ESA ISS Automatic Transfer Vehicle Overview

8/14/2019 ESA ISS Automatic Transfer Vehicle Overview

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ATV Overview

A cutaway view ofthe Automated Transfer

Vehicle (ATV) .(Image: ESA/D. Ducros)



Integrated Cargo Carrier



The Pressurised section of the ATV Integrated Cargo carrierbeing loaded with dry cargo on 8 December 2007.

(Image: ESA /CNES/Arianespace/Photo optique video du CSG)

Unpressurised section (Fluid cargo) Behind the back wall or interface of the pressurisedsection is the unpressurised section of theIntegrated Cargo Carrier where the fluid cargo isstored. This external bay houses 22 spherical fluidtanks of different sizes and colours. These tanksare used to resupply the Station with refuellingpropellant for the Station's own propulsion system,

water and air (oxygen and nitrogen) for the crew

- 840 kg of drinking water;- 100 kg of air (oxygen and nitrogen);- 860 kg of refuelling propellant for the Station’s

propulsion system;- 4700 kg of propellant for re-boost;- 5500 kg of dry supplies like bags, drawers and

fresh food;

Front Cone (Rendezvous and Docking Equipment) The ‘nose’ of the Integrated Cargo Carrier housesthe Russian-made docking system and avionicsand propulsion hardware, critical to the automaticapproach, rendezvous and docking of the ATVwith the ISS. There are two videometers (imageprocessing system able to compute distance andorientation of the ISS), two telegoniometers,



ATV Service Module

Avionics The avionics bay is the brain of the ATV. It lookslike a cylindrical ring of 1.36m high, and is locatedin the upper part of the Service Module. It

accommodates critical items like computers,gyroscopes, navigation and control systems andcommunications equipment. All these items aremounted on ten equipment carrier trays which areprotected from the temperature variations bystate-of-the-art heat pipes. The ATV ServiceModule takes advantage of a very sophisticatedarchitecture for its hardware and software in orderto keep the ATV functioning in case of hardware

failure or main malfunction.



electrical power to rechargeable batteries, whichare vital for powering ATV systems during eclipseperiods in orbit. The solar arrays are comprised ofsilicium solar cells, spread on 4 carbon fibrereinforced plastic sandwich panels per array witha total surface area of 33.6m² (4 X 8,4m²) andable to produce an average of 4800 watts. Mounted on the ATV Service Module, the four suntracking arrays are totally independent and canget the best orientation to the sun thanks torotating mechanisms.

ISS attitude control, debris avoidancemanoeuvres and reboosting the Station. In orderto perform this reboost the ATV may use up to 4.7tonnes of its own propellant at intervals of 10 to 45days. At the end of the mission the ATV ServiceModule thrusters will use their remaining fuel tode-orbit the spacecraft.



Key Mission Data

MISSIONMission Name:

ISS Mission Designation

LAUNCHER AND SPACECRAFTSpacecraftSpacecraft mass at launchLauncher

LAUNCH SITE

MISSION PARAMETERS

Launch parametersScheduled Launch dateInclinationInitial Orbit Altitude

ATV Jules Verne Mission

ATV1

Automated Transfer Vehicle (ATV)19,357 kgAriane 5 ES ATV

European Spaceport, Kourou, French Guiana

9 March 2008 (00:59 local time 04:59 CET)51.6 °260 km



Pre-Launch to Final Countdown

The ATV will be launched from the EuropeanSpaceport in French Guiana by an Ariane 5 ESATV. It will be injected into a 51.6º orbit, the sameas the ISS, and at an altitude of around 260 km,

below the Stations' altitude of around 340 km.

Ariane 5 moving by rail to the launch pad.

Finally, with 6 min 30 s until ignition of the mainstage engine, the automatic sequence coveringthe final checks and launcher activationprocedures begins. The launcher becomes

autonomous with 1 min until main stage ignitionas the power supply is switched to Ariane 5internal power.

With 22 s until main stage ignition the flight controlsystems on the lower stages are activated,followed 10 s later by a pressure check on themain stage tanks. The main stage engine is nowignited.



Launch and Early Orbit Activities

Once it has been ascertained that the Vulcain 2engine is running normally, 7 s after ignition, thesolid rocket boosters are ignited and the Ariane 5lifts off from the launch pad. The Ariane 5 is on

automatic pilot and is carefully monitored as itcarries the ATV into orbit.



