cdr version 1

Critical Design Review

CDR Document ID:

LEVITATE A HIGH-ALTITUDE BALLOON PROJECT

Team Leader

Muhammad Zulfadli bin Abdul Ghafar

Members

Anuar bin Mohamad Nazri

Chin Bing Yao

Choo Jacqueline

Lai Mei Ling

Muhammad Syukri bin Mohamed Shamsuddin

Muhammad Naim bin Shamsudin

Nabil bin Muhamad Usamah

Nazreen Shah bin Nasip

Version: Issue Date: Document Type:

0 23/11/2014 Spec

2

CHANGE RECORD

Version Date Changed Chapter Remarks

0 23/11/2014 -

3

Table of Contents

1.0 INTRODUCTION ............................................................................................................................ 6

1.1 Mission Goal ............................................................................................................................. 6

1.2 Experiment Objective ............................................................................................................... 6

1.3 Concept of Operations ............................................................................................................. 7

1.4 Team Organization ................................................................................................................... 8

1.4.1 Management Team ....................................................................................................... 8

1.4.2 Technical and Engineering Team .................................................................................. 8

1.5 Funding Support ....................................................................................................................... 9

2.0 MISSION REQUIREMENT .......................................................................................................... 10

2.1 Mission Timeline ................................................................................................................... 10

3.0 SYSTEM OVERVIEW .................................................................................................................. 10

4.0 SUBSYSTEM DESIGN & REVIEW................................................................................................ 13

4.1 Payload & Computer System ................................................................................................ 13

4.2 Structure System .................................................................................................................. 17

4.2.2 The main structure shape ........................................................................................... 17

4.2.3 Components Layout .................................................................................................... 19

4.3 Thermal System ................................................................................................................... 21

4.4 Communication System ........................................................................................................ 22

4.4.1 Video Transmission (Standalone) ............................................................................. 22

4.5 Balloon & Navigation System ............................................................................................... 27

4.5.1 Balloon Trajectories Prediction ................................................................................... 27

5.0 TESTING PLAN .......................................................................................................................... 32

5.1 Payload & Computer System ................................................................................................ 32

5.1.1 Power System (Voltage Regulator and Battery) ....................................................... 33

5.1.2 Components Testing ................................................................................................. 34

Arduino Microcontroller Setup ..................................................................................... 34

BMP180 + LM35 + SD card (Integrated Program) ......................................................... 35

Adxl330 3-axis Accelerometer (Program) .................................................................. 36


5.3 Thermal System .................................................................................................................... 38

5.4 Communication System ....................................................................................................... 41

5.4.1 CanSat Experiment ....................................................... Error! Bookmark not defined.

4

5.4.2 SPOT GPS Device ............................................................ Error! Bookmark not defined.

5.4.3 Transmitter (NTX2) ....................................................... Error! Bookmark not defined.

5.4.4 Live feed video test ................................................................................................... 41

5.5 Balloon & Navigation System ............................................................................................... 42

5.5.1 Parachute Testing...................................................................................................... 42

6.0 PROTOTYPE & ANALYSIS .......................................................................................................... 44

6.1 Payload & Computer System ............................................................................................... 44


6.2.1 Drop Test ................................................................................................................... 46

6.2.3 Float Test ................................................................................................................... 47

6.2.4 Impact Test ................................................................................................................ 48

6.3 Thermal System ...................................................................................................................... 49

6.4 Communication System ............................................................ Error! Bookmark not defined.

6.5 Balloon & Navigation System ............................................................................................ 51

6.5.1 Parachute testing result .............................................................................................. 51

7.0 RISK MANAGEMENT ................................................................................................................. 53

7.1 Current Risks ......................................................................................................................... 53

7.1.1 Payload & Computer System .................................................................................... 53

7.1.2 Structure System ....................................................................................................... 56

7.1.3 Thermal System ......................................................................................................... 57

7.1.4 Communication System........................................................ Error! Bookmark not defined.

7.1.5 Balloon & Navigation ......................................................................................................... 58

8.0 PROJECT SCHEDULE .................................................................................................................. 59

9.0 PROJECT BUDGET ..................................................................................................................... 60

9.1 Subsystem Budget ............................................................................................................... 60

9.1.1 Payload and Computer System ................................................................................... 60

9.1.2 Structure & Thermal ................................................................................................... 60

9.1.3 Communication ........................................................................................................... 62

9.1.4 Balloon & Navigation .................................................................................................. 63

9.2 Project Budget ..................................................................................................................... 63

8.0 OUTREACH PROGRAM ............................................................................................................. 64

9.0 REFERENCES ............................................................................................................................. 64

10.0 APPENDIX ............................................................................................................................... 64

5

10.1 Appendix A: Gantt chart (Subsystem) .................................................................................. 65

10.2 Appendix B:Result of BMP180 + LM35 + SD card Testing .................................................... 67

10.3 Appendix C: Coding (Payload & Computer system) ............................................................. 68

10.3.1 BMP180 + LM35 + SD card (Integrated Program) ................................................... 68

10.3.2 Adxl330 3-axis Accelerometer ............................................................................. 71

10.3.3 JPEG Camera ........................................................................................................... 73

10.4 Appendix D: Power details of on-board components .......................................................... 76

6

1.0 INTRODUCTION

1.1 Mission Goal

To be able to launch a high altitude balloon into the stratosphere level and collect data required by the

stakeholders and successfully retrieve it upon landing

1.2 Experiment Objective

1. To be able to reach a minimum altitude of 10,000m from sea level.

2. To be able to capture photos or video of the horizon at 3 different atmosphere

layer; troposphere, first stratosphere and second stratosphere.

3. To determine the maximum altitude of the balloon with the respective payload

weight given the fixed balloon parameters.

4. To record altitudes, pressures and corresponding temperatures at 3 different

atmosphere layer; troposphere, first stratosphere and second stratosphere.

5. To accomplish the requirement given by the stakeholders ( collect gravitational

force data when descending)

7

1.3 Concept of Operations

Building High Altitude Balloon is to perform certain operation and aim to achieve missions at near space

area. It brings the payload up to about 30km above the sea level. During the period, all the data required

to be measured will be captured and stored in a functional system. High Altitude Balloon generally

consists of electronic equipment including camera, radio transmitter, GPS receiver or navigation system.

When the balloon reaches about to the targeted altitude, it will burst due to pressure different. After that,

parachute must be deployed completely and transforms into descent operation. For parachute and

payload in stratosphere, the drop velocity will be faster due to lower air density. Under stratosphere

region, the parachute will achieve a terminal velocity which is estimated to be 3.2 m/s.

Before launching the balloon, helium gas will be pumped to the balloon. It takes approximately 20 minutes

to fill up the whole balloon. During the moment, final inspection or checking process will be carried out to

make sure the system works properly. The connection between the payload, balloon and parachute via

rings will be checked so that they are in secured condition. The structure subsystem is the main housing

for the entire payload and the communication system. The structure is designed to withstand high impact

and unfavorable conditions that might arise during landing.

Once the balloon is released to the air, it will keep ascending. Communication system is the only system to

track the balloon. The core components of the communication system are transmitter inside the payload

and a receiver at ground. Communication system relates closely to the payload and computer system in

tracking the payload and the balloons trajectory during flight. Computer system acts as the brain of the

mission by controlling all on-board sensors and camera (payload) including that of the communication

system.

Upon launching, the balloon travels through different levels of atmosphere with different temperature

and pressure conditions. And with the drastic change in temperature and pressures at different

atmosphere levels that the payload is exposed to, there is a high risk of system malfunction. Therefore,

thermal system is important to ensure the temperature in the box is regulated and maintained at the

optimum temperature for the on-board system to function and perform at its best. Various tests and

research has been done before the suitable thermal system is identified and finalized that best suits the

purpose of this mission.

In order to retrieve the payload, the trajectory of the balloon can be estimated by doing flight simulation.

The weather update is crucial because it greatly influence the trajectory of the balloon during ascent and

descent operations. In addition, the software that is going to be utilized takes into account of the weather

forecast including wind direction and wind magnitude. Usually the accuracy is high when the estimated

date is closed to present time. Hence, the estimation of the weather has to be checked time by time for

better result.

