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s HMM Assessment Study Report: CDF-20(A) February 2004 page 202 of 422 set of capabilities for the command & control, the data handling and the human interfaces. Given what is already available for guidance and control for military systems (like combat helicopters) or commercial airliners, it is clear that more and more controls shall be managed in complete onboard automation. In everyday life, human beings prone to accept an involvement of automated machine intelligence in many potentially life-endangering tasks. Robotic surgery and automated driving are examples. A 3-5 year mission of a spacecraft far more complex than the actual ISS with no practical escape solution for the crew requires the acceptance of a system where the on-board computer (even if not identifiable anymore with a single box) has full control of the spacecraft health management and is the real mission control entity. The on-board control system will also exploit capabilities like the on-board calculation of trajectories and manoeuvres, contingency management, FDIR, and all those autonomies requested by the long signal turnaround. This approach will also save a great amount of workload for the crew (and for the ground control), during the mission and in the (presumably long) training phase. Crewmembers shall be interfaced with the avionics by means of systems like PDAs or wrist computers and even the concept of a centralized command deck shall disappear. Human machine interfaces shall be weightless, the availability of powerful processors allows speech recognition and the use of touch screens is becoming common even in airliner cockpits. The use of Personal Satellite Robot Assistants was already spotted (1998) as very useful on shuttle and ISS but its development by NASA-AMES is now suspended [RD35]. 3.3.6.1.8 Reliable path-independent long distance multi-hop data transfer protocol A key aspect of Martian exploration will be the ability of future missions to interoperate. Figure 3-56: Interoperability scenario for a Mars mission.
s HMM Assessment Study Report: CDF-20(A) February 2004 page 203 of 422 These protocols establish a framework for interoperability by providing standard communication, navigation, and timing services. In addition, these services include strategies to recover gracefully from communication interruptions and interference while ensuring backward compatibility with previous missions from previous phases of exploration. CFDP (CCSDS File Delivery Protocol) is a new international standard, built on the familiar Consultative Committee for Space Data Systems (CCSDS [RD40]) space data communication protocols, developed to meet a comprehensive set of deep-space file transfer requirements as stated by a number of space agencies including NASA, <strong>ESA</strong>, NASDA, CNES, and BNSC/DERA. In addition, CFDP will serve as a prototype for the future Interplanetary Internet (IPN [RD42]) as envisioned by the IPN Study team: it encompasses a subset of the anticipated functionality of the IPN, and it implements several key IPN design concepts including store-and-forward operation with deferred transmission and concurrent transactions. CFDP [RD28] allows an automatic, reliable file transfer between spacecraft and ground (in both directions) designed to support the operation of spacecraft by means of file transfer and remote file system management. Its embedded transport layer provides applications the capability of transferring their data products end-to-end across the entire space link with two optional transmission modes: reliable or unreliable. In reliable mode the data loss is automatically detected and retransmission of the lost data is performed automatically. In unreliable mode, data are transferred in a “best effort” way over an unidirectional link. Furthermore, CFDP provides four different selective retransmission strategies for negative acknowledgement. Its capabilities include: • Reliable/Unreliable copying a file from the filestore of one entity (protocol engine, located in a spacecraft or ground control centre) to that of another entity • Reliable/Unreliable transmission of arbitrary small messages, defined by the user, in the metadata accompanying a file • Reliable/Unreliable transmission of file system management commands to be executed automatically at a remote entity – typically at a spacecraft – upon complete reception of a file • Store-and-forward mechanism allowing an end-to-end transfers that can span multiple CFDP waypoint nodes in case source and destination entities are not in direct view. CFDP is designed to offer these capabilities even across interplanetary distances, where data errors, data loss and out-of-sequence delivery may occur; minimising the return path overhead of the protocol for optimised performances. As such, it must function despite extremely long data propagation delays (measured in minutes or hours, rather than in milliseconds as in terrestrial networks) and frequent, lengthy interruptions in connectivity. Unlike TCP/IP, the transport layer embedded in CFDP requires no handshaking and is datagram-and transaction based to deal with space link characteristics (e.g. long RTLT and non-persistent links). Additionally, CFDP is adaptable to fit the proximity link as well. Metadata associated with each transaction describes the data transfer including data processing once the file arrives.
