2020 R&D Achievements
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Suborbital Platforms and Range Services (SPARS)
Suborbital Capabilities for Science & Technology Small Missions Workshop @ Johns Hopkins University June 10, 2019 Mike Hitch, Giovanni Rosanova Goddard Space Introduction Flight Center AGENDAWASP OPIS ▪ Purpose ▪ History & Importance of Suborbital Carriers to Science ▪ Suborbital Platforms ▪ Sounding Rockets ▪ Balloons (brief) ▪ Aircraft ▪ SmallSats ▪ WFF Engineering ▪ Q & A P-3 Maintenance 12-Jun-19 Competition Sensitive – Do Not Distribute 2 Goddard Space Purpose of the Meeting Flight Center Define theWASP OPISutility of Suborbital Carriers & “Small” Missions ▪ Sounding rockets, balloons and aircraft (manned and unmanned) provide a unique capability to scientists and engineers to: ▪ Allow PIs to enhance and advance technology readiness levels of instruments and components for very low relative cost ▪ Provide PIs actual science flight opportunities as a “piggy-back” on a planned mission flight at low relative cost ▪ Increase experience for young and mid-career scientists and engineers by allowing them to get their “feet wet” on a suborbital mission prior to tackling the much larger and more complex orbital endeavors ▪ The Suborbital/Smallsat Platforms And Range Services (SPARS) Line Of Business (LOB) can facilitate prospective PIs with taking advantage of potential suborbital flight opportunities P-3 Maintenance 12-Jun-19 Competition Sensitive – Do Not Distribute 3 Goddard Space Value of Suborbital Research – What’s Different? Flight Center WASP OPIS Different Risk/Mission Assurance Strategy • Payloads are recovered and refurbished. • Re-flights are inexpensive (<$1M for a balloon or sounding rocket vs >$10M - 100M for a ELV) • Instrumentation can be simple and have a large science impact! • Frequent flight opportunities (e.g. “piggyback”) • Development of precursor instrument concepts and mature TRLs • While Suborbital missions fully comply with all Agency Safety policies, the program is designed to take Higher Programmatic Risk – Lower cost – Faster migration of new technology – Smaller more focused efforts, enable Tiger Team/incubator experiences. -
Measurements of Auroral Particles by Means of Sounding Rockets of Mother-Daughter Type A
MEASUREMENTS OF AURORAL PARTICLES BY MEANS OF SOUNDING ROCKETS OF MOTHER-DAUGHTER TYPE A. Falck KGI REPORT 192 NOVEMBER 1985 KIRUNA U-OI'HYSICAL INSTITITK MKINA N\X|1>I\ MEASUREMENTS OF AURORAL PARTICLES BY MEANS OF SOUNDING ROCKETS OF MOTHER-DAUGHTER TYPE by A. Falck Kiruna Geophysical Institute P.O. Box 704, S-981 27 KIRUNA, Sweden KGI Report 192 November 1985 Printed in Sweden Kiruna Geophysical Institute Kiruna 19^5 ISSN 034/-f 405 Contents Page 1. Presentation of the S17 payioads 3 1.1 The scientific objective of the sounding rockets S17 3 1.2 S17 experiments 3 1.3 Physical characteristics of the payioads 3 1.4 Physical characteristics of the Nike-Tomahawk rocket 5 1.5 Nominal characteristics of flight events 7 1.6 Attitude measurements 8 1.7 Separation of the two payload units 20 1.8 Telemetry and data analyzing technique 33 2. Description of the instrumentation for the particle experiments in the S17 payioads 38 2.1 General theory of CEM - detectors 38 2.2 Calibration of th* CEM - detectors 42 2.3 Solid state detectors in SI7 payioads 44 2.4 Mounting of the detectors 48 2.5 The efficiency of channel multipliers 48 3. Review of the geophysical conditions during the SI7 flights and presentation of some supporting observations 51 j.1 The auroral situation during S17 flights 51 :• 2 Magnetic activity 51 .'.3 Other supporting observations 56 .4 The lowlightlevel-TV-system 56 'K Particle fluxes and electric currents coupling the magnetosphere and the ionosphere during a magnetospheric substorm 66 4.1 Review of some substorm terminology and definitions 66 4.2 Reference and comparisons of SI7-2 measure- ments with the results of the IMS-study 75 4.3 Comparison of simultaneous particle observa- tions at low ionospheric altitude (S17-1) and at the magnetic equatorial region (ATS-6) 91 4.4 Summary and conclusions 99 5. -
Colorado Space Grant Consortium
