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Rideshare and the Orbital Maneuvering Vehicle: the Key to Low-Cost Lagrange-Point Missions
SSC15-II-5 Rideshare and the Orbital Maneuvering Vehicle: the Key to Low-cost Lagrange-point Missions Chris Pearson, Marissa Stender, Christopher Loghry, Joe Maly, Valentin Ivanitski Moog Integrated Systems 1113 Washington Avenue, Suite 300, Golden, CO, 80401; 303 216 9777, extension 204 [email protected] Mina Cappuccio, Darin Foreman, Ken Galal, David Mauro NASA Ames Research Center PO Box 1000, M/S 213-4, Moffett Field, CA 94035-1000; 650 604 1313 [email protected] Keats Wilkie, Paul Speth, Trevor Jackson, Will Scott NASA Langley Research Center 4 West Taylor Street, Mail Stop 230, Hampton, VA, 23681; 757 864 420 [email protected] ABSTRACT Rideshare is a well proven approach, in both LEO and GEO, enabling low-cost space access through splitting of launch charges between multiple passengers. Demand exists from users to operate payloads at Lagrange points, but a lack of regular rides results in a deficiency in rideshare opportunities. As a result, such mission architectures currently rely on a costly dedicated launch. NASA and Moog have jointly studied the technical feasibility, risk and cost of using an Orbital Maneuvering Vehicle (OMV) to offer Lagrange point rideshare opportunities. This OMV would be launched as a secondary passenger on a commercial rocket into Geostationary Transfer Orbit (GTO) and utilize the Moog ESPA secondary launch adapter. The OMV is effectively a free flying spacecraft comprising a full suite of avionics and a propulsion system capable of performing GTO to Lagrange point transfer via a weak stability boundary orbit. In addition to traditional OMV ’tug’ functionality, scenarios using the OMV to host payloads for operation at the Lagrange points have also been analyzed. -
Cubesat Mission: from Design to Operation
applied sciences Article CubeSat Mission: From Design to Operation Cristóbal Nieto-Peroy 1 and M. Reza Emami 1,2,* 1 Onboard Space Systems Group, Department of Computer Science, Electrical and Space Engineering, Luleå University of Technology, Space Campus, 981 92 Kiruna, Sweden 2 Aerospace Mechatronics Group, University of Toronto Institute for Aerospace Studies, Toronto, ON M3H 5T6, Canada * Correspondence: [email protected]; Tel.: +1-416-946-3357 Received: 30 June 2019; Accepted: 29 July 2019; Published: 1 August 2019 Featured Application: Design, fabrication, testing, launch and operation of a particular CubeSat are detailed, as a reference for prospective developers of CubeSat missions. Abstract: The current success rate of CubeSat missions, particularly for first-time developers, may discourage non-profit organizations to start new projects. CubeSat development teams may not be able to dedicate the resources that are necessary to maintain Quality Assurance as it is performed for the reliable conventional satellite projects. This paper discusses the structured life-cycle of a CubeSat project, using as a reference the authors’ recent experience of developing and operating a 2U CubeSat, called qbee50-LTU-OC, as part of the QB50 mission. This paper also provides a critique of some of the current poor practices and methodologies while carrying out CubeSat projects. Keywords: CubeSat; miniaturized satellite; nanosatellite; small satellite development 1. Introduction There have been nearly 1000 CubeSats launched to the orbit since the inception of the concept in 2000 [1]. An up-to-date statistics of CubeSat missions can be found in Reference [2]. A summary of CubeSat missions up to 2016 can also be found in Reference [3]. -
Geoscan: a Geoscience Facility from Space
