ATV-2 vessel engineering - briefing for the Media 9-Feb-2011

The ATV2 Flight Segment

Media Briefing

H.P. Leiseifer

09 February 2011

Pag.2

Table of Content1. ATV2 Mission Objectives

2. ATV2 Lay Out and Design

3. ATV 2 Functions

4. Contingencies and Safety Aspects

4.1 System Requirements on Fault Tolerance and their Implementation

4.2 Manoeuvres

4.3 Re-Entry

5. Launcher & Launch Configuration

6. Inflight Services and Cargo

6.1 Refuelling

6.2 Water & Gas Delivery

6.3 Reboost

6.4 Dry Cargo

Acknowledgements

Pag.3

Media Briefing- 1. ATV 2 Mission Objectives

Objectives and Mass Budgets

– Propulsive Support to ISS including Re-boost, Attitude Control, Control Moment Gyro ( CMG) de-saturation and Debris Avoidance

– Delivery of Cargo, Gas and Retrieval of Wastes

– ISS refuelling

– For Johannes Kepler the Mission mass budget is:

– ATV Total Mass at Launch: 20060.5 kg – this includes

– Mission & Reboost Propellant: 6565,6 kg

– Propellant for Refuelling: 850,6 kg

– Gas ( Oxygen): 100 kg

– Integrated Dry Cargo : 2689,4 Kg ( Incl. 1084,3 Kg Racks)

Pag.4

Media Briefing- 2. ATV 2 Layout and DesignEnvelope and Mayor Constituents

– ATV Overall Envelope

– Compliant with AR 5 Fairing Constraints

– Length:10773 mm ( including Adapter , 2000 mm)

– Diameter:4482 mm ( max MDPS w/o MLI)

– ATV Major Constituents

– Integrated Cargo Carrier ( ICC) with

– 22 m3 of total pressurized module volume, shirt sleeve environment

– 16 m3 available for cargo accommodation

– 6 Integrated Light Racks ( ILRs )

– 2 Temporary Storage Racks (TSRs)

– Russian Docking System, Active Part to dock to Russian Service Module of the ISS

– Equipped External Bay ( EEB) with Refuelling System ( RFS) and Gas and Water Tanks , 3+3 ( Fluid Cargo)

Pag.5

Media Briefing- 2. ATV 2 Layout and Design Cont’d

– Meteorid and Debris Protection System ( MDPS)

– Sensors for GNC Functions

– Star Tracker , Videometers, Telegoniometer, Visual Video Targets, and Range Cues

– Antenna H/W for Communication Function– Proximity Link Antennas

– Antennas for TDRSS/Artemis Communication Chains

– KURS Antenna for direct ATV – Russian Segment communication

Pag.6


Integrated Cargo Carrier

Pag.7

Russian Docking System


Pag.8


– ATV Major Constituent Cont’d

– ATV Spacecraft ( SC) with

– Equipped Avionics Bay ( EAB)

– Equipped Propulsion Bay ( EPB)

– Separation and Distancing Module (SDM)

– Solar Generator System ( Sun Tracking)

– 4 Solar Arrays with 22.3 m span, 8.4 m2 each, 4.8 KW power total

– MDPS

Pag.9


ATV Configuration Drawing( w/o SDM)

Pag.10

Media Briefing 2. ATV 2 Layout and Design Cont’d

ATV Overall View

Pag.11

ATV Equipped Avionics Bay

Exploded View

VCHP other trays

Radiators other trays

Radiators batteries

Trays

Avionics equipment

VCHP batteries

Media Briefing 2. ATV 2 Layout and Design Cont’d

Pag.12


ATV 2 Equipped Avionics Bay - View Inside

Pag.13

Media Briefing -2. ATV 2 Layout and Design Cont’d

ATV 2 Equipped Propulsion Bay

Pag.14


ATV 2 in CSG ( Kourou) Integration Hall

Pag.15

Media Briefing- 3. ATV 2 Functions: Propulsion

– Bipropellant System with Monomethyl-Hydrazine ( MMH) as Fuel and Mixed Oxygen Nitrogen (MON) as Oxidizer

– MMH and MON are stored in 4 + 4 tanks, pressurized with He ( 2 Tanks)

– 4 Main Thrusters ( 400 N engines) located at ATV aft ( opposite the Docking System location ),

– 20 AOCS Thrusters ( 200 N engines), assembled in

– 4 Clusters with 5 thrusters each

– 8 Front Attitude Control Thrusters ( 200 N engines), assembled in

– 4 Clusters ATV Front Cone (Docking Adapter side ), with 2 thrusters each

Pag.16

Media Briefing-3.ATV 2 Functions: Propulsion Cont’d

Pag.17

Media Briefing-3.ATV 2 Functions: Propulsion Cont’dATV 2 Main Thruster View during Assembly ,Integration and Test

