thermal management: communications: solar ...projects.eng.uci.edu/sites/default/files/cubesat...

1
TEAM MEMBERS Erling Eriksen Benjamin Sorensen Anthony Drabeck Baldwin Ngo Dylan Kao Eduardo Garcia Micah Raney Ricardo Rojas-Salcedo Armen Avetisyan Taekyoo Won Nicole Alvarez Felix Slothower Fadi Samaan Advisor: Kenneth Mease GOALS: To design and build a low cost nanosatellite that will be launched into low earth orbit and perform a six month mission. We aim to build a framework for future payloads from students and professors. OBJECTIVES: · Build and operate a functional transceiver and ground station. · Build custom solar panels. · Maintain temperature control of critical components. · Test CubeSat in launch and operational environments. · Ingetrate payload into the CubeSat design and downlink experiment data. · Create an open source website for future CubeSat projects. THE BIG PICTURE: A low cost design combined with our open source website will allow for other projects to complete their mission more easily, ultimately facilitating the democratization of space. CONTACT: Project lead: Erling Eriksen [email protected] Website: ucicubesat.com SOLAR POWER: Solar panels using cost effective TrisolX solar cells will cover all four sides of the CubeSat and the top to recharge our Lithium Ion Batteries. These solar cells along with the battery management will provide consistent and lasting power to all subsystems for the six month mission. COMMUNICATIONS: A PQ9ISH transceiver board, designed by the Libre Space Foundation, will transmit our payload data to the SATNOGs ground station. Using the ground station and transceiver, our team will be able to make changes to the payload experiment remotely. THERMAL MANAGEMENT: During its orbit the CubeSat will undergo temperatures changes from -39 to 60 degrees Celsius. In order to maximize the performance of the battery, each cell must stay within -20 to 60 degrees Celsius. To achieve this, the battery pack will be wrapped in a heating element made from nichrome wire and kapton polyimide tape. PAYLOAD: The payload is a variable emissivity device (VED). The VED can change its emissivity value to regulate the temperature of the CubeSat during the 90 minute orbital period. NEXT STEPS: Fall 2019 Winter 2020 Spring 2020 -Ground station testing - Subsystem testing - Manufacture subsystem PCBs -Vibration, thermal vacuum, and shock testing - Day in the life -Complete any redesigns - Final preparations for launch

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Page 1: THERMAL MANAGEMENT: COMMUNICATIONS: SOLAR ...projects.eng.uci.edu/sites/default/files/CubeSat spring...Advisor: Kenneth Mease GOALS: To design and build a low cost nanosatellite that

TEAM

MEM

BER

S

Erling

Eriksen

Ben

jamin

Soren

sen

An

thon

y Drab

eck B

aldw

in N

go

Dylan

Kao

Edu

ardo G

arciaM

icah R

aney

Ricard

o Rojas-S

alcedo

Arm

en A

vetisyan

Taekyoo Won

N

icole Alvarez

Felix Sloth

ower

Fadi S

amaan

Ad

visor: Ken

neth

Mease

GO

ALS

:To d

esign

and

bu

ild a low

cost nan

osatellite that w

ill be

laun

ched

into low

earth orb

it and

perform

a six mon

th

mission

.

We aim

to bu

ild a fram

ework for fu

ture p

ayloads from

stu

den

ts and

professors.

OB

JECTIV

ES:

·B

uild

and

operate a fu

nction

al transceiver an

d g

roun

d station

Bu

ild cu

stom solar p

anels.

·M

aintain

temp

erature con

trol of critical comp

onen

ts.·

Test Cu

beS

at in lau

nch

and

operation

al environ

men

ts.·

Ing

etrate payload

into th

e Cu

beS

at desig

n an

d d

own

link exp

erimen

t data.

·C

reate an op

en sou

rce web

site for futu

re Cu

beS

at projects.

THE B

IG P

ICTU

RE:

A low

cost desig

n com

bin

ed w

ith ou

r open

source w

ebsite w

ill allow

for other p

rojects to comp

lete their m

ission m

ore easily, u

ltimately facilitatin

g th

e dem

ocratization of sp

ace.

CO

NTA

CT:

Project lead

: Erling

Eriksen

eeriksen@

uci.ed

u

Web

site: ucicu

besat.com

SO

LAR

PO

WER

:

Solar p

anels u

sing

cost effective TrisolX solar

cells will cover all fou

r sides of th

e Cu

beS

at an

d th

e top to rech

arge ou

r Lithiu

m Ion

B

atteries. These solar cells alon

g w

ith th

e b

attery man

agem

ent w

ill provid

e consisten

t an

d lastin

g p

ower to all su

bsystem

s for the six

mon

th m

ission.

CO

MM

UN

ICA

TION

S:

A P

Q9

ISH

transceiver b

oard,

desig

ned

by th

e Libre S

pace

Foun

dation

, will tran

smit ou

r p

ayload d

ata to the S

ATN

OG

s g

roun

d station

. Usin

g th

e g

roun

d station

and

tran

sceiver, our team

will b

e ab

le to make ch

ang

es to the

payload

experim

ent rem

otely.

THER

MA

L MA

NA

GEM

ENT:

Du

ring

its orbit th

e Cu

beS

at will

un

derg

o temp

eratures ch

ang

es from

-39

to 60

deg

rees Celsiu

s. In ord

er tom

aximize th

e perform

ance of th

eb

attery, each cell m

ust stay w

ithin

-20

to 60

deg

rees Celsiu

s. To achieve

this, th

e battery p

ack will b

e wrap

ped

in a h

eating

elemen

t mad

e fromn

ichrom

e wire an

d kap

ton p

olyimid

etap

e.

PA

YLO

AD

:Th

e payload

is a variable

emissivity d

evice (VED

). The

VED

can ch

ang

e its emissivity

value to reg

ulate th

e tem

peratu

re of the C

ub

eSat

du

ring

the 9

0 m

inu

te orbital

period

.

NEX

T STEP

S:

Fall 20

19

Win

ter 20

20

Sp

ring

20

20

-Grou

nd

stationtestin

g-S

ub

systemtestin

g-

Man

ufactu

resu

bsystem

PC

Bs

-Vib

ration, th

ermal

vacuu

m, an

d sh

ocktestin

g-

Day in

the life

-Com

plete an

yred

esign

s-

Final

prep

arations for

laun

ch

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