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MIDN 1/C Ben OrloffMIDN 1/C Ben OrloffMIDN 1/C Eric Kinzbrunner MIDN 1/C Eric Kinzbrunner
MIDN 1/C JoEllen RoseMIDN 1/C JoEllen RoseMidn 1/C Steven SchwarzerMidn 1/C Steven Schwarzer
2223 Feb 200523 Feb 2005 RAFT Critical Design Review
Assumption: Launch NET February 2006Assumption: Launch NET February 2006
RAFT KickoffRAFT Kickoff Apr 04 Apr 04 RAFT USNA SRRRAFT USNA SRR Sep 04 Sep 04 RAFT PDRRAFT PDR 19 Nov 0419 Nov 04 RAFT Phase 0/1 SafetyRAFT Phase 0/1 Safety 16 Dec 0416 Dec 04 RAFT Phase 2 SafetyRAFT Phase 2 Safety 10 Feb 0510 Feb 05 RAFT CDRRAFT CDR 23 Feb 0523 Feb 05 RAFT Flight Unit TestingRAFT Flight Unit Testing May 05 May 05 RAFT Phase 3 SafetyRAFT Phase 3 Safety Aug 05 Aug 05 RAFT Delivery/InstallRAFT Delivery/Install Oct 05 Oct 05 RAFT Flight (STS-116)RAFT Flight (STS-116) 09 Feb 06 09 Feb 06
Key Milestones: ScheduleKey Milestones: Schedule
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So Many CUBEsatsSo Many CUBEsats30 to 50 in Construction30 to 50 in Construction
AIAA/USUSmall Sat Conference
30% of papers were for PICO, NANO and CUBEsats
All smaller than 10 cm
How to Track them???
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Mission StatementMission Statement
To provide the Navy Space Surveillance (NSSS) radar fence To provide the Navy Space Surveillance (NSSS) radar fence with a with a means to determine the boundsmeans to determine the bounds of a constellation of of a constellation of PicoSats otherwise undetectable by the radar fencePicoSats otherwise undetectable by the radar fence
To enable NSSS to independently To enable NSSS to independently calibrate their transmit and calibrate their transmit and
receive beamsreceive beams using signals from RAFT. using signals from RAFT.
This must be accomplished with This must be accomplished with two PicoSatstwo PicoSats, one that will , one that will actively transmit and receive, and one with a passively actively transmit and receive, and one with a passively augmented radar cross-section.augmented radar cross-section.
Additionally, RAFT will provide experimental Additionally, RAFT will provide experimental communications communications transponderstransponders for the Navy Military Affiliate Radio System, the for the Navy Military Affiliate Radio System, the United States Naval Academy’s Yard Patrol crafts, and the United States Naval Academy’s Yard Patrol crafts, and the Amateur Satellite Service.Amateur Satellite Service.
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NSSS Radar FenceNSSS Radar Fence
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NOTE: Top Cover and Latchtrain Cover not shown in this view
No separation until after both picosats clear launcher
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ITEM QTY DESCRIPTION
5 1 DOOR
PIC OSAT
PUSHER
MAINSPRING
PRELOAD BLOCK
24
2 1
13
1 2
PARTS LIST
1
2
45
8
6
9
3
6
8
7
9 NEA DEVICE
BAC K COVER
LATCH
LATCHROD
1
1
1
1
* FRONT PICOSAT NOT SHOWN BUT IS IDENTIC AL TO REAR PICOSAT AND REPRESENTED WITH HIDDEN LINES
F
F
F
F
F7
ITEM QTY DESCRIPTION
5 1 DOOR
PIC OSAT
PUSHER
MAINSPRING
PRELOAD BLOCK
24
2 1
13
1 2
PARTS LIST
1
2
45
8
6
9
3
6
8
7
9 NEA DEVICE
BAC K COVER
LATCH
LATCHROD
1
1
1
1
* FRONT PICOSAT NOT SHOWN BUT IS IDENTIC AL TO REAR PICOSAT AND REPRESENTED WITH HIDDEN LINES
F
F
F
F
F7
For SSPL4410 with MEPSI:• PICOSAT mass m = 1.6 kg = 3.5 lbs• Preload > { 24 g x 3.5 lbs = 84 lbs } • F = 125 lb max preload + 24 g x 3.5 lb 210 lbs• 24 g calculated in SVP
For SSPL5510 with RAFT:• PICOSAT mass m = 7 kg = 15.4 lbs• Preload > { 24 g x 15.4 lbs = 370 lbs }• F = 500 lb max preload + 24 g x 15.4 lb 870 lbs
SSPL4410 LAUNCHER: Preload and SSPL4410 LAUNCHER: Preload and Launch LoadsLaunch Loads
credit:
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Side Panel Buckling AnalysisSide Panel Buckling Analysis
