1. Zachary Cuseo, Sydni Smith, Andrew Fruge’, Tyler Knappe, Christopher Nie, and Shweta Maurya 8 October 2009

2. Mission Overview  The twofold purpose of this BalloonSat mission will be to show that the Earth's magnetic field varies and to show that magnetometers can be used to determine the attitude of a BalloonSat.

3. Mission Overview Continued Hypothesis – Fluctuation in the Earth’s magnetic field – Finding a vector which will facilitate in determining in which direction the camera is pointed Satellite attitude To better understand the magnetic field

4. Requirements Flow Down – Objective One Goal (G1) – The BalloonSat CATEOS will ascend to an altitude of 30km to measure the Earth’s magnetic field vector in order to determine the strength of the Earth’s magnetic field as it varies with altitude and determine where the on-board camera is pointed. Objective 1 (O1) – Build a BalloonSat that will ascend from the ground to 30 km with the equipment necessary to support the scientific mission. Objective requirements: o The 16 cm cube BalloonSat structure will be constructed to include a flight computer, power system, camera, and heater. System Requirements: o Foam Core Structure o AVR microcontroller o Power system o Camera o Heater

5. Requirements Flow Down – Objective 2 Objective 2 (O2) – Measure the strength of the Earth’s magnetic field as it varies with altitude and analyze the data to determine any trends in the field. Objective requirements: o A magnetic field sensor, connected to the flight computer with an analog proto board, will output the measured strength of the Earth’s magnetic field within a range of ±3.2 gauss (±3.2 x 10 -4 tesla). System Requirements: o The magnetic field sensors must be placed in a position that will allow it to accurately and predictably measure the strength of the Earth’s magnetic field, as well as in a position that will allow for easy correlation to the direction of the camera. The sensors must receive an input of 5V DC to operate and be connected to flash memory that will store its analog data output.

6. Requirements Flow Down – Objective 3 Objective 3 (O3) – Use the vector output of the sensors to determine the orientation of the BalloonSat which will be used to determine the direction that the camera is pointed when each picture is taken. Objective requirements: o Each picture will be coded with a time stamp and number that will be used to correlate each picture with the magnetic field vector at that point, making it possible to determine the direction in which the picture was taken. System requirements: o Write a program that the AVR controller will execute during flight that will correspond each picture to a magnetic field measurement. o The magnetic field sensor will record data on the same timer as the camera. When the camera is instructed to take a picture, the magnetic sensor will also record the current vector.

7. Design

9. Functional Block Diagram

10. Monetary Budget ComponentPurchase LocationQuantityUnit Cost Magnetic Field Sensor Vernier Software and Technology2$58.00 Analog Proto Board Connector Vernier Software and Technology2$10.00 Shipping Vernier Software and Technology2$15.64 Flight BatteriesProvided4 Foam CoreProvided3 Temperature CableProvided1 AVR Microcontroller BoardProvided1 SwitchesProvided2 HeaterProvided1 Aluminum TapeProvided1 Adhesive (Hot Glue Sticks)Provided10Provided Additional MaterialsLocal Stores ~ $16.36 Total Cost $183.64

11. Mass Budget ComponentPurchase Location Item Code Quantit y Single Item Mass (grams)Sum (grams) Magnetic Field Sensor* Vernier Software and TechnologyMG-BTA269.2138.4 Analog Proto Board Connector* Vernier Software and TechnologyBTA-ELV25.611.2 Camera with Batteries*Provided 1228.5 HOBOProvided 130 AVR Microcontroller Board, Heater, Power Connectors, and Switches*Provided 1117.1 9V Batteries*Provided 446.7186.8 Washers*Provided 214.929.8 Paper Clips*Provided 21.22.4 American FlagProvided 111 Foam Core StructureProvided 1563 cm 2 98.6 Tape, Glue, etc.Provided as needed6.2 (remaining weight)6.2 Total 850 *all weights measured for our actual components

