1. Peer Review
DINO
July 9, 2003

2. Agenda Overview ADCS C&DH COMM PWR Science Software Structures Thermal
Systems CM
Actions and Review Summary
September 16, 2018

3. Overview
Purpose: For everyone to understand the satellite at a systems level, help other subsystems with their current design, and to determine that interfaces between subsystems are correct.
Action Item forms
September 16, 2018

4. Jeff Parker Stephen Stankevich
ADCS Peer Review
Jeff Parker
Stephen Stankevich

5. Requirements Maintain attitude knowledge to within 2°.
Control s/c in 60° cone for boom deployment.
Maintain control in roll/pitch axis to +/- 10°.
Maintain yaw control per science requirements ~ +/- 10°.
September 16, 2018

6. Requirements System use of less than 2kg and 4W Weight Power
Actuators < 1.5kg
Sensors < 1.5kg
More weight allotment possible
Power
and < 2.5W
Sensors < 1W
September 16, 2018

7. Possible Hardware Sensors Actuator Magnetometer Sun Sensor
Earth Sensor
Rate Gyro
GPS
Actuator
Torque Rod/Coil
Reaction Wheel
September 16, 2018

8. Sensor Trade Studies Magnetometer Sun Sensor Earth Sensor Rate Gyro
Low cost, low weight, low power
Effective measurement of field to compare with model.
Sun Sensor
Accurate measurement of s/c - sun direction vector in 2 axis.
Earth Sensor
Medium weight and power draw
Very accurate measurement of earth horizon (Yaw Axis).
Rate Gyro
Large weight and expense
Excellent measure of s/c rotation rates.
September 16, 2018

9. Sensors Magnetometer Sun Sensor Honeywell HMC2003 100g 20mA @ 12V
40μGauss Resolution with +/- 2 Gauss Range
$200
Sun Sensor
Possible donation from Ithaco Space Systems
September 16, 2018

10. Torque Rods Less complex and lighter than reaction wheels.
Commonly made of cylindrical iron core wrapped with copper wire.
The output is a magnetic dipole moment based on the current passed through the wire, # of turns of wire, and area of the rod. (M=INA)
Dipole moment interacts with Earth’s magnetic field to create the desired torque. (T = MxB)
Need to actuate torque rods as multiple current levels.
September 16, 2018

11. Torquer Sizing Power Length = 0.75” Diameter = 1.8” Moment = 1 A*m2
I = 150 mA
V = 5V
P = 0.75 W
Length = 0.75”
Diameter = 1.8”
Moment = 1 A*m2
Mass < 0.3 kg
Power Dissipation < 0.02 W
# Turns ~ 40
September 16, 2018

12. Slew Times
Torque Rods will not allow for immediate slew maneuvers of the s/c
The larger the torque rods the quicker the slew times.
September 16, 2018

13. Converters
A/D Converters will be needed for the magnetometer and sun sensors
Intersil HI7188 for magnetometer
8 Channel, 16 Bit 5V
D/A converter may be necessary for torque rods
September 16, 2018

14. ADCS Control Diagram
September 16, 2018

15. ADCS Flow Diagram
September 16, 2018

16. C&DH
Peer Review

17. Why RPX_LITE? Processor: MPC823E Software compatibility
Supports necessary interfaces
Lightweight, low power
September 16, 2018

18. Requirements Imposed by EPS:
1 RS-232 serial port for subsystems control
Current Sensor readings?
General purpose I/O Lines?
September 16, 2018

19. Requirements Imposed by COMM
1 dedicated RS-232 serial port to TNC
1 RS-232 serial port to radios
September 16, 2018

20. Requirements Imposed by Science
Multiple USB ports for cameras.
I think Science should be responsible for USB hub
Control lines?
September 16, 2018

21. Requirements Imposed by ADCS
16 bit ADC with 4 channels (minimum)
September 16, 2018

22. Requirements Imposed by Tip-Mass
802.11b link between main satellite and tip-mass
September 16, 2018

23. Other Requirements?
Structures -?
Thermal
September 16, 2018

24. Interface Board FLIGHT COMPUTER USB I2C TIP-MASS SCIENCE USB HUB
General Purpose I/O Pins
USB
RESET
SMC1
SMC2
I2C
PCMCIA
TIP-MASS
SCIENCE
USB HUB
RS232 DRIVER
RS232 Serial
802.11b
MULTIPLEXER
CPLD
CPLD
ADC
INTERFACE BOARD
ADCS
TNC
RADIO
EPS
Multiple Wires
COMM
Wireless