CO_FY16_Year2_APD Colorado Space Grant Consortium Lead Institution: University of Colorado Boulder Director: Chris Koehler Telephone Number: 303.492.3141 Consortium URL: http://spacegrant.colorado.edu Grant Number: NNX15AK04H Lines of Business (LOBs): NASA Internships, Fellowships, and Scholarships; Stem Engagement; Institutional Engagement; Educator Professional Development A. PROGRAM DESCRIPTION The National Space Grant College and Fellowship Program consists of 52 state-based, university- led Space Grant Consortia in each of the 50 states plus the District of Columbia and the Commonwealth of Puerto Rico. Annually, each consortium receives funds to develop and implement student fellowships and scholarships programs; interdisciplinary space-related research infrastructure, education, and public service programs; and cooperative initiatives with industry, research laboratories, and state, local, and other governments. Space Grant operates at the intersection of NASA’s interest as implemented by alignment with the Mission Directorates and the state’s interests. Although it is primarily a higher education program, Space Grant programs encompass the entire length of the education pipeline, including elementary/secondary and informal education. The Colorado Space Grant Consortium is a Designated Consortium funded at a level of $760,000 for fiscal year 2016. B. PROGRAM GOALS • Population of students engaged in COSGC hands-on programs (awardees and non- awardees) will be at least 40% women and 23.7% from ethnic minority populations underrepresented in STEM fields. • Maintain student hands-on programs at all 8 COSGC Minority Serving Institutions and engaged at least 30 students on MSI campuses. • 30% of COSGC NASA funds will be awarded directly to students. • Award 80 scholarships to support students working on hands-on projects. -
S P a C E C U B E Spacecube V3.0 Mini
https://ntrs.nasa.gov/search.jsp?R=20190028775 2019-09-26T19:38:05+00:00Z National Aeronautics and Space Administration SpaceCube v3.0 Mini NASA Next-Generation Data-Processing System for Advanced CubeSat Applications Cody G. Brewer Science Data Processing Branch Software Engineering Division NASA - Goddard Space Flight Center Greenbelt, MD, USA The Twelfth Space Computing Conference S p a c e C u b e July 2019 www.nasa.gov Acronyms Acronym Definition BL-TMR BYU-LANL TMR SEL Single-Event Latchup cFE Core Flight Executive SEM Soft Error Mitigation cFS Core Flight System Spacecraft Supercomputing for Image and Video Center for High-performance Reconfigurable SSIVP Processing CHREC Computing STP-Hx Space Test Program Houston CPU Central Processing Unit TID Total Ionizing Dose CSP CHREC/CubeSat Space Processor TMR Triple Modular Redundancy DSP Digital Signal Processor TRL Technology Readiness Level ELC ExPRESS Logistics Carrier UVSC Ultraviolet Spectro-Coronagraph EM Engineering Model FF Flip-Flop FLT Flight FPGA Field Programmable Gate Array FSM Finite State Machine GMSEC Goddard Mission Services Evolution Center GOPS Giga-Operations Per Second ISA Instruction Set Architecture LEO low-Earth Orbit MGT Multi-Gigabit Transceiver MIPS Million instructions per second NSF National Science Foundation ORS Operationally Responsive Space PCB Printed Circuit Board RE Recuring Engineering SBC Single-Board Computer SCIENCE DATA PROCESSING BRANCH • Code 587 • NASA GSFC 2 SpaceCube v3.0 Mini - NASA Goddard Space Flight Center – July 2019 Outline 1 Introduction -
Methods of Oabservation at Sea Meteorological Soundings in The
WORLD METEOROLOGICAL ORGANIZATION WORLD METEOROLOGICAL ORGANIZATION TECHNICAL NOTE No. 2 TECHNICAL NOTE No. 60 METHODS OF OABSERVATION AT SEA METEOROLOGICAL SOUNDINGS IN THE PARTUPPER I – SEA SURFACEATMOSPHERE TEMPERATURE by W.W. KELLOGG WMO-No.WMO-No. 153. 26. TP. 738 Secretariat of the World Meteorological Organization – Geneva – Switzerland THE WMO The WOTld :Meteol'ological Organization (Wl\IO) is a specialized agency of the United Nations of which 125 States and Territories arc Members. It was created: to facilitate international co~operation in the establishment of networks of stations and centres to provide meteorological services and observationsI to promote the establishment and maintenance of systems for the rapid exchange of meteorological information, to promote standardization of meteorological observations and ensure the uniform publication of observations and statistics. to further the application of rneteol'ology to Rviatioll, shipping, agricultul"C1 and other human activities. to encourage research and training in meteorology. The machinery of the Organization consists of: The World Nleteorological Congress, the supreme body of the o.rganization, brings together the delegates of all Members once every four years to determine general policies for the fulfilment of the purposes of the Organization, to adopt Technical Regulations relating to international meteorological practice and to determine the WMO programme, The Executive Committee is composed of 21 dil'cetors of national meteorological services and meets at least once a yeae to conduct the activities of the Organization and to implement the decisions taken by its Members in Congress, to study and make recommendations Oll matters affecting international meteorology and the opel'ation of meteorological services. -
