AubieSat-I Auburn University s First Student Built Satellite. Thor Wilson, Project Manager
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1 AubieSat-I Auburn University s First Student Built Satellite Thor Wilson, Project Manager
2 AubieSat-I Mission AS-I Goals To develop a student satellite building capability at Auburn University To space test a Ga-N based UV sensor developed in the Auburn University Physics Department Planned on launching on a Dnepr rocket 2
3 Management Procedure Define goals and objectives for the semester Define milestones (including reviews) Make a schedule Make a work breakdown structure (specific tasks) Monitor and control activities at bi-weekly meetings DOCUMENTATION
4 Systems Engineering Eric Grimes/Thor Wilson, Systems Engineering
5 Design Philosophy Conform to all Cal Poly specifications Simplicity/COTS parts Redundancy All components selected through trade studies 5
6 Functional Block Diagram 6
7 Mass Budget C&D H ADC Structure Comm EPS Payload Subsystem CBE CBE + 10% Initial estimate ADC C&DH COMM PAYLOAD EPS STRUCTURE Total
8 Failure Modes Analysis Code Name Description 4 Mission Failure If this error cannot be mitigated, the mission will be a failure no communications to the ground station. 3 Reduced Lifetime If this error cannot be mitigated, the mission is still a success, but further research is needed to extend mission lifetime in future missions. 2 Reduced Capability If this error cannot be mitigated, the mission is still a success, but further research is needed to provide increased capability. 1 Non-Critical If this error occurs, the primary mission could still be accomplished without additional need for redundancy.
9 Payload Justin Van Cleave, Payload
10 Purpose Effectiveness Space environment Performance over lifespan Key characteristics Responsively (325nm): ~ 0.1 A/W UV/V selectivity: ~ 10 6 Dark current ~ 0.8 na/cm 2 10
11 Communications Robert Thompson/Thor Wilson, Communications
12 Functional Block Diagram Antenna A C&DH TNC-X Digipeater VX-2R Switching Network Secondary Receiver Antenna B 12
13 Antenna 13 Center feed half-wave dipole Amateur Band frequency MHz Approximately 34 cm Made of Nitonol or Measuring tape
14 Antenna Testing Configuration of half wave dipole with best test results was angle of 100 degrees between antenna arms. Signal strength vs. Angle Signal strength (dbm) angle,.027 d, nitinol 100 angle,.027 d, nitinol 100 angle, 5mm, measuring tape Angle (degree)
15 Beacon Done through primary communications system Function Help tracking Provides secondary communications Two Modes Data beacon Short burst of data from TNC-X Morse code beacon C&DH keys VX-2R to create Morse code 15
16 Electrical Power System Michael Carroll, EPS
17 Block Diagram Solar Cells MAX1879 Battery Regulator 3.3V Reg UBP Ah Li-Ion Battery UBP Ah Li-Ion Battery MAX /4.5V Regulator 4.5V Reg MAX1709 5V DC/DC 5V Unreg 3.7V Unreg 17
18 Attitude Determination and Control Justin Van Cleave, ADC
19 Purpose of Control Provide proper orientation primarily for communication Passive magnetic control Hysteresis Dampening to help control 19
20 Orientation of Magnet After antenna testing was complete the ideal orientation of the magnet was determined
21 Attitude Determination Passive system requires no determination Use of coarse sun-sensor Based on data transmission constraints Get experience with determination 21
22 Structures & Mechanisms Zach Johnston/Neil Dougherty, Structures
23 Interior Structure Stackable Antenna deployment 1 EPS C&DH Batteries TNC-X and VX-2R Secondary receiver Antenna deployment 2 23
24 External Structure BOTTOM PLATE Support boards with 9.4 mm standoffs with hole to run 10 cm bolt through Run bolts through the top plate and boards and fasten bolt to the bottom plate. Boards are secure to these plates SIDE PLATES Four side plates with solar cells screw in to top and bottom plate Cutouts for antennas and data port Side Plate to Bottom Plate Assembly
25 Antenna Deployment Mechanism 25
26 CAD Model 26
27 Command & Data Handling Brad Dutton & William Woodall
28 Block Diagram Data Bus Comm. USART Watch Crytal MCU SPI Data Memory I 2 C I 2 C GPIO ADC ADC ADC ADC Power Relays & Antenna Release Solar Panel Voltages Critical Voltages Payload and AUX Thermistors 28
29 ATmega2561L 256kB program storage 8kB internal SRAM Two Wire SPI 2.7V, 15mW 16 channel 10 bit ADC Open source WinAVR C compiler 29
30 Satellite Modes One time launch sequence Four modes Safe mode C&DH is on and performs basic tasks, such as battery charging, checking vital housekeeping. Idle mode Only housekeeping electronics are on. C&DH is storing housekeeping information. Transmitting beacon. Normal mode Science experiment running, C&DH will be storing data from experiment. C&DH is collecting housekeeping data. Transmitting beacon. Transmit mode Retrieve and transmit stored data, beacon is off.
