EXPERIENCE GAINED IN CLTP7

Mohammed Khalil Ibrahim, Ph.D.

mkhalil@cu.edu.eg

Cairo University - Egypt

OUTLINE

Objectives

Timeline

The i-CanSat Assembly

Recovery System

Testing (Drop, Mechanical, and Thermal)

Launching

Results

Conclusions

Further Developments

OBJECTIVES

Experience the teaching method used in CLTP7.

Collect participants’ feedback about the i-CanSatmanual.

Propose improvements to i-CanSat-6 kit.

TIMELINE

Day 1

21.9.16

Day 2

22.9.16

Day 3

23.9.16

Day 4

24.9.16

Day 5

25.9.16

Day 6

26.9.16

Day 7

27.9.16

Day

28.9.16

Day 9

29.9.16

Day 10

30.9.16

Day 11

1.10.16

- Orientation

- i-CanSat Assembly

- Orientation

- Introductory Presentation

- i-CanSat Assembly

- Continuity test

- GPS Configuration

- Xbee Configuration

- Cancam operation

- General operation

- Google Map & GPS data

- Parachute fabrication

- Drop test

User board Assembly

- Testing

- User board Development

Sapporo

Sightseeing

- Move to Akabira

- Paper rocket Fabrication

- Paper rocket Fabrication

- First Launch

Final

Presentation

- Second Launch

- Presentation Preparation

I-CANSAT

i-CanSat: Structure & Parachute

USR PCB i-CanSat

RECOVERY SYSTEM

1

2

3

PARACHUTE TESTING

First test with dummy load: Failed

Second test with dummy load: passed

TEMPERATURE TESTING

-5

0

5

10

15

20

25

30

35

40

45

0 500 1000 1500 2000 2500 3000 3500

Tem

per

atu

re [

Co]

Time [seconds]

Actual Air Temperature

Set Temperature

i-CanSat Temperature Sensor Reading

VIBRATION TESTING

Sine wave vibration

Random vibration

Shock vibration

VIBRATION GENERATOR

EMIC 916-AW/LA

SINE CHARACTERSITICS

1

10

100

1000

1 1.5 2 2.5 3 3.5 4

m/s^2

wave

Actual [m/s^2]

Target [m/s^2]

Upper Alarm Limit [m/s^2]

Lower Alarm Limit [m/s^2]

Upper Abort Limit [m/s^2]

Lower Abort Limit [m/s^2]

Frequency = 10 Hz

RANDOM CHARACTERISTICS

-52.50645

-32.50645

-12.50645

7.4935455

27.493546

47.493546

0 0.05 0.1 0.15

m/s^2

sec1E-04

0.001

0.01

0.1

1

1 10 100 1000 10000

(m/s^2)^2/H

z

Hz

Target [(m/s^2)^2/Hz]

Actual [(m/s^2)^2/Hz]

Reading [(m/s^2)^2/Hz]

Upper Alarm Limit [(m/s^2)^2/Hz]

Lower Alarm Limit [(m/s^2)^2/Hz]

Upper Abort Limit [(m/s^2)^2/Hz]

Lower Abort Limit [(m/s^2)^2/Hz]

Measured acceleration

SHOCK CHARACTERISTICS

-94.2

-74.2

-54.2

-34.2

-14.2

5.8000031

25.800003

45.800003

65.800003

85.800003

0.1411406 0.1461406 0.1511406 0.1561406 0.1611406

m/s^2

sec

8msec8G

Target [m/s^2]

Lower Limit [m/s^2]

Upper Limit [m/s^2]

Actual [m/s^2]

ACCELEROMETER READINGS

-2.5

-2

-1.5

-1

-0.5

0

0.5

1

1.5

2

2.5

0 50 100 150 200 250 300 350 400

Acc

ele

ration [g

]

Time [seconds]

X-axis Y-axis Z-axis

Sine Random Shock

LAUNCHING

1 2

3 4

LAUNCHING

GPS RESULTS – FIRST LAUNCH (29.09.2016)

