This Version of the Database Includes Launches Through July 31, 2020
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GT 1020 Datasheet
HARDWARE • DATASHEET GT 1020 Cellular-based telematics for general asset management applications. Complete visibility of transportation and heavy equipment assets, industrial equipment and more. The compact and versatile GT 1020 is designed to fit a wide range of asset tracking 4G LTE cellular applications across various market segments, including transportation, supply communications chain, heavy equipment and maritime. As part of a comprehensive solution that can include cellular connectivity, sensors and a cloud application, the GT 1020 enables remote monitoring of fixed and mobile assets, and delivers actionable data Integrated antennas to ensure complete visibility of operations and enable informed business planning. Feature-rich Quick and easy installation Future proof your solution with global communications over the 4G LTE cellular network with 3G/2G fallback. The GT 1020 features optional Bluetooth support for wireless sensors plus an intelligent reporting system that optimizes power and Compact and rugged airtime usage by adjusting the frequency of location updates based on vehicle motion. An optional CAN Bus interface enables advanced vehicle reporting, analytics and diagnostics, while a backup battery enables reporting for up to 11 Optional CAN Bus support months (depending on reporting frequency) without external power. The device includes a digital input that can be used to report on status changes, such as tire pressure alarms or whether the vehicle is on or off. Feature-rich and versatile Quick and discrete installation Integrated cellular and GPS antennas and mounting options with VHB tape or Long-lasting screws make the GT 1020 quick and easy to install and remove. Its small size backup battery supports covert installations on smaller equipment and assets to deter theft and tampering. -
China Science and Technology Newsletter No. 14
CHINA SCIENCE AND TECHNOLOGY NEWSLETTER Department of International Cooperation No.14 Ministry of Science and Technology(MOST), P.R.China July 25 2014 Special Issue: China’s Space Development Achievements and Prospects of China’s Space Development The 64th IAC Held in Beijing Shenzhou 10 Misson Successfully Accomplished Chang’e 3 Achieved Soft Landing on the Moon GF-1 Satellite - The First Satellite of CHEOS Achievements and Prospects of China’s Space Development Mr. Xu Dazhe, Chairman of China Aerospace Science in 1970 marked the start of China entering into space and and Technology Corporation (CASC) delivered a speech exploring the universe. Due to substantial governmental at the 64th International Astronautical Congress (IAC) on support and promotion, China’s space industry developed September 23, 2013, sharing experiences gained in the quite fast and has made world-known achievements. development of China’s space industry with international As the leader in China’s space sector, CASC is colleagues. assigned to develop, manufacture and test launch OUTSTANDING ACHIEVEMENTS MADE BY vehicles, manned spaceships, various satellites and CHINA’S SPACE INDUSTRY other spacecraft for major national space programs such as China’s Manned Space Program, China’s Lunar China’s space programs have had 57 years of Exploration Program, BeiDou Navigation Satellite development since the 1950s. The successful launch of System, and China’s High-Resolution Earth Observation China’s first artificial satellite Dongfanghong 1 (DFH-1) Monthly-Editorial Board:Building A8 West, Liulinguan Nanli, Haidian District, Beijing 100036, China Contact: Prof.Zhang Ning E-mail: [email protected] [email protected] http://www.caistc.com System. -
By Tamman Montanaro
