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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. -
Douglas Missile & Space Systems Division
·, THE THOR HISTORY. MAY 1963 DOUGLAS REPORT SM-41860 APPROVED BY: W.H.. HOOPER CHIEF, THOR SYSTEMS ENGINEERING AEROSPACE SYSTEMS ENGINEERING DOUGLAS MISSILE & SPACE SYSTEMS DIVISION ABSTRACT This history is intended as a quick orientation source and as n ready-reference for review of the Thor and its sys tems. The report briefly states the development of Thor, sur'lli-:arizes and chronicles Thor missile and booster launch inGs, provides illustrations and descriptions of the vehicle systcn1s, relates their genealogy, explains sane of the per fon:iance capabilities of the Thor and Thor-based vehicles used, and focuses attention to the exploration of space by Douelas Aircraf't Company, Inc. (DAC). iii PREFACE The purpose of The Thor History is to survey the launch record of the Thor Weapon, Special Weapon, and Space Systems; give a systematic account of the major events; and review Thor's participation in the military and space programs of this nation. The period covered is from December 27, 1955, the date of the first contract award, through May, 1963. V �LE OF CONTENTS Page Contract'Award . • • • • • • • • • • • • • • • • • • • • • • • • • 1 Background • • • • • • • • • • • • • • • • • • • • • • • • • • • • l Basic Or�anization and Objectives • • • • • • • • • • • • • • • • 1 Basic Developmenta� Philosophy . • • • • • • • • • • • • • • • • • 2 Early Research and Development Launches • • • ·• • • • • • • • • • 4 Transition to ICBM with Space Capabilities--Multi-Stage Vehicles . 6 Initial Lunar and Space Probes ••••••• • • • • • • • -
L AUNCH SYSTEMS Databk7 Collected.Book Page 18 Monday, September 14, 2009 2:53 PM Databk7 Collected.Book Page 19 Monday, September 14, 2009 2:53 PM
databk7_collected.book Page 17 Monday, September 14, 2009 2:53 PM CHAPTER TWO L AUNCH SYSTEMS databk7_collected.book Page 18 Monday, September 14, 2009 2:53 PM databk7_collected.book Page 19 Monday, September 14, 2009 2:53 PM CHAPTER TWO L AUNCH SYSTEMS Introduction Launch systems provide access to space, necessary for the majority of NASA’s activities. During the decade from 1989–1998, NASA used two types of launch systems, one consisting of several families of expendable launch vehicles (ELV) and the second consisting of the world’s only partially reusable launch system—the Space Shuttle. A significant challenge NASA faced during the decade was the development of technologies needed to design and implement a new reusable launch system that would prove less expensive than the Shuttle. Although some attempts seemed promising, none succeeded. This chapter addresses most subjects relating to access to space and space transportation. It discusses and describes ELVs, the Space Shuttle in its launch vehicle function, and NASA’s attempts to develop new launch systems. Tables relating to each launch vehicle’s characteristics are included. The other functions of the Space Shuttle—as a scientific laboratory, staging area for repair missions, and a prime element of the Space Station program—are discussed in the next chapter, Human Spaceflight. This chapter also provides a brief review of launch systems in the past decade, an overview of policy relating to launch systems, a summary of the management of NASA’s launch systems programs, and tables of funding data. The Last Decade Reviewed (1979–1988) From 1979 through 1988, NASA used families of ELVs that had seen service during the previous decade. -
Learning from Other People's Mistakes
Learning from Other People’s Mistakes Most satellite mishaps stem from engineering mistakes. To prevent the same errors from being repeated, Aerospace has compiled lessons that the space community should heed. Paul Cheng and Patrick Smith he computer onboard the Clementine spacecraft froze immediately after a thruster was commanded to fire. A “watchdog” algorithm designed to stop “It’s always the simple stuff the thrusters from excessive firing could not execute, and CTlementine’s fuel ran out. !e mission was lost. Based on that kills you…. With all the this incident, engineers working on the Near Earth Asteroid Rendezvous (NEAR) program learned a key lesson: the testing systems, everything watchdog function should be hard-wired in case of a com- puter shutdown. As it happened, NEAR suffered a similar computer crash during which its thrusters fired thousands looked good.” of times, but each firing was instantly cut off by the still- —James Cantrell, main engineer operative watchdog timer. NEAR survived. As this example illustrates, insights from past anoma- for the joint U.S.-Russian Skipper lies are of considerable value to design engineers and other mission, which failed because program stakeholders. Information from failures (and near its solar panels were connected failures) can influence important design decisions and pre- vent the same mistakes from being made over and over. backward (Associated Press, 1996) Contrary to popular belief, satellites seldom fail because of poor workmanship or defective parts. Instead, most failures are caused by simple engineering errors, such as an over- looked requirement, a unit mix-up, or even a typo in a docu- ment. -
