RAFTRAFTRadar Fence TransponderRadar Fence TransponderPreliminary Design Review Preliminary Design Review

19 Nov0419 Nov04MIDN 1/C Eric Kinzbrunner MIDN 1/C Eric Kinzbrunner MIDN 1/C Ben OrloffMIDN 1/C Ben Orloff

MIDN 1/C JoEllen RoseMIDN 1/C JoEllen Rose

OLAW RAFT TeamOLAW RAFT Team Chief Of Integration & Ops: Capt Yvonne Fedee Chief Of Integration & Ops: Capt Yvonne Fedee Payload Manager: Mr Perry BallardPayload Manager: Mr Perry Ballard Back Up Payload Manager: Lt Reann CaldwellBack Up Payload Manager: Lt Reann Caldwell Payload Integration Engineer(PIE): Mr Carson TaylorPayload Integration Engineer(PIE): Mr Carson Taylor Launcher & Back Up PIE: Mr Scott RitterhouseLauncher & Back Up PIE: Mr Scott Ritterhouse Safety Engineer (SE): Ms. Theresa ShafferSafety Engineer (SE): Ms. Theresa Shaffer Launcher & Back up SE: Mr Darren BromwellLauncher & Back up SE: Mr Darren Bromwell

Assumption: Launch NET December 2005Assumption: Launch NET December 2005

RAFT KickoffRAFT Kickoff Apr 04Apr 04 RAFT USNA SRRRAFT USNA SRR Sep 04Sep 04 RAFT PDRRAFT PDR 19 Nov 04 19 Nov 04 Launcher CDR Launcher CDR Nov 04Nov 04 RAFT Phase 0/1 SafetyRAFT Phase 0/1 Safety Dec 04Dec 04 RAFT CDRRAFT CDR Feb 05Feb 05 RAFT Phase 2 SafetyRAFT Phase 2 Safety Feb 05Feb 05 RAFT Flight Unit DeliveryRAFT Flight Unit Delivery May 05May 05 RAFT Phase 3 SafetyRAFT Phase 3 Safety Aug 05Aug 05 RAFT Delivery/InstallRAFT Delivery/Install Oct 05Oct 05 RAFT Flight (STS-116)RAFT Flight (STS-116) NETNET Feb 06Feb 06

Key Milestones: Tentative ScheduleKey Milestones: Tentative Schedule

Shuttle Manifest: 2004 - Shuttle Manifest: 2004 - 20082008

BackgroundBackground30 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???

Mission StatementMission StatementThe mission of RAFT is:The mission of RAFT is: To provide the Navy Space Surveillance (NSSS) To provide the Navy Space Surveillance (NSSS)

radar fence with a radar fence with a means to determine the boundsmeans to determine the bounds of a constellation of PicoSats otherwise of a constellation of PicoSats otherwise undetectable by the radar fence undetectable by the radar fence

To enable NSSS to independently To enable NSSS to independently calibrate their calibrate their transmit and receive beamstransmit and receive beams using signals from using signals from RAFT.RAFT.

This must be accomplished with This must be accomplished with two PicoSatstwo PicoSats, one , one that will actively transmit and receive, and one that will actively transmit and receive, and one with a passively augmented radar cross-section.with a passively augmented radar cross-section.

Additionally, RAFT will provide experimental Additionally, RAFT will provide experimental communications transponderscommunications transponders for the Navy Military for the Navy Military Affiliate Radio System, the United States Naval Affiliate Radio System, the United States Naval Academy’s Yard Patrol crafts, and the Amateur Academy’s Yard Patrol crafts, and the Amateur Satellite Service.Satellite Service.