31 Software Design The finite state machine 31
32 32 Ground Station Software
33 Block Diagram 33
34 Hardware Transceiver ICOM 910H TNC KCP3+ Antenna 436CP30 circular polarized Yagia Rotator and control Yaesu G5500 rotator Yaesu GS-232A rotator control Extra hardware 34 LCU-3 Level Converter
35 35 Ground Station Software
36 Software Tracking software NOVA for windows Doppler shift software Ham radio deluxe Communications software UI-View 36
37 Questions
38 AubieSat-I Auburn University s First Student Built Satellite Design Review, Spring 2007
39 AUSSP: A NASA Space Grant Workforce Development Program NASA s Education mission: inspire, engage, educate and employ our youth Develop the workforce of tomorrow Attract and retain students in the STEM disciplines AUSSP: the Auburn University Student Space Program is funded by the Alabama Space Grant Consortium 39 AubieSat-I Design Review
40 The National Space Grant Student Satellite Program From Model Rockets to Mars 40 AubieSat-I Design Review
41 Essential Features Hands-on learning Teamwork Process Complements class work NASA and Aerospace link 41 AubieSat-I Design Review
42 The AUSSP Three Teams: Ballooning Small Sats Management Learning Management and Systems Engineering Engineering skills Teamwork 42 AubieSat-I Design Review
43 The CubeSat Program Jamie Droddy, Project Manager
44 The CubeSat Program Developed by Cal Poly & Stanford Creates launch opportunities for those previously unable to access space Low cost launch Standard Deployment System (P-POD) Coordination of required documents & licenses Delivery to launch facility and integration with launch vehicle Access to CubeSat Community 44 AubieSat-I Design Review
45 CubeSat Specifications 10 cm cube (100mm x 100mm x mm) 1 kg Center of mass w/in 2cm of geometric center Thermal expansion of material similar to that of P-POD Electrically dead during launch No operation until 15 minutes after launch Qualified & Accepted per Cal Poly Specifications 45 AubieSat-I Design Review
46 Amateur Radio Use FCC Licensing FCC & IARU regulations governing amateur satellite operation Capable of killing all transmission whenever requested to do so Orbital Debris Mitigation Report 46 AubieSat-I Design Review
47 AubieSat-I Our Mission
48 AubieSat-I Mission AS-I Goals To develop a student satellite building capability at Auburn University To space test a Ga-N based UV sensor developed in the Auburn University Physics Department 48 AubieSat-I Design Review
49 AubieSat-I Mission Spring 2007 Goal A functional table-top prototype of AS-1 All subsystems powered by EPS All subsystems nominally operational All subsystems properly interfaced Fully operational Ground Station 49 AubieSat-I Design Review
50 Mission Analysis Eric Grimes, Systems
51 Launch, Dnepr III Kosmotras, Baikonour Cosmodrome (Kazakhstan 63 E and 46 N) Converted RS-20 (SS-18) ICBM Delivery for final integration: April, 2008 Launch date: Summer 2008!! 51 AubieSat-I Design Review
52 Orbital Parameters Sun-synchronous, near polar Inclination: ~98 (slightly retrograde) Period: ~99 min Altitude: ~650 km (LEO) Eccentricity: ~ minute eclipse time 52 AubieSat-I Design Review
53 Systems Engineering Eric Grimes/Thor Wilson, Systems Engineering
54 Design Philosophy Conform to all Cal Poly specifications Simplicity/COTS parts Redundancy All components selected through trade studies 54 AubieSat-I Design Review
55 Functional Block Diagram 55 AubieSat-I Design Review
56 Mass Budget Subsystem CBE CBE + 10% Initial estimate ADC C&DH COMM PAYLOAD EPS STRUCTURE Total AubieSat-I Design Review
57 Failure Modes Analysis Code Name Description 4 Mission Failure If this error cannot be mitigated, the mission will be a failure no communications to the ground station. 3 Reduced Lifetime If this error cannot be mitigated, the mission is still a success, but further research is needed to extend mission lifetime in future missions. 2 Reduced Capability If this error cannot be mitigated, the mission is still a success, but further research is needed to provide increased capability. 1 Non-Critical If this error occurs, the primary mission could still be accomplished without additional need for redundancy.