8

1.4 Team Organization

1.4.1 Management Team

1.4.2 Technical and Engineering Team

Project Advisor Dr. Norilmi Amilia binti Ismail

Project Leader

Muhammad Zulfadli bin Abdul Ghafar

Financial Manager Lai Mei Ling

Corporate Communication- Nazreen Shah bin Nasi- Muhammad Syukri bin Mohamed Shamsuddin

Safety Officer Nabil bin Mohamad Usamah

Rescue Team- Anuar bin Mohamad Nazri

- Muhammad Naim bin Shamsudin

Secretary 1 Chin Bing Yao

Secretary 2 Choo Jacqueline

Lai Mei LingCommunication

Team

Muhamad Syukri bin Mohamed Shamsuddin

Nabil bin Mohamad Usamah

Anuar bin Mohamad Nazri

Computer System & Payload Team

Muhammad Naim bin Shamsudin

Muhammad Zulfadli bin Abdul GhafarStructure Team

Choo JacquelineThermal Team

Chin Bing Yao

Nazreen Shah bin Nasip

Balloon & Navigation Team

9

1.5 Funding Support

This project is financially supported using resources from the School of Aerospace

Engineering, Universiti Sains Malaysia (USM). Apart from the resources available

from the school, we are also looking for stakeholders from industries, individuals,

academicians and other academic institutions. Up to this stage of the project, we

have successfully acquired our first stakeholder, Dr. Norizham Abdul Razakand, Dr.

Parvathy from the School of Aerospace Engineering. Dr. Norizham hopes to collect

gravitational force measurement during the flight while Dr. Parvathy wished to

collect data of the air content of the upper atmosphere for Air Pollution Index

(API). They both will provide any necessary sensors for the respective purposes.

Besides working on securing stakeholders for this project, we are also in the

process of acquiring donations and support through crowd funding campaign via

Pozible website at this link http://www.pozible.com/project/187780. Total fund

from the website is about RM 104.

10

2.0 MISSION REQUIREMENT

2.1Mission Timeline

Time, t (secs) Phenomenon

0.0 Balloon Launch! Collection of data begins

3514.2 Entering Stratosphere level

6240.5 Balloon burst Burst Altitude : 93211.9 ft

6241.0 Descending begins G-force measurement begins Parachute deploys

8865.1 Payload tracking begins

10264.0 Payload landed Search & Rescue begins

11

Payload & Computer System

- acts as the main system that collect and stored data

- the system that governs the performance of on-board components

(sensors,camera etc)

Thermal System

- the system that is responsible for regulating the temperature inside

the box during the whole mission to ensure the performance of on-board

components and systems

Communication System

- the system that is responsible on communicating with ground station

- important to to trasmit and received data during the entire mission

- useful for tracking purposes upon landing

Balloon & Navigation

- the system that acts as the main engine of the project

- provide lift for the mission to the upper atmosphere

- important for estimated balloon location and its trajectory during ascending and

descending

Structure System

- the system that is protecting the on-board components from damage upon

landing

- acts as the main housing for other systems ( house for integration)

3.0 SYSTEM OVERVIEW

System integration is vital to ensure the mission is successful and the objectives are

achieved. Among the subsystems involves in this mission are Payload & Computer system,

Structure, Thermal, Communication and last but not least Balloon and Navigation system.

Each of these subsystems is important to ensure the success of the mission. The main

functions and the importance of each subsystem are presented in the chart below

together on how these subsystems are integrated to produce a larger system that drives

the mission.

Levitate

System

12

With the subsystem description above, the top level (most critical) subsystem is identified to be

the payload & computer system and communication system although other subsystems are of

equally importance. These subsystems govern the most important part of the mission namely the

data collection and storage, transmitting of the video and image capture throughout the mission.

These two subsystems are considered to be the heart of the mission. Prediction and damage

analysis have been made for all subsystems and the results are obvious that the failures of both

of these subsystems are defined as mission failure or unsuccessful.

Therefore, in order to avoid mission failure, it is of outmost importance that these two

subsystems are heavily tested and inspected before launching. Various tested will be conducted

on each of the component of these subsystems to ensure their reliability, capability, performance

and efficiency at various temperatures and conditions. Risks that are associated with these

subsystems have been identified and management plan for the risks has been made.

13

4.0 SUBSYSTEM DESIGN & REVIEW

4.1Payload & Computer System

i) Micro Controller

The chosen micro controller is Arduino MEGA. The main reason Arduino MEGA is

selected is due to its price and the number of I/O pins. Arduino MEGA acts as the

main onboard data handler and will be powered using a 12V power system. The

Arduino MEGA will be test to run along with other payload component in two

different conditions:

- Normal room temperature condition (to test the functionality of Arduino

MEGA)

- Worst case condition , -40 Celsius (to test whether the system can work well

during the mission phase)

Figure 1: Arduino Mega Micro Controller

ii) Camera

Two cameras will be used throughout the mission phase. One camera will be used

to capture image basis of time interval while the other camera will be used to

record live feed video using FPV system. The two cameras chosen are TTL Serial

JPEG Camera and Mobius Action Camera.

Figure 2: TTL Serial JPEG

14

Figure 3: Mobius Action Camera

The TTL Serial JPEG camera needs to work with Arduino while the Mobius Action

camera is a stand-alone camera that comes with its own power supply. The testing of

these cameras will only include normal condition. The operating temperature for both

cameras is only between 0 60 degree Celsius. Therefore, adequate and proper

thermal control mechanism is crucial to maintain the temperature within this

allowable range.

iii) Sensors

The list of chosen sensors and its function is as follows:

Adxl330

Since Adxl330 is a 3 axis accelerometer which provides 3 pin output for the

microcontroller to read. The main purpose of the Adxl330 is used to determine

the ascending and descending rate of the balloon. The calibration of the z-axis

pin is planned.

BMP180

As for BMP180, it reads the pressure of the surrounding and the temperature

while with the pressure it is programmed to calculate the altitude of the

BMP180. The test for the maximum pressure and thermal for the BMP is

planned.

SD Card

SD card is used to store the result and picture collected though the journey of

the balloon. The thermal test proved that the SD card start to fail at -12.50

Celsius.

TTL Serial JPEG Camera

The cameras havent been integrated into the board, however it is planned

with guide from the internet library.

15

Table 1: Selected Sensors for the Mission

BMP 180 Use to measure the pressure at the highest altitude

ADXL 335 Use to measure the acceleration experienced by the payload

MQ2 Gas sensor to detect Hydrogen level

MQ7- Gas sensor to detect CO level

DHT11- Use to measure air humidity level

LM35- Use to measure temperature

Since BMP180, MQ2, MQ7, and DHT11 sensor will need to be placed

outside of the box structure, it is important to test the component at the

worst temperature during the mission phase. From the datasheet of each

sensor, the temperature range for these sensors is around -40 to 60 degree

Celsius. Each individual component will test at first, follow up by the

complete assembly subsystem test.

16

iv) Power System

Battery

The selected battery is Energizer Ultimate Lithium AA (8 pieces) to produce 12

V of output voltage to be supplied to the micro controller. Each battery

consists of 1.5 V and it is very reliable as it produces a highest value of power

to weight ratio compared to other type of power sources. The weight which is

1/3 less than a standard weight of alkaline batteries contributes a huge

advantages as weight of total system is really crucial to be analyzed.

Advantages of using the battery are as follows:

I. Perform in extreme temperatures from -40C to 60C.

II. Hold power for 15 years when not in use.

III. Due to the higher voltage, it has more energy than alkaline.

IV. The batteries have a very long storage time and can be used in very

cold condition.

V. Very impressive at high current.

Voltage Regulator

Voltage regulator is used to regulate and maintain a constant voltage level to

its suitable range. The chosen voltage regulator is LM 2596 as the efficiency is

among the highest compared to others which are up to 80%. The voltage

regulator could provide the input voltage ranging from 4.2V to 40 V and output

voltage of 1.25 V to 37 V which is very compatible to the chosen micro

controller. The wide temperature range proves that the voltage regulator could

function well in any extreme temperature and unexpected condition.

17

4.2Structure System

4.2.1 Requirements and objectives

The requirements and objectives of our main structure are:

High strength-to-weight ratio

High buoyancy

Good stability

Resistant from impact and load when hitting the ground

The location of the payload inside the main structure is fixed and steady

even though the main structure undergoes slightly high impact and load

4.2.2 The main structure shape

The shape design of the main structure is confirmed to be a cuboid shape which is

made up from polystyrene material. The reason this shape is chosen because:

Cuboid shape is the most ideal and famous shape used by most high altitude

balloon team globally

Easy to obtain

Easy to locate all the payload and subsystems because of the flat surface at

the base

Cuboid has a good strength of a structure which is the ability to maintain its

original shape and integrity when forces are applied to it.