RAFT1 Mission RAFT1 Mission ArchitectureArchitecture

NSSS Radar FenceNSSS Radar Fence

NSSS Radar FenceNSSS Radar FenceTransmit Power: 768 kW of power from Lake Kickapoo, TXAntenna Gain: About 30dBTransmission Sites: Lake Kickapoo, Texas

Jordan Lake, AlabamaGila River, Arizona

Receiving Sites: San Diego, CaliforniaElephant Butte, New MexicoRed River, ArkansasSilver Lake, MississippiHawkinsville, GeorgiaTattnall, Georgia

RAFT1 and MARScomRAFT1 and MARScom

PSK-31 Audio PSK-31 Audio Spectrogram of Satellite Spectrogram of Satellite

DopplerDoppler

Example audio Spectrogram

Expected from one-way Doppler

Fence interaction about 1-3 secs

NSSS / Moon InterceptNSSS / Moon Intercept

PassPass GeometryGeometry

Raft1 Block DiagramRaft1 Block Diagram

RAFT1 RAFT1 Internal Internal DiagramDiagram

TopTopViewView

RAFT RAFT Internal Internal DiagramDiagram

CornerCornerDetailDetail

Top PanelTop Panel

VHF Antenna holes

HF whip hole

Antenna pockets for other satellite

Side PanelSide Panel

Side Panel CloseSide Panel Close

Depressurization RateDepressurization Rate

.040 hole

Gives 2:1 margin for

depresurization

PRELIMINARY

MARScom Mission MARScom Mission Architecture Architecture

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 during periods of emergency or while conducting drills….

Assist in effecting normal communications under emergency conditions.

Handle morale and quasi-official message and voice communications traffic for

members of the Armed Forces and authorized U.S. Government civilian personnel

Provide, during daily routine operations, a method of exchanging MARSGRAMS and

… contacts between service personnel and their families back home.

Yard Patrol Craft Yard Patrol Craft ApplicationApplication

MARScom Block DiagramMARScom Block Diagram

RAFTRAFTDeploymentDeployment

Velocity of CM:

1.00 m/s

Velocity of RAFT:

0.57 m/s

Velocity of MARScom:

1.57 m/s

Air Track Separation TestAir Track Separation Test

SSPL4410 LAUNCHER: Main SSPL4410 LAUNCHER: Main ComponentsComponents

MATERIALS: All aluminum 6061-T6 except for electronics and CRES parts: fasteners, springs, latchrod, NEA device internal hardware, hingepin

NEA device:fuse wireactuated release mechanism

PICOSAT 1

PICOSAT 2

preload block

Pusherspring

door

hingepin

latch

latchrod

firing circuit (FC)

latchwall

hingewall

GSE connector

Orbiter connector

bottom cover(attaches to Orbiter via

APC adaptor – not shown)

NOTE: Top Cover and Latchtrain Cover not shown in this view

door frame

credit:

Pusher plate stops here

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

credit:

ITEM QTY DESCRIPTION

5 1 DOOR

PICOSAT

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

BACK COVER

LATCH

LATCHROD

1

1

1

1

* FRONT PICOSAT NOT SHOWN BUT IS IDENTICAL TO REAR PICOSAT AND REPRESENTED WITH HIDDEN LINES

F

F

F

F

F7

ITEM QTY DESCRIPTION

5 1 DOOR

PICOSAT

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

BACK COVER

LATCH

LATCHROD

1

1

1

1

* FRONT PICOSAT NOT SHOWN BUT IS IDENTICAL 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:

STS-116 Configuration: RAFT as Part of STS-116 Configuration: RAFT as Part of STP-H2STP-H2

CAPE

RAFT /SSPL5510

CAPEInclined AdapterAssembly

ICU/ANDE

ICC

MEPSI /SSPL4410

1) Deployment of the ICU/ANDE from CAPE

2) Deployment of RAFT picosats from SSPL5510

NOTES:

• Non-simultaneous deployment occurs following undock from ISS, not necessarily in the order shown.

• Remaining ICC complement not shown for clarity

• MEPSI/SSPL4410 not shown

STS-116 Configuration: RAFT as Part of STS-116 Configuration: RAFT as Part of STP-H2STP-H2

CAPE

CAPE Inclined Adapter Assembly

ICU/ANDE

RAFTpicosats

SSPL5510

3) Deployment of MEPSI picosats from SSPL4410

STS-116 Configuration: RAFT as Part of STS-116 Configuration: RAFT as Part of STP-H2STP-H2

Pre- Deployment At Deployment

STP PICOSat Launcher STP PICOSat Launcher Mark IIMark II

RAFTRAFTAntennaAntennaSeparationSeparationMechanismsMechanisms

RAFT Antenna SpringsRAFT Antenna Springs

Solar Cell DesignSolar Cell Design

Unique Side Panel for Antenna Unique Side Panel for Antenna CrankCrank

AssemblyAssembly

Solar Power BudgetSolar Power Budget

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.