58 Flight Qualification Acceptance Testing: Ensure safety of launch vehicle Qualification Testing (Functional) Maximum probability of mission success "Test as you fly, fly as you test." 58 AubieSat-I Design Review
59 Acceptance Testing Safety of launch vehicle Vibration Thermal vacuum (5 x 10-4 Torr) 59 AubieSat-I Design Review
60 Qualification Testing Maximize probability of mission success Components tested individually first 60 AubieSat-I Design Review
61 Future Include final redundancy Summer 2007 Flight qualification plans Summer 2007 Individual component qualification Summer 2007 Qualification review Fall AubieSat-I Design Review
62 Payload Justin Van Cleave, Payload
63 Overview GaN based visible blind Almost no response from visible light Key characteristics Responsivity (325nm): ~ 0.1 A/W UV/V selectivity: ~ 10 6 Dark current ~ 0.8 na/cm 2 63 AubieSat-I Design Review
64 Purpose Effectiveness Space environment Mission lifespan Future work Build circuit to measure current Design housing and lens for cell 64 AubieSat-I Design Review
65 Communications Robert Thompson/Thor Wilson, Communications
66 Functional Block Diagram 66 AubieSat-I Design Review
67 Antenna Center feed half-wave dipole Amateur Band frequency MHz Approximately 34 cm Made of Nitonol 67 AubieSat-I Design Review
68 Nitonol Super Elastic Wire Shape memory alloy Conductivity Nitinol 1.27x10 4 Copper 5.81x10 7 Rubber 1x10-13 Diameter.027 in 68 AubieSat-I Design Review
69 VX-2R FM Transceiver Power Output 2 W 6 V 1.5 A 1 W 3.7 V 1.2 A Structure (estimated) Mass 41 g Size 43 x 73 x10 mm 69 AubieSat-I Design Review
70 PicoPacket PicoPacket Z80181 Microprocessor TCM3105 Modem Mass: 63 g Volume: 8x6x1.2 cm Voltage: 7-14 V Current: ma Data Rate: 1200 baud 70 AubieSat-I Design Review
71 Beacon Function Help tracking Provides secondary communications Basic hardware CW transmitter Morse code generator Still in design phase 71 AubieSat-I Design Review
72 Link Budget Options: Link Budget Calculation: NRZ Data Rate = 1200 Baud Required Rcvr Input Power = dbm G/S Receiver Noise Figure = 3.7 db G/S Cable and connector loss = -0.1 db G/S Antenna Gain = db Not final G/S rcvr antenna gain = db AS-1 Transmitter power (W) W Free space path loss = db Polarization mismatch loss = -3 db AS-1 transmitter antenna gain = 0 db Assumptions: AS-1 Cable and connector loss = -0.1 db Demodulator Threshold (FM) = 21 db AS-1 Transmitter power (dbm) = Bit Error Rate; 1 in = 1.00E+04 BER Data rate to BW ratio = 10 Ratio Path Distance = 2500 km Operating Frequency = 436 MHz AS-1 Transmitter power (dbw) = 0.27 dbw Craft DC to RF Efficiency = 0.2 Ratio AS-1 Transmitter power (W) = Watts Demodulator Inefficiency = 3.5 db AS-1 Transmitter prime power = Watts Constants: Link Margin 3.01 db Boltzmanns constant = 1.38E-23 J/K Required transmitter power (dbm) dbm Effective temperature, K = 290 K Required transmitter power (W) Watts Required transmitter prime power = Watts Link Situation: Carrier to noise ratio (C/kT) 14.5 db IF Bandwidth = Hertz Noise power = 4.80E-17 Watts Noise power (dbm) = dbm Receiver noise level = dbm Input Carrier to Receiver = dbm Wavelength = Meters Path loss = db 72 AubieSat-I Design Review
73 Electrical Power System Michael Carroll, EPS
74 Block Diagram Solar Cells MAX1879 Battery Regulator 3.3V Reg UBP Ah Li-Ion Battery UBP Ah Li-Ion Battery MAX /4.5V Regulator 4.5V Reg MAX V Regulator 12V Reg 3.7V Unreg 74 AubieSat-I Design Review
75 Standard Orbit 75 AubieSat-I Design Review
76 COMM Orbit 76 AubieSat-I Design Review
77 Power Supply Power is supplied by solar cells on 5 faces of the satellite. Each face has two 26.8% efficiency solar cells. Each face has an open circuit voltage of 4.4V. 77 AubieSat-I Design Review
78 Energy Storage Two Lithium-Ion batteries will be used to store energy. Each battery is rated for 1.7Ah, which is roughly 18,115 Joules, under specific conditions. The open circuit voltage on the batteries is 3.7V The batteries are connected in parallel to provide peak current. 78 AubieSat-I Design Review
