TEAM NAPOLEONLaunch Readiness Review

Connor Strait, Chris Gray, Chad Alvarez, Akeem Huggins, Ashley Zimmer, Tucker Emmett, Ginny Christiansen , Caleb Lipscomb

Tuesday, November 26, 2012

Mission Overview

Our Mission is to prove that 3D imaging is possible for small objects close to the camera in space, and that 3D imaging is not viable for large, distant objects in space.

Design Overview

Our satellite consists of a structure made of foam core, with four plastic viewing ports on the front and top of the structure, and a heater.

Our satellite contains two Arduinos The 1st Arduino has our External Temperature sensor,

internal temperature sensor, humidity sensor, pressure sensor, and accelerometer

The 2nd Arduino has a gyroscope and controls our camera rig motor

Our satellite also contains two identical Canon Cameras used for 3D imaging and a GoPro for HD film

Structure

Heater

Warm

1st Arduino Environmental Sensors

2nd Arduino

Gyroscope and Motor

Canon Cameras and Rig Not a Pepsi Advertisement

GoPro Camera

3D image testing

We took images with the Canon cameras of known objects close to the cameras over an hour long period. We then attempted to create 3D images from these images Cameras were successfully synced, and took

pictures at the same time We successfully created 3D images We were also able to make a 3D video

2D image

3D imageLooks cooler with 3D glasses

Functional Testing

We ran all of our sensors in 3 different controlled environments in order to calibrate our environmental sensors. We subtracted the average value our sensors

read during the test from the actual environmental value of the room.

Our final test was in a room of 18 degrees C, a humidity of 35%, and a pressure of 14.673 psi The accelerometer was placed on a flat

surface with the z-axis pointing up

Accelerometer

Results: Our accelerometer is still a small percentage

off actual readings X-axis reads about .2 g high Y-axis reads about .16g high Z-axis reads about .06 g high The results of this final test will be used to

calibrate the accelerometer sensors one more time, and they will be tested again before the flight.

Accelerometer (g)

371 29489 58748 87869 1170281462991754732047512339022630432921853213443506303797730

0.05

0.1

0.15

0.2

0.25

0.3

AccelX (g)

AccelX (g)

Accelerometer (g)

371 33904 67572 1011161347011684062020852356612692243027903364853700620

0.05

0.1

0.15

0.2

0.25

AccelY (g)

AccelY (g)

Accelerometer (g)

371 29489 58748 87869 1170281462991754732047512339022630432921853213443506303797730.96

0.98

1

1.02

1.04

1.06

1.08

1.1

1.12

AccelZ (g)

AccelZ (g)

Pressure sensor

Our pressure sensor is fairly accurate, reading about .2 psi low during the test. We will use this data to make a final

calibration to our sensor. The change in the values of the pressure

sensor in a room of constant pressure showed that our sensor is accurate to about +-.04 psi.

Pressure (psi)

371 31262 62290 93174 12409115513618619521711224802827893230985034090237181814.39

14.4

14.41

14.42

14.43

14.44

14.45

14.46

14.47

Pressure (psi)

Pressure (psi)

Temp Sensors

Our internal temperature sensor was very accurate during the test, reading between 17.5 C and 18.5 for the duration of the test

Our external temperature sensor read about 1.7 degrees C high for the test, and will be calibrated to solve this error.

Internal Temperature Sensor

371 31262 62290 93174 12409115513618619521711224802827893230985034090237181816.5

17

17.5

18

18.5

19

19.5

Thermo (Deg C)

Thermo (Deg C)

External Temperature Sensor

371 31262 62290 93174 12409115513618619521711224802827893230985034090237181819.5

19.55

19.6

19.65

19.7

19.75

19.8

19.85

OneWire(Deg C)

OneWire(Deg C)

Humidity Sensor

Our humidity sensor performed well during the test, reading at about 35% for the duration of the test

Humidity

371 29489 58748 87869 1170281462991754732047512339022630432921853213443506303797730

5

10

15

20

25

30

35

40

45

Humidity (%)

Humidity (%)

Gyroscope

To test our Gyroscope, we rotated the gyro about each axis individually 180 degrees in one second. We also recorded the reading of our gyroscope on a flat surface while not moving

We used the results of this test to calibrate our gyroscope

We are not yet able to write our gyroscope’s data to an SD card.

Cold Test

We placed our satellite in a cooler filled with dry ice for an hour and a half and ran all of our sensors.