Pag.18

Media Briefing-3.ATV 2 Functions: Power

– The ATV Power System is composed of 4 identical completely independent power chains including

– 4 solar wings, each consisting of 4 panels; every solar array wing is provided with a rotating drive mechanism (SADM)

– 4 PCDUs that distribute power with a regulated voltage to the avionics units and with non-regulated voltage to the heaters; each PCDU receives power from one panel of each solar wing

– 4 rechargeable (NiCd) batteries, each with 40 Ah capacity

– 4 non-rechargeable (LiMnO2) batteries for MSU (segregation) and RSCE (high power peaks)

– 4 PCUs connected to PCDUs which provide regulated power to MSU, RECS and KURS equipment

Pag.19

Media Briefing-3. ATV 2 Functions: Power Cont’d

Y

1.41.3

1.21.1

W1

2.42.3

2.22.1

3.43.3

3.23.1

4.44.3

4.24.1

W4

PCDU1PCDU1

PCDU1PCDU1

PCDU2

PCDU2PCDU2

PCDU2

PCDU3 PCDU3

PCDU3PCDU3

PCDU4

PCDU4PCDU4

PCDU4

Z

1553 Bus A 1553 Bus B

1553 Bus C

28 V to usersConnected to1553B bus D

PCDU 4PCDU 3

28 V to usersconnected to1553B bus C

28 V to usersconnected to 1553B bus B

28 V to usersconnected to1553B bus A

PCDU 1 PCDU 2

28 VPCDU3

SADE1 SADE2

SA

DM

1

SA

DM

2

SA

DM

3

SA

DM

4

28

V R

EC

S (

ISS

)

28

V R

EC

S (

ISS

)

28

V R

EC

S (

ISS

)

28

V R

EC

S (

ISS

)

WIN

G 1

WIN

G 2

WIN

G 3

WIN

G 4

RB

AT

4

RB

AT

1

RB

AT

2

RB

AT

3

Wing 2

Wing 4

Wing 3

RB

at m

on

itorin

g an

d sa

fing

To

TC

U 3

To

TC

U 4

To

TC

U 4

To

TC

U 1

To

TC

U 2

To

TC

U 3

Wing 4

Wing 3

Wing 2

Wing 4

Wing 3

Wing 2

Win

g 4W

ing 3

Win

g 2

1553 Bus D

EG

SE

EG

SE

EG

SE

EG

SE

Pag.20

Media Briefing-3. ATV 2 Functions: Thermal Control

The Main Features of the ATV Thermal Control Concept are:

– Passive Thermal Control utilising Multi Layer Insulation ( MLI) and Constant Conductance Heatpipes (ICC and EPB)

– Active Thermal Control utilising Heater System to keep the ICC shell Temperature within Specification

– Active Thermal Control utilising Variable Conductance Heatpipes and Radiators for Electronic Boxes of the Equipped Avionics Bay

vapour

Heater command=> gas dilatation

Q

Non Condensable Gas

liquid

liquid

ControlAlgorithm

Thermistormeasurement

Heater command=> gas dilatation

Non Condensable Gasvapour

ControlAlgorithm

Thermistormeasurement

VCHP IN « CONTROLLED CONDUCTANCE » MODE VCHP IN « CONDUCTANCE OFF » MODE

liquid

liquid

liquid

liquidvapour

Pag.21

Media Briefing-ATV 2 Functions Datamanagement & Software

– Datahandling System architecture based on

– Fault Tolerant Computer ( FTC ) with 3 Data Processing Units , ATV internal MIL Bus System and MIL Bus I/Fs to SM/ISS

– FTC is 2 Fault Tolerant , dedicated to nominal operations including Failure Detection Isolation and Recovery ( FDIR)

– Monitoring & Safing Unit ( MSU) which is dedicated to the independent Proximity Flight Safety function to ensure ISS safety

– Flight Application Software (FAS) runs on FTC and the associated Soft Ware Units.

– For the FAS Category C SW has been accepted

– The MSU Software is Category A, since here Safety Critical Functions are managed with potentially catastrophic consequences and no adequate means of intervention.

