DOCSLIB.ORG

United Launch Alliance Advanced Development

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
United Launch Alliance Advanced Development United Launch Alliance Advanced Development August 28, 2007 Bernard Kutter Dwight Drefs 303-269-5538 303-269-5470 [email protected] [email protected] Copyright © 2006 ULA. All rights reserved. Agenda ! ULA overview –Existing products ! ULA advanced programs –Secondary and multiple payloads –Large payload fairings –Lunar missions –Cargo transfer vehicles –Advanced common evolved stage –Long duration cryo storage –On-orbit refueling –Flight demonstration 1 Copyright © 2006 ULA. All rights reserved. ULA Overview ! 50/50 joint Lockheed Martin/Boeing ownership –Responsible for all Atlas and Delta design, engineering, production, and U.S. government sales ! Strengthened Ability to Ensure Mission Success ! Assured Access via Two Independent Systems ! Reduced Costs –Consolidated Infrastructure –Integrated Streamlined Management ! Favorable Environment for Innovation Superior Performance, Lower Costs = Mission Success 2 Copyright © 2006 ULA. All rights reserved. Launch Vehicle Products Medium Class Intermediate – Heavy Class Delta II Delta IV Delta IV Heavy Atlas V 100% mission success is imperative 3 Copyright © 2006 ULA. All rights reserved. ULA Upper Stages ! ULA is currently flying 4 upper stages Delta 2 stage 2 Centaur Delta IV stage 2 Delta IV stage 2 1.0 mT dry 2.1 mT dry 4m diameter 5m diameter 5.9 mT propellant 21 mT propellant 2.8 mT dry 3.5 mT dry 21 mT propellant 27 mT propellant 4 Copyright © 2006 ULA. All rights reserved. Atlas Evolution Atlas V Family Phase 1 Family Phase 2 Family Phase 3 Addition Baseline Phase 1 Phase 2 Phase 3A Phase 3B HLV (Wide Body Centaur) (Wide Body Booster) (5 Body) (5 Body) (9-28 mT LEO) (9-40 mT LEO) (9-74 mT LEO) (107 mT) (54-140 mT) (33 mT w/ Options) (45 mT w/ Options) (90 mT w/ Options) -or- 7.2M PLF 8.4M PLF 5.4M Cent. Tank 1 to 4 RL10’s 5.4M Booster Tank Cluster 5.4M CCB 8.4M Tank 5 RD-180’s 1 to 2 RD-180’s Existing Pad and Existing Pad and Existing Pad and New Launch New Launch Infrastructure Infrastructure Infrastructure Site Site Centaur Engine Out Centaur and Booster Engine Out Logical, Low Risk Path to Enhanced Performance 5 Copyright © 2006 ULA. All rights reserved. Delta Evolution 50 s ) t 4 n e , ) ) e 5 d ! 2 Double the Payload ( 2 , a , m e r 4 5 + m e ( Capability ( d 40 g u c M a i p + + n r d u a ! M g Up to 6.5-m Diameter M e e h s p A M g n u Fairing s M 8 A a e 6 t e E M 8 - r s g 30 6 G E ! s e Up to 85-ft Length Fairing S - A a d h t G 6 R n M 8 S t s 2 6 E o 6 R + + ! - Existing Infrastructure d ) G n A S + + + + k 2 8 r 6 R ! Minor Pad Modifications 6 o - + + + w S 20 - ! Existing RS-68A y R n i v ( + a (in development) e LEO Payload* (t) H ! East and West Coast 10 Capable ! Potential for Common Growth Upper Stage with Atlas V 0 Current Delta IV Family Delta IV Heavy+ (6.5-m Fairing) *Ref orbit: 407-km circular at 28.5-deg inc. 6 Copyright © 2006 ULA. All rights reserved. ULA Advanced Programs ! ULA IRAD investments include transportation capabilities not currently offered ! NASA’s exploration program offers a very exciting opportunity to extend ULA’s core competencies –Launch –In-Space stages –Landers 7 Copyright © 2006 ULA. All rights reserved. Secondary Payload Options Atlas Atlas Delta Delta Atlas Delta Type-C Carrier Integrated Payload Secondary Attach Carrier (IPC) (TCC) 35 lbs ea. Mounting (SAM) Reduced-Height • NASA funded phase-1 study Dual Payload • Supports Large/Multiple SPs • Uses CalPoly pPod dispenser • 3 Payloads up to 300-lbs Attach • Used for LCROSS mission • Clampband interface Fitting (DPAF) • Payloads up to 3000-lbs Atlas • Clampband interface Atlas Atlas Delta Existing Secondary Payload Carrier Mounting (SPC) 125 lbs ea. Brackets • Up to (4) on a C-adapter EELV Secondary Payload Aft Bulkhead Carrier Adapter (ESPA) 400 lb ea. (ABC) 100 lbs ea. • Proven on STP-1 8 Copyright © 2006 ULA. All rights reserved. Dual Spacecraft System (DSS) Payload Envelope: ! Low cost medium dual No DSS Plugs payload carrier 100” Dia ! Derived from existing flight 50” hardware Dia –2 Centaur forward adapters 50” 100” Tall –4m PLF separation bolts Three DSS Plugs 100” Dia DSS 50” Dia 125”175” Tall Atlas V or Delta IV 9 Copyright © 2006 ULA. All rights reserved. Common DPC Configuration on Atlas ! Dual Payload Carrier (DPC) is a 77ft PLF common adapter for both Atlas & Delta launch vehicles to launch two Upper Payload primary payloads on a single mission Envelope (PLE) Lower PLE DPC located Common DPC within 77 ft. PLF on Atlas V 5xx 10 Copyright © 2006 ULA. All rights reserved. Common DPC Configuration on Delta 63-ft PLF Upper Payload Envelope (PLE) Lower PLE Common DPC DPC Located within 63-ft PLF on Delta IV Heavy 11 Copyright © 2006 ULA. All rights reserved. Larger Payload Fairings ! Larger payload fairings can be accommodated within current 110’ system infrastructure 6.5-m – Longer PLF’s 86-ft length – Larger diameter PLF’s 87’ 77’ ! Enhanced PLFs derived 14’ 68’ from current design – Delta IV heritage: 10’ to 4-m to 5-m – Flight proven heritage separation systems 4.2m 5.4m 5.4m 7m 14’ 17.8’ 17.8’ 22’ 12 Copyright © 2006 ULA. All rights reserved. Lunar Missions De-Orbit ! Numerous transportation Burn architecture options Descent ! Key considerations include: Lunar Orbit – Mission design Coast • Staging at LEO, TLI, LOI,… • Upper stage lunar impactor Landing Burn – Launch vehicle Lunar Insertion Burn • Number of stages: 3 or 4 • Propellant (storable/cryogenic) Launch Trans-Lunar Coast Low Earth Earth Orbit Orbit Insertion Burn Earth Departure Burn Possible Delivery Points Optimal Transportation Architecture Depends on Mission Requirements 13 Copyright © 2006 ULA. All rights reserved. LPRP Possible Launch Options Assumptions: Legend Payload Lander dry/prop mass -MF derived from Delta 2 2nd stage -ISP = 320 -TLI: C3=-1.9 km2/sec2 401+storable lander 0.5 0.7/2.5 0.7/2.5 -2,560 m/s for LOI+Descent Stage during TLI Reference: nd 431+storable lander 1.3 0.7/3.6 Delta 2 2 stage: 1.0 / 5.9 mT Stage during TLI Star 48 0.23 / 1.9 mT Centaur 2.1 / 21 mT DIV US 4m 2.8 / 21 mT 551+storable lander 1.7 0.8/3.8 Stage after TLI DIV US 5m 3.5 / 27 mT In Work 552S+taDg2e dUuSr+insgt oTrLaI b&le d ularinndg eLrOI 2.8 0.9/5.6 A-HLV+storaSbtalege l aanftdere TrLI In Work D-HLSVta+gDe 2a fUteSr +TsLtIo &ra dbulrein lga ndedsecrent 2.5 0.7/3.3 552+2nd CeSntatageu sr+ubst LoErOa b&le d ularinndg eLrOI 3.9 3.1/32 Stage during TLI A-HLV+Centaur derived lander 