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Structure Displacements Structure Displacements
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Depressurization RateDepressurization Rate
.040 hole
Gives 2:1 margin for
depressurization
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Battery BoxBattery Box
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Custom Side Panel Custom Side Panel for Antenna Crank and GSE Connectorfor Antenna Crank and GSE Connector
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Mass Budget (kg)Mass Budget (kg)RAFT1 MARScom
Component Mass (kg) Comments Component Mass (kg) CommentsSpool w/ HF Antenna 0.0664 Actual Spool w/ HF Antenna 0.0664 ActualVHF Antenna 0.0046 Estimate VHF FM RCVR 0.094 EstimateUHF Antenna 0.0046 Estimate VHF AM RCVR 0.094 EstimatePSK-10 Board 0.1215 Includes Interface SSB Exciter 0.1 EstimateTNC Board 0.1409 Actual 1W Linear PA 0.04 EstimateInterface Board 0 Estimated in PSK-10 Splitter 0.04 EstimateTransmitter Board 0.0941 Actual Decoder 0.04 EstimateReceiver Board 0.083 Actual Batteries 0.168 EstimateBattery Boxes (2) 0.0406 Actual Ant/Spring combo 0.3 EstimateAA Batteries (11) 0.2607 Actual 20% Reserve 0.1752 EstimateB1 Panel 0.189 Actual B1 Panel 0.189 ActualB2 Panel 0.189 Actual B2 Panel 0.189 ActualTransmitter Panel 0.155 Actual Transmitter Panel 0.155 ActualReceiver Panel 0.146 Actual Receiver Panel 0.146 ActualBottom Panel 0.121 Actual Bottom Panel 0.121 ActualTop Panel 0.121 Actual Top Panel 0.121 ActualPCSat Solar Panels (5) 0.3255 Actual PCSat Solar Panels (5) 0.3255 ActualTOTAL 2.0629 Total 2.2977Max Allowed 4 Max Allowed 3
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Each panel one pigtail
All plug into Interface Board on the PSK
panel
RAFT1 Panels and Connectors
New @ CDR
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Interface BoardInterface Board
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EPS and Solar Power EPS and Solar Power BudgetBudget
Computing average solar power for a cube satellite taking weighted average of all 26 possible orientations.
This analysis is for an ISS orbit with a maximum eclipse of 39% with a 25% efficient solar cell.
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Solar Power BudgetSolar Power Budget
Conclusion: The PCsat panels per side of the satellite and a 39% eclipse time, an average available bus load of 0.96 watts will be available to the spacecraft.
SCef f =Solar Cell Efficiency
Id=Elements of Inherent Degradation
a=Sun Angle
n=number of exposed cells
A=area of one cell
t=exposure multiple
ttotal=total number of exposures
Td=Time in Daylight
Te=Time in EclipseXd=Daylight path efficiency
SCef f (%) 25 25 25
Id 0.77 0.77 0.77
SolarConstant 1367 1367 1367
PBOL (W/m2) 263.15 263.15 263.15
a (deg) 90 45 33
P (W/m2) 263.15 186.07 143.32n 4 8 12
A (m2) 0.0028 0.0028 0.0028
P total (W) 2.95 4.17 4.82
t 6 12 8
ttotal 26 26 26
x 1/4 1/2 1/3Pav g (W) 0.6801 1.9237 1.4817
P totalav g (W) 2.08
Td 0.61
Te 0.39
Xe 0.65
Xd 0.85
L (W) 0.96
Xe=Eclipse path efficiency
L=BusLoad
PBOL=SCef f *Id*SolarConstant
P=PBOL*sin(a)
L=(P totalav g*Xe*Xd*Td)/(Te*Xd+Td*Xe)
P totalav g=Pav g1+Pavg2+Pav g3
P total=P*n*A
x=t/ttotal
Pav g=P total*x
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RAFT1 Required Power RAFT1 Required Power BudgetBudget
Current (mA) Normal Avrg (mA) PSK-31 Avrg (mA) STBY Avrg (mA)VHF FM TX 500.00 2% 10.00 10% 50.00 1% 5.00VHF FM RX 30.00 100% 30.00 100% 30.00 100% 30.00
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MARScom Required MARScom Required Power BudgetPower Budget
Current (mA) Normal Current (mA) YPSATCOM Current (mA)VHF FM RX 30.00 100% 30.00 100% 30.00UHF AM RX 40.00 0% 0.00 100% 30.00SSB XMTR 200.00 8.34% 4.17 8.34% 4.17
