Brittany Dupre Jason Mueller Jeff Weinell TEAM TOTAL RESISTANCE PRELIMINARY DESIGN REVIEW 1

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Brittany DupreJason MuellerJeff Weinell

TEAM TOTAL RESISTANCE

PRELIMINARY DESIGN REVIEW

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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.

MISSION GOAL

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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.

SCIENCE OBJECTIVES

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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.

SCIENCE BACKGROUND

Figure 1. Change in gravity with increasing altitude

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SCIENCE BACKGROUND

Figure 2. Experimental data from the DUCKY Ia

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Team Total Resistance shall comply with all LaACES requirements.

The payload shall protect internal components from balloon interface conditions and ambient environmental conditions.

TECHNICAL OBJECTIVES

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The position of the payload from a fi xed point on Earth’s surface can be determined by the position of the balloon relative to a fi xed point on Earth and the payload’s position relative to the balloon using the following equation:

To fi nd the acceleration:

TECHNICAL BACKGROUND

y

𝑥

𝑟റ0

𝑟റ

𝑟റ′

Figure 3. Relative position of payload to balloon

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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.


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Accelerometers measure an object’s proper acceleration.

Figure 4. A capacitive MEMS accelerometer design showing the moveable plates and fi xed outer plates

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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

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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

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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.

TECHNICAL REQUIREMENTS

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SYSTEM DESIGN

Figure 7. System Design

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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

SENSORS

Figure 8. A picture of a micro electro-mechanical system (MEMS) ADXL330 accelerometer and finger for size comparison

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Type: LSM303DLHC Magnetometer


Operating voltage: 2 to 4 volts

SENSORS

Figure 9. A LSM303DLHC magnetometer by STMicroelectronics

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Type: PS-MPU-6100A Gyroscope


Operating voltage: 2.4 to 3.5 volts

SENSORS

Figure 10. A PS-MPU-6100 by InvenSense

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SENSOR INTERFACE

Figure 11. Schematic of a capacitive accelerometer

Figure 12. Schematic diagram of type MPU-6100 gyroscope

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Schematic diagram of the LSM303DLHC Magnetometer

Can be programmed by the user using the I²C interface

SENSOR INTERFACE

Figure 13. A schematic of a LSM303DLHC

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Schematic diagram of ADIS16400

Has a 3-axis accelerometer, a 3-axis magnetometer, and a 3-axis gyroscope

SENSOR INTERFACE

Figure 14. An ADIS16400 multi-sensor by iSensor

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POWER BUDGET

Table 1. Power budget.

Device Current Voltage (V)

mA/hr

BalloonSat (microcontroller)

80 mA +9 to +15 320

Accelerometer 500 µA +4 to +6 2

Magnetometer 110 µA +2 to +4 .44

Gyroscope 3.6 mA +2 to +4 14.4

ADC 4 mA 0 to +3 16

Total 89 mA +9 to +15 353

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Functional software flowchart that demonstrates how the software will function.

FLIGHT SOFTWARE DIAGRAM

Figure 15. Flight software diagram

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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.

THERMAL DESIGN

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Isometric view of preliminary hexagonal-prism payload structure

MECHANICAL DESIGN

Figure 16. Isometric view of our payload

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MECHANICAL DESIGN

Figure 18. A schematic of our payload structure

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WEIGHT BUDGET

Table 2. Weight Budget.

Component

Weight Approximation (grams)

BalloonSat

61.5

Sensing Unit

5

Payload Structure

200

Total 266.5

RemainingAllowed

233.5

BalloonSat

Sensing Unit

Payload Structure

Payload Structure 75%

BalloonSat23%

Sensing Unit1.9%

Figure 19. Weight budget pie chart

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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.

PAYLOAD DEVELOPMENT PLAN

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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.


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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.