4.6 0.7/2.7 Stage during TLI & during descent HLV+2nd Centaur+storable lander 0 1 Lun2 ar Land3ed Mass4 (mT) 5 6 7 Mass (mT) ULA Provides Alternative Lunar Transportation Options 14 Copyright © 2006 ULA. All rights reserved. Long Duration US Operations ! Reasonable upgrades enable long duration missions –Hours to several months using passive thermal management only ! Multi-Layer Insulation (MLI) ! Sun shield Solar Power Adapter ! Thermodynamic vent system (TVS) – Vapor venting in low-g ! Vapor cooled shield(s) (VCS) Navigation update – Boiler + Superheat – Penetration thermal shorting (e.g. fill/feed/vent lines) Improved Thermal Control using TVS ! Vehicle orientation ! H para-ortho conversion 2 Additional N2H4 – Increased heat capacity Centaur Delta IV US 15 Copyright © 2006 ULA. All rights reserved. Large US Derived Landers ! Upgrades enable upper stage derived landers –Landing large cryo stage vertically poses issues • Very tall stage • Requires deep throttling of RL10 Horizontal Landing Offers Advantages –Horizontal landing with auxiliary propulsion attractive –Large payload capability –Provides potential linkage to LSAM Large tanks & hardware may Large residual H2 & O2 benefit insitu and base beneficial for ground operations External “Hot” Structure & Landing Payload/Equipment Mounts Propellant Sidewall & Solar Power Bulkhead MLI Landing Adapter Thrusters 16 Copyright © 2006 ULA. All rights reserved. Commercial LEO Delivery ! Potential New Market for Construction, Crew and Cargo Delivery to Low Bigelow Habitat Earth Orbit (LEO) ISS – Service to Destinations SpaceX Dragon with Permanent Human Presence ATV Rocketplane Kistler – ISS exists, Bigelow OV-1 Habitat in Planning Stage ! Commercial LEO SpaceDev DreamChaser Transportation System HTV Consists of Two Elements: Launch Vehicle & Transfer TRANSFER VEHICLE Vehicle LAUNCH VEHICLE * Photos courtesy of NASA, Bigelow Aerospace, SpaceX, Rocketplane Kistler , SpaceDev 17 Copyright © 2006 ULA. All rights reserved. ARCTUS: Astrotech Research & Conventional Technology Utilization Spacecraft ! Cargo Delivery Vehicle o – Capability A/B/C rg ! Evolved From Existing a Components /C – Structure/Propulsion: Centaur w – Avionics/ProxOps: Orbital Express re – Reentry: IRVE & PaiDai l C ! Compatible with existing, ia flight-proven vehicles rc ! Features e – Flexible performance m – Existing payload processing m – Based on flight proven o elements C – Benign ascent environments – Low impact return/recovery 18 Copyright © 2006 ULA. All rights reserved. Advanced Common Evolved Stage (ACES) 1 RL10 Vehicle equipment Vapor- Monocoque Al cooled Payload adapters 2 RL10 Aft thrust structure alloy tank structure forward skirt Booster severance system Monolithic spun Aft skirt domes 4 RL10 6 RL10 H2 vent Tank interface ring Coaxial VJ H2 ducts sump Engine interface structure Modular Design Maximizes Utility, Minimizes Risk & Cost 19 Copyright © 2006 ULA. All rights reserved. Friction Stir Weld ! Developing next generation tank construction –Extending Delta’s current longitudinal FSW to circumferential and thinner gauge Aluminum alloys (0.04” to 0.1”) –Goal to implement circumferential FSW on Atlas Booster at Decatur –Goal: Reduce ACES tank weight by 2 relative to Centaur 20 Copyright © 2006 ULA.