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Radiation Hazard = NoneRadiation Hazard = None
Deployed and Active
11 V/m
Pre-Separation 0.11 V/m
Antennas Compressed, Shorted, Shielded and Sep-SW OFF
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Material StatusMaterial Status Material On Hand: Material On Hand:
• All flight ReceiversAll flight Receivers• All flight TransmittersAll flight Transmitters• All flight TNC'sAll flight TNC's• All Electronic Components from stockAll Electronic Components from stock• All Connectors All Connectors • All wire and cables All wire and cables
On Order (delivery any day now): On Order (delivery any day now): • All Solar Panels All Solar Panels • All Nicad Cells All Nicad Cells
To be Ordered: To be Ordered: • Flight TNC ROMS (after engineering model testing) Flight TNC ROMS (after engineering model testing) • Flight Interface PCBFlight Interface PCB
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Material Status (cont.)Material Status (cont.)
To Be Manufactured: To Be Manufactured: • 2 top panels 2 top panels • 2 Bottom panels 2 Bottom panels • 2 B1 panels 2 B1 panels • 2 B2 panels 2 B2 panels • 2 RX panels 2 RX panels • 2 TX panels 2 TX panels • 4 Ant PCB and spring assemblies 4 Ant PCB and spring assemblies • 2 sets HF antenna boards 2 sets HF antenna boards • 2 HF flight antenna spool assemblies 2 HF flight antenna spool assemblies
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Fracture Control Plan Fracture Control Plan Captive & RedundantCaptive & Redundant Fastener integrity Fastener integrity Captive & RedundantCaptive & Redundant Structural model of RAFTStructural model of RAFT Ideas model, Ideas model,
Must have circuit interrupters in ground legMust have circuit interrupters in ground leg Inner surface and terminals coated with insulating materialsInner surface and terminals coated with insulating materials Physically constrained from movement and allowed to ventPhysically constrained from movement and allowed to vent Absorbent materials used to fill void spacesAbsorbent materials used to fill void spaces Battery storage temperature limits are -30°C to +50°CBattery storage temperature limits are -30°C to +50°C Prevent short circuits and operate below MFR’s maxPrevent short circuits and operate below MFR’s max Thermal analysis under load and no-loadThermal analysis under load and no-load Battery must meet vibration and shock resistance stdsBattery must meet vibration and shock resistance stds Must survive single failure without inducing hazardsMust survive single failure without inducing hazards Match cells for voltage, capacity, and charge retentionMatch cells for voltage, capacity, and charge retention
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Questions?Questions?
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Backup SlidesBackup Slides
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-60 °C Battery Tests-60 °C Battery Tests
Triple walled chamber
Sealed for condensation
Adding
Dry Ice
30 Hour test @ -60C
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-60 °C Battery Test: -60 °C Battery Test: Thermal ConditionsThermal Conditions
Thermal Battery Test
-100
-80
-60
-40
-20
0
20
40
0 5 10 15 20 25 30 35 40 45 50
Time (hrs)
Tem
per
atu
re (
°C)
Batteries
Can
Ice
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Post -60 °C Charge Temp Post -60 °C Charge Temp in Vacuumin Vacuum
0
5
10
15
20
25
30
35
0.00 5.00 10.00 15.00 20.00 25.00
Time (hr)
Te
mp
°C
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Post Cold Test Discharge Post Cold Test Discharge CurrentCurrent
0.00
0.05
0.10
0.15
0.20
0.25
0.30
0.35
0.40
0.45
0 50 100 150 200
Time (min)
Cu
rre
nt
(A)
852 mA-H
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Dead Battery Charge Dead Battery Charge EfficiencyEfficiency