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. -
NYC Aerospace Rocket Program
NYC Aerospace Rocket Program NYC Aerospace’s 100,000ft rocket program is committed to designing and manufacturing a sounding rocket to reach 100,000ft, above 99% of the atmosphere. The purpose of this mission is to research the applications of ammonium perchlorate composite propellant (APCP) to large rockets. Many future aerospace engineers have learned a great deal about rocketry from participating in this project, which is one of NYC Aerospace’s many projects involving students citywide. Rocket details Our goal is to send a single-stage rocket to 100,000ft using ammonium perchlorate composite propellant (APCP). In order to reach this altitude, the rocket will likely need to maintain structural integrity at velocities on the order of Mach 2 and above. Therefore, the rocket body will need to be made of a light metal such as aluminum or titanium. A metal body necessitates the capacity of the rocket motor to be in the O range of near 30,000Ns of impulse. Assuming a perfectly efficient motor, this requires around 30lb of propellant. We can calculate fuel fraction by first establishing our delta v budget. Δv = √2gz = √2(9.8m/s2)(30480m) =772m/s= mach 2.25 Using the delta v necessary, we can calculate the minimum fuel fraction using Tsiolkovsky’s ideal rocket equation. Assuming the specific impulse of our motor is 228s: m final Δv =− v eln m initial m final = exp(− 772/2280) = 0.71 m initial Thus, we only need 29% of our rocket to be fuel. This brings the max mass of our rocket to 103lb. -
The Advanced Cryogenic Evolved Stage (ACES)- a Low-Cost, Low-Risk Approach to Space Exploration Launch
The Advanced Cryogenic Evolved Stage (ACES)- A Low-Cost, Low-Risk Approach to Space Exploration Launch J. F. LeBar1 and E. C. Cady2 Boeing Phantom Works, Huntington Beach CA 92647 Space exploration top-level objectives have been defined with the United States first returning to the moon as a precursor to missions to Mars and beyond. System architecture studies are being conducted to develop the overall approach and define requirements for the various system elements, both Earth-to-orbit and in-space. One way of minimizing cost and risk is through the use of proven systems and/or multiple-use elements. Use of a Delta IV second stage derivative as a long duration in-space transportation stage offers cost, reliability, and performance advantages over earth-storable propellants and/or all new stages. The Delta IV second stage mission currently is measured in hours, and the various vehicle and propellant systems have been designed for these durations. In order for the ACES to have sufficient life to be useful as an Earth Departure Stage (EDS), many systems must be modified for long duration missions. One of the highest risk subsystems is the propellant storage Thermal Control System (TCS). The ACES effort concentrated on a lower risk passive TCS, the RL10 engine, and the other subsystems. An active TCS incorporating a cryocoolers was also studied. In addition, a number of computational models were developed to aid in the subsystem studies. The high performance TCS developed under ACES was simulated within the Delta IV thermal model and long-duration mission stage performance assessed. -
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. -
ULA Rideshare Capabilities for Providing Low-Cost Access to Space
United Launch Alliance Rideshare Capabilities for Providing Low-Cost Access to Space Keith Karuntzos United Launch Alliance PO Box 3788, MIS C4102 Centennial, CO 80155-3788 303-269-5499 [email protected] Abstract-United Launch Alliance (ULA) has a long history of REFERENCES ••••••••••••••••••••••••••••••••••••••••••••••••••••••••• 9 providing launch services to high-value payloads for a variety BIOGRAPHY •••••••••••••••••••••••••••••••••••••••••••••••••••••••••• 9 of customers, including the US Department of Defense, the National Reconnaissance Office, NASA, and commercial customers. These missions have deployed a wide variety of capabilities into Earth orbit and beyond, such as navigation, 1. VVHAT IS RIDESHARE? communication, R&D, observation, and science, all which have Since the dawn of the space age, spacecraft have often provided us with a tremendous amount of knowledge about Earth and our solar system. The majority of these spacecraft shared launch services with one another while being has been launched as primary payloads, and used the full delivered into space. This approach has normally been done capability of the launch vehicle; yet there is a lower-cost to support spacecraftmuch smaller than the primary payload alternative for achieving similar mission objectives: rideshare. it is launching with. By designing launch services in this manner, spacecraft operators were able to deliver more Rideshare is the approach of sharing available launch vehicle payloads to orbit for a fraction of the cost of a full-up launch performance and volume margins with two or more spacecraft service. that would otherwise go underutilized by the spacecraft community. This allows spacecraft customers the opportunity This method of launching multiple payloads into orbit on a to get their spacecraft to orbit and beyond in an inexpensive single launch vehicle is called rideshare. -
