Flight Opportunities and Small Spacecraft Technology Program Updates NAC Technology, Innovation and Engineering Committee Meeting | March 19, 2020
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
Bolden Testimony
HOLD FOR RELEASE UNTIL PRESENTED BY WITNESS November 17, 2011 Statement of The Honorable Charles F. Bolden, Jr. Administrator National Aeronautics and Space Administration before the Subcommittee on Science and Space Committee on Commerce, Science and Transportation U. S. Senate Mr. Chairman and Members of the Subcommittee, thank you for the opportunity to appear before you today to discuss the outlook for NASA’s human space flight program. This has been a remarkable year, as we have completed assembling and outfitting of the U.S. On-orbit Segment (USOS) of the International Space Station (ISS), allowing us to focus on full utilization of the Station’s research capabilities; taken key steps in moving forward into the future of exploration beyond Low-Earth Orbit (LEO); celebrated the 50 th anniversary of human spaceflight; and witnessed the successful conclusion of the historic Space Shuttle Program. We are also pleased with the progress our industry partners have made in developing an American capability to transport cargo and eventually astronauts to the ISS, and end the outsourcing of this work to foreign governments. More importantly, this will add a critical level of redundancy for transporting cargo and crew to the ISS. A robust transportation architecture is important to ensuring full utilization of this amazing research facility. Enabling commercial crew and cargo transportation systems in LEO allows NASA to focus on developing its own systems for sending astronauts on missions of exploration beyond LEO. This split between commercial and Government systems allows for a cost effective approach to promote a broad base for human exploration by the United States. -
Project Selene: AIAA Lunar Base Camp
Project Selene: AIAA Lunar Base Camp AIAA Space Mission System 2019-2020 Virginia Tech Aerospace Engineering Faculty Advisor : Dr. Kevin Shinpaugh Team Members : Olivia Arthur, Bobby Aselford, Michel Becker, Patrick Crandall, Heidi Engebreth, Maedini Jayaprakash, Logan Lark, Nico Ortiz, Matthew Pieczynski, Brendan Ventura Member AIAA Number Member AIAA Number And Signature And Signature Faculty Advisor 25807 Dr. Kevin Shinpaugh Brendan Ventura 1109196 Matthew Pieczynski 936900 Team Lead/Operations Logan Lark 902106 Heidi Engebreth 1109232 Structures & Environment Patrick Crandall 1109193 Olivia Arthur 999589 Power & Thermal Maedini Jayaprakash 1085663 Robert Aselford 1109195 CCDH/Operations Michel Becker 1109194 Nico Ortiz 1109533 Attitude, Trajectory, Orbits and Launch Vehicles Contents 1 Symbols and Acronyms 8 2 Executive Summary 9 3 Preface and Introduction 13 3.1 Project Management . 13 3.2 Problem Definition . 14 3.2.1 Background and Motivation . 14 3.2.2 RFP and Description . 14 3.2.3 Project Scope . 15 3.2.4 Disciplines . 15 3.2.5 Societal Sectors . 15 3.2.6 Assumptions . 16 3.2.7 Relevant Capital and Resources . 16 4 Value System Design 17 4.1 Introduction . 17 4.2 Analytical Hierarchical Process . 17 4.2.1 Longevity . 18 4.2.2 Expandability . 19 4.2.3 Scientific Return . 19 4.2.4 Risk . 20 4.2.5 Cost . 21 5 Initial Concept of Operations 21 5.1 Orbital Analysis . 22 5.2 Launch Vehicles . 22 6 Habitat Location 25 6.1 Introduction . 25 6.2 Region Selection . 25 6.3 Locations of Interest . 26 6.4 Eliminated Locations . 26 6.5 Remaining Locations . 27 6.6 Chosen Location . -
Richard Hunter1, Mike Loucks2, Jonathan Currie1, Doug Sinclair3, Ehson Mosleh1, Peter Beck1
Co-Authors: Richard Hunter1, Mike Loucks2, Jonathan Currie1, Doug Sinclair3, Ehson Mosleh1, Peter Beck1 1 Rocket Lab USA, Inc. 2Space Exploration Engineering 3Sinclair by Rocket Lab (formerly Sinclair Interplanetary) Photon-enabled Planetary Small Spacecraft Missions For Decadal Science A White Paper for the 2023-2032 Planetary Decadal Survey 1. OVERVIEW Regular, low-cost Decadal-class science missions to planetary destinations enabled by small high-ΔV spacecraft, like the high-energy Photon, support expanding opportunities for scientists and increase the rate of science return. The high-energy Photon can launch on Electron to precisely target escape asymptotes for planetary small spacecraft missions with payload masses up to ~50 kg without the need for a medium or heavy lift launch vehicle. The high-energy Photon can also launch as a secondary payload with even greater payload masses to deep-space science targets. This paper describes planetary mission concepts connected to science objectives that leverage Rocket Lab’s deep space mission approach. The high-energy Photon can access various planetary science targets of interest including the cislunar environment, Small Bodies, Mars, Venus, and the Outer Planets. Additional planetary small spacecraft missions with focused investigations are recommended, including dedicated small spacecraft missions that do not rely on launch as a secondary payload. 2. HIGH-ENERGY PHOTON Figure 1: The high-energy The high-energy Photon (Figure 1) is a self-sufficient small spacecraft Photon enables small planetary capable of long-duration interplanetary cruise. Its power system is science missions, including Venus probe missions. conventional, using photovoltaic solar arrays and lithium-polymer secondary batteries. The attitude control system includes star trackers, sun sensors, an inertial measurement unit, three reaction wheels, and a cold-gas reaction control system (RCS). -
