Iac-09-D2.8.2 Ares V: Shifting the Payload Design Paradigm
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Mission to Jupiter
This book attempts to convey the creativity, Project A History of the Galileo Jupiter: To Mission The Galileo mission to Jupiter explored leadership, and vision that were necessary for the an exciting new frontier, had a major impact mission’s success. It is a book about dedicated people on planetary science, and provided invaluable and their scientific and engineering achievements. lessons for the design of spacecraft. This The Galileo mission faced many significant problems. mission amassed so many scientific firsts and Some of the most brilliant accomplishments and key discoveries that it can truly be called one of “work-arounds” of the Galileo staff occurred the most impressive feats of exploration of the precisely when these challenges arose. Throughout 20th century. In the words of John Casani, the the mission, engineers and scientists found ways to original project manager of the mission, “Galileo keep the spacecraft operational from a distance of was a way of demonstrating . just what U.S. nearly half a billion miles, enabling one of the most technology was capable of doing.” An engineer impressive voyages of scientific discovery. on the Galileo team expressed more personal * * * * * sentiments when she said, “I had never been a Michael Meltzer is an environmental part of something with such great scope . To scientist who has been writing about science know that the whole world was watching and and technology for nearly 30 years. His books hoping with us that this would work. We were and articles have investigated topics that include doing something for all mankind.” designing solar houses, preventing pollution in When Galileo lifted off from Kennedy electroplating shops, catching salmon with sonar and Space Center on 18 October 1989, it began an radar, and developing a sensor for examining Space interplanetary voyage that took it to Venus, to Michael Meltzer Michael Shuttle engines. -
JUICE Red Book
ESA/SRE(2014)1 September 2014 JUICE JUpiter ICy moons Explorer Exploring the emergence of habitable worlds around gas giants Definition Study Report European Space Agency 1 This page left intentionally blank 2 Mission Description Jupiter Icy Moons Explorer Key science goals The emergence of habitable worlds around gas giants Characterise Ganymede, Europa and Callisto as planetary objects and potential habitats Explore the Jupiter system as an archetype for gas giants Payload Ten instruments Laser Altimeter Radio Science Experiment Ice Penetrating Radar Visible-Infrared Hyperspectral Imaging Spectrometer Ultraviolet Imaging Spectrograph Imaging System Magnetometer Particle Package Submillimetre Wave Instrument Radio and Plasma Wave Instrument Overall mission profile 06/2022 - Launch by Ariane-5 ECA + EVEE Cruise 01/2030 - Jupiter orbit insertion Jupiter tour Transfer to Callisto (11 months) Europa phase: 2 Europa and 3 Callisto flybys (1 month) Jupiter High Latitude Phase: 9 Callisto flybys (9 months) Transfer to Ganymede (11 months) 09/2032 – Ganymede orbit insertion Ganymede tour Elliptical and high altitude circular phases (5 months) Low altitude (500 km) circular orbit (4 months) 06/2033 – End of nominal mission Spacecraft 3-axis stabilised Power: solar panels: ~900 W HGA: ~3 m, body fixed X and Ka bands Downlink ≥ 1.4 Gbit/day High Δv capability (2700 m/s) Radiation tolerance: 50 krad at equipment level Dry mass: ~1800 kg Ground TM stations ESTRAC network Key mission drivers Radiation tolerance and technology Power budget and solar arrays challenges Mass budget Responsibilities ESA: manufacturing, launch, operations of the spacecraft and data archiving PI Teams: science payload provision, operations, and data analysis 3 Foreword The JUICE (JUpiter ICy moon Explorer) mission, selected by ESA in May 2012 to be the first large mission within the Cosmic Vision Program 2015–2025, will provide the most comprehensive exploration to date of the Jovian system in all its complexity, with particular emphasis on Ganymede as a planetary body and potential habitat. -
The J–2X Engine Powering NASA’S Ares I Upper Stage and Ares V Earth Departure Stage