12. Schedule:  9/22 - Conceptual Design Review (CoDR)  9/25 - Design Complete  9/27 - Program AVR (Microcontroller, Camera, and Heater)  9/29 - Hardware Ordering and Authority to proceed (ATP)  10/6 - Design Document revision A/B  10/8 - Critical Design Review (CDR)  10/9 - Acquire hardware  10/9 - External structure complete  10/11 - Drop test, Stair Test, Whip Test.  10/12 - Magnetometer testing (Faraday cage determination)  10/16 - External testing complete (whip test, drop test, and stair test)  10/16 - Internal component assembly complete  10/18 – Cold test, functional test, and data test  10/25 - Internal testing complete (cold test, functional test, and data test)  10/26 - Final assembly complete  10/27 - Pre-launch inspection  10/29 - Mission simulation  11/3 - Launch readiness review and design document revision C  11/6 - Final weigh-in and turn in  11/7 - Launch day @ 6:50 am. ("Bad" weather launch days: 11/8 or 11/14)  12/1 - Final presentation  12/5 - ITLL deign expo (from 9:00 - 4:00)  12/5 - Design document revision D due  *Team meeting will be every Sunday and during the week as needed.

13. Proposal Requirements RequirementCompliance ScienceMeasuring Earth’s magnetic field with respect to altitude changes Analog sensor inputs cannot exceed 5vProvided sensors and magnetometers use 5V DC Ready to fly again after flight Structure will be tested thoroughly in order to ensure the ability to fly again after flight Secure, non-metal flight string tube A paper clip will be used to secure the tube, as well as hot glue if needed Internal temperature must remain above -10 degrees Celsius A heater system will maintain the temperature of the internal structure Total weight cannot exceed 850gMass of payload has been budgeted and is within the requirements Acquire ascent and descent rates of flight The design will be constructed to withstand the changes in pressure and high speeds during ascent and descent Design shall allow for a 30g HOBOProvided, set-up, and accounted for in mass and design External Temperature CableProvided AVR Microcontroller Board and Batteries – 150gProvided, set-up, and accounted for in mass and design Heater - 100gProvided, set-up, and accounted for in mass and design Canon Digital Camera - 220gProvided, to be set-up, and accounted for in mass and design Foam CoreProvided and is being used for the external structure Allowance for spare parts on budget and parts listSome money has been allotted within the budget for spare parts U.S. Flag and Contact info on outsideProvided and will be attached on external structure Keep documents and design in metricDesign and documents are consistently kept in metric units Launch on November 7, 2009 The team has created a schedule which accommodates for launch date on 11/7 No one shall get hurt Team shall use goggles, gloves, and other safety gear when necessary Return hardware to program in working order Hardware will be securely placed inside the structure to ensure that it returns in working order All parts paid by Chris Koehler and receipts provided Order forms are completed, orders have been made, receipts have been sent Turn in receipts within 60 daysAdditional receipts will be sent when purchases are made Have fun and be creative Team Magnaritaville is having fun and being creative with its satellite, Cheeseburger at the Edge of Space No living things on payloadNo living things are being used in the experiment, or in the payload Complete final report with bonus videoThe team plans to make a video and complete report on time

14. Test Plan  Structural Testing Drop test, Whip test, Stair test, and the Kick test Complete on 10/11 – at latest by 10/16  Magnetometer Testing Connect magnetometers to AVR and measure in different positions Test the effect or interference of electronics in the presence of the Magnetometers Complete by 10/12  Internal Testing Cold test, functional test (flight duration), structural security Complete on 10/18 – at latest by 10/25

15. Expected Results - We expect to see the magnetic field decrease as 1/(R), where R = the radius of the Earth. - We expect these results because we are traveling away from the source of the magnetic field, the Earth. - Using a single magnetometer we expect to determine the direction of each photograph.

16. Potential Problems  Magnetic field may fluctuate due to the composition of the Earth’s crust.  May also fluctuate based on the solar cycle.

17. Team Organization

18. Biggest Worries  Coordinating the acquired data with the time  Finding the magnetic strength with two magnetometers  Constructing a Faraday Cage and determining if needed  Mass

19. Questions?