USA Master Template - Revised...SPACE SHUTTLE PROGRAM Orbiter Project Office NASA Johnson Space...
28
ABSTRACT Remote Controlled Orbiter Capability The Remote Control Orbiter (RCO) capability allows a Space Shuttle Orbiter to perform an unmanned re-entry and landing. This low-cost capability employs existing and newly added functions to perform key activities typically performed by flight crews and controllers during manned re-entries. During an RCO landing attempt, these functions are triggered by automation resident in the on-board computers or uplinked commands from flight controllers on the ground. In order to properly route certain commands to the appropriate hardware, an In-Flight Maintenance (IFM) cable was developed. Currently, the RCO capability is reserved for the scenario where a safe return of the crew from orbit may not be possible. The flight crew would remain in orbit and await a rescue mission. After the crew is rescued, the RCO capability would be used on the unmanned Orbiter in an attempt to salvage this national asset. https://ntrs.nasa.gov/search.jsp?R=20070019347 2020-06-27T22:03:03+00:00Z
Transcript of USA Master Template - Revised...SPACE SHUTTLE PROGRAM Orbiter Project Office NASA Johnson Space...
ABSTRACT Remote Controlled Orbiter Capability The Remote Control Orbiter (RCO) capability allows a Space Shuttle Orbiter to perform an unmanned re-entry and landing. This low-cost capability employs existing and newly added functions to perform key activities typically performed by flight crews and controllers during manned re-entries. During an RCO landing attempt, these functions are triggered by automation resident in the on-board computers or uplinked commands from flight controllers on the ground. In order to properly route certain commands to the appropriate hardware, an In-Flight Maintenance (IFM) cable was developed. Currently, the RCO capability is reserved for the scenario where a safe return of the crew from orbit may not be possible. The flight crew would remain in orbit and await a rescue mission. After the crew is rescued, the RCO capability would be used on the unmanned Orbiter in an attempt to salvage this national asset.
https://ntrs.nasa.gov/search.jsp?R=20070019347 2020-06-27T22:03:03+00:00Z
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0
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
ject
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
Rem
ote
Con
trol O
rbite
r Cap
abilit
y
AIA
A B
riefin
g05
/11/
07
M. G
arsk
e/N
ASA
RC
O P
roje
ct M
anag
er a
nd D
esig
n En
gine
erR
. de
la T
orre
/ Boe
ing
IDS
GN
C E
ntry
Eng
inee
r
Page
1
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
ject
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
RC
O A
bstr
act
The
Rem
ote
Con
trol O
rbite
r (R
CO
) cap
abili
ty a
llow
s a
Spa
ce S
huttl
e O
rbite
r to
perfo
rm a
n un
man
ned
re-e
ntry
and
land
ing.
Thi
s lo
w-c
ost c
apab
ility
empl
oys
exis
ting
and
new
ly a
dded
func
tions
to p
erfo
rm k
ey a
ctiv
ities
typi
cally
per
form
ed
by fl
ight
cre
ws
and
cont
rolle
rs d
urin
g m
anne
d re
-ent
ries.
Dur
ing
an R
CO
la
ndin
g at
tem
pt, t
hese
func
tions
are
trig
gere
d by
aut
omat
ion
resi
dent
in th
e on
-bo
ard
com
pute
rs o
r upl
inke
dco
mm
ands
from
flig
ht c
ontro
llers
on
the
grou
nd.
In o
rder
to p
rope
rly ro
ute
certa
in c
omm
ands
to th
e ap
prop
riate
har
dwar
e, a
n In
-Flig
ht M
aint
enan
ce (I
FM) c
able
was
dev
elop
ed. C
urre
ntly
, the
RC
Oca
pabi
lity
is re
serv
ed fo
r the
sce
nario
whe
re a
saf
e re
turn
of t
he c
rew
from
orb
it m
ay n
ot b
e po
ssib
le. T
he fl
ight
cre
w w
ould
rem
ain
in o
rbit
and
awai
t a re
scue
m
issi
on. A
fter t
he c
rew
is re
scue
d, th
e R
CO
cap
abili
ty w
ould
be
used
on
the
unm
anne
d O
rbite
r in
an a
ttem
pt to
sal
vage
this
nat
iona
l ass
et.