25. Power Needs FLIGHT COMPUTER (5V, 1A) USB I2C TIP-MASS RS232 Serial
General Purpose I/O Pins
USB
RESET
SMC1
SMC2
I2C
PCMCIA
TIP-MASS
RS232 Serial
RS232 DRIVER
(5V, 7mA)
SCIENCE
USB HUB
(5V min)
802.11b
(5V, 1A)
MULTIPLEXER
(5V)
CPLD
CPLD
(5V, 150mA)
ADC
INTERFACE BOARD
ADCS
TNC
RADIO
EPS
Multiple Wires
COMM
Wireless

26. Communication System
DINO Peer Review
July 9, 2003

27. Subsystem Block Diagram
September 16, 2018

28. Power Requirements Daytime Operation
Receiver: 0.54 W (6 V, 90 mA) always.
TNC: 5.52 W (13.8 V, 400 mA) always.
Transmitter: 8.4 W (6 V, 1.4 A) for approx. 2 minutes, otherwise same as Receiver (0.54 W).
September 16, 2018

29. Power Requirements Nighttime Operation Safe Mode
Receiver: 0.54 W (6 V, 90 mA) always.
TNC: 5.52 W (13.8 V, 400 mA) always.
Transmitter: 8.4 W (6 V, 1.4 A) for approx. 4 seconds, otherwise same as Receiver (0.54 W).
Safe Mode
Same as nighttime.
September 16, 2018

30. Calculating Transmission Time
Time needed to send one packet:
10 bits/byte * 256 bytes/packet  9600 bits/sec = sec/packet
Total transmission time (assuming 50 kB per pass during daytime):
0.267 sec/packet * 50 kB/pass
 256 bytes/packet
= 52 sec/pass
September 16, 2018

31. Transceiver Trade Study: Four Choices
ICOM IC-ID1 1.2 GHz digital
Pros
Allows for small antenna
Built-in TNC with kbps baud rate
USB interface
Cons
Expensive
Only one frequency band: need half-duplex comm.
Newly released, untested, unlicensed by FCC
Needs new ground equipment
September 16, 2018

32. Transceiver Trade Study
Kenwood TH-D7 dual band 70 cm/ 2 m
Pros
Operates in 2 frequency bands
One third of the cost of the ICOM radio
Compatible ground equipment already set up
Previous experience from other missions
Cons
Max. baud rate of 9.6 kbps.
Requires larger antenna than ICOM
Uses RS-232 interface
September 16, 2018

33. Transceiver Trade Study
TEKK SD-5200 synthesized radio and TEKK KS-960 crystal radio
Pros
Can be set to one frequency by the manufacturer: no actual programming required (unlike Kenwood)
Currently being proven in space flight on Stanford’s Quakesat mission
Significantly cheaper than the Kenwood radios
Cons
Only UHF version available: so we would need a different radio for VHF (no longer advantageous)
September 16, 2018

34. Design Decision
Two Kenwood TH-D7 radios: one for uplink, the other for downlink.
Reasons
Only choice that allows two distinct channels for uplink and downlink, respectively.
Much better to use same model for both channels
9.6 kbps should be a sufficient baud rate for the purposes of this mission
No idea when the ICOM 1.2 GHz radio will ever be available for our use.
September 16, 2018

35. Antenna Trade Study Monopole Pros Cons Simple design
Does not take up space on the satellite’s surface
Cons
Deployable
Could be very long (~50 cm)
September 16, 2018

36. Antenna Trade Study Patch Pros Cons Preferable gain pattern
Non-deployable
Cons
Could occupy a lot of space on nadir surface
More complicated design process
More expensive
September 16, 2018

37. Power
DINO Peer Review

38. Side Panel and Aero Fins
ADCS
COMM
Science
Structures
12 Volt Line
5 Volt Line
28 Volt Line
EPS System
C&DH
Inhibits
Side Panel and Aero Fins
FITS Solar Array
Batteries
September 16, 2018