The Evolving Launch Vehicle Market Supply and the Effect on Future NASA Missions
Presented at the 2007 ISPA/SCEA Joint Annual International Conference and Workshop - www.iceaaonline.com The Evolving Launch Vehicle Market Supply and the Effect on Future NASA Missions Presented at the 2007 ISPA/SCEA Joint International Conference & Workshop June 12-15, New Orleans, LA Bob Bitten, Debra Emmons, Claude Freaner 1 Presented at the 2007 ISPA/SCEA Joint Annual International Conference and Workshop - www.iceaaonline.com Abstract • The upcoming retirement of the Delta II family of launch vehicles leaves a performance gap between small expendable launch vehicles, such as the Pegasus and Taurus, and large vehicles, such as the Delta IV and Atlas V families • This performance gap may lead to a variety of progressions including – large satellites that utilize the full capability of the larger launch vehicles, – medium size satellites that would require dual manifesting on the larger vehicles or – smaller satellites missions that would require a large number of smaller launch vehicles • This paper offers some comparative costs of co-manifesting single- instrument missions on a Delta IV/Atlas V, versus placing several instruments on a larger bus and using a Delta IV/Atlas V, as well as considering smaller, single instrument missions launched on a Minotaur or Taurus • This paper presents the results of a parametric study investigating the cost- effectiveness of different alternatives and their effect on future NASA missions that fall into the Small Explorer (SMEX), Medium Explorer (MIDEX), Earth System Science Pathfinder (ESSP), Discovery, -
Orbital ATK - Aerospace Structures Overview
Orbital ATK - Aerospace Structures Overview Revision update May 2017 O12 – Orbital ATK ASD Overview Lite Version 2017 – Approved for Public Release 0 Orbital ATK Overview • Global Aerospace and Defense Systems Company Established by Merger of Orbital and Alliant Techsystems in Early 2015 • Northrop Grumman announced in September 2017 that they have positioned themselves to acquire Orbital ATK and make them a fourth sector of their business. Orbital ATK will remain a merchant supplier for composite components for the aerospace industry • Leading Developer and Manufacturer of Reliable, Innovative and Affordable Products for Government and Commercial Customers Aerospace Structures, Launch Vehicles and Rocket Propulsion Systems Tactical Missile Products, Armament Systems and Ammunition Satellites, Advanced Systems, Space Components and Technical Services • More Than 12,500 Employees, Including About 4,000 Engineers and Scientists • Targeting About $4.6 Billion in Revenue and Up to $6.00 in Earnings per Share in 2017 • Over $14 Billion in Contract Backlog With Good Near-Term Growth Prospects O12 – Orbital ATK ASD Overview Lite Version 2017 – Approved for Public Release 1 Three Operating Groups and 12 Product Lanes Flight Systems Space Systems Defense Systems • Space Launch Vehicles • Satellites Systems • Tactical Missile Systems • Rocket Propulsion Systems • Advanced Programs • Defense Electronic Systems • Aerospace Structures • Spacecraft Components • Armament Systems • Space Technical Services • Ammunition and Energetics 2017 Corporate -
Atlas As a Human Rated LV
AtlasAtlas As As A A Human Human RatedRated LV LV STAIF Conference 2006 Lockheed Martin Space Systems Company Atlas for Human Spaceflight 15 Feb 2006 1 © 2006 Lockheed Martin Corporation. All Rights Reserved Reliable and Versatile Launch Vehicle Family Atlas I Atlas II Atlas IIA Atlas IIAS Atlas IIIA Atlas IIIB Atlas V-400 Atlas V-500 AC-69 AC-102 AC-105 AC-108 AC-201 AC-204 AV-001 AV-003 Jul 1990 Dec 1991 Jun 1992 Dec 1993 May 2000 Feb 2002 Aug 2002 Jul 2003 8/11 10/10 23/23 30/30 2/2 4/4 4/4 3/3 Legend: First Flight X/Y X successes in Y flights •8 of 8 First Flight Successes •78 Consecutive Successful Atlas Centaur Flights •100% Mission Success Atlas II, IIA, IIAS, III & V Families •487 Total Launch Successes Since Atlas Program Inception Mission Success—One Launch at a Time Atlas for Human Spaceflight 15 Feb 2006 2 AV-010 Launch • January 19, 2006 • NASA Pluto New Horizons Spacecraft • First 551 configuration • First Block 2 Fault Tolerant Avionics • First Block B SRB • Nuclear certified • Nominal flight profile • Injection conditions well within 1 sigma – C3, RLA, DLA Fastest Spacecraft Ever Launched Atlas for Human Spaceflight 15 Feb 2006 3 Atlas Evolution History Atlas I/II Family Atlas III Family Atlas V Family 5-m PLF ) 30 GSO Kit T m ( y 26 t i l Avionics i Single Common Upgrade b Engine a 22 Centaur Centaur p a C 3.8-m . Common c 18 r LO2 Core i Tank Booster C Stretch ) 14 m n 0 2 10 Liquid 2 SRBs ( Strap-ons m RD-180 SRBs k 6 Engine 7 0 Atlas I Atlas IIAS Atlas IIIA Atlas IIIB Atlas V Atlas V Atlas V 4 2 Atlas II (SEC) (DEC)