Solar Power BudgetSolar Power Budget

Conclusion: Using four 25% efficient solar cells 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

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% 5.00UHF FM RX 30.00 100% 30.00 100% 30.00 100% 30.00

TNC 15.00 100% 15.00 100% 15.00 100% 15.00Down Converter 50.00 0% 0.00 10% 0.05 0% 0.00

29 MHz RX 50.00 0% 0.00 10% 0.05 0% 0.0020% Reserve 9.00 9.00 9.00 9.00

Avrg (mA) 64.00 104.10 59.00

Normal Use PSK-31 STBY AvailableAvrg(mA) 64.00 104.10 59.00 114.2857

System (Volts) 8.40 8.40 8.40 8.4Avrg (Watts) 0.5376 0.87444 0.4956 0.96

MARScom Required Power MARScom Required Power BudgetBudget

Current (mA) Normal Current (mA) YPSATCOM Current (mA)VHF FM RX 30.00 100% 30.00 100% 30.00UHF AM RX 30.00 0% 0.00 100% 30.00SSB Exciter 50.00 8.34% 4.17 8.34% 4.17

1W Linear PA 100.00 8.34% 8.34 8.34% 8.34Decoder 10.00 100% 10.00 100% 10.00

20% Reserve 8.00 8.00 8.00Avrg (mA) 60.51 90.51

Normal Use YPSATCOM AvalibleAvrg (mA) 60.51 90.51 114.2857143

System (Volts) 8.40 8.40 8.4Avrg (Watts) 0.51 0.76 0.96

Power SystemPower System

Simplified Power SystemSimplified Power System

-60 °C Battery Tests-60 °C Battery Tests

Time LineTime Line

-60 °C Battery Test: Thermal -60 °C Battery Test: Thermal ConditionsConditions

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

-60 °C Battery Test: Charge -60 °C Battery Test: Charge TempTemp

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

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

Post Cold Test Battery Post Cold Test Battery ConditionCondition

(No Leakage)(No Leakage)

Battery Battery BoxBox

PCsat I-V CurvePCsat I-V CurveVoltage 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

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

Dead Battery Recovery TestDead Battery Recovery Test

Dead Battery Charge Dead Battery Charge EfficiencyEfficiency

Interface BoardInterface Board

PCB LayoutPCB Layout

217Mhz Receiver217Mhz Receiver

217Mhz Receiver PCB217Mhz Receiver PCB

1.55in

2.175in

IDEAS ModelIDEAS Model

IDEAS ModelIDEAS Model

CommunicationCommunication RAFT1 requires an IARU Request RAFT1 requires an IARU Request

FormForm• TX: 145.825 MHz, 2 Watt, 20 KHz B/W FMTX: 145.825 MHz, 2 Watt, 20 KHz B/W FM• 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 requires a DD 1494MARScom requires a DD 1494• 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

VHF EZNEC PlotVHF EZNEC Plot

VHF EZNEC PlotVHF EZNEC Plot

RAFT1 Magnetic Attitude RAFT1 Magnetic Attitude ControlControl

RAFT Lifetime EstimateRAFT Lifetime Estimate

MARScom Lifetime MARScom Lifetime EstimateEstimate

Mass Budget (kg)Mass Budget (kg)RAFT1 MARScom

Component Mass (kg) Comments Component Mass (kg) CommentsSpool w/ HF Antenna 0.0536 Estimate VHF FM RCVR 0.094 EstimateVHF Antenna 0.0046 Estimate VHF AM RCVR 0.094 EstimateUHF Antenna 0.0046 Estimate SSB Exciter 0.1 EstimatePSK-10 Board 0.1215 Includes Interface 1W Linear PA 0.04 EstimateTNC Board 0.1409 Actual Splitter 0.04 EstimateInterface Board 0 Estimated in PSK-10 Decoder 0.04 EstimateTransmitter Board 0.0941 Actual Batteries 0.168 EstimateReceiver Board 0.083 Actual Ant/Spring combo 0.3 EstimateBattery Boxes (2) 0.0406 Actual 20% Reserve 0.1752 EstimateAA Batteries (11) 0.2607 Actual 1/4" Aluminum 1.5 EstimateB1 Panel 0.138 Estimate Total 2.5512B2 Panel 0.138 Estimate Max Allowed 3Transmitter Panel 0.138 EstimateReceiver Panel 0.138 EstimateBottom Panel 0.138 EstimateTop Panel 0.138 EstimatePCSat Solar Panels (5) 0.3255 ActualTOTAL 1.9571Max Allowed 4

