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RAFTRAFTRadar Fence TransponderRadar Fence Transponder
Critical Design ReviewCritical Design ReviewBob Bruninga, CDR USN (ret)Bob Bruninga, CDR USN (ret)
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
3323 Feb 200523 Feb 2005 RAFT Critical Design Review
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???
4423 Feb 200523 Feb 2005 RAFT Critical Design Review
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.
6623 Feb 200523 Feb 2005 RAFT Critical Design Review
RAFT1 Mission RAFT1 Mission ArchitectureArchitecture
7723 Feb 200523 Feb 2005 RAFT Critical Design Review
MARScom Mission MARScom Mission Architecture Architecture
8823 Feb 200523 Feb 2005 RAFT Critical Design Review
Military Affiliate Radio Military Affiliate Radio SystemSystem
The Mission of the MARS system is to:
Provide auxiliary communications for military, federal and local disaster management officials
Assist in effecting communications under emergency conditions.
Handle morale and quasi-official communications traffic for members of the Armed Forces and authorized U.S. Government civilian personnel
Provide routine operations in support of MARSGRAMS and … contacts between service personnel and their families back home home.
9923 Feb 200523 Feb 2005 RAFT Critical Design Review
Yard Patrol Craft Yard Patrol Craft ApplicationApplication
Unique UHF AM Uplink and HF SSB downlink
101023 Feb 200523 Feb 2005 RAFT Critical Design Review
RAFT1 and RAFT1 and MARScomMARScom
5” Cubes
3 Antennas Each
Identical Mechanical
151523 Feb 200523 Feb 2005 RAFT Critical Design Review
RAFT Lifetime EstimateRAFT Lifetime Estimate
6.5 Months
3.8 Mo
161623 Feb 200523 Feb 2005 RAFT Critical Design Review
MARScom Lifetime MARScom Lifetime EstimateEstimate
4.9 Months
3 Mo
171723 Feb 200523 Feb 2005 RAFT Critical Design Review
RAFTRAFTDeploymentDeployment
Velocity of pair:
1.5 m/s
Velocity of RAFT:
1.19 m/s
Velocity of MARScom:
1.91 m/s
181823 Feb 200523 Feb 2005 RAFT Critical Design Review
Low Friction Track Low Friction Track Separation TestSeparation Test
202023 Feb 200523 Feb 2005 RAFT Critical Design Review
Using “IDEAS” CAD Using “IDEAS” CAD ModelingModeling
222223 Feb 200523 Feb 2005 RAFT Critical Design Review
Solar Panel Design on 5 Solar Panel Design on 5 SidesSides
COTS Silicon Cells on PCB panel
Covered with Clear Teflon Coating
1.5 Watt panel
Mechanically rugged for rain/hail/birds
PCsat Flight Heritage
232323 Feb 200523 Feb 2005 RAFT Critical Design Review
Multi-Function Top Multi-Function Top PanelPanel
VHF Antenna holes
HF whip hole
Pockets for other satellite antennas and Sep Switch
242423 Feb 200523 Feb 2005 RAFT Critical Design Review
RAFT1 RAFT1 InternInternal al DiagraDiagramm
Top Top ViewView
Ant pocket& Sep SW
252523 Feb 200523 Feb 2005 RAFT Critical Design Review
RAFT RAFT InternaInternal l
Corner Corner DetailDetail Whip antenna and
sep springs
262623 Feb 200523 Feb 2005 RAFT Critical Design Review
RAFT RAFT SEP-SEP-SwitchSwitch
Corner Corner DetailDetail
272723 Feb 200523 Feb 2005 RAFT Critical Design Review
MARS- MARS- comm comm InternInternal al
Top Top ViewView
292923 Feb 200523 Feb 2005 RAFT Critical Design Review
Side Panel DetailSide Panel Detail
Loaded Side
.25” thick
303023 Feb 200523 Feb 2005 RAFT Critical Design Review
1. NEA DEVICE ACTUATES2. LATCH ROD SLIDES FORWARD3. DOOR SWINGS OPEN AND LATCHES4. PICOSATs EJECT
1
2
3
4
Door in open, latched, landing position
SSPL4410 LAUNCHER: OperationSSPL4410 LAUNCHER: Operation
