RAFT USNA PDR2

RAFTRadar Fence TransponderPreliminary Design Review 19 Nov04: 

RAFT Radar Fence Transponder Preliminary Design Review 19 Nov04 MIDN 1/C Eric Kinzbrunner MIDN 1/C Ben Orloff MIDN 1/C JoEllen Rose

OLAW RAFT Team: 

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

Key Milestones: Tentative Schedule: 

Assumption: Launch NET December 2005 RAFT Kickoff Apr 04 RAFT USNA SRR Sep 04 RAFT PDR 19 Nov 04 Launcher CDR Nov 04 RAFT Phase 0/1 Safety Dec 04 RAFT CDR Feb 05 RAFT Phase 2 Safety Feb 05 RAFT Flight Unit Delivery May 05 RAFT Phase 3 Safety Aug 05 RAFT Delivery/Install Oct 05 RAFT Flight (STS-116) NET Feb 06 Key Milestones: Tentative Schedule

Shuttle Manifest: 2004 - 2008: 

Shuttle Manifest: 2004 - 2008

Background: 

Background 30 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 Statement: 

Mission Statement The mission of RAFT is: To provide the Navy Space Surveillance (NSSS) radar fence with a means to determine the bounds of a constellation of PicoSats otherwise undetectable by the radar fence To enable NSSS to independently calibrate their transmit and receive beams using signals from RAFT. This must be accomplished with two PicoSats, one that will actively transmit and receive, and one with a passively augmented radar cross-section. Additionally, RAFT will provide experimental communications transponders for the Navy Military Affiliate Radio System, the United States Naval Academy’s Yard Patrol crafts, and the Amateur Satellite Service.

RAFT1 Mission Architecture: 

RAFT1 Mission Architecture

NSSS Radar Fence: 

NSSS Radar Fence

NSSS Radar Fence: 

NSSS Radar Fence Transmit Power: 768 kW of power from Lake Kickapoo, TX Antenna Gain: About 30dB Transmission Sites: Lake Kickapoo, Texas Jordan Lake, Alabama Gila River, Arizona Receiving Sites: San Diego, California Elephant Butte, New Mexico Red River, Arkansas Silver Lake, Mississippi Hawkinsville, Georgia Tattnall, Georgia

RAFT1 and MARScom: 

RAFT1 and MARScom

PSK-31 Audio Spectrogram of Satellite Doppler: 

PSK-31 Audio Spectrogram of Satellite Doppler Example audio Spectrogram Expected from one-way Doppler Fence interaction about 1-3 secs

NSSS / Moon Intercept: 

NSSS / Moon Intercept

Pass Geometry: 

Pass Geometry

Raft1 Block Diagram: 

Raft1 Block Diagram

RAFT1 Internal DiagramTopView: 

RAFT1 Internal Diagram Top View

RAFT Internal DiagramCornerDetail: 

RAFT Internal Diagram Corner Detail

Top Panel: 

Top Panel VHF Antenna holes HF whip hole Antenna pockets for other satellite

Side Panel: 

Side Panel

Side Panel Close: 

Side Panel Close

Depressurization Rate: 

Depressurization Rate .040 hole Gives 2:1 margin for depresurization

Slide22: 

PRELIMINARY

MARScom Mission Architecture : 

MARScom Mission Architecture

Military Affiliate Radio System: 

Military Affiliate Radio System 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 Application: 

Yard Patrol Craft Application

MARScom Block Diagram: 

MARScom Block Diagram

RAFTDeployment: 

RAFT Deployment Velocity of CM: 1.00 m/s Velocity of RAFT: 0.57 m/s Velocity of MARScom: 1.57 m/s

Air Track Separation Test: 

Air Track Separation Test

SSPL4410 LAUNCHER: Main Components: 

SSPL4410 LAUNCHER: Main Components MATERIALS: All aluminum 6061-T6 except for electronics and CRES parts: fasteners, springs, latchrod, NEA device internal hardware, hingepin NEA device: fuse wire actuated release mechanism PICOSAT 1 PICOSAT 2 preload block Pusher spring 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:

SSPL4410 LAUNCHER: Operation: 

Pusher plate stops here 1. NEA DEVICE ACTUATES 2. LATCH ROD SLIDES FORWARD 3. DOOR SWINGS OPEN AND LATCHES 4. PICOSATs EJECT 1 2 3 4 Door in open, latched, landing position SSPL4410 LAUNCHER: Operation NOTE: Top Cover and Latchtrain Cover not shown in this view No separation until after both picosats clear launcher credit:

SSPL4410 LAUNCHER: Preload and Launch Loads: 

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 Launch Loads credit:

Slide32: 

STS-116 Configuration: RAFT as Part of STP-H2 CAPE RAFT / SSPL5510 CAPE Inclined Adapter Assembly ICU/ANDE ICC MEPSI / SSPL4410

Slide33: 

Deployment of the ICU/ANDE from CAPE 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 STP-H2 CAPE CAPE Inclined Adapter Assembly ICU/ANDE RAFT picosats SSPL5510 3) Deployment of MEPSI picosats from SSPL4410

Slide34: 

STS-116 Configuration: RAFT as Part of STP-H2 Pre- Deployment At Deployment

STP PICOSat Launcher Mark II: 

STP PICOSat Launcher Mark II

RAFTAntennaSeparationMechanisms: 

RAFT Antenna Separation Mechanisms

RAFT Antenna Springs: 

RAFT Antenna Springs

Solar Cell Design: 

Solar Cell Design

Unique Side Panel for Antenna Crank: 

Unique Side Panel for Antenna Crank

Assembly: 

Assembly

Solar Power Budget: 

Solar Power Budget

Slide42: 

Solar 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.