The J–2X Engine Powering NASA’s Ares I Upper Stage and Ares V Earth Departure Stage The U.S. launch vehicles that will carry nozzle. It will weigh approximately 5,300 explorers back to the moon will be powered pounds. With 294,000 pounds of thrust, the in part by a J–2X engine that draws its engine will enable the Ares I upper stage to heritage from the Apollo-Saturn Program. place the Orion crew exploration vehicle in low-Earth orbit. The new engine, being designed and devel oped in support of NASA’s Constellation The J–2X is being designed by Pratt & Program, will power the upper stages of Whitney Rocketdyne of Canoga Park, Calif., both the Ares I crew launch vehicle and Ares for the Exploration Launch Projects Office at V cargo launch vehicle. NASA’s Marshall Space Flight Center in Huntsville, Ala. The J–2X builds on the The Constellation Program is responsible for legacy of the Apollo-Saturn Program and developing a new family of U.S. crew and relies on nearly a half-century of NASA launch vehicles and related systems and spaceflight experience, heritage hardware technologies for exploration of the moon, and technological advances. Mars and destinations beyond. Fueled with liquid oxygen and liquid hydro The J–2X will measure 185 inches long and gen, the J–2X is an evolved variation of two 120 inches in diameter at the end of its historic predecessors: the powerful J–2 upper stage engine that propelled the Apollo-era Shortly after J–2X engine cutoff, the Orion capsule will Saturn IB and Saturn V rockets to the moon in the separate from the upper stage. -
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. -
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 New Vision for Space Exploration
Constellation The New Vision for Space Exploration Dale Thomas NASA Constellation Program October 2008 The Constellation Program was born from the Constellation’sNASA Authorization Beginnings Act of 2005 which stated…. The Administrator shall establish a program to develop a sustained human presence on the moon, including a robust precursor program to promote exploration, science, commerce and U.S. preeminence in space, and as a stepping stone to future exploration of Mars and other destinations. CONSTELLATION PROJECTS Initial Capability Lunar Capability Orion Altair Ares I Ares V Mission Operations EVA Ground Operations Lunar Surface EVA EXPLORATION ROADMAP 0506 07 08 09 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 LunarLunar OutpostOutpost BuildupBuildup ExplorationExploration andand ScienceScience LunarLunar RoboticsRobotics MissionsMissions CommercialCommercial OrbitalOrbital Transportation ServicesServices forfor ISSISS AresAres II andand OrionOrion DevelopmentDevelopment AltairAltair Lunar LanderLander Development AresAres VV and EarthEarth DepartureDeparture Stage SurfaceSurface SystemsSystems DevelopmentDevelopment ORION: NEXT GENERATION PILOTED SPACECRAFT Human access to Low Earth Orbit … … to the Moon and Mars ORION PROJECT: CREW EXPLORATION VEHICLE Orion will support both space station and moon missions Launch Abort System Orion will support both space stationDesigned and moonto operate missions for up to 210 days in Earth or lunar Designedorbit to operate for up to 210 days in Earth or lunar orbit Designed for lunar -
Progress on the J-2X Upper Stage Engine for the Ares Launch Vehicles
https://ntrs.nasa.gov/search.jsp?R=20080036837mSFC-9;LO 2019-08-30T05:16:33+00:00Z From Concept to Design: Progress on the J-2X Upper Stage Engine for the Ares Launch Vehicles Thomas Byrd, Deputy Manager, J-2X Upper Stage Engine Element Ares Projects Office Marshall Space Flight Center Huntsville, AL 35812 Abstract In accordance with national policy and NASA's Global Exploration Strategy, the Ares Projects Office is embarking on development ofa new launch vehicle fleet to fulfill the national goals ofreplacing the space shuttle fleet, returning to the moon, and exploring farther destinations like Mars. These goals are shaped by the decision to retire the shuttle fleet by 2010, budgetary constraints, and the requirement to create a new fleet that is safer, more reliable, operationally more efficient than the shuttle fleet, and capable ofsupporting long-range exploration goals. The present architecture for the Constellation Program is the result ofextensive trades during the Exploration Systems Architecture Study and subsequent refinement by the Ares Projects Office at Marshall Space Flight Center. The vehicles selected to support those goals are the Ares I crew launch vehicle and the Ares V cargo launch vehicle, the first new human-rated launch vehicles developed by NASA in more than three decades (Figure 1). Ares I will begin its initial operating capability offlying up to six astronauts to the International Space Station (ISS) no later than 2015. Ares V is scheduled to be operational in the 2020 timeframe to support lunar missions. Figure 1. The Ares V Cargo Launch Vehicle (left) and Ares I Crew Launch Vehicle (right) will form the backbone of America's new space fleet. -