Page
2
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
ject
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
Aut
hor B
io’s
Mic
hael
T. G
arsk
e –
NA
SA
, Spa
ce S
huttl
e P
rogr
am, O
rbite
r Pro
ject
Offi
ce
281-
483-
0790
mic
hael
.t.ga
rske
@na
sa.g
ov
Mr.
Gar
ske
has
alm
ost 2
3 ye
ars
of c
ombi
ned
expe
rienc
e in
NA
SA
wor
king
for t
he S
pace
Shu
ttle
Pro
gram
in
eng
inee
ring,
ope
ratio
ns, a
nd m
anag
emen
t fro
m tw
o N
AS
A c
ente
rs-K
enne
dy a
nd J
ohns
on S
pace
C
ente
rs.
He
earn
ed h
is B
.S. i
n Te
chni
cal P
hysi
cs a
nd A
.A. i
n A
stro
nom
y fro
m S
outh
wes
t Mis
sour
i S
tate
Uni
vers
ity in
198
3 an
d a
M.S
. in
Eng
inee
ring
Man
agem
ent f
rom
Uni
vers
ity o
f Cen
tral F
lorid
a in
19
90.
He
is th
e S
enio
r Pro
ject
Man
ager
for t
he O
rbite
r Pro
ject
Offi
ce a
nd is
the
Pro
ject
Man
ager
for
RC
O.
He'
s ea
rned
man
y N
AS
A a
war
ds in
clud
ing
the
NA
SA
Exc
eptio
nal S
ervi
ce M
edal
and
the
NA
SA
Spa
ce F
light
Aw
aren
ess
Aw
ard.
Raf
ael d
e la
Tor
re –
Boei
ng ID
S, S
pace
Exp
lora
tion
Div
isio
n
Mr.
de la
Tor
re h
as o
ver 9
yea
rs e
xper
ienc
e in
the
Spa
ce S
huttl
ePr
ogra
m a
s a
cont
ract
or a
t the
Ken
nedy
an
d Jo
hnso
n S
pace
Cen
ters
. He
has
been
ana
lyzi
ng th
e S
pace
Shu
ttle
Orb
iter E
ntry
GN
&C
sys
tem
an
d O
rbite
r ent
ry a
nd la
ndin
g pe
rform
ance
for t
he la
st 7
yea
rs. I
n ad
ditio
n to
his
ana
lysi
s ac
tiviti
es, h
is
curre
nt re
spon
sibi
litie
s in
clud
e ow
ners
hip
of s
ever
al fl
ight
sof
twar
e fu
nctio
ns re
late
d to
the
entry
G
N&
C s
yste
m, i
nclu
ding
app
roac
h an
d la
ndin
g gu
idan
ce a
nd th
e he
ad-u
p di
spla
y. H
e ea
rned
his
B.S
. in
Aer
ospa
ce E
ngin
eerin
g fro
m E
mbr
y-R
iddl
e A
eron
autic
al U
nive
rsity
in 2
000
and
M.S
. in
Phy
sics
fro
m T
he U
nive
rsity
of H
oust
on -
Cle
ar L
ake
in 2
007.
He
has
been
a k
ey c
ontri
buto
r to
deve
lopi
ng,
impl
emen
ting
and
test
ing
GN
&C
-rela
ted
softw
are
mod
ifica
tions
in s
uppo
rt of
RC
O.