RAFT1 Required Power Budget: 

RAFT1 Required Power Budget

MARScom Required Power Budget: 

MARScom Required Power Budget

Power System: 

Power System

Simplified Power System: 

Simplified Power System

-60 °C Battery Tests: 

-60 °C Battery Tests

Time Line: 

Time Line

-60 °C Battery Test: Thermal Conditions: 

-60 °C Battery Test: Thermal Conditions

-60 °C Battery Test: Charge Temp: 

-60 °C Battery Test: Charge Temp

Post Cold Test Discharge Current: 

Post Cold Test Discharge Current 852 mA-H

Post Cold Test Battery Condition(No Leakage): 

Post Cold Test Battery Condition (No Leakage)

Battery Box: 

Battery Box

PCsat I-V Curve: 

PCsat I-V Curve

PCsat P-V Curve: 

PCsat P-V Curve

Dead Battery Recovery Test: 

Dead Battery Recovery Test

Dead Battery Charge Efficiency: 

Dead Battery Charge Efficiency

Interface Board: 

Interface Board

PCB Layout: 

PCB Layout

217Mhz Receiver: 

217Mhz Receiver

217Mhz Receiver PCB: 

217Mhz Receiver PCB 1.55in 2.175in

IDEAS Model: 

IDEAS Model

IDEAS Model: 

IDEAS Model

Communication: 

Communication RAFT1 requires an IARU Request Form TX: 145.825 MHz, 2 Watt, 20 KHz B/W FM RX: 29.400-29.403 MHz PSK-31 Receiver RX: 145.825 MHz AX.25 FM 216.98 MHz NSSS transponder MARScom requires a DD 1494 148.375-148.975 MHz VHF cmd/user uplink 24-29 MHz Downlink 300 MHz UHF YP Craft Uplink Whip Resonate at 216.98 MHz

VHF EZNEC Plot: 

VHF EZNEC Plot

VHF EZNEC Plot: 

VHF EZNEC Plot

RAFT1 Magnetic Attitude Control: 

RAFT1 Magnetic Attitude Control

RAFT Lifetime Estimate: 

RAFT Lifetime Estimate

MARScom Lifetime Estimate: 

MARScom Lifetime Estimate

Mass Budget (kg): 

Mass Budget (kg)

RAFT Integration & Safety: 

RAFT Integration & Safety We will be using the “normal” processes as best we can

RAFT Schedule: 

RAFT Schedule

Shuttle Safety Requirements: 

Shuttle Safety Requirements Fracture Control Plan Fastener integrity A structural model of RAFT Venting analysis Simple mechanisms Materials compatibility / Outgassing Conformally coated PC boards Wire sizing and fusing Radiation hazard Battery safety requirements Shock and vibration

Battery Safety Requirements: 

Battery Safety Requirements Must have circuit interrupters in ground leg Inner surface and terminals coated with insulating materials Physically constrained from movement and allowed to vent Absorbent materials used to fill void spaces Battery storage temperature limits are -30°C to +50°C Prevent short circuits and operate below MFR’s max Thermal analysis under load and no-load Battery must meet vibration and shock resistance stds Must survive single failure without inducing hazards Match cells for voltage, capacity, and charge retention

Key Requirement Documents: 

Key Requirement Documents Key Requirement Documents: NSTS 1700.7B, Safety Policy and Requirements for Payloads Using the Space Transportation System NSTS/ISS 18798, Interpretations of NSTS Payload Safety Requirements NSTS/ISS 13830C, Payload Safety Review and Data Submittal Requirements KHB 1700.7B, Space Shuttle Payload Ground Safety Handbook NSTS 14046, Payload Verification Requirements NASA-STD-5003, Fracture Control Requirements for Payloads using the Space Shuttle

Key Reference Documents: 

Key Reference Documents Reference/Requirements Documents (not all inclusive): JSC 26943, Guidelines for the Preparation of Payload Flight Safety Data Packages and Hazard Reports MSFC-STD-3029, Guidelines for the Selection of Metallic Materials for SCC Resistance MSFC-HDBK-527/JSC 09604 (MAPTIS), Materials Selection List for Space Hardware Systems JSC 20793, Manned Space Vehicle Battery Safety Handbook TM 102179, Selection of Wires and Circuit Protective Devices for STS Orbiter Vehicle Payload Electrical Circuits

RAFT Schedule: 

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

IDEAS Model Demonstration: 

IDEAS Model Demonstration Located in Rickover Computer Labs