Payload Accommodations • Expendable Launch Vehicles • Space Shuttle • Secondary Payloads

Total Page:16

File Type:pdf, Size:1020Kb

Payload Accommodations • Expendable Launch Vehicles • Space Shuttle • Secondary Payloads Payload Accommodations • Expendable launch vehicles • Space shuttle • Secondary payloads © 2014 David L. Akin - All rights reserved http://spacecraft.ssl.umd.edu U N I V E R S I T Y O F Payload Accommodations MARYLAND ENAE 791 - Launch and Entry Vehicle Design1 Pegasus XL U N I V E R S I T Y O F Payload Accommodations MARYLAND 2 ENAE 791 - Launch and Entry Vehicle Design Pegasus Payload Performance U N I V E R S I T Y O F Payload Accommodations MARYLAND 3 ENAE 791 - Launch and Entry Vehicle Design Falcon 1/1e and Falcon 9 • New vehicles developed by Space Exploration Technologies, Inc (“SpaceX”) • “Operate an aerospace company like a dot-com company” • Cost reduction through modern fabrication techniques, vertical integration • Falcon 1/1e - $11M/flight • Falcon 9 - $103M/flight U N I V E R S I T Y O F Payload Accommodations MARYLAND 4 ENAE 791 - Launch and Entry Vehicle Design Falcon 1/1e Payload Fairings U N I V E R S I T Y O F Payload Accommodations MARYLAND 5 ENAE 791 - Launch and Entry Vehicle Design Falcon 1/1e Performance to LEO U N I V E R S I T Y O F Payload Accommodations MARYLAND 6 ENAE 791 - Launch and Entry Vehicle Design Minotaur IV Launch Vehicle Family U N I V E R S I T Y O F Payload Accommodations MARYLAND 7 ENAE 791 - Launch and Entry Vehicle Design Minotaur SSO Payload Performance U N I V E R S I T Y O F Payload Accommodations MARYLAND 8 ENAE 791 - Launch and Entry Vehicle Design Antares U N I V E R S I T Y O F Payload Accommodations MARYLAND 9 ENAE 791 - Launch and Entry Vehicle Design Antares Payload Performance from WFF U N I V E R S I T Y O F Payload Accommodations MARYLAND 10 ENAE 791 - Launch and Entry Vehicle Design Evolved Expendable Launch Vehicles U N I V E R S I T Y O F Payload Accommodations MARYLAND 11 ENAE 791 - Launch and Entry Vehicle Design Delta IV Evolution and GTO Capability U N I V E R S I T Y O F Payload Accommodations MARYLAND 12 ENAE 791 - Launch and Entry Vehicle Design Delta IV RS-68 Engine U N I V E R S I T Y O F Payload Accommodations MARYLAND 13 ENAE 791 - Launch and Entry Vehicle Design Delta IV Upper Stages U N I V E R S I T Y O F Payload Accommodations MARYLAND 14 ENAE 791 - Launch and Entry Vehicle Design Delta IV Heavy GTO Ascent Profile U N I V E R S I T Y O F Payload Accommodations MARYLAND 15 ENAE 791 - Launch and Entry Vehicle Design Delta IV Heavy Payload to LEO Circular U N I V E R S I T Y O F Payload Accommodations MARYLAND 16 ENAE 791 - Launch and Entry Vehicle Design Atlas V 551 GTO Ascent Profile U N I V E R S I T Y O F Payload Accommodations MARYLAND 17 ENAE 791 - Launch and Entry Vehicle Design Atlas V 552 LEO Ascent Profile U N I V E R S I T Y O F Payload Accommodations MARYLAND 18 ENAE 791 - Launch and Entry Vehicle Design Falcon 9 Performance to LEO U N I V E R S I T Y O F Payload Accommodations MARYLAND 19 ENAE 791 - Launch and Entry Vehicle Design Falcon 9 Payload Fairing U N I V E R S I T Y O F Payload Accommodations MARYLAND 20 ENAE 791 - Launch and Entry Vehicle Design Falcon 9 Performance to Earth Escape U N I V E R S I T Y O F Payload Accommodations MARYLAND 21 ENAE 791 - Launch and Entry Vehicle Design Falcon Heavy (SpaceX) • Growth version of Falcon 9 • 53,000 kg of payload to LEO (28.5°) • 21,200 kg of payload to GTO • First flight early 2015 U N I V E R S I T Y