Cloud Download
NASA Technical Memorandum 106110 Comparisons of Selected Laser Beam Power Missions to Conventionally Powered Missions John M. Bozek National Aeronautics and Space Administration Lewis Research Center Cleveland, Ohio and Steven R. Oleson, Geoffrey A. Landis, and Mark W. Stavnes Sverdrup Technology, Inc. Lewis Research Center Group Brook Park, Ohio Prepared for the First Annual Wireless Power Transmission Conference sponsored by the Center for Space Power, Texas A&M University San Antonio, Texas, February 23-25, 1993 NASA COMPARISONS OF SELECTED LASER BEAM POWER MISSIONS TO CONVENTIONALLY POWERED MISSIONS John M. Bozek National Aeronautics and Space Administration Lewis Research Center Cleveland, Ohio 44135 and Steven R. Oleson, Geoffrey A. Landis, and Mark W. Stavnes Sverdrup Technology, Inc. Lewis Research Center Group Brook Park, Ohio 44142 SUMMARY Earth-based laser sites beaming laser power to space assets have shown benefits over competing power system concepts for specific missions. Missions analyzed in this report that show benefits of laser beam power are low-Earth-orbit (LEO) to geosynchronous-Earth-orbit (GEO) transfer, LEO to low-lunar-orbit (LLO) cargo missions, and lunar-base power. Both laser- and solar-powered orbit transfer vehicles (OTV's) make a "tug" concept viable, which substantially reduces cumulative initial mass to LEO in comparison to chemical propulsion concepts. In addition, electric propulsion OTV's powered by a laser beam have shorter trip times to and from GEO than do competing OTV's powered solely by the Sun. A round-trip savings of 3 months was calculated for the use of a laser OTV tug instead of a solar OTV tug. -
Status of the Space Shuttle Solid Rocket Booster
The Space Congress® Proceedings 1980 (17th) A New Era In Technology Apr 1st, 8:00 AM Status of The Space Shuttle Solid Rocket Booster William P. Horton Solid Rocket Booster Engineering Office, George C. Marshall Space Flight Center, Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Horton, William P., "Status of The Space Shuttle Solid Rocket Booster" (1980). The Space Congress® Proceedings. 3. https://commons.erau.edu/space-congress-proceedings/proceedings-1980-17th/session-1/3 This Event is brought to you for free and open access by the Conferences at Scholarly Commons. It has been accepted for inclusion in The Space Congress® Proceedings by an authorized administrator of Scholarly Commons. For more information, please contact [email protected]. STATUS OF THE SPACE SHUTTLE SOLID ROCKET BOOSTER William P. Horton, Chief Engineer Solid Rocket Booster Engineering Office George C. Marshall Space Flight Center, AL 35812 ABSTRACT discuss retrieval and refurbishment plans for Booster reuse, and will address Booster status Two Solid Rocket Boosters provide the primary for multimission use. first stage thrust for the Space Shuttle. These Boosters, the largest and most powerful solid rocket vehicles to meet established man- BOOSTER CONFIGURATION rated design criteria, are unique in that they are also designed to be recovered, refurbished, It is appropriate to review the Booster config and reused. uration before describing the mission profile. The Booster is 150 feet long and is 148 inches The first SRB f s have been stacked on the in diameter (Figure 1), The inert weight Mobile Launch Platform at the Kennedy Space is 186,000 pounds and the propellant weight is Center and are ready to be mated with the approximately 1.1 million pounds for each External Tank and Orbiter in preparation for Booster. -
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. -
Highlights in Space 2010
