1. JASMM Conceptual Design Review
Virginia Tech
Jeff Crayley
Adam Jones
Sruthi Krishnan
Melissa Motylinski
Michelle Perez
10/23/2009

2. Mission Overview Objective:
To fly plug and play hardware from an Air Force Cube Sat Kit
To demonstrate appropriate Technical Readiness Level for plug and play satellite system
To fly a Photometric Space Weather Probe
To demonstrate appropriate Technical Readiness Level for a new probe and amplifier system

3. Mission Expectations Expect to Prove:
A sufficient Technical Readiness Level (TRL) for a Cube Sat plug and play kit
Prove a plug and play kit is a low cost alternative and low cost way to access space
Plug and play systems could be a feasible way to explore space with small scale satellites
CubeSat
Space is available to low end customers

4. Learning Expectations
Photometric Space Weather Probe
To obtain and analyze basic space weather data
To understand what components are necessary for the probe to complete successful data measurement and acquisition
Learning to design, build and operate satellite-like components

5. Overview of Science and Theory
The Space Weather Photometric Probe will be used to measure specific features of space weather
The exact measurement capabilities of this probe are currently pending
The science and theory behind the operation and measurements of the probe will be presented at PDR when they have been provided to the team by the ECE Department

6. Previous Research: Space@VT
Space Weather Research at VT
focuses on research investigations of the science, technological impact, and utilization of the geo-space environment.
For the past 15 years, engineers and scientists have gained a greater understanding of global warming, the effects of geomagnetic storms, the impact of the solar wind interacting on the magnetized region around the earth, and other dynamic processes that occur in the Earth's near-space environment.
Students use a high-latitude network of radars to obtain increasingly sophisticated views of electric fields, plasma structures, atmospheric waves, and other effects in the ionosphere and atmosphere.

7. Previous Research: Space@VT
Research Capabilities:
Satellite Mission Design and Remote Sensing
Space-based Instrument Development
Ground-based Instrument Development
Spacecraft Modeling, Simulation, and Design
Physics-based Modeling, Simulation, and High Performance Computing
Global Navigation Satellite System Receiver Design

8. Mission Requirements Access to the Optical Port
Since the probe is fiber optic, the probe could use the existing camera port

9. Mission Hardware Space Weather Photometric Probe MEMS IMU
Sensor Interface
Data Hub
GumStix
Back Up Computer: CF2 Flight Computer
Additional Hardware

10. Space Weather Photometric Probe
Fiber – optic Probe
Will require at least shared access to an optical port
Small in volume and mass
Estimated Mass = 1 lb
Will require the use of an amplifier
Estimated Mass = 0.5 lb
More information will be presented at PDR when it is received from the Virginia Tech ECE Department

11. Memsense uIMU Sensor
MEMSense µIMU Micro Inertial Measurement Unit IM C050T00
Operating Temperature Range: 0°C to 70°C
Tri-axis gyroscope with digital range scaling
Dynamic Range ± 1200 deg/sec
Input Voltage 8.0 – 13.0 V
2000 g Shock Qualified
Size: in. Diameter x in. Height
The reason we chose this new sensor is that it will allow us to measure the roll rate of the rocket

12. Plug and Play: Sensor Interface and Hub
Make and Model
muRataPs NDL2405SC G0833
Mass: lbs
0.002 lbs- 4 screws
Volume: x x inches
Hub and Sensors have equivalent masses and volumes

13. Gumstix Computer Make and Model Mass: 0.2 lbs
Vulcan Wireless Inc.
PCB10080 ET80
Mass: 0.2 lbs
Volume: 0.67 x 2.28 inches
Gumstix Computer runs off of a Linux Operating System
Marvell PXA270 Processor
Speed: 400 MHz
Memory:
64MB RAM
16MB Flash
Features
Bluetooth Communication
microSD adapter
USB host signals
WiFi

14. Risk Mitigation CF2 Flight Computer System
Persistor CF2 DataLogger
Motorola based single board computer
Vibration tolerant, low power, light weight
1 MB Flash, 1 MB SRAM, 512 MB CompactFlash card
UART, I2C, and SPI communications
Persistor R212 Recipe Card
Turnkey analog/digital converter board
Eight 12-bit channels
2.5 V precision reference
Capable of 80k Samples/second

15. Additional Hardware G-switch Batteries Resistors, Capacitors Relays
Voltage regulator
Surface mount adapters
RS converter
LED

16. Success Criteria Lowest Level of Success Mid Level of Success
All hardware and software operate properly on the ground
Mid Level of Success
Able to integrate the system into the RockSat Payload
System flies on RockSat
Highest Level of Success
All hardware and software operate properly in space and generate usable data for data analysis

17. Benefits
Operating a plug and play system in space will generate a TRL for a low cost option and access way to space
Opens up space exploration and satellite development to smaller private companies and individuals
Plug and Play satellite system decreases time to flight
Demonstrates a TRL for a new Photometric Probe developed at Virginia Tech

18. Expected Results Plug and Play Results
It will work and operate in the sub-orbital environment
It will provide the necessary infrastructure and equipment for an instrument to operate with the probe
The software and hardware will function correctly throughout the mission
It will store data that can later be accessed for data analysis
Potentially by AFRL

19. Expected Results Space Weather Photometric Probe
Measurement capabilities of the probe are pending
Expected results of the experiment will be determined once the ECE Department provides further details on the probe

20. Why is it Relevant?
Demonstration of new technology for Space Weather measurements
Successful measurements with this new space weather photometric probe could lead to new developments in Space Weather research
The Photometric Probe measurements could help to provide a greater understanding of Space Weather phenomenon

21. RockSat Payload Canister Compliance
Preliminary Mass Budget
Component
Quantity
Mass (lbs)
Photometric Probe 1
Amplifier
0.5
Sensor Interface 2
0.118
Hub
Gumstix
0.2
Battery Pack
FPGA Board
G Switch with Mount
0.013
IMU Sensor Unit
0.209
Miscellaneous
Total
5.776

22. RockSat Payload Canister Compliance
Payload Activation
Using a G-Switch and a Shorting Plug
See Block Diagram
Rocket Interface
Use of Shorting Wires

23. Block Diagram

24. Shared Can Logistics Plan on occupying half a can
Plan on taking up half of the mass and volume
We are requesting access to the optical Port
Since it is a fiber optic probe, it can be shared access
We will work with the other team to provide mounting points
We may just use a plate to provide a mounting interface

25. Management Senior Design Project Undergraduate Team
Will be managed and controlled by 5 Senior Aerospace Engineering students
Undergraduate Team
Will recruit a team of Undergraduate Electrical and Aerospace Engineering students
Responsible for Testing and Construction under the direction of the Senior Students
A full organization chart and Work Breakdown Structure is being developed and will be presented at PDR
The Schedule according the to RockSat User Manual will be followed

26. Management

27. Monetary Budget Monetary
The Budget for the Probe is currently being worked on and will be finalized by PDR
The Probe is being supplied by the ECE Department at Virginia Tech
All other components for the system are pre-existing technology
Plug and Play System from AFRL
RockOn Disk Platform

28. Conclusions
Mission to fly a Photometric Space Weather Probe with a Plug and Play satellite system
To further research and understand Space Weather
To demonstrate TRL for Plug and Play and the Probe

29. References