satellite system engineering design tool ” m ......1. introduction satellite design area / design...
TRANSCRIPT
SATELLIT
E SYSTEM ENGIN
EERIN
G DESIG
N TOOL
“SSET”
M.M
irsham
s, R.M
akhmalbaf
Space Research Lab.
K.N.Toosi University of technology, Tehran, Iran
This project initiated in October 2004 and has been
developed in Space Research Lab of K.N. Toosi
University of technology of Iran.
The first phase of this project completed as version
3.4 in summer 2006.
This software can be used either for im
provem
ent
and optimization of an existing satellite design or
in a conceptual design stage of a new
mission.
Contents
Contents
1.Introduction
2.Software structure and design m
ethod
3.SSET introduction
4.SSET verification
5.Conclusion
1. Introduction
Satellite Design area / design m
ethods and parameters
Cs
C
Cm
C
Cl
C
Co
C
Cr
C
SED
SED
Ps
P
Pp
P
Pa
P
Ppl
P
PE
P
PB
P
Yr
life
Mission
Td
Tperiod
P
piVs
V
Te
T
Se
S
The
rurpr
mp
m
Rs
R
Ms
M
Ixx
I
Iyy
I
Izz
I
delta
MuTD
T
YTh
Phre
R
rrH S
M
LOrS
peak
av
PL
EOL
BOL
day
Satellite
eclipse
eclipse
eclipseppSS
xxyyzz
Dtotale
============
=
=
=
=
====
========
=∆
=
=
======
Pr
)(
h
π
θ
ρµψθϕ
max
min
ndeg
radatio
max
min
max
min
max
|
Re
tan
TT
TT
betxx
xx
betm
a
betmi
Asu
A
alb
a
Ka
K
rue
Qwa
Q
JeJ
StbJs
J
Emi
Abs
Tus
T
Tls
T
Tup
T
Tlp
T
Asp
Asp
Lcm
L
IbI
Vb
Voltage
bus
nBL
MEPS
M
Mreg
M
Mca
M
Mba
M
Msa
M
Asa
A
da
Array
Po
P
nb
N
Thwc
Psc
P
Xs
X
na
su
a
W
ES
USLS
UpLp
Cablingbus
BL
EPS
g
cabasaarray
Solar
ob
Case
Worst
tCons
Solar
S
array ==============
=======
=
=
=
======
=
=
==
=
=
==
β
ββ
ρσεαη
θ
η
1. Introduction
Main objective and taken solution
We want to design a suitable bus for a specific payload
We want to design a suitable bus for a specific payload
We need a system engineering design tool
We need a system engineering design tool
to produce and optimize desired answers
to produce and optimize desired answers
So
Contents
Contents
1.Introduction
2.Software structure and design m
ethod
3.SSET introduction
4.SSET verification
5.Conclusion
2. Software structure and design m
ethod
2.1. Designing the design process (META)
Start
MN + PL
0
ADCS
1
By: Makhmalbaf, Reza
SATELLITE SET – Program (+space m
ission)
End
VisioDocument
EPS
3
TCS
4
PROP
2
STS
5
ORB
8
TT&C+DH
6
MECH
7 ES
10
LV 9
Space Program
Payload
Bus
Orbit
Launch
Vehicle
Earth
Station
Space
segment
-Propulsion
-Mission + Payload
-Attitude Determination
and Control Subsystem
-Electronic Power
Subsystem
-Thermal Control
Subsystem
-Structure
Subsystem
-Telemetry, Tracking
and Command + Data
Handling Subsystem
-Mechanism
SSET m
ain design scenario
2. Software structure and design m
ethod
2.2. Choosing subsystem
s main parameters
Definition of coding
param
eters
nmm
N
nss
N
nes
N
mrw
M
nrw
N
mmw
M
nmw
N
Dm
D
BB
MM
Coe
C
Cle
C
Cse
C
Mse
M
cttc
C
pttc
P
mttc
M
hdr
Hdr
pco
Pco
osc
OSc
wco
Wco
pen
Pen
wen
Wen
vcdh
V
cme
Cme
nme
Nme
pcs
PCs
Trp
Trp
trw
Trw
rfp
RFP
mmSs
Es
rwrw
mw
mwMOeLe
Se
Se
TTC
TTc
TTC
cdh
==========================
=
====
MFS
standard
form
at
message
[][][]
][[]
][[]
].
