Page 1 Presentation title – file name – date From ATV to ATV Evolution February 2004 Hans-Jörg Heidmann Transportation for In-Orbit Infrastructure and beyond

Page 2 Presentation title – file name – date ISS ATTITUDE CONTROL Major features of ATV mission GYRODYNES/CMG DESATURATION RETRIEVAL OF WASTE AND DESTRUCTION DURING REENTRY ISS REFUELING DRY CARGO WATER AND GAS ISS ORBIT CONTROL DEBRIS AVOIDANCE BY ISS

Page 3 Presentation title – file name – date General layout and characteristics Mass = 20.5 tons at launch dry mass : 11 tons gross cargo : 9.5 tons up to 8 tons of propellant at launch Sizes 10.3 m length 4.5 m diameter 22.3 m with deployed solar wings (4.8 kW) 22 m 3 pressurized module (16 m 3 for pressurized cargo)

Page 4 Presentation title – file name – date ATV subsystems Power supply : - 4 independent distribution chains with rotative solar panels (Si) and rechargeable batteries (NiCd) Data Management System : - 3 Failure Tolerant Computers running the main Flight Applicative Software Monitoring and Safety Chain : - 2 independent and autonomous chains for Rendezvous monitoring and Collision Avoidance Maneuver with specific means (data processor, category A software, primary power sources, thrusters…) Propulsion Subsystem : - 28 ACS thruster (240N) - 4 OCS thrusters (490 N) - 8 propellant tanks (8 tons of MON + MMH) Semi passive TCS : - 40 Variable Conductance Heat Pipes

Page 5 Presentation title – file name – date ATV subsystems (cont’d) External Rendezvous monitoring by the ISS : - Visual Video Target - RF Kurs navigation transponder - Visual Ranging Cues Navigation and Monitoring of RV : - Relative GPS - Laser sensors (2 Telegoniometer + 2 Videometers) General navigation equipment : - Star Tracker, Accelerometer, Gyrometer, Sun Sensor for survival Communication subsystem : - 2 chains compatible TDRSS/Artemis for ATV-CC - 2 chains (S-band) for proximity link with ISS

Page 6 Presentation title – file name – date ATV subsystems (cont’d) Pressurized Module : - 22 m 3 pressurized module - up to 8 Standard Racks - Environment and Control Life Support (fan, smoke detector, light) Unpressurized Cargo Tanks : - 3 water tanks - 3 Gas tanks - 2 refueling kits Russian Docking System : - Active Docking Unit featuring mechanical, fluidic, electrical and data interface Russian Equipment Control Set : - 2 redundant equipment chains to control interfaces with ISS

Page 7 Presentation title – file name – date ESA ATV Flight Segment Prime Contractorship. System engineering. Verification of ATV FS. Development of Flight Software. Development and Procurement of Propulsion and Reboost subsystem and of Avionics Chains. ATV assembly, integration and testing. Support to ESA for external interfaces. Cargo Carrier development and integration. Russian equipment set procurement Thermal control studies. Development of Spacecraft structure subsystem. Development of Solar Generation subsystem. EADS-ST (F+D) ATV INDUSTRIAL TEAM Development of Videometer and Star Tracker. Development of Telegoniometer ALENIA SPAZIO (I) CONTRAVES SPACE (CH) DUTCH SPACE (NL) EADS SODERN (F) DJO (D)

Page 8 Presentation title – file name – date 1 st ATV flight model at overall integration Equipped Avionics Bay Integrated Cargo Carrier Equipped Propulsion Bay Launcher adapter with separation system ATV sub-assemblies delivered at EADS-ST Bremen - Nov st ATV launch by Ariane 5 (Jules-Verne) scheduled May 2005

Page 9 Presentation title – file name – date Servicing of the US-Segment  The NASA Shuttle fleet will be retired from up to 2010, which could lead to a logistical gap for the ISS at least until 2014  This logistical gap could be overcome by ATV derived unmanned transportation vehicles such as: - ATV Download System - Cargo Capsule System - Unpressurized Logistic Carrier  For the logistic supply of the US-Segment by ATV could be developed a special docking mechanism called IBDM (International Docking and Berthing Mechanism).