O F Payload Accommodations MARYLAND 22 ENAE 791 - Launch and Entry Vehicle Design Delta IV Heavy Coordinate System U N I V E R S I T Y O F Payload Accommodations MARYLAND 23 ENAE 791 - Launch and Entry Vehicle Design Delta Standard Payload Attach Fittings U N I V E R S I T Y O F Payload Accommodations MARYLAND 24 ENAE 791 - Launch and Entry Vehicle Design Marmon Band/Separation Springs U N I V E R S I T Y O F Payload Accommodations MARYLAND 25 ENAE 791 - Launch and Entry Vehicle Design Marmon Band/Separation Springs U N I V E R S I T Y O F Payload Accommodations MARYLAND 26 ENAE 791 - Launch and Entry Vehicle Design Delta 1575-4 Bolted Payload Interface U N I V E R S I T Y O F Payload Accommodations MARYLAND 27 ENAE 791 - Launch and Entry Vehicle Design Delta 4394-5 Bolted Interface U N I V E R S I T Y O F Payload Accommodations MARYLAND 28 ENAE 791 - Launch and Entry Vehicle Design Atlas V Bolted 173 inch PAF U N I V E R S I T Y O F Payload Accommodations MARYLAND 29 ENAE 791 - Launch and Entry Vehicle Design Atlas V 400 Allowable CG Locations U N I V E R S I T Y O F Payload Accommodations MARYLAND 30 ENAE 791 - Launch and Entry Vehicle Design Delta Payload Fairings U N I V E R S I T Y O F Payload Accommodations MARYLAND 31 ENAE 791 - Launch and Entry Vehicle Design Delta Metallic Fairing Temperatures U N I V E R S I T Y O F Payload Accommodations MARYLAND 32 ENAE 791 - Launch and Entry Vehicle Design Delta Composite Fairing Temperatures U N I V E R S I T Y O F Payload Accommodations MARYLAND 33 ENAE 791 - Launch and Entry Vehicle Design Delta IV Heavy Payload Venting U N I V E R S I T Y O F Payload Accommodations MARYLAND 34 ENAE 791 - Launch and Entry Vehicle Design Delta IV Heavy Acoustic Environment U N I V E R S I T Y O F Payload Accommodations MARYLAND 35 ENAE 791 - Launch and Entry Vehicle Design Delta IV Heavy Dynamic Loads U N I V E R S I T Y O F Payload Accommodations MARYLAND 36 ENAE 791 - Launch and Entry Vehicle Design Shuttle Mission Profile U N I V E R S I T Y O F Payload Accommodations MARYLAND 37 ENAE 791 - Launch and Entry Vehicle Design Orbiter Coordinate System U N I V E R S I T Y O F Payload Accommodations MARYLAND 38 ENAE 791 - Launch and Entry Vehicle Design Orbiter Payload Bay Envelope U N I V E R S I T Y O F Payload Accommodations MARYLAND 39 ENAE 791 - Launch and Entry Vehicle Design Orbiter Longeron Bridge Fittings U N I V E R S I T Y O F Payload Accommodations MARYLAND 40 ENAE 791 - Launch and Entry Vehicle Design Orbiter Five-Point Attach System U N I V E R S I T Y O F Payload Accommodations MARYLAND 41 ENAE 791 - Launch and Entry Vehicle Design Orbiter Three-Point Attach System U N I V E R S I T Y O F Payload Accommodations MARYLAND 42 ENAE 791 - Launch and Entry Vehicle Design Orbiter Payload Attach Fittings U N I V E R S I T Y O F Payload Accommodations MARYLAND 43 ENAE 791 - Launch and Entry Vehicle Design Shuttle Payload Bay Temperatures U N I V E R S I T Y O F Payload Accommodations MARYLAND 44 ENAE 791 - Launch and Entry Vehicle Design Orbiter ROEU U N I V E R S I T Y O F Payload Accommodations MARYLAND 45 ENAE 791 - Launch and Entry Vehicle Design Payload Qualification Testing • Structural load testing (flight x 1.25) • Acoustic load testing (flight + 3 dB) • Sinusoidal vibration testing (flight + 3 dB at 2 octaves/min sweep rate) • Shock testing (actuation of pyrotechnics) U N I V E R S I T Y O F Payload Accommodations MARYLAND 46 ENAE 791 - Launch and Entry Vehicle Design Delta IV Heavy Launch Processing Flow U N I