May 2020 Space Business Review
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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. -
Cape Canaveral Air Force Station Support to Commercial Space Launch
The Space Congress® Proceedings 2019 (46th) Light the Fire Jun 4th, 3:30 PM Cape Canaveral Air Force Station Support to Commercial Space Launch Thomas Ste. Marie Vice Commander, 45th Space Wing Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Ste. Marie, Thomas, "Cape Canaveral Air Force Station Support to Commercial Space Launch" (2019). The Space Congress® Proceedings. 31. https://commons.erau.edu/space-congress-proceedings/proceedings-2019-46th/presentations/31 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]. Cape Canaveral Air Force Station Support to Commercial Space Launch Colonel Thomas Ste. Marie Vice Commander, 45th Space Wing CCAFS Launch Customers: 2013 Complex 41: ULA Atlas V (CST-100) Complex 40: SpaceX Falcon 9 Complex 37: ULA Delta IV; Delta IV Heavy Complex 46: Space Florida, Navy* Skid Strip: NGIS Pegasus Atlantic Ocean: Navy Trident II* Black text – current programs; Blue text – in work; * – sub-orbital CCAFS Launch Customers: 2013 Complex 39B: NASA SLS Complex 41: ULA Atlas V (CST-100) Complex 40: SpaceX Falcon 9 Complex 37: ULA Delta IV; Delta IV Heavy NASA Space Launch System Launch Complex 39B February 4, 2013 Complex 46: Space Florida, Navy* Skid Strip: NGIS Pegasus Atlantic Ocean: Navy Trident II* Black text – current programs; -
ESPA Ring Datasheet
PAYLOAD ADAPTERS | ESPA ESPA THE EVOLVED SECONDARY PAYLOAD ADAPTER ESPA mounts to the standard NSSL (formerly EELV) interface bolt pattern (Atlas V, Falcon 9, Delta IV, OmegA, Vulcan, Courtesy of Lockheed Martin New Glenn) and is a drop-in component in the launch stack. Small payloads mount to ESPA ports featuring either a Ø15-inch bolt circle with 24 fasteners or a 4-point mount with pads at each corner of a 15-inch square; both of these interfaces have become small satellite standards. ESPA is qualified to carry 567 lbs (257 kg), and a Heavy interface Courtesy of NASA (with Ø5/16” fastener hardware) has been introduced with a capacity of 991 lbs (450 kg). All small satellite mass capabilities require the center of gravity (CG) to be within 20 inches (50.8 cm) of the ESPA port surface. Alternative configurations can be accommodated. ESPA GRANDE ESPA Grande is a more capable version of ESPA with Ø24-inch ports; the ring height is typically 42 inches. The Ø24-inch port has been qualified by test to Courtesy of ORBCOMM & Sierra Nevada Corp. carry small satellites up to 1543 lb (700 kg). ESPA ESPA IS ADAPTABLE TO UNIQUE MISSION REQUIREMENTS • The Air Force’s STP-1 mission delivered multiple small satellites on an Atlas V. • NASA’s Lunar Crater Observation and Sensing Satellite (LCROSS): ESPA was the spacecraft hub for the LCROSS shepherding satellite in 2009. • ORBCOMM Generation 2 (OG2) launched stacks of two and three ESPA Grandes on two different Falcon 9 missions and in total deployed 17 satellites. -
The Annual Compendium of Commercial Space Transportation: 2012
Federal Aviation Administration The Annual Compendium of Commercial Space Transportation: 2012 February 2013 About FAA 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 (2013) 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. • i • Federal Aviation Administration’s Office of Commercial Space Transportation Dear Colleague, 2012 was a very active year for the entire commercial space industry. In addition to all of the dramatic space transportation events, including the first-ever commercial mission flown to and from the International Space Station, the year was also a very busy one from the government’s perspective. It is clear that the level and pace of activity is beginning to increase significantly. -
Of S.P. Korolev Rocket and Space Public Corporation Energia for 2013
OF S.P. KOROLEV ROCKET AND SPACE PUBLIC CORPORATION ENERGIA FOR 2013 This Annual Report of S.P. Korolev Rocket and Space Public Corporation Energia (also hereinafter called “OAO RSC Energia”, “RSC Energia”, “the Corporation”) by the 2013 performance is drawn up in accordance with the RF Government Decree No 1214 as of December 31, 2010 “On Improvement of the Procedure for Management of Open Joint-Stock Companies Whose Stock is in Federal Ownership and Federal State Unitary Enterprises” with due regard for the requirements set forth in the Order issued by the RF Federal Financial Markets Service No 11-46/pz-n as of October 4, 2011 “On Approval of the Provision on Information Disclosure of Issuers of Registered Securities”. This Annual Report was preliminarily approved by RSC Energia’s Board of Directors on April 29, 2014. Minutes No10 as of May 6, 2014. Accuracy of the data contained in this Annual Report was confirmed by RSC Energia’s Auditing Committee Report as of April 17, 2014. 