CALL FOR IDEAS FOR THE RE-USE OF THE MARS EXPRESS PLATFORM PLATFORM CAPABILITIES. D. McCoy
|
|
|
- Kory Preston
- 5 years ago
- Views:
Transcription
1 Mars Express Reuse: Call for Ideas CALL FOR IDEAS FOR THE RE-USE OF THE MARS EXPRESS PLATFORM PLATFORM CAPABILITIES D. McCoy PARIS 23 MARCH 2001 page 1
2 Mars Express Reuse: Call for Ideas PRESENTATION CONTENTS MARS EXPRESS PLATFORM CHARACTERISTICS OPTIMAL DESIGN OF MISSION AND INSTRUMENTS PLANNING STUDY PRIORITIES page 2
3 MARS EXPRESS PLATFORM CHARACTERISTICS PRINCIPLE PHYSICAL CHARACTERISTICS Three Axis stabilised: gyros, star trackers, reaction wheels Bi-propellant Propulsion System: main engine (400 N) and attitude thrusters (10 N) Fixed Communications Antennae: X/S band transmit and receive Single Axis Solar Array Articulation two deployable arrays with rotation motors Fixed orientations for experiment viewing, earth communications and cold face for cryogenic radiators page 3
4 MARS EXPRESS PLATFORM CHARACTERISTICS Experiment Panel Dimensions ~ 1.5 x 1.5 m 25/10/ :39:21 High Gain Antenna = 1.6 m diameter page 4 Solar Array Length = 11 m Cruise Phase Configuration Orbit Phase Configuration
5 MARS EXPRESS PLATFORM CHARACTERISTICS PERFORMANCE CHARACTERISTICS Attitude Control: During NADIR ~ 0.05 deg. With stability deg (30 sec) Slew rate up to 0.15 deg/second with reaction wheels Fuel Load: Tanks capable of ~480 kg (equivalent to ~1500 m/s velocity increment on Mars Express) Data Handling: Maximum data transmission of 228 kbps (without coding) On board mass memory with 12 Gbits capacity page 5
6 MARS EXPRESS PLATFORM CHARACTERISTICS PERFORMANCE CHARACTERISTICS cont d Power System Capable of distributing up to 1500 watts Mars Express maximum power generation is on the order of 750 watts (currently consuming ~600 watts maximum) Three batteries (Lithium Ion) to support eclipse and smooth out power generation fluctuations over mission life. Thermal System Power dissipation is relatively smooth over typical operations cycle allowing passive controls. Radiator (for low temperature at experiment IR sensor) provides 180 deg Kelvin with heat load of 7 watts. page 6
7 MARS EXPRESS PLATFORM CHARACTERISTICS Experiment Panel (interior side) Equipment Panel (interior side) 27/11/ :30:48 Main Engine and Attitude Thrusters Radiator Panel (interior side) Equipment Panel (exterior side with stowed solar array) Propulsion Tank page 7
8 MARS EXPRESS PLATFORM CHARACTERISTICS Experiment Panel (exterior side) Equipment Panel (interior side) 27/11/ :30:12 Star Trackers Radiator Panel (exterior side) Large Experiment Mounting Propulsion Tank Equipment Panel (exterior side with stowed solar array and stowed radar ant.) page 8
9 OPTIMAL DESIGN OF MISSION AND INSTRUMENTS CONSTRAINTS RESULTING FROM THE REUSE OBJECTIVE Structure/propulsion maintain the basic platform/shear wall construction and propulsion layout Spacecraft electrical architecture maintain the existing cold redundant system with reallocation of resources such as power, pyros, data, and commanding Software maintain the core functions and operational modes Launch environment maintain the Soyuz/Fregat launch environment; other launchers might require re-qualifications in Sine/Acoustic. page 9
10 LAUNCH CONFIGURATION ON FREGAT Soyuz Fairing 07/12/ :09:15 Adaptor Insert view of spacecraft in fairing with notes on fairing dimensions, and interface to Fregat. Fregat Upper Stage page 10
11 OPTIMAL DESIGN OF MISSION AND INSTRUMENTS MISSION CONSIDERATIONS Mission operations must be oriented to a store and forward type of approach divide into observation period and a communications period to optimise use of existing operations modes. The thermal environment of the chosen mission can alter the design significantly. Try to work within existing thermal limits (typical operational unit temperatures from -10 to +40 C). Maintain overall spacecraft inertias to minimise changes to the attitude and orbit control system Limited by pointing requirements and reaction wheel capacities as well as dynamics. page 11
12 OPTIMAL DESIGN OF MISSION AND INSTRUMENTS INSTRUMENT CONSIDERATIONS Accommodate experiments within existing envelopes Departures from this will require a new structure design. Use the existing data and power interfaces. Three high rate data carriers (IEEE 1355 ~500 kbps - 10 Mbps. Remaining four are OBDH links (10-80 kbps) Total power to experiments ~ 250 watts. No special EMC or Magnetic requirements for experiments (platform for normal EMC standards). Moderate pointing performance requirements page 12