Importance Oi Thermistor Mount Configuration to Meteorological
James F. Morrissey importance oi and Andrew S. Carten, Jr. thermistor mount configuration A. F. Cambridge Research Laboratories to meteorological rocket Bedford, Mass. temperature measurements Abstract tions. Thus, we are receiving more data than ever be- A description is given of the original rocketsonde ther- fore—thanks to more successful firings and improved mistor mount, consisting of a 10-mil bead suspended signal reception—but data quality has stayed at a low between two metal posts. The difficulties encountered to medium level. Recent evidence, described later in this with this mount and the subsequent development of article, confirms our belief that caution is in order. the superior "thin-film" mount are also described. The Today's rocketsonde is, for the most part, a more uncertainties associated with the use of the latter mount rugged version of the standard radiosonde. This is only are outlined along with their effect on data acceptance. natural, considering both the effort which has gone into A different approach to the original problem is de- refining radiosonde and associated ground equipment scribed, which employs longer leads for dissipation of design and the success which has crowned that effort. heat conducted to the bead. The uncertainty associated In choosing a sensor for the rocketsonde, it was recog- with the long lead is shown to be minimal. Preliminary nized that the small bead thermistor has the necessary results of a series of 10 rocket flights are presented. response time to provide useful measurements to about These results tend to confirm the advantages of the 60 km. A 10-mil diameter bead, aluminized to minimize long lead mount. -
NASA Sounding Rockets Annual Report 2020
National Aeronautics andSpaceAdministration National Aeronautics NASA Sounding Rockets Annual Report 2020 science payload launched on a Terrier-Improved Malemute provided by NASA, experienced a vehicle failure and science data was not recorded. The Cusp Heating Investigation (CHI) for Dr. Larsen, Clemson University, measured neutral upwelling and high-resolution electric fields over an extended region in the cusp, and was a resound- ing success. Additionally, the Cusp-Region Experiment (C-REX) 2 for Dr. Conde, University of Alaska, was staged and ready to go at Andoya Space Center, Norway, however, science conditions did not materialize, and after 17 launch attempts the window of opportunity closed. C-REX 2 is currently on schedule for launch in December 2020. The final geospace science launch for fiscal year 2020 took place from Poker Flat Research Range, Alaska. Polar Night Nitric Oxide Message from the Chief Message Giovanni Rosanova, Jr. (PolarNOx), for Dr. Bailey, Virginia Tech, was successfully launched Chief, Sounding Rockets Program Office in January 2020. Data from PolarNOx will aid in the understanding of the abundance of NO in the polar atmosphere, and its impact on I will start this year’s message with expressing my gratitude to the peo- ozone. ple supporting the sounding rockets program. Through the challeng- ing time of the CoVid-19 pandemic, the outstanding efforts by the Technology development is a core aspects of the program. This year entire team have enabled us to continue meeting several milestones. we launched the eighth dedicated technology development flight, Our mission meetings have been held using virtual tools. Enhanced SubTEC-8. -
Highlights of Dod Research on the ISS
