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Antenna moduledipole 0.2no off dipole 4electronics 0.2solar generator 0.4box 0.3Module 1.7no off Module 33Total Ant Modules 56.1 kg
Payload on LanderSilex terminal 150Ant data acquisition 45Miscell 50Remaining on Lander 245 kgcable kg/km 2km 45total cable 90 kg
Rover:Power 60Propulsion 80Structures 50Avionics 30total Rover x 3 660 kg
Mechanisms, Ramps 150 kg
Payload 1201 kg
Page 10 Lunar Lander Concept 23/24.11.2006
ASTRIUMPayload Power Budget
Antenna Module PowerNo of arm 3ant mod per arm 11feeds per ant mod 2PWR ADC/feed 0.1RCU/feed 0.2Safety factor 2Total ant mod. 1.2 WSolar generator W/m² 170min. area cm² 70.59Area required for ops above 6° 705.9 cm²Array size (n cm by n cm) 26.6
Duty cycle 46.7 % overall93.3 % daytime
0 % nighttime
Payload on LanderNo off FPGA 57Power / FPGA 5 WTotal power 285 Wother 50 WSilex terminal 130 W
COM Functional Architecture – Layout Onboard Lunar Lander
TMHGA
TC
MGA
LGA1
LGA2
Data
Radio Frequency
Distribution Unit
(RFDU)
(Diplexer,Switches,
Hybrid)
SSPA
SSPA
TWTA
TWTA
Dip
lexe
rD
iple
xer
CPF 2redund.
CPF 1nominal
X-Band Transmitternominal
X-Band Transmitterredundant
S-Band Transponderredundant
S-Band Transpondernominal
Page 18 Lunar Lander Concept 23/24.11.2006
ASTRIUMPropulsion
Clustered / Plugged Nozzle Layout
Page 19 Lunar Lander Concept 23/24.11.2006
ASTRIUMPropulsion
Tanks
2-Tank Concept:• Alphabus propellant tank• V=1911 dm^3 • MEOP 24 bar • thin titanium liner with CFRP overwrap• new development of MT Aerospace • Diameter x Height: 1154.2 mm x 1372 mm
4-Tank Concept:• Spacebus propellant tank• V = 1000 dm^3 • MEOP 19.5 bar• titanium tank• EADS-ST• Diameter x Height: 1154.2 mm x 1259 mm
Page 20 Lunar Lander Concept 23/24.11.2006
ASTRIUMConclusion
Within the LIFE scenario, the Lunar Lander is a very challengingproject:
• With todays technology, only RTGs can fulfill the power require-ments during lunar night – the power demand is a serious challenge (considering the RTG procurement problems)
• It is therefore proposed to refrain from night time operations• The data transfer requirements and the unique location on lunar
far side necessitate additional infrastructural elements (e. g. optical laser link, data relay satellites)
• Compared to the above, the remaining technical challenges can be covered with moderate development effort