=

Where = Pressure

= Force

= Area

The surface area at the base of the cuboid is higher, so from equation

above, the pressure exerted on the surface will be lower.

Cuboid has a good stability of a structure which is the ability to maintain its

original position and orientation when the force is applied.

18

The cuboid that has a long side at its base will have a smaller bending

moment that will increase the ability of the structure to maintain its original

position so the structure is difficult to push over by the wind force acting on

the parachute.

Parachute

s

s

Figure 4: Easy to push over during landing

Figure 5: Difficult to push over during landing

=

Where = Moment

= Force

= Perpendicular distance

M

M

Parachute

19

4.2.3 Components Layout

For the inside component compartment, Arduino mega is placed at the center so

that it is easier to connect all the others component to that microcontroller. The

TTL camera and Mobius camera are placed at the side of the main structure which

is the right side is for TTL camera and the left side is for Mobius camera which is

the standalone camera that will capture the view together with the USM logo.

Besides that, the spot GPS and accelerometer are placed near to the Arduino

mega.

Arduino

Mega

GPS

Accelerometer

Power

system TTL

Camera

Video

Tx Mobius

Camera

ca

USM

Logo

Figure 6: Inside Components Compartment

20

For outside component compartment which is at the top of the main structure, we will install the

cloverleaf antenna to increase the strength of the signal because the signal strength can be

affected when there is something or objects that block the signal such as the main structure itself

when it is installed inside the main structure. Not only the cloverleaf antenna, we are also going

to install the MQ2, MQ7, DHT11 and pressure sensor on the outside at the top of the main

structure. MQ2 is the gas sensor to detect hydrogen level, MQ7 is the gas sensor to detect the CO

level, DHT11 is used to measure air humidity level and pressure sensor that will measure the

pressure. So, all these sensors need to install outside the main structure because the gaseous,

pressure and the air humidity level definitely different between inside and outside the main

structure.

Cloverleaf

Antenna MQ2

DHT11

MQ7

Pressure

Sensor

Figure 7: Outside (Top part) Components Compartment

21

4.3Thermal System

After the preliminary design review, several details are finalized and determined,

necessary items were purchased and testing was carried out. Finalized design of the

thermal system will make use of hand warmers/heat packs as the source of heat and

Aluminium foil as reflector to regulate the temperature inside the payload box.

Tests were carried out to determine the number of heat packs/hand warmers and

the layers of reflector needed for the mission. In the meantime, analysis on the heat

released by the on-board system was calculated based on the power requirements of

each component of the on-board system. The details and results of the analysis are shown

in Appendix D. With the total power consumption of on-board system of about 8W, heat

calculation is performed using the equations below.

= ()

=T

With the above equation the estimated heat released by the on-board system is

86.4kJ.Therefore, with an initial temperature of about 35 degree Celsius, the number of

heat packs needed are determined. However, the results from this calculation will have to

be verified through testing.

At the same time, the analysis that were previously done on the mission timeline is

revised from time to time to make sure the changes are taken into consideration when

carrying out the tests and if necessary, the thermal system design will be modified to

cater for these changes. Based on the updated details about the mass of payload, the rate

of change of temperature and ascent rate estimation in each atmosphere level was

recorded in the table below.

Table 2 Rate of Change of Temperature at Different Level of Atmosphere

Atmospheric Level Troposphere Stratosphere

Rate of change of temperature

-8C/km ( -ve refers to decreasing

temperature) 1C/km

Rate of Ascent ( with a payload of 1.5 kg)

29.284 minutes 3.66 minutes

22

4.4Communication System

*antenna selection*

4.4.1 Video Transmission (Standalone)

Figure 8: Security Bo Tong Yi Ge 1.5W 1.2G Wireless Video Transmission

Description:

Video Transmitter (Yellow) Video Receiver (Silver)

Model Digital 1.5W JS1200

Dimension 7.3 4.1 1.4cm 11.5 6.0 2.0cm

Weight 90g 160g

Specification

Transmission frequency: HC1: 1080 HC2: 1120 HC3: 1160 HC4: 1200 (MHz)

Frequency control: Control of digital phase-locked loop frequency locking each lock point.

Transmitting signals: video, audio synchronous transmission

Linear transmission distance: 500-1000m (Stock antenna)

Voltage: DC + 12V

Current: 500mA

Receiving frequency: 0.9 - 1.2GHz

Received signal: audio, video, image synchronous transmission

Receiving sensitivity: -85dBm

Video input level: 1Vp-p

Audio input level: 1Vp-p

Operating Temperature: -20 ~ + 50 C / -4 ~ + 122 H

Operating Humidity: 85% RH

Voltage: DC + 12V

Current: 500mA

Cost RM190

23

Figure 9: 1.2GHz Four leaf clover antenna clover antenna mushrooms (TX antenna)

Description:

Gain: 2dBi-2.5dBi

Directivity: Omni directional

Best for closing transmitter for video

Note Bobby:

24

Wireless Calculation

Fixed Parameters:

Transmitter Power: 31.76 dBm = 1500mW

Receiver Sensitivity: -85 dBm

Receiver Cable Loss: 2dBi

Assumed distance: 25km (from ground station to balloon)

1. Free Space Path Loss (FSPL)

= ( ) + ( ) + .

= () + () + .

= .

2. Fade Margin

=

= +

+

= 31.76 + 2 121.98 + 14 2

= 76.22

= . ()

= . (Normal Link)

3. TX & RX Antenna Gain

EXCELLENT LINK: >22dB

GOOD LINK: 14~22dB

NORMAL LINK:

25

= + +

+ + . + ()()

= . . + + . + . + .

= # PROVEN

= + +

+ + . + () + ()

= . . + + . + . + .

= # PROVEN

Using this calculation and the TX and RX system, to obtain excellent link which is more than 22dB

between receiver and transmitter, the optimum distance will be at most 5.4km where the fade

margin is equal to 22.088dB.

The maximum distance available for the link to connect between receiver and transmitter is

68.6km, where the fade margin is equals to 0.010dB.

Interface planning

26

Choosing frequency

900 MHz

+ Signal will go easy around and penetrate walls and trees because of the low frequency.

+ Works with 2.4 GHz RC transmitters

+ DIY antennas are easy to make because of the low frequency but the size are big

- Used by cellphone companies

- Picture quality not as good as 5.8 GHz (Because of lower frequency)

- 'Old' technology

- Medium range

1.2 GHz (1200 MHz)

+ Signal will penetrate walls and trees because of the low frequency

+ DIY antennas are easy to make because of low frequency but are big

+ Works with 2.4 GHz RC transmitters if use special filters.

- Stay away from these frequencies:

1227.60 1575.42 MHz - GPS

962 - 1213 MHz - for navigation of airplanes

- Picture quality not as good as 5.8 GHz (Because of lower frequency)

That's the theory I have tested both 1.2 GHz and 5.8 GHz with the same camera but we could

not see any difference!

- Medium/long rang

2.4 GHz (2400 MHz)

+ Used for long range FPV flights

+ Best technology

+ Much antenna's to choose from

- Wont penetrate walls and trees as good as 900MHz and 1.2 GHz

- Frequency is crowded.

- Medium/long range (longer range then 1.2 GHz)

5.8 GHz (5800 MHz)

+ Perfect for short range

+ Works with 2.4 GHz RC transmitters

+ Easy to setup

- Shorter range when the air is humid or when flown close to clouds.

- Frequency is crowded

- DIY antennas are small but need to be made really precisely for good effect.

- Short range/Medium range

27

4.5Balloon & Navigation System

4.5.1 Balloon Trajectories Prediction

Balloon trajectories prediction is the essential prediction in this project. This is due

to the location of the balloon and in order to retrieve the payload. Generally, two

main programs will be used based on the suggestion by previous team member,

which are CUSF Landing Prediction by University of Cambridge and Balloon Track

Program by University of Wyoming. Both of these prediction programs are made

on Global Forecast System (GFS) of model National Oceanic & Atmospheric

Administration (NOAA). The detail of the location prediction is shown in the

following:

1. CUSF Landing Prediction

CUSF Landing Prediction is considered as an option for users. It has been

used widely to carry out experiments or project operations. This is an

online program whereby the users can obtain the output information by

inputting the required parameters. Figure 1 shows the users interface of

the program.