SSC12-IV-9 GEOScan: A GEOScience Facility From Space Lars P. Dyrud, Jonathan T. Fentzke, Gary Bust, Bob Erlandson, Brian Bauer, and Aaron Q. Rogers The Johns Hopkins University Applied Physics Laboratory 11101 Johns Hopkins Road, Laurel, MD 20723-6099 USA; (240) 543-5117 [email protected] Warren Wiscombe Brian Gunter NASA Goddard Space Flight Center Dept. of Aerospace Engineering, Technical Univ. Delft Greenbelt Road, Greenbelt, MD 20770 USA Bldg. 62, Kluyverweg 1, 2629 HS Delft, The Netherlands Shawn Murphy Kerri Cahoy Charles Stark Draper Laboratory Dept. of Aeronautics and Astronautics, MIT 555 Technology Square, 77 Massachusetts Avenue, 33-207, Cambridge, MA 02139 USA Cambridge, MA 02139 USA Rebecca Bishop Chad Fish The Aerospace Corporation Space Dynamics Laboratory 2310 E. El Segundo Blvd., 1695 North Research Park Way, El Segundo, CA 90245-4609 USA North Logan, UT 84341 USA Om Gupta Iridium Communications Inc. 1750 Tysons Blvd., McLean, VA 22102-4244 USA ABSTRACT GEOScan, proposed as a globally networked orbiting facility utilizing Iridium NEXT’s 66-satellite constellation, will provide revolutionary, massively dense global geoscience observations and targets questions scientists have not been able to answer, and will not answer, until simultaneous global measurements are made. GEOScan dramatically lowers the logistical and cost barriers for transmitting “big data” from 66 satellites by using Iridium’s communications platform and commercial-off-the-shelf components. Iridium’s Hosted Payload Program facilitates the effort, but -
The Annual Compendium of Commercial Space Transportation: 2017
Federal Aviation Administration The Annual Compendium of Commercial Space Transportation: 2017 January 2017 Annual Compendium of Commercial Space Transportation: 2017 i Contents About the FAA Office of Commercial Space Transportation The Federal Aviation Administration’s Office of Commercial Space Transportation (FAA AST) licenses and regulates U.S. commercial space launch and reentry activity, as well as the operation of non-federal launch and reentry sites, as authorized by Executive Order 12465 and Title 51 United States Code, Subtitle V, Chapter 509 (formerly the Commercial Space Launch Act). FAA AST’s mission is to ensure public health and safety and the safety of property while protecting the national security and foreign policy interests of the United States during commercial launch and reentry operations. In addition, FAA AST is directed to encourage, facilitate, and promote commercial space launches and reentries. Additional information concerning commercial space transportation can be found on FAA AST’s website: http://www.faa.gov/go/ast Cover art: Phil Smith, The Tauri Group (2017) Publication produced for FAA AST by The Tauri Group under contract. NOTICE Use of trade names or names of manufacturers in this document does not constitute an official endorsement of such products or manufacturers, either expressed or implied, by the Federal Aviation Administration. ii Annual Compendium of Commercial Space Transportation: 2017 GENERAL CONTENTS Executive Summary 1 Introduction 5 Launch Vehicles 9 Launch and Reentry Sites 21 Payloads 35 2016 Launch Events 39 2017 Annual Commercial Space Transportation Forecast 45 Space Transportation Law and Policy 83 Appendices 89 Orbital Launch Vehicle Fact Sheets 100 iii Contents DETAILED CONTENTS EXECUTIVE SUMMARY . -
Iridium NEXT Sensorpods: Global Access for Your Scientific Payloads Dr
SSC11-IV-6 Iridium NEXT SensorPODs: Global access for your scientific payloads Dr. Om P. Gupta Iridium Communications Inc. 1750 Tyson Blvd, McLean, VA, USA +1-703-287-7427 [email protected] ABSTRACT The operational Iridium constellation is comprised of 66 satellites in low Earth orbit at 781 km and inclination of 86.4°, resulting in unprecedented 24/7 coverage and real-time visibility of the entire globe. Recently, through funding from the National Science Foundation (NSF), Iridium has been utilized for a unique scientific experiment called the Active Magnetosphere and Planetary Electrodynamics Response Experiment (AMPERE). AMPERE provides real-time magnetic field measurements using the existing Iridium constellation as part of a new observation network to forecast weather in space. In February 2007, Iridium announced Iridium NEXT, a novel design for a second-generation satellite constellation. Anticipated to begin launching in 2015, Iridium NEXT will maintain the existing Iridium constellation architecture of 66 cross-linked low-Earth Orbit (LEO) satellites covering 100% of the globe. Iridium NEXT will also offer new Earth and space observation opportunities through hosted payloads (up to 50 Kg) on the Iridium NEXT satellite network. Recently, Iridium introduced a new hosting concept called “SensorPOD” for smaller scientific payloads (up to 5 Kg). SensorPODs will offer unique benefits such as unprecedented spatial and temporal coverage, and real- time relay of data to and from SensorPODs. SensorPODs are housed in a 4U frame (20 cm x 20 cm x 14 cm). Scientists provide just the payload; all other spacecraft bus functions such as power, data transfer, and attitude control are provided by Iridium NEXT. -