[
][
].
[
$]
[
$]
[
$]
[
][
$]
[
][
][
][
][[]
][
][
][
][
][[][]
][
][
][
][
2
3
3
kgkg
mAteslam
tesla
mmmkgmWkgWkgWkgCm
MB
MHz
WkgW
sbits
2. Software structure and design m
ethod
2.3. Subsystem
s design algorithms
Satellite weight classification
2. Software structure and design m
ethod
2.3. Subsystem
s design algorithms
Satellite orbit height classification
2. Software structure and design m
ethod
2.3. Subsystem
s design algorithms
6489
.0
0033
.0
−×
=h
TDtotal
0802
.8
15
10
4−
××
=h
TDtotal
][
10
98
.3
2
35
skm
×=
µ
ϕµ
2sin
32
]))[
((
3
2
Dtotalyy
zz
Tr
kgm
II
=∆⇒
−=
∆
Calculating of disturbance torques
Not spin stabilization
Xs=1
O121
spin stabilization
O31131
Panel-mounted array
O31132
Body-mounted array
O122 = Theta-spin stabilization
No
Yes
O31133
Omni directional
O31132
Cylindrical
Xs=4
Xs=2.5
Not spin stabilization
Xs=1
O121
spin stabilization
O31131
Panel-mounted array
O31132
Body-mounted array
O122 = Theta-spin stabilization
No
Yes
O31133
Omni directional
O31132
Cylindrical
Xs=4
Xs=2.5
2. Software structure and design m
ethod
2.3. Subsystem
s design algorithms
Determining of arrays mounting m
ethod
Contents
Contents
1.Introduction
2.Software structure and design m
ethod
3.SSET introduction
4.SSET verification
5.Conclusion
3. SSET instruction
SSET welcome window
SSET m
ission specification
3. SSET instruction
SSET m
ission specification
3. SSET instruction
SSET m
ission specification
3. SSET instruction
Payload specification and initial guess
3. SSET instruction
Hint show as a help for beginner users
3. SSET instruction
SSET m
ain output (m
ass, power and cost budgets)
3. SSET instruction
Contents
Contents
1.Introduction
2.Software structure and design m
ethod
3.SSET introduction
4.SSET verification
5.Conclusion
4. SSET VERIFIC
ATIO
N
Assessing SSET by two real satellites
SSTL Enhanced M
icrosat
Payload specifications
Bus specifications
Bus specifications
Comparison
SSTL M
icroSat-70
Payload specifications
Bus specifications
Bus specifications
Comparison
4. SSET VERIFIC
ATIO
N
4.1. Assessing “SSET" by first satellite specifications
SSTL Enhanced M
icrosat
4. SSET VERIFIC
ATIO
N
Assessing “SSET" by second satellite specifications
SSTL M
icroSat-70
Contents
Contents
1.Introduction
2.Software structure and design m
ethod
3.SSET introduction
4.SSET verification
5.Conclusion
5. Conclusion
•Despite having some problems, the future for developing
countries in designing small scientific satellites depends on
strategy of space research technology. This strategy should
be base on system
atic view over the space industry.
•SSET (version 3.4) consist some modules the goal of them
are system
design of scientific satellite bus subsystem
s focusing on small and m
edium-sized satellites.
•SSET can help the beginners and senior designers enter the
world of satellite system
design.
•Our lab is ready to share its experiences with any inserted
organization or persons.
Thank you for your attention
Space Research Lab.
www.SPACERL.com