Artist’s impression of the Ariane 5/ATV following fairing jettison. (Image: ESA/D. Ducros)

Just over 9 minutes after launch the Vulcain engineshuts down. At this point the main stage separatesand follows a ballistic trajectory during before re-entering the atmosphere. Most of it burns up in theatmosphere and the remaining parts fall into thePacific Ocean, some 2000 km off the coast ofSouth America.

After main stage separation over the AtlanticOcean, the Aestus engine of the upper stage willperform a first boost lasting 8 minutes to reach anelliptical orbit (136 km x 260 km). After a coastingphase to the apogee of the elliptical orbit lasting45 minutes, a second boost with a duration of 30seconds serves to reach the ATV circular injectionorbit at an altitude of 260 km.

This second firing of the Aestus engine will takeplace over southeast Australia, just over an hourinto the flight. At this point ATV telemetry will startas will the initialisation of the ATV propulsionsystem and the ATV Control Centre will carry out acheck of ATV status. Just short of 70 minutes afterlaunch the ATV will separate from the Ariane 5

upper stage over the Pacific and will activatenavigation and propulsion systems. Responsibilityfor the ATV flight has now transferred from Kourouto the ATV Control Centre in Toulouse, France.

ATV communications are optimised by setting upa link via the Tracking and Data Relay SatelliteSystem. About 25 minutes after final separationthe ATV will be automatically navigating using

i t f it t t k Thi i f ll d fi



In-Orbit Activities: Phasing and Demonstration Days



Rendezvous and Docking



Docked Activities



Undocking/Destructive Reentry



ATV Payload

When the Jules Verne ATV is launched to the ISSit will be carrying around 8.3 tonnes of wet and drycargo with an additional 2.3 tonnes of cargosupport hardware. The cargo will be used in orderto transport the ATV to the ISS, to reboost the ISSto a higher orbiting altitude, to resupply the ISS,and to deorbit the ATV with waste and items nolonger needed on the ISS at the end of themission. The cargo is split as follows:

Refuelling propellant (860 kg)Once attached to the Station, 860 kg of refuellingpropellant will be transferred from the ATV to theISS. This consists of two different fluids: the fuelunsymmetrical dimethylhydrazine (UDMH) andthe oxidiser, nitrogen tetroxide (N2O4), whichprovides a source of oxygen so the fuel can igniteand burn in orbit. This will be used by the ISS fororbit and attitude control.

Water (270 kg)This is what is known as potable water for use bythe crew for drinking, food rehydration and oralhygiene.

Oxygen (20 kg)This is used for resupply of oxygen in theatmosphere inside the ISS, which is similar to thaton Earth. Once in orbit, the 20 kg of oxygencarried up by Jules Verne ATV, is manuallyinjected by the crew into the ISS atmosphere.



Rendezvous and Docking Technology

From a distance of around 30 km from the ISS theATV will use relative GPS in order to close in on theISS up to a distance of 249 m. Hereafter the ATVwill use a brand new European-built technology

called a videometer, together with additional datafrom telegoniometers, to successfully rendezvousand dock with Russian Zvezda Service Module ofthe International Space Station.



Engineers monitor ATV rendezvous testing at Europe’s largest

ship hull test facility, 100 km west of Paris in 2006. (Image: ESA)

The Jules Verne videometer is designed andmanufactured by Sodern, a subsidiary of EADS, inLimeil-Brévannes, a Paris suburb. All ATVspacecraft will have two identical videometers,installed 20 cm apart on the front of the ATV. Bothare active during rendezvous with one acting as aback-up.

Like the two videometers, two telegoniometers(one back-up), located on the ATV front cone,emit laser pulses (at a different wavelength to thevideometers) towards the retroflectors on the ISS.The travel time of the pulses, which are reflectedback, gives the distance between the twospacecraft. The direction from the ATV to the ISS

is given by the orientation of the telegoniometers’two built-in mirrors, which rotate to aim the lasertowards the retroreflectors.

The distance and direction information from thetelegoniometer can be compared to that obtainedvia image processing using the videometer.However, only the videometer can compute theorientation of the ISS. Activated at the same

250 m distance from the ISS, the telegoniometer’sradar-like pulses provide 10 000 hits per second,whereas the camera-like videometer illuminatesits objective from once per second to 10 times persecond as it approaches its target.



