dsl$mission$conceptatlunar$orbit - astron · space engineering solution • launch into lunar orbit...
TRANSCRIPT
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DSL Mission Concept at Lunar Orbit
Jingye Yan
Na9onal Space Science Center (NSSC) Chinese Academy of Sciences (CAS)
1 2015-‐02-‐02, ASTRON, The Netherland
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Payload onboard single nano-‐sat
2 Element antenna
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Outline
• Requirements • Mission concept and preliminary design
• Summary
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Qualita9ve requirements
• RFI free/minimum – Moon shielding is beRer than mi9ga9on
• Long baseline for high resolu9on – Long distance high speed communica9on
• Dense UV coverage – Discover unknowns
• S-‐mission
4
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Quan9ta9ve requirements
• Angular resolu9on • Frequency • Spectral resolu9on • Integra9on 9me • Polariza9on
Chengdu 5
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Array design = Op9mize the UV coverage
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DSL array at Lunar orbit
7
• Linear array along the same orbit • Dish UV coverage every half orbit • Baseline’s length varies from orbit to orbit
by maneuver, Full UV coverage (Nyquist) every 10 days
• UV coverage is configurable in orbit according to parEcular scienEfic goal
• Linear array simplifies the formaEon maintenance and maneuver
• 30% of the life Eme is RFI FREE
Example array: 1 4 10 22 24 35 39 52 63 71 74 78 79 km
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Snapshot
Chengdu 8
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u-‐v-‐w filling • 3-‐D u-‐v filling a`er a full precession period (360°); • In DSL case, ~450 days is required to have a full u-‐v filling in 3-‐D(0.76°
precession per day);
6° precession per orbit is assumed for beRer demonstra9on.
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Moon blockage
Chengdu 10
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Earth-‐Moon system and RFI free
Chengdu 11
• 30% RFI free • 60% coverage (taking into
account the conjugate points) • RFI mi9ga9on (if works)
improves the coverage
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RFI free + precession
Chengdu 12
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RFI free + Moon blockage + precession
Chengdu 13
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Make denser coverage in UV plane
Advantages: ü Easy change the baseline in a linear array ü Dense and controllable coverage ü Image quality is improving orbit by orbit
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Mission concept
mother
daughter
control
Scientific data Status control
Wireless bus
communication
p Linear formation flying
p Central correlation/control
p Downlink from the mother
Ground station
daughter
daughter
daughter
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Mission concept
10-02-15 16
Baselines change from 100km to 100m within 5 days needs 15g cold gas for 12 satellites maneuver
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Satellite
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Mission Concept
18
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Target orbit analysis
10-02-15 19
Orbit al9tude: 300km Sun/Earth free: 30%
l Perfect RFI free l 1 or more strong sources will be blocked 9me to 9me, enabling diverse comparisons l Orbit is stable, no crash will be happened l Easier to avoid satellites collision
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Antenna field of view
20
31.8° 1700km
1700km 300km
Moon
Earth
Sun
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Integrated Electronic Subsystem(IES)
Chengdu 21
PowerDistributor
On-Board Computer
Mass Memory
Payload Interface
PowerSource
Attitude and Orbital
Control Sensor
Lock/unlock Controller
Thermalcontrol sensor Payload
InterSatelliteSynchronization&Communication
Transponder/Transmitter
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Communica9on, Ranging and Time Synchroniza9on
22
tΔ
1T
2t tΔ+τ 1r
1t tΔ−τ 2r
2T
ÖÕ¶ËA·¢ËÍ
ÖÕ¶ËB·¢ËÍ
ÖÕ¶ËA½ÓÊÕ
ÖÕ¶ËB½ÓÊÕ
Dual One-‐way Ranging,DOR
Ta
Tb
Ra
Rb
Ranging Precision under Current Link Situation: 2cm
Time Synchroniza9on
crrttTTD ⋅+−+−+⋅= )]()()[(21
212121 )]()()[(21
211221 rrttTTt −−−−−⋅=Δ
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Ajtude control and baseline determina9on
23
• Mother sat – 1 orbit control thruster, 12 ajtude control thrusters and 4 momentum wheels.
