Akatsuki Venus Climate Orbiter |
Akatsuki Venus Climate Orbiter |
Mar 13 2010, 11:29 AM
Post
#501
|
|
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 |
|
|
Oct 28 2011, 05:13 AM
Post
#502
|
|
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
|
|
|
Oct 28 2011, 10:30 AM
Post
#503
|
|
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 Thanks, Paolo There is nothing we do not know on pages 1 to 3. These pages talk about history up until now. So, my translation starts with page 4 as follows. page 4 3.Operation of oxidiser dumping This was conducted on 6th, 12th, and 13th October 2011 for 6 minutes, 9 minutes, and 9 minutes respectively. (There are two graphs here) (with the graph on the left the vertical is temp and the horizontal is time in minute relative to the start of dumping of NTO) (This graph is the temp history and) red: fuel propellant valve temp blue: oxidiser propellant valve temp purple: oxidiser tank temp green: injector temp (with the graph on the right the vertical is acceleration in m/sxs and the horizontal is the measued value of acceleration) (there are 4 zones from left to right and the are) blue: test discharge (1 min) red: 1st discharge (6 min) green: 2nd discharge (9 min) purple: 3rd discharge (9 min) (top left character string says) : RCS settling (3 seconds) (bottm righ string pointing to a sudden drop says) : end of discharge Although power is supplied to the propellant valve on the fuel side while discharging operation is in progress there is no cooling by fuel available. Thus, it was feared that the temp of the fuel side propellant valve might exceed the allowed limit. Also, freezing of the OME injector was feared. However, we judged that discharging operation was feasible from the ground tests and analyses as long as we divide the operation into several times. It was confirmed that the discharging operation was completed at the 3rd time without exceeding the allowed temp limit. The sudden drop in acceleration during the 3rd discharging operation indicatef that pressurising helium gas pushed through and discharging was complete as planned. end of page 4 (and 2 more pages to go and they will follow tommorrow) P |
|
|
Lo-Fi Version | Time is now: 27th September 2024 - 06:51 AM |
RULES AND GUIDELINES Please read the Forum Rules and Guidelines before posting. IMAGE COPYRIGHT |
OPINIONS AND MODERATION Opinions expressed on UnmannedSpaceflight.com are those of the individual posters and do not necessarily reflect the opinions of UnmannedSpaceflight.com or The Planetary Society. The all-volunteer UnmannedSpaceflight.com moderation team is wholly independent of The Planetary Society. The Planetary Society has no influence over decisions made by the UnmannedSpaceflight.com moderators. |
SUPPORT THE FORUM Unmannedspaceflight.com is funded by the Planetary Society. Please consider supporting our work and many other projects by donating to the Society or becoming a member. |