Ulyssesulysses
UlyssesUlysses Achievements: first in situ investigation of the inner heliosphere from the solar equator to the poles; first exploration of the dusk sector of Jupiter’s magnetosphere; fastest spacecraft at launch (15.4 km/s) Launch date: 6 October 1990 Mission end: planned September 2004 Launch vehicle/site: NASA Space Shuttle Discovery from Kennedy Space Center, USA Launch mass: 370 kg (including 55 kg scientific payload) Orbit: heliocentric, 1.34x5.4 AU, inclined 79.1° to ecliptic, 6.2 year period Principal contractors: Dornier (prime), British Aerospace (AOCS, HGA), Fokker (thermal, nutation damper), FIAR (power), Officine Galileo (Sun sensors), Laben (data handling), Thomson-CSF (telecommand), MBB (thrusters)] Ulysses is making the first-ever of the heliosphere, and slow wind study of the particles and fields in confined to the equatorial regions), the inner heliosphere at all solar the discovery that high- and low- latitudes, including the polar latitude regions of the heliosphere regions. A Jupiter flyby in February are connected in a much more 1992 deflected Ulysses out of the systematic way than previously ecliptic plane into a high-inclination thought, the first-ever direct solar orbit, bringing it over the Sun’s measurement of interstellar gas south pole for the first time in (both in neutral and ionised state) September 1994 and its north pole and dust particles, and the precise 10.5 months later. Ulysses spent a measurement of cosmic-ray isotopes. total of 234 days at latitudes >70°, These, together with numerous other reaching a maximum 80.2° in both important findings, have resulted in hemispheres. The mission was more than 700 publications to date originally to end in September 1995, in the scientific literature. -
Preparation of Papers for AIAA Technical Conferences
AIAA 2015-4611 SPACE Conferences & Exposition 31 Aug-2 Sep 2015, Pasadena, California AIAA SPACE 2015 Conference and Exposition A Conceptual Mars Exploration Vehicle Architecture with Chemical Propulsion, Near- Term Technology, and High Modularity to Enable Near-Term Human Missions to Mars Mark G. Benton, Sr.* The Boeing Company, El Segundo, CA 90009-2919, USA [Abstract] The Mars Exploration Vehicle (MEV) Architecture was first presented in January, 2012. It describes a possible method to accomplish a long-stay conjunction class Mars surface exploration mission, for 2033 or 2035 opportunities, with a four-person crew and using chemical propulsion, existing or near-term technology, and common modular elements to minimize development costs. It utilizes a common Cryogenic Propulsion Stage (CPS) that can be configured as an Earth Departure Stage (EDS) or Mars Transfer Stage (MTS). It satisfies mission requirements using a combination of Earth orbit rendezvous, aerobraking of unmanned landers, Mars orbit rendezvous, and Mars surface rendezvous. The purpose of this paper is to present major enhancements to the architecture and provide additional design details. The MEV architecture is assembled in low Earth orbit (LEO) from subassemblies launched by Space Launch System rockets and includes a Mars Crew Transfer Vehicle (MCTV) with a crew of four, two redundant unmanned Mars Lander Transfer Vehicles (MLTVs), and four redundant Booster Refueling Vehicles which top off CPS LH2 propellants before Trans-Mars Injection (TMI). The MCTV and its assembly sequence were redesigned to reduce mechanical complexity, enhance design commonality, simplify LEO assembly, and improve mission reliability. Each MLTV utilizes one EDS and one MTS and carries three landers as payload: The Mars Personnel Lander (MPL) provides two-way transport for four crew members between low Mars orbit (LMO) and surface. -
Apollo Rocket Propulsion Development
