cansat 2019 post flight review (pfr) outlinecansat 2019 pfr: team 6160 | grizu-263 6 cansat overview...

Team Logo

Here

(If You Want)

Team Logo

Here

CanSat 2019 PFR: Team 6160 | grizu-263 1

CanSat 2019

Post Flight Review (PFR) Outline

Version 1.1

Team # 6160

grizu-263

Team Logo

Here

(If You Want)

Team Logo

Here


Presentation Outline

Presenter: Senanur SAMUR

Contest Presenter

Introduction Senanur SAMUR

System Overview Senanur SAMUR

Concept of Operations and Sequence of

Events

Senanur SAMUR

Flight Data Analysis Sedef ÖZEL

Failure Analysis Sedef ÖZEL

Lessons Learned Sedef ÖZEL

Conclusions Sedef ÖZEL

Team Logo

Here

(If You Want)

Team Logo

Here


Introduction

Senanur SAMUR

Team Logo

Here

(If You Want)

Team Logo

Here


Team Organization


Team Logo

Here

(If You Want)

Team Logo

Here


Systems Overview

Senanur SAMUR

Team Logo

Here

(If You Want)

Team Logo

Here


CanSat Overview (1 of 3)


Mission

CanSat is an auto-gyro controlled container that protects the electronic part and protects the

payload.

Mission Objectives

• CanSat consists of 2 parts: payload and container.

• Container protects the payload that will perform the desired mission.

• The launched CanSat will leave the rocket at an altitude of 670 to 725 m.

• CanSat will go down to 450 m with a speed of 20 m/s via the parachute .

• The container will be separated from the auto-gyro controlled payload after 450 m.

• The container will descent via parachute after separation.

• Auto-gyro's descent speed will be 10 to 15 m/s.

• The auto-gyro rotates passively during descent.

• When going under the control of payload auto-gyro, the payload will transmit telemetry,

which will include air pressure, outside temperature, battery voltage, GPS position, pitch

and roll, auto-gyro blade spin rate.

• After the landing, the payload will be stopped telemetry transmission and starts to give

warning sound and light.

Team Logo

Here

(If You Want)

Team Logo

Here




Bonus Objective

• The camera will be integrated into the payload. After released payload from the container (450

meters), the camera will start to record video.

• The camera shall point downward 45 degrees from nadir. It shall be spin stabilized and point in

one direction relative to the earth’s magnetic field with stability of +/- 10 degrees.

• The video camera resolution will be at least 640x480 pixels and will be colored to 30 frames per

second.

External Objective

• Our goal is to be among the top three in CanSat 2019.

• We have gained an acceptable experience with CanSat Competition and started a new national

project to design and produce Turkey's first PocketQube satellite.

• PocketQube will be dimensions of the 5x5x5 cm.

• It will be placed in orbit at an altitude of about 500 km.

• PocketQube and CanSat internet address:

– https://x.grizu-263.space/

– https://grizu-263.space/cansat/

https://grizu-263.space/cansat/

Team Logo

Here

(If You Want)

Team Logo

Here




Mechanic

• Total CanSat weight is 496 grams. The weight requirement successfully

was provided.

• There is no damage on the container end of the launch. However we

couldn’t find our payload.

Separation

• First separation; the CanSat separated from the rocket at an altitude 690 m.

• Second separation; the payload separated from the container at an altitude

461 m.

Data Transfer

• Total flight time of CanSat is 1 min 24 sec .(From rocket launch to reaching

to ground again). While this time, 69 data packet reach to the ground

station.

GCS interface

• 69 data packet plotted in real-time and saved to the .csv file.

Team Logo

Here

(If You Want)

Team Logo

Here


Payload Design Description (1 of 6)


Design of Payload

• Height: 250 mm

• Diameter: 80 mm

• Weight: 268 g

• Construction materials: fiberglass, epoxy

• Payload is flourosent orange

Team Logo

Here

(If You Want)

Team Logo

Here




• We put switch out of the payload. In this way we could easily open and close the

electronic circuit.

• We used zipper on the payload for easy accessible to batteries.

• We attached flaps for not to rotation of payload.

• We used bearing for easy rotation to Propellers.

Team Logo

Here

(If You Want)


10 DOF-IMU

Teensy 3.6

Batteries

GPSHall Effect

Sensor

Camera

Payload On/Off Switch

CanSat 2019 PFR: Team 6160 | grizu-26311


XBee

Antenna

Bar Magnet

Buzzer

Major Electronical Parts

Digital Compass

Team Logo

Here

(If You Want)

Team Logo

Here




• The system started with payload switch.

• We have successfully measured altitude, air pressure, air temperature, battery voltage, pitch and

roll via payload electronic circuit.

