Delta II Icesat-2 Mission Booklet
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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. -
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. -
Materials for Liquid Propulsion Systems
https://ntrs.nasa.gov/search.jsp?R=20160008869 2019-08-29T17:47:59+00:00Z CHAPTER 12 Materials for Liquid Propulsion Systems John A. Halchak Consultant, Los Angeles, California James L. Cannon NASA Marshall Space Flight Center, Huntsville, Alabama Corey Brown Aerojet-Rocketdyne, West Palm Beach, Florida 12.1 Introduction Earth to orbit launch vehicles are propelled by rocket engines and motors, both liquid and solid. This chapter will discuss liquid engines. The heart of a launch vehicle is its engine. The remainder of the vehicle (with the notable exceptions of the payload and guidance system) is an aero structure to support the propellant tanks which provide the fuel and oxidizer to feed the engine or engines. The basic principle behind a rocket engine is straightforward. The engine is a means to convert potential thermochemical energy of one or more propellants into exhaust jet kinetic energy. Fuel and oxidizer are burned in a combustion chamber where they create hot gases under high pressure. These hot gases are allowed to expand through a nozzle. The molecules of hot gas are first constricted by the throat of the nozzle (de-Laval nozzle) which forces them to accelerate; then as the nozzle flares outwards, they expand and further accelerate. It is the mass of the combustion gases times their velocity, reacting against the walls of the combustion chamber and nozzle, which produce thrust according to Newton’s third law: for every action there is an equal and opposite reaction. [1] Solid rocket motors are cheaper to manufacture and offer good values for their cost. -
Gateway Program Acquisition Strategy Overview
70th International Astronautical Congress (IAC), Washington D.C., United States, 21-25 October 2019. Copyright ©2019 by the International Astronautical Federation (IAF). All rights reserved. IAC-19,E3,6,5,x53831 GATEWAY PROGRAM ACQUISITION STRATEGY OVERVIEW Emma Lehnhardta, Christopher Zavrelb, Nicole Herrmannc a National Aeronautics and Space Administration, Johnson Space Center, United States, [email protected] b Stellar Solutions Inc, United States, [email protected] c National Aeronautics and Space Administration, Headquarters, United States, [email protected] Abstract This paper will provide an overview of the acquisition strategy for the Gateway Program. The Gateway will be an outpost orbiting the Moon that provides vital support for a sustainable, long-term human return to the lunar surface, as well as a staging point for further deep space exploration. The Gateway will foster U.S. industry and international partnerships and enable multi-discipline utilization. The National Aeronautics and Space Administration (NASA) will lead this next step and will serve as the integrator of the spaceflight capabilities and contributions of U.S. commercial partners and international partners to develop the Gateway. The Gateway will be developed in a manner that will also allow future capabilities and collaborations with U.S. Government, private sector companies, and international partners. Gateway is embracing innovation and flexibility; both in system architecture and in procurement approach. The Gateway’s agile acquisition strategy will shape the entire system life cycle, from design and analysis through production, verification, launch, logistics and operations. This strategy will encourage new ways of doing business to accommodate new techniques, technologies and approaches; improving affordability and maximizing Gateway utility. -
Atlas V Cutaway Poster
ATLAS V Since 2002, Atlas V rockets have delivered vital national security, science and exploration, and commercial missions for customers across the globe including the U.S. Air Force, the National Reconnaissance Oice and NASA. 225 ft The spacecraft is encapsulated in either a 5-m (17.8-ft) or a 4-m (13.8-ft) diameter payload fairing (PLF). The 4-m-diameter PLF is a bisector (two-piece shell) fairing consisting of aluminum skin/stringer construction with vertical split-line longerons. The Atlas V 400 series oers three payload fairing options: the large (LPF, shown at left), the extended (EPF) and the extra extended (XPF). The 5-m PLF is a sandwich composite structure made with a vented aluminum-honeycomb core and graphite-epoxy face sheets. The bisector (two-piece shell) PLF encapsulates both the Centaur upper stage and the spacecraft, which separates using a debris-free pyrotechnic actuating 200 ft system. Payload clearance and vehicle structural stability are enhanced by the all-aluminum forward load reactor (FLR), which centers the PLF around the Centaur upper stage and shares payload shear loading. The Atlas V 500 series oers 1 three payload fairing options: the short (shown at left), medium 18 and long. 1 1 The Centaur upper stage is 3.1 m (10 ft) in diameter and 12.7 m (41.6 ft) long. Its propellant tanks are constructed of pressure-stabilized, corrosion-resistant stainless steel. Centaur is a liquid hydrogen/liquid oxygen-fueled vehicle. It uses a single RL10 engine producing 99.2 kN (22,300 lbf) of thrust. -