13 EXAMPLE OF LARGE MARS EXPRESS INSTRUMENT Optical and electronic units of OMEGA during integration at Paris Observatory ( Mass = 29 kg Dimensions ~ 900 x 260 x 380 mm (2 units) page 13
14 PLANNING MINIMUM SCHEDULE Assumes no major developmental undertakings. Refurbishing and use of Mars Express spare units is baselined. Assumes the re-use of MGSE and EGSE as well as test benches and other supporting test items such as software test environments. Based on actual Mars Express planning experience. page 14
15 PLANNING Activity Description Origem % Early Dur u Start Return from Baikonur 0 30JUN03* Early Finish JAFEMAAPMAJUJUAUSEOCNODEJAFEMAAPMAJUJUAUSEOCNODEJAFEMAAPMAJUJUAUSEOCNODEJAFEMAAPMAJUJUAUSEOCNODEJAFEMAAPMAJUJUAUSEOCNODEA Mars Express Refurbishment period 66 30JUN03 29SEP JAN01 01JAN01 Initiate Units Procurement 0 01NOV01* Start manufacture Structure & Propulsion 0 03JUN02* Structure/Propulsion mating start 0 01JUL03* FM Experiment Delivery 0 03NOV03* Procurement of S/C FM Units NOV01 31OCT02 EM Experiment Development MAR02* 31DEC02 FM Experiment Development NOV02* 01JUL03 Test Bench S/W Validation NOV02* 31OCT03 Design/Manufacture Structure/Propulsion NOV01* 31OCT03 Start FM Integration 0 03NOV03* FM System Integration NOV03 01JUL04 FM Environmental Testing JUL04 28FEB05 FM Delivery to ESA 0 01MAR05* ESA Launch Campaign/margin MAR05 29JUL05 Launch 0 01AUG05* Start Date 01JAN01 Early Bar Finish Date 29JUL05 Data Date 01JAN01 Progress Bar Run Date 02MAR01 13:39 Critical Activity Primavera Systems, Inc. Schedule Overview 2005 Science Mission ESA/ESTEC (tentative) page 15
16 STUDY PRIORITIES Accommodation Study The restrictions imposed by the platform re-use require study to ensure scientific objectives can be met. Particular items to clarify with respect to proposed missions are Experiment mounting arrangements and stability needs Platform operations Thermal environments; operational and non-operational Power requirements page 16
Commercial-in-Confidence Ashton Old Baths Financial Model - Detailed Cashflow
Year 0 1 2 3 4 5 6 7 8 9 10 11 12 13 Oct-16 Nov-16 Dec-16 Jan-17 Feb-17 Mar-17 Apr-17 May-17 Jun-17 Jul-17 Aug-17 Sep-17 Oct-17 2,038 2,922 4,089 4,349 6,256 7,124 8,885 8,885 8,885 8,885 8,885 8,885 9,107
Solar Electric Propulsion Benefits for NASA and On-Orbit Satellite Servicing
Solar Electric Propulsion Benefits for NASA and On-Orbit Satellite Servicing Therese Griebel NASA Glenn Research Center 1 Overview Current developments in technology that could meet NASA, DOD and commercial
Exomars Orbiter Module Bus OMB
Exomars Orbiter Module Bus OMB TAS-F 23rd Sept 2010 Exomars Industrial day- Turin 1 Exomars OMB definition Exomars OMB will: serve as a carrier to deliver the EDM at the right landing latitude in the 2016
COMPARISON OF FIXED & VARIABLE RATES (25 YEARS) CHARTERED BANK ADMINISTERED INTEREST RATES - PRIME BUSINESS*
COMPARISON OF FIXED & VARIABLE RATES (25 YEARS) 2 Fixed Rates Variable Rates For Internal Use Only. FIXED RATES OF THE PAST 25 YEARS AVERAGE RESIDENTIAL MORTGAGE LENDING RATE - 5 YEAR* (Per cent) Year
COMPARISON OF FIXED & VARIABLE RATES (25 YEARS) CHARTERED BANK ADMINISTERED INTEREST RATES - PRIME BUSINESS*
COMPARISON OF FIXED & VARIABLE RATES (25 YEARS) 2 Fixed Rates Variable Rates FIXED RATES OF THE PAST 25 YEARS AVERAGE RESIDENTIAL MORTGAGE LENDING RATE - 5 YEAR* (Per cent) Year Jan Feb Mar Apr May Jun
AN OPTIMIZED PROPULSION SYSTEM FOR Soyuz/ST
1 RD-0124 AN OPTIMIZED PROPULSION SYSTEM FOR Soyuz/ST Versailles, May 14,2002 Starsem Organization 2 35% 25% 15% 25% 50-50 European-Russian joint venture providing Soyuz launch services for the commercial
THE KOREASAT5 PROGRAM
THE KOREASAT5 PROGRAM - Design, AI&T, Launch and Operation KT CORPORTION Contents I. Introduction II. Design III. Assembly, Integration and Test (AI&T) IV. Launch V. Operation VI. Q & A THE KOREASAT 5
System Testing by Flight Operators the Rosetta Experience
European Space Operations Center System Testing by Flight Operators the Rosetta Experience E. Montagnon, P. Ferri, L. O Rourke, A. Accomazzo, I. Tanco, J. Morales, M. Sweeney Spaceops 2004, Montréal, Canada,
Copyright 2016 Boeing. All rights reserved.
