Akatsuki Venus Climate Orbiter |
Akatsuki Venus Climate Orbiter |
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![]() Senior Member ![]() ![]() ![]() ![]() Group: Members Posts: 1729 Joined: 3-August 06 From: 43° 35' 53" N 1° 26' 35" E Member No.: 1004 ![]() |
I thought it was time to start a separate thread on this mission, launching soon
some good medium-resolution images of the spacecraft are available on JAXA digital archives http://jda.jaxa.jp/jda/p3_e.php?time=N&...mp;mission=4066 |
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#2
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![]() Senior Member ![]() ![]() ![]() ![]() Group: Members Posts: 1729 Joined: 3-August 06 From: 43° 35' 53" N 1° 26' 35" E Member No.: 1004 ![]() |
a new pdf release by JAXA http://www.jaxa.jp/press/2011/10/20111026_sac_akatsuki.pdf
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#3
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Member ![]() ![]() ![]() Group: Members Posts: 817 Joined: 17-April 10 From: Kamakura, Japan Member No.: 5323 ![]() |
a new pdf release by JAXA http://www.jaxa.jp/press/2011/10/20111026_sac_akatsuki.pdf above for ease of reference page 5 4.Considerations relating to orbit control by RCS 1. Maintaining the thermal balance in the thruster 's catalytic layers during the continuous firing Main points of concern with the continuous firing of RCS and our current stance are as follows. By adopting the orbit control attitude (+X pointing in the sun's direction) the +X side of the thruster will be in a thermally difficult state. However, analyses confirmed that the temp of the catalytic layers during the burn will be in an equiribruim state. 2. Temp rise of the propellant valve by the heat soakback (*) after the continuous firing Although the temp of the thruster valve will increase by the heat soakback after the continuous firing it was confirmed that the rise will remain within the allowed temp range. * This is a occurrence in which the temp of the propellant valve kept cooled by the supplied fuel will increase by the heat conducted from the hot burner after the continuous firing of the engine 3 Temp increase of various parts of the probe due to the attitude maintenance operation during the continuous firing Orbit control attitude (+X sun pointing direction) will lead to temp increase in the various parts of the probe. However, we will change back to +Z sun pointing direction immediatelyy after the firing and it was confirmed that all parts of the probe will not exceed the allowed temp range. Conclusion: Based on the report of 30 September at the investigation meeting regarding the RCS continuous firing and records of similar burning in orbit by other satellites in addition to above further consideration as reported here we reached a conclusion that an orbit control firing by RCS will be conducted in November this year during a nearest sun approach. end of page 5 P |
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