2 TABLE OF CONTENTS KEY PERFORMANCE INDICATORS ........................................................................... 6 ON CORPORATION ACTIVITIES ................................................................................. 8 Corporation background ................................................................................................................................8 Corporation structure (its participation in subsidiary and affiliated companies) ...........................................9 Information about purchase and sale contracts for -
Finding of No Significant Impact for Boost-Back and Landing of Falcon Heavy Boosters at Landing Zone-1, Cape Canaveral Air Force Station, Florida
DEPARTMENT OF TRANSPORTATION Federal Aviation Administration Office of Commercial Space Transportation Adoption of the Environmental Assessment and Finding of No Significant Impact for Boost-back and Landing of Falcon Heavy Boosters at Landing Zone-1, Cape Canaveral Air Force Station, Florida Summary The U.S. Air Force (USAF) acted as the lead agency, and the Federal Aviation Administration (FAA) was a cooperating agency, in the preparation of the February 2017 Supplemental Environmental Assessment to the December 2014 EA for Space Exploration Technologies Vertical Landing of the Falcon Vehicle and Construction at Launch Complex 13 at Cape Canaveral Air Force Station, Florida (2017 SEA), which analyzed the potential environmental impacts of Space Exploration Technologies Corp. (SpaceX) conducting boost-backs and landings of up to three Falcon Heavy boosters at Landing Zone 1 (LZ-1) at Cape Canaveral Air Force Station (CCAFS), Florida during the same mission. LZ-1 is also known as Launch Complex 13 (LC-13). The scope of the action analyzed in the 2017 SEA also included the option of landing one or two Falcon Heavy boosters on SpaceX’s autonomous droneship in the Atlantic Ocean. The 2017 SEA also addressed construction of two landing pads as well as construction and operation of a processing and testing facility for SpaceX’s Dragon spacecraft. The National Aeronautics and Space Administration (NASA) also participated as a cooperating agency in the preparation of the 2017 SEA. The 2017 SEA was prepared in accordance with the National Environmental Policy Act of 1969, as amended (NEPA; 42 United States Code [U.S.C.] § 4321 et seq.); Council on Environmental Quality NEPA implementing regulations (40 Code of Federal Regulations [CFR] parts 1500 to 1508); the USAF’s Environmental Impact Analysis Process (32 CFR 989); and FAA Order 1050.1F, Environmental Impacts: Policies and Procedures. -
LSP Brochure
National Aeronautics and Space Administration There’s a reason challenging endeavours are called ‘rocket science’... Table of Contents Introduction NASA’s Launch Services Program (LSP) assists customers who Table of Contents ................................................................................1 need specialized, high-technology support world-wide, and Introduction & Objective .......................................................................2 enables some of NASA’s greatest scientific missions and technical achievements. Let’s explore LSP’s ‘earth’s bridge to space.’ Rocket Science 411~Take 1 ............................................................ 3-4 Strategy ........................................................................................... 5-6 Services .......................................................................................... 7-8 Rocket Science 411~Take 2 ...............................................................9 Objective Launch Fleet ......................................................................................10 This portfolio is intended to educate and connect you to some of Launch Vehicle Capabilities, Primary Missions ............................. 11-14 NASA’s most significant unmanned missions, and to highlight the Small Satellite Missions ............................................................... 15-18 contributions made by LSP. Through enriching your understanding of LSP’s benefit to NASA, you may also realize its benefit to you LSP Launch Sites ........................................................................ -
Failures in Spacecraft Systems: an Analysis from The