Increasing Launch Rate and Payload Capabilities
Aerial Launch Vehicles: Increasing Launch Rate and Payload Capabilities Yves Tscheuschner1 and Alec B. Devereaux2 University of Colorado, Boulder, Colorado Two of man's greatest achievements have been the first flight at Kitty Hawk and pushing into the final frontier that is space. Air launch systems aim to combine these great achievements into a revolutionary way to deliver satellites, cargo and eventually people into space. Launching from an aircraft has many advantages, including the ability to launch at any inclination and from above bad weather, which could delay ground launches. While many concepts for launching rockets from an airplane have been developed, very few have made it past the drawing board. Only the Pegasus and, to a lesser extent, SpaceShipOne have truly shown the feasibility of such a system. However, a recent push for rapid, small payload to orbit launches by the military and a general need for cheaper, heavy lift options are leading to an increasing interest in air launch methods. In order for the efficiency and flexibility of the system to be realized, however, additional funding and research are necessary. Nomenclature ALASA = airborne launch assist space access ALS = air launch system DARPA = defense advanced research project agency LEO = low Earth orbit LOX = liquid oxygen RP-1 = rocket propellant 1 MAKS = Russian air launch system MECO = main engine cutoff SS1 = space ship one SS2 = space ship two I. Introduction W hat typically comes to mind when considering launching people or satellites to space are the towering rocket poised on the launch pad. These images are engraved in the minds of both the public and scientists alike. -
Paper Session II-B-National Launch System Payload Accommodations
The Space Congress® Proceedings 1992 (29th) Space - Quest For New Fontiers Apr 22nd, 2:00 PM Paper Session II-B - National Launch System Payload Accommodations Capt James M. Knauf National Launch System Requirements Officer HQ Airor F ce Space Command Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Knauf, Capt James M., "Paper Session II-B - National Launch System Payload Accommodations" (1992). The Space Congress® Proceedings. 15. https://commons.erau.edu/space-congress-proceedings/proceedings-1992-29th/april-22-1992/15 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]. NATIONAL LAUNCH SYSTEM PAYLOAD ACCOMMODATIONS Capt James M. Knauf National Launch System Requirements Officer HQ Air Force Space Command - Peterson AFB, CO ABSTRACT Early definition, documentation, acceptance, and continuing implementation of a standard system of payload accommodations for space launch systems is essential. Attempts to provide truly standard payload accommodations have not met with significant success in increasing responsiveness or reducing operations costs. The operational philosophy of the National Launch System (NLS) is based on standardization and includes standardized payload accommodations. These must be incorporated into NLS design concepts early in the development phase to ensure the NLS goal of increased responsiveness and reduced operating cost. At the same time, sufficient flexibility will be maintained to accommodate the rare unique payload requirement which cannot meet the standard due to specific mission requirements, safety concerns, or other reasons. -
Integrated Spacecraft/Payload Element Fact Sheet
