[Isocops] IBEX Orbit# 240 ATS (17 Mar 14 - 26 Mar 14) - v001 approval

Thu Mar 6 23:16:28 EST 2014

All, 

I have looked at the orbit 240 ATS, 

IBEX_2014_076_o0240a_v001.scr, 

and I approve. 

There are no constraint violations in 

IBEX_2014_076_o0240a_v001.ccvr. 

The PL commands in the v001 ATS match those in the v003 STF, 

IBEX_2014_076_o0240a_v003.stf. 

Ascending and descending command sequences are consistent with each other and 15 Re ascending, the apogee maneuver time and 15 Re descending as determined from the OEF, 

IBEX_2014_076_o0240a_v001.oef, 

and as verified with ibex_orbit. 

The Hi ABAB command sequences and timing look reasonable. 

There are two star tracker outages. The first starts in arc B of orbit 239 and ends 10+ hours before apogee. The second starts 30+ hours after apogee and ends 2+ days later. Some despinning may be required due to these outages. 

There is one moon in Lo FOV session in arc B. The ATS start time is about 45 minutes after that in the OEF and the ATS end time is about 1 1/2 hours before that in the OEF. These differences are not unusual. 

The ground station command sequence is correct and the timing and bit rate match those in the contacts file, 

IBEX_Orbit240Contacts.txt, 

for the apogee contact. All other contacts will be blind acquisitions while we are doing Hi ABAB operations. 

No battery cell balancing this orbit; we'll do it again in the next orbit. 

The sun precession maneuver at perigee of orbit 239 left us pointing in safe directions for orbit 240 arc A ascending and descending sequences: 

ibex_rotate -o -r +356.280 -d -1.604 -w ibex-sun -t 2014/03:17:18:26:06 
Quaternion +0.000000,+0.000000,+0.000000,+0.000000 
points axis +1.000000,+0.000000,+0.000000 
towards ECI +0.997502,-0.064855,-0.027991 
which is R.A. +356.280 Decl. -1.604 
missing R.A. +357.171 Decl. -1.232 (ibex-sun) 
error is R.A. +0.891 Decl. +0.372 
for a total 0.965 deg 

ibex_rotate -o -r +356.280 -d -1.604 -w ibex-sun -t 2014/03:21:10:33:58 
Quaternion +0.000000,+0.000000,+0.000000,+0.000000 
points axis +1.000000,+0.000000,+0.000000 
towards ECI +0.997502,-0.064855,-0.027991 
which is R.A. +356.280 Decl. -1.604 
missing R.A. +0.572 Decl. +0.211 (ibex-sun) 
error is R.A. +355.708 Decl. +1.815 
for a total 4.659 deg 

The inertial maneuver at apogee leaves us pointing in safe directions at the time of the maneuver and for arc B ascending and descending sequences: 

ibex_rotate -o -u 0.999618,-0.019613,-0.019494 -w ibex-sun -t 2014/03:21:12:17:28 
Quaternion +0.000000,+0.000000,+0.000000,+0.000000 
points axis +1.000000,+0.000000,+0.000000 
towards ECI +0.999618,-0.019613,-0.019494 
which is R.A. +358.876 Decl. -1.117 
missing R.A. +0.636 Decl. +0.239 (ibex-sun) 
error is R.A. +358.240 Decl. +1.356 
for a total 2.222 deg 

ibex_rotate -o -u 0.999618,-0.019613,-0.019494 -w ibex-sun -t 2014/03:21:13:52:12 
Quaternion +0.000000,+0.000000,+0.000000,+0.000000 
points axis +1.000000,+0.000000,+0.000000 
towards ECI +0.999618,-0.019613,-0.019494 
which is R.A. +358.876 Decl. -1.117 
missing R.A. +0.695 Decl. +0.265 (ibex-sun) 
error is R.A. +358.181 Decl. +1.382 
for a total 2.285 deg 

ibex_rotate -o -u 0.999618,-0.019613,-0.019494 -w ibex-sun -t 2014/03:25:17:46:39 
Quaternion +0.000000,+0.000000,+0.000000,+0.000000 
points axis +1.000000,+0.000000,+0.000000 
towards ECI +0.999618,-0.019613,-0.019494 
which is R.A. +358.876 Decl. -1.117 
missing R.A. +4.377 Decl. +1.902 (ibex-sun) 
error is R.A. +354.499 Decl. +3.019 
for a total 6.274 deg 

