 2011; Britten et al. 2012) • Low doses of space radiation are causative of an increased incidence and early appearance of cataracts in astronauts (Cuccinota et al. 2001) • Cardiovascular disease mortality rate among Apollo lunar astronauts is 4-5-fold higher than in non-flight and LEO astronauts (Delp et al.