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The Automated Transfer
Vehicle (ATV) is a cylinder 10.1 meters long and 4.5 meters in
diameter shrouded by insulating foil and extended solar panels.
the ATV consists of two modules, the spacecraft itself and the
integrated cargo carrier.
The pressurized section has room
for up to eight racks, stowing standard ISS Cargo Transfer Bags.
The cargo module includes a pressurized section, complete with
life-support system so that the ISS crew can access the contents.
The integrated Cargo Carrier also carries titanium tanks, which
can carry up to 840 kg of water, 860 kg of propellant, and 100 kg
of oxygen. The the docking equipment is located in the forward
section of the cargo section as well as most of the spacecraft's
avionics, with assorted sensors and antennas.
The ATV's spacecraft module
contains the four main thrusters plus 20 smaller thrusters for
attitude control. After docking, the ATV can perform ISS attitude
control, debris avoidance maneuvers and boost the station's orbit
to overcome the effects of atmospheric drag. To boots the ISS the
ATV can use up to four metric tonnes of propellant.
When the ATV is docked
with the station the crew will be able to enter the cargo section
and remove the cargo. Meanwhile, the ATV's gas and liquid tanks
will be connected to the station's plumbing to discharge their
contents. The ATV can remain attached to ISS for up to six months,
its life-support system kept running by its own solar panels.
During that time, the crew will refill the cargo section with the
station's waste. At intervals, the ATV thrusters can be used to
boost the station's altitude.
|
ATV
Automated
Transfer
Vehicle |
|
|
|
|
|
SPECIFICATIONS |
| Launch
Vehicle compatibility |
Ariane
5 (300 x 300 km, 51.6° transfer path) |
| On-orbit
life |
6
months |
|
DIMENSIONS |
| Length |
9,794 mm |
| Largest
Diameter |
4,480 mm |
| Payload
Envelope |
2
x 0.314 m3 and 2 x 0.414 m3 for each
of up to 8 racks |
| Span,
with solar arrays deployed |
22,281
mm |
|
CARGO
MASS BUDGET |
| Mass,
Dry Cargo |
1500 - 5500 kg |
| Mass,
Water |
0 - 840 kg |
| Mass, Gas
(Nitrogen, Oxygen, air, 2 gasses/flight) |
0 - 100 kg |
| Mass, ISS
re-boost and attitude control propellant |
0 - 4500 kg |
| Mass,
Total Cargo Upload Capacity |
7,667 kg |
|
ATV
MASS BUDGET |
| Mass,
spacecraft (dry) |
5,320 kg |
| Mass,
integrated cargo carrier (dry) |
5,150 kg |
| Air /
Consumables |
2,094 kg |
| Mass,
Total ATV |
12,564
kg |
| Mass,
Total ATV maximum, at launch |
20,231
kg |
Mass,
Download Capacity
(400 km altitude, 51.6° inclination) |
6,500 kg |
|
POWER |
| Power,
EOL (after 6 months) |
3.800
kW |
| Ascent
to orbit and de-orbit |
4
Solar panel wings of 4 panels each and 40 Ah rechargeable
batteries |
| Number
of solar arrays |
4 |
| Number
of panels per solar array |
4 |
| Solar
array construction |
Silicium
Solar Cells on 4 Carbon Fiber Reinforced Plastic Sandwich
panels |
| Required
power supplied by ISS |
<
0.300 kW Dormant mode
< 0.800 kW Active mode |
|
PROPULSION |
| Main
Propulsion System |
4
x 490 N thrusters
Pressure fed liquid bi-propellant system |
| Attitude
Control System |
28
x 220 N thrusters
Pressure fed liquid bi-propellant system |
| Propellant |
Monomethyl
hydrazine fuel
Nitrogen tetroxide oxidizer |
| Pressurization |
Helium
pressurant at 31.4 MPa |
|
COMMUNICATION
/ NAV |
| to
Ground |
S-band
via TDRS satellite |
| ATV to
ISS |
S-band
antenna |
| Navigation |
GPS |
|
THERMAL
/ ENVIRONMENTAL CONTROL |
| Thermal
Control |
Multi
Layer Isolation material, active thermal control using
Variable & Constant |
|
Conductive
Heat Pipes and paints |
| ECLSS |
Fire
detection, air circulation, air temperature monitoring |
|
CONSTRUCTION
MATERIAL |
| Pressure
Shell |
Al-2219 |
| Micrometeoroid
and Debris Protection System |
|
| Primary
Bumper |
Al-6061-T6 |
| Secondary
Bumper |
Nextel/Kevlar
blankets |
| Thermal
Insulation |
Goldised
Kapton Multi Layer Insulation blanket |
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