NOZOMI Exploration Operations Challenges Japan's Mars Mission

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NOZOMI Exploration Operations Challenges ?
Japan's Mars Mission ?
18 May, 2004

• Ichiro Nakatani
• Institute of Space and Astronautical Science/JAXA

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Research Targets of Nozomi
Study on the mechanism of the direct interaction
between the solar wind and the Martian ionosphere
a wherea included 1) science of other
disciplines 2) establishment of the engineering
technology for planetary exploration
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Overview of the Project
Spacecraft Mass wet mass 540 kg
(science payload 35 kg ) propellant 280
kg Launch Vehicle M-V-3 Mission Sequence
(originally planned) launch July 3,
1998 Mars Orbit Insertion October
1999 Mission Life in Mars Orbit (originally
planned) 1 Martian year (2 Earth years) Orbit
(originally planned) periapsis 150
km apoapsis 15 Rm
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Nozomi Science Payload
Magnetic Field (MGF) 3 - axis fluxgate, lt0.1nT
accuracy Energetic Electron (ESA) 12 eV - 15 keV,
3D up to 8sec Energetic Ions (ISA) 6 eV/q - 16
keV/q, 3D up to 8sec Energetic Ion Mass (IMI) 10
eV/q - 35 keV/q, 3D up to 4sec Sweden High
Energy Particles (EIS) 30 - 350 keV for e, 30 -
1000 keV for p Thermal Ion Analyzer (TPA) 0.1 -
100 eV, drift Canada Electron Temperature
(PET) el. Temp. 500 - 10,000 K Plasma wave
(LFA) ELF/VLF wave detection UV spectra imager
(UVS) H, O, CO, CO2 Imaging, D/H ratio EUV
spectrometer (XUV) He(583) He(304) HF sounder
receiver (PWS) topside sounder and plasma
wav Visible Camera (MIC) 3 colors, 100m/pix,
1024x1024 France Dust counter (MDC) 10-10 -
10-5g at 1 km/s, 10-18 - 10-13g at 10
km/s Germany Neutral Gas mass (NMS) 1 - 60
Daltons with M / DM gt 105 USA Radio
Science USO(Df / f 10-14) USA
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Final On-orbit Configuration
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Major Events after Launch
1998. 7. 3 Launch 1998. 9.24 1st lunar
swing-by 1998.12.18 2nd lunar swing-by 1998.12.20
1st Earth swing-by
Trans-Mars Orbit Insertion
?Trouble with one of the valves
Wasted excessive propellant.
Trajectory revised (MOI 1999.10 ?
200312 ) 2002. 4.25 Loss of telemetry thermal
control (only beacon
mode possible) 4.28 Beacon mode
telemetry established by turning on/off
the X-band power amplifier
5.14 X-band beacon loss during
recovery operation 7.14 recovery of
X-band beacon 9.2-12 a series of
successful attitude/orbit control 2002.12.20 2nd
Earth swing-by 2003. 6.19 3rd Earth
swing-by 2003.Jul.- Dec. Recovery
operation 2003.12.14 Failure of MOI (Mars fly-by)
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Major Events after Launch
1998. 7. 3 Launch 1998. 9.24 1st lunar
swing-by 1998.12.18 2nd lunar swing-by 1998.12.20
1st Earth swing-by
Trans-Mars Orbit Insertion
?Trouble with one of the valves
Wasted excessive propellant.
Trajectory revised (MOI 1999.10 ?
200312 ) 2002. 4.25 Loss of telemetry thermal
control (only beacon
mode possible) 4.28 Beacon mode
telemetry established by turning on/off
the X-band power amplifier
5.14 X-band beacon loss during
recovery operation 7.14 recovery of
X-band beacon 9.2-12 a series of
successful attitude/orbit control 2002.12.20 2nd
Earth swing-by 2003. 6.19 3rd Earth
swing-by 2003.Jul.- Dec. Recovery
operation 2003.12.14 Failure of MOI (Mars fly-by)
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Valve failure at the earth
swing-by
July 3,1998
Originally Planned Orbit Sequence
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Revised Trajectory to Mars
Mars orbit insertion Dec.2003
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Major Events after Launch
1998. 7. 3 Launch 1998. 9.24 1st lunar
swing-by 1998.12.18 2nd lunar swing-by 1998.12.20
1st Earth swing-by
Trans-Mars Orbit Insertion
?Trouble with one of the valves
Wasted excessive propellant.
Trajectory revised (MOI 1999.10 ?
200312 ) 2002. 4.25 Loss of telemetry thermal
control (only beacon
mode possible) 4.28 Beacon mode
telemetry established by turning on/off
the X-band power amplifier
5.14 X-band beacon loss during
recovery operation 7.14 recovery of
X-band beacon 9.2-12 a series of
successful attitude/orbit control 2002.12.20 2nd
Earth swing-by 2003. 6.19 3rd Earth
swing-by 2003.Jul.- Dec. Recovery
operation 2003.12.14 Failure of MOI (Mars fly-by)
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Major Events after Launch
1998. 7. 3 Launch 1998. 9.24 1st lunar
swing-by 1998.12.18 2nd lunar swing-by 1998.12.20
1st Earth swing-by
Trans-Mars Orbit Insertion
?Trouble with one of the valves
Wasted excessive propellant.
Trajectory revised (MOI 1999.10 ?
200312 ) 2002. 4.25 Loss of telemetry thermal
control (only beacon
mode possible) 4.28 Beacon mode
telemetry established by turning on/off
the X-band power amplifier
5.14 X-band beacon loss during
recovery operation 7.14 recovery of
X-band beacon 9.2-12 a series of
successful attitude/orbit control 2002.12.20 2nd
Earth swing-by 2003. 6.19 3rd Earth
swing-by 2003.Jul.- Dec. Recovery