V E R S I T Y O F Payload Accommodations MARYLAND 47 ENAE 791 - Launch and Entry Vehicle Design Delta IV Horizontal Integration Facility U N I V E R S I T Y O F Payload Accommodations MARYLAND 48 ENAE 791 - Launch and Entry Vehicle Design Integration Documentation (part 1) U N I V E R S I T Y O F Payload Accommodations MARYLAND 49 ENAE 791 - Launch and Entry Vehicle Design Integration Documentation (part 2) U N I V E R S I T Y O F Payload Accommodations MARYLAND 50 ENAE 791 - Launch and Entry Vehicle Design Spacecraft Contractor Data Requirements U N I V E R S I T Y O F Payload Accommodations MARYLAND 51 ENAE 791 - Launch and Entry Vehicle Design EELV Secondary Payload Adapter (ESPA) U N I V E R S I T Y O F Payload Accommodations MARYLAND 52 ENAE 791 - Launch and Entry Vehicle Design ESPA Mass/CG Limitations U N I V E R S I T Y O F Payload Accommodations MARYLAND 53 ENAE 791 - Launch and Entry Vehicle Design ESPA Mechanical Interface U N I V E R S I T Y O F Payload Accommodations MARYLAND 54 ENAE 791 - Launch and Entry Vehicle Design ESPA Surface Temperature Profiles U N I V E R S I T Y O F Payload Accommodations MARYLAND 55 ENAE 791 - Launch and Entry Vehicle Design ESPA Shock Environment U N I V E R S I T Y O F Payload Accommodations MARYLAND 56 ENAE 791 - Launch and Entry Vehicle Design Final Thoughts about Payloads • Payload development details are specific to the launch vehicle • Integration processes are unique to the individual launch site • Every launch is a custom operation • Payload documentation for launch is comparable to complexity of payload itself • But there’s nothing like seeing your payload heading to orbit!!! U N I V E R S I T Y O F Payload Accommodations MARYLAND 57 ENAE 791 - Launch and Entry Vehicle Design.
Recommended publications
  • Launch and Deployment Analysis for a Small, MEO, Technology Demonstration Satellite
    46th AIAA Aerospace Sciences Meeting and Exhibit AIAA 2008-1131 7 – 10 January 20006, Reno, Nevada Launch and Deployment Analysis for a Small, MEO, Technology Demonstration Satellite Stephen A. Whitmore* and Tyson K. Smith† Utah State University, Logan, UT, 84322-4130 A trade study investigating the economics, mass budget, and concept of operations for delivery of a small technology-demonstration satellite to a medium-altitude earth orbit is presented. The mission requires payload deployment at a 19,000 km orbit altitude and an inclination of 55o. Because the payload is a technology demonstrator and not part of an operational mission, launch and deployment costs are a paramount consideration. The payload includes classified technologies; consequently a USA licensed launch system is mandated. A preliminary trade analysis is performed where all available options for FAA-licensed US launch systems are considered. The preliminary trade study selects the Orbital Sciences Minotaur V launch vehicle, derived from the decommissioned Peacekeeper missile system, as the most favorable option for payload delivery. To meet mission objectives the Minotaur V configuration is modified, replacing the baseline 5th stage ATK-37FM motor with the significantly smaller ATK Star 27. The proposed design change enables payload delivery to the required orbit without using a 6th stage kick motor. End-to-end mass budgets are calculated, and a concept of operations is presented. Monte-Carlo simulations are used to characterize the expected accuracy of the final orbit.
    [Show full text]
  • 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.