Load more

Recommended publications
  • Vulcan Centaur
    VULCAN CENTAUR The Vulcan Centaur rocket design leverages the flight-proven success of the Delta IV and Atlas V launch vehicles while introducing new technologies and innovative features to ensure a reliable and aordable space launch service. Vulcan Centaur will service a diverse range of markets including 225 ft commercial, civil, science, cargo and national security space customers. 1 The spacecraft is encapsulated in a 5.4-m- (17.7-ft-) diameter payload fairing (PLF), a sandwich composite structure made with a vented aluminum-honeycomb core and graphite-epoxy face sheets. The bisector (two-piece shell) PLF encapsulates the spacecraft. The payload attach fitting (PAF) is a similar sandwich composite structure creating the mating interface from spacecraft to second stage. The PLF separates using a debris-free horizontal and vertical separation system with 2 200 ft spring packs and frangible joint assembly. The payload fairing is available in the 15.5-m (51-ft) standard and 21.3-m (70-ft) 1 long configurations. The Centaur upper stage is 5.4 m (17.7 ft) in diameter and 3 11.7 m (38.5 ft) long with a 120,000-lb propellant capacity. Its propellant tanks are constructed of pressure-stabilized, corrosion-resistant stainless steel. Centaur is a liquid hydrogen/liquid oxygen-fueled vehicle, with two RL10C 4 engines. The Vulcan Centaur Heavy vehicle, flies the upgraded 2 Centaur using RL10CX engines with nozzle extensions. The 5 175 ft cryogenic tanks are insulated with spray-on foam insulation (SOFI) to manage boil o of cryogens during flight. An aft equipment shelf provides the structural mountings for vehicle electronics.
    [Show full text]
  • ULA Atlas V Launch to Feature Full Complement of Aerojet Rocketdyne Solid Rocket Boosters
    April 13, 2018 ULA Atlas V Launch to Feature Full Complement of Aerojet Rocketdyne Solid Rocket Boosters SACRAMENTO, Calif., April 13, 2018 (GLOBE NEWSWIRE) -- The upcoming launch of the U.S. Air Force Space Command (AFSPC)-11 satellite aboard a United Launch Alliance Atlas V rocket from Cape Canaveral Air Force Station, Florida, will benefit from just over 1.74 million pounds of added thrust from five AJ-60A solid rocket boosters supplied by Aerojet Rocketdyne. The mission marks the eighth flight of the Atlas V 551 configuration, the most powerful Atlas V variant that has flown to date. The Atlas V 551 configuration features a 5-meter payload fairing, five AJ-60As and a Centaur upper stage powered by a single Aerojet Rocket RL10C-1 engine. This configuration of the U.S. government workhorse launch vehicle is capable of delivering 8,900 kilograms of payload to geostationary transfer orbit (GTO), and also has been used to send scientific probes to explore Jupiter and Pluto. The Centaur upper stage also uses smaller Aerojet Rocketdyne thrusters for pitch, yaw and roll control, while both stages of the Atlas V employ pressurization vessels built by Aerojet Rocketdyne's ARDÉ subsidiary. "The Atlas V is able to perform a wide variety of missions for both government and commercial customers, and the AJ-60A is a major factor in that versatility," said Aerojet Rocketdyne CEO and President Eileen Drake. "Aerojet Rocketdyne developed the AJ-60A specifically for the Atlas V, delivering the first booster just 42 months after the contract award, which underscores our team's ability to design and deliver large solid rocket motors in support of our nation's strategic goals and efforts to explore our solar system." The flight of the 100th AJ-60A, the largest monolithically wound solid rocket booster ever flown, took place recently as part of a complement of four that helped an Atlas V 541 place the nation's newest weather satellite into GTO.