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RISK MANAGEMENT

Table 3. Identified RisksRisk Event Likelihood

(Low=1, High=5)Impact(Low=1, High=5)

Detection Difficulty

(Low=1, High=5)

When

1 Impact causes damage to payload memory 1 5 1 Flight

2 Payload rotation rate exceeds measuring range of gyroscope

2 4 2 Flight

3 Magnetic interference from other electronic devices causes magnetometer error

2 3 5 Flight

4 Timing between payload and balloon beacon data is not set correctly

1 3 1 Preflight

5 The EEPROM runs out of storage space due to improper calculations of bytes per measurement

2 4 2 Flight

6 Flight is delayed 3 2 1 Preflight7 The power source’s amp-hours are too low 2 4 2 Flight

8 The power source’s current degrades with temperature at an amount that causes an electronic device to fail

2 4 2 Flight

9 The payload is too heavy 1 4 1 Preflight10 The payload gets rained on 2 3 1 Flight

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RISK MANAGEMENT

11 Rapid depressurization causes payload structural damage

1 4 1 Flight

12 Shipping is delayed for parts included in payload design

3 3 3 Preflight

13 Parts included in payload design are no longer manufactured

2 3 1 Preflight

14 Software does not convert between computers

2 2 1 Post Flight

15 All software needed for post analysis is not on a team member’s laptop when we arrive at Palestine, Texas

1 3 1 Post Flight

16 The WFM crashes 2 4 2 Throughout Project

17 Position measurements are not available from ACES management

1 5 2 Post Flight

18 Units are not all converted to International System of Units (SI)

2 5 4 Throughout Project

19 Binary, hexadecimal, etc. language is not translated correctly

2 3 3 Throughout Project

20 The sensing axes are not stable 3 3 2 Flight

21 A team member quits 2 5 3 Throughout Project

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Figure 20. Risk severity matrix

RISK MANAGEMENT

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CONTINGENCY PLAN

Table 4. Contingency PlanRisk Event Response Contingency Plan Trigger Responsibility

1 Impact causes damage to payload memory

Reduce Prepare failure analysis Memory is missing or unreadable

Jeff Weinell

2 Payload rotation rate exceeds measuring range of gyroscope

Reduce Analyze data that are within measuring range

Measurements are at limits of operating range or missing

Brittany Dupre

3 Magnetic interference from other electronic devices causes magnetometer error

Reduce Move the magnetometer to a different position in the payload

Magnetometer does not record correctly during payload testing

Brittany Dupre

4 Timing between payload and balloon beacon data is not set correctly.

Reduce Reset payload to Coordinated Universal Time (UTC)

Verify that the time recorded by the payload matches UTC time

Jason Mueller

5 The EEPROM runs out of storage space due to improper calculations of bytes per measurement

Reduce Memory expansion Less measurements were taken than planned

Jason Mueller

6 Flight is delayed Transfer Be patient Flight time has passed and the balloon is on the ground

ACES Staff

7 The power source’s amp-hours are too low

Reduce Failure Analysis Multimeter displays current that is too low for circuitry to work

Brittany Dupre

8 The power source’s current degrades with temperature at an amount that causes an electronic device to fail

Reduce Failure Analysis The circuitry fails during thermal testing, and multimeter displays current that is too low for circuitry to work

Brittany Dupre

9 The payload is too heavy Reduce Identify methods to reduce weight

The scale reads over 500 grams

Jeff Weinell

10 The payload gets rained on Retain Retrieve usable data The payload is wet ACES Staff

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CONTINGENCY PLAN

11 Rapid depressurization causes payload structural damage

Reduce Rebuild payload with an increase in ultimate stresses

The payload is in multiple pieces as a result of pressure testing

Jeff Weinell

12 Shipping is delayed for parts included in payload design

Retain Work on other tasks The part(s) didn’t show up on time.

Jason Mueller

13 Parts included in payload design are no longer manufactured

Retain Use different parts Customer service says that the part is no longer available

Jason Mueller

14 Software does not convert between computers

Reduce Download software that works

Error message appears Jason Mueller

15 All software needed for post analysis is not on a team member’s laptop when we arrive at Palestine, Texas

Reduce Download software from WFM

The team member informed other members that the software is not on their computer

Jason Mueller

16 The WFM crashes Retain Get the files from ACES computer.

WFM is unavailable ACES Staff

17 Position measurements are not available from ACES management

Transfer Failure analysis ACES Staff informs the groups

ACES Staff

18 Units are not all converted to SI Reduce Change them to SI Calculations errors Jason Mueller 19 Binary, hexadecimal, etc.

language is not translated correctly

Reduce Correct it Program errors Jason Mueller

20 The sensing axes are not stable Reduce Redesign internal structure to stabilize sensing axes

Shock testing and calibration

Jeff Weinell

21 A team member quits Retain Divide tasks amongst remain team members

The team member informs the other members

Remaining group members

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