Pag.22

Media Briefing- 3.ATV 2 Functions Datamanagement & Software Cont’d

Pag.23

Media Briefing-3. ATV 2 Functions: GNC

– The ATV Navigation. Guidance and Control function, encompassing ATV Flight Control and Flight Control Monitoring, is implemented in the Flight Application Software

– Based on the measurements obtained by the GNC Measurement System (GMS):

– 4 Gyrometers and 2 Startrackers for attitude measurement during free-flight and phasing

– 4 accelerometers for monitoring the ATV boosts during orbital manoeuvres

– 2 GPS receivers for relative (RGPS) navigation with ISS starting from 50-30 km distance from ISS

– 2 digital camera sensors (Videometers) for relative position and (from 30 m) relative attitude measurement during final docking approach starting from 300 m distance

– 2 laser range finders (Telegoniometers) for monitoring the GNC performance in relative position, range and range-rate to Station

Pag.24

ATV GNC Architecture

Media Briefing-3. ATV 2 Functions: GNC Cont’d

GPS1GPS2

GPS Antennas

Star Trackers

28 VPCDU4 28 V

PCDU3

28 VPCDU1

28 VPCDU2

28 VPCDU3

28 VPCDU4

28 VPCDU2

1553 Bus A 1553 Bus B

1553 Bus C1553Bus D

DTG1 DTG2 DTG3 DTG4

MS

U1

26

V

MS

U2

26

V

MS

U1

26

V

MS

U2

26

V

STR 2

STR 1

VDM 1

VDM 2

TGM 1

TGM 2

Videometers

Telegoniometers

28 VPCDU1

28 VPCDU4

28 VPCDU2

28 VPCDU3

ACM 2

Accelerometers

ACM 1

ACM 3

28 VPCDU2

28 VPCDU3

28 VPCDU4

Gyrometers

28 VPCDU1

Pag.25

Media Briefing-ATV 2 Functions: Communications

– Two segregated RF chains, one redundant one for comm’s with the ATV CC via TDRSS link, and one redundant for the proximity comm’s link to ISS

– 2 TDRSS link chains (1 kbps TC data rate, 8 or 64 kbps TM data rate 30W transmitted output power

– 2 transponders (receivers in hot, transmitters in cold redundancy)

– 3 S-band TDRSS antennas, one dedicated to the nominal chain pointing towards nadir, two for the redundant chain, with one pointing towards nadir and one towards earth

– 1 Switch to select the nadir or the earth pointing antenna in the redundant TDRSS chain

– 2 PROX link chains (20 kbps TM and TC data rate, 5 W transmitted output power

– PLAST transponders (receivers in hot, transmitters in cold redundancy)

– 2 PROX antennas, one nadir pointing, one earth pointing

– 2 CPFs in hot redundancy for HLTCs and HLTMs, and in cold redundancy for other commands and telemetry.

Pag.26

Media Briefing- 3.ATV 2 Functions: Communications

ATV Communications Architecture

BUS 1553

CPF1Mon.Mon.

CPF2

HLTMHLTCMon. Mon.

SSPA SSPA

Ground I/F

MSU MSU

SWITCH

TXRX

PLASTPROX1

TXRXPLASTPROX2

TXRXTrsp

TDRS2

Hybbrid

PL3 +Z

TD2 -Z TD3 -Z TD1 +Z

PL2 -Z

TXRXTrsp

TDRS1

Att 17.5 dB

DiplexerDiplexer

Ground I/F

PCDUs

Pag.27

Media Briefing- 3.ATV 2 Functions: Communications

ATV Overall Communication Paths

ISS

TDRS

ATV-CC MCC-M

White Sands

MCC-H

IGS

ISS-USOS <-> MCC-H

ARTEMIS

ATV

GPS

ARTEMIS MCF

RussianGroundStations

AT

V <

-> A

TV

-CC

COL-CC

REDU EET

CVI

DaSS

Pag.28

Media Briefing-4. ATV 2 Contingency & Safety Aspects

System Requirements on Failure Tolerance

1. no single failure or operator error shall have major or critical or catastrophic consequences

2. no combination of either:

- two failures, or

- two operator errors, or

- one failure and one operator error,

shall have catastrophic consequences

Pag.29

Media Briefing-ATV 2 Contingency & Safety Aspects Cont’d

Main Features of Implementation of Fault Tolerance in the ATV Avionic

System

– 4 segregated power chains (SGS chains, Batteries, PCDUs, PWR buses)

– 4 1553 MIL-bus data buses

– 2FT computer (3 voting DPUs, each one able to take control of every data bus)

– After the loss of 2 functional chains the vehicle is still able of SURVIVAL; however ATV operation in ISS vicinity may not be safe any more

– ISS safety in this case is guaranteed by a completely independent safety system (Proximity Safety Function - PFS) ), which will execute a Collision Avoidance Manoeuvre (CAM) that propels ATV out of the ISS proximity