    [Show full text]
  • Delta II Icesat-2 Mission Booklet
    A United Launch Alliance (ULA) Delta II 7420-10 photon-counting laser altimeter that advances MISSION rocket will deliver the Ice, Cloud and land Eleva- technology from the first ICESat mission tion Satellite-2 (ICESat-2) spacecraft to a 250 nmi launched on a Delta II in 2003 and operated until (463 km), near-circular polar orbit. Liftoff will 2009. Our planet’s frozen and icy areas, called occur from Space Launch Complex-2 at Vanden- the cryosphere, are a key focus of NASA’s Earth berg Air Force Base, California. science research. ICESat-2 will help scientists MISSION investigate why, and how much, our cryosphere ICESat-2, with its single instrument, the is changing in a warming climate, while also Advanced Topographic Laser Altimeter System measuring heights across Earth’s temperate OVERVIEW (ATLAS), will provide scientists with height and tropical regions and take stock of the vege- measurements to create a global portrait of tation in forests worldwide. The ICESat-2 mission Earth’s third dimension, gathering data that can is implemented by NASA’s Goddard Space Flight precisely track changes of terrain including Center (GSFC). Northrop Grumman built the glaciers, sea ice, forests and more. ATLAS is a spacecraft. NASA’s Launch Services Program at Kennedy Space Center is responsible for launch management. In addition to ICESat-2, this mission includes four CubeSats which will launch from dispens- ers mounted to the Delta II second stage. The CubeSats were designed and built by UCLA, University of Central Florida, and Cal Poly. The miniaturized satellites will conduct research DELTA II For nearly 30 years, the reliable in space weather, changing electric potential Delta II rocket has been an industry and resulting discharge events on spacecraft workhorse, launching critical and damping behavior of tungsten powder in a capabilities for NASA, the Air Force Image Credit NASA’s Goddard Space Flight Center zero-gravity environment.
    [Show full text]
  • 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;
    [Show full text]
  • 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 .
    [Show full text]
  • The SKYLON Spaceplane
    The SKYLON Spaceplane Borg K.⇤ and Matula E.⇤ University of Colorado, Boulder, CO, 80309, USA This report outlines the major technical aspects of the SKYLON spaceplane as a final project for the ASEN 5053 class. The SKYLON spaceplane is designed as a single stage to orbit vehicle capable of lifting 15 mT to LEO from a 5.5 km runway and returning to land at the same location. It is powered by a unique engine design that combines an air- breathing and rocket mode into a single engine. This is achieved through the use of a novel lightweight heat exchanger that has been demonstrated on a reduced scale. The program has received funding from the UK government and ESA to build a full scale prototype of the engine as it’s next step. The project is technically feasible but will need to overcome some manufacturing issues and high start-up costs. This report is not intended for publication or commercial use. Nomenclature SSTO Single Stage To Orbit REL Reaction Engines Ltd UK United Kingdom LEO Low Earth Orbit SABRE Synergetic Air-Breathing Rocket Engine SOMA SKYLON Orbital Maneuvering Assembly HOTOL Horizontal Take-O↵and Landing NASP National Aerospace Program GT OW Gross Take-O↵Weight MECO Main Engine Cut-O↵ LACE Liquid Air Cooled Engine RCS Reaction Control System MLI Multi-Layer Insulation mT Tonne I. Introduction The SKYLON spaceplane is a single stage to orbit concept vehicle being developed by Reaction Engines Ltd in the United Kingdom. It is designed to take o↵and land on a runway delivering 15 mT of payload into LEO, in the current D-1 configuration.