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
gram
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
Page
4
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
ject
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
Intr
oduc
tion
•In
itial
ass
umpt
ion
or ri
sk is
that
the
Orb
iter T
ile P
rote
ctio
n Sy
stem
(TPS
) co
uld
suffe
r dam
age
such
that
re-e
ntry
with
flig
ht c
rew
wou
ld b
e to
o ris
ky,
even
if re
paire
d•
The
Spac
e Sh
uttle
Pro
gram
(SSP
) Mis
sion
Man
agem
ent T
eam
(MM
T) w
ould
de
clar
e a
Safe
Hav
en a
nd b
egin
cre
w re
scue
ope
ratio
ns v
ia a
noth
er s
huttl
e la
unch
•M
eanw
hile
, the
“co
mpr
omis
ed”
Orb
iter w
ould
be
a su
rrog
ate
to th
est
rand
ed
crew
and
ISS
crew
and
its
reso
urce
s de
plet
ed to
min
imum
requ
ired
to
supp
ort a
re-e
ntry
/bre
akup
for a
n oc
ean
ditc
h•
Spac
e Sh
uttle
Pro
gram
was
sea
rchi
ng fo
r eas
y co
ncep
t to
retr
ieve
/reco
ver a
co
mpr
omis
ed O
rbite
r and
not
dis
card
a v
alua
ble
asse
t•
The
Rem
ote
Con
trol
Orb
iter (
RC
O) c
apab
ility
was
dev
elop
ed a
nd
impl
emen
ted
to p
rovi
de th
e SS
P th
e ca
pabi
lity
to la
nd th
e O
rbite
r with
out a
fli
ght c
rew
in a
n em
erge
ncy
situ
atio
n –
Use
s th
e A
utol
and
func
tiona
lity
•Th
e Sp
ace
Shut
tle P
rogr
am h
as re
ques
ted
a ca
pabi
lity
to re
cove
r the
veh
icle
in
lieu
of a
n oc
ean
ditc
h w
hen
a Sa
fe H
aven
has
bee
n de
clar
ed –
Salv
age
oper
atio
n
Page
5
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
ject
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
Ove
rvie
w
•Th
e O
rbite
r flig
ht d
eck
pane
ls th
at a
re u
sed
to m
anua
lly c
ontr
olth
e fo
llow
ing
func
tions
wer
e ta
rget
ed to
be
reco
nfig
ured
:–
APU
sta
rt/ru
n–
Air
Dat
a Pr
obe
(AD
P) d
eplo
y–
Mai
n La
ndin
g G
ear (
MLG
) arm
/dow
n–
Dra
g C
hute
arm
/dep
loy
–Fu
el C
ell r
eact
ant v
alve
clo
sure
•Th
e re
conf
igur
atio
n is
acc
ompl
ishe
d by
the
fligh
t cre
w p
erfo
rmin
g an
In-F
light
M
aint
enan
ce (I
FM) p
roce
dure
to in
stal
l a p
re-fa
bric
ated
cab
le a
nd lo
adin
g sp
ecia
l so
ftwar
e de
sign
ed to
sup
port
cap
abili
ty•
RC
O IF
M in
stal
ls a
cab
le to
pro
vide
ele
ctric
al c
onne
ctiv
ity fr
omG
roun
d C
ontr
ol
Inte
rfac
e Lo
gic
(GC
IL) a
vion
ics
box
up to
the
fligh
t dec
k pa
nel s
witc
hes
–En
able
s gr
ound
con
trol
lers
to c
ontr
ol th
e ta
rget
ed fu
nctio
ns v
iaco
mm
and
uplin
k–
Allo
ws
fligh
t sof
twar
e to
con
trol
cer
tain
targ
eted
func
tions
•Th
e ca
ble
is 2
8 fe
et lo
ng, w
eigh
s 5.
4 lb
s, a
nd is
sto
wed
on
the
ISS
for e
mer
genc
y us
e•
RC
O IF
M C
able
with
its
supp
ortin
g fli
ght s
oftw
are
chan
ge w
ill p
rovi
de th
e SS
P th
e ca
pabi
lity
to la
nd th
e O
rbite
r with
out a
flig
ht c
rew
in a
n em
erge
ncy
situ
atio
n
Page
6
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
ject
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
Prog
ram
Des
ign
Gro
undr
ules
•R
CO
IFM
Cab
le s
uppo
rts a
n em
erge
ncy
cont
inge
ncy
oper
atio
n
•R
CO
IFM
Cab
le m
ust b
e si
ngle
faul
t tol
eran
t for
func
tions
that
:
–A
ffect
cre
w s
afet
y (w
hile
doc
ked
or d
urin
g un
dock
ing
oper
atio
ns)
–A
ffect
the
safe
ty o
f peo
ple
on th
e gr
ound
•Ze
ro fa
ult t
oler
ance
for R
CO
IFM
Cab
le fu
nctio
ns th
at p
rote
ct fr
om lo
ss o
f V
ehic
le
•Th
e la
ndin
g si
te s
hall
be V
ande
nber
g.
•S
yste
ms
certi
ficat
ion
is n
ot p
erfo
rmed
.
•Th
e R
CO
Cab
le s
hall
be in
stal
led
as a
n In
Flig
ht M
aint
enan
ce (I
FM).