39. EPS System Voltage Bus Switches Sensors Batteries Charge Controller
Microprocessor
C&DH
September 16, 2018

40. The Ball Systems vs. CU System
The drop dead decision date is tomorrow
Ball: Complicated, Clean, Expensive
CU: Simple, Cheap, Not as good
Ball will advise regardless
September 16, 2018

41. Power Distribution and Monitoring
Must distribute and regulate power to all subsystems
+24V (regulated)
+15V (unregulated)
+12V (regulated)
+5V (regulated)
Must be commandable by C&DH
Communication will be through a RS-232 port
The PWR team must provide a commands list to C&DH and Software
September 16, 2018

42. Power Distribution and Monitoring
4 internal temperature monitors for each battery cell
Voltage Monitoring
Battery Stack Voltage
All major voltage buses
Each solar panel
The current draws from each subsystem must be monitored
September 16, 2018

43. Power Distribution and Monitoring
The temperature should nominal be 20ºC and can fluctuate ±20ºC.
The latest sample from the monitoring must be able to be stored in memory.
All subsystems must be able to turn on/off.
September 16, 2018

44. Structural Concerns The power system shall weight less than 2.25 kg
The system will use only required components
The system will use the lightest components possible
The power system shall be structurally supported
The batteries will be in a contained box with potting material
The EPS will be in box mounted to a side panel of the satellite
The structure ground will be separate from the electrical ground
The structure will have less than an 1 ohms resistance
The boxes of the structure will be anodize to prevent electrical shorts
September 16, 2018

45. Power Safety Meeting all safety concerns
Following NASA’s guidelines for safety
The proper connections will be made between systems
The system will be properly grounded and tested
Inhibits will be used to ensure systems are NOT powered
4 inhibits will be used to separate the power sources
switches will be used to turn on and off devices
Ball Aerospace will assist us in testing
Selection of batteries will be supervised
Charge control system will be test with Ball Engineers
September 16, 2018

46. Relays Switch Pros Pros Manages large amounts of power.
Used on previous mission.
Resets to a open state.
Simple circuit design
Widely available costing about $2-5
Cons
Has a bulky size, about 2-3 cm tall.
Will require a driver to trigger.
Slow reaction time, the time is based how fast the coils will charge.
A switch can do most of the same functions
Pros
Simple setup, Is either on or off.
Low power usage, using less than a Mw.
Controlled by high and low signals.
The cost of switches will between $1-3.
Cons
There is no fail safe.
May not be able to handle the power going through it.
September 16, 2018

47. Lithium Batteries 4 Cell Stack ~3.7V/Cell, 14.8V Stack
At least 4 A-hr capacity
Cells must be structurally contained
Cells from Valence Tech.

48. Why Lithium-Polymer?
High capacity, small physical size and weight make an unbeatable combination
No liquid electrolyte reduces risk of fire/short
Support from Ball Aerospace
3.7 V/Cell
Nickel-based cells are too heavy and lack enough capacity
September 16, 2018

49. What’s the catch?
Cell stack will need careful charging to make it last for entire mission
Charge controllers will need to have different, optimal charge profiles
Each cell in the stack will need temperature monitoring and shunt diodes
Cells have no integral structure and must be completely supported
No Space Shuttle flight heritage
Battery system must be two-fault tolerant
September 16, 2018

50. Science
Jessica Pipis

51. September 16, 2018

52. Power Needs For Camera’s
A 5 Volt line going to each camera is needed.
To start up,each camera will require 190mA.
When idle, each camera will require 178mA.
While taking a picture, each camera will require 186mA.
An interface board will require power to switch between camera’s.
September 16, 2018

53. Data Each picture is about 200k at maximum resolution (1248x960).
Takes about seconds for images to store.
Takes a couple minutes to pull pictures off of the camera’s.
May take more or less time depending on software.
September 16, 2018

54. Durability of Camera’s
All components (except for lens) look to be secured to circuit board.
The circuit board will need to be conformal coated.
Housing for lens is only concern.
Not secured to circuit board.
A box can be built to secure it.
Unknown plastic used for casing
We may find way to get plastic analyzed.
We may find a replacement casing.
September 16, 2018

55. Software Subsystem

56. Overview Ground software Flight software
Uplink commands/schedule to spacecraft
Downlink H&S/science data from spacecraft
Flight software
Perform commands from ground
Gather H&S and process science data
Update schedule based on opportunities or problems
September 16, 2018

