ESA Document - Emits - ESA
ESA Document - Emits - ESA ESA Document - Emits - ESA
s Characteristic Value number of thrusters 4 number of tanks 2+2 Thrust 33 kN/each (restartable) Isp 330 sec exit diametre 1070 lengh 1730 mm thruster mass 120 kg propellant MMH/NTO O/F ratio 2.05 tank material Ti max MEOP 7 bar Mass of UDMH tank 17.1 kg (each) Mass of NTO tank 21.1 kg (each) 4.5.7.4 Baseline design 2nd stage Table 4-64: Propulsion system for the first stage Figure 4-121: AESTUS Engine HMM Assessment Study Report: CDF-20(A) February 2004 page 392 of 422 Four YUZHNOYE RD 869 pump-fed thruster have been chosen as propulsion system for this module. The thruster is under development for 4 th stage of the European VEGA Launcher. The propulsion system presents the following characteristics.
s 4.5.7.5 Budgets Characteristic Value Number of thruster 4 Thrust 5 kN (pump- fed) Isp 325 sec exit diameter 325 mm length 600 mm thruster mass 34 kg propellant UDMH/NTO O/F ratio 2.1 number of tanks 2+2 Tanks material Ti max MEOP 7 bar Mass of UDMH tank 5 kg (each) Mass of NTO tank 5.8 kg (each) Table 4-65: Propulsion system for the second stage Propellant mass 2986 kg Propulsion Dry mass (including margins) 267 kg HMM Assessment Study Report: CDF-20(A) February 2004 page 393 of 422 This mass includes an estimation of thrusters mass, the tanks, and a roughly estimation of feedlines, valves and regulators, propulsion thermal control, avionics, actuators and does not consider the structure of the propulsion system, power and communication. 4.5.8 Environmental control and life support system The life support comprises the following subsystems • Atmosphere Supply and Control • Atmosphere Revitalization • Temperature and Humidity Control • Water Management • Waste Management • Food Management • Safety • EVA Provisions • Hygiene • Crew Accommodations Crew accommodations have been added to the classical set of life support functions as the crew accommodation engineering domain does not posses a separate workbook in the CDF study, in which hardware specifications could be added.
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s<br />
4.5.7.5 Budgets<br />
Characteristic Value<br />
Number of thruster 4<br />
Thrust 5 kN (pump- fed)<br />
Isp 325 sec<br />
exit diameter 325 mm<br />
length 600 mm<br />
thruster mass 34 kg<br />
propellant UDMH/NTO<br />
O/F ratio 2.1<br />
number of tanks 2+2<br />
Tanks material Ti<br />
max MEOP 7 bar<br />
Mass of UDMH tank 5 kg (each)<br />
Mass of NTO tank 5.8 kg (each)<br />
Table 4-65: Propulsion system for the second stage<br />
Propellant mass 2986 kg<br />
Propulsion Dry mass (including margins) 267 kg<br />
HMM<br />
Assessment Study<br />
Report: CDF-20(A)<br />
February 2004<br />
page 393 of 422<br />
This mass includes an estimation of thrusters mass, the tanks, and a roughly estimation of<br />
feedlines, valves and regulators, propulsion thermal control, avionics, actuators and does not<br />
consider the structure of the propulsion system, power and communication.<br />
4.5.8 Environmental control and life support system<br />
The life support comprises the following subsystems<br />
• Atmosphere Supply and Control<br />
• Atmosphere Revitalization<br />
• Temperature and Humidity Control<br />
• Water Management<br />
• Waste Management<br />
• Food Management<br />
• Safety<br />
• EVA Provisions<br />
• Hygiene<br />
• Crew Accommodations<br />
Crew accommodations have been added to the classical set of life support functions as the crew<br />
accommodation engineering domain does not posses a separate workbook in the CDF study, in<br />
which hardware specifications could be added.
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