The inertial precession maneuver at perigee leaves us pointing in safe directions at the time of the maneuver and at orbit 241 apogee: 

ibex_rotate -o -u 0.998634,0.051025,0.011292 -w ibex-sun -t 2014/03:25:19:51:41 
Quaternion +0.000000,+0.000000,+0.000000,+0.000000 
points axis +1.000000,+0.000000,+0.000000 
towards ECI +0.998634,+0.051025,+0.011292 
which is R.A. +2.925 Decl. +0.647 
missing R.A. +4.455 Decl. +1.936 (ibex-sun) 
error is R.A. +1.530 Decl. +1.289 
for a total 2.000 deg 

ibex_rotate -o -u 0.998634,0.051025,0.011292 -w ibex-sun -t 2014-03-30T17:51:29.618Z 
Quaternion +0.000000,+0.000000,+0.000000,+0.000000 
points axis +1.000000,+0.000000,+0.000000 
towards ECI +0.998634,+0.051025,+0.011292 
which is R.A. +2.925 Decl. +0.647 
missing R.A. +9.049 Decl. +3.865 (ibex-sun) 
error is R.A. +6.124 Decl. +3.218 
for a total 6.913 deg 

No Lo O-mode. 

There is no overlap with orbit 239 commands by manual inspection or by checking at 

http://ibex.unh.edu/cgi-bin/ats.cgi . 

Command Approval Checklist is attached. 

Ken 

----- Original Message -----
From: "Ibex Mission Operations" <ibexops at gmail.com> 
To: joe at boulder.swri.edu, "IBEX-FDG" <IBEX.fdg at applieddefense.com>, "IBEXOPS/ORB" <IBEXops at orbital.com>, "ISOC at New Hampshire" <isocops at lists.sr.unh.edu>, "John Cavallo" <cavallo.john at orbital.com>, "Ken Fairchild" <fair-play at comcast.net>, "Mark Tapley" <mtapley at swri.edu>, "Nigel Angold" <ngangold at earthlink.net>, "Robert Lockwood" <Lockwood.Robert at Orbital.com>, "Roland Vanderspek" <roland at space.mit.edu>, "Ryan Tyler" <tyler.ryan at orbital.com>, "Sheral Wesley" <wesley.sheral at orbital.com>, "Thomas Regiec" <regiec.thomas at orbital.com>, "Tim Perry" <perry.tim at orbital.com> 
Sent: Tuesday, March 4, 2014 2:51:18 PM 
Subject: IBEX Orbit# 240 ATS (17 Mar 14 - 26 Mar 14) 

Guys, 
Here are the planning files for Orbit# 240. 
Please respond to this email thread with any questions and approvals. 
All approvals are required before 7 Mar 14 @2200 UTC 

Please note the following 

1. OEF Generation 
The OEF was generated using o0238a OEF because Orbit# 239 has a Sun Maneuver at Perigee 

2. Small Eclipse at Perigee that requires no action 
# Orbit# 240 PERIGEE: Small Eclipse, No Action Required 
# 2014-03-26T10:26:50.562Z,EclipseEntry,moderate:false,long:false,orbit:240 
# 2014-03-26T10:42:37.825Z,EclipseExit,moderate:false,long:false,orbit:240 

3. No Battery Balancing Commands 

4. Moon in Lo FOV Commands 
# Orbit# 240 APOGEE: Moon in Lo FOV Commands 
# 2014-03-25T00:30:09.041Z,MoonInLoFovStart,orbit:240 
# 2014-03-25T12:51:01.535Z,MoonInLoFovStop,orbit:240 

5. IBEX_Hi Gain Test commands occur around Apogee commands 
# Orbit# 240 IBEX_Hi Gain Test 
# Start: $TIME=2014/03:19:16:00:00 
# End: $TIME=2014/03:19:20:13:45 

6. Special Ops/Post-LUT Changes 
Hi negative collimator voltage set to 1400 
Hi ABAB (CEM comparison) 

-- 

Sheral R. Wesley 
SPVR., Satellite Operations 
IBEX Mission OPS 
CYGNUS Mission Planning 
(304) 279-6678 
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