57. Ground S/W - Uplink Web browser MySQL SCL COMM STK Disk/ Files
Immediate Cmds
Scheduled
Cmds
Web
browser
MySQL
Cmds
Pkts
SCL
COMM
Events
STK
Schedules
= H/W Interface
Schedules
Disk/ Files
September 16, 2018

58. Ground S/W - Downlink Web browser MySQL SCL COMM STK Disk/ Files
Sci data
H&S (All)
Sensor data
Web
browser
MySQL
Pkts
Orbit data
SCL
COMM
STK
H&S (ADCS)
Pictures
= H/W Interface
Disk/ Files
Sci data (pictures)
September 16, 2018

59. Ground S/W – H/W Interfaces
Radio to Communications module (COMM)
Could be different for each ground station
CU’s radio requires serial RS-232 connection
Software will handle serial RS-232 and have the ability to add others as needed
TNC to Communications module (COMM)
CU’s TNC requires serial RS-232 connection
September 16, 2018

60. Ground S/W – S/W Interfaces
Web to MySQL
Perl
Inputs and outputs: TBD
Web to STK
Perl or C++
Web to SCL
September 16, 2018

61. Ground S/W – S/W Interfaces
COMM to SCL
C++
Inputs and outputs: TBD
COMM to STK
COMM to MySQL
September 16, 2018

62. Ground S/W – S/W Interfaces
STK to MySQL
Perl
Inputs and outputs: TBD
September 16, 2018

63. Ground S/W – Human Interfaces
Website to issue commands
MOPS interface
Distributed Investigator interface
General Public interface
Website to see H&S and Sci data
September 16, 2018

64. Ground S/W – Human Interfaces
STK to visualize current and expected orbit characteristics – MOPS interface only
SCL to visualize data/cmds flowing to and from spacecraft – MOPS interface only
September 16, 2018

65. Flight S/W – Process_Cmd
ADCS ?
I2C_mgr ?
BPGEN ?
COMM
SCI
serialmgr
Route_cmd ?
SWM
usbmgr
POWER ?
= H/W Interface
SCL DB
SCL
September 16, 2018

66. Flight S/W – Process_Reply
ADCS ?
I2C_mgr ?
BPGEN ?
COMM
Return_reply
SCI
serialmgr ?
SWM
usbmgr
POWER ?
= H/W Interface
SCL DB
SCL
September 16, 2018

67. Flight S/W – H/W Interfaces
Radio to Communications module (COMM)
Either serial or USB
TNC to Communications module (COMM)
Software to Serial (exists)
Software to I2C (exists)
Software to USB (yet to be developed)
September 16, 2018

68. Flight S/W – S/W Interfaces
ProcessTask functions to ProcessTask objects
C++
Inputs and outputs: exists
SCL to ProcessTask objects
ProcessTask objects to IO managers
Inputs and outputs: serial and I2C exist, USB TBD
September 16, 2018

69. Flight S/W – S/W Interfaces
ProcessTask objects to SCL DB
C++
Inputs and outputs: exists
ProcessTask objects to COMM
September 16, 2018

70. Other S/W Tasks
Besides the existing ProcessTasks talking to hardware, DINO Software needs to:
Convert stereo images to topo maps
Reschedule failed events within SCL
Schedule new images when unexpected opportunities arise (i.e. new clouds are seen)
No new interfaces needed but this is all new software code that needs to be written and tested.7
September 16, 2018

71. Trade Studies Linux vs. VxWorks Linux has bigger kernel
Linux = about 3 mb +/- 1 mb
VxWorks = about 1 mb +/- 0.5 mb
Flight software needs to be ported
All kernel calls changed = 2-3 week task
Memory management (i.e. shared memory) = 3 -4 week task
Flight code compiled into own libraries
Starting flight code would change
September 16, 2018

72. Trade Studies Linux vs. VxWorks (cont) Cross compiling needed for PPC
Need to compile kernel on a machine like Thinker or another Linux computer
Much bigger knowledge base for Linux
New students to Space Grant can help development much quicker than learning VxWorks
Questions can be posted on discussion groups and more likely to be answered
September 16, 2018