•S
AIL
func
tiona
l ver
ifica
tion
test
ing
shal
l be
perfo
rmed
•B
uild
one
cab
le fo
r flig
ht a
nd o
ne fo
r SA
IL.
–S
tow
one
flig
ht c
able
onb
oard
ISS
.
Page
7
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
ject
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
RC
O C
able
Page
8
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
ject
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
RC
O IF
M C
once
pt
•One
RC
O IF
M c
able
for S
AIL
to s
uppo
rt in
tegr
atio
n of
har
dwar
e/so
ftwar
e av
ioni
cs
test
ing,
IFM
ver
ifica
tion
and
one
cabl
e fo
r flig
ht
BAY
1
BAY
2
BAY
3A
PI-1
&2Pa
nel C
3A5
(not
all
2 co
nnec
tors
de
pict
ed)
Pane
l F6A
3(n
ot a
ll 3
conn
ecto
rs
depi
cted
)Pa
nel F
2
Rec
omm
ende
d Fe
edth
ru(p
ort
side
) for
SA
ILR
oute
and
sec
ure
with
tie
wra
ps, v
elcr
ost
raps
, and
duc
t ta
pe.
Pane
l R2
GC
IL
Rec
omm
ende
d fe
edth
ru(s
tarb
oard
) for
Flig
htR
oute
and
sec
ure
with
tie
wra
ps, v
elcr
ost
raps
, and
duc
t ta
pe.
Page
9
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
ject
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
RC
O C
able
Rou
ting
PN
L F6
A3
(Lan
ding
Gea
r Con
trols
)M
idde
ckA
vion
ics
Bay
3A
GC
IL h
ooku
p
Page
10
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
ject
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
RC
O F
light
Sof
twar
e
•SW
cha
nges
targ
eted
onl
y ne
cess
ary
item
s–
Crit
ical
and
cou
ld n
ot b
e up
linke
d–
Tim
e-cr
itica
l com
man
ds•
Cha
nges
impl
emen
ted
via
phas
ed a
ppro
ach
–O
I-30
STS
-117
•S
peci
al F
light
Sof
twar
e pa
tch
•O
MS
Bur
n en
able
win
dow
exp
ansi
on fo
r Deo
rbit
burn
(15
sec
–3
min
)•
Sta
te V
ecto
r inf
o tra
nsfe
r fro
m G
3 to
S2
durin
g en
try o
ps fo
r ant
enna
m
anag
emen
t–
OI-3
2 S
TS-1
20•
OI-3
0 ch
ange
s ba
selin
edin
FS
W•
RC
O In
hibi
t/Ena
ble
ITE
M e
ntry
add
ed to
dis
play
for a
ctiv
atio
n of
FSW
fu
nctio
ns–
OI-3
3 TB
D•
Aut
omat
es la
ndin
g ge
ar a
nd d
rag
chut
e ar
m &
dep
loy
•In
corp
orat
es G
PS
dur
ing
rollo
ut fo
r lat
eral
trac
king
Page
11
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
ject
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
SAIL
Tes
ting
(OV-
095)
•H
isto
ry m
akin
g ev
ent…
Firs
t tim
e G
3 an
d S
2 G
PC
mem
ory
conf
igur
atio
n co
mbi
natio
n w
as u
sed
for e
ntry
and
land
ing
•V
erifi
ed F
light
Sof
twar
e m
ods
are
read
y to
sup
port
STS
-117
with
OI-3
0
•V
erifi
ed F
light
Sof
twar
e m
ods
are
read
y to
sup
port
STS
-120
with
OI-3
2
•V
erifi
ed h
ardw
are
inte
rface
s (v
olta
ge a
nd c
urre
nt le
vels
)
•Te
st ru
n of
IFM
inst
alla
tion
and
proc
edur
e w
ith S
TS-1
21 C
rew
•A
lso,
und
ock
and
back
aw
ay s
teps
, inc
ludi
ng P
LBD
clo
sure
via
man
ual
uplin
k co
mm
ands
wer
e ru
n an
d va
lidat
ed
Page
12
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
ject
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
Uni
que
Ops
Gui
delin