operation 2003.12.14 Failure of MOI (Mars fly-by)
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Problem with Power System -On April 25, 2002, a
problem was found with part of the communication
and attitude control system. -The most likely
cause was guessed to be high energy particles
from the sun during the strong solar flares
starting on April 21, 2002. The direct cause,
however, has not been identified. -A short mode
failure occurred in one of the circuits which
were provided power by CI-PSU. -Attitude control
function was recovered after the frozen
propellant melted in August. -The telemetry and
the main thruster never recovered after the
recovery operations in May 2002 and in July -
December 2003.
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Problem with Power System -On April 25, 2002, a
problem was found with part of the communication
and attitude control system. -The most likely
cause was guessed to be high energy particles
from the sun during the strong solar flares
starting on April 21, 2002. The direct cause,
however, has not been identified. -A short mode
failure occurred in one of the circuits which
were provided power by CI-PSU. -Attitude control
function was recovered after the frozen
propellant melted in August. -The telemetry and
the main thruster never recovered after the
recovery operations in May 2002 and in July -
December 2003.
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SOHO LASCO Image Data (02/04/21 0142 - 0618)
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Solar Proton Monitor Count Rate Data
Exceed Maximum count rate (65535/8sec) about 6
hrs. Highest count rate Nozomi is ever
experienced !
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Summary of the Problem -On April 25, 2002, a
problem was found with part of the communication
and attitude control system. -The most likely
cause was guessed to be high energy particles
from the sun during the strong sun flares
starting on April 21. The direct cause, however,
has not been identified. -A short mode failure
occurred in one of the circuits which were
provided power by CI-PSU. -Attitude control
function was recovered after the frozen
propellant melted in August. -The telemetry and
the main thruster never recovered after the
recovery operations in May 2002 and in July -
December 2003.
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Ranging
Telemetry
Block Diagram around CI-PSU
Power Supply
Command
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Beacon Mode Telemetry
Status Only beacon was available with no
telemetry information.
Autonomous Command Function onboard Nozomi -
Nozomi had "AI mode" where onboard computer
could execute command by judging the
spacecraft status. -Ground operator could
specify any HK item to be judged for
executing onboard command.
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Beacon Mode Telemetry (continued)
- Example Ground operator could arrange the
following 1) Turn off the beacon if the
temperature, T of the specified point
is higher than 5deg. C. 2) Turn off the beacon
if its temperature, T is lower than 8
deg.C. 3) If both of the above questions are
responded as "YES" by turning off the
beacon, then 5deg. lt T lt 8 deg.
has been identified - Iteration of the above
process could eventually identify any
HK item, although it took a significant amount of
time.
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Malfunctioning of a circuit after April 21 Solar
flare
020421
Nozomi trajectory relative to the Earth
Sun
Earth
Sun-Earth fixed frame
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Summary of the Problem -On April 25, 2002, a
problem was found with part of the communication
and attitude control system. -The most likely
cause was guessed to be high energy particles
from the sun during the strong sun flares
starting on April 21. The direct cause, however,
has not been identified. -A short mode failure
occurred in one of the circuits which were
provided power by CI-PSU. -A recovery operation
was conducted trying to burn out the short
circuit, but it was unsuccessful. -Two
additional Earth swing-by's were successfully
conducted. The telemetry and the main thruster
never recovered.
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night side
day side
dusk
(JST)
Nozomi orbit
Mar orbit
Nozomi Mars Fly-by Orbit
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Summary of the Nozomi Operation
- Mal function of one of the valves which
resulted in 4 year delay of the MOI
exceeding the designed life of the
spacecraft. - The problem with one of the power
systems was found immediately after the
strong solar flare. - The recovery operations
to burn out the short circuit did not go well
and MOI was not conducted. - Basic technologies
for planetary explorations have been
established. - Significant science observations
have been conducted during a very long
cruising phase.
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Imaging Earth's Plasmasphere by He(304)
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All sky map by UV and EUV spectrometer
He
H
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END