International Astronautical Federation Committee on Space Research International Institute of Space Law 94 bis, Avenue de Suffren c/o CNES 94 bis, Avenue de Suffren UNITED NATIONS 75015 Paris, France 2 place Maurice Quentin 75015 Paris, France Tel: +33 1 45 67 42 60 Fax: +33 1 42 73 21 20 Tel. + 33 1 44 76 75 10 E-mail: : [email protected] E-mail: [email protected] Fax. + 33 1 44 76 74 37 URL: www.iislweb.com OFFICE FOR OUTER SPACE AFFAIRS URL: www.iafastro.com E-mail: [email protected] URL : http://cosparhq.cnes.fr Highlights in Space 2010 Prepared in cooperation with the International Astronautical Federation, the Committee on Space Research and the International Institute of Space Law The United Nations Office for Outer Space Affairs is responsible for promoting international cooperation in the peaceful uses of outer space and assisting developing countries in using space science and technology. United Nations Office for Outer Space Affairs P. O. Box 500, 1400 Vienna, Austria Tel: (+43-1) 26060-4950 Fax: (+43-1) 26060-5830 E-mail: [email protected] URL: www.unoosa.org United Nations publication Printed in Austria USD 15 Sales No. E.11.I.3 ISBN 978-92-1-101236-1 ST/SPACE/57 *1180239* V.11-80239—January 2011—775 UNITED NATIONS OFFICE FOR OUTER SPACE AFFAIRS UNITED NATIONS OFFICE AT VIENNA Highlights in Space 2010 Prepared in cooperation with the International Astronautical Federation, the Committee on Space Research and the International Institute of Space Law Progress in space science, technology and applications, international cooperation and space law UNITED NATIONS New York, 2011 UniTEd NationS PUblication Sales no. -
Cislunar Tether Transport System
FINAL REPORT on NIAC Phase I Contract 07600-011 with NASA Institute for Advanced Concepts, Universities Space Research Association CISLUNAR TETHER TRANSPORT SYSTEM Report submitted by: TETHERS UNLIMITED, INC. 8114 Pebble Ct., Clinton WA 98236-9240 Phone: (206) 306-0400 Fax: -0537 email: [email protected] www.tethers.com Report dated: May 30, 1999 Period of Performance: November 1, 1998 to April 30, 1999 PROJECT SUMMARY PHASE I CONTRACT NUMBER NIAC-07600-011 TITLE OF PROJECT CISLUNAR TETHER TRANSPORT SYSTEM NAME AND ADDRESS OF PERFORMING ORGANIZATION (Firm Name, Mail Address, City/State/Zip Tethers Unlimited, Inc. 8114 Pebble Ct., Clinton WA 98236-9240 [email protected] PRINCIPAL INVESTIGATOR Robert P. Hoyt, Ph.D. ABSTRACT The Phase I effort developed a design for a space systems architecture for repeatedly transporting payloads between low Earth orbit and the surface of the moon without significant use of propellant. This architecture consists of one rotating tether in elliptical, equatorial Earth orbit and a second rotating tether in a circular low lunar orbit. The Earth-orbit tether picks up a payload from a circular low Earth orbit and tosses it into a minimal-energy lunar transfer orbit. When the payload arrives at the Moon, the lunar tether catches it and deposits it on the surface of the Moon. Simultaneously, the lunar tether picks up a lunar payload to be sent down to the Earth orbit tether. By transporting equal masses to and from the Moon, the orbital energy and momentum of the system can be conserved, eliminating the need for transfer propellant. Using currently available high-strength tether materials, this system could be built with a total mass of less than 28 times the mass of the payloads it can transport. -
For Immediate Release: TWO GOOGLE LUNAR XPRIZE
Media Contact: Kyoko Yonezawa [email protected] For Immediate Release: TWO GOOGLE LUNAR XPRIZE TEAMS ANNOUNCE RIDESHARE PARTNERSHIP FOR MISSION TO THE MOON IN 2016 Team HAKUTO (Japan) and Team Astrobotic (U.S.) Plan Cooperative Launch in Pursuit of $30 Million Prize to Land a Private Spacecraft on the Lunar Surface TOKYO, Japan (February 24, 2015) – HAKUTO, the only Japanese team competing for the $30 million Google Lunar XPRIZE, has announced a contract with fellow competitor, Astrobotic, based in Pittsburgh, Pa., to carry a pair of rovers to the moon. Astrobotic plans to launch its Google Lunar XPRIZE mission on a SpaceX Falcon 9 rocket from Cape Canaveral, Fla., during the second half of 2016. HAKUTO’s twin rovers, Moonraker and Tetris, will piggyback on Astrobotic's Griffin lander to reach the lunar surface. Upon touchdown, the rovers will be released simultaneously with Astrobotic’s Andy rover, developed by Carnegie Mellon University, travel 500 meters on the moon’s surface and send high-definition images and video back to Earth, all in pursuit of the $20M Google Lunar XPRIZE Grand Prize. Last month, both teams were awarded Google Lunar XPRIZE Milestone Prizes: HAKUTO won $500,000 for technological advancements in the Mobility category, while Astrobotic, in partnership with Carnegie Mellon University, won a total of $1.75M for innovations in all three focus areas—Landing, Mobility and Imaging. Throughout the judging process, all three rovers, Moonraker, Tetris and Andy, demonstrated the ability to move 500 meters across the lunar surface and withstand the high radiation environment and extreme temperatures on the moon. -
NVIDIA Maximus Success Story NVIDIA Maximus Technology Helps Astrobotic Ignite New Era of Moon Exploration When the Google Luna