• We used GPS and buzzer for find payload location.

• We used SQ11 camera .

• We have successfully measured auto-gyro blade spin rate data via hall effect sensor.

Team Logo

Here

(If You Want) Payload Design Description (5 of 6)

13CanSat 2019 PFR: Team 6160 | grizu-263Presenter: Senanur SAMUR

Major Mechanical Parts

PropellersBearings

Zipper

Axle

Flaps

Team Logo

Here

(If You Want) Payload Design Description (6 of 6)

14CanSat 2019 PFR: Team 6160 | grizu-263Presenter: Senanur SAMUR

• Propellers Diameter: 80 mm

• Weight: 24 g

• Auto-gyro propeller material is carbon fiber

and axle material is carbon fiber stick.

Propellers Folding Mechanism

We used fabric elastic stretched. The auto-gyro system is successfully opened and closed. In this

way we placed the payload in the container.

Fabric elastic

stretched

Closed position hinge

Opened position hinge

Team Logo

Here

(If You Want)

Team Logo

Here


Container Design Description (1 of 5)


Design of Container

• Height: 310 mm

• Diameter: 120 mm

• Weight: 228 g

• Total mass budget: 496 g (requirement successfully provided)

• Construction materials: fiberglass, epoxy

• Container is flourosent orange

120 mm

310 m

m

Team Logo

Here

(If You Want)

Team Logo

Here




RELEASE METHOD

• The burn of wire method worked at an

altitude 461 meters in the container.

• In this way, container bottom cover opened.

• The burn of wire pulls a current of 1.4 A.

• The fishline breaks under a second.

• Separation successfully was completed.

Team Logo

Here

(If You Want)

Team Logo

Here




Clamp

Container on/off switch

SD Card Module

Major Electrical Parts

Arduino Nano

Buzzer

Buzzer

Battery

Fishline

burn of wire

Team Logo

Here

(If You Want)

Team Logo

Here




• The system started with container switch.

• We have successfully measured altitude and air pressure via container

electronic circuit.

• Buzzer activated at last 5 meters so we found container.

Buzzer

Team Logo

Here

(If You Want)

Team Logo

Here




Parachute

Hinges

Container on/off switch

Hinge

Switch hole

(for payload)

Major Mechanical Parts

• Parachute materials: Silnylon 30D Nylon 66

Team Logo

Here

(If You Want)

Team Logo

Here


Cost of CanSat <$1000 (1 of 4)


Electronics Hardware

Team Logo

Here

(If You Want)

Team Logo

Here




Mechanics Hardware

Team Logo

Here

(If You Want)

Team Logo

Here




CanSat Requirement Cost – Exact Total = Margin

$1000 - $253.75 = $746.25

Team Logo

Here

(If You Want)




Bulent Ecevit University met the money needed for

CanSat to produce grizu-263. We have completed

sponsorship negotiations for travel and all other

necessary expenses. All agreements will be approved

for acceptance into the competition. We will not have a

problem this year in terms of the budget.

Other Cost

Team Logo

Here

(If You Want)

Team Logo

Here


Concept of Operations and Sequence

of Events

Senanur SAMUR

Team Logo

Here

(If You Want)

Team Logo

Here


Comparison of Planned and Actual

Con-Ops (1 of 3)


Planned Con-OPS Actual Con-OPS

Pre

-la

un

ch

Set-up ground station system. Set-up ground station system.

We will have a powerbank for a cooling fan. We will have a powerbank for a cooling fan.

The payload system will be calibrated with

the command sent from the ground station.

The payload system will be calibrated with the

command sent from the ground station.

Communication tests. Communication tests.

Check of mechanical systems. Check of mechanical systems.

Sensors will be calibrated. Sensors will be calibrated.

We will use an umbrella in the area. We will use an umbrella in the area.

Team Logo

Here

(If You Want)

Team Logo

Here



Con-Ops (2 of 3)



La

un

ch

CanSat placed into the rocket. CanSat placed into the rocket.

Rocket launch. Rocket launch.

The electronic system will start sending data. The electronic system will start sending data.

CanSat separated from the rocket (between 670-

725 meters).

CanSat separated from the rocket

(between 670-725 meters).

The parachute will be opened. The parachute will be opened.

The speed up to 450 m is 20 m/s. The speed approximately 10 m/s.

The release of the payload at 450 m. The release of the payload at 450 m.

The payload will descent passively with

the propellers

The payload will descent passively with

the propellers.

The payload speed will be between 10 to 15 m/s. The payload speed will be between 10 to

15 m/s.

The camera starts to record video at 450 meters -

The buzzer will be activated in 5 meters and

telemetry data stops.

Couldn’t found the payload.