4 Reusable First Stage Rockets y1 = 15.338 m m1 = 2.047 x 10 kg 5 y2 = 5.115 m m2 = 1.613 x 10 kg By Tamman Montanaro What is the moment of inertia? What is the force required from the cold gas thrusters if we assume constancy. Figure 1. Robbert Goddard’s design of the first ever rocket to fly in 1926. Source: George Edward Pendray. The moment of inertia of a solid disk: rper The Rocket Formula Now lets stack a bunch of these solid disk on each other: Length = l Divide by dt Figure 2: Flight path for the Falcon 9; After separation, the first stage orientates itself and prepares itself for landing. Source: SpaceX If we do the same for the hollow cylinder, we get a moment of inertia Launch of: Specific impulse for a rocket: How much mass is lost? What is the mass loss? What is the moment of inertia about the center of mass for these two objects? Divide by m Figure 3: Falcon 9 first stage after landing on drone barge. Source: SpaceX nd On December 22 2015, the Falcon 9 Orbcomm-2 What is the constant force required for its journey halfway (assuming first stage lands successfully. This is the first ever orbital- that the force required to flip it 90o is the equal and opposite to class rocket landing. From the video and flight logs, we Flip Maneuver stabilize the flip). can gather specifications about the first stage. ⃑ How much time does it take for the first stage to descend? We assume this is the time it takes � Flight Specifications for the first stage to reorientate itself. -
Kaluza-Klein Gravity, Concentrating on the General Rel- Ativity, Rather Than Particle Physics Side of the Subject
Kaluza-Klein Gravity J. M. Overduin Department of Physics and Astronomy, University of Victoria, P.O. Box 3055, Victoria, British Columbia, Canada, V8W 3P6 and P. S. Wesson Department of Physics, University of Waterloo, Ontario, Canada N2L 3G1 and Gravity Probe-B, Hansen Physics Laboratories, Stanford University, Stanford, California, U.S.A. 94305 Abstract We review higher-dimensional unified theories from the general relativity, rather than the particle physics side. Three distinct approaches to the subject are identi- fied and contrasted: compactified, projective and noncompactified. We discuss the cosmological and astrophysical implications of extra dimensions, and conclude that none of the three approaches can be ruled out on observational grounds at the present time. arXiv:gr-qc/9805018v1 7 May 1998 Preprint submitted to Elsevier Preprint 3 February 2008 1 Introduction Kaluza’s [1] achievement was to show that five-dimensional general relativity contains both Einstein’s four-dimensional theory of gravity and Maxwell’s the- ory of electromagnetism. He however imposed a somewhat artificial restriction (the cylinder condition) on the coordinates, essentially barring the fifth one a priori from making a direct appearance in the laws of physics. Klein’s [2] con- tribution was to make this restriction less artificial by suggesting a plausible physical basis for it in compactification of the fifth dimension. This idea was enthusiastically received by unified-field theorists, and when the time came to include the strong and weak forces by extending Kaluza’s mechanism to higher dimensions, it was assumed that these too would be compact. This line of thinking has led through eleven-dimensional supergravity theories in the 1980s to the current favorite contenders for a possible “theory of everything,” ten-dimensional superstrings. -
Dod Space Technology Guide
Foreword Space-based capabilities are integral to the U.S.’s national security operational doctrines and processes. Such capa- bilities as reliable, real-time high-bandwidth communica- tions can provide an invaluable combat advantage in terms of clarity of command intentions and flexibility in the face of operational changes. Satellite-generated knowledge of enemy dispositions and movements can be and has been exploited by U.S. and allied commanders to achieve deci- sive victories. Precision navigation and weather data from space permit optimal force disposition, maneuver, decision- making, and responsiveness. At the same time, space systems focused on strategic nuclear assets have enabled the National Command Authorities to act with confidence during times of crisis, secure in their understanding of the strategic force postures. Access to space and the advantages deriving from operat- ing in space are being affected by technological progress If our Armed Forces are to be throughout the world. As in other areas of technology, the faster, more lethal, and more precise in 2020 advantages our military derives from its uses of space are than they are today, we must continue to dynamic. Current space capabilities derive from prior invest in and develop new military capabilities. decades of technology development and application. Joint Vision 2020 Future capabilities will depend on space technology programs of today. Thus, continuing investment in space technologies is needed to maintain the “full spectrum dominance” called for by Joint Vision 2010 and 2020, and to protect freedom of access to space by all law-abiding nations. Trends in the availability and directions of technology clearly suggest that the U.S. -
