From%20ATV%20to%20ATV%20Evolution

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From ATV to ATV Evolution

• February 2004
• Hans-Jörg Heidmann

Transportation for In-Orbit Infrastructure and
beyond
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Major features of ATV mission
RETRIEVAL OF WASTE AND DESTRUCTION DURING REENTRY
DRY CARGO
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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 m3 pressurized module (16 m3 for pressurized
  cargo)

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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

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ATV subsystems (contd)

• 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

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ATV subsystems (contd)

• Pressurized Module - 22 m3 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

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ESA
ATV INDUSTRIAL TEAM
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.
Development of Videometer and Star Tracker.
Development of Telegoniometer
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1st ATV flight model at overall integration
EquippedPropulsion Bay
IntegratedCargo Carrier
EquippedAvionics Bay
Launcher adapterwith separation system
1st ATV launch by Ariane 5 (Jules-Verne)schedule
d May 2005
ATV sub-assembliesdelivered at EADS-ST Bremen -
Nov. 2003
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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).

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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

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-V-bar Approach Scenario

• 2. Scenario Description (7)
• PTV Scenario

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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

• 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

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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

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ULC Mission Scenario
2. Scenario Description (10)

• 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

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Capsule adaptor module upper I/F close to capsule
intermediate diameter,
4. PTV System Architect. ATV S/CModifications
(2)
Front docking module
Same configuration for CTV but with Additional
redundancies

• CoG of capsule close to I/F plane

Capsule adapter module

• 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)

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4. PTV System Architect. ATV S/CModifications
(3)
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4. CTV System Architect. ATV S/CModifications
(1) Global architecture choice (1)
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

• Capsule adaptor module slightly modified
  compared to PTV
• Same Front Docking module
• Emergency Escape module added
• Modified Ariane5 fairing added

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4. CTV System Architect. ATV S/CModifications
(5)
CTV Crew P/L Accommodation Results (Crew of 5)

• 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 10.32 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

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6. ULC System Architect. ATV S/CModifications
(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