Boeing s Commercial Crew Program John Mulholland, Vice President and Program Manager International Symposium for Personal and Commercial Spaceflight October 13, 2016 CST-100 Starliner Spacecraft Flight-proven
ITT ISSUE DATE. Selected Bidder - Name of Contractor. Issuing Company ITT Title AO Number STATUS
Selected Bidder Name of Airbus Defence and Space SAS (FR) C1x Subsystems C11 Structure Shielding and Thermal Subsystem AO60156 06/11/2015 Awarded EADS CASA Espacio CASA (ES) C111 MGSE Batch 1 : TDM mockup
Lunette: A Global Network of Small Lunar Landers
Lunette: A Global Network of Small Lunar Landers Leon Alkalai and John O. Elliott Jet Propulsion Laboratory California Institute of Technology LEAG/ILEWG 2008 October 30, 2008 Baseline Mission Initial
Europa Lander. Mission Concept Update 3/29/2017
Europa Lander Mission Concept Update 3/29/2017 2017 California Institute of Technology. Government sponsorship acknowledged. 1 Viable Lander/Carrier Mission Concept Cruise/Jovian Tour Jupiter orbit insertion
Baseline Concepts of the Kayser-Threde Team
Kayser-Threde GmbH Space Industrial Applications e.deorbit Mission Phase A Baseline Concepts of the Kayser-Threde Team 6 May 2014, Conference Centre Leeuwenhorst, The Netherlands Agenda Introduction Target
NanoRacks External Payload Platform
NanoRacks External Payload Platform Introduction NanoRacks has developed a hosted payload service, NanoRacks External Payload Platform (NREP) NREP will be installed on the JEM EF Hosted payloads will utilize
r bulletin 96 november 1998 Figure 1. Overall ATV configuration (ESA/D. Ducros)
r bulletin 96 november 1998 Figure 1. Overall ATV configuration (ESA/D. Ducros) atv The Automated Transfer Vehicle P. Amadieu Head of ATV/CTV Projects Division, ESA Directorate of Manned Spaceflight and
Results of annual simulation
2 x Vitosol 100-FM SVKF Total gross surface area:4,46 m² Azimuth: 0 Incl.: 30 160 Liters/Day 50 C Gas-fired boiler 26 kw Vitocell 100-B Vol : 250 l Results of annual simulation Installed collector power:
ELECTRIC PROPULSION MISSION TO GEO USING SOYUZ/FREGAT LAUNCH VEHICLE M.S. Konstantinov *, G.G. Fedotov *, V.G. Petukhov ±, G.A.
ELECTRIC PROPULSION MISSION TO GEO USING SOYUZ/FREGAT LAUNCH VEHICLE M.S. Konstantinov *, G.G. Fedotov *, V.G. Petukhov ±, G.A. Popov * Moscow Aviation Institute, Moscow, Russia ± Khrunichev State Research
AMBR* Engine for Science Missions
AMBR* Engine for Science Missions NASA In Space Propulsion Technology (ISPT) Program *Advanced Material Bipropellant Rocket (AMBR) April 2010 AMBR Status Information Outline Overview Objectives Benefits
EPIC Workshop 2017 SES Perspective on Electric Propulsion
EPIC Workshop 2017 SES Perspective on Electric Propulsion PRESENTED BY Eric Kruch PRESENTED ON 24 October 2017 SES Proprietary SES Perspective on Electric Propulsion Agenda 1 Electric propulsion at SES
Adrestia. A mission for humanity, designed in Delft. Challenge the future
Adrestia A mission for humanity, designed in Delft 1 Adrestia Vision Statement: To inspire humanity by taking the next step towards setting a footprint on Mars Mission Statement Our goal is to design an
Michael J. Cully Director of Civil and Commercial Space Swales Aerospace Beltsville, Maryland
SSC03-IX-7 I-CONE FOR RAPID RESPONSE AND LOW COST ACCESS TO SPACE 1 Director of Civil and Commercial Space Swales Aerospace Beltsville, Maryland Peter Alea Manager of Thermal Products Swales Aerospace
European Lunar Lander: System Engineering Approach
human spaceflight & operations European Lunar Lander: System Engineering Approach SECESA, 17 Oct. 2012 ESA Lunar Lander Office European Lunar Lander Mission Objectives: Preparing for Future Exploration
LEOSTAR A Small Spacecraft for LEO Communication Missions. (1) G. Barresi - (1) G. Rondinelli - (1) C. Soddu (2) D. 1. Brown
LEOSTAR A Small Spacecraft for LEO Communication Missions (1) G. Barresi - (1) G. Rondinelli - (1) C. Soddu (2) D. 1. Brown (1) TALSPAZO Consorzio ndustriale per e Attivita Spaziali Via V.E. Orlando, 83-00185
The European Lunar Lander Mission
The European Lunar Lander Mission Alain Pradier ASTRA Noordwijk, 12 th April 2011 European Space Agency Objectives Programme Objective PREPARATION FOR FUTURE HUMAN EXPLORATION Lunar Lander Mission Objective