RAFT Integration & SafetyRAFT Integration & Safety

We will be using We will be using the “normal” the “normal” processes as best processes as best we canwe can

RAFT ScheduleRAFT ScheduleI D Task Nam e Dur at ion St ar t Finish Pr edecessor s

10 CDR 123 days? M on 8/ 30/ 04 Tue 2/ 15/ 05

11 Saf et y 1 67 days? M on 8/ 30/ 04 Tue 11/ 30/ 04

12 USNA Saf et y Pkg 24 days M on 8/ 30/ 04 Thu 9/ 30/ 04

13 STP Saf et y Pkg 11 days? Fr i 10/ 1/ 04 Fr i 10/ 15/ 0412

14 Saf et y Subm ission 31 days? M on 10/ 18/ 04M on 11/ 29/ 0413

15 Saf et y Review 1 day? Tue 11/ 30/ 04 Tue 11/ 30/ 0414

16 Saf et y 2 123 days? M on 8/ 30/ 04 Tue 2/ 15/ 05

17 Saf et y 3 209 days? M on 8/ 30/ 04 Wed 6/ 15/ 05

18 M i ssi on 22 days? M on 8/ 30/ 04 Tue 9/ 28/ 04

19 O r bit Decay 3 days? M on 8/ 30/ 04 Wed 9/ 1/ 04

20 Fr equency Allocat ion 22 days? M on 8/ 30/ 04 Tue 9/ 28/ 04

21 Separat i on and Ant enna 50 days? M on 8/ 30/ 04 Fr i 11/ 5/ 04

22 Physi cs 13 days? M on 8/ 30/ 04 Wed 9/ 15/ 04

23 Com put at ions 10 days? M on 8/ 30/ 04 Fr i 9/ 10/ 04

24 Air Table 13 days? M on 8/ 30/ 04 Wed 9/ 15/ 04

25 M echani cal 50 days? M on 8/ 30/ 04 Fr i 11/ 5/ 04

26 M ass M odels 6 days? Wed 9/ 1/ 04 Wed 9/ 8/ 04

27 Ant enna Spr ings 50 days? M on 8/ 30/ 04 Fr i 11/ 5/ 04

28 M at chi ng 8 days? M on 8/ 30/ 04 Wed 9/ 8/ 04

29 EZNEC M odel 8 days? M on 8/ 30/ 04 Wed 9/ 8/ 04

30 EPS 116 days? M on 8/ 30/ 04 Sun 2/ 6/ 05

31 Sol ar 116 days? M on 8/ 30/ 04 Sun 2/ 6/ 05

32 Design/ I D cell 70 days? M on 8/ 30/ 04 Fr i 12/ 3/ 04

33 Pr ocur e 22 days? Fr i 1/ 7/ 05 Sun 2/ 6/ 05

34 Bat t er i es 55 days? Wed 9/ 15/ 04 Tue 11/ 30/ 04

35 Ther m al Analysis 23 days? Wed 9/ 15/ 04 Fr i 10/ 15/ 04

36 Cell Select ion 33 days? Fr i 10/ 15/ 04 Tue 11/ 30/ 04

37 Regulat or 1 day? M on 8/ 30/ 04 M on 8/ 30/ 04

38 Power Budget 7 days? M on 8/ 30/ 04 Tue 9/ 7/ 04

Saf et y Revi ew

T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T F S S M T W T FAug 22, '04 Aug 29, '04 Sep 5, '04 Sep 12, '04 Sep 19, '04 Sep 26, '04 O ct 3, '04 O ct 10, '04 O ct 17, '04 O ct 24, '04 O ct 31, '04 Nov 7, '04 Nov 14, '04 Nov 21, '04 Nov 28, '04 Dec 5, '04 Dec 12, '04 Dec 19, '04 Dec 26, '04 Jan 2, '05 Jan 9, '05 Jan 16, '05 Jan 23, '05 Jan 30, '05 Feb 6, '05 Feb 13, '05 Feb 20, '05 Feb 27, '05 M ar 6, '05 M ar 13, '05 M ar 20, '05 M ar 27, '05 Apr 3, '05 Apr 10, '05 Apr 17, '05 Apr 24, '05 M ay 1, '05 M ay 8, '05 M ay 15, '05 M ay 22, '05 M ay 29, '05 Jun 5, '05 Jun 12, '05