NOTE: Top Cover and Latchtrain Cover not shown in this view
No separation until after both picosats clear launcher
313123 Feb 200523 Feb 2005 RAFT Critical Design Review
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:
323223 Feb 200523 Feb 2005 RAFT Critical Design Review
Side Panel Buckling AnalysisSide Panel Buckling Analysis
333323 Feb 200523 Feb 2005 RAFT Critical Design Review
Structure Displacements Structure Displacements
343423 Feb 200523 Feb 2005 RAFT Critical Design Review
Depressurization RateDepressurization Rate
.040 hole
Gives 2:1 margin for
depressurization
363623 Feb 200523 Feb 2005 RAFT Critical Design Review
Custom Side Panel Custom Side Panel for Antenna Crank and GSE Connectorfor Antenna Crank and GSE Connector
373723 Feb 200523 Feb 2005 RAFT Critical Design Review
RAFTRAFTAntennaAntennaSeparationSeparationMechanismsMechanisms
414123 Feb 200523 Feb 2005 RAFT Critical Design Review
Separation VelocitiesSeparation Velocities
Initial Energy Final Energy
i fSpring Potential Spring Potential Kinetic Energy HFWork
0.720separationmv s
1
1
41.5 0.720 1.91
7
31.5 0.720 1.19
7
RAFTMARScom launch separation
total
MARScomRAFT launch separation
total
m kgm m mv v v s s sm kg
m kgm m mv v v s s sm kg
Click here for entire documentation
424223 Feb 200523 Feb 2005 RAFT Critical Design Review
Antenna Buckling AnalysisAntenna Buckling Analysis
444423 Feb 200523 Feb 2005 RAFT Critical Design Review
Long-Wire Antenna DetailLong-Wire Antenna Detail
464623 Feb 200523 Feb 2005 RAFT Critical Design Review
RAFT1 Magnetic Attitude RAFT1 Magnetic Attitude ControlControl
474723 Feb 200523 Feb 2005 RAFT Critical Design Review
Engineering DrawingsEngineering Drawings
Top PanelTop Panel Bottom PanelBottom Panel TX Panel (TX Panel (Page 1Page 1 / / Page2Page2)) RX Panel (RX Panel (Page 1Page 1 / / Page 2Page 2)) HF HF SpoolSpool//CasingCasing
484823 Feb 200523 Feb 2005 RAFT Critical Design Review
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
494923 Feb 200523 Feb 2005 RAFT Critical Design Review
Each panel one pigtail
All plug into Interface Board on the PSK
panel
RAFT1 Panels and Connectors
New @ CDR
515123 Feb 200523 Feb 2005 RAFT Critical Design Review
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.
525223 Feb 200523 Feb 2005 RAFT Critical Design Review
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
535323 Feb 200523 Feb 2005 RAFT Critical Design Review
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
TNC 15.00 100% 15.00 100% 15.00 100% 15.0029 MHz RX 50.00 0% 0.00 10% 0.05 0% 0.00
20% Reserve 9.00 9.00 9.00 9.00Avrg (mA) 64.00 104.05 59.00
Normal Use PSK-31 STBY AvailableAvrg(mA) 64.00 104.05 59.00 114.2857
System (Volts) 8.40 8.40 8.40 8.4Avrg (Watts) 0.5376 0.87402 0.4956 0.96
Whole Orbit Average
10% Depth of Discharge
545423 Feb 200523 Feb 2005 RAFT Critical Design Review
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
TNC 30.00 100% 100% 10.0020% Reserve 12.00 100% 100% 8.00
Avrg (mA) 34.17 82.17
Normal Use YPSATCOM AvalibleAvrg (mA) 34.17 82.17 114.2857143
System (Volts) 8.40 8.40 8.4Avrg (Watts) 0.29 0.69 0.96
565623 Feb 200523 Feb 2005 RAFT Critical Design Review
Simplified Power SystemSimplified Power System
Charge in Parallel
Transmit in Series
Duty cycle 4%
100 mA
100 mA
60 mA
575723 Feb 200523 Feb 2005 RAFT Critical Design Review
Charge in Parallel
Transmit in Series
Duty cycle 4%
585823 Feb 200523 Feb 2005 RAFT Critical Design Review
Operations Safety FeaturesOperations Safety Features
All Transmitter circuits time-out to OFF