Pag.30

Media Briefing- 4.ATV 2 Contingencies & Safety Aspects Cont’d

Manoeuvres

– Flight Control Monitoring performs a fine monitoring to detect any potential dangerous trajectory towards the ISS due to Failures not detected by FDIR. Depending on the anomaly, and the Mission Phase there is triggering of a

– Wait Manoeuvre

– Escape Manoeuvre

– Enabled as soon as Proximity Operations are staring ( 30 km distance to ISS)

– Handled by the nominal System

– Ensures a Delta V such that for 24 Hours ATV and ISS trajectories are apart

– Collision Avoidance Manoeuvre (CAM)

– Same as Escape however

– Handled by the MSU , since the nominal system is not capable anymore to handle the anomaly

Pag.31

Media Briefing-4. ATV 2 Contingency & Safety Aspects Cont’d

Re-entry

– The nominal re-entry is performed after ATV-2 de-docks from the ISS. It then goes to a 381x220 km intermediate orbit. The re-entry may take place in daily repeat orbit 4.

– The general situation is shown in the first picture ( ATV 1 case ) . Also to define the South Pacific Ocean Unpopulated Area (SPOUA ) applicable to ATV.

– The footprint of the ATV 2 re-entry case is shown in the next picture and fits perfectly inside theSPOUA

Pag.32


ATV 1 Re-entry Pattern

Pag.33


ATV 2 Re-entry Pattern

Pag.34

Media Briefing-5. Launcher & Launch Configuration

ATV to be launched on top of Ariane 5 Launcher

– Flight V 200, Scheduled for 15 February 2011

– Configuration: A5 ES

– Long Fairing

– 2 Solid Rocket Boosters (“welded”)

– EPS Uperstage

– ATV Mounted onto A 63936 Adapter “Separation and Distancing Module “ (SDM) which constitutes the ATV to 5 Interface

Pag.35

Media Briefing- 6. ATV 2 Inflight Services and Cargo

Refuelling

– 2x148.3 kg Unsymmetrical-DiMethyl-Hydrazine (UDMH )as Fuel

– 2x277 kg Nitrogen-TetraOxyde (NTO) as Oxydizer

– Automatic ISS refuelling through Docking Adapter

Water& Gas Delivery

– 100 Kg Oxygen as ISS supply

– Provided via Gas Control Panel – Crew operated

– ATV 2 mission does not provide for Water , tanks will be filled with liquid waste before de-docking via Water Control Panel – Crew operated

Reboost

– Currently 9 reboosts are planned , the first one is likely to happen shortly after docking

Pag.36

Media Briefing- 6. ATV 2 Inflight Services and Cargo

Gas Control Panel

Pag.37

Media Briefing- 6. ATV 2 Inflight Services and Cargo Cont’d

Water Control Panel

Pag.38


– Final mass of ATV-2 is 20,060 kg

– 6 Integrated Light Racks

– 4 M-01 bags mounted

– 64 Cargo Transfer bags (CTBs) + 4 M-01 bags integrated

in 4 lower racks during nominal

loading

– 29 CTBs integrated in 2 upper racks during late load, 13 days before launch

– Late load cargo mass reached maximum loading target

Fluid Cargo LoadingATV-2[kg]

ATV-1[kg]

Mission Propellant 2030 3598

ISS Propulsive Support 4535 2260

Water 0 267

Gas (3 tanks: Oxygen) 100 20

Refuel Propellant 850.6 860

Total Fluid Cargo 5486 3407

Dry Cargo Loading

Nominal Load Cargo (Integrated 17 Sep 2010) 1170 1150

Late Load Cargo (Integrated 28-29 Jan 2011)

435No late load for ATV-1

Total Dry Cargo 1605 1150

Total Cargo Fluid + Dry 7091 4557

Pag.39


Cargo TypeUtilization

Mass 204.58

Spares 555.59

Supplies (hygiene, batteries, cleaning)

181.72

Tools 26.52

Clothing 48.09

Food 519.94

PR Items 14.73

Other 54.18

Total 1605.35

Geoflow2

Columbus Power

Distribution Unit

(PDU)

Pag.40


M01 Bag Loading

Pag.41

Media Briefing- Acknowledgements

Thanks to

K. MacDonell

H. Wartenberg

F.Bouckaert

F.Caramelli

ATV-2 vessel engineering - briefing for the Media 9-Feb-2011

Technology

media briefingatv

clusters atv

atv power system

propulsion contd atv

atv interna

design contd pag

power contd pag

atv total mass