Zachary Cuseo, Sydni Smith, Andrew Fruge’, Tyler Knappe, Christopher Nie,

and Shweta Maurya

8 October 2009

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.

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

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 Structureo   AVR microcontrollero   Power systemo   Camerao   Heater

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.

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.

Design

Design

Functional Block Diagram

Monetary BudgetComponent Purchase Location Quantity Unit Cost

Magnetic Field SensorVernier Software and Technology 2 $58.00

Analog Proto Board ConnectorVernier Software and Technology 2 $10.00

ShippingVernier Software and Technology 2 $15.64

Flight Batteries Provided 4 Provided

Foam Core Provided 3 Provided

Temperature Cable Provided 1 Provided

AVR Microcontroller Board Provided 1 Provided

Switches Provided 2 Provided

Heater Provided 1 Provided

Aluminum Tape Provided 1 Provided

Adhesive (Hot Glue Sticks) Provided 10 Provided

Additional Materials Local Stores   ~ $16.36

Total Cost     $183.64

Mass BudgetComponent Purchase Location

Item Code

Quantity

Single Item Mass (grams) Sum (grams)

Magnetic Field Sensor*Vernier Software and Technology MG-BTA 2 69.2 138.4

Analog Proto Board Connector*Vernier Software and Technology BTA-ELV 2 5.6 11.2

Camera with Batteries* Provided 1 228.5 228.5

HOBO Provided 1 30 30

AVR Microcontroller Board, Heater, Power Connectors, and Switches* Provided 1 117.1 117.1

9V Batteries* Provided 4 46.7 186.8

Washers* Provided 2 14.9 29.8

Paper Clips* Provided 2 1.2 2.4

American Flag Provided 1 1 1

Foam Core Structure Provided 1563

cm2 98.6 98.6

Tape, Glue, etc. Provided as

needed 6.2 (remaining weight) 6.2

Total 850

*all weights measured for our actual components

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.

Proposal RequirementsRequirement Compliance

Science Measuring Earth’s magnetic field with respect to altitude changes

Analog sensor inputs cannot exceed 5v Provided 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 850g Mass 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 HOBO Provided, set-up, and accounted for in mass and design

External Temperature Cable ProvidedAVR Microcontroller Board and Batteries – 150g Provided, set-up, and accounted for in mass and design

Heater - 100g Provided, set-up, and accounted for in mass and design

Canon Digital Camera - 220g Provided, to be set-up, and accounted for in mass and design

Foam Core Provided and is being used for the external structure

Allowance for spare parts on budget and parts list Some money has been allotted within the budget for spare parts

U.S. Flag and Contact info on outside Provided and will be attached on external structure

Keep documents and design in metric Design 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 days Additional 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 payload No living things are being used in the experiment, or in the payload

Complete final report with bonus video The team plans to make a video and complete report on time

Test Plan Structural Testing

Drop test, Whip test, Stair test, and the Kick testComplete on 10/11 – at latest by 10/16

Magnetometer TestingConnect magnetometers to AVR and measure in

different positionsTest the effect or interference of electronics in the

presence of the MagnetometersComplete by 10/12

Internal TestingCold test, functional test (flight duration), structural

securityComplete on 10/18 – at latest by 10/25

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.

Potential Problems

Magnetic field may fluctuate due to the composition of the Earth’s crust.

May also fluctuate based on the solar cycle.

Team Organization

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

Questions?