es
•O
rbit
SM c
ontr
ollin
g PL
MD
Ms
thro
ugh
land
ing
(No
BFS
load
ed/ru
nnin
g)–
Supp
orts
Ant
enna
Man
agem
ent f
or c
omm
unic
atio
ns–
Supp
orts
PLB
D c
losu
re–
Har
dwar
e co
nfig
urat
ion
cons
trai
nts
prev
ent u
se o
f BFS
–SM
is m
ore
robu
st o
pera
ting
syst
em•
Vand
enbe
rg s
elec
ted
as la
ndin
g si
te–
Low
est r
isk
to th
e pu
blic
or g
roun
d re
sour
ces
due
to w
ater
app
roac
h–
Nee
ds M
LS e
quip
men
t ins
talle
d to
sup
port
aut
olan
dso
ftwar
e–
Orb
iter F
SW m
ods
(OI-3
3) e
nabl
e G
PS d
urin
g la
ndin
g ro
llout
•A
utol
and
GN
C c
apab
ility
will
be
utili
zed
–A
ppro
ach
& L
andi
ng p
itch
and
roll
guid
ance
–A
utom
ated
land
ing
gear
and
dra
g ch
ute
depl
oy (O
I-33)
–A
uto
dero
tatio
nan
d no
se-w
heel
ste
erin
g du
ring
rollo
ut
Page
13
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
ject
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
Ops
Ove
rvie
w
•O
n O
rbit
-Saf
e H
aven
Dec
lare
d, S
alva
ge th
e O
rbite
r
–D
ocke
d w
ith IS
S
–S
ome
leve
l of T
PS
repa
irs c
ould
be
perfo
rmed
–P
repa
re O
rbite
r for
rem
ote
cont
rolle
d ca
pabi
lity
•P
erfo
rm IF
M’s
(und
ock
and
RC
O) a
nd c
ockp
it sw
itchl
ist(
entry
)•
Ena
ble
RC
O F
light
Sof
twar
e
–C
rew
Egr
ess
to IS
S, c
lose
and
sec
ure
hatc
h•
Han
dove
r Orb
iter c
ontro
l to
MC
C g
roun
d fli
ght c
ontro
llers
–U
ndoc
k &
Sep
arat
e O
rbite
r fro
m IS
S•
Gro
und
uplin
ks D
EU
’sno
rmal
ly p
erfo
rmed
by
crew
key
boar
d en
tries
Page
14
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
ject
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
Ops
Ove
rvie
w C
ontin
ued
•P
re-D
eOrb
itB
urn
setu
ps
–C
onfig
ure
GP
C’s
to G
3/S
2 m
emor
y co
nfig
urat
ion
(Not
e: n
o B
FS)
•Lo
ad a
nd a
ctiv
ate
TFL
172
dow
nlin
k te
lem
etry
form
at (n
orm
ally
164
)
–U
plin
k an
d lo
ad D
eOrb
itta
rget
s
–U
plin
k S
tore
d P
rogr
amm
ed C
omm
ands
•S
PC
’sar
e up
linke
dan
d st
ored
onb
oard
for t
imed
ex
ecut
ion…
grou
nd u
ses
traje
ctor
y pr
edic
tion
tool
s to
pre
dict
the
time
for e
xecu
tion
of th
e fo
llow
ing
RC
O fu
nctio
ns:
–A
ir D
ata
Pro
bes
Dep
loym
ent
–La
ndin
g G
ear D
eplo
ymen
t (O
I-30,
OI-3
2)–
Dra
g C
hute
Dep
loym
ent (
OI-3
0, O
I-32)
–Fu
el C
ell S
hutd
own
–C
lose
Pay
load
Bay
Doo
rs
–S
tart
thre
e A
PU
’svi
a R
eal T
ime
Com
man
d up
link
Page
15
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
ject
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
Ops
Ove
rvie
w C
ontin
ued
•P
erfo
rm D
e-O
rbit
Bur
n
–C
omm
and
GP
C’s
to G
NC
Maj
or M
ode
303
and
to S
M M
ajor
Mod
e 20
1
–A
PU
’sto
nor
m P
ress
(HY
D P
ress
ure
to n
orm
al) v
ia u
plin
k R
TC
–C
omm
and
GP
C’s
to G
NC
Maj
or M
ode
304
•E
ntry
Inte
rface
, 400
,000
ft.
•A
t Mac
h 5,
the
Air
Dat
a P
robe
s de
ploy
via
onb
oard
SP
C
•A
t Mac
h 2.
5 en
ter t
he T
AEM
inte
rface
•A
ppro
ach
and
Land
ing
inte
rface
at T
ouch
dow
n m
inus
~80
sec
onds
•A
t 200
0 ft.