Mars Express Bus: Simplified User Manual
Issue : Draft Rev. : 01 Date : 09/04/01 Page : i Title Mars Express Bus: Simplified User Manual Name and Function Date Signature Prepared by MARS EXPRESS team 04/01 Verified by Approved by Authorized by
Thinking Outside the Cube
CHANGING THE ECONOMICS OF SPACE Thinking Outside the Cube 34 th Space Symposium Colorado Springs Monday 16 th April 2018 Anita Bernie a.bernie@sstl.co.uk Commercial in Confidence. SSTL 2017 SpaceNews Home
Preliminary Design of the Electrical Power Subsystem for the European Student Moon Orbiter Mission
Preliminary Design of the Electrical Power Subsystem for the European Student Moon Orbiter Mission Steve Ulrich Jean-François Veilleux François Landry Corbin Picture courtesy of ESA Presentation Outline
SMARTSat. Shape Memory Alloy Research Technology Satellite. Allison Barnard Alicia Broederdorf. Texas A&M University Space Engineering Institute
SMARTSat Shape Memory Alloy Research Technology Satellite Allison Barnard Alicia Broederdorf Texas A&M University Space Engineering Institute Outline Introduction / Mission Objectives Systems Overview
The GHOST of a Chance for SmallSat s (GH2 Orbital Space Transfer) Vehicle
The GHOST of a Chance for SmallSat s (GH2 Orbital Space Transfer) Vehicle Dr. Gerard (Jake) Szatkowski United launch Alliance Project Mngr. SmallSat Accommodations Bernard Kutter United launch Alliance
The Mars Express Mission A Continuing Challenge. Erhard Rabenau, NOVA Space Associates Ltd Mars Express Senior Mission Planner
The Mars Express Mission A Continuing Challenge Erhard Rabenau, NOVA Space Associates Ltd Mars Express Senior Mission Planner Mars Society, Munich, 13 October, 2012 The Mars Express Mission - a First in
From MARS To MOON. V. Giorgio Director of Italian Programs. Sorrento, October, All rights reserved, 2007, Thales Alenia Space
From MARS To MOON Sorrento, October, 2007 V. Giorgio Director of Italian Programs Page 2 Objectives of this presentation is to provide the Lunar Exploration Community with some information and status of
On the feasibility of a fast track return to Mars
On the feasibility of a fast track return to Mars Mars Lander(s) 2011 Mars Demonstration Landers (MDL) Page 1 Technology Demonstrators SMART 1 SMART 2 LISA PF Solar Electric Propulsion Drag Free Control
LUNAR INDUSTRIAL RESEARCH BASE. Yuzhnoye SDO proprietary
LUNAR INDUSTRIAL RESEARCH BASE DESCRIPTION Lunar Industrial Research Base is one of global, expensive, scientific and labor intensive projects which is to be implemented by the humanity to meet the needs
Seminar 12! The Future of Space Flight! Spacecraft Power & Thermal Control!
Seminar 12! The Future of Space Flight! Spacecraft Power & Thermal Control! Robert Stengel! FRS 112, From the Earth to the Moon! Princeton University, 2015! " NASA s Strategic Direction! Rationales and
The DoD Space Test Program Standard Interface Vehicle (ESPA) Class Program
The DoD Space Test Program Standard Interface Vehicle (ESPA) Class Program Mr. Mike Marlow STP-SIV Program Manager Co-Authors Lt Col Randy Ripley Capt Chris Badgett Ms. Hallie Walden 20 th Annual AIAA/USU
Martin J. L. Turner. Expedition Mars. Published in association with. Chichester, UK
Martin J. L. Turner Expedition Mars Springer Published in association with Praxis Publishing Chichester, UK Contents Preface Acknowledgements List of illustrations, colour plates and tables xi xv xvii
FlexCore Low-Cost Attitude Determination and Control Enabling High-Performance Small Spacecraft
FlexCore Low-Cost Attitude Determination and Control Enabling High-Performance Small Spacecraft Dan Hegel Director, Advanced Development Blue Canyon Technologies hegel@bluecanyontech.com BCT Overview BCT
NE (SE) Beam
Predicted clear day beam and diffuse irradiances (/ W m 2 ) on vertical and horizontal surfaces on specified days in northern (N) and southern (S) hemispheres (see notes at foot of table): LATITUDE 60
Sunrise: 05:48 N (S) Beam
Predicted clear day beam and diffuse irradiances (/ W m 2 ) on vertical and horizontal surfaces on specified days in northern (N) and southern (S) hemispheres (see notes at foot of table): LATITUDE 40
ENERGIA 1. IDENTIFICATION. 1.1 Name. 1.2 Classification Family : K Series : K-1/SL-17 Version : 4 strap-ons
