1. System Requirements Review
2 Nov 2016
RadSat-u
System Requirements Review
Dr. Brock LaMeres
Connor Julien
Colin Delaney
RadSat-u SRR

2. Agenda Time (MST) Topic 1100 – 1105 Mission Overview 1105 – 1110
Concept of Operations
1110 – 1120
Mission and System Requirements
1120 – 1125
Spacecraft Bus Overview
1125-
1130
Programmatics
1130 – 1200
Open Discussion
RadSat-u SRR

3. Meet the RadSat Team Space Science and Engineering Laboratory
2 Nov 2016
Brock LaMeres
Principle Investigator
Space Science and Engineering Laboratory
Keith Mashburn
Logistics, Engineering advisor
Connor Julien
Graduate Mentor
RadSat-u SRR
Colin Delaney
Team Lead, Physics
David Kelly
CpE
Daniel Mills EE
Colton Marchwinshki EE
Jonathan Dover EE
Matt Johnson ME

4. Mission Overview
2 Nov 2016
Mission Overview
RadSat-u SRR

5. Radiation Tolerant Computer Overview
2 Nov 2016
RadSat-u is to demonstrate a novel computer architecture design to mitigate radiation induced faults using soft processors implemented on an FPGA.
The Radiation Tolerant Computer Stack (RTCS) will detect faults on orbit and replace the damaged tile with a known good spare, then repair the damaged tile through partial reconfiguration.
Mission Overview
RadSat-u SRR

6. RTCS Design Mission Requirements
2 Nov 2016
Uses a combination of methods (TMR + spares, partial reconfiguration, memory scrubbing) to detect and repair faults caused by radiation.
Data Board – Interfaces with the data SD card for data storage and the USB port for data extraction.
FPGA Board – Contains an experiment FPGA (Artix-7) and a master FPGA (Spartan-6).
Power Board – Provides multiple voltage rails to different parts of the stack.
Will interface with the MFIB board to receive commands and send data.
RTCS
Mission Requirements
Power Board
FPGA Board
Data Board
RadSat-u SRR

7. Radiation Tolerant Computing Legacy
2 Nov 2016
Matured at MSU over the course of 8 years, tested on the following missions:
1 Cyclotron firing
8 High altitude Balloons
2 Sounding Rockets
SL9 Up Aerospace
Deleon 14114
1 ISS Flight (in progress)
Mission Overview
RadSat-u SRR

8. Proposed Sensor Mission Overview
Ionizing radiation detection sensor using a off the shelf solar cell as a silicon surface to absorb SEE energy.
Mission Overview
RadSat-u SRR

9. Concept of Operations
2 Nov 2016
Concept of Operations
RadSat-u SRR

10. Initial Ground Contacts
Concept of Operations
2 Nov 2016
NANORACKS Deployment
Off ISS
Autonomous Startup
EPS
CDH
COMM Rx
Deploy antennas (delayed)
Start tracking beacon (delayed)
Initial Ground Contacts
Bus Commissioning
Payload Commissioning
Launch
(Passive ACS)
Concept of Operations
Begin Nominal Science Operations
The RTCS will give count updates every 60 min and the beacons will reflect important data from last received RTCS packet.
During the ~12 hour Watchdog avionics payload the RTCS will stay powered. After each shutdown the MFIB will reinitialize communications with the RTCS.
RadSat-u SRR
Single Event Effects
Daily Science Downlinks

11. Mission Operations Overview
2 Nov 2016
RadSat-u
K7MSU Mission Operations Center
Space Science Laboratory, Montana State University
K7MSU-01
Satellite Earth Station
Concept of Operations
Science and Telemetry Data (L0)
Command Loads
RadSat-u SRR
Tested with HRBE, Firebird I, Firebird II
Tasking
Data Packets
RadSat Lab

12. Mission Requirements
2 Nov 2016
Mission Requirements
RadSat-u SRR

13. Mission Requirements Flow down
2 Nov 2016
Mission Objectives
Mission Requirements
Flight System
MOC
SOC
Mission Requirements
RadSat-u SRR

14. Flight System Requirements Overview
2 Nov 2016
FS Requirements
RadSat-u SRR

15. S1-1
2 Nov 2016
FS Requirements
RadSat-u SRR
Our computer architecture needs to be in a high radiation environment for long periods of time to be struck by radiation.
Our solution is a 3U CubeSat.
Needs to be a 3U for power requirements

16. S1-2
2 Nov 2016
FS Requirements
RadSat-u SRR
The Firebird stack has a 24 hour Watchdog that power cycles the spacecraft using basic logic gates (555 timer) to avoid errors incurred on the avionics.
Our experimental computer needs to run continuously so it needs to be not part of that watchdog.

