UCK-14 Project Report of C’Space 2014

23/Aug/2014 ~ 30/Aug/2014 at Biscarrosse, FranceCHAPTER 1

Project Outline

2

Orientation of C’Space 2014
The team UCK had built many model rockets and took part in C'Space many times. But we broke off
activity and didn't build any new rocket after C'Space 2009. In 2012 the team was renewed with newmembers and decided to participate in C'Space 2014. Some of the new members have some experiencein C'Space, project management, and rocket building. Based on the experience, we try to make both therocket and project more refined this time.
We aim to standardize CanSat deployment mechanism in order to hold a CanSat or Rocket Campaign byourselves in the future. The rocket itself is designed so that each section can be independently
developed without difficulty and that a section leader can learn system design and management easily.
For us, C'Space 2014 is the opportunity where we can build our first rocket and CanSat toward theabove stated goal.

Outline of the productions
Rocket system for the “Experimental Rocket Campaign” in C’Space

2 CanSats

One for both CanSat Competition & RocketCampaign
Another for Rocket Campaign3Organization Chart

Structure Outline D.Fukuyama
Stability D.Fukuyama

Chairman
M.Shimoda

Nose Cone J.Maruo
CanSat Bus J.Maruo

Project Leader
K.NaitoSystem Leader
D.Fukuyama

Organizers
Accounting
K.NaitoPublic Relations
D.Fukuyama
EnglishCommunication
J.MaruoElectric System K.Naito
Recovery System D.Fukuyama
Propulsion J.Maruo
Fins J.Maruo
Flight Profile Detector
T. Nobuhara
Telemetry K. Naito
CanSat No.1 & 2
OIT & Kandai Students4Schedule

2013

2014
Jan. – Mar.

2014
Apr.

2014
May2014
Jun.

2014
Jul.

2014
Aug.

2014
Sep.

2014
OctGathering ofMembers

CanSat TeamActivity
System Design &Manufacturing
intermediatesurvey

FinishJerome Coming

System TestC’Space 2014
Campaign
Report AfterC’SpaceEnd of Project5

CHAPTER 2

Rocket System Designing6

Outline & Characteristics
Through this project we aim to standardize CanSat ejection mechanism in order towelcome other teams’ CanSats into our rocket in the future. The rocket itself isdesigned so that each section can be independently developed without difficulty andthat a section leader can learn system design and management easily.
Based on this design concept, we adopted the structure which consists of frames andrings. The frames have the interface to fix mechanical parts and electric parts of therocket. What is more, in order to make the developing and assembling processes
easier, the CFRP shells can be detached from the frame structure.
From the view point of electrics, the system is split into several electric boards andeach board has only one or few functions to develop the small subsystems
independently.

Missions
1. Ejection of 2 CanSats
2. Detection of the Flight Profile7

Shells and Frames of the Rocket8

Parts of SystemFins

Nose ConeCanSat Door
1

CanSat Door
2Parachute DoorElectric Tower
Battery

Main PowerCanSat
Dep. 1

CanSatDep. 2

Recovery System

Flight Prof.
Main CPU

Trigger

Rocket body A(CFRP Cylinder)

Motor

Sub-Battery

Payload Part

Nose Cone(GFRP Parabolic Cone)

Motor Mount

Telemetry

Rocket body B(CFRP Cylinder)

Sub-Trigger

Rocket body C(CFRP Cylinder)9

Rocket Structure

Electric Boards& frame structure(1)Overall View

Electric Boards& frame structure(1)Motor Mount

CHAPTER 3

CanSat System Designing11

Outline & Missions
CanSat“BENTO”

parachute(Fall speed adjustment)◇ Missions
AcrylicIR1Lux2
UV3Environmentalparameter

GPSAir Pressure

Positional information

Xbee

μSD

Data preservation

Mission➀Measurement of the Infrared light and Lux
Mission②
Measurement of the UVMission③
Measurement of the Air pressure

Protection housing
Antenna

Earth station(Data preservation , State monitoring)System Block Diagram
1st Stage
UV sensor, IR sensor, and Lux sensor are equipped .
Each sensor is located on the upper stage.
The cover of CanSat is made from the acrylic which has highpermeability for UV, IR, visible light.
2nd Stage
After deciding the arrangement of 1st, 4th, and 3rd stages, therest is located here.
3rd Stage
We lowered the center of gravity by locating battery as low as
possible and raised the stability at the time of the fall.
4thStage
We adopted Xbee as a communication module.
An antenna of Xbee should be placed outside of the can.

UVGPSLux

AIRPICIRµSD

Underside
Li+Battery

5V raisemodule

Xbee
pro

Xbee
pro

PC

CanSat Assembly & Naming← A board and a parachute are
already attatched

The structure of our CanSat
whose stages are piled up
resembles to the Japanesetraditional lunch box" BENTO"
Traditional lunch box →Any radio wave doesn't work until the moment of the fall ➀We want to make use of the experience of C'Space 2014 for various CanSat projects in future.
What we aimed this occasion is the design that could be adapted for different release mechanisms flexibly.
It is an ideal way for this design to detect the moment of the fall by a sensor and software without fixing any trigger
for release mechanism.
We examined which sensor equipped in our CanSat can detect the moment of the fall.

Mark Sensor

Remarks

Voltage of the Lux sensor in the release mechanism○Lux sensor

A value greatly changed at a prior
test△

UV sensor

UV enters into the box

Voltage of the Lux sensor in the control room？

IR sensor

Not examined=3V×

Air pressure Software is complicated, and theresensor
is no certainty=1V⇒ The difference is 2 V

We set the threshold as 2V

Any radio wave doesn't work until the moment of the fall ②
How to stop the Xbee communication;
The beacon signal is usually working if the switch is on.
It is necessary to go into sleep mode to stop the beacon signal.
High / Low of the 13pin of Xbee should be switched to be in sleep mode.

As explained on the previous slide, if the voltage of Lux sensor:
More than 1V⇒

13 pin High (check if sleep mode is off)

Less than 3V⇒

9 pin Low (turn sleep mode on)Thus, we can control the radio wave at will for sure!!

Internal construction of CANSAT

Overall view of CANSAT