    [Show full text]
  • Starliner Rudolf Spoor Vertregt-Raket Van De Hoofdredacteur
    Starliner Rudolf Spoor Vertregt-raket Van de hoofdredacteur: Ook de NVR ontsnapt niet aan de gevolgen van het Corona- virus: zoals u in de nieuwsbrief heeft kunnen lezen zijn we genoodzaakt geweest de voor maart, april en mei geplande evenementen op te schorten. In de tussentijd zijn online ruimtevaart-gerelateerde initiatieven zeer de moeite waard om te volgen, en in de nieuwsbrief heeft u daar ook een overzicht van kunnen vinden. De redactie heeft zijn best gedaan om ook in deze moeilijke tijden voor u een afwisselend nummer samen te stellen, met onder andere aandacht voor de lancering van de eerste Starliner, een studentenproject waarin een supersone para- Bij de voorplaat chute getest wordt, tests van een prototype maanrover op het DECOS terrein in Noordwijk en een uitgebreide analyse Kunstzinnige weergave van de lancering van de Vertregt-raket vanuit met moderne middelen van het Vertregt raketontwerp uit de Suriname. De vlammen zijn gebaseerd op die van andere raketten jaren ‘50. Dit laatste artikel is geïnspireerd door de biografie met dezelfde stuwstoffen. [achtergrond: ESA] van Marius Vertregt die in het tweede nummer van 2019 gepubliceerd werd, en waarvan we een Engelstalige versie hebben ingediend voor het IAC 2020 in Dubai. Dit artikel is ook daadwerkelijk geselecteerd voor presentatie op de confe- rentie, maar door de onzekerheden rond het Coronavirus is de conferentie helaas een jaar uitgesteld. Ook andere artikelen uit Ruimtevaart worden in vertaalde vorm overgenomen door Engelstalige media. Zo verscheen het artikel van Henk Smid over Iraanse ruimtevaart uit het eerste nummer van dit jaar zelfs in de bekende online publicatie The Space Review.
    [Show full text]
  • Centaur Dl-A Systems in a Nutshell
    NASA Technical Memorandum 88880 '5 t I Centaur Dl-A Systems in a Nutshell (NASA-TM-8888o) CElTAUR D1-A SYSTEBS IN A N87- 159 96 tiljTSBELL (NASA) 29 p CSCL 22D Andrew L. Gordan Lewis Research Center Cleveland, Ohio January 1987 . CENTAUR D1-A SYSTEMS IN A NUTSHELL Andrew L. Gordan National Aeronautics and Space Administration Lewis Research Center Cleveland, Ohio 44135 SUMMARY This report identifies the unique aspects of the Centaur D1-A systems and subsystems. Centaur performance is described in terms of optimality (pro- pellant usage), flexibility, and airborne computer requirements. Major I-. systems are described narratively with some numerical data given where it may 03 CJ be useful. v, I W INTRODUCT ION The Centaur D1-A launch vehicle continues to be a key element in the Nation's space program. The Atlas/Centaur and Titan/Centaur combinations have boosted into orbit a variety of spacecraft on scientific, lunar, and planetary exploration missions and Earth orbit missions. These versatile, reliable, and accurate space booster systems will contribute to many significant space pro- grams well into the shuttle era. Centaur D1-A is the latest version of the Nation's first high-energy cryogenic launch vehicle. Major improvements in avionics and payload struc- ture have enhanced mission flexibility and mission success reliability. The liquid hydrogen and liquid oxygen propellants and the pressurized stainless steel structure provide a top-performance vehicle. Centaur's primary thrust comes from two Pratt 8, Whitney constant- thrust, turbopump-fed, regeneratively cooled, liquid-fueled rocket engines. Each RL10A-3-3a engine can generate 16 500 lb of thrust, for a total thrust of 33 000 lb.
    [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]
  • Orion Capsule Launch Abort System Analysis
    Orion Capsule Launch Abort System Analysis Assignment 2 AE 4802 Spring 2016 – Digital Design and Manufacturing Georgia Institute of Technology Authors: Tyler Scogin Michel Lacerda Jordan Marshall Table of Contents 1. Introduction ......................................................................................................................................... 4 1.1 Mission Profile ............................................................................................................................. 7 1.2 Literature Review ........................................................................................................................ 8 2. Conceptual Design ............................................................................................................................. 13 2.1 Design Process ........................................................................................................................... 13 2.2 Vehicle Performance Characteristics ......................................................................................... 15 2.3 Vehicle/Sub-Component Sizing ................................................................................................. 15 3. Vehicle 3D Model in CATIA ................................................................................................................ 22 3.1 3D Modeling Roles and Responsibilities: .................................................................................. 22 3.2 Design Parameters and Relations:............................................................................................