Our satellite remained above -10 degrees C the entire test, reaching a max temperature of 35 degrees C

Cold Test

5819 479482 953398 1427381190164523757592849976332384037977404272094474625452205700

5

10

15

20

25

30

35

40

Thermo (Deg C)

Thermo (Deg C)

Structure Test

Drop Test: Thrown off bridge between DLC and ITLL

Stair Test: Thrown a flight of stairs at down Stairs at DLC

Results: Sides of Structure held up well. One corner did break open, not enough hot

glue was used. Problem solved by applying hot glue to

outside of corners as well as inside

Whip Test

Box whipped around Tucker’s head at a high velocity for 3 minutes

Results: Main Structure survived Flight tube became loose during test Problem solved by applying more hot glue

secure the flight tube and by correct placement of paper clips in tube

Whip Test

Predicted Flight Results

We expect to successfully take 3D images of close up objects (other satellites, the balloon) but not of distant objects (the earth, mountains on the earth, the sun, ect.)

We expect all of our sensors to successfully collect and record data to the SD cards.

We expect our satellite’s internal temperature to remain about -10 degrees C for the entire flight.

Worries/Concerns

Cameras remaining in sync for the entire flight

Camera rig not rotating correctly

Requirements# Mission Objectives, Level 0 Requirements. Origin

0 Test ability to produce 3D images in a near space environment.

Mission Statement

1 Determine attitude and rotation of our satellite during the entire flight.

Mission Statement

2 Our Satellite shall reach an altitude of 30 km. RFP

3 Keep total weight under 1125g and total money spent $250.

RFP

4 Keep internal temperature of Satellite above -10 C.

RFP

5 Record environmental variables. RFP

6 Ensure the safety of all members of the team. RFP

7 Balloon Sat must be able to fly again. RFP

Level 0 Requirements

Requirements# Objective 0, Level 1 Reference #

0.1 Satellite Shaniqua shall fly two Cannon SD 780 cameras side by side to capture “3D” images.

0

0.2 Shaniqua shall fly a GoPro to capture standard 2D video.

0

0.3 The two cameras and GoPro shall be connected by a miniB USB cable that will sync the timers on

the camera hardware and software before the fight to take pictures automatically during the

duration of the flight.

0

0.4 The Cannon Cameras and GoPro shall be attached to a mechanism that shall rotate the

cameras 90 degrees 25 minutes prior to balloon burst.

0

Level 1 Requirements

Requirements

# Objective 2, Level 1 Reference #

2.1 Our satellite Shaniqua shall be attached to a hydrogen balloon that shall carry our satellite to

an altitude of 30km.

2

2.2 Shaniqua shall be attached to a rope that is connected to the Balloon via a tube running

through the center of our satellite.

2

2.3 Shaniqua shall use washers and clips to keep it stable on the rope.

2

# Objective 1, Level 1 Reference #

1.1 Satellite Shaniqua shall fly a Gyroscope that will collect data continuously for the entire duration

of the flight.

1

1.2 The data collected by the gyroscope shall be recorded and used to determine our satellite’s

attitude and spin rate.

1

Requirements

# Objective 3, Level 1 Reference #

3.1 A weight budget shall be kept and updated weekly to ensure our satellite shall weight less

than 1125g.

3

3.2 A cost budget shall be kept and updated weekly to ensure our satellite cost does not

exceed $250.

3

# Objective 4, Level 1 Reference #4.1 Our Satellite shall have an internal heater

powered by 9V batteries that shall heat the satellite for the duration of the flight.

4

4.2 Our satellite shall have ½ inch foam insulation on the interior of the structure.

4

Requirements # Objective 5, Level 1 Reference #

5.1 Our Satellite shall have an external and internal temperature sensor that shall continuously collect data for the duration of the flight.

5

5.2 Our satellite shall have a pressure sensor that shall continuously collect external pressure data

for the duration of the flight.

5

5.3 Our satellite shall have an internal humidity sensor that shall collect data continuously for

the duration of the flight

5

5.4 Our satellite shall have a 3 axis accelerometer that shall collect data continuously for the

duration of the flight.

5

5.5 All data collected from the temperature sensors, pressure sensor, humidity sensors, and

accelerometer shall be stored on a 2 GB SD card.

5

5.6 Data collected form the temperature sensor, pressure sensor, and accelerometer shall be

used to determine the altitude of our satellite as a function of time.

5

Requirements

# Objective 6, Level 1 Reference #6.1 Construction and Soldering equipment shall be used

only in the proper manner and for the direct purpose of constructing our satellite.

6

6.2 All construction equipment and soldering tools shall be properly stored.

6

# Objective 7, Level 1 Reference #7.1 The structure of our satellite shall be made of

foam core and shall be held together using aluminum tape and hot glue.

7

7.2 Our satellite’s structure shall remain intact during the entire flight, including the ascent,

the balloon burst, the descent and

7

7.3 All of our satellite’s sensors, cameras, and Arduino boards shall be functioning during the

duration of the flight and after landing.

7

End