, the
Lan
ding
Gea
r is
arm
ed a
nd d
eplo
yed
*
•To
uchd
own
–A
rm a
nd d
eplo
y dr
ag c
hute
*
–A
uto
dero
tatio
nan
d st
eerin
g (u
sing
GP
S in
OI-3
3)
•La
ndin
g R
ollo
ut c
ompl
ete
–O
rbite
r Pow
er d
own
via
onbo
ard
SP
C to
clo
se F
uel C
ell R
eact
ant v
alve
s
*via
onb
oard
SP
C th
roug
h O
I-32,
Aut
omat
ed fo
r OI-3
3
Page
16
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
ject
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
Ris
ks/c
once
rns
•N
one
at th
e C
able
leve
l
•O
nly
parti
al c
heck
out c
apab
ility
prio
r to
use
can
be a
ccom
mod
ated
on-
orbi
t
•O
verfl
ight
risk
NO
T an
issu
e fo
r MM
T an
d A
genc
y w
ith w
ater
app
roac
h to
Van
denb
erg
•V
ande
nber
g su
ppor
t fac
ilitie
s ne
ar ru
nway
cou
ld s
usta
in d
amag
e
•R
CO
IFM
Cab
le lo
ss o
f fun
ctio
n/re
sult
tabl
e:
Func
tion
Loss
Of F
unct
ion/
Act
ion
Res
ult
Sta
rt A
PU
sAc
tivat
e 3
prio
r to
de-o
rbit
burn
. If
2 o
f 2
AP
U s
tring
s do
not
act
ivat
e, e
xecu
te o
cean
di
tch
If ai
r dat
a pr
obes
fails
to d
eplo
y, ta
ke
Nav
igat
ion
Der
ived
Air
Dat
a S
houl
d ge
ar fa
il, th
en la
ndin
g w
ill be
with
ge
ar u
p
If D
rag
chut
e fa
ils to
dep
loy,
then
runw
ay
rol lo
ut w
ill be
long
Fuel
cel
l(s) e
xpec
ted
to o
verh
eat,
if he
at
reje
ctio
n lo
st, p
rior t
o ru
nnin
g ou
t of c
ryo
whi
le s
till p
rodu
cing
pow
er.
Loss
of O
rbite
r in
ocea
n
Dep
loy
Air
Dat
a P
robe
Pote
ntia
l los
s of
Orb
iter
with
in la
ndin
g si
teA
rm, D
eplo
y La
ndin
g G
ear
Loss
of O
rbite
r on
runw
ay
and
pote
ntia
l fac
ilitie
s da
mag
eD
eplo
y D
rag
Chu
teEx
ceed
ing
runw
ay le
ngth
m
ay c
ause
dam
age
to
Orb
iter
Em
erge
ncy
Pow
er D
own
Pot
entia
l los
s of
Orb
iter o
n ru
nway
due
to F
uel C
ell
over
tem
p.
Page
17
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
ject
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
Sum
mar
y
•Th
e R
CO
IFM
Cab
le w
ith it
s su
ppor
ting
fligh
t sof
twar
e ch
ange
will
pro
vide
th
e SS
P th
e ca
pabi
lity
to la
nd th
e O
rbite
r with
out a
flig
ht c
rew
in a
n em
erge
ncy
situ
atio
n•
The
RC
O IF
M C
able
and
con
cept
pro
vide
s th
e be
nefit
of r
ecov
erin
ga
high
va
lued
ass
et in
lieu
of d
isca
rdin
g in
the
ocea
n
Bac
kup
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
gram
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
gram
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
TPS
Re-
enfo
rced
Car
bon-
Car
bon
(RC
C)
TPS
Tile
Page
20
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
ject
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
Pane
ls A
cces
sed
F7F6
F8
F1W
3W
4W
5
W6
W2
W1
F2F4
F3
A2
F5
L1
L4
L2L3
A2A1
A2
A1C
1C
4C
5
B1
B2
C2
C3
A1
A2
A3
A1
A6
A7
A3
A5
C6
C7
S2S1
A2
A1
F9
R1
R2R3
R5
R4
A2
R7
R6
R8
R9
L6
L5
L7
L8