17. S1-3
2 Nov 2016
FS Requirements
RadSat-u SRR
We do not have enough power to run the sensor continuously, so it will be intermittently run for correlation.

18. S1-4
2 Nov 2016
FS Requirements
RadSat-u SRR
We want our spacecraft to be at a consistent angle with respect to the magnetic field to increase consistency of our experiment

19. S1-5
2 Nov 2016
FS Requirements
RadSat-u SRR
Data will be saved locally on the SD card on the RTCS then intermittently fed to the Spacecraft C&DH where it will be transmitted down.

20. S1-6 FS Requirements Same, but for the radiation sensor 2 Nov 2016
RadSat-u SRR
Same, but for the radiation sensor

21. S1-7
2 Nov 2016
FS Requirements
RadSat-u SRR
Firebird II is SSEL’s most successful satellite (1.5 years), and because of that we want to reuse as much of the design as possible, to increase chances of success and decrease development times.

22. Mission Operations Center Requirements Overview
2 Nov 2016
MOC Requirements
RadSat-u SRR

23. S2-1
2 Nov 2016
MOC Requirements
RadSat-u SRR
Similar reason to S1-7, K7MSU is proven to work and it’s available.

24. S2-2
2 Nov 2016
MOC Requirements
RadSat-u SRR
Using L3’s In-Control which is running K7MSU, it handles archiving data, generating commands for the satellite, and decrypting incoming packets
The ICD is in works

25. S2-3
2 Nov 2016
MOC Requirements
RadSat-u SRR
Using L3’s In-Control which is running K7MSU, it handles archiving data, generating commands for the satellite, and decrypting incoming packets

26. S2-4
2 Nov 2016
MOC Requirements
RadSat-u SRR
To correlate our data, we will map it’s position the computer was struck, that requires us to use TLE propagation to know it’s approximate position

27. S2-5 MOC Requirements Clock needs to be synchronized after launch
2 Nov 2016
MOC Requirements
RadSat-u SRR
Clock needs to be synchronized after launch

28. Science Operations Center Requirements Overview
2 Nov 2016
SOC Requirements
RadSat-u SRR

29. S3-1
2 Nov 2016
SOC Requirements
RadSat-u SRR
All data is automatically backed up from our primary ground station computer to SSEL’s data-redundant server, Titan.

30. S3-2
2 Nov 2016
SOC Requirements
RadSat-u SRR
For Firebird, we have an automated script that we can request specific data from different times from. The script then translates that to which blocks the operator needs to download at the next pass.

31. Spacecraft Bus Concept
2 Nov 2016
Spacecraft Concept
RadSat-u SRR

32. RadSat-u Overview Spacecraft Concept Radiation Sensor
11/12/2018
Communication Paths
Radiation Sensor
-> Redesigned solar cell based radiation sensor
Spacecraft Concept
RF Link
RTCS
-> Existing RTCS Design, no changes
Harness
RadSat-G
MFIB
-> New MFIB to interface to FTCS with built in protection
Lithium L1 Radio
-> New Radio Board (Compatible with old software)
GSE Link
EPS
-> Re-Worked EPS board for MPPT (Compatible with old software)
CD&H
-> No Changes

33. Solar-Cell Experiment
Structure Concept
2 Nov 2016
Li-Ion Battery
3U CubeSat Form factor
Avionics stack derived from Firebird II design.
RTCS design identical to Artemis mission
Li-Ion battery pack copied from SSEL’s IT-SPINS mission.
Solar-Cell Experiment
Spacecraft Concept
Data Logging Board
RTCS
FPGA Board
RTCS Power Board
RadSat-u SRR
Magnet Board
MFIB
Avionics
Radio
EPS
C&DH