Figure 11: Users Interface for the Prediction Program

28

Figure 12: Result of the Prediction

Figure 13: CUSF Landing Prediction by University of Cambridge

29

However, one of the drawbacks of this software is about the limitation of

timing. Furthermore, the program is only able to predict the landing

location within one week or 180 hours from the time on. This is because of

the weather prediction can only be predicted within available period.

Figure 4 shows the unavailability of the program which the input period is

more than 180 hours.

Figure 14: Prediction Unavailable in 16 December of 2014

2. Balloon Tracking Program

Figure 15: Parameters needed for the Prediction Program

30

Figure 16: Balloon Tracking Program by University of Wyoming

3. Combination of Both Prediction

Figure 17: Both Predictions by CUSF and Balloon Track Program

31

4. Wind Prediction

Figure 18: Wind prediction on Certain Day

Based on the two aforementioned softwares, the landing prediction is

considered as accurate. According to the research shows on the internet, these

two softwares play a very important role in the prediction of the landing location

of High Altitude Balloon with specific criteria that have been set up. In addition,

the previous team members had also recommended the both softwares due to the

successfully retrieve of the payload. Therefore, conclusion has been come out and

the decision has been made on using these two softwares.

32

5.0 TESTING PLAN

5.1Payload & Computer System Component Test

Qualification at all payload component level is achieved using the following method:

Subsystem Test

This level testing will be conducted inside the actual HAB box structure. All subsystem will

undergo functional testing to ascertain proper function under every mission condition.

Component Functional

Test

Vibration Test

Component Functional

Test

Shock TestComponent Functional

Test

Thermal Vacuum and Functional

Test

Subsystem Functional

Test

Vibration Test

Subsystem Functional

Test

Shock TestSubsystem Functional

Test

Thermal Vacuum and Functional

Test

33

5.1.1 Power System (Voltage Regulator and Battery)

Thermal Test

In order to conduct the thermal test for power system both component

should be done together to obtain the desired results. The complete

system should be placed in a room temperature first to achieve the best

data and been recorded. Then, the complete system of power system must

be placed in various temperatures to see how it works and how much it

varies from the optimum results.

Battery arrangement

Both series and parallel arrangement must be conducted to obtain the

output readings of voltage, current and resistance produced by each

arrangement. Based on the mission objectives, the most suitable value of

voltage, current and resistance must be selected from either series or

parallel arrangement.

34

5.1.2Components Testing

Arduino Microcontroller Setup

Read and buy from the Arduino.cc and purchases at one of the most trusted

supplier in Malaysia, Cytron.

Apparatus and procedure:

1. Arduino Board

2. USB cable wire

Procedure:

1. Download the new Arduino IDE on the computer at Arduino.cc

2. Install the software

3. Plug in the USB cable into the Computer with Arduino board

4. Run one example from the library sheet

5. Blink the permanent LED provided at Pin 13

6. Run

35

BMP180 + LM35 + SD card (Integrated Program)

Coding is provided below

Testing the sensor and Data logging capabilities

Apparatus:

1. Arduino Board

2. BMP180 (barometric pressure sensor)

3. LM35 (thermal sensor)

4. SD card shield

5. SD card

6. USB cable

Procedure:

1. Download the BMP180 library at GITHUB

https://github.com/adafruit/Adafruit_BMP085_Unified

2. Plug in all the cable and complete the wiring as show in example.

Figure 19: Complete Wiring

3. Using the Data logger code, BMP180 and LM35 example from the library

the code is integrated into one program.

4. Compile and fix any error and Upload it into the board.

5. Result *Refer to Appendix B*

https://github.com/adafruit/Adafruit_BMP085_Unified

36

Adxl330 3-axis Accelerometer (Program)

Testing the capabilities of the 3 axis accelerometer

Procedure and Apparatus:

1. Place the Adxl330 into the breadboard and wire it up

2. Plug in the USB cable from the board into computer and run the example

given in the library

3. Using the user Serial Monitor from the computer and monitor the analog

input from the accelerometer from the 3 axis.

4. Calibration is planned however it yet to be done since to focus on the other

sensors.

Figure 20: Analog input of Accelerometer from 3-Axis

JPEG Camera

1. Received

2. Still in progress however the library has been obtain

Thermocouple Wire

1. Received

2. Programming and calibration in progress

3. Substitute for LM35 due to its rate of sensing and operating temperature.

37

5.2Structure System

Several tests for the structure system will be done to test the limit of its

capability. The item that needs to be tested is similar to that during launch. The

following will be the test that we will conduct before launch day:

Drop test

The purpose of this test is to test the strength and toughness of the

main structure system. The main structure is dropped from a certain

height together with parachute system. The main structure is make

sure to has a weight about 2 kg before conduct the test by adding

others object which are not the payloads or components because they

will have a high risk for damage. The height of the drop will be ensured

reasonable enough so that there will plenty of periods for the

parachute to deploy safely. Our target height is about 60 meters from

ground level. This test is considered successful if the main structure

landed at its original position before launch and does not have any

damage.

Float test

The purpose of this test is to ensure that the main structure has a high

buoyancy ability and water resistant. The main structure is make sure

to has about 2 kg by putting anything inside it just for the sake of the

test. Before conducting the experiment, the main structure will be

wrapped completely by the plastic wrap. This experiment is considered

successful if the main structure does not sink and the water does not

get inside the main structure.

Impact test

The purpose of this test is to ensure that the main structure has a high

strength during landing even though the parachute is failed to deploy.

The main structure that has about 2 kg is drop at about 10 m without

parachute system. Before conducting the experiment, the main

structure will be covered with the safety vest. This experiment is

considered successful if the main structure does not have any damage

after the impact test.

38

5.3Thermal System

After the details of the mission are finalized, tests for thermal system can be carried

out. Thermal tests will be carried out in two different freezers of different temperatures (-

20 deg. C & -80 deg. C) to mimic the condition that the payload will experienced after

launch and the worst case scenario .Tests will be conducted in the Composite lab of School

of Aerospace Engineering and also the Petroleum lab at the School of Chemical Engineering.

The table below shows the tests that were planned for thermal system.

Table 3 Planned test for thermal system

Test Description Expected Results/Parameter

1

To test heat packs capability to release heat Temperature: Room Temperature (28 deg. C) Duration: 3 hours No. of heat pack: 1 Reflector : None

Heat release rate

2

To test heat transfer rate between the box and the surroundings Temperature: -20 deg. C Duration: 3 hours No. of heat pack: None Reflector : None

Heat transfer rate

3

To test heat packs capability to release heat Temperature: -20 deg. C Duration: 3 hours No. of heat pack: 5 Reflector : None

Heat release rate

4

To test heat packs capability to release heat Temperature: -20 deg. C Duration: 3 hours No. of heat pack: 5 Reflector : Yes

Heat release rate

Difference in the rate between two different conditions

5

To verify the prediction of temperature in the box Temperature: -80 deg. C Duration: 1 hour No. of heat pack: 5 Reflector : Yes

Heat release rate

6

To test the number of reflector necessary Temperature: -20 deg. C Duration: 3 hours No. of heat pack: 5 Reflector : Yes (2 layers)

Controlled temperature in the box

7

To verify the heat released of the on-board system Temperature: Room Temperature (28 deg. C) Duration: 3 hours No. of heat pack: None Reflector : Yes

Temperature matches the calculated temperature

39

Figure 21: The arrangement of heat packs inside the payload box Figure 20: The temperature sensor in the payload box connected to the Arduino microprocessor inside the freezer

All the tests above were plan to be carried out in order for the thermal system to

determine the capabilities and efficiency of the heat pack to release heat at room

temperature and also in cold temperatures, the rate of heat transfer between the box and

its surroundings, the functionality of the heat pack at low temperatures for a period of

time and also to verify the prediction of the temperature in the box with respect to the

number of heat pack placed in it.

Set-up of thermal test

Materials/components involved with thermal testing includes the payload box,

heat packs, duct tape, cling wrap, temperature sensors, thermocouples, aluminium foil,

Arduino microprocessor and a computer. The set-up of the testing are shown in the

picture below.