Ariane 5 ES ATV

of the Ariane 5 has been designed to place theATV into a 260 km circular low Earth orbit inclinedat 51.6˚. From this orbit the ATV will use its ownpropulsion system to automatically reach and dock

with the International Space Station (ISS).

The Ariane 5 ES ATV is 53 m in height, has adiameter of up to 5.4 m and a mass of 760 tonnesat lift off. It is composed of the same lowersections as an Ariane 5 ECA using the sameboosters and the same cryogenic main stageequipped with the improved Vulcain 2 engine. Theupper composite is composed of a re-ignitableStorable Propellant Stage and a new reinforcedvehicle equipment bay as it will be placing morethan twice the payload mass of any previousAriane 5 launch into orbit.

BoostersThe Ariane 5 solid propellant boosters are thelargest solid rocket boosters ever produced inEurope. Weighing 37 tonnes each when empty,they are 31 m high and 3 m in diameter. Each

b i f l i l i h



Artist’s impression of Ariane 5 ES ATV upper composite (cutaway view) (Image: ESA/D. Ducros)

A h b f h C i M i S i h i i i i f di l i h h



European Spaceport, Kourou, French Guiana



ATV Control Centre, Toulouse, France(Responsible for ATV operations)



To allow continuous coordination with the othercontrol centres and to remain in contact with theATV during the mission, using the NASA Trackingand Data Relay Satellite System as well as ESA‘sArtemis relay satellite, the ATV Control Centre willrely on the European ISS ground communicationnetwork, which is controlled from the Columbus

Control Centre located at DLR, inOberpfaffenhofen, Germany.

The Columbus Control Centre. (Image: DLR)



Jupiter Control Centre, Kourou, French Guiana (Responsible for Ariane 5 launch and ascent and placing ATV into orbit)



Mission Control Centre – Moscow, Russia (Responsible for Russian ISS modules and Soyuz/Progress spacecraft)



Mission Control Center – Houston, Texas, USA (Overall Control of ISS activities)



ATV Industrial Team



Credits

This document has been compiled, produced andwritten by the Coordination Office of the EuropeanSpace Agency’s Directorate of HumanSpaceflight, Microgravity and Exploration

Programmes in Noordwijk, The Netherlands. Ithas been compiled from internal ESA sourceswith additional images and information kindlysupplied by the following organisations:

EADS Astrium

French Space Agency (CNES)

National Aeronautics andSpace Administration (NASA)

Thales Alenia Space

Contacts

European Space Agency (ESA)Directorate of Human Spaceflight, Microgravityand Exploration ProgrammesESTEC, Keplerlaan 1, PO Box 299

2200 AG Noordwijk, The Netherlands.Tel: +31 (0) 71 565 6799Fax: +31 (0) 71 565 5441www.esa.int/spaceflightwww.esa.int/atvwww.esa.int/columbus

ESA Media RelationsESA Head Office, Paris, France.Tel. + 33 1 5369 7155Fax. + 33 1 5369 [email protected]

EADS Astriumhttp://www.astrium.eads.net/

Utilisation Relevant Data A t t d T f V hi l (ATV)



www.spaceflight.esa.int/users I l l u s t r a t i o n s : E S A / D .

D u c r o s

Utilisation Relevant Data

Launch site: Kourou, French Guiana.

First flight: Spring 2008

Flight rate: Mean: 1 ATV/18 months

OnOrbitConfiguration

Deployed solar arrays, with a total span of 22.3 m, that provide electrical power torechargeable batteries for eclipse periods.Automated flight towards the InternationalSpace Station.

FlightHardware

Propulsion and re-boost systemAvionics equipmentGuidance navigation and control systemCommunications systemPower generation and storage systemThermal control systemRussian docking and refueling system

LaunchConfiguration

Payload 8 racks with 2 x 0.314 m3 and 2 x 0.414 m3

envelope: each 1.146 m3 in front of 4 of these 8 racks

Cargo mass: Dry cargo: 1,500 - 5,500 kg

Water: 0 - 840 kg

Gas (Nitrogen, Oxygen, air, 2 gases/flight): 0 -

100 kg

ISS Refueling propellant: 0 - 860 kg (306 kg

of fuel, 554 kg of oxidizer)

ISS re-boost and attitude control propellant: 0 -

4,700kg

Total cargo upload capacity: 7,667 kg

Launch vehicle: Ariane 5 (300 x 300 km, 51.6° transfer orbit

ATV will be launched with its solar panels

folded to the body of the spacecraft. Electrical

power will be supplied by non rechargeable

batteries.