606023 Feb 200523 Feb 2005 RAFT Critical Design Review
Battery Tests NiCdBattery Tests NiCd
No mass change, no leakageWorst case 10% loss of capacityDesign Capacity has a 4 to 20 overdesign factor
616123 Feb 200523 Feb 2005 RAFT Critical Design Review
PCsat Solar Panel I-V PCsat Solar Panel I-V CurveCurve
Voltage vs. Current
0
0.01
0.02
0.03
0.04
0.05
0.06
0.07
0.08
0 1 2 3 4 5 6 7 8 9 10 11
Volts
Am
ps
Amps @ 0
Amps @ 20
Amps @ 30
Amps @ 40
Amps @ 50
Amps @ 60
discharged
Full charge Angle
626223 Feb 200523 Feb 2005 RAFT Critical Design Review
Post Cold Test Battery Post Cold Test Battery ConditionCondition
(No Leakage)(No Leakage)
636323 Feb 200523 Feb 2005 RAFT Critical Design Review
Dead Battery Recovery Dead Battery Recovery TestTest
646423 Feb 200523 Feb 2005 RAFT Critical Design Review
PCsat P-V CurvePCsat P-V CurvePower vs. Voltage
0
0.05
0.1
0.15
0.2
0.25
0.3
0.35
0.4
0.45
0.5
0 1 2 3 4 5 6 7 8 9 10 11
Volts
Wa
tts
Power @ 0
Power @ 20
Power @ 30
Power @ 40
Power @ 50
Power @ 60
discharged
Full charge
656523 Feb 200523 Feb 2005 RAFT Critical Design Review
Frequency CoordinationFrequency Coordination
RAFT1 ITU Request Form submitted.RAFT1 ITU Request Form submitted.• TX: 145.825 MHz, 2 Watt, 20 KHz B/W TX: 145.825 MHz, 2 Watt, 20 KHz B/W
FMFM• RX: 29.400-29.403 MHz PSK-31 ReceiverRX: 29.400-29.403 MHz PSK-31 Receiver• RX: 145.825 MHz AX.25 FMRX: 145.825 MHz AX.25 FM• 216.98 MHz NSSS transponder216.98 MHz NSSS transponder
MARScom DD 1494 submitted.MARScom DD 1494 submitted.• 148.375-148.975 MHz VHF cmd/user 148.375-148.975 MHz VHF cmd/user
uplinkuplink• 24-29 MHz Downlink24-29 MHz Downlink• 300 MHz UHF YP Craft Uplink Whip300 MHz UHF YP Craft Uplink Whip
Resonate at 216.98 MHzResonate at 216.98 MHz
666623 Feb 200523 Feb 2005 RAFT Critical Design Review
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
676723 Feb 200523 Feb 2005 RAFT Critical Design Review
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
Manufactured: Manufactured: • 4 Diagonal Corner Brackets 4 Diagonal Corner Brackets
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
686823 Feb 200523 Feb 2005 RAFT Critical Design Review
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
696923 Feb 200523 Feb 2005 RAFT Critical Design Review
Shuttle Safety Shuttle Safety RequirementsRequirements
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,
BucklingBuckling Venting analysisVenting analysis Done. 0.04 “Done. 0.04 “ Simple mechanismsSimple mechanisms AntennasAntennas Materials / OutgassingMaterials / Outgassing COTS, COTS, Replace ElectrolyticsReplace Electrolytics Conformal coat PC boardsConformal coat PC boards YesYes Wire sizing and fusingWire sizing and fusing #24, fuse 1 amp#24, fuse 1 amp Radiation hazardRadiation hazard Below 0.1v/mBelow 0.1v/m Battery safetyBattery safety YesYes Shock and vibrationShock and vibration YesYes
707023 Feb 200523 Feb 2005 RAFT Critical Design Review
Battery Safety Battery Safety RequirementsRequirements
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
737323 Feb 200523 Feb 2005 RAFT Critical Design Review
-60 °C Battery Tests-60 °C Battery Tests
Triple walled chamber
Sealed for condensation
Adding
Dry Ice
30 Hour test @ -60C
747423 Feb 200523 Feb 2005 RAFT Critical Design Review
-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
757523 Feb 200523 Feb 2005 RAFT Critical Design Review
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
767623 Feb 200523 Feb 2005 RAFT Critical Design Review
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