73. Trade Studies Linux vs. VxWorks (cont)
Our recommendation:
Linux (mostly for the student’s ability to start work with it)
VxWorks will be contingency OS if Linux development/porting takes too long (time TBD)
Still need to decide on which distribution of Linux:
Commercial: MontaVista, RedHat, TimeSys
Free: Debian, muLinux, ThinLinux, etc.
September 16, 2018

74. Structures and Mechanisms - Peer Design Review -
Jen Getz
Anthony Lowrey
Grayson McArthur
Tim Shilling
Terry Song
9/16/2018

75. - Table Of Contents - Structure Deployable Block Diagram
Needed from other Teams
September 16, 2018

76. Structure Revision C Dimensions: 18.15in x Ø17.75in Mass: 5.78 kg
Material: Aluminum 6061
* All dimensions are in inches *
September 16, 2018

77. Mounting Holes Revision C Side Top * All dimensions are in inches *
September 16, 2018

78. Clearance Revision C Side Bottom Top * All dimensions are in inches *
September 16, 2018

79. Boxes Tall Components Short Components Benefits
* Less wasted material = Lower Cost
* Internal components more accessible
* Mounting is more flexible
September 16, 2018

80. Boom Deployment
Open Loop System (Push tip mass away with springs and let the system deploy on its own)
Mini-Lightband release ring or Hop Release
September 16, 2018

81. Hight Output Paraffin Actuator (H.O.P)
Pin Puller
Less then 120g
Small, only about 3 inches tall and ¾ inch diameter
50 lbs of force
Activated with 28V at 18 watts, which heats up the wax inside the piston, expanding it and causing the pin puller to move
September 16, 2018

82. FITs solar Array Deployment
Thin Film Solar Arrays
FITs solar Array Deployment
September 16, 2018

83. One H.O.P = Multiple Deployments
September 16, 2018

84. FITs and Aerofins Release Mechanism
Spring Pushes Latch
H.O.P Released
Pin Released
September 16, 2018

85. Aerofins and FITS solar Arrays
Input and Control
Aerofins and FITs Solar Arrays
H.O.P
18 28V
for 1.5 minutes
Composite Hinges
10 28V per Hinge
for 1 minute
2-4 Hinges required
High/Low output
(Switch signaling final
deployed position)
released position)
September 16, 2018

86. Boom Input and Control OR H.O.P 18 watts @ 28V for 1.5 minutes
Lightband Separator
10 12V
for 1 minute
High/Low output
(Switch successful separation
and final deployed position) OR
September 16, 2018

87. (Switch signaling final
Antenna
Input and Control
Solenoid
5watts at 12 V
High/Low output
(Switch signaling final
deployed position)
September 16, 2018

88. Summarized Structure’s Needs
7-9 hi/low output lines, signaling various stages of deployment
2 Solenoids, 5watts at 12V (May not be needed)
1 or 2 H.O.Ps, 18 28V for 1.5 minutes
1 possible Lightband Separator, 10 12V for 1 minute
4 total, 2 at a time deployment Composite Hinges, 10 28V per Hinge for 1 minute
September 16, 2018

89. Thermal Subsystem
Peer Review
7-9-3

90. Objective:
To maintain all components of the space craft within their specific temperature range

91. Model Empty Spacecraft for entire orbit:
Method
Model Empty Spacecraft for entire orbit:
Assumptions:
ISS Orbit
Thermal Properties
Structure
Results:
Heat gain from Radiation
Heat reflected within satellite

92. Inside-the-Box Modeling
Thermistors
Used to monitor temperatures at specific locations during orbit. This will allow for us to troubleshoot during the mission when components are not acting properly.
Sensor is glued to surface of interest, where it creates a specific resistance in response to temperature measurement.
Approximately, 50 thermistors will be required at $3-$6 each.

93. Inside-the-Box Modeling
Temperature Control
Isolation
Some sensitive electrical components will need to be isolated from the radiative/conductive environment. We can do this thru MLI blankets.
Heat Reservoirs
Components which are exposed to alternating hot and cold modes, will need to be in contact with heat reservoirs which will both gather and supply heat when needed.

94. Inside-the-Box Modeling
Heat Expulsion
Radiator:
The radiator rejects excess heat into space.
Placement:
The best position for the radiator is the earth facing side of the satellite. This should not affect the cameras, and is standard practice.