79 Battery Regulators Each battery will be regulated by the Maxim 1879 Li-Ion regulator. The MAX1879 was selected for it s over-voltage, undervoltage and temperature protection. Also an easy to assemble, proven circuit. 79 AubieSat-I Design Review
80 3.3V/4.5V Regulator The 3.3V and 4.5V regulated busses are provided by the MAX1705. Multiple regulators are used to provide peak current and redundancy. 3.3V is provided on LDO and 4.5V is on POUT as a by-product. 80 AubieSat-I Design Review
81 12V Regulation The 12V bus is provided by the MAX1771 The MAX1771 was selected for it s high efficiency. 81 AubieSat-I Design Review
82 Attitude Determination and Control Justin Van Cleave, ADC
83 Mission Provide proper orientation for: Battery Charging Communication Payload 83 AubieSat-I Design Review
84 Magnetic Control Passive Alnico 5 magnets Resistant Forces Gravity Gradient ~ 10-9 Nm Air Drag ~ Nm Solar Pressure ~10-10 Nm Required Torque ~ 10-6 Nm Required dipole moment ~.048 Am 2 Dipole moment of magnet =.055 Am2 84 AubieSat-I Design Review
85 Hysteresis Dampening Loop work provides dampening force. Ni/Fe/Mo Permalloy from Goodfellow 85 AubieSat-I Design Review
86 Determination Passive system requires no determination Use of course sun-sensor Based on data transmission constraints. 86 AubieSat-I Design Review
87 System Orientation 87 AubieSat-I Design Review
88 Future Work Fabrication of dampener Orbital Calculations Risk analysis 88 AubieSat-I Design Review
89 Structures & Mechanisms Zach Johnston/Neil Dougherty, Structures
90 Data Summary Mass of Structure: grams Allotted Mass Budget: 400 grams Center of Mass: x-direction.65mm y-direction 3.51mm z-direction.41mm Allowed Center of Mass Margin: 2 cm 90 AubieSat-I Design Review
91 Interior Structure
92 Design 1 92 AubieSat-I Design Review
93 Design 2 93 AubieSat-I Design Review
94 Design 3 94 AubieSat-I Design Review
95 Internal Chassis Plate 95 AubieSat-I Design Review
96 Internal Chassis 96 AubieSat-I Design Review
97 Integrated Internal Chassis 97 AubieSat-I Design Review
98 Exterior Structure
99 Tube Frame 99 AubieSat-I Design Review
100 Tube Frame 100 AubieSat-I Design Review
101 Antenna Deployment Mechanism 101 AubieSat-I Design Review
102 Anodizing Anodizing is required on the deployment rails of our satellite because of the harsh environment of space. Anodizing is an electrochemical process that thickens and toughens the naturally occurring protective oxide on the aluminum 102 AubieSat-I Design Review
103 Final CAD Model 103 AubieSat-I Design Review
104 Command & Data Handling Brad Dutton & William Woodall
105 Command and Data Handling Processing, formatting, and storing science and housekeeping data Executing ground commands Control all of the functions of the satellite 105 AubieSat-I Design Review
106 Input / Output Diagram 106 AubieSat-I Design Review
107 Block Diagram Data Bus Comm. USART Watch Crytal MCU SPI Data Memory I 2 C I 2 C GPIO ADC ADC ADC ADC Power Relays & Antenna Release Solar Panel Voltages Critical Voltages Payload and AUX Thermistors 107 AubieSat-I Design Review
108 ATmega2561L 256kB program storage 8kB internal SRAM Two Wire SPI 2.7V, 15mW 16 channel 10 bit ADC Open source WinAVR C compiler 108 AubieSat-I Design Review
109 Burr-Brown ADS7828 ADC 12 bit, 8 channel multiplexer 0.75 mw power dissipation *Thermistor Data Resolution Full Scale (Volts) ADC Resolution (bits) Resolution (mv) **Voltage Data Resolution Full Scale (Volts) ADC Resolution (bits) Resolution (mv) AubieSat-I Design Review
110 Omron G6HK-2 power relays Dual coil latching Surface mount, low magnetic interference 1A carry current 3ms set time, 5V 110 AubieSat-I Design Review
111 C&DH properties C&DH Properties Summary V1.0 Mass 60.7 grams Power Consumption 68.6 mw maximum Tallest Component 5 mm 3V power relay 111 AubieSat-I Design Review