European servicing and logistics vehicle

PROJECT:

TITLE: AutomatedTransfer Vehicle

DOCUMENT N°:

International

Space Station

ERASMUS User Centre and Communication Office - Directorate of Human Spaceflight, Microgravity and Exploration Programmes

Automated Transfer Vehicle (ATV)

The Automated Transfer Vehicle is an unmanned automatic vehicle which is put in orbit by the

European Ariane 5 launcher. It provides the International Space Station with: pressurized cargo,

water, air, nitrogen, oxygen and attitude control propellant. It also removes waste from the station and

re-boosts it to a higher altitude to compensate for the atmospheric drag.

Multi-Layer

Insulation blanket

Russian

docking

and refueling

system

2 x visual targets

for crew monitoring

S-Band Antenna

Boom

GPS antennas

for positioning

TDRS antennas

for communication

2 x star

trackers

Ranging

cues

4 x optical

rendez-vous sensors

Payload

racks

Integrated Cargo Carrier

(ICC)

Propulsion Module (PM)

Spacecraft

subassembly

Stand-off Water and gas tank

EUC-ESA-FSH-003

REV.

1.2

Primary

structure

Micrometeoroid and

orbital debris

protection system

Multi-Layer

Insulation

blanket

Radio frequency link with

Space Station

for proximity operations

Attitude control and braking

thrusters (28 x 220 N)

Main engine

(4 x 490 N)

4 x solar arrays

for generation of

electricity

Specifications



Dimensions

Length: 9,794 mm (probe retracted)Largest diameter: 4,480 mmSolar arrays span: 22,281 mm

MassBudget

Vehicle dry mass: 10,470 kgVehicle consumables: 2,613 kgTotal vehicle mass: 13,083 kg

Total cargo upload capacity: 7,500 kgMass at launch (max): 20,750 kgWaste download capacity: 6,300 kg

(420 km altitude, 51.6° inclination)

Propulsion

Main propulsion system: 4 x 490 N thrusters (Pressurizedliquid bi-propellant system)

Attitude control system: 28 x 220 N thrusters (Pressurizedliquid bi-propellant system)Propellant: Monomethyl hydrazine fuel and

Nitrogen tetroxide oxidizer Pressurization: Helium pressurant at 31 MPa

CommunicationsInfrastructure

To ground: S-band via TDRS satelliteATV to ISS: S-band antenna via Proximity linkNavigation: GPS

Thermal/EnvironmentalControl

Thermal Control: Multi Layer Insulation material,active thermal control usingVariable & Constant ConductiveHeat Pipes and paints

ECLSS: Fire detection, air circulation, air temperature monitoring

ElectricalPower

Ascent to ISS and de-orbit: 4 Solar panel wings of 4 panels

each and 40 Ah rechargeable

batteriesNumber of arrays: 4Number of panels/array: 4Generated power: 3,800 W after 6 months in orbitRequired power: < 400 W Dormant mode,supplied by ISS: < 900 W Active mode

MainConstructionMaterial

Pressure shell: Al - 2219Micrometeoroid and DebrisProtection System:Primary bumper: Al-6061-T6Secondary bumper: Nextel/Kevlar blanketsInternal structure (racks): Al-6061-T6Thermal insulation: Goldised Kapton Multi-layer Insula-

tion blanket & aluminised beta cloth

Solar arrays: Silicium Solar Cells on 4 CarbonFibre Reinforced Plastic

Sandwich panels MainContractor

EADS-Space Transportation, Leading a consortium of manysub-contractors

SCALE : 1:75

DIMENSIONS : mm

TITLE: DOCUMENT N° :

∅ 22316

1 1 5 8

1 1 1 5 8

4482

13602045

49163405957

9794 (probe retracted)

10269 (probe deployed)

Specifications

REV.

4480

22281

Automated

International

Space Station

PROJECT:

ESA ISS Automatic Transfer Vehicle Overview

Documents

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