1. IDENTIFICATION 1.1 Name 1.2 Classification Family : K Series : K-1/SL-17 Version : 4 strap-ons Category : SPACE LAUNCH VEHICLE Class : Heavy Lift Vehicles (HLV) Type : Expendable Launch Vehicle (ELV)
Industrial-and-Research Lunar Base
Industrial-and-Research Lunar Base STRATEGY OF LUNAR BASE CREATION Phase 1 Preparatory: creation of international cooperation, investigation of the Moon by unmanned spacecraft, creation of space transport
Europa Lander Mission Overview and Update
Europa Lander Mission Overview and Update Steve Sell 15 th International Planetary Probe Workshop, Boulder CO June 2018 2018 California Institute of Technology. Government sponsorship acknowledged. Predecisional
EPIC Gap analysis and results
EPIC Gap analysis and results PSA Consortium Workshop Stockholm 11/02/2015 EPIC Gap Analysis and results/ Content Content: Scope Process Missions Analysis (i.e GEO (OR + SK)) Gaps results Gap analysis
Yield Reduction Due to Shading:
x Fronius International NA-E35L5 35 W FRONIUS IG Plus 20 V-3 2 0,0kW x Fronius International NA-E35L5 35 W FRONIUS IG Plus 20 V-3 4 0,0kW 84 x SHARP Corporation x Fronius International NA-E35L5 35 W FRONIUS
Thinking Outside the Cube
Thinking Outside the Cube Anita Bernie 1, Alex da Silva Curiel 1, Nikki Antoniou 1, Luis Gomes 1, Rob Goddard 1, Jonathan Friend 1, Sir Martin Sweeting 2 1) Surrey Satellite Technology Ltd., Tycho House,
OMOTENASHI. (Outstanding MOon exploration TEchnologies demonstrated by NAno Semi-Hard Impactor)
SLS EM-1 secondary payload OMOTENASHI (Outstanding MOon exploration TEchnologies demonstrated by NAno Semi-Hard Impactor) The smallest moon lander launched by the most powerful rocket in the world * Omotenashi
Formation Flying Experiments on the Orion-Emerald Mission. Introduction
Formation Flying Experiments on the Orion-Emerald Mission Philip Ferguson Jonathan P. How Space Systems Lab Massachusetts Institute of Technology Present updated Orion mission operations Goals & timelines
Economics of Integrating Renewables DAN HARMS MANAGER OF RATE, TECHNOLOGY & ENERGY POLICY SEPTEMBER 2017
Economics of Integrating Renewables DAN HARMS MANAGER OF RATE, TECHNOLOGY & ENERGY POLICY SEPTEMBER 2017 Presentation Outline Understanding LPEA s expenses and what drives them Economics of net metering
NASA Glenn Research Center Intelligent Power System Control Development for Deep Space Exploration
National Aeronautics and Space Administration NASA Glenn Research Center Intelligent Power System Control Development for Deep Space Exploration Anne M. McNelis NASA Glenn Research Center Presentation
Yield Reduction Due to Shading:
x9 31 x SunPower 1 x Power-One SPR-E0-37 37 W TRIO-8.5-TL-OUTD 10 ; 1x13 1x13 1 x Power-One 10 ; -30 7.5kW 9 x SunPower 1 x Power-One SPR-E0-37 37 W 10 ; 59 7.5kW 7 x SunPower 1 x Power-One SPR-E0-37 37
FEDERAL SPACE AGENCY OF RUSSIAN FEDERATION LAVOCHKIN ASSOCIATION PROGRAM OF THE MOON EXPLORATION BY AUTOMATIC SPACE COMPLEXES
FEDERAL SPACE AGENCY OF RUSSIAN FEDERATION LAVOCHKIN ASSOCIATION PROGRAM OF THE MOON EXPLORATION BY AUTOMATIC SPACE COMPLEXES 2007 CONCEPT 1. The program foresees development of automatic space complexes
OLEV AN ON-ORBIT SERVICING PROGRAM FOR COMMERCIAL SPACECRAFTS IN GEO
Von der Erde ins All. Und zurück. Intelligente Lösungen für Industrie und Wissenschaft. From Earth to Space. And back. Intelligent solutions for industry and science. E a r t h S p a c e & F u t u r e
Pathfinder Technology Demonstrator
Demonstrating Advanced Technologies for Advanced Missions CubeSat Developer s Workshop April 26 th, 2017 NASA Space Technology Mission Directorate NASA Small Spacecraft Technology Program NASA Ames Research
SOYUZ-IKAR-FREGAT 1. IDENTIFICATION. 1.1 Name. 1.2 Classification Family : SOYUZ Series : SOYUZ Version : SOYUZ-IKAR SOYUZ-FREGAT
1. IDENTIFICATION 1.1 Name 1.2 Classification Family : SOYUZ Series : SOYUZ Version : SOYUZ-IKAR SOYUZ-FREGAT Category : SPACE LAUNCH VEHICLE Class : Medium Launch Vehicle (MLV) Type : Expendable Launch
HYDROS Development of a CubeSat Water Electrolysis Propulsion System
HYDROS Development of a CubeSat Water Electrolysis Propulsion System Vince Ethier, Lenny Paritsky, Todd Moser, Jeffrey Slostad, Robert Hoyt Tethers Unlimited, Inc 11711 N. Creek Pkwy S., Suite D113, Bothell,