Team Logo

Here

(If You Want)

Team Logo

Here



Con-Ops (3 of 3)



Po

st-

lau

nc

h

The location of the payload will be find via GPS

and buzzer.

The location of the payload will be find via

GPS and buzzer.

The location of the container will be find via

buzzer.

The location of the container will be find via

buzzer.

We will take the SD card from the payload and

container.

We will take the SD card from the payload

and container.

Take video recording. -

To analyze the data. To analyze the data.

Delivery of received data to the jury. Delivery of received data to the jury.

Preparation for PFR. Preparation for PFR.

Team Logo

Here

(If You Want)

Team Logo

Here



SOE (1 of 2)


Planned SOE Actual SOE

Arr

ival Check launch and CanSat. Check launch and CanSat.

Arrival at the launch location. Arrival at the launch location.

Set up of ground station System. Set up of ground station System.

Pre

-lau

nc

h

Software calibration command will send by

GS.

Software calibration command will send

by GS.

Checking size and weight of CanSat (MCO). Checking size and weight of CanSat (MCO).

Check communication (GSC). Check communication (GSC).

Camera calibration according to the magnetic field

of the North earth.

Camera calibration according to the magnetic

field of the North earth.

Check propeller(CC). Check propeller(CC).

Check separation mechanism (CC-GSC). Check separation mechanism (CC-GSC).

Drop test(MCO-GSC-CC). Drop test(MCO-GSC-CC).

Check safety (MCO). Check launch and CanSat.

La

un

ch

Launch Launch

Team Logo

Here

(If You Want)

Team Logo

Here



SOE (2 of 2)


Planned SOE Actual SOE

Fli

gh

t

rec

ove

ry

Payload we’ll take the SD card and back

up video on GSC.

-

Get backed up telemetry data from SD card.

Get backed up telemetry data from SD card.

Delivery of received data to the jury . Delivery of received data to the jury .

Data

an

aly

sis

Check camera data. -

Checking and backing up telemetry dataplot outliers.

Checking and backing up telemetry data plotoutliers.

Check of real-time graphics. Check of real-time graphics.

Po

st

Fli

gh

t

Re

vie

w

Preparation of post-flight review

presentation file.

Preparation of post-flight review presentation

file.

Delivery of the PFR file to the Jury. Delivery of the PFR file to the Jury.

Explaining the PFR file to other participants.

Explaining the PFR file to other participants.

Team Logo

Here

(If You Want)

Team Logo

Here


Flight Data Analysis

Sedef ÖZEL

Team Logo

Here

(If You Want)

Team Logo

Here


Container Separation Altitude

Presenter: Sedef ÖZEL

Container separation

successfully was

completed at an altitude

461 meters

-200

-100

0

100

200

300

400

500

600

700

800

0 200 400 600 800 1000 1200 1400 1600

Altitude

(m)

Second (s)

Altitude

The burn of wire

method

successfully was

worked in the

container.

Team Logo

Here

(If You Want)

Team Logo

Here


Payload Pressure Sensor Data Plot


Pressure

decrease with

altitude

88000

89000

90000

91000

92000

93000

94000

95000

96000

97000

00:19:18 00:19:35 00:19:52 00:20:10 00:20:27 00:20:44 00:21:01

Pre

ssure

(Pa)

Mission Time (s)

Pressure

Team Logo

Here

(If You Want)

Team Logo

Here


Payload Altitude Plot (1 of 2)


• Altitude shown on column ‘D’ and software state shown on column ‘P’

• Altitude has been identified as 463 meters when separation occurs and software state

shown as ‘4’

• As seen on data from the chart separation occurs at an altitude 453 meters.

Team Logo

Here

(If You Want)

Team Logo

Here

-100

0

100

200

300

400

500

600

700

800

900

00:19:18 00:19:35 00:19:52 00:20:10 00:20:27 00:20:44 00:21:01

Altitude

(m)

Mission Time (s)

Altitude


Payload Altitude Plot (2 of 2)


Payload

average speed

is 12.34 m/s

Separation

altitude is 453

meters

Team Logo

Here

(If You Want)

Team Logo

Here


Payload Temperature Sensor Plot


The CanSat is

heated inside

rocket to around

48 °C.