Figure 23: Usage of thermocouple instead of the microprocessor with the temperature sensor

Figure 22: The computer and Arduino microprocessor that is Outside the freezer(Payload is inside the freezer)

40

Figure 24: The overall test set-up with the microprocessor and the thermocouple. Payload box is sealed with cling wrap before placing it in the freezer

41

5.4 Communication System

5.4.4 Live feed video test

Currently, all the main items for the test session are sufficient. The test session has

started off by connecting all the components/items involved. Unfortunately, an

accident occurred when the video camera SJ4000 was plugged into wrong voltage

input of 12V. The required voltage was only 5V. As a result, the camera undergoes

a short circuit and we had try to revive it in many ways but we failed. Besides,

there are lack in wire connection between the video camera and the video

transmission. All the insufficient wires had been identified and we will replace the

video camera with Mobius camera, a much smaller and lighter camera. Therefore,

the test session was delayed to another time after CDR.

In the future before Flight Readiness Review (FRR), we will ensure that the live

feed video will work and then we will construct a range test of 2.4km, located at

the main road in front of USM.

42

5.5Balloon & Navigation System

5.5.1 Parachute Testing

1. Objectives

To ensure the designed configuration of the parachute will function

properly (deployment)

To estimate the deploy time of the parachute and landing time of the

payload

To determine the effect of the centre hole on the parachute

2. Apparatus and Material

Prototyped parachute made by plastic bag (with and without centre

hole)

Actual Fabricated Fabric Parachute (without centre hole)

Payload (about 1.5kg)

Stopwatch

Paper Ring

Nylon Rope

Testing 1 Prototype

Testing 2 Real parachute

Re-fabricate

If needed

Addition of hole, mounting to the balloon or refabricate if something happened during testing

Inspection Ensuring balloon, parachute, mounting and joints ready

Ready to fly

43

3. Procedure

i. The prototyped plastic parachute (without centre hole) is prepared.

ii. The Nylon rope is connected from the parachute to the paper ring

evenly.

iii. The Nylon rope is connected from the payload to the paper ring evenly.

iv. The prototyped plastic parachute is thrown from 7th floor (Desasiswa

Utama) in height, about 22.4 meters.

v. The time taken is started by using stopwatch once the parachute is

released to the air.

vi. The time is taken when the payload falls on ground.

vii. The experiment/testing is repeated by using prototyped plastic

parachute (without center hole) and actual fabricated Fabric parachute.

viii. The time taken is recorded and tabulated.

The test will be done again when the center hole is made on the fabric parachute.

44

6.0 PROTOTYPE & ANALYSIS

6.1Payload & Computer System Breadboard Wiring and Schematic Diagram of LM35, SD Card shield, BMP180, ADXL330, camera

into Arduino mega 2560:

Figure 25: Breadboard Wiring Diagram

Diagram above show the connection of 5 components into the Arduino with power supply. The

lest is the BMP180 which sense the pressure and temperature of the surrounding and it required 4

connection which are the SDA(green), SCL(yellow), Ground and 3.3 volts power supply. Next is the SD card

shield which is more complicated compared to BMP180, where it required 6 connections which are MISO

(brown), MOSI (green), SCL (yellow), CS (blue), Ground and 5 volt power supply.

The Axl330 which is the 3 axis accelerometer required 5 connection into the board whereas the ground,

3.3volts, x-axis (pink), y-axis (yellow) and z-axis (blue). However, the camera still in progress where the

connection still in research for the integrated program. Finally the LM35 (thermal sensor) that required

only 3 pin which is the 5 volts, ground and Vout (light blue).

45

Figure 26: Schematic Diagram

46

6.2 Structure System

6.2.1 Drop Test

Drop test is done to make sure that our main structure can land at its original

position which is the position before dropping it. The main structure that has weight

about 2 kg together with the parachute system is drop at a high about 25 m. This

drop test is successfully done because our main structure landed as their original

position and does not push over by the wind force that acting on the parachute.

47

6.2.3 Float Test

Float test is done to make sure that the main structure has a high floating ability.

The weight of the main structure is about 2 kg. The main structure is wrapped first

with the plastic wrap to avoid water get inside our main structure. After that, a

long rope is attached with the main structure. It will make our job easier after the

main structure is thrown away on the water because we just need to pull the rope

to get back our main structure. As the result for this test, the main structure

floated well and the water does not get inside our main structure so, this test is

succeed.

48

6.2.4 Impact Test

Impact test is done to make sure that our main structure can resist the impact during landing

even though the parachute system is malfunction. The main structure that has weight about 2 kg

together with the safety vest is drop at a high about 10 m. This drop test is successfully done

because our main structure does not have any damages after the test.

49

6.3Thermal System

Test 1 and 3 has been conducted and the results are tabulated and discussed below.

Test 1 Results

The heat packs are tested at room temperature for about 3 hours to determine its efficiency and

the rate of change of temperature of the surroundings. The above graph is obtained when the

results from the testing is tabulated. The estimated results from this testing is that heat pack loses

its efficiency after 2.5 hours. However, this graphs shows otherwise. It shows that the heat packs

efficiency varies with time and is unpredictable. Although the results are not as what we have

expected, we still manage to estimate the rate of change of temperature of 1 heat pack that is

about 2 degrees increment about every 3hours. With that estimation at hand, we conducted

several other tests to verify its reliability.

0

5

10

15

20

25

30

35

40

45

2.45 2.53 3 3.03 3.15 3.2 3.25 3.3 3.41 3.48 4.04 4.18 4.2 4.4 4.52 4.58 5.05

Tem

epra

ture

(d

eg C

)

Time

Heat Pack Efficiency

50

Test 3 results

Test 3 is conducted with 5 heat packs in the freezer to analyze and observe the efficiency of the

heat pack at -20degC temperature. The graphs show some irregularity, that the heat packs

efficiency is not a linear function with respect to time. However, from the graph what can be

deduce is that the heat pack does function by maintaining temperature inside the box to decrease

at a slower rate than it should. After 3 hours of data, the temperature is very well maintain at a

temperature higher than that of the freezer. The temperature inside the payload box maintain for

about 25 minutes at a temperature of -7 degrees Celsius just as predicted and expected based on

the results from Test 1.

Future tests will be conducted and will be involving reflector to improve the heat insulation of the

payload box.

-20.00

-15.00

-10.00

-5.00

0.00

5.00

10.00

15.00

20.00

25.00

30.00

35.00A

xis

Titl

e

Axis Title

Temperature VS Time

51

6.5 Balloon & Navigation System

6.5.1 Parachute testing result

Height = 22.4m

Diameter of centre hole = 0.1m

Type of Parachutes Time taken for payload to fall on ground (s)

Plastic Parachute (without centre hole) 14

Plastic Parachute (with centre hole) 11.6

Fabricated Fabric Parachute (without centre hole)

8

Type of Parachutes Velocity (m/s)

Plastic Parachute (without centre hole) 1.6

Plastic Parachute (with centre hole) 1.93

Fabricated Fabric Parachute (without centre hole)

2.8

Analysis

Based on the testing result, fabricated fabric parachute has a higher velocity compare

to both plastic parachutes. The contributed factors might affect this result is the

weather. During testing on plastic parachute, there was a strong wind blowing

whereas contrary goes to fabricated fabric parachute. The objective of the testing is to

determine the necessity of the centre hole on fabric parachute. If there is necessary,

the diameter of the centre hole has to be determined. Regarding to the situation, a

maximum diameter 10cm of centre hole can be made on the fabric parachute for

stability purpose. As a result, the velocity of the parachute will be slightly higher than

2.8 m/s as refer to the case study on plastic parachute.

52

Pictures from the testing (both plastic bag and fabric)

Figure 27: Parachute testing with prototype (plastic bag)

Figure 28: Parachute testing with fabricated nylon fabric

53

7.0 RISK MANAGEMENT

7.1 Current Risks

7.1.1 Payload & Computer System

i) The effect of temperature on the battery capacity

We are using the ENERGIZER L91 Ultimate Lithium batteries as a power

system. However, from the datasheet of this battery, we found that the

amount of battery capacity decreases along with the decrease in

temperature. The batteries should work fine at 0 Celsius, but decline

linearly afterwards. Since the optimum operating temperature for the

batteries is around 20 to 40 Celsius, thermal subsystem play a very

important role in maintaining the temperature within the box. We will also

test the discharge rate of the batteries in different temperature so that the

information from the datasheet can be verified.