The Common Spacecraft Bus and Lunar Commercialization
The Common Spacecraft Bus and Lunar Commercialization Alex MacDonald NASA Ames Research Center alex.macdonald@balliol.ox.ac.uk Will Marshall NASA Ames Research Center william.s.marshall@nasa.gov Summary
Instruction Manual: Space Launch System Payload Transfer Module (PTM)
Instruction Manual: Space Launch System Payload Transfer Module (PTM) Designer s comments: This model has been designed without the benefit of engineering blueprints. Only publically available conceptual
Cibola Flight Experiment
Cibola Flight Experiment Diane Roussel-Dupré & Micahel Caffrey Los Alamos National Laboratory John Buckley & Phil Davies Surrey Satellite Technology, LTD 7 Cities of Cibola: sought after by Spanish explorers
E3000 High Power SADM Development
E3000 High Power SADM Development Steve G Bamford / Paul McMahon EADS Astrium UK Ltd, Gunnels Wood Road, Stevenage, Herts., England, SG1 2AS, +44(0)1438 773339 steve.bamford@astrium-space.com / paul.mcmahon@astrium-space.com
ASTRIUM. Lunar Lander Concept for LIFE. Hansjürgen Günther TOB 11. Bremen, 23/
Lunar Lander Concept for LIFE Hansjürgen Günther TOB 11 Bremen, 23/24.11.2006 This document is the property of EADS SPACE. It shall not be communicated to third parties without prior written agreement.its
W (W) Beam
Predicted clear day beam and diffuse irradiances (/ W m 2 ) on vertical and horizontal surfaces on specified days in northern (N) and southern (S) hemispheres (see notes at foot of table): LATITUDE 0 N/S
MARS-OZ: A Design for a Simulated Mars Base in the Arkaroola Region
MARS-OZ: A Design for a Simulated Mars Base in the Arkaroola Region David Willson (david.willson@au.tenovagroup.com) and Jonathan D. A. Clarke (jon.clarke@bigpond.com), Mars Society Australia The centrepiece
VACCO ChEMS Micro Propulsion Systems Advances and Experience in CubeSat Propulsion System Technologies
VACCO ChEMS Micro Propulsion Systems Advances and Experience in CubeSat Propulsion System Technologies May 1 st, 2018 VACCO Proprietary Data Shall Not Be Disclosed Without Written Permission of VACCO VACCO
Cygnus Payload Accommodations: Supporting ISS Utilization
The Space Congress Proceedings 2018 (45th) The Next Great Steps Feb 27th, 1:30 PM Cygnus Payload Accommodations: Supporting ISS Utilization Frank DeMauro Vice President and General Manager, Advanced Programs
PDR Energy Baseline Alternative. Proposal for Discussion October 27, 2015
PDR Energy Baseline Alternative Proposal for Discussion October 27, 2015 Update Since Last Meeting Since the October 12 th Working Group Meeting Stem, Solar City, AMS and CESA have had over a half-dozen
Li-ion battery and super-capacitor Hybrid energy system for low temperature SmallSat applications
Li-ion battery and super-capacitor Hybrid energy system for low temperature SmallSat applications K.B. Chin*, M.C. Smart, E.J. Brandon, G.S. Bolotin, N.K. Palmer Jet Propulsion Laboratory, California Institute
Proposed Europa Lander Descent Stage Overview
Proposed Europa Lander Descent Stage Overview Tejas Kulkarni, Devin Kipp, Steve Sell, Aline Zimmer, David Skulsky, Miguel San Martin Jet Propulsion Laboratory, California Institute of Technology, Pasadena,
ELECTRON LOSSES AND FIELDS INVESTIGATION U.S. AIR FORCE. Ground Support Equipment Mission PDR. Michael Anderson
ELECTRON LOSSES AND FIELDS INVESTIGATION Ground Support Equipment Mission PDR Michael Anderson Los Angeles, California February 12, 2015 1 GSE AGENDA Major Campaigns to Support Notable Requirements GSE-Spacecraft
Example printout. Building project. SDC Example. Dyfi Eco Park SY20 8AX Machynlleth UK. Mr C. Laughton Phone:
Building project SDC Example Dyfi Eco Park SY20 8AX Machynlleth UK Contact person: Mr C. Laughton Phone: 01654 700324 E-Mail: software@solardesign.co.uk Results of annual simulation Installed collector
Philae : A made to measure battery. Richard Hague ESTEC AIM Workshop 22/23 Feb 2016
Philae : A made to measure battery Richard Hague ESTEC AIM Workshop 22/23 Feb 2016 Agenda 1 SAFT s Space Heritage 2 Philae 3 ExoMars Rover AIM 2 presnetation 1 SAFT S SPACE HERITAGE 3 Space Satellites
NEXT Exploration Science and Technology Mission. Relevance for Lunar Exploration
