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

ParkinsonSAT - USNA

ParkinsonSAT - USNAUHF 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 DocumentsODTML- 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 mount Antennas 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 frameThermal compound to satellite structureBlack anodized

ParkinsonSAT - USNA

Ideas modelConnectorsWiring harnessVibrations TestPreparation for Space:

Staking componentsConformal 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/wattEMCOR 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 Cycle Avg (mA)

H L S H L S

VHF FM TX1 500 27% 6% 2% 133 29 8

VHF FM TX2 500 27% 6% 2% 133 29 8

VHF FM RX1 30 100% 100% 100% 30 30 30

VHF FM RX2 30 100% 100% 100% 30 30 30

VHF FM RX3 30 100% 100% 100% 30 30 30

VHF FM RX4 30 100% 100% 100% 30 30 30

TNC1 40 100% 100% 100% 40 40 40

TNC2 40 100% 100% 100% 40 40 40

10% Reserve         47 26 22

Avg (mA)         513 284 238

MiDn 119 100% 0% 0% 119 0 0

ODTML 625 100% 16% 3% 625 100 20

RFI 50 100% 0% 0% 50 0 0

ADCS 500 20% 10% 5% 100 50 25

10% Reserve (payloads)

        89 15 5

Avg (mA)         1496 449 288

ParkinsonSAT – Charging Current

Isa (mA)Ie

(mA)Id (mA) Id-Ie (mA)

 

2500 250 1926 1676  

2500 500 1726 1226  

2500 750 1527 777  

2500 1000 1327 327  

2500 1250 1128 -122  

2500 1500 928 -572  

2500 1750 729 -1021  

2500 1496 931 -565 H

2500 449 1767 1318 L

2500 288 1895 1607 S

ParkinsonSAT - USNABUDGET 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 - USNAParts 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 - USNASolar Panel Acceptance Testing

Psat Solar Panel I-V Curve

0

10

20

30

40

50

60

70

80

90

0 2 4 6 8 10 12Voltage (Volts)

Cu

rren

t (m

A)

Side 1 Side 2

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

• 500uA @ 3.3V DC• Field

measurement range +/-1100uT

• Resolution as low as 0.015uT

ParkinsonSAT - USNAX Axis Calibration with Compass at 0 Degrees

y = -0.0413x + 0.528

R2 = 0.9641-3.5

-3

-2.5

-2

-1.5

-1

-0.5

0

0.5

1

0 20 40 60 80 100

Angle of Sensor

Sen

sor

X V

alu

e O

utp

ut

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

ParkinsonSAT - Rabbit Core 3000 Navigation and Control Board

ParkinsonSAT - USNA

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 Exposure2. Minimum Torque, (long string needed)3. Minimum Disturbances4. Out of Reach5. Easy Access

ParkinsonSAT-Apparatus Safety Test

P-SAT Weight- 5.9kg

String=rated at a 13.5 kgDouble 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

610

610

610

610

410

410

902

22

ParkinsonSAT - SPID

Small

Particle

Impact

Detector

ParkinsonSAT - SPID

Deployment Sequence

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

Space Communications International Educational Network Classroom Experience

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