• Daughter cubesat – 1 bias momentum wheel and 8 ajtude control thruster.
baseline
baseline determina9on CCD camera of 0.01°angular resolu9on
x
z
y
Bias momentum wheel
1A
1B
2A
2B
3A
3B
4A
4B
Ajtude control
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Radio interferometry
Rx2
Rx/Tx Mothership
Daughter Satellite
Rx1
One main and two sub antennas is mounted on the Mothership. The angle of arrival (AOA) is measured by interferometry between antennas.
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Naviga9on
25
INS
Ground remote measure
Star tracker
Mother satellite
Absolute position infomation
Attitude infomation
Relative distance meausre
Relative angle meausre
+
+
Relate position
Daughter satellite
DS Abs position
MS Abs positon
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Power Subystem • Power subsystem component
– Solar panel – Lithium Ion baReries – power management and distribu9on system
solar panel
power management
Lithium Ion batteries
Powerdistribution output
The block diagram of power subsystem
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Down link requirement
Assump9on: correlate 30MHz bandwidth at the same 9me (not possible for ISL)
• 13.2Mbps • 6.6Mbps (far side observa9on, near side download) • High gain antenna is mandatory
Chengdu 27
0
0
2
1 rfi-free= :
( )2
_( )
m
n ls
f f f
Tcff L
p Wdata rate Tf
τ ηπ
τ
=
⋅= ∑
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TT&C Solu9on
TT&C
Transponder
TC
TM
USO
Crosslink(ISL) subsystem
PA
DUP LGA1
LGA2
BASE
SW
OBDH
PD
HGA
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In orbit calibra9on • Rela9ve amplitude calibra9on by cosmic background
radia9on • Rela9ve amplitude and phase calibra9on by calibra9on signal
from Mother • Absolute amplitude calibra9on by matched load and cosmic
background • Mothership is difficult to be used as a part of the array
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High speed downlink (op9onal) Phased array antenna– no moving parts Reflector antenna-‐ light and easier
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Space engineering solution
• Launch into lunar orbit by LM-2D or Vega plus an upper stage Launch
• CCSDS Proximity-1 • SOIS Wireless bus
• Dual One-way Ranging,DOR Relative distance
• Dual time comparison Time synchronization
• Relative distance • Relative spatial angle Relative positioning
• Star tracker Attitude measurement
• Space-borne radio synthetic aperture radiometer with 12 nano-satellites Payload
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Mission: • Orbit: 300 km • Number of satellites: 13 (1 mother + 12 daughters) • Mass: 300kg
Mother: 180kg Daughters: 10kg*12
• Power: 15W*12 + 1200W • Downlink rate: <20Mbps (onboard correlaEon);
>100 Mbps (raw data, HGA) • Life Eme: 3 years
Payload • Frequency range: 0.3 ÷ 30 MHz • PolarizaEon: Full-‐pol (circular pol) • Antenna: Cross dipole, 2.5 m each sEck • Baseline: 100 m to 100 km • Angular resoluEon: 6’@ 1 MHz, 12”@30 MHz • VisibiliEes: ≈ 54K (half orbit), 59M (20 days)
Preliminary specificaEons
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Mass and Power consump9on • Mother satellite mass and power consump9on
Subsystem Subsystem Mass(kg)
Subsystem Power(W)
ADCS 3.87 6.6 Power 40.00 0.0 Propulsion 65.00 1100.0 Structure 50.00 0.0 Thermal 6.00 8.0 Communications 7.86 97.0 Payload 4.00 25.0 Data Handling 1.40 9.0 Total 178.13 1229.6
The mass of mother
satellite is 178.13kg, and
power is 1229.6W.
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Mass and Power Consump9on • Daughter satellite mass and power consump9on
Subsystem Subsystem Mass(kg)
Subsystem Power(W)
ADCS 1.08 2.3 Power 1.55 0.0 Propulsion 0.60 2.0 Structure 2.00 0.0 Thermal 1.00 1.0 Communications 0.50 6.0 Payload 2.00 1.5 Data Handling 0.60 3.0 Total 9.33 15.8
The mass of daughter
satellite is 9.33kg, and
power is 15.8W.
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Summary
• High reliability observa9on with Moon’s shield • Longer baseline is available due to HGA by linear array
• Denser, univform and controllable UVW coverage
• High performance and feasible within the envelop of S-‐mission is pre-‐studied
Chengdu 35