GPS – 3D RESULTSLongitude: 141.999802

Latitude: 43.579588

Altitude: 234.580 ft

Speed: 3.7 mph

Heading: 16.6

IMAGES – FIRST LAUNCH (29.09.2016)

ACCELEROMETER RESULTS– FIRST LAUNCH (29.09.2016)

-1.5

-1

-0.5

0

0.5

1

1.5

2

0 100 200 300 400 500

Acc

eler

atio

m [

g]

Time [seconds]

X-Axis

Y-Axis

Z-Axis

Flight Portion

ACCELEROMETER RESULTS– FIRST LAUNCH (29.09.2016)

-1.5

-1

-0.5

0

0.5

1

1.5

2

0 20 40 60 80

Acc

eler

atio

m [

g]

Time [seconds]

X-Axis

Y-Axis

Z-Axis

LaunchTouch Down

Separation

Parachute

Deployment

GYROSCOPE RESULTS– FIRST LAUNCH (29.09.2016)

-2000

-1500

-1000

-500

0

500

1000

1500

2000

2500

3000

0 20 40 60 80

Ang

ula

r Ra

te d

eg

/se

c.

Time [seconds]

G1

G2

Launch

FIRST LAUNCH: SPINNING

PRESSURE SENSOR RESULTS– FIRST LAUNCH (29.09.2016)

-50

0

50

100

150

200

250

300

350

965

970

975

980

985

990

995

1000

1005

1010

0 20 40 60 80

Altitude

[m]

Pre

ssure

[H

ecto

Pa]

Time [seconds]

Pressure Altitude [m]

19.0

25.1013144330][

pmh

GPS RESULTS – SECOND LAUNCH (30.09.2016)

GPS – 3D RESULTS

Longitude: 142.000090

Latitude: 43.580445

Altitude: 330.381 ft

Speed: 26.2 mph

Heading: 172.1

IMAGES – SECOND LAUNCH (30.09.2016)

ACCELEROMETER RESULTS– SECOND LAUNCH (30.09.2016)

-5

-4

-3

-2

-1

0

1

2

0 50 100 150 200

Acc

eler

atio

m [

g]

Time [seconds]

X-Axis

Y-Axis

Z-Axis

GYROSCOPE RESULTS– SECOND LAUNCH (30.09.2016)

-2500

-2000

-1500

-1000

-500

0

500

1000

1500

2000

2500

0 50 100 150 200

Ang

ula

r Ra

te d

eg

/se

c.

Time [seconds]

G1

G2

PRESSURE SENSOR RESULTS– SECOND LAUNCH (30.09.2016)

-150

-100

-50

0

50

100

1000

1005

1010

1015

1020

1025

1030

0 50 100 150 200

Altitude

[m]

Pre

ssure

[H

ecto

Pa]

Time [seconds]

Pressure Altitude

CONCLUSIONS

i-CanSat Assembly, Integration and Testing (AI&T)

Launching and Operation: Complete Cycle

Hands-on Training Project: Low cost and short time Parachute

Paper rocket

Hardware & Firmware development skills Soldering, GPS & XBEE configurations.

PIC programming

Sampling time.

Project Based Education Rocket spinning

Parachute deployment

FURTHER DEVELOPMENT

Manual Revision with improved software content

External Power Supply

PIC Limitation (USR board Development)

Testing: Modal Analysis Experiments

Sensor Calibration

ACKNOWLEDGEMENT

UNSEC Ms. Rei Kawashima

Mr. Michio Ozawa

Hokkaido University Prof. Tsuyoshi Totani

Mr. Tomohiro Takanashi

Mr. Ryohei Goto

Mr. Jyunya Sato

Mr. Delburg MITCHAO

Nihon University Prof. Yasuyuki Miyazaki

Uematsu Electric Co.,Ltd

Sakura Rubber Co., Ltd. Mr. Tetsuya Iwasaki

CLTP participants & alumini

Thank you

Questions?