95. What’s Next? Thermal Model
Upon reporting specifications of materials and equipment, as well as their modes of operation, our model can be expanded to increase accuracy.
Placement of Thermistors will result from the reporting of these specifications, so we can identify points of interest for temperature measurement.

96. References http://www.angels-crossing.com/gifts.html
gore.ocean.washington.edu/.../ Students/Crone/therm.htm
index.shtml

97. Systems
Peer Review

98. Satellite Communications
Serial
Ethernet
Analog Data
Digital Data
USB RF
Cam 1
Cam 2
September 16, 2018

99. Satellite Power Cam 1 Cam 2 Imaging Thermal HOP SW FIN SW 1 15 V 5 V
September 16, 2018

100. Satellite Mass Budget Allocation (%) Goal (Budget) Current (kg)
Allocation (%)
Goal (Budget)
Current (kg)
Subsystems
ADCS 14
2.63
0.12
C&DH 3
0.56
0.15
Comm 5
0.94
0.70
Power
1.44
Science 8
1.50
0.07
Software
0.00
Str/Mech 49
9.19
6.94
Thermal 2
0.38
Cabling
Total
18.75
Margin
6.25
100%
25.00
9.42
September 16, 2018

101. Tip Payload Mass Budget
Allocation (%)
Goal (Budget)
Current (kg)
Subsystems
ADCS
0.00
C&DH
Comm 10
0.38
Power 20
0.75
0.31
Science 13
0.49
Software
Str/Mech 52
1.95
Thermal 2
0.08
Cabling 3
0.11
Total
3.75
Margin
1.25
100%
5.00
September 16, 2018

102. Daytime Power Budget Goal (Budget) Power Allocation (%) Goal (Budget)
Goal (Budget) Power
Allocation (%)
Goal (Budget)
Current Mission Power
Power (W)
Duration (min)
Budget (W-hr)
Available
30.0 55
27.50
Subsystems
ADCS
4.0
3.67
16.7
3.7
0.3
C&DH
3.6
Comm Rx
1.0
0.92
4.2
0.9
6.7
Comm Tx
19.0 5
1.58
7.2
1.6
0.1
Power
-2.6
Science
11.0 50
9.17
41.7
9.2
1.1
Software
0.0
0.00
Str/Mech
Thermal
2.3
2.09
9.5
2.1
Total
22.0
Margin
5.5
100.0%
27.5
September 16, 2018

103. Nighttime Power Budget
Goal (Budget) Power
Allocation (%)
Goal (Budget)
Current Mission Power
Power (W)
Duration (min)
Budget (W-hr)
Available
30.0 35
17.50
Subsystems
ADCS
4.0 20
1.33
9.5
1.3
0.3
C&DH
2.33
16.7
2.3
Comm Rx
1.0
0.58
4.2
0.6
10.0
Comm Tx
19.0 3
0.95
6.8
0.0
Power
13.6
Science
0.00
Software
Str/Mech
Thermal
2.0
1.17
8.3
1.2
Total
14.0
Margin
3.5
49.6%
17.5
26.2
September 16, 2018

104. Configuration Management
Document Naming
DINO-SUBSYS-TYPE-NAME, Rev. 1
SUBSYS: A two to four letter description of the subsystem involved.
TYPE: A two to four letter description of the type of document.
NAME: A six letter abbreviation of the document title.
September 16, 2018

105. Subsystems Management MNG Systems SYS Software SW Structures STR
Mission Operations
MOPS
Communications
COMM
Thermal
THR
Attitude Determination/ Control
ADCS
Command and Data Handling
CDH
Power
PWR
Mechanisms
MECH
Imaging
IMG
September 16, 2018

106. Procedures/Instructions
Document Type
Requirements
RQT
Part Lists PL
Material Lists ML
Report
RPT
Plan
PLN
Procedures/Instructions
PROC
Manual
MAN
Policy
POL
Drawing
DRW
Part
PRT
Assembly (not a plan)
ASM
September 16, 2018

107. Actions and Summary Action Items from review Requirements updating
Requirements Review on 7/23/03
SHOT Workshop
Thursday at 2:00 Power and Inhibits
Friday at 8:15 NanoSat PDR Overview
Logo Contest July 17, 2003 at the huddle
September 16, 2018