34. Preliminary Mass Budget
2 Nov 2016
Spacecraft Concept
RadSat-u SRR

35. CD&H Spacecraft Concept
2 Nov 2016
The CD&H from Pumpkin will be used with no modifications from the FIREBIRD Architecture.
The software will have to be modified with new command sequences and telemetry information.
Spacecraft Concept
RadSat-u SRR

36. MFIB Spacecraft Concept
2 Nov 2016
The MFIB (Multi-Function Interface Board) is based of the FIREBIRD MFIB Architecture.
Latching Relay for continuous power of RTCS with built in hardware protection
Payload Interface
NAND Storage
The MFIB will be sensing the temperature and current of the RTCS independent of the RTCS.
If a overcurrent or over temperature situation occurs the MFIB will automatically shutdown the RTCS
Spacecraft Concept
RadSat-u SRR

37. EPS Spacecraft Concept
2 Nov 2016
EPS will have a MPPT input implementation to accommodate off the shelf 7S1P Solar Panel Solution from Clyde Space (provided power budget signoff).
A re-working of the EPS Phoenix V2.1 version to the EPS Phoenix V2.2 will include suggested improvements such as RX/TX crossovers and MPPT. The voltage sensing resistors will also be recalculated.
A single payload switch will supply power to the Radiation Sensor
Spacecraft Concept
RadSat-u SRR

38. Spacecraft Power Bus Concept
2 Nov 2016
Spacecraft Concept
RadSat-u SRR

39. Solar Panels Spacecraft Concept Clyde Space 7S1P Spectrolab UTJ cells
2 Nov 2016
Clyde Space 7S1P Spectrolab UTJ cells
Sun Detectors and temp sensors included
Magnetorquer included (not used)
Forces us to use a MPPT
$5,300 per side
Spacecraft Concept
RadSat-u SRR

40. Preliminary Power Budget
2 Nov 2016
Spacecraft Concept
RadSat-u SRR
*Based on Clyde Space Solution

41. Satellite communications Bus Concept
2 Nov 2016
Spacecraft Concept
RadSat-u SRR

42. COMM Concept Overview Spacecraft Concept
2 Nov 2016
Adapting Firebird II design to the Lithium Radio (Li-1) from AstroDev from the Helium radio for the built in RX/TX Switch.
This decision is based on the new IARU rule not allowing VHF/UHF communications. Going to the UHF/UHF configuration allows for ease of antenna design.
May have antenna matching circuitry dual phased monopole for better Far-Field performance of the system depending on antenna simulations.
Should have direct software compatibility with the Helium Radio.
Will have direct pin replacement compatibility.
Spacecraft Concept
RadSat-u SRR

43. COMM Antenna Concept
2 Nov 2016
The deployable antennas are constrained to the satellite structure using Kevlar thread and nylon (monofilament) string.
The antennas are wrapped around the body of the CubeSat and then deployed using a hot-wire based release system
RadSat-u will use the same deployment system that succeeded on Firebird.
Spacecraft Concept
RadSat-u SRR

44. COMM Antenna Far field Spacecraft Concept
2 Nov 2016
Simulations derived from IT-SPINS: a 3U CubeSat with a 17cm monopole antenna being developed by SSEL. The antenna design is identical to RadSat-u
Simulations were ran with a 170 mm antenna will be tuned to MHz
Spacecraft Concept
RadSat-u SRR

45. Link Budget
2 Nov 2016
Spacecraft Concept
RadSat-u SRR

46. Programmatics
2 Nov 2016
Programmatics
RadSat-u SRR

47. Top Level Schedule 1
2 Nov 2016
Programmatics
RadSat-u SRR

48. Top Level Schedule 2
2 Nov 2016
Programmatics
RadSat-u SRR

49. Configuration Management
2 Nov 2016
Data is securely stored on SSEL’s Titan Server
Revisions are be manually saved
The SSEL Engineering Management Handbook provides guidance to engineering staff on CM procedures and documentation requirements
Programmatics
RadSat-u SRR

50. Questions?
2 Nov 2016
RadSat-u SRR