    [Show full text]
  • Review of Nasa's Acquisition of Commercial Launch Services
    FEBRUARY 17, 2011 AUDIT REPORT OFFICE OF AUDITS REVIEW OF NASA’S ACQUISITION OF COMMERCIAL LAUNCH SERVICES OFFICE OF INSPECTOR GENERAL National Aeronautics and Space Administration REPORT NO. IG-11-012 (ASSIGNMENT NO. A-09-011-00) Final report released by: Paul K. Martin Inspector General Acronyms COTS Commercial Orbital Transportation Services CRS Commercial Resupply Services DOD Department of Defense EELV Evolved Expendable Launch Vehicle ELV Expendable Launch Vehicle ESMD Exploration Systems Mission Directorate GAO Government Accountability Office GLAST Gamma-ray Large Area Space Telescope IBEX Interstellar Boundary Explorer ICBM Intercontinental Ballistic Missile ICESat-II Ice, Cloud, and Land Elevation Satellite IDIQ Indefinite-Delivery, Indefinite-Quantity ISS International Space Station LADEE Lunar Atmosphere and Dust Environment Explorer LCROSS Lunar Crater Observation and Sensing Satellite LRO Lunar Reconnaissance Orbiter LSP Launch Services Program NLS NASA Launch Services OCO Orbiting Carbon Observatory OIG Office of Inspector General PPBE Planning, Programming, Budgeting, and Execution SMAP Soil Moisture Active Passive SMD Science Mission Directorate SOMD Space Operations Mission Directorate ULA United Launch Alliance REPORT NO. IG-11-012 FEBRUARY 17, 2011 OVERVIEW REVIEW OF NASA’S ACQUISITION OF COMMERCIAL LAUNCH SERVICES The Issue Commercial U.S. launch services providers compete domestically and internationally for contracts to carry satellites and other payloads into orbit using unmanned, single-use vehicles known as expendable launch vehicles (ELVs). However, since the late 1990s the global commercial launch market has generally declined following the downturn in the telecommunications services industry, which was the primary customer of the commercial space industry. Given this trend, U.S. launch services providers struggling to remain economically viable have been bolstered by the Commercial Space Act of 1998 (Public Law 105-303), which requires NASA and other Federal agencies to plan missions and procure space transportation services from U.S.
    [Show full text]
  • Atlas Launch System Mission Planner's Guide, Atlas V Addendum
    ATLAS Atlas Launch System Mission Planner’s Guide, Atlas V Addendum FOREWORD This Atlas V Addendum supplements the current version of the Atlas Launch System Mission Plan- ner’s Guide (AMPG) and presents the initial vehicle capabilities for the newly available Atlas V launch system. Atlas V’s multiple vehicle configurations and performance levels can provide the optimum match for a range of customer requirements at the lowest cost. The performance data are presented in sufficient detail for preliminary assessment of the Atlas V vehicle family for your missions. This guide, in combination with the AMPG, includes essential technical and programmatic data for preliminary mission planning and spacecraft design. Interface data are in sufficient detail to assess a first-order compatibility. This guide contains current information on Lockheed Martin’s plans for Atlas V launch services. It is subject to change as Atlas V development progresses, and will be revised peri- odically. Potential users of Atlas V launch service are encouraged to contact the offices listed below to obtain the latest technical and program status information for the Atlas V development. For technical and business development inquiries, contact: COMMERCIAL BUSINESS U.S. GOVERNMENT INQUIRIES BUSINESS INQUIRIES Telephone: (691) 645-6400 Telephone: (303) 977-5250 Fax: (619) 645-6500 Fax: (303) 971-2472 Postal Address: Postal Address: International Launch Services, Inc. Commercial Launch Services, Inc. P.O. Box 124670 P.O. Box 179 San Diego, CA 92112-4670 Denver, CO 80201 Street Address: Street Address: International Launch Services, Inc. Commercial Launch Services, Inc. 101 West Broadway P.O. Box 179 Suite 2000 MS DC1400 San Diego, CA 92101 12999 Deer Creek Canyon Road Littleton, CO 80127-5146 A current version of this document can be found, in electronic form, on the Internet at: http://www.ilslaunch.com ii ATLAS LAUNCH SYSTEM MISSION PLANNER’S GUIDE ATLAS V ADDENDUM (AVMPG) REVISIONS Revision Date Rev No.
    [Show full text]
  • 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.