Highlights of DoD Research on the ISS Jim McLeroy Senior Project Engineer DoD Human Spaceflight Payloads Office Houston, Texas 27 June 2012 © The Aerospace Corporation 2010 Executive Summary • The Department of Defense has flown over 270 Experiments on NASA’s Human Spaceflight Vehicles on the Space Shuttle and the International Space Station • The Space Test Program has used every human spaceflight launch vehicle or spacecraft for launch and operations • The Space Test Program accomplishes its mission through a small, cost effective, highly successful team working together with NASA and the International Partners 2 DoD Human Spaceflight Payloads Office • Mission Statement: The DoD Space Test Program-Houston office is the single face to NASA for all DoD payloads on the International Space Station, and other human-rated launch vehicles, both domestic and International Partner – Provide timely space flight for DoD payloads • Assure payload is ready for flight and completes mission objectives • Provide project management support to complete the NASA safety and integration processes • Provide technical integration support to maximize the efficiency and effectiveness of payload design, schedule, and cost Mission: To fly payloads 3 DoD Team at Houston • Houston is unique… • Manned aspect brings great flexibility but also unique safety requirements • Constant high level of interaction with NASA required • “Hands on” approach • Small unit, many projects, “experiment to data” in relatively short period • Return of items from space Launch Site Fabrication Training Operations and Testing Processing DoD personnel are engaged across all these functions 4 DoD Firsts in Human Spaceflght • 1st DoD payload on Shuttle mission STS-4 in 1982 • 1st internal DoD payload on Mir • 1st internal payload on ISS (MACE II, 2000) • 1st external payload on ISS (MISSE 1&2, 2001) • 1st U.S. -
Customer Innovation Issue Xcellxcelljournaljournal SOLUTIONS for a PROGRAMMABLE WORLD
2010 Customer Innovation Issue XcellXcelljournaljournal SOLUTIONS FOR A PROGRAMMABLE WORLD 85,000 to 2.5 Billion Transistors and Beyond: CELEBRATING CUSTOMER INNOVATION www.xilinx.com/xcell/ Development kits help ramp up new Spartan®-6 or Virtex®-6 FPGA designs Avnet Electronics Marketing introduces three new development kits based on the Xilinx Targeted Design Platform (TDP) methodology. Designers now have access to the silicon, software tools and reference designs needed to quickly ramp up new designs. This New baseboards for Spartan®-6 approach accelerates time-to-market and allows you to focus on and Virtex®-6 FPGAs creating truly differentiated products. » Spartan-6LX16EvaluationKit » Spartan-6 LX150T Development Kit Critical to the TDP methodology is the FPGA Mezzanine Card » Virtex-6 LX130T Development Kit (FMC) from the VITA standards body. Avnet has collaborated with several industry-leading semiconductor manufacturers to create a host of FMC modules that add functionality and interfaces to the New FMC Modules for Baseboards new baseboards, allowing for easy customization to meet design- » Dual Image Sensor FMC specific requirements. » DVI I/O FMC » Industrial Ethernet FMC Learn more about the new Spartan-6 and Virtex-6 FPGA baseboards and FMC modules designed by More are soon to be released! Avnet at www.em.avnet.com/drc 1 800 332 8638 ©Avnet, Inc. 2010. All rights reserved. AVNET is a registered trademark of Avnet, Inc. www.em.avnet.com DNV6F6PCIe Six powerful Virtex®-6 FPGAs, up to 24 Million ASIC gates, clock speeds to 710 Mhz: this new board races ahead of last generation solutions. The Dini Group has implemented new Xilinx V6 technology in an easy to use PCIe hosted or stand alone board that features: • 4 DDR3 SODIMMs, up to 4GB per socket • Hosted in a 4-lane PCIe, Gen 1 slot • 4 Serial-ATA ports for high speed data transfer • Easy configuration via PCIe, USB, or GbE • Three independent low-skew global clock networks The higher gate count FPGAs, with 700 MHz LVDS chip to chip interconnects, provide easier logic partitioning. -
Investigation of the In-Flight Failure of the Stratos III Sounding Rocket
ISASI 2019 - Investigation of the in-flight failure of the Stratos III Sounding Rocket Rolf Wubben, Lead Investigator Eoghan Gilleran, General Investigator Krijn de Kievit, General Investigator Bart Kevers, Structural Analysis Maurits van Heijningen, Data Analysis Martin Christiaan Olde, RCA Methodology Delft Aerospace Rocket Engineering, Stevinweg 1 2628 CN Delft, South Holland, The Netherlands The Stratos III sounding rocket is a rocket developed by students from Delft Aerospace Rocket Engineering (DARE) at Delft University of Technology. It is the third generation of the Stratos rocket and was intended to break the European student altitude record of 33.5 km. However, 22.12 seconds into the flight of Stratos III an anomaly occurred, resulting in the loss of the vehicle. At this time, the rocket was travelling at approximately