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. -
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, -
Photographs Written Historical and Descriptive
CAPE CANAVERAL AIR FORCE STATION, MISSILE ASSEMBLY HAER FL-8-B BUILDING AE HAER FL-8-B (John F. Kennedy Space Center, Hanger AE) Cape Canaveral Brevard County Florida PHOTOGRAPHS WRITTEN HISTORICAL AND DESCRIPTIVE DATA HISTORIC AMERICAN ENGINEERING RECORD SOUTHEAST REGIONAL OFFICE National Park Service U.S. Department of the Interior 100 Alabama St. NW Atlanta, GA 30303 HISTORIC AMERICAN ENGINEERING RECORD CAPE CANAVERAL AIR FORCE STATION, MISSILE ASSEMBLY BUILDING AE (Hangar AE) HAER NO. FL-8-B Location: Hangar Road, Cape Canaveral Air Force Station (CCAFS), Industrial Area, Brevard County, Florida. USGS Cape Canaveral, Florida, Quadrangle. Universal Transverse Mercator Coordinates: E 540610 N 3151547, Zone 17, NAD 1983. Date of Construction: 1959 Present Owner: National Aeronautics and Space Administration (NASA) Present Use: Home to NASA’s Launch Services Program (LSP) and the Launch Vehicle Data Center (LVDC). The LVDC allows engineers to monitor telemetry data during unmanned rocket launches. Significance: Missile Assembly Building AE, commonly called Hangar AE, is nationally significant as the telemetry station for NASA KSC’s unmanned Expendable Launch Vehicle (ELV) program. Since 1961, the building has been the principal facility for monitoring telemetry communications data during ELV launches and until 1995 it processed scientifically significant ELV satellite payloads. Still in operation, Hangar AE is essential to the continuing mission and success of NASA’s unmanned rocket launch program at KSC. It is eligible for listing on the National Register of Historic Places (NRHP) under Criterion A in the area of Space Exploration as Kennedy Space Center’s (KSC) original Mission Control Center for its program of unmanned launch missions and under Criterion C as a contributing resource in the CCAFS Industrial Area Historic District. -
Physical & Thermodynamic Properties Of
PHYSICAL & THERMODYNAMIC PROPERTIES OF HYPERGOLIC PROPELLANTS: A REVIEW AND UPDATE S.L ARNOLD ENSCO, INC. VANDENBERG AFB, CA ABSTRACT Significant errors and omissions were found in some of the reported literature values for nitrogen tetroxide, monomethylhydrazine, and Aerozine-50. The methods used to try and resolve some of these errors included (1) a comparison of various literature values, including an assessment of data quality, to determine whether reported values were measured or estimated, (2) a derivation of temperature dependent correlation coefficients and validation with independent measurements (where sufficient measured data were available), and (3) an estimation of the missing parameters using modern techniques such as the method of corresponding states or group contribution methods. Utilizing these methods resulted in a validated set of properties (many as functions temperature) for hypergolic propellants, which are suitable for environmental modeling applications and more general engineering calculations. The complete parameter set is provided, along with references and examples illustrating the above methods. Also, mixing rules, pseudo-critical properties, and mixture properties are provided for a nominal composition Aerozine-50 mixture. INTRODUCTION The objective of this work was to find and validate existing hypergol parameters for use in environmental modeling applications. However, standard references and chemical engineering journals either do not have all of the required data, such as vapor viscosity as a function of temperature, or they contain crudely estimated values and outright errors. Although they contain some of the more hard to find parameters, the current propellant manuals no longer contain the ancillary information regarding data quality, sources, etc. Also, some of the reported data is mis- represented, i.e., if the original experiment was not specifically designed to measure critical properties, it’s most likely not an appropriate source for those parameters (especially when the original author has so stated). -
Instrument Host Overview - Spacecraft ======