    [Show full text]
  • Spaceflight, Inc. General Payload Users Guide
    Spaceflight, Inc. SF‐2100‐PUG‐00001 Rev F 2015‐22‐15 Payload Users Guide Spaceflight, Inc. General Payload Users Guide 3415 S. 116th St, Suite 123 Tukwila, WA 98168 866.204.1707 spaceflightindustries.com i Spaceflight, Inc. SF‐2100‐PUG‐00001 Rev F 2015‐22‐15 Payload Users Guide Document Revision History Rev Approval Changes ECN No. Sections / Approved Pages CM Date A 2011‐09‐16 Initial Release Updated electrical interfaces and launch B 2012‐03‐30 environments C 2012‐07‐18 Official release Updated electrical interfaces and launch D 2013‐03‐05 environments, reformatted, and added to sections Updated organization and formatting, E 2014‐04‐15 added content on SHERPA, Mini‐SHERPA and ISS launches, updated RPA CG F 2015‐05‐22 Overall update ii Spaceflight, Inc. SF‐2100‐PUG‐00001 Rev F 2015‐22‐15 Payload Users Guide Table of Contents 1 Introduction ........................................................................................................................... 7 1.1 Document Overview ........................................................................................................................ 7 1.2 Spaceflight Overview ....................................................................................................................... 7 1.3 Hardware Overview ......................................................................................................................... 9 1.4 Mission Management Overview .................................................................................................... 10 2 Secondary
    [Show full text]
  • Minotaur I User's Guide
    This page left intentionally blank. Minotaur I User’s Guide Revision Summary TM-14025, Rev. D REVISION SUMMARY VERSION DOCUMENT DATE CHANGE PAGE 1.0 TM-14025 Mar 2002 Initial Release All 2.0 TM-14025A Oct 2004 Changes throughout. Major updates include All · Performance plots · Environments · Payload accommodations · Added 61 inch fairing option 3.0 TM-14025B Mar 2014 Extensively Revised All 3.1 TM-14025C Sep 2015 Updated to current Orbital ATK naming. All 3.2 TM-14025D Sep 2018 Branding update to Northrop Grumman. All 3.3 TM-14025D Sep 2020 Branding update. All Updated contact information. Release 3.3 September 2020 i Minotaur I User’s Guide Revision Summary TM-14025, Rev. D This page left intentionally blank. Release 3.3 September 2020 ii Minotaur I User’s Guide Preface TM-14025, Rev. D PREFACE This Minotaur I User's Guide is intended to familiarize potential space launch vehicle users with the Mino- taur I launch system, its capabilities and its associated services. All data provided herein is for reference purposes only and should not be used for mission specific analyses. Detailed analyses will be performed based on the requirements and characteristics of each specific mission. The launch services described herein are available for US Government sponsored missions via the United States Air Force (USAF) Space and Missile Systems Center (SMC), Advanced Systems and Development Directorate (SMC/AD), Rocket Systems Launch Program (SMC/ADSL). For technical information and additional copies of this User’s Guide, contact: Northrop Grumman
    [Show full text]
  • Trade Studies Towards an Australian Indigenous Space Launch System
    TRADE STUDIES TOWARDS AN AUSTRALIAN INDIGENOUS SPACE LAUNCH SYSTEM A thesis submitted for the degree of Master of Engineering by Gordon P. Briggs B.Sc. (Hons), M.Sc. (Astron) School of Engineering and Information Technology, University College, University of New South Wales, Australian Defence Force Academy January 2010 Abstract During the project Apollo moon landings of the mid 1970s the United States of America was the pre-eminent space faring nation followed closely by only the USSR. Since that time many other nations have realised the potential of spaceflight not only for immediate financial gain in areas such as communications and earth observation but also in the strategic areas of scientific discovery, industrial development and national prestige. Australia on the other hand has resolutely refused to participate by instituting its own space program. Successive Australian governments have preferred to obtain any required space hardware or services by purchasing off-the-shelf from foreign suppliers. This policy or attitude is a matter of frustration to those sections of the Australian technical community who believe that the nation should be participating in space technology. In particular the provision of an indigenous launch vehicle that would guarantee the nation independent access to the space frontier. It would therefore appear that any launch vehicle development in Australia will be left to non- government organisations to at least define the requirements for such a vehicle and to initiate development of long-lead items for such a project. It is therefore the aim of this thesis to attempt to define some of the requirements for a nascent Australian indigenous launch vehicle system.
    [Show full text]