Mach 3 at an altitude of 10 km. An investigation was performed by the students of DARE with the help of Delft University of Technology personnel. The purpose of this report is to show how the investigation was performed, what the results are, how future anomalies can be prevented and how future investigations can be improved. After performing a root cause analysis (RCA) it was determined that inertial roll coupling was the main cause of the Stratos III anomaly. This could be concluded from data provided by on-board inertial measurement units (IMUs) as well as ground radar and Doppler data. This data shows divergence of the sideslip angles of the rocket during flight, until the limit values are reached at the disintegration event. Inertial roll coupling is a complex phenomenon that can be caused by a plethora of different factors, such as the large length to diameter ratio of the rocket or flexibility and misalignment of the rocket body, resulting in both a large effective thrust misalignment as well as an induced aerodynamic pitching moment. -
Sounding Rockets : Principle, Functioning and Applications
Sounding Rockets : Principle, Functioning and Applications Florimond Collette Yann Kempf BASI-P2, Université du Luxembourg Małgorzata Karaś Warsaw School of Economics Abstract Sounding rockets appeared in the mid-20th century and proved to be an extremely useful science tool in all fields of physics and even beyond. These rockets are conceived for sub-orbital flights, to take measurement and/or perform experiments in the high atmosphere, in near space and/or in micro-gravity conditions. They also allow to introduce young scientists to space sciences by undertaking a full-scale pedagogical science project with a relatively moderate cost. This paper presents the origins and principles of sounding rockets, how they work, as well as a few recent science applications. Introduction Sounding rockets are small rockets (vehicles powered by the high-speed ejection of matter through a nozzle) with one or several stages and solid, liquid or hybrid propellant. They perform sub-orbital flights at maximal altitudes ranging from less than 1 km to more than 1200 km. After a thrust phase, they generally have a ballistic flight phase before touching or splashing down. If they have the right equipment, they can be retrieved after the flight. Apart from the engines, sounding rockets comprise a payload made of science experiments performed during the flight, as well as a data processing system, either with real-time radio downlink, or on-board saving. The first case implies real-time tracking by one or more ground telemetry stations. The second case implies recovery of the rocket after the flight to extract the data. Sounding rockets are a privileged tool because they reach zones of the atmospheric and near-space environment that are unaccessible by other means. -
Adapting the Reconfigurable Spacecube Processing
Adapting the Reconfigurable SpaceCube Processing System for Multiple Mission Applications David Petrick, Daniel Espinosa, Robin Ripley, Gary Crum, Alessandro Geist, and Thomas Flatley NASA Goddard Space Flight Greenbelt, MD 20771 [email protected] Abstract—This paper highlights the methodology and slower computer currently used on ISS, as the main avionics effectiveness of adapting the reconfigurable SpaceCube system for two upcoming ISS experiment campaigns. This paper will to solve complex application requirements for a variety of show how we quickly reconfigured the SpaceCube system to space flight missions. SpaceCube is a reconfigurable, modular, meet the more stringent reliability requirements. compact, multi-processing platform for space flight applications demanding extreme processing power. The SpaceCube system is suitable for most mission applications, TABLE OF CONTENTS particularly those that are computationally and data intensive such as instrument science data processing. We will show how 1. INTRODUCTION ............................................... 1 the SpaceCube hybrid processing architecture is used to meet 2. HYBRID FLIGHT COMPUTING ......................... 2 data processing performance requirements that traditional flight processors cannot meet. 3. SPACECUBE V1.0 DESCRIPTION ...................... 2 4. MISSION USE CASES........................................ 6 This paper discusses the flexible computational architecture of 5. CONCLUSIONS ............................................... 17 the SpaceCube system