    [Show full text]
  • 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.
    [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]
  • Interstellar Probe on Space Launch System (Sls)
    INTERSTELLAR PROBE ON SPACE LAUNCH SYSTEM (SLS) David Alan Smith SLS Spacecraft/Payload Integration & Evolution (SPIE) NASA-MSFC December 13, 2019 0497 SLS EVOLVABILITY FOUNDATION FOR A GENERATION OF DEEP SPACE EXPLORATION 322 ft. Up to 313ft. 365 ft. 325 ft. 365 ft. 355 ft. Universal Universal Launch Abort System Stage Adapter 5m Class Stage Adapter Orion 8.4m Fairing 8.4m Fairing Fairing Long (Up to 90’) (up to 63’) Short (Up to 63’) Interim Cryogenic Exploration Exploration Exploration Propulsion Stage Upper Stage Upper Stage Upper Stage Launch Vehicle Interstage Interstage Interstage Stage Adapter Core Stage Core Stage Core Stage Solid Solid Evolved Rocket Rocket Boosters Boosters Boosters RS-25 RS-25 Engines Engines SLS Block 1 SLS Block 1 Cargo SLS Block 1B Crew SLS Block 1B Cargo SLS Block 2 Crew SLS Block 2 Cargo > 26 t (57k lbs) > 26 t (57k lbs) 38–41 t (84k-90k lbs) 41-44 t (90k–97k lbs) > 45 t (99k lbs) > 45 t (99k lbs) Payload to TLI/Moon Launch in the late 2020s and early 2030s 0497 IS THIS ROCKET REAL? 0497 SLS BLOCK 1 CONFIGURATION Launch Abort System (LAS) Utah, Alabama, Florida Orion Stage Adapter, California, Alabama Orion Multi-Purpose Crew Vehicle RL10 Engine Lockheed Martin, 5 Segment Solid Rocket Aerojet Rocketdyne, Louisiana, KSC Florida Booster (2) Interim Cryogenic Northrop Grumman, Propulsion Stage (ICPS) Utah, KSC Boeing/United Launch Alliance, California, Alabama Launch Vehicle Stage Adapter Teledyne Brown Engineering, California, Alabama Core Stage & Avionics Boeing Louisiana, Alabama RS-25 Engine (4)
    [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]
  • 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.
    [Show full text]
  • Delta IV Parker Solar Probe Mission Booklet
    A United Launch Alliance (ULA) Delta IV Heavy what is the source of high-energy solar particles. MISSION rocket will deliver NASA’s Parker Solar Probe to Parker Solar Probe will make 24 elliptical orbits an interplanetary trajectory to the sun. Liftoff of the sun and use seven flybys of Venus to will occur from Space Launch Complex-37 at shrink the orbit closer to the sun during the Cape Canaveral Air Force Station, Florida. NASA seven-year mission. selected ULA’s Delta IV Heavy for its unique MISSION ability to deliver the necessary energy to begin The probe will fly seven times closer to the the Parker Solar Probe’s journey to the sun. sun than any spacecraft before, a mere 3.9 million miles above the surface which is about 4 OVERVIEW The Parker percent the distance from the sun to the Earth. Solar Probe will At its closest approach, Parker Solar Probe will make repeated reach a top speed of 430,000 miles per hour journeys into the or 120 miles per second, making it the fastest sun’s corona and spacecraft in history. The incredible velocity trace the flow of is necessary so that the spacecraft does not energy to answer fall into the sun during the close approaches. fundamental Temperatures will climb to 2,500 degrees questions such Fahrenheit, but the science instruments will as why the solar remain at room temperature behind a 4.5-inch- atmosphere is thick carbon composite shield. dramatically Image courtesy of NASA hotter than the The mission was named in honor of Dr.
    [Show full text]