Team: 1/C Campbell, 1/C Lewis, 1/C Londoño, 1/C Smythe, 1/C Mayer, 1/C Dedinger

ParkinsonSAT - USNA PRIMARY MISSION  Satellite for data exfoliation ODTML for DOD ocean buoys Remote sensor data in the Amateur Satellite Service A comms transponder in continuation of PCSat Mission  Educational transponder support for other schools and universities SECONDARY MISSION  Support the MiDN experiment Measure radiation levels in orbit using dosimeter  Support a UHF RFI mitigation receiver Locate and identify interference to Navy UHF satellites  Support SPID Small Particle Impact Detector (former LADD-C project)

ParkinsonSAT - USNA

UHF RFI Mitigation Experiment

ParkinsonSAT – Configuration Management/Documentation  P-SAT Design Paper- Campbell Requirements and Verification Document- Londoño P-SAT Frequency Request Form- Londoño Specification Document- Londoño Interface Control Documents ODTML- Okun SPID- Campbell UHF-RFI- Lindsay

ParkinsonSAT – Drawing List Drawing Number: Name: Description ASSEMBLY DRAWINGS NA-PK- SY-A - Bulkhead Assembly 4 Bulkheads Mated NA-PK-SY-A- Sidepanel Assembly 4 Panels Mated NA-PK-SY-A-Antenna mountAntennas mounted on cube NA-PK-SY-A- ODTML Assembly Box assembled  Summary of Drawings:  Assembly(4)  Side-Panel (12)  Bulkhead (8)  Antenna (2)  EPS (5)  Comms (6)  MIDN (3)  ODTML (3)  ADCS (3)  RFI (3)  Sep (2)  Propulsion (2)  Transponder (2)

ParkinsonSAT - USNA Communications Package  Dual Redundant System – System A and B  Desired - a structure to contain Receivers (2), Transmitter, TNC, and system control board. Structure is self-contained and capable of being used on missions other than ParkinsonSat (MidSTAR-2)  Progress: Developed initial concept for box structure

ParkinsonSAT - USNA Comms Transponder Box - Initial Concept

ParkinsonSAT - USNA Side 1 Receivers (2) Transmitter Interference/Control Board

ParkinsonSAT - USNA Side 2 TNC Mechanism for Securing TNC Interference connectors

ParkinsonSAT - USNA Thermal Control:  Heat Sink transfer to frame  Thermal compound to satellite structure  Black anodized

ParkinsonSAT - USNA  Ideas model  Connectors  Wiring harness  Vibrations Test  Preparation for Space:  Staking components  Conformal coating Still to do:

ParkinsonSAT–Sun Pointing Design Sides Panel Cost=$200 Top Panel Cost=$9000

 Pointing requirements are relaxed +/- 40 deg  High precision vector math not required Paquette ODTML off (4.5 W) ODTML on (18W) ParkinsonSAT-Sun Pointing Attitude Control System

ParkinsonSAT - USNA PC Sat Panel $20/watt EMCOR University Cells $500/watt

ParkinsonSAT - USNA Separation Device

ParkinsonSAT - Structure Battery Cells Internal Bulkhead Solar Panel NEA Location Payload Bay

ParkinsonSAT – Satellite Health Major System Health Telemetry Beacons

ParkinsonSAT – Telemetry Schematic

ParkinsonSAT – EPS Block Diagram

ParkinsonSAT– Load Requirements Current (mA) Duty CycleAvg (mA) HLSHLS VHF FM TX150027%6%2% VHF FM TX250027%6%2% VHF FM RX130100% 30 VHF FM RX230100% 30 VHF FM RX330100% 30 VHF FM RX430100% 30 TNC140100% 40 TNC240100% 40 10% Reserve Avg (mA) MiDn119100%0% ODTML625100%16%3% RFI50100%0% 5000 ADCS50020%10%5% % Reserve (payloads) Avg (mA)

ParkinsonSAT – Charging Current Isa (mA) Ie (mA) Id (mA)Id-Ie (mA) H L S

ParkinsonSAT - USNA BUDGET Solar Panels$8k for Emcor cells $2k for PCsat style cells Machining$5k Anodizing and Coatings$2k Flight Hardware$5k Proto/Test/Spares HW$10k Vib/TVAC at NRL$5k Travel (Prof. Bruninga)$3k Travel (Midshipmen)$4k Miscellaneous$2k Alumni Tax$3k ________________________________________ Total$50k

ParkinsonSAT - USNA Parts Procurement Kyocera Mini Solar Panels Purchased 30 of them, $24 each -> $720 3-Axis Magnetometer Purchased 8 of them, $55 a piece ->$440 High Speed Transmitters and Receivers Purchased 4 Xmitters, 6 Receivers, $220 a piece -> $2200

ParkinsonSAT - USNA Solar Panel Acceptance Testing Over 91% of the solar panels tested were within 3% of the voltage of the reference panel. 100% were within 5%.

ParkinsonSAT- Attitude Determination and Control CPU Controlled Uses solar panels and magnetometer to determine attitude Commands momentum wheels and magnetic torquing coils to maintain sun pointing attitude

ParkinsonSAT- 3-Axis Magnetometer 3.3V DC Field measurement range +/-1100uT Resolution as low as 0.015uT

ParkinsonSAT - USNA Testing indicates sensor has an accuracy of ± 5% for roll and pitch

ParkinsonSAT - Rabbit Core 3000 Navigation and Control Board

ParkinsonSAT - USNA

29.4Mhz Processor Programmed with Dynamic C 10 Channels 5V A2D 4 PWM Channels 5V-9V input up to 400mA 4 External Interrupts

ParkinsonSAT - USNA CPU will also be used for housekeeping and telemetry and control  Log experiment data  Parse telemetry into packets  Command systems on or off  Monitor health of satellite systems and experiments

ParkinsonSAT – ADCS Model  Momentum Wheel  3-axis Magnetometer  CPU Control System  Telemetry System  Command and Control Radio

ParkinsonSAT–RickSAT ADCS Requirements: 1.Sun Exposure 2.Minimum Torque, (long string needed) 3.Minimum Disturbances 4.Out of Reach 5.Easy Access

ParkinsonSAT- Apparatus Safety Test P-SAT Weight- 5.9kg String=rated at a 13.5 kg Double String= factor of 4 safety A-Frame Support- tested to 38 kg= factor of 6 safety

ParkinsonSAT –ADCS String test Simulation Quality  Typical Disturbance Torques  Gravity Gradient-2*  Solar Radiation- 6*  Aerodynamic- 3*  Magnetic- 1* for a 2 Amp-m magnetic moment Measuring String Torsion Constant  k=1.1* kg-m /sec  T=k*  Disturbance angle ( ) where string Torque is less than 1* is 90 deg String impact is minimal for Sun tracking within +/-90 degrees. Rickover

ParkinsonSAT - SPID S mall P article I mpact D etector

ParkinsonSAT - SPID Deployment Sequence

PSAT- S.C.I.E.N.C.E ISS S pace C ommunications I nternational E ducational N etwork C lassroom E xperience

PSAT- S.C.I.E.N.C.E ISS