National Aeronautics and Space Administration Space Launch System Integrated Spacecraft/ Payload Element NASA’s Space Launch System (SLS) will pro- vide the agency with super heavy-lift capability to return astronauts to the Moon and launch payloads to the Moon or deeper into the solar system. The integrated spacecraft/payload element for the initial SLS configuration, called Block 1, consists of the upper stage and payload section facts of the rocket, above the core stage, including adapters and separation systems. In the SLS Block 1 crew configuration, the inte- grated spacecraft/payload element connects the core stage to the Orion crew vehicle. In the Block 1 cargo variant, the integrated spacecraft/ payload element sits at the top of the vehicle, above the core stage, and includes a 5 meter- diameter payload fairing that encapsulates the payload. NASA is building the super heavy-lift SLS rocket to send astronauts in Orion to the Moon and NASA to launch cargo and scientific payloads to the Moon or deep into the solar system. Block 1 is the initial launcher, with progressively more powerful vehicles planned for the future to SLS Block 1 will be used for NASA’s first Artemis enable NASA to establish a sustainable pres- missions. The initial flight, Artemis I, is a test of ence at the Moon before sending humans to the new system – including Orion and ground sys- Mars. tems at Kennedy Space Center – and will include deployment of 13 CubeSats. The integrated spacecraft/payload element on the Block 1 crew vehicle is comprised of the In- The next flight, Artemis II, is a lunar flyby mission terim Cryogenic Propulsion Stage (ICPS), which that will make astronauts in Orion the record- provides in-space propulsion, the Launch Ve- holders for farthest distance humans have trav- hicle Stage Adapter (LVSA), and the Orion Stage eled from Earth. -
Analysis of a Heavy Lift Launch Vehicle Design Using Small Liquid
Analysis of a Heavy Lift Launch Vehicle Design Using Small Liquid Rocket Engines by DAVID PHILLIP RUSS S.B., Massachusetts Institute of Technology 1987 SUBMITTED IN PARTIAL FULFILLMENT OF THE REQUIREMENTS FOR THE DEGREE OF MASTER OF SCIENCE IN AERONAUTICS AND ASTRONAUTICS at the MASSACHUSETTS INSTITUTE OF TECHNOLOGY May 1988 ® David P. Russ 1988 The author hereby grants M.I.T. and Hughes Aircraft Company permission to reproduce and to distribute copies of this thesis document in whole or in part. Signature of Author Department of Aeronautics and Astronautics December 18, 1987 Reviewed by C. P. Rubin Hughes Aircraft Company Certified by Professor Walter M. Hollister Thesis Supervjsor, Departmer of Aeronautics and Astronautics .. Accepted by , .AU Professor Harold Y. Wachman Chairman, Depart'rmental Graduate Committee Department of Aeronautics and Astronautics MAY i od ;WITHDRAWfIN i M.I.1W.i..: P. I LBRARt S UBAer 7:Ir_ Aero Analysis of a Heavy Lift Launch Vehicle Design Using Small Liquid Rocket Engines by David P. Russ Submitted to the Department of Aeronautics and Astronautics in partial fulfillment of the requirements for the degree of Master of Science in Aeronautics and Astronautics May, 1988 Abstract The trend in launch vehicle design has been to increase performance by using en- gines of greater and greater complexity, which has a negative effect on cost and reliability. However, a design making use of over 300 small, simple rocket engines can deliver over 340,000 lbs to low Earth orbit. This design, derived by using the rocket equations to size the major components, features a 42 ft. -
Hosted Payload Interface Guide for Proposers
Common Instrument Interface Project Hosted Payload Interface Guide for Proposers Mar. 22, 2018 Hosted Payload Interface Document Version: Initial Document No: HPIG0001 Effective 3/22/2018 Page 1 of 119 Submitted By: Nikzad Toomarian (signed) ___________________________ Nikzad Toomarian JPL/CII Project Lowell E. Primm (signed) ___________________________ Lowell E. Primm GSFC/CII Project Manager C. Randy Regan (signed) ___________________________ C. Randy Regan NASA ESSP PO Chief Engineer Approved By: ___________________________ ___________________________ Gregory Stover (signed) 22 Mar., 2018 ___________________________ ___________________________ Gregory Stover Date NASA ESSP PO Program Director Hosted Payload Interface Document Version: Initial Document No: HPIG0001 Effective 3/22/2018 Page 2 of 119 Change Log Section Version Date Affected Description Hosted Payload Interface Document Version: Initial Document No: HPIG0001 Effective 