FAILURES IN SPACECRAFT SYSTEMS: AN ANALYSIS FROM THE PERSPECTIVE OF DECISION MAKING A Thesis Submitted to the Faculty of Purdue University by Vikranth R. Kattakuri In Partial Fulfillment of the Requirements for the Degree of Master of Science in Mechanical Engineering August 2019 Purdue University West Lafayette, Indiana ii THE PURDUE UNIVERSITY GRADUATE SCHOOL STATEMENT OF THESIS APPROVAL Dr. Jitesh H. Panchal, Chair School of Mechanical Engineering Dr. Ilias Bilionis School of Mechanical Engineering Dr. William Crossley School of Aeronautics and Astronautics Approved by: Dr. Jay P. Gore Associate Head of Graduate Studies iii ACKNOWLEDGMENTS I am extremely grateful to my advisor Prof. Jitesh Panchal for his patient guidance throughout the two years of my studies. I am indebted to him for considering me to be a part of his research group and for providing this opportunity to work in the fields of systems engineering and mechanical design for a period of 2 years. Being a research and teaching assistant under him had been a rewarding experience. Without his valuable insights, this work would not only have been possible, but also inconceivable. I would like to thank my co-advisor Prof. Ilias Bilionis for his valuable inputs, timely guidance and extremely engaging research meetings. I thank my committee member, Prof. William Crossley for his interest in my work. I had a great opportunity to attend all three courses taught by my committee members and they are the best among all the courses I had at Purdue. I would like to thank my mentors Dr. Jagannath Raju of Systemantics India Pri- vate Limited and Prof. -
Payload Fairing Geometries As Space Stations with Flexible “Plug and Play” Rack System
49th International Conference on Environmental Systems ICES-2019-113 7-11 July 2019, Boston, Massachusetts Payload Fairing Geometries as Space Stations with Flexible “Plug and Play” Rack System Leonardo A. Guzman1 SICSA, University of Houston, Houston, Texas, 77004 This paper outlines a design methodology of modifying launch vehicle payload fairing geometries into pressurized single or multi-element space stations. The project investigates how Carbon Fiber Reinforced Polymer with Aluminum honeycomb core (CFRP-Al/HC) fairing structure used for deploying satellites can be applied to function as space habitats. Large volume, low budget microgravity space stations that can be achieved along with the utilization of a pre-integrated flexible “Plug and Play” rack system prior to launch on the ground. Nomenclature LEO = Low-Earth Orbit CFRP = Carbon Fiber Reinforced Polymer P&P = “Plug & Play” Rack System TRL = Technology readiness level TPS = Thermal Protection System psi = Pounds per square inch IDSS = International Docking System Standard MMOD = Micro-meteoroid orbital debris I. Introduction ITH the necessity of generating return on investments, private space companies are focusing on reusability, Woptimization and commonality of architecture and systems to get to orbit. Efficient and sustainable commerce is proving to be the way the space industry will become a democratized reality. Looking to generate returns in sending satellites into orbit, launch companies are effectively solving the conventional and new methods to reaching Low-Earth Orbit (LEO) and Geostationary Orbit (GTO). In 2018 alone there were more than 110 successful launches to orbit by both international agencies and private companies. Following the growing trend of the space industry, is to be noted that launch and payload capacities are getting larger and costs are decreasing. -
A Conceptual Analysis of Spacecraft Air Launch Methods
A Conceptual Analysis of Spacecraft Air Launch Methods Rebecca A. Mitchell1 Department of Aerospace Engineering Sciences, University of Colorado, Boulder, CO 80303 Air launch spacecraft have numerous advantages over traditional vertical launch configurations. There are five categories of air launch configurations: captive on top, captive on bottom, towed, aerial refueled, and internally carried. Numerous vehicles have been designed within these five groups, although not all are feasible with current technology. An analysis of mass savings shows that air launch systems can significantly reduce required liftoff mass as compared to vertical launch systems. Nomenclature Δv = change in velocity (m/s) µ = gravitational parameter (km3/s2) CG = Center of Gravity CP = Center of Pressure 2 g0 = standard gravity (m/s ) h = altitude (m) Isp = specific impulse (s) ISS = International Space Station LEO = Low Earth Orbit mf = final vehicle mass (kg) mi = initial vehicle mass (kg) mprop = propellant mass (kg) MR = mass ratio NASA = National Aeronautics and Space Administration r = orbital radius (km) 1 M.S. Student in Bioastronautics, [email protected] 1 T/W = thrust-to-weight ratio v = velocity (m/s) vc = carrier aircraft velocity (m/s) I. Introduction T HE cost of launching into space is often measured by the change in velocity required to reach the destination orbit, known as delta-v or Δv. The change in velocity is related to the required propellant mass by the ideal rocket equation: 푚푖 훥푣 = 퐼푠푝 ∗ 0 ∗ ln ( ) (1) 푚푓 where Isp is the specific impulse, g0 is standard gravity, mi initial mass, and mf is final mass. Specific impulse, measured in seconds, is the amount of time that a unit weight of a propellant can produce a unit weight of thrust. -
The Evolving Revolution in Manned Space Exploration Where We Have Been
The Evolving Revolution in Manned Space Exploration Where we have been. Mercury 1961-1963 6 Flights Gemini 1965-1966 10 Flights 1961-1972 Summary 27 Manned Space Missions Apollo 1968 – 1972 2.5 Manned Missions per year 11 Flights 2.25 Manned lunar missions 9 Lunar Flights per year after Apollo 8 6 Lunar Landings Apollo – Soyuz Skylab One Flight – July 1975 1973 – 1979 3 Crewed Missions – 9 Astronauts 28 – 59 – 84 Days 5 Space Shuttles Space Shuttle Program Columbia – Challenger 1981 – 2011 Discovery 135 Missions Endeavour - Atlantis 833 (536) Astronaut Flights Avg. Cost Per Mission $455 mil Flights Per Year: 4.5 2 Crews Lost (14) Challenger 1986 – Columbia 2003 International Space Station 1998 – Today To date – 50 ISS Missions – 388 Astronauts In Perspective: Total astronaut DAYS in low earth orbital space: 29,000 days Total astronaut DAYS In deep space beyond the Van Allen belt: 96 days Where are we now? Government Manned Space Programs United States Russia China Private Space Programs (All USA) SpaceX Boeing Blue Origin - New Glenn / New Shepard Dream Chaser Mars One Government Programs: USA Maintaining ISS Mars is the current primary exploration destination Possible Asteroid Mission Russia Servicing ISS Lunar Base Plans China Building Space Station Lunar Base Plans NASA Manned Space Exploration Programs 1st SLS Launch Scheduled September 2018 KSC Pad 39B 1st NASA Manned Mars Mission Scheduled for 2030’s Asteroid Mission? Lunar Base? Private Space Ventures in Low Earth Orbit SpaceX Dragon Boeing Starliner Sierra Nevada Dreamchaser Boeing at the Kennedy Space Center Blue Origin at the Kennedy Space Center New Shepherd Suborbital Rocket The Future in Space – View 1 The Future in Space – View 2 The Future in Space – View 3 SpaceX at the Kennedy Space Center The Future of Space Exploration Landing at Sea The Technical Secret of the Booster Landings Hypersonic Thrust Reversal Reduces atmospheric vehicle heating, terminal velocity and damage. -
Assessing the Impact of US Air Force National Security Space Launch Acquisition Decisions
C O R P O R A T I O N BONNIE L. TRIEZENBERG, COLBY PEYTON STEINER, GRANT JOHNSON, JONATHAN CHAM, EDER SOUSA, MOON KIM, MARY KATE ADGIE Assessing the Impact of U.S. Air Force National Security Space Launch Acquisition Decisions An Independent Analysis of the Global Heavy Lift Launch Market For more information on this publication, visit www.rand.org/t/RR4251 Library of Congress Cataloging-in-Publication Data is available for this publication. ISBN: 978-1-9774-0399-5 Published by the RAND Corporation, Santa Monica, Calif. © Copyright 2020 RAND Corporation R® is a registered trademark. Cover: Courtesy photo by United Launch Alliance. Limited Print and Electronic Distribution Rights This document and trademark(s) contained herein are protected by law. This representation of RAND intellectual property is provided for noncommercial use only. Unauthorized posting of this publication online is prohibited. Permission is given to duplicate this document for personal use only, as long as it is unaltered and complete. Permission is required from RAND to reproduce, or reuse in another form, any of its research documents for commercial use. For information on reprint and linking permissions, please visit www.rand.org/pubs/permissions. The RAND Corporation is a research organization that develops solutions to public policy challenges to help make communities throughout the world safer and more secure, healthier and more prosperous. RAND is nonprofit, nonpartisan, and committed to the public interest. RAND’s publications do not necessarily reflect the opinions of its research clients and sponsors. Support RAND Make a tax-deductible charitable contribution at www.rand.org/giving/contribute www.rand.org Preface The U.S.