The CanSat cools

down naturally

when exposed to

open air flow

47.7

47.75

47.8

47.85

47.9

47.95

48

00:19:18 00:19:35 00:19:52 00:20:10 00:20:27 00:20:44 00:21:01

Tem

pera

ture

(°C

)

Mission Time (s)

Temperature

Team Logo

Here

(If You Want)

Team Logo

Here


Payload GPS Plot (1 of 2)


-98.2002

-98.2

-98.1998

-98.1996

-98.1994

-98.1992

-98.199

-98.1988

-98.1986

-98.1984

-98.1982

-98.198

32.238 32.239 32.24 32.241 32.242 32.243 32.244 32.245 32.246

Lo

ng

itu

de

Latitude

GPS

Team Logo

Here

(If You Want)

Team Logo

Here


Payload GPS Plot (2 of 2)


Launch

Pad

1

2

Last GPS

location

About 437 m

32.240963, -98.199959

32.244724, -98.199959

Team Logo

Here

(If You Want)

Team Logo

Here


Payload Battery Power Plot


Battery power

average value

is 3.7 V.

2

2.5

3

3.5

4

00:19:18 00:19:35 00:19:52 00:20:10 00:20:27 00:20:44 00:21:01

Battery

Voltage

(V)

Mission Time (s)

Battery Voltage

The camera

was active, so

it drew current

from the

battery and

peaked.

Team Logo

Here

(If You Want)

Team Logo

Here


Tilt Sensor Plot (1 of 2)


The auto-gyro

system was +/- 20

degrees wobble

around according

to X-Axis.

-450

-400

-350

-300

-250

-200

-150

-100

-50

0

00:19:18 00:19:35 00:19:52 00:20:10 00:20:27 00:20:44 00:21:01

Pitch (

°)

Mission Time (s)

X-Axis

In this two peak,

cross wind effect

the payload.

1

2

Team Logo

Here

(If You Want)

Team Logo

Here


Tilt Sensor Plot (2 of 2)


The auto-gyro

system was +/- 35

degrees wobble

around according

to Y-Axis.

-150

-100

-50

0

50

100

00:19:18 00:19:35 00:19:52 00:20:10 00:20:27 00:20:44 00:21:01

Roll

(°)

Mission Time (s)

Y-Axis

Team Logo

Here

(If You Want)

Team Logo

Here

-500

0

500

1000

1500

2000

2500

00:19:18 00:19:35 00:19:52 00:20:10 00:20:27 00:20:44 00:21:01

Bla

de

Spin

Rate

(R

PM

)

Mission Time (s)

Blade Spin Rate


Auto-gyro Blade Spin Rate Plot


The payload

separated

from the

container and

auto-gyro

system

successfully

was activated.

Team Logo

Here

(If You Want)

Team Logo

Here


Camera Video


0

50

100

150

200

250

300

00:20:1400:20:1800:20:2300:20:2700:20:3100:20:3600:20:4000:20:4400:20:4800:20:5300:20:57

Accord

ing

toN

ort

h A

ngle

(°)

Mission Time (s)

Bonus Direction

We couldn’t found the payload but have bonus

direction data. Despite windy weather, we were

successfully obtained continuously bonus mission

data.

Team Logo

Here

(If You Want)

Team Logo

Here


Failure Analysis

Sedef ÖZEL

Team Logo

Here

(If You Want)

Team Logo

Here


Identification of failures, root

causes, corrective actions


Failures Root causes Corrective actions

• Didn’t get GPS data collect

last 25 seconds.

• Didn’t find the payload.

• We have collect perfect data

up to the last 40 meters.

• Fail of the GPS.

• Weather conditions was

worse and GPS fail.

• Lots of trees get in between

gcs antenna and probe.

• Better quality GPS to be

used.

• Consider the weather

conditions.

• Using more power wireless

communication model.

Team Logo

Here

(If You Want)

Team Logo

Here


Lessons Learned

Sedef ÖZEL

Team Logo

Here

(If You Want)

Team Logo

Here


Discussion of what worked and

what didn't


What worked What didn’t worked

• Auto-gyro blade spin rate

• Separation mechanism

• Folding mechanism

• GPS data was obtained during 1 minutes

• Camera was worked

• Real-time plotting (air pressure, air

temperature, blade spin rate, altitude,

battery voltage and bonus direction)

• Data transfer

• Pitch and roll data

• Bonus direction data

• Last 25 seconds, GPS signal was lost

Team Logo

Here

(If You Want)

Team Logo

Here


Conclusions


• Totally Launch was successfully. All the requirements and mission

completed.

• We observed that how important to testing for a successfull mission.

• We learned how to management time.

• We improved the knowledge of product, design and mounting of

mechanic parts.

• Participants of the team learned how to choose materials selection

and design for a satellite project.

• We learned that we need to consider weather conditions and external

factors while developing the project.

• We learned that the software we developed should be parametric.

• We get a lot of experience an interdisciplinary project.

Team Logo

Here

(If You Want)

Team Logo

Here


Conclusions


Thanks for listening

cansat 2019 post flight review (pfr) outlinecansat 2019 pfr: team 6160 | grizu-263 6 cansat overview...

Documents