REMEMBERING THE GIANTS APOLLO ROCKET PROPULSION DEVELOPMENT Editors: Steven C. Fisher Shamim A. Rahman John C. Stennis Space Center The NASA History Series National Aeronautics and Space Administration NASA History Division Office of External Relations Washington, DC December 2009 NASA SP-2009-4545 Library of Congress Cataloging-in-Publication Data Remembering the Giants: Apollo Rocket Propulsion Development / editors, Steven C. Fisher, Shamim A. Rahman. p. cm. -- (The NASA history series) Papers from a lecture series held April 25, 2006 at the John C. Stennis Space Center. Includes bibliographical references. 1. Saturn Project (U.S.)--Congresses. 2. Saturn launch vehicles--Congresses. 3. Project Apollo (U.S.)--Congresses. 4. Rocketry--Research--United States--History--20th century-- Congresses. I. Fisher, Steven C., 1949- II. Rahman, Shamim A., 1963- TL781.5.S3R46 2009 629.47’52--dc22 2009054178 Table of Contents Foreword ...............................................................................................................................7 Acknowledgments .................................................................................................................9 Welcome Remarks Richard Gilbrech ..........................................................................................................11 Steve Fisher ...................................................................................................................13 Chapter One - Robert Biggs, Rocketdyne - F-1 Saturn V First Stage Engine .......................15 -
+ Part 17: Acronyms and Abbreviations (265 Kb PDF)
17. Acronyms and Abbreviations °C . Degrees.Celsius °F. Degrees.Fahrenheit °R . Degrees.Rankine 24/7. 24.Hours/day,.7.days/week 2–D. Two-Dimensional 3C. Command,.Control,.and.Checkout 3–D. Three-Dimensional 3–DOF . Three-Degrees.of.Freedom 6-DOF. Six-Degrees.of.Freedom A&E. Architectural.and.Engineering ACEIT. Automated.Cost-Estimating.Integrated.Tools ACES . Acceptance.and.Checkout.Evaluation.System ACP. Analytical.Consistency.Plan ACRN. Assured.Crew.Return.Vehicle ACRV. Assured.Crew.Return.Vehicle AD. Analog.to.Digital ADBS. Advanced.Docking.Berthing.System ADRA. Atlantic.Downrange.Recovery.Area AEDC. Arnold.Engineering.Development.Center AEG . Apollo.Entry.Guidance AETB. Alumina.Enhanced.Thermal.Barrier AFB .. .. .. .. .. .. .. Air.Force.Base AFE. Aero-assist.Flight.Experiment AFPG. Apollo.Final.Phase.Guidance AFRSI. Advanced.Flexible.Reusable.Surface.Insulation AFV . Anti-Flood.Valve AIAA . American.Institute.of.Aeronautics.and.Astronautics AL. Aluminum ALARA . As.Low.As.Reasonably.Achievable 17. Acronyms and Abbreviations 731 AL-Li . Aluminum-Lithium ALS. Advanced.Launch.System ALTV. Approach.and.Landing.Test.Vehicle AMS. Alpha.Magnetic.Spectrometer AMSAA. Army.Material.System.Analysis.Activity AOA . Analysis.of.Alternatives AOD. Aircraft.Operations.Division APAS . Androgynous.Peripheral.Attachment.System APS. Auxiliary.Propulsion.System APU . Auxiliary.Power.Unit APU . Auxiliary.Propulsion.Unit AR&D. Automated.Rendezvous.and.Docking. ARC . Ames.Research.Center ARF . Assembly/Remanufacturing.Facility ASE. Airborne.Support.Equipment ASI . Augmented.Space.Igniter ASTWG . Advanced.Spaceport.Technology.Working.Group ASTP. Advanced.Space.Transportation.Program AT. Alternate.Turbopump ATCO. Ambient.Temperature.Catalytic.Oxidation ATCS . Active.Thermal.Control.System ATO . Abort-To-Orbit ATP. Authority.to.Proceed ATS. Access.to.Space ATV . Automated.Transfer.Vehicles ATV . -
4.1.6 Interplanetary Travel
Interplanetary 4.1.6 Travel In This Section You’ll Learn to... Outline ☛ Describe the basic steps involved in getting from one planet in the solar 4.1.6.1 Planning for Interplanetary system to another Travel ☛ Explain how we can use the gravitational pull of planets to get “free” Interplanetary Coordinate velocity changes, making interplanetary transfer faster and cheaper Systems 4.1.6.2 Gravity-assist Trajectories he wealth of information from interplanetary missions such as Pioneer, Voyager, and Magellan has given us insight into the history T of the solar system and a better understanding of the basic mechanisms at work in Earth’s atmosphere and geology. Our quest for knowledge throughout our solar system continues (Figure 4.1.6-1). Perhaps in the not-too-distant future, we’ll undertake human missions back to the Moon, to Mars, and beyond. How do we get from Earth to these exciting new worlds? That’s the problem of interplanetary transfer. In Chapter 4 we laid the foundation for understanding orbits. In Chapter 6 we talked about the Hohmann Transfer. Using this as a tool, we saw how to transfer between two orbits around the same body, such as Earth. Interplanetary transfer just extends the Hohmann Transfer. Only now, the central body is the Sun. Also, as you’ll see, we must be concerned with orbits around our departure and Space Mission Architecture. This chapter destination planets. deals with the Trajectories and Orbits segment We’ll begin by looking at the basic equation of motion for interplane- of the Space Mission Architecture.