Page 10 Presentation title – file name – date 2. Scenario Description (6) PTV Scenario Lift-off Separation of Ariane 5 EAPs Fairing jettisoning Separation of the EPC Ignition of the ESP Separation of the ESP Separation completed PTV attitude stabilized Solar panels deployed Antennas deployed Check-up by the PTV control centre Transfer to the phasing orbit Maneuver 1 Drift period 1 Maneuver 2 Phasing Drift period 2 Mid course correction Drift period 3 Transfer to the ISS vicinity – Interface with the RV scenario

Page 11 Presentation title – file name – date -V-bar Approach Scenario 2. Scenario Description (7) PTV Scenario

Page 12 Presentation title – file name – date 2. Scenario Description (8) ISS Attached and Return Phase  Connections  Repressurization of inter volume and tightness control  Hatch opening  PTV power down to stand by mode  Payload operations  PTV power up out of stand by mode  Check out  Hatch closing  Depressurization of inter volume  Unlatch  Separation  Distancing  Orbit correction  Drift  Reentry vehicle power-up (avionics / GNC)  Wetting of propulsion system of the reentry vehicle (pyro valve)  Pyros armed  Checkout prior to reentry  Transfer of the state vector and reentry information to GNC of reentry vehicle  Deorbit impulse  Separation of the ATV Propulsion part  Separation of the docking adapter Checkout prior to reentry Transfer of the state vector and reentry information to GNC of reentry vehicle Deorbit impulse Separation of the ATV Propulsion part Separation of the docking adapter Reentry Hypersonic flare Descent Back cover jettison Parachute sequence deployment (for instance, extractor, drogue chute, main chute) Heat shield jettison Landing Landing system deployment (airbag) Touch down Vehicle passivation and safing Beacon and post-landing systems deployment Arrival of ground crew Manual vehicle safing Hatch opening and express payload removal Hoisting on transport vehicle Transport

Page 13 Presentation title – file name – date 2. Scenario Description (9) CTV scenario Mission Scenario similar To PTV Safeguard Scenario during Launch phase Two-Failure Tolerance Required ATV S/C Modification Analysis led to the Result that it would be the design of a new Vehicle

Page 14 Presentation title – file name – date ULC Mission Scenario Launch by Ariane 5 ECA After nominal separation from AR5 upper stage jettisoning of ULC cover/cargo door ULC operates in a safe orbit below ISS orbit ULC conducts ISS approach similar to the ATV after ISS okay Final Approach differs from ATV due to different docking locations ULC approach is similar with PTV ULC will be docked at Node 2 Port Exchange of complete platform pallets or of single ORUs by SSRMS and/or Special Purpose Dexterous System Pallets attachment places are at the truss (starboard, port) via PAS, UCCAS or ULCAS De-docking Leaving approach ellipsoid Braking manoeuvres for initiating of de-orbiting 2. Scenario Description (10)

Page 15 Presentation title – file name – date Capsule adaptor module upper I/F close to capsule intermediate diameter,  CoG of capsule close to I/F plane  CoG of complete vehicle below I/F plane  I/F on a 20° cone structure  No separation interference  I/F as far as possible from nose (Reentry thermal aspect) Front docking module Capsule adapter module 4. PTV System Architect. & ATV S/C Modifications (2) Same configuration for CTV but with Additional redundancies

Page 16 Presentation title – file name – date 4. PTV System Architect. & ATV S/C Modifications (3)

Page 17 Presentation title – file name – date 4. CTV System Architect. & ATV S/C Modifications (1) Global architecture choice (1)  Capsule adaptor module slightly modified compared to PTV  Same Front Docking module  Emergency Escape module added  Modified Ariane5 fairing added Vehicle launch with Ariane5 ESC-B (23.0 tons capacity) US-port (V-bar as baseline, -R-bar as back-up treated by delta compared to V-bar) IBDM device Same reentry capsule as PTV configuration Autonomous reentry capsule (no power, thermal regulation, … deliveries) No refuel, no reboost No emergency detachment requirements 1 month docking phase

Page 18 Presentation title – file name – date  Blunt Biconic shape launched “nose-down”, 4.4 m ext. diameter, 5 crew member  PC internal volume of 25.8 m³  PC equipment volume 9.1 m³ (preliminary figure)  Considering 2 m³ per crew member of free volume, 6.7 m³ can be occupied by payload.  Considering:  20% volume margin to account for secondary structures and packaging factors  payload density of about 300 Kg per cubic meter the theoretical P/L occupying all the residual volume of about 6.7 m³ is 1600 Kg  Considering a Capsule mass of 13.1 tons:  The mass w/o P/L is tons  Potential P/L Mass is 2.78 tons  Also assuming a tilting of 30 deg for seats in landing configuration the biconic shape can easily accommodate a crew of 5 CTV Crew & P/L Accommodation Results (Crew of 5) 4. CTV System Architect. & ATV S/C Modifications (5)

Page 19 Presentation title – file name – date 6. ULC System Architect. & ATV S/C Modifications (1) ATV-ULC Layout and Configuration  Unpressurized cargo bay  Doors jettisoned before circularization  Cargo on 2 Express pallets (Boeing) or ICC pallets (EADS-ST)  Front cone with stan- dard RV equipment and Common Berthing Mech- anism (CBM)  SSRMS grapple on aft bay wall