Instrument Host Overview - Spacecraft ===================================== Launch Vehicle Description -------------------------- The launch vehicle used for Mars Pathfinder was the McDonnell Douglas Delta II 7925. An engine section in the Delta first stage housed the Rocketdyne RS-27 main engine and two Rocketdyne LR101-NA-11 vernier engines. The vernier engines provided roll control during main engine burn, and attitude control after main engine cutoff and before second stage separation. The RS-27 main engine was a single start, liquid bi-propellant rocket engine which provided approximately 894,094 N of thrust at lift off. The first stage propellant load (96,000 kg) consisted of RP-1 fuel (thermally stable kerosene) and liquid oxygen as an oxidizer. The RP-1 fuel tank and liquid oxygen tank were separated by a center body section that housed control electronics, ordnance sequencing equipment, a telemetry system, and a rate gyro. First stage thrust augmentation was provided by nine solid-propellant Graphite Epoxy Motors (GEMs), each fueled with 12,000 kg of hydroxyl-terminated polybutadiene solid propellant. Each GEM provided an average thrust of 439,796 N at lift off. The main engine, vernier engines, and six of the GEMs were ignited at lift off. The remaining three GEMs were ignited in flight. The GEMs were jettisoned from the first stage after motor burnout. The interstage assembly extended from the top of the first stage to the second stage mini-skirt. This assembly carried loads to the first stage, and contained an exhaust vent and six spring driven separation rods. The Delta II 7925 second stage propulsion system included a restartable, liquid bi-propellant Aerojet AJ10-118K engine that consumed Aerozine 50 fuel (a 50/50 mix of hydrazine and asymmetric dimethyl hydrazine) and nitrogen tetroxide (N2O4). -
Falcon 1 User's Guide
Falcon 1 Launch Vehicle Payload User’s Guide Rev 7 TABLE OF CONTENTS 1. Introduction 4 1.1. Revision History 4 1.2. Purpose 6 1.3. Company Description 6 1.4. Falcon Program Overview 6 1.5. Mission Management 7 2. Falcon 1 Launch Vehicles 8 2.1. Overview 8 2.1.1. Falcon 1 9 2.1.2. Falcon 1e 11 2.2. Availability 12 2.3. Reliability 13 2.4. Performance 15 2.5. Pricing 16 2.6. Standard Services 16 2.7. Non‐standard Services 16 2.8. Vehicle Axes/Attitude Definitions 17 3. Requirements & Environments 18 3.1. Mass Properties 18 3.2. Payload Interfaces 19 3.2.1. Falcon Payload Attach Fittings 19 3.2.2. Test Fittings and Fitcheck Policy 19 3.2.3. Electrical Design Criteria 19 3.3. Documentation Requirements 21 3.4. Payload Environments 23 3.4.1. Transportation Environments 23 3.4.2. Humidity, Cleanliness and Thermal Control 23 3.4.3. Payload Air Conditioning 24 3.4.4. Launch and Flight Environments 24 4. Facilities 32 4.1. Headquarters – Hawthorne, California 32 4.2. Washington, DC 32 4.3. Test Facility ‐ Central Texas 32 4.4. Launch Site – Kwajalein Atoll 33 4.4.1. Processing Services and Equipment 33 5. Launch Operations 36 5.1. Launch Control Organization 36 5.2. Mission Integration 37 5.2.1. Payload Transport to Launch Site 38 5.2.2. Payload Integration 38 5.2.3. Example Flight Profiles 41 D000973 Rev Falcon 1 User’s Guide ‐ D000973 Rev. 7 Page | 3 6. -
Gao-21-306, Nasa
United States Government Accountability Office Report to Congressional Committees May 2021 NASA Assessments of Major Projects GAO-21-306 May 2021 NASA Assessments of Major Projects Highlights of GAO-21-306, a report to congressional committees Why GAO Did This Study What GAO Found This report provides a snapshot of how The National Aeronautics and Space Administration’s (NASA) portfolio of major well NASA is planning and executing projects in the development stage of the acquisition process continues to its major projects, which are those with experience cost increases and schedule delays. This marks the fifth year in a row costs of over $250 million. NASA plans that cumulative cost and schedule performance deteriorated (see figure). The to invest at least $69 billion in its major cumulative cost growth is currently $9.6 billion, driven by nine projects; however, projects to continue exploring Earth $7.1 billion of this cost growth stems from two projects—the James Webb Space and the solar system. Telescope and the Space Launch System. These two projects account for about Congressional conferees included a half of the cumulative schedule delays. The portfolio also continues to grow, with provision for GAO to prepare status more projects expected to reach development in the next year. reports on selected large-scale NASA programs, projects, and activities. This Cumulative Cost and Schedule Performance for NASA’s Major Projects in Development is GAO’s 13th annual assessment. This report assesses (1) the cost and schedule performance of NASA’s major projects, including the effects of COVID-19; and (2) the development and maturity of technologies and progress in achieving design stability.