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s HMM Assessment Study Report: CDF-
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s STUDY TEAM HMM Assessment Study R
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s T A B L E O F C O N T E N T S HMM
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s L I S T O F F I G U R E S HMM Ass
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s L I S T O F T A B L E S HMM Asses
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s 1 INTRODUCTION 1.1 Background HMM
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s 2 GENERAL ARCHITECTURE 2.1 Study
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s 2.2.4.2 Accelerations HMM Assessm
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s 2.2.4.4 Temperature and relative
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s Figure 2-10: Trajectory Overview
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s 2.4.3.5 TEI and planetary protect
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s Mars Excursion Vehicle Transfer H
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s 2.7.5.1 Mission elements dry mass
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s 2.7.5.8 MEV release The MEV is re
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s Total mission time (days) 1200 10
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s stack 9 Propellant mass of the ne
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s The core supporting structure has
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s 2.7.7.1.3 Mars excursion module S
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s 2.7.7.1.4 Earth return capsule HM
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s Mission Phase Description Event s
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s Mission Phase Description Event s
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s 2.7.10 Mission performance Table
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s Days on Martian surface 450 400 3
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s Maximum manoeuvre duration 6 mont
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s % of loss from baseline 20 18 16
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s 2.7.15 Sensitivity analysis HMM A
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s 2.7.15.4 Influence of the mass of
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s Parameters used: • No Shuttle
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s 2.8.3.3 Launch 3- Front node Figu
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s 2.10.1.4 Communications HMM Asses
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s 2.10.2.2.2 LEO assembly HMM Asses
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s Basic RF link Four 70-m Ka-band s
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s 3 TRANSFER VEHICLE 3.1 Systems…
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s Operational Requirements It shall
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s Trans Mars Injection Module Mars
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s Figure 3-2: Parallel configuratio
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s Figure 3-6: Global dimensions com
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s Front Node 3.2.3.1.3 EVA systems
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s Trans Mars Injection (three stage
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s Figure 3-16: Recommendations for
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s Factors to be considered Impacts
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s Figure 3-24: Baseline design back
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Page 249 and 250: s 4 MARS EXCURSION VEHICLE 4.1 Syst
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s Figure 4-2: Option 2: Vertical co
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s 4.3 Surface habitation module Fig
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s Figure 4-11: Section through the
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s 4.3.1.5 Baseline design HMM Asses
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s 4.3.1.5.3 Top level Figure 4-20:
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s 4.3.2.3 Baseline design HMM Asses
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s Schedule in hours for the most ac
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s 4.3.3.6 Waste production HMM Asse
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s Figure 4-26: Total pressure vs. O
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s ECLS system mass: Figure 4-27: Ma
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s Figure 4-28: Mars albedo (L), ars
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s sun flux (W/m2) 450 400 350 300 2
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s Insulation structure (external) F
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s cryocooler heat lift [W] cryocool
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s • a duty cycle value (duration
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s Figure 4-48: MAV Power Inputs HMM
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s 4.3.5.4.2 Power storage HMM Asses
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s Figure 4-52: Regenerative Fuel Ce
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s Figure 4-54: Solar irradiance on
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s 450.00 400.00 350.00 300.00 250.0
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s 4.3.6.1 Budgets HMM Assessment St
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s Surface Surface Container MAV Con
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s 4.3.9.3 Baseline design 4.3.9.3.1
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s Bio-Lock Masses: Core Samples No.
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s Figure 4-72: Entry Velocity (L) a
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s 2 3.9 233 923.1 347 923 12.3 352
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s Figure 4-85: Communications MEV/M
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s 4.4.5.3.2 GNC equipment HMM Asses
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s 4.4.5.4 Control laws generation H
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s Finally, the Figure 4-97 shown th
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s velocity (m/sec) altitude (km) 50
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s 4.5 Mars Ascent Vehicle 4.5.1 Tra
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s Term Value Unit Radius of equator
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s 4.5.2.1 Requirements and design d
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s Inclination (deg) 47.5 47 46.5 46
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s 4.5.3 Structures HMM Assessment S
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s 4.5.5 Thermal HMM Assessment Stud
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s 4.5.5.3 Baseline thermal design H
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s Crew Ingress/Egress Hatch: HMM As
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s Element 3: Mars Ascent Vehicle HM
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s 4.5.7.5 Budgets Characteristic Va
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s PER DAY PER MISSION DRINKING WATE
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s 5 OVERALL CONCLUSIONS HMM Assessm
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s 6 APPENDIX A - MARTIAN SURFACE NU
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s Figure 6-1: Example of buried rea
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s 7 APPENDIX B - REFERENCES [RD1] C
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s [RD26] IES2, Phase A0: Final Repo
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s [RD85] Mars Transportation Enviro
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s 8 APPENDIX C - ACRONYMS AAA Avion
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s MLI Multi-Layer Insulation MMH Mo
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ESA Document - Emits - ESA

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