112 Direct Control of Critical Relays Command and Data Handling PCB Power PCB Direct Control LIne Critical Relay Micrcontroller Serial Bus Input/ Output Expander 112 AubieSat-I Design Review
113 Redundant Critical Relays 113 AubieSat-I Design Review
114 Radiation Trade Study Radiation Trade Study Option Pros Cons Decision Conclusion High resistance to Radiation Hardened Chips radiation Expensive No Possibly prevent some Expensive, heavy, and Physical shielding radiation exposure hard to test. No Best chance to avoid system failure against Hardware redundancy radiation Requires more hardware Yes Could allow for self checking and error Complicated and resource Redundant Software Design prevention intensive Very complicated, possibly Yes Self healing/correcting Could allow self mitigation too intensive for our software and healing microtroller No Too expensive for project scope Too expensive and cumbersum in design This will be our best chance to safe guard against radiation This has potential to help prevent system failure without much cost Too complicated and not commonly used on microcontrollers 114 AubieSat-I Design Review
115 Operating System Feature RTOS Procedural OS Resource usage High Low Scheduling Yes No Multi-Tasking Yes No Threading Yes No Design Complex Simple Light weight design No Yes Design knowledge Documentation Our design 115 AubieSat-I Design Review
116 Software Design The finite state machine 116 AubieSat-I Design Review
117 Mode Flow Diagram 117 AubieSat-I Design Review
118 Specific Mode Flow Diagrams AubieSat-I Design Review 118
119 Ground Station Brian Stump & David Sconzo
120 Block Diagram 120 AubieSat-I Design Review
121 KCP-3 Plus Easy setup Operating modes- Packet and KISS Data rate bps Extra features: mailbox and digipeating 121 AubieSat-I Design Review
122 TNC Basics Components microprocessor modem software (in EPROM) Two main capabilities AX.25 protocol command line interface 122 AubieSat-I Design Review
123 ICOM-910H Satellite mode Modes FM, SSB, CW Frequency bands 2m, 70cm 123 AubieSat-I Design Review
124 Antenna Requirements Yagi beamwidth degrees. high gain circular polarization meet size limitations 124 AubieSat-I Design Review
125 Antenna Frequency range MHz Gain dbdc Beamwidth 30 degrees Polarity Circular Boom Length 117 VSWR Feed Impedance Power Handling 1.6:1 Max 50 ohms 600 Watts 125 AubieSat-I Design Review
126 Radiation Pattern 126 AubieSat-I Design Review
127 Extra Radio Hardware LCU-3 Level Converter Converts nonstandard positive or negative logic input voltages to standard DTL logic. Integrated PCI Card Provides an extra two DB-9 serial ports to the computer. 127 AubieSat-I Design Review
128 Rotator Hardware Yaesu GS-232A Computer Interface Provides digital control for rotator. Async serial line can be 1200 to 9600 baud. Yaesu Rotator G5500 points antenna power requirements 128 AubieSat-I Design Review
129 Structure Specially design steel and fiberglass structure to mount to the Allison Lab chimney Fiberglass boom for rotator Option for second 2-meter antenna. Built to survive strong winds 129 AubieSat-I Design Review
130 Ground Station Software 130 AubieSat-I Design Review
131 NOVA for Windows Provides software control for rotator Main purpose: az/el antenna autotracking Uses Keplerian elements to predict satellite path Daily update of elements from Celestrack NORAD publishes LEO satellites in two-line element format. 131 AubieSat-I Design Review
132 Ham Radio Deluxe Provides software control for transceiver Main purpose: Doppler shift correction Uses Keplerian elements to predict frequency change. 132 AubieSat-I Design Review
133 UI-View Not satellite-based. Send and receive messages on the local APRS network. Track other ground stations. 133 AubieSat-I Design Review
134 Future Work Develop ground support software to extract satellite information from packets. Integrate NOVA, HRD, and new logging program using DDE-capabilities. And, of course, track more satellites. 134 AubieSat-I Design Review
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