NEXT Exploration Science and Technology Mission Relevance for Lunar Exploration Alain Pradier & the NEXT mission team ILEWG Meeting, 23 rd September 2007, Sorrento AURORA PROGRAMME Ministerial Council
LOW SHOCK RELEASE UNIT EASY RESETTABLE AND 100 % REUSABLE. Jens Müller 1, Christoph Zauner 2
LOW SHOCK RELEASE UNIT EAS RESETTABLE AND 100 % REUSABLE Jens Müller 1, Christoph Zauner 2 1 Astrium GmbH, 2 Chair of Lightweight Structures - Technical University of Munich Astrium GmbH, 81663 München
Rover development status
EXOMARS PROJECT 2018 Mission Rover development status ASTRA Workshop 15-17 May 2013 P. Baglioni & the EXM Rover Team Progress on the 2018 Mission Following EXM Program approvals from the Council and IPC
ULA Briefing to National Research Council. In-Space Propulsion Roadmap. March 22, Bernard Kutter. Manager Advanced Programs. File no.
ULA Briefing to National Research Council In-Space Propulsion Roadmap March 22, 2011 Bernard Kutter Manager Advanced Programs File no. Copyright 2011 United Launch Alliance, LLC. All Rights Reserved. Key
Palamede, more than a microsatellite. Workshop on University Micro Satellites in Italy Rome, July 27, 2005
Palamede, more than a microsatellite The Palamede Team (represented by Franco Bernelli and Roberto Armellin) Workshop on University Micro Satellites in Italy Rome, July 27, 2005 Outline Mission and educational
Development of Low Shock Release Device
Development of Low Shock Release Device 2007.10.30 Takao Matsui, Jun Nakagawa(MELCO) Hiroshi Miyaba(JAXA) Needs Development Point The high shock of conventional pyrotechnic Lock Release Device constrains
PM Individual Weapons Ms. Barbara Muldowney
Our Strength and Purpose PM Individual Weapons Ms. Barbara Muldowney 26 April 2016 PM Individual Weapons Portfolio Operations & Support Production & Deployment Development Future (images notional) M1911
Van Ness Transit Corridor Improvement Project. Engineering, Maintenance and Safety Committee March 25, 2015
Van Ness Transit Corridor Improvement Project Engineering, Maintenance and Safety Committee March 25, 2015 Project Need 16,000 daily passenger boardings within the project corridor Average bus speed 8
Energy Produced by PV Array (AC):
4x17 2x16 400 x PHOTON SOLAR 4 x KACO new energy PH-250P-60 (HDS) INT 250 W Powador 30,0 TL3 15 ; 0 25,0kW Location: Climate Data Record: PV Output: Gross/Active PV Surface Area: Antalya Antalya (1961-1990)
Facilitated Discussion on the Future of the Power Grid
Facilitated Discussion on the Future of the Power Grid EPRI Seminar: Integrated Grid Concept and Technology Development Tokyo Japan, August 20, 2015 Matt Wakefield, Director Information, Communication
First results and next steps in Kazakhstan Earth Observation missions in cooperation with SSTL
First results and next steps in Kazakhstan Earth Observation missions in cooperation with SSTL M.Moldabekov (1), M.Nurguzhin (2), V.Ten (3), S.Murushkin (3), H.Lambert (3), A.da Silva Curiel (4), D.King
DEVELOPMENT OF AN EUROPEAN EDDY CURRENT DAMPER (ECD-100)
DEVELOPMENT OF AN EUROPEAN EDDY CURRENT DAMPER (ECD-100) 1 ABSTRACT Authors M. Hofer & M. Humphries Oerlikon Space AG, Schaffhauserstr. 580 CH-8052 Zürich-Seebach Switzerland Oerlikon Space have been designing
Canisterized Satellite Dispenser (CSD) As A Standard For Integrating and Dispensing Hosted Payloads on Large Spacecraft and Launch Vehicles
Canisterized Satellite Dispenser (CSD) As A Standard For Integrating and Dispensing Hosted Payloads on Large Spacecraft and Launch Vehicles Ryan Hevner, Ryan Williams and (Presented by) Walter Holemans
Virginia Tech Research Center Arlington, Virginia, USA. PPT slides will be available at
SMART BUILDINGS & A SMART CITY CONNECTED COMMUNITY Guest Professor Inaugural Lecture at Tsinghua University Professor Saifur Rahman Director, Virginia Tech Advanced Research Inst., USA President-elect,
Power Team Mission Day Instructions
Overview Power Team Mission Day Instructions Every 90 minutes the space station orbits the earth, passing into and out of the sun s direct light. The solar arrays and batteries work together to provide
Validation System (EVS)
Presentation of the Astrium EGSE Validation System (EVS) Compiled Clive Catley Introduction document is the property of Astrium. It shall not be communicated to third Its content shall not be disclosed.