Enhanced Orbit Determination for Beidou Satellites with Fengyun-3C Onboard GNSS Data
GPS Solut DOI 10.1007/s10291-017-0604-y ORIGINAL ARTICLE Enhanced orbit determination for BeiDou satellites with FengYun-3C onboard GNSS data 1,2 1 1 3 3 Qile Zhao • Chen Wang • Jing Guo • Guanglin Yang • Mi Liao • 1 1,2 Hongyang Ma • Jingnan Liu Received: 3 September 2016 / Accepted: 27 January 2017 Ó The Author(s) 2017. This article is published with open access at Springerlink.com Abstract A key limitation for precise orbit determination (Root Mean Square) of overlapping orbit differences of BeiDou satellites, particularly for satellites in geosta- (OODs) is 2.3 cm for GPS-only solution. The 3D RMS of tionary orbit (GEO), is the relative weak geometry of orbit differences between BeiDou-only and GPS-only ground stations. Fortunately, data from a low earth orbiting solutions is 15.8 cm. Also, precise orbits and clocks for satellite with an onboard GNSS receiver can improve the BeiDou satellites were determined based on 97 global geometry of GNSS orbit determination compared to using (termed GN) or 15 regional (termed RN) ground stations. only ground data. The Chinese FengYun-3C (FY3C) Furthermore, also using FY3C onboard BeiDou data, two satellite carries the GNSS Occultation Sounder equipment additional sets of BeiDou orbit and clock products are with both dual-frequency GPS (L1 and L2) and BeiDou determined with the data from global (termed GW) or (B1 and B2) tracking capacity. The satellite-induced vari- regional (termed RW) stations. In general, the OODs ations in pseudoranges have been estimated from multipath decrease for BeiDou satellites, particularly for GEO observables using an elevation-dependent piece-wise linear satellites, when the FY3C onboard BeiDou data are added. -
6. the INTELSAT 17 Satellite
TWO COMMUNICATIONS SATELLITES READY FOR LAUNCH Arianespace will orbit two communications satellite on its fifth launch of the year: INTELSAT 17 for the international satellite operator Intelsat, and HYLAS 1 for the European operator Avanti Communications. The choice of Arianespace by leading space communications operators and manufacturers is clear international recognition of the company’s excellence in launch services. Based on its proven reliability and availability, Arianespace continues to confirm its position as the world’s benchmark launch system. Ariane 5 is the only commercial satellite launcher now on the market capable of simultaneously launching two payloads. Arianespace and Intelsat have built up a long-standing relationship based on mutual trust. Since 1983, Arianespace has launched 48 satellites for Intelsat. Positioned at 66 degrees East, INTELSAT 17 will deliver a wide range of communication services for Europe, the Middle East, Russia and Asia. Built by Space Systems/Loral of the United States, this powerful satellite will weigh 5,540 kg at launch. It will also enable Intelsat to expand its successful Asian video distrubution neighborhood. INTELSAT 17 will replace INTELSAT 702. HYLAS 1 is Avanti Communications’ first satellite. A new European satellite operator, Avanti Communications also chose Arianespace to orbit its HYLAS 2 satellite, scheduled for launch in the first half of 2012. HYLAS 1 was built by an industrial consortium formed by EADS Astrium and the Indian Space Research Organisation (ISRO), using a I-2K platform. Fitted with Ka-band and Ku-band transponders, the satellite will be positioned at 33.5 degrees West, and will be the first European satellite to offer high-speed broadband services across all of Europe. -
What Is Gravity Probe B? a Quest for Experimental Truth the GP-B Flight
