Team Total Resistance Preliminary Design Review

1. Team Total ResistancePreliminary Design Review Brittany Dupre Jason Mueller Jeff Weinell

2. Mission Goal • Team Total Resistance will build a payload to measure Earth’s gravity field as a function of altitude for heights of up to 100,000 feet (30,480 meters), and compare our findings to theoretical and experimental high altitude gravity models.

3. Science objectives • The payload shall take measurements to show an approximately linear decrease in the relative change of gravitational acceleration as a function of altitude to 30,480 meters. • Team Total Resistance shall analyze data recorded by the payload.

4. Science background • This graph shows the theoretical change in gravity as function of altitude according to Newton’s second law. • As the payload’s altitude increases, we expect to see a slight decrease in gravitational acceleration. Figure 1. Change in gravity with increasing altitude

5. Science background Figure 2. Experimental data from the DUCKY Ia

6. Technical objectives • Team Total Resistance shall comply with all LaACES requirements. • The payload shall protect internal components from balloon interface conditions and ambient environmental conditions.

7. Technical background • The position of the payload from a fixed point on Earth’s surface can be determined by the position of the balloon relative to a fixed point on Earth and the payload’s position relative to the balloon using the following equation: • To find the acceleration: Figure 3. Relative position of payload to balloon

8. Technical background • Team Total Resistance will use coordinates from the GPS receiver that correspond to the position of the ACES balloon at the time each payload measurement is taken. • Team Total Resistance will time stamp each measurement according to hours, minutes, seconds, such that the starting time is synchronized with the clock that ACES staff will use for GPS measurements.

9. Technical background • Accelerometers measure an object’s proper acceleration. • Figure 4. A capacitive MEMS accelerometer design showing the moveable plates and fixed outer plates

10. Technical Background • A 3-axis magnetometer measures the intensity of magnetic flux density along three perpendicular axes. • The payload will obtain measurements to determine the angle between the sensing axis and the direction of gravity. • Digital MEMS magnetometers usually contain temperature sensors and signal conditioning circuitry to correct for temperature bias. Figure 5. A diagram showing how Earth’s core generates a magnetic field

11. Technical background • When the rotor is spinning at high speeds, a gyroscope will remain stable oriented in the same direction independent of its position. Figure 6. A diagram of different parts of a mechanical gyroscope

12. Technical requirements • Team Total Resistance shall comply with all LaACES requirements. • The payload shall take enough measurements to show a trend in the relative change of gravitational acceleration as a function of altitude. • The payload shall take measurements in order to calculate relative gravitational acceleration changes to a minimum accuracy of . • Team Total Resistance shall analyze data recorded by the payload.

13. System design Figure 7. System Design

14. sensors • Type: MXC6226XC MEMS Accelerometer • Size: 1.2 mm x 1.7 mm x 1.0 mm • Temperature range: -20 to 70 degrees Celsius • Operating voltage: 2.5 to 5.5 volts Figure 8. A picture of a micro electro- mechanical system (MEMS) ADXL330 accelerometer and finger for size comparison

15. sensors • Type: LSM303DLHC Magnetometer • Temperature range: -40 to 85 degrees Celsius • Operating voltage: 2 to 4 volts Figure 9. A LSM303DLHC magnetometer by STMicroelectronics

16. sensors • Type: PS-MPU-6100A Gyroscope • Temperature range: -40 to 85 degrees Celsius • Operating voltage: 2.4 to 3.5 volts Figure 10. A PS-MPU-6100 by InvenSense

17. Sensor interface Figure 11. Schematic of a capacitive accelerometer Figure 12. Schematic diagram of type MPU-6100 gyroscope

18. Sensor interface • Schematic diagram of the LSM303DLHC Magnetometer • Can be programmed by the user using the I²C interface Figure 13. A schematic of a LSM303DLHC

19. Sensor interface • Schematic diagram of ADIS16400 • Has a 3-axis accelerometer, a 3-axis magnetometer, and a 3-axis gyroscope Figure 14. An ADIS16400 multi-sensor by iSensor

20. Power budget

21. Flight software diagram • Functional software flowchart that demonstrates how the software will function. Figure 15. Flight software diagram

22. Thermal design • Our payload must function within an ambient temperature range of -60 to 38 degrees Celsius. • The payload structure will be made out of polystyrene. • We will use Gorilla Glue as the polystyrene and wood adhesive.

23. Mechanical design • Isometric view of preliminary hexagonal-prism payload structure Figure 16. Isometric view of our payload

24. Mechanical Design Figure 18. A schematic of our payload structure

25. Weight budget Figure 19. Weight budget pie chart

26. Payload development plan • Software Design Development • The software shall be written to perform the required tasks. • The software shall be run and tested on the BalloonSat. • Revisions to the software will be made is bugs are found.

27. Payload development plan • Electrical Design Development • We shall test and calibrate all chosen sensors. • Each sensor shall go through temperature and pressure testing. • After testing is completed, the circuitry must be completed for each sensor. • A complete power budget will be completed.

28. Payload development plan • Mechanical Design Development • The amount of payload insulation, payload volume, and weight distribution all depend on the choice of sensors. • We will calculate theoretical ultimate stress values for the payload. • The dimensions of the payload will be determined by preliminary circuit design and weight requirements dictated by ACES. • We will determine how the top of the payload is going to remain closed.

29. Risk management

30. Risk management

31. Risk management Figure 20. Risk severity matrix

32. Contingency Plan

33. Contingency Plan

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38. Questions?