NVIDIA Maximus Success Story NVIDIA Maximus Technology Helps Astrobotic Ignite New Era of Moon Exploration When the Google Lunar X PRIZE was announced in 2010, Astrobotic Technology was among the first to heed the call. The reward: a total of $30 million, the largest international incentive prize of all time, available to privately funded teams. The challenge: be the first to safely land a robot on the surface of the moon, control the robot to travel 500 meters over the lunar surface, and send high-definition (HD) video, images, and data back to earth. “Astrobotic is a bit like UPS, but for the moon,” said Jason Calaiaro, director of Information Systems for Astrobotic Technology. The company’s primary service is the delivery of payloads – scientific instruments, space agency exploration gear, data collection devices, etc. – to the lunar surface. The Lunar X PRIZE fit nicely with Astrobotic’s goals and business model and promises to provide some high-profile publicity to the company. To help keep its competitive dreams on track, Astrobotic needed to be able to do its complex robot design, structural and vibration analysis, and visualization more quickly and completely. The company upgraded its hardware to include NVIDIA® Maximus™ technology powering Dassault Systèmes SolidWorks, ANSYS, and MathWorks MATLAB software. Not only is this sophisticated technology helping position Astrobotic for Lunar X success, it is also helping to ramp up the company’s main commercial ventures. CHALLENGE Astrobotic was founded in 2008 as a spin-off from the Robotics Institute of Carnegie Mellon University in Pittsburgh, PA, with the mission to build robots able to explore and deliver payloads to the moon, Mars, and beyond. -
EART193 Planetary Capstone
EART193 Planetary Capstone Francis Nimmo Volcanism • Volcanism is an important process on most solar system bodies (either now or in the past) • It gives information on the thermal evolution and interior state of the body • It transports heat, volatiles and radioactive materials from the interior to the surface • Volcanic samples can be accurately dated • Volcanism can influence climate • “Cryovolcanism” can also occur but is less well understood This Week - Interiors • How is melt generated? – What are the heat sources? – How does melt production change over time? • How does it get to the surface? – Density contrasts – Ascent timescale (viscosity) vs. cooling • We will consider conventional (silicate) volcanism and low-temperature cryovolcanism Melting • Only occurs at a single temperature for a pure single-component material. • Most planetary materials are mixtures. Components melt at different temperatures • Solidus: Temperature at which the first melt appears • Liquidus: Temperature at which the last solid crystal disappears Eutectic Phase Diagram Eutectic (Di+An crystallize) Solid Solution Phase diagram Other Effects • Usually have more than two components – Ternary, quaternary diagrams – Computer models (e.g. MELTS) • Pressure – Modifies volume, entropy, melting temperature – Solid-state phase transitions • Volatiles – Water lowers melting temperature – CO2 lowers solubility of water • “Cryo”magmas – At low temperatures, ice behaves like rock – See later Effect of Water on Peridotite melting Clausius-Clapeyron Equation • Melting -
Design a Crew Module Drop Test Data Log Use This Data Log to Record the Results of Each Drop Test
National Aeronautics and DESIGN A Space Administration CREWYour Challenge MODULE Design and build a crew module model that will secure two astronaut figures during a drop test. Do First Watch the instructional video for this module: go.nasa.gov/34hVUvL Astronaut safety is of the highest Design Constraints importance. For Artemis missions, 1) The crew module must safely carry two astronauts. You must design and build a secure NASA’s Orion spacecraft must seat for the astronauts, without gluing or taping them in place. The astronauts should be able to support astronauts stay in their seats during each drop test. for weeks at a time and operate reliably in the harsh space 2) The crew module must fit into the container you chose. This item is simply for size environment. restraints. The crew module must not be dropped while inside the container. 3) The crew module must have one hatch that opens and closes easily. The hatch should remain shut during all drop tests. 4) Your crew module design should consider mass and strength. Mass is important in space travel. The heavier the crew module, the more expensive it is to build and, ultimately, to launch. NASA is looking for a lightweight but strong crew module. Ask and Imagine Think of ways to safely secure two astronauts inside of the crew module. Learn more: • What types of materials will protect the astronauts? Orion Capabilities for Deep Space • How can you reduce the impact on the crew module and astronauts? Enabled Crewed Artemis Moon • What essential elements are needed for crew safety? Missions go.nasa.gov/2GEMBN1 Top 5 Technologies needed for a LET’S GET STARTED! Spacecraft to Survive Deep Space 1.