Shuttle Safety Shuttle Safety RequirementsRequirements

Fracture Control PlanFracture Control Plan Fastener integrityFastener integrity A structural model of RAFTA structural model of RAFT Venting analysisVenting analysis Simple mechanismsSimple mechanisms Materials compatibility / OutgassingMaterials compatibility / Outgassing Conformally coated PC boardsConformally coated PC boards Wire sizing and fusingWire sizing and fusing Radiation hazardRadiation hazard Battery safety requirementsBattery safety requirements Shock and vibrationShock and vibration

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

Key Requirement Key Requirement DocumentsDocuments

Key Requirement Documents:Key Requirement Documents:• NSTS 1700.7B, Safety Policy and Requirements for NSTS 1700.7B, Safety Policy and Requirements for

Payloads Using the Space Transportation SystemPayloads Using the Space Transportation System• NSTS/ISS 18798, Interpretations of NSTS Payload Safety NSTS/ISS 18798, Interpretations of NSTS Payload Safety

RequirementsRequirements• NSTS/ISS 13830C, Payload Safety Review and Data NSTS/ISS 13830C, Payload Safety Review and Data

Submittal RequirementsSubmittal Requirements• KHB 1700.7B, Space Shuttle Payload Ground Safety KHB 1700.7B, Space Shuttle Payload Ground Safety

HandbookHandbook• NSTS 14046, Payload Verification RequirementsNSTS 14046, Payload Verification Requirements• NASA-STD-5003, Fracture Control Requirements for NASA-STD-5003, Fracture Control Requirements for

PayloadsPayloads using the Space Shuttleusing the Space Shuttle

Key Reference DocumentsKey Reference Documents Reference/Requirements Documents (not all inclusive):Reference/Requirements Documents (not all inclusive):

• JSC 26943, Guidelines for the Preparation of Payload JSC 26943, Guidelines for the Preparation of Payload Flight Safety Data Packages and Hazard ReportsFlight Safety Data Packages and Hazard Reports

• MSFC-STD-3029, Guidelines for the Selection of Metallic MSFC-STD-3029, Guidelines for the Selection of Metallic Materials for SCC ResistanceMaterials for SCC Resistance

• MSFC-HDBK-527/JSC 09604 (MAPTIS), Materials Selection MSFC-HDBK-527/JSC 09604 (MAPTIS), Materials Selection List for Space Hardware SystemsList for Space Hardware Systems

• JSC 20793, Manned Space Vehicle Battery Safety JSC 20793, Manned Space Vehicle Battery Safety HandbookHandbook

• TM 102179, Selection of Wires and Circuit Protective TM 102179, Selection of Wires and Circuit Protective Devices for STS Orbiter Vehicle Payload Electrical Devices for STS Orbiter Vehicle Payload Electrical CircuitsCircuits

RAFT ScheduleRAFT Schedule Systems Definition complete – 15 APR 2004Systems Definition complete – 15 APR 2004 Systems Requirement Baseline – 15 SEP 2004 (SRR)Systems Requirement Baseline – 15 SEP 2004 (SRR) Prelim.Design Review– 19 NOV 2004Prelim.Design Review– 19 NOV 2004 Engineering Model Available– 15 JAN 2004Engineering Model Available– 15 JAN 2004 System Design Complete – 15 FEB 2005 (CDR)System Design Complete – 15 FEB 2005 (CDR) Flight unit for Environmental testing – May 2005Flight unit for Environmental testing – May 2005 Flight Hardware for Integration/Flight – OCT 2005Flight Hardware for Integration/Flight – OCT 2005 Launch – FEB 2005Launch – FEB 2005

IDEAS Model IDEAS Model DemonstrationDemonstration

Located in Rickover Located in Rickover Computer LabsComputer Labs