3/22/2018 Page 3 of 119 Special Acknowledgement The development of the Hosted Payloads Interface Guide (HPIG) is the direct result of a collaborative effort between the NASA Common Instrument Interface (CII) Project, the Earth System Science Pathfinder Program Office, the USAF Space and Missile Center’s Hosted Payload Office, and The Aerospace Corporation. The HPIG provides a prospective Instrument Developer with technical recommendations to assist them in designing an Instrument or Payload that may be flown as a hosted payload on commercial satellites flown in Low Earth Orbit (LEO), or Geostationary Earth Orbit (GEO). The document is now in its second iteration, with several updates and improvements. We wish to express a special thanks to our teammates within the USAF Space and Missile Center’s Hosted Payload Office, and The Aerospace Corporation. Their contributions have been remarkable, timely, and accurate. -
SPACE-EU Conference the Role of Satellite Telecommunications
SPACE-EU Conference The role of Satellite Telecommunications February 2012 – Christine Leurquin SES – Who we are A world-leading telecommunications satellite operator Premier provider of transmission capacity, related platforms and services worldwide for • media • enterprise and telcos • government and institutions Headquartered in Luxembourg, with 1,200 staff worldwide Listed on Euronext Paris and the Luxembourg Stock Exchange One platform, global reach ▲ Global fleet of 50 satellites provides comprehensive coverage ▲ Coverage for 99% of the world’s population ▲ A well-connected teleport infrastructure ▲ Leading direct-to-home(DTH) satellite operator in Europe ▲ Major supplier to cable headends in the Americas ▲ Hosts some of the fastest-growing DTH platforms in emerging markets Improving our service by expanding our regional teams 3 Satellite Telecommunications: a key pillar of European Space Policy “With the gradual maturation of space technologies and systems, satellite applications have become the main source of revenue for the European space industry, and the main driver for business growth for the European industry, particularly within commercial markets for telecommunications systems.” (Eurospace Facts and Figures 2011, p.10) Satellite telecommunications accounts for 63% of the manufacturing of satellites for operational applications and for 37% of industry sales as a whole (extracted from Eurospace figures 2011) . 4 Global fleet launches till 2014 A track record of 6 successful launches since 2011; 7 more satellites to be -
Carl Schueler Orbital Sciences Corporation [email protected] 805-895-8425 Poster 277A AMS 8 Th Symposium on Space Weather Abstract
Hosted Payload Lessons Carl Schueler Orbital Sciences Corporation [email protected] 805-895-8425 Poster 277a AMS 8 th Symposium on Space Weather Abstract Commercial satellites can host remote sensing at dramatically lower cost than dedicated missions Air Force’s Commercially Hosted Infrared Payload (CHIRP) to demonstrate commercially hosted geostationary remote -sensing this year* CHIRP, in S/C I&T, is confirming advantages of commercial hosting & providing lessons to mitigate real & perceived disadvantages relative to dedicated missions This poster focuses on hosted payload lessons *Brinton, Turner, “Industry Banking on Market for Hosted Payloads,” Space News , 6 October 2008 GEO Addresses Requirements Defense Civil Operational Mission Planning Land & Water Resources Strategic Disaster & Tactical Resolution and Regional Repeat Weather Operations Responsiveness Data Sets Rapid Repeat & High Fidelity Commercial Turnaround Radiometry Research Competitive Global Survey - Spatial Resolution Stable Sensing Low Cost Complement Field Experiments Many GEO Hosted Payload Applications Inter-Satellite Communication Links Military UHF SATCOM Augmentation Missile Warning Prototype Technology Demonstrations Space Environmental Sensors Space Situation Awareness Science Experiments Weather Sensors CHIRP Example Commercially Hosted Infrared Payload (CHIRP), US Air Force experiment CY-2011 Gary Payton, USAF, Oct 2008 (Brinton): “The deal…was fantastic…a fourth-of-world view at geo & a year…of data…for less than the cost of a launch vehicle.” US