Figure 29: Graph of ENERGIZER L91 capacity against temperature

ii) The wiring connection between Arduino and other payload components

The connection of all wire that involve sensors and power supply is held

merely by the use of a bread board. There will be a high chance that some

of the wire will be loose during launching or landing period. The first

alternative is to secure each connection using appropriate tape and

adhesive. If it is not possible and deemed not fit, the second option

includes the use of a proto breakout shield. The photo breakout shield

enables all the wire to be solder on top of the Arduino MEGA controller

board.

54

Figure 30:: MEGA Photo Breakout Shield

iii) The minimum temperature at the stratosphere

To enable each and every payload component to work successfully, the

minimum temperature at the stratosphere must be known. In general, the

study of stratosphere indicates that the minimum temperature at this

region can be up to -60 Celsius. However, the data provided by the TSR,

Thailand Space and Aeronautic research suggest that the minimum

temperature will be around -35 Celsius while the data from MET, Malaysian

Meteorological Department suggest the temperature to be -80 Celsius.

Most of electrical component can still works at -40 Celsius with exception

of the batteries. Proper thermal insulating and temperature control will be

necessary to control this problem.

iv) Camera lens covered with fog

The sudden drop in temperature will ended with a high risk for the camera

lens to be covered with fog or water droplets. This fog can decrease the

quality of image and video being captured by the camera. The solution

suggest is to use an Anti-fog spray that can prevent the lens from getting

blur or foggy.

Figure 31: Anti-fog spray

55

v) Power System

Voltage Regulator

At certain range of altitude and temperature, the voltage regulator is not

performing well in terms of regulating the voltage used due to the affected

discharged rate by the batteries. Certain temperature might differ the discharging

rate of the battery as well as the input voltage of the voltage regulator. It is

suggested to conduct a thermal test to study the capability to function well at

certain temperature of the voltage regulator. By having this test, the surrounding

temperature around the voltage regulator can be optimized to its best working

temperature.

Battery

The arrangement of the battery must be decided either to be in series or parallel.

Referring to the theory, each arrangement has its own pros and cons depending

on the mission. For series arrangement, the voltage supplied to the payload would

be increased while in parallel arrangement, the current supplied to the payload

will be increased. The resistance in parallel arrangement will be slightly lower

compared to the series arrangement although the power output for both

arrangements is the same. Therefore, a test to investigate the suitable

arrangement for this mission should be done with respect to the requirements of

the payloads.

Arrangement Series Parallel

Voltage

= 1 + 2 + 3 + +

= 1 = 2 = 3 = =

Current

= 1 = 2 = 3 = =

= 1 + 2 + 3 + +

Resistance

= 1 + 2 + 3 + +

1

=

1

1+

1

2+

1

3+ +

1

The selected battery, Energizer Ultimate Lithium can function well in temperature

range from -40C to 60C based on the provider products information. The battery

is also strongly suggested for its longer-lasting capability and more power can be

provided to the whole system. It is still a need to conduct a thermal test to ensure

that the battery can perform well in extreme and various temperatures.

56

7.1.2 Structure System

There are many risks when conducting the testing, which are drop testing,

float testing and impact testing. First, is the high impact of the main structure

during landing. The drop testing had been done together with the parachute

system. The height of the drop is ensure suitable enough so that the parachute can

deploy safely and reduce the impact of the main structure. Polystyrene cardboard

is used to make the compartment of the components as a cushion to absorb

impact during landing.

The next risk is the main structure landed not in its original position. The wind

force acting on the parachute can push over the main structure during landing. So,

the cuboid polystyrene that has a long side at its base is used rather than using the

cuboid polystyrene that has a short side at its base.

The book rope broke also one of our risks during conducting the drop test. Book

rope is used to attach the safety vest with the nylon string. Conducting the drop

test at a higher place can break the book rope so high strength book rope is used

and the stitches at the safety vest is ensure to be strong enough.

There is high possibility for the safety vest to tear during drop test. The safety

vest is used to cover the main structure that can increase the physical appearance

to ease the rescue process. During drop testing, the weight of the main structure is

about 2 kg so a high strength safety vest is used to support the weight of our main

structure.

The next risk is the water get inside the main structure during float testing. The

main structure will be thrown away on the water to analyze the floating ability.

Plastic wrap is used to wrap completely our main structure to make sure that the

water does not get inside the main structure even though the main structure

landed at any surfaces.

The last risk is the main structure has a severe damage during the impact testing

because the parachute system will not be applied during the testing. The main

structure will be dropped at a high about 10 m so the possibility that our main

structure will damage is definitely high. We have extra cuboid polystyrene that can

be used when our first cuboid polystyrene is damaged during this test.

57

7.1.3 Thermal System

After a few tests have been done, risks associated with the thermal system

are revisited for reassessment. There are new risks that surfaced as the

testing was conducted. Among the risks that surfaced at this stage of

7.1.3.1 Capability of heat packs

Heat packs are tested are their operating temperature, specs and also

behavior in different temperatures. From the tests, the results show the

inconsistency of the heat packs at releasing heat. Currently, thermal team

is still researching and understanding the capabilities and efficiency of the

heat pack at various temperatures with respect to time. This factor is very

important in order for the thermal team to predict the number of heat

pack required to regulate and maintain the temperature inside the box for

the mission.

7.1.3.2 Inaccurate prediction/calculation that leads to overheating problems

Heat released by the on-board system is calculated with simple

assumptions where linearity is in place. The results from the calculation will

further be verified through a series of tests to ensure the accuracy of the

calculated value and thus the sufficient amount of heat can be produced to

retain the temperature in the box.

58

7.1.5 Balloon & Navigation

7.1.5.1 Balloon and Parachute

One of the risks that might be encountered is about the unexpected

collision such as bird strike or any other substances that might cause the

balloon burst or parachute broken. This will result in failure of the project

in ascend or descent period. In term of balloon, when balloon burst before

the targeted altitude, the data will not be captured at that certain altitude.

In term of parachute, failure in deploying the parachute or parachute

broken will cause the payload to have a large impact when it is landed on

ground. The camera or other payload components will experience a severe

damage due to its high velocity without aid of parachute.

7.1.5.2 Rope Tangled Issue and Uneven Rope Length

The Nylon rope is used to connect the payload/balloon to the paper ring.

Due to the uneven tight pattern, the length of the rope will become

irregular. Hence, in term of payload, it becomes imbalance when it hangs in

the air. This will affect the stability of whole configuration. Plus, another

problem goes to entangled rope, there are eight Nylon ropes connected

from parachute to the paper ring and six Nylon ropes are linked from

payload to paper ring. However, the rope tends to be tangled when it is in

ascent or descent period.

59

8.0 PROJECT SCHEDULE *Refer to Appendix A for Project Gantt chart*

60

9.0 PROJECT BUDGET

9.1Subsystem Budget

9.1.1 Payload and Computer System

9.1.2 Structure & Thermal

No. Item Description Quantity Cost

1. Arduino Mega + Shield Microprocessor 1 RM220.00

2. Barometric Pressure

Sensor (BMP 180) Sensor 1 RM35.00

3. Accelerometer Sensor 1 Stakeholder

4. MQ2 Gas sensor module

(hydrogen) Sensor 1 RM18.00

5. MQ7 Gas sensor (Carbon

Monoxide) Sensor 1 RM10.00

6. DHT11 Digital

Temperature and Humidity Sensor

Sensor 1 RM14.00

7. TTL Serial JPEG Camera Camera 1 RM145.00

8. SJ4000 HD CAM + 32gb micro SD memory card

Video Camera 1 RM380.00

9. Mobius Camera Video Camera 1 RM300

10. LM 2596 Voltage Regulator 1 RM18.00

11. 8 x AA Batteries Holder

Case Box Battery holder 1 RM5.00

12. Energizer Ultimate

Lithium Battery 8 RM60.00

13. SanDisk SD Card Memory card 1 RM20.00

14. Anti-Fog Fluid Prevent fog at

camera 1 RM20.50

15. Other components and

wires etc. 1 -

16. Shipping Allocation 1 RM35

TOTAL= RM1280.50

61


1. Heat Pack Thermal Source 20 RM50.00

2. Plastic Wrap Wrap the box

structure for buoyancy

1 RM5.90

3. Safety Vest

Act as carrier to connect the balloon with the box

2 RM13.80

4. Polystyrene Box &

Polystyrene Cardboard For main structure

(box) 2 Free

5. Araldite Attachment

between polystyrene

1 Free

6.. Duct tape To seal the box 3 RM9.50

7. Book rope To attach safety

vest with nylon string

8 RM20.00

8. Reflector To contain the

heat within the payload box

- Free

TOTAL= RM99.20

62

9.1.3 Communication


1. SPOT Satellite GPS

Messenger GPS 1 Sponsored by USM

2.

uBLOX MAX-M8Q Breakout with Quad-V

Antenna GPS 1

RM 213.31

3. Uniden BC95XLT Receiver 1 Available

4.

