ESA Document - Emits - ESA
ESA Document - Emits - ESA ESA Document - Emits - ESA
s Passive thermal control External radiators Two radiators of 57 m2, each weighting 850 kg (15 kg/m2 from ISS PVR) Insulation 0 kg for the main body of the transfer vehicle: the thermal properties of the MOD shield are exploited, the related budget transferred to structure. 150 kg are provisioned for specific external and internal elements insulation. Heating system 5.58 kW installed power corresponding to 13 kg (heaters, thermostats, sensors, lines) 3 control units (1 on), each 6 kg, 29W when shell heaters are 100% duty cycle (COF) Cryo systems Oxygen tank (life support) 4 coolers, each 3kg, consumption 35W each MLI: x kg for each tank (x 2) Overall budget (as introduced in the system) 3.3.4 Power Table 3-27: Design summary Table 3-28: Overall budgets HMM Assessment Study Report: CDF-20(A) February 2004 page 182 of 422 3.3.4.1 Design drivers The main drivers of the power subsystem design are: • The mission duration: 3 years and the required assembly time in LEO • A safety level issued to the transportation of astronauts • A power subsystem that fits with the assembly constraint (volume limitation, mounting,…) • The use of technologies expected to be qualified in 2015 Future technologies for power generation, conditioning or storage are abundant. Some of them seem really interesting for space purposes but still only exist on paper or in the best case at the level of experimentation. For this design, technologies that are more mature (already qualified in space but in which improvements are expected in the coming years) and ones have reached a high state of art are the only ones taken into account.
s HMM Assessment Study Report: CDF-20(A) February 2004 page 183 of 422 The performances considered of each element (mechanical, electrical) are issued from the ESA roadmap technology plan. The design proposed hereafter may therefore not be the most optimised one but is today one of the most feasible with the present technology knowledge. Therefore, the confidence in this subsystem will be higher compared to other possible designs for which technical improvements or qualifications are milestones that have less chance not to be reached on time. 3.3.4.2 Requirements 3.3.4.2.1 Mission requirements The mission is divided into: • An assembly phase until the Transfer Vehicle is completely built in LEO • The cruise to Mars orbit with an arrival date expected to be November 2033 • 553 days in orbit on Mars with the separation with the MEV sometime during this phase (orbit duration: 122.95 minutes with a worst case eclipse of 41 minutes) • The cruise back to Earth with a maximum duration of 1 year During all the phases, power has to be supplied to the different subsystems. Figure 3-42 shows the different modes of the mission. The time durations correspond to the reference time considered for the power design. Figure 3-42: TV Mission Modes
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s<br />
HMM<br />
Assessment Study<br />
Report: CDF-20(A)<br />
February 2004<br />
page 183 of 422<br />
The performances considered of each element (mechanical, electrical) are issued from the <strong>ESA</strong><br />
roadmap technology plan.<br />
The design proposed hereafter may therefore not be the most optimised one but is today one of<br />
the most feasible with the present technology knowledge. Therefore, the confidence in this<br />
subsystem will be higher compared to other possible designs for which technical improvements<br />
or qualifications are milestones that have less chance not to be reached on time.<br />
3.3.4.2 Requirements<br />
3.3.4.2.1 Mission requirements<br />
The mission is divided into:<br />
• An assembly phase until the Transfer Vehicle is completely built in LEO<br />
• The cruise to Mars orbit with an arrival date expected to be November 2033<br />
• 553 days in orbit on Mars with the separation with the MEV sometime during this phase<br />
(orbit duration: 122.95 minutes with a worst case eclipse of 41 minutes)<br />
• The cruise back to Earth with a maximum duration of 1 year<br />
During all the phases, power has to be supplied to the different subsystems.<br />
Figure 3-42 shows the different modes of the mission. The time durations correspond to the<br />
reference time considered for the power design.<br />
Figure 3-42: TV Mission Modes
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