What is Gravity Probe B? than Gravity Probe B. It’s just a star, a telescope, and a spinning sphere.” However, it took the exceptional collaboration of Stanford, Gravity Probe B (GP-B) is a NASA physics mission to experimentally MSFC, Lockheed Martin and a host of others more than four decades investigate Einstein’s 1916 general theory of relativity—his theory of gravity. to develop the ultra-precise gyroscopes and the other cutting- GP-B uses four spherical gyroscopes and a telescope, housed in a satellite edge technologies necessary to carry out this “simple” experiment. orbiting 642 km (400 mi) above the Earth, to measure, with unprecedented accuracy, two extraordinary effects predicted by the general theory of rela- The GP-B Flight Mission & Data Analysis tivity: 1) the geodetic effect—the amount by which the Earth warps the local spacetime in which it resides; and 2) the frame-dragging effect—the amount On April 20, 2004 at 9:57:24 AM PDT, a crowd of over 2,000 current and by which the rotating Earth drags its local spacetime around with it. GP-B former GP-B team members and supporters watched and cheered as the tests these two effects by precisely measuring the precession (displacement) GP-B spacecraft lifted off from Vandenberg Air Force Base. That emotionally angles of the spin axes of the four gyros over the course of a year and com- overwhelming day, culminating with the extraordinary live video of paring these experimental results with predictions from Einstein’s theory. the spacecraft separating from the second stage booster meant, as GP-B Program Manager Gaylord Green put it, “that 10,000 things went right.” A Quest for Experimental Truth Once in orbit, the spacecraft first underwent a four-month Initialization The idea of testing general relativity with orbiting gyroscopes was sug- and Orbit Checkout (IOC), in which all systems and instruments were gested independently by two physicists, George Pugh and Leonard Schiff, initialized, tested, and optimized for the data collection to follow. -
In This Issue
Vol. 39 No.4, January 2014 Editor: Jos Heyman FBIS In this issue: Satellite Update 3 Cancelled Projects: X-33 4 News Apstar-9 2 AsiaSat-9 7 ICESat-2 7 ISS 7 KSC launch Pad 39A 6 L2 and L3 Missions 2 Mars One 7 NROL-39 6 Panasonic 6 Robonaut-2 3 SGDC 2 SOAR 7 Soyuz 2-1v/Volga 7 TDRS-L 5 Tupac Katari-1 2 TIROS SPACE INFORMATION SGDC 86 Barnevelder Bend, Southern River WA 6110, Australia Tel + 61 8 9398 1322 Brazil has ordered a civil-military communications satellite from Thales Alenia Space using the (e-mail: [email protected]) Spacebus 4000 platform. The Tiros Space Information (TSI) - News Bulletin is published to promote the scientific exploration and To be known as the Satélite Geoestacionário de Defesa e Comunicações Estratégicas (SGDC) commercial application of space through the dissemination of current news and historical facts. (for Geostationary and Defense and Strategic Communications Satellite), it will carry 50 Ka In doing so, Tiros Space Information continues the traditions of the Western Australian Branch of the band transponders. Apart from the military applications, the satellite will also be used to extend Astronautical Society of Australia (1973-1975) and the Astronautical Society of Western Australia (ASWA) internet communications throughout Brazil. (1975-2006). Launch by an Ariane 5 launch vehicle is expected in 2017. The News Bulletin can be received worldwide by e-mail subscription only. Subscriptions can be requested by sending an e-mail address to [email protected]. Tiros Space Information reserves the right to refuse any subscription request without the need to provide a reason. -
Cubesat Data Analysis Revision
371-XXXXX Revision - CubeSat Data Analysis Revision - November 2015 Prepared by: GSFC/Code 371 National Aeronautics and Goddard Space Flight Center Space Administration Greenbelt, Maryland 20771 371-XXXXX Revision - Signature Page Prepared by: ___________________ _____ Mark Kaminskiy Date Reliability Engineer ARES Corporation Accepted by: _______________________ _____ Nasir Kashem Date Reliability Lead NASA/GSFC Code 371 1 371-XXXXX Revision - DOCUMENT CHANGE RECORD REV DATE DESCRIPTION OF CHANGE LEVEL APPROVED - Baseline Release 2 371-XXXXX Revision - Table of Contents 1 Introduction 4 2 Statement of Work 5 3 Database 5 4 Distributions by Satellite Classes, Users, Mass, and Volume 7 4.1 Distribution by satellite classes 7 4.2 Distribution by satellite users 8 4.3 CubeSat Distribution by mass 8 4.4 CubeSat Distribution by volume 8 5 Annual Number of CubeSats Launched 9 6 Reliability Data Analysis 10 6.1 Introducing “Time to Event” variable 10 6.2 Probability of a Successful Launch 10 6.3 Estimation of Probability of Mission Success after Successful Launch. Kaplan-Meier Nonparametric Estimate and Weibull Distribution. 10 6.3.1 Kaplan-Meier Estimate 10 6.3.2 Weibull Distribution Estimation 11 6.4 Estimation of Probability of mission success after successful launch as a function of time and satellite mass using Weibull Regression 13 6.4.1 Weibull Regression 13 6.4.2 Data used for estimation of the model parameters 13 6.4.3 Comparison of the Kaplan-Meier estimates of the Reliability function and the estimates based on the Weibull regression 16 7 Conclusion 17 8 Acknowledgement 18 9 References 18 10 Appendix 19 Table of Figures Figure 4-1 CubeSats distribution by mass .................................................................................................... -