433MHz RF (UART) Transceiver Module

Transceiver 2 RM130.27

NTX2B 434Mhz Radio Module NTX2B-FA

Transmitter 1 Available

5. Video Transmission

Security Bo Tong Yi Ge 1.5W 1.2G wireless video wireless transmitter receiver wireless surveillance

1 RM190.00

1.2GHz Four leaf clover antenna clover antenna mushrooms (TX antenna)

1 RM22.00

1.2GHz KBT flat antenna for audio/video transmission system (RX antenna)

1 RM82.00

6. Shipping Allocation for

video transmission 1 RM55

TOTAL = RM 692.58

63

9.1.4 Balloon & Navigation

No Item Description Quantity Cost

1 Helium gas It uses to inflate the balloon

Volume of Tank: 6.4 3 Targeted use: 4.25 3

Sponsored by USM

2 Balloon It uses to generate lift filled up with helium gas

1 for testing 1 for launch day

Sponsored by USM

3 Parachute fabric To bring down the payload

Size: 1x5 3 RM 40.00 includes shipping

4 Tailor Service To sew the parachute and cover for the main structure

1 RM 60.00

5 Plastic Beg Handmade of parachute for testing

1 FREE

6 Tapes

Cellophane tapes

Duct Tape

Multi-purpose 6 RM 25.00

7 Ring As a medium to connect parachute and the main structure

4 RM 2.90

8 Nylon rope

Soft (Testing)

Hard (Real)

To connect the parachute, balloon and main structure

2

RM 3.90 RM 12.00

TOTAL =RM 143.80

9.2Project Budget

No. Team Cost

1. Payload& Computer System RM1280.50

2. Structural and Thermal RM 99.20

3. Communication RM 692.58

4. Balloon &Navigation RM 143.80

TOTAL PROJECT COST = RM 2216.08

64

8.0 OUTREACH PROGRAM

In order to ensure the community involvement in our project, we established a

blog/website where people/students can keep themselves updated with our project

progress. They can learn about the latest decision or modification we had made for our

project, giving comments and even ideas to make our project better! Heres the link to

our website, http://levitatehab.wordpress.com/

9.0 REFERENCES

1. Project Horus,High Altitude Balloon Project http://projecthorus.org/ 2. High Altitude Balloon Project PDR Report (October, 2013)

3. Parachute Calculator from Rocket Reviews http://www.rocketreviews.com/index.php 4. Descent Rate Calculator from Rocket Reviews http://www.rocketreviews.com/descent-rate-calculator.html 5. Linking an Arduino to a Radiometrix NTX2B Transmitter,UKHAS Wiki, UK High Altitude

Society http://ukhas.org.uk/guides:linkingarduinotontx2 6. Building the Tracking Device for a High Altitude Balloon, TheHABLab http://thehablab.com/blog/building-the-tracking-device-for-a-high-altitude-balloon-10

10.0 APPENDIX

http://levitatehab.wordpress.com/http://projecthorus.org/http://www.rocketreviews.com/index.phphttp://www.rocketreviews.com/descent-rate-calculator.htmlhttp://ukhas.org.uk/guides:linkingarduinotontx2http://thehablab.com/blog/building-the-tracking-device-for-a-high-altitude-balloon-10

65

10.1 Appendix A: Gantt chart (Subsystem)

LEGEND

Task Breakdown W1 W2 W3 W4 W5 W6 W7 W8 W9 W10 W11 W12 W13 W14 W15

Payload & Computer System Team

High Altitude Group Briefing

Task Allocation Among Payload Engineer

Information Gathering & Research

Payload Component Trade-off

Programming

Computer System Prototype

Purchasing of Payload Component

Configure & Test Component Connection

Launch : Retrieve & Distribute Data

Documentation

Structure Team

Define mission Objectives and Task

Allocation

Research on Structural Requirements

Expected Budget for Proposal

Finalize Item and Structural Configuration

Critical Design Review (CDR)

Flight Readiness Review (FRR)

Structural Project Work & Fabrication

Preparation for Final Presentation

Testing & Launching

Thermal Team

Project Introduction & Team Forming

Task Identification


Preliminary Design Review (PDR)

Detailed Design Review (CDR)

Thermal Testing

Launch

Documentation

Planned Completed

66

Task Breakdown W1 W2 W3 W4 W5 W6 W7 W8 W9 W10 W11 W12 W13 W14 W15

Communication System


Identify Project & System Requirements

Design System Layout

Project Proposal

Intense Research on System & Electronics

Components

Preliminary Design Report (PDR)

Testing & Practical Hands On

Finalizing Components and System Design

Configuration

Critical Design Review (CDR)

Configure & Test Components

Project Launch Day

Balloon & Navigation Team


Task Allocation


Balloon & Parachute Conceptual Design

Preliminary Design Review

Balloon & Parachute Detail Design

Launch Day

Documentation

67

10.2 Appendix B:Result of BMP180 + LM35 + SD card Testing

68

10.3 Appendix C: Coding (Payload & Computer system)

10.3.1 BMP180 + LM35 + SD card (Integrated Program)

/*

The circuit:

* analog sensors on analog ins 0, 1, and 2

* SD card attached to SPI bus as follows:

** MOSI - pin 11

** MISO - pin 12

** CLK - pin 13

** CS - pin 3

*/

#include

#include

#include

#include

// On the Ethernet Shield, CS is pin 4. Note that even if it's not

// used as the CS pin, the hardware CS pin (10 on most Arduino boards,

// 53 on the Mega) must be left as an output or the SD library

// functions will not work.

constintchipSelect = 53;

Adafruit_BMP085_Unified bmp = Adafruit_BMP085_Unified(10085);

floattempO;

inttempPin = 1;

int p = 0;

voiddisplaySensorDetails()

{

sensor_t sensor;

bmp.getSensor(&sensor);

Serial.println("------------------------------------");

Serial.print ("Sensor: "); Serial.println(sensor.name);

Serial.print ("Driver Ver: "); Serial.println(sensor.version);

Serial.print ("Unique ID: "); Serial.println(sensor.sensor_id);

Serial.print ("Max Value: "); Serial.print(sensor.max_value); Serial.println(" hPa");

Serial.print ("Min Value: "); Serial.print(sensor.min_value); Serial.println(" hPa");

Serial.print ("Resolution: "); Serial.print(sensor.resolution); Serial.println(" hPa");

Serial.println("------------------------------------");

Serial.println("");

delay(500);

}

void setup()

{

69

// Open serial communications and wait for port to open:

Serial.begin(9600);

Serial.print("Initializing SD card...");

// make sure that the default chip select pin is set to

// output, even if you don't use it:

pinMode(53, OUTPUT);

// see if the card is present and can be initialized:

if (!SD.begin(chipSelect)) {

Serial.println("Card failed, or not present");

// don't do anything more:

return;

}

Serial.println("card initialized.");

//pressure sensor test

Serial.println("Pressure Sensor Test"); Serial.println("");

/* Initialise the sensor */

if(!bmp.begin())

{

/* There was a problem detecting the BMP085 ... check your connections */

Serial.print("Ooops, no BMP085 detected ... Check your wiring or I2C ADDR!");

while(1);

}

/* Display some basic information on this sensor */

displaySensorDetails();

Serial.println("Pressure Sensor Detected");

Serial.println("Pre");

}

void loop()

{

sensors_event_t event;

bmp.getEvent(&event);

tempO = analogRead(tempPin); // read the analog value from the lm35 sensor.

tempO = (5.0 * tempO * 100.0)/1024.0; // convert the analog input to temperature in

centigrade.