Lunar Surface Access from Earth-Moon L1/L2 A novel lander design and study of alternative solutions
Lunar Surface Access from Earth-Moon L1/L2 A novel lander design and study of alternative solutions 28 November 2012 Washington, DC Revision B Mark Schaffer Senior Aerospace Engineer, Advanced Concepts
Graph #1. Micro-Generation Generating Units in Alberta 20
2, Graph #1. Micro-Generation Generating Units in Alberta 2 Cumulative # of Generating Units 1,9 1,8 1,7 1,6 1,5 1,4 1,3 1,2 1,1 1, 9 8 7 6 5 4 3 2 Number of MGG Units as of 216 Mar 31 Number of Solar
Cal Poly CubeSat Workshop 2014
Cal Poly CubeSat Workshop 2014 866.204.1707 www.spaceflightservices.com info@spaceflightservices.com hhh @spaceflightinc 1 Spaceflight Business Model Our Model Arrange launch opportunities for secondary
Modeling and Comparison of Dynamics of AC and DC Coupled Remote Hybrid Power Systems
Modeling and Comparison of Dynamics of AC and DC Coupled Remote Hybrid Power Systems Presenter: Tanjila Haque Supervisor : Dr. Tariq Iqbal Faculty of Engineering and Applied Science Memorial University
Company name: Created by: Phone:
Qty. Description 1 SQF 2.5-2 Note! Product picture may differ from actual product Product No.: 95027330 The 3" SQFlex pump with helical rotor is for high heads and low flow rates. The SQFlex system is
Space Transportation Atlas V / Auxiliary Payload Overview
Space Transportation Atlas V / Auxiliary Payload Overview Lockheed Martin Space Systems Company Jim England (303) 977-0861 Program Manager, Atlas Government Programs Business Development and Advanced Programs
ANCR CRU Statistics February 2007 to December 2007
ANCR CRU Statistics February 2007 to December 2007 o Jan/07 Feb/07* Mar/07 Apr/07 May/07 Jun/07 Jul/07 Aug/07 Sep/07 Oct/07 Nov/07 Dec/07 Total notes data from Perimeter phone system unavailable prior
GLAST LAT Project Subsystem Managers Meeting, May 13, Introduction. Lowell A. Klaisner Stanford Linear Accelerator Center Project Manager
Gamma-ray Large Area Space Telescope GLAST Large Area Telescope: Introduction Lowell A. Klaisner Stanford Linear Accelerator Center Project Manager Klaisner@slac.stanford.edu 650-926-2726 Rev B 1 Two towers
In-Space Demonstration of HighPerformance Green Propulsion (HPGP) and its Impact on Small Satellites
In-Space Demonstration of HighPerformance Green Propulsion (HPGP) and its Impact on Small Satellites Ben Crowe and Kjell Anflo 25 th Annual AIAA/Utah State University Conference on Small Satellites 10th
USA FALCON 1. Fax: (310) Telephone: (310) Fax: (310) Telephone: (310) Fax: (310)
1. IDENTIFICATION 1.1 Name FALCON 1 1.2 Classification Family : FALCON Series : FALCON 1 Version : FALCON 1 Category : SPACE LAUNCH VEHICLE Class : Small Launch Vehicle (SLV) Type : Expendable Launch Vehicle
Systems Engineering. Chris Hall AOE 4065 Fall 2005
Systems Engineering Chris Hall AOE 4065 Fall 2005 Activity Matrix Representing the Systems Engineering Process Logic Steps Time Steps 1 Program 2 Project 3 System Development 4 Production 1 2 3 4 5 6 7
ANTENNA SCAN MECHANISM FOR AN INTER SATELLITE LINK OF A CONSTELLATION PROGRAM
ANTENNA SCAN MECHANISM FOR AN INTER SATELLITE LINK OF A CONSTELLATION PROGRAM Ingo Köker, AIRBUS DS GmbH, ingo.koeker@airbus.com Frank Härtel, AIRBUS DS GmbH, frank.haertel@airbus.com Abstract For a constellation
University of Michigan Eco-Driving Index (EDI) Latest data: October 2017
University of Michigan Eco-Driving Index () http://www.ecodrivingindex.org Latest data: October 2017 Developed and issued monthly by Michael Sivak and Brandon Schoettle Sustainable Worldwide Transportation
ARCHIVED REPORT. For data and forecasts on current programs please visit or call
Space Systems Forecast - Launch Vehicles & Manned Platforms ARCHIVED REPORT For data and forecasts on current programs please visit www.forecastinternational.com or call +1 203.426.0800 Outlook ATV-5,