Thesis Submitted to Florida Institute of Technology in Partial Fulfllment of the Requirements for the Degree Of
Dynamics of Spacecraft Orbital Refueling by Casey Clark Bachelor of Aerospace Engineering Mechanical & Aerospace Engineering College of Engineering 2016 A thesis submitted to Florida Institute of Technology in partial fulfllment of the requirements for the degree of Master of Science in Aerospace Engineering Melbourne, Florida July, 2018 ⃝c Copyright 2018 Casey Clark All Rights Reserved The author grants permission to make single copies. We the undersigned committee hereby approve the attached thesis Dynamics of Spacecraft Orbital Refueling by Casey Clark Dr. Tiauw Go, Sc.D. Associate Professor. Mechanical & Aerospace Engineering Committee Chair Dr. Jay Kovats, Ph.D. Associate Professor Mathematics Outside Committee Member Dr. Markus Wilde, Ph.D. Assistant Professor Mechanical & Aerospace Engineering Committee Member Dr. Hamid Hefazi, Ph.D. Professor and Department Head Mechanical & Aerospace Engineering ABSTRACT Title: Dynamics of Spacecraft Orbital Refueling Author: Casey Clark Major Advisor: Dr. Tiauw Go, Sc.D. A quantitative collation of relevant parameters for successfully completed exper- imental on-orbit fuid transfers and anticipated orbital refueling future missions is performed. The dynamics of connected satellites sustaining fuel transfer are derived by treating the connected spacecraft as a rigid body and including an in- ternal mass fow rate. An orbital refueling results in a time-varying local center of mass related to the connected spacecraft. This is accounted for by incorporating a constant mass fow rate in the inertia tensor. Simulations of the equations of motion are performed using the values of the parameters of authentic missions in an endeavor to provide conclusions regarding the efect of an internal mass transfer on the attitude of refueling spacecraft. -
SIGINT: the Mission Cubesats Are Made for a Small Country’S Perspective
Naval Research Laboratory 22 June 1960 SIGINT: The Mission CubeSats are Made For A Small Country’s Perspective 32nd Annual AIAA/USU Conference on Small Satellites 1 ISIS - Innovative Solutions In Space Vertically Integrated Small Satellite Company SATELLITE CUBESAT LAUNCH SERVICES R&D SERVICES SOLUTIONS PRODUCTS 2 SIGINT – ELINT – Spectrum Monitoring SIGINT SpectrumCOMINT Monitoring ELINT FISINT/TELINT TECHNICAL OPERATIONAL • Discover new systems • Location • Details about emissions • Schedule • Performance estimation • Movement • ECM development • Warning 3 Spectrum Monitoring Causes of Interference Source: Eutelsat briefing to the ITU (2013) 4 Miniturization 5 ELINT: Single-Satellite Solution Lotos-S/Pion-NKS 8 - 12 m Images courtesy of RussianSpaceWeb 6 ELINT: Direction Finding Direction of Arrival/Angle of Arrival 7 Fundamental Limits Why the Shrink-Ray Won’t Work Size has effect on direction finding accuracy because of: • Antenna gain (i.e. SNR) • Number of array elements that can be placed • Array element spacing A 6U-face of CubeSat offers very limited real estate Images courtesy of NASA 8 BRIK-II Royal Netherlannds Air Force 9 ELINT: Multi-Satellite Solution Naval Ocean Surveillance System Picture by John C. Murphy 10 Capacité de Renseignement Electromagnétique Spatiale (CERES) 781 M€ Essaim 216 M€ 2004 Elisa 115 M€ 2007 2009 2011 CERES 450 M€ 2013 2015 2020 Images courtesy of CNES 11 Miniturization through Distribution Opening Up The Trade Space Number of satellites in orbit Image courtesy of the Science and Technology Policy Institute 12 Radio Astronomy An Intransparent Affair 13 Orbiting Low Frequency Antennas for Radio Astronomy < 100 km > 50 satellites = 0.006° (30 MHz) 14 Maturing CubeSats for ELINT/Spectrum Monitoring & Astronomy Development Areas Station-Keeping ISL & Synchronization 2-100 Satellites Relative Position Knowledge From A.