IBEX_2018_035_o0396a_v001.scr,
and I approve.
The only constraint violations in
IBEX_2018_035_o0396a_v001_.ccvr
are from the removal of the
ACT_SetSpinPulseProtectEnable Enable
commands (2); the violations are expected.
The PL commands in the v001 ATS match those in the v002 STF,
IBEX_2018_035_o0396a_v002.stf.
Ascending and descending command sequences are consistent with each other, 15 Re ascending, the apogee maneuver time and 15 Re descending as determined from the OEF,
IBEX_2018_035_o0396a_v001.oef,
and as verified with ibex_orbit.
There is one star tracker outage. The outage starts 7+ hours after apogee and runs for almost 3 days. Some despinning may be required due to this outage.
There is one moon in Lo FOV session in arc B. The ATS start time is about 3 hours before that in the OEF and the ATS end time is about 6 hours before that in the OEF. These differences are not unusual.
The ground station command sequences are correct and the timing and bit rates match those in the contacts file,
IBEX_Orbit396_Contacts.txt,
for all contacts (3).
We are doing battery cell balancing this orbit and the balancing commands are correct and offset by enough time from other commands.
The inertial maneuver at perigee of orbit 395 left us pointing in safe directions for the orbit 396 arc A ascending and descending sequences:
ibex_rotate -o -u 0.667031,-0.679725,-0.305031 -w ibex-sun -t 2018/02:04:14:30:55
Quaternion +0.000000,+0.000000,+0.000000,+0.000000
points axis +1.000000,+0.000000,+0.000000
towards ECI +0.667031,-0.679725,-0.305031
which is R.A. +314.460 Decl. -17.760
missing R.A. +317.970 Decl. -16.210 (ibex-sun)
error is R.A. +3.510 Decl. +1.550
for a total 3.697 deg
ibex_rotate -o -u 0.667031,-0.679725,-0.305031 -w ibex-sun -t 2018/02:07:20:48:21
Quaternion +0.000000,+0.000000,+0.000000,+0.000000
points axis +1.000000,+0.000000,+0.000000
towards ECI +0.667031,-0.679725,-0.305031
which is R.A. +314.460 Decl. -17.760
missing R.A. +321.277 Decl. -15.198 (ibex-sun)
error is R.A. +6.817 Decl. +2.562
for a total 7.020 deg
The inertial precession 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 0.773007,-0.578178,-0.261094 -w ibex-sun -t 2018/02:07:22:31:29
Quaternion +0.000000,+0.000000,+0.000000,+0.000000
points axis +1.000000,+0.000000,+0.000000
towards ECI +0.773007,-0.578178,-0.261094
which is R.A. +323.205 Decl. -15.135
missing R.A. +321.347 Decl. -15.175 (ibex-sun)
error is R.A. +1.858 Decl. +0.040
for a total 1.794 deg
ibex_rotate -o -u 0.773007,-0.578178,-0.261094 -w ibex-sun -t 2018/02:08:00:06:35
Quaternion +0.000000,+0.000000,+0.000000,+0.000000
points axis +1.000000,+0.000000,+0.000000
towards ECI +0.773007,-0.578178,-0.261094
which is R.A. +323.205 Decl. -15.135
missing R.A. +321.412 Decl. -15.153 (ibex-sun)
error is R.A. +1.793 Decl. +0.018
for a total 1.731 deg
ibex_rotate -o -u 0.773007,-0.578178,-0.261094 -w ibex-sun -t 2018/02:12:12:06:43
Quaternion +0.000000,+0.000000,+0.000000,+0.000000
points axis +1.000000,+0.000000,+0.000000
towards ECI +0.773007,-0.578178,-0.261094
which is R.A. +323.205 Decl. -15.135
missing R.A. +325.769 Decl. -13.678 (ibex-sun)
error is R.A. +2.564 Decl. +1.457
for a total 2.879 deg
The inertial maneuver at perigee leaves us pointing in safe directions at the time of the maneuver and at orbit 397 apogee:
ibex_rotate -o -u 0.775715,-0.575173,-0.259696 -w ibex-sun -t 2018/02:12:14:16:56
Quaternion +0.000000,+0.000000,+0.000000,+0.000000
points axis +1.000000,+0.000000,+0.000000
towards ECI +0.775715,-0.575173,-0.259696
which is R.A. +323.444 Decl. -15.052
missing R.A. +325.859 Decl. -13.650 (ibex-sun)
error is R.A. +2.415 Decl. +1.402
for a total 2.727 deg
ibex_rotate -o -u 0.775715,-0.575173,-0.259696 -w ibex-sun -t 2018-02-17T10:06:55.182Z
Quaternion +0.000000,+0.000000,+0.000000,+0.000000
points axis +1.000000,+0.000000,+0.000000
towards ECI +0.775715,-0.575173,-0.259696
which is R.A. +323.444 Decl. -15.052
missing R.A. +330.668 Decl. -12.004 (ibex-sun)
error is R.A. +7.224 Decl. +3.048
for a total 7.656 deg
No Lo O-mode.
There is no overlap with orbit 395 commands by manual inspection or by checking at
http://ibex.unh.edu/cgi-bin/ats.cgi.
Command Approval Checklist is attached.
Ken
Guys,
Here are the planning files and ATS for Orbit# 396.
Please respond to this email with comments and approvals
Approvals are required before 24 Jan 18 @1800 UTC
Note the following:
1. Battery Balancing at Perigee
Orbit# 396 Battery Balancing at Perigee
# 2018-02-13T00:05:58.104Z,Perigee,orbit:396
SetLongEclipseFlag TRUE $TIME=2018/02:13:01:00:00
SetLongEclipseFlag FALSE $TIME=2018/02:13:02:30:00
2. Moon in Lo FOV
Orbit# 396 APOGEE: Moon in LO FOV Commands
# 2018-02-10T10:05:05.989Z,MoonInLoFovStart,orbit:396
# 2018-02-11T03:20:53.145Z,MoonInLoFovStop,orbit:396
3. Command Load Constraint Violation Report
IBEX_2018_035_o0396a_v001.scr
==========================
HARD CONSTRAINT VIOLATIONS
==========================
NO VIOLATIONS.
==========================
SOFT CONSTRAINT VIOLATIONS
==========================
IBX-CLC-016: No command to enable spin pulse protection was found after
transition to science mode at 2018/02/04 13:01:47 UTC
IBX-CLC-016: No command to enable spin pulse protection was found after
transition to science mode at 2018/02/07 23:36:35 UTC
==============
OTHER MESSAGES
==============
NO MESSAGES.
Sheral R. Wesley
Sr Systems Engineer
IBEX , OCO2 Mission OPS
CRS/CYGNUS Mission Planning
Bldg. 2 Room 1337
Office (703) 406-5641
Cell (202) 236-0802