p = p+1;

if (event.pressure)

{

/* Display atmospheric pressue in hPa */

Serial.print("Pressure: ");

Serial.print(event.pressure);

Serial.println(" hPa");

/* Calculating altitude with reasonable accuracy requires pressure *

* sea level pressure for your position at the moment the data is *

* converted, as well as the ambient temperature in degress *

* celcius. If you don't have these values, a 'generic' value of *

70

* 1013.25 hPa can be used (defined as SENSORS_PRESSURE_SEALEVELHPA *

* in sensors.h), but this isn't ideal and will give variable *

* results from one day to the next. *

* *

* You can usually find the current SLP value by looking at weather *

* websites or from environmental information centers near any major *

* airport. *

* *

* For example, for Paris, France you can check the current mean *

* pressure and sea level at: http://bit.ly/16Au8ol */

/* First we get the current temperature from the BMP085 */

float temperature;

bmp.getTemperature(&temperature);

Serial.print("InsideTemperature: ");

Serial.print(temperature);

Serial.println(" C");

Serial.print("OutsideTemperature: ");

Serial.print((byte)tempO);

Serial.println("C");

/* Then convert the atmospheric pressure, and SLP to altitude */

/* Update this next line with the current SLP for better results */

floatseaLevelPressure = SENSORS_PRESSURE_SEALEVELHPA;

Serial.print("Altitude: ");

Serial.print(bmp.pressureToAltitude(seaLevelPressure, event.pressure));

Serial.println(" m");

Serial.println("");

}

else

{

Serial.println("Sensor error");

}

// open the file. Note that only one file can be open at a time,

// so you have to close this one before opening another.

File dataFile = SD.open("test2.txt", FILE_WRITE);

// if the file is available, write to it:

if (dataFile) {

dataFile.print(p);

dataFile.print(". ");

dataFile.print("Pressure,hPa= ");

dataFile.print(event.pressure);

float temperature;

bmp.getTemperature(&temperature);

dataFile.print(" InsideTemperature,C= ");

dataFile.print(temperature);

71

dataFile.print(" OutsideTemperature,C= ");

dataFile.print(tempO);

floatseaLevelPressure = SENSORS_PRESSURE_SEALEVELHPA;

dataFile.print(" Altitude,m= ");

dataFile.print(bmp.pressureToAltitude(seaLevelPressure, event.pressure));

dataFile.println("");

dataFile.close();

// print to the serial port too:

}

// if the file isn't open, pop up an error:

else

{

Serial.println("error opening compile.txt");

}

delay(1000);

}

10.3.2 Adxl330 3-axis Accelerometer

No calibration

Simple voltage read

/*

ADXL3xx

Reads an Analog Devices ADXL3xx accelerometer and communicates the acceleration to

the computer. The pins used are designed to be easily compatible with the breakout

boards from Sparkfun, available from:

http://www.sparkfun.com/commerce/categories.php?c=80

http://www.arduino.cc/en/Tutorial/ADXL3xx

The circuit:

analog 0: accelerometer self-test

analog 1: z-axis

analog 2: y-axis

analog 3: x-axis

analog 4: ground

analog 5: vcc

created 2 Jul 2008

by David A. Mellis

modified 30 Aug 2011

by Tom Igoe

http://www.arduino.cc/en/Tutorial/ADXL3xx

72

This example code is in the public domain.

*/

// these constants describe the pins. They won't change:

// analog input pin 5 -- voltage

constintxpin = A10; // x-axis of the accelerometer

constintypin = A9; // y-axis

constintzpin = A8; // z-axis (only on 3-axis models)

void setup()

{

// initialize the serial communications:

Serial.begin(9600);

// Provide ground and power by using the analog inputs as normal

// digital pins. This makes it possible to directly connect the

// breakout board to the Arduino. If you use the normal 5V and

// GND pins on the Arduino, you can remove these lines.

}

void loop()

{

// print the sensor values:

Serial.print("x= ");

Serial.print(analogRead(xpin));

// print a tab between values:

Serial.print("\t");

Serial.print("y= ");

Serial.print(analogRead(ypin));

// print a tab between values:

Serial.print("\t");

Serial.print("z= ");

Serial.print(analogRead(zpin));

Serial.println();

// delay before next reading:

delay(500);

}

73

10.3.3 JPEG Camera

-havent tested yet

#include

#include

// comment out this line if using Arduino V23 or earlier

#include

// uncomment this line if using Arduino V23 or earlier

// #include

// SD card chip select line varies among boards/shields:

// Adafruit SD shields and modules: pin 10

// Arduino Ethernet shield: pin 4

// Sparkfun SD shield: pin 8

// Arduino Mega w/hardware SPI: pin 53

// Teensy 2.0: pin 0

// Teensy++ 2.0: pin 20

#define chipSelect 10

// Using SoftwareSerial (Arduino 1.0+) or NewSoftSerial (Arduino 0023 & prior):

#if ARDUINO >= 100

// On Uno: camera TX connected to pin 2, camera RX to pin 3:

SoftwareSerialcameraconnection = SoftwareSerial(2, 3);

// On Mega: camera TX connected to pin 69 (A15), camera RX to pin 3:

//SoftwareSerialcameraconnection = SoftwareSerial(69, 3);

#else

NewSoftSerialcameraconnection = NewSoftSerial(2, 3);

#endif

Adafruit_VC0706 cam = Adafruit_VC0706(&cameraconnection);

// Using hardware serial on Mega: camera TX conn. to RX1,

// camera RX to TX1, no SoftwareSerial object is required:

//Adafruit_VC0706 cam = Adafruit_VC0706(&Serial1);

void setup() {

// When using hardware SPI, the SS pin MUST be set to an

// output (even if not connected or used). If left as a

// floating input w/SPI on, this can cause lockuppage.

#if !defined(SOFTWARE_SPI)

#if defined(__AVR_ATmega1280__) || defined(__AVR_ATmega2560__)

if(chipSelect != 53) pinMode(53, OUTPUT); // SS on Mega

#else

if(chipSelect != 10) pinMode(10, OUTPUT); // SS on Uno, etc.

#endif

#endif

Serial.begin(9600);

74

Serial.println("VC0706 Camera snapshot test");

// see if the card is present and can be initialized:

if (!SD.begin(chipSelect)) {

Serial.println("Card failed, or not present");

// don't do anything more:

return;

}

// Try to locate the camera

if (cam.begin()) {

Serial.println("Camera Found:");

} else {

Serial.println("No camera found?");

return;

}

// Print out the camera version information (optional)

char *reply = cam.getVersion();

if (reply == 0) {

Serial.print("Failed to get version");

} else {

Serial.println("-----------------");

Serial.print(reply);

Serial.println("-----------------");

}

// Set the picture size - you can choose one of 640x480, 320x240 or 160x120

// Remember that bigger pictures take longer to transmit!

cam.setImageSize(VC0706_640x480); // biggest

//cam.setImageSize(VC0706_320x240); // medium

//cam.setImageSize(VC0706_160x120); // small

// You can read the size back from the camera (optional, but maybe useful?)

uint8_timgsize = cam.getImageSize();

Serial.print("Image size: ");

if (imgsize == VC0706_640x480) Serial.println("640x480");



Serial.println("Snap in 3 secs...");

delay(3000);

if (! cam.takePicture())

Serial.println("Failed to snap!");

else

Serial.println("Picture taken!");

75

// Create an image with the name IMAGExx.JPG

char filename[13];

strcpy(filename, "IMAGE00.JPG");

for (inti = 0; i< 100; i++) {

filename[5] = '0' + i/10;

filename[6] = '0' + i%10;

// create if does not exist, do not open existing, write, sync after write

if (! SD.exists(filename)) {

break;

}

}

// Open the file for writing

File imgFile = SD.open(filename, FILE_WRITE);

// Get the size of the image (frame) taken

uint16_tjpglen = cam.frameLength();

Serial.print("Storing ");

Serial.print(jpglen, DEC);

Serial.print(" byte image.");

int32_t time = millis();

pinMode(8, OUTPUT);

// Read all the data up to # bytes!

bytewCount = 0; // For counting # of writes

while (jpglen> 0) {

// read 32 bytes at a time;

uint8_t *

cdr version 1

Documents

structure system

system overview

thermal system

communication system

balloon navigation system

payload computer system

engineering team

team organization