O1
O2
O3
O6
O7
O8
O5
O9
O13
O14
O15
O16
O17
O18
O19
O20
A8
A2
A6
A9
A10
A12
A11
A9
A12
A13
A3
A4
A9
A12
A13
A3
A4
Pane
l R2
APU
Ope
rate
APU
Hyd
Mai
n Pu
mp
Pres
sure
Pane
l C3A
5Fu
el C
ell R
eact
ant V
alve
Dep
loy
Left
Air
Dat
a Pr
obe
Pane
l F6A
3La
ndin
g G
ear A
RM
Land
ing
Gea
r DO
WN
Pane
l F2
Dra
g-C
hute
AR
MD
rag-
Chu
te D
EPLO
Y
Page
21
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
ject
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
Com
man
d/dr
iver
Ove
rvie
w
Upl
ink
Com
man
ds/
Dow
nlin
k
Com
mG
PC
NS
P/
MD
M
PC
MM
U
PL M
DM
GC
ILD
river
s
PSP-
1LC
Adr
iver
Gea
r Arm
APU
1, 2
, 3St
art/r
un(lo
w p
ress
/nor
m)
L&R
AD
Pde
ploy
Dra
g C
hute
Arm
/dep
loy
Fuel
Cel
l1
and
3Sh
utdo
wn*
*
** N
ote
Fuel
Cel
l 2 is
alre
ady
dow
nM
N A
to M
N B
bus
s tie
Orb
iter G
CIL
/LC
A D
river
sO
rbite
r Flig
ht D
eck
Pan
el F
unct
ions
RC
O IF
M
Cab
le
PSP-
2LC
Adr
iver
PI-1
LCA
Driv
er*
PI-2
LCA
driv
er
Gea
r Dow
n
* Not
e PI
-1 L
CA
driv
er w
ill be
dio
de la
tche
d O
N w
hen
activ
ated
.
L&R
AD
PA
RM
Page
22
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
ject
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
RC
O C
able
Des
ign
Ana
lysi
s
•FM
EA b
ent p
in a
naly
sis
perf
orm
ed•
Orb
iter s
yste
m c
ircui
t ana
lysi
s pe
rfor
med
•H
azar
d an
alys
is p
erfo
rmed
•M
ater
ials
cer
tific
atio
n co
mpl
eted
•Pa
rts
dera
ting
anal
ysis
per
form
ed•
EMI a
naly
sis
perf
orm
ed
Page
23
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
ject
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
RC
O C
able
Har
dwar
e
•R
CO
IFM
Cab
le p
arts
list
(one
cab
le)
–16
con
nect
ors
with
pin
s, b
acks
hells
, and
cap
s–
~800
ft 2
2AW
G N
icke
l coa
ted
wire
(MIL
-W-2
2759
/12-
22-9
)–
5 di
odes
(JA
NTX
1N49
42)
–sp
lices
–G
orte
xou
ter j
acke
t for
cab
le p
rote
ctio
n–
Velc
ro s
trap
s–
Oth
er s
mal
l har
dwar
e m
isc…
Page
24
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
ject
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
RC
O O
pera
tiona
l Gui
delin
es
•O
ther
than
the
initi
al o
rbite
r TP
S d
amag
e ca
usin
g S
afe
Hav
en, a
ll ot
her o
rbite
r sy
stem
s ar
e fu
lly fu
nctio
nal
–A
vion
ics
and
Flig
ht C
ontro
l Sys
tem
s re
dund
ancy
not
cha
nged
exc
ept:
•P
L1 M
DM
J6
dem
ated
due
to C
ontin
genc
y S
huttl
e C
rew
Sup
port
(CS
CS
) IF
M
•R
isk
asse
ssm
ent f
or V
ehic
le s
urvi
vabi
lity
durin
g re
-ent
ry is
som
ewhe
re b
etw
een
re-e
ntry
with
cre
w o
nboa
rd a
nd o
cean
ditc
h•
Use
Saf
e H
aven
IFM
und
ocki
ng a
ppro
ach
•Ta
sks
hist
oric
ally
per
form
ed b
y th
e C
rew
acc
omm
odat
ed b
y;–
Gro
und
uplin
k (R
TC’s
and
DE
U E
quiv
alen
ts)
–G
roun
d up
link
Sto
red
Pro
gram
Com
man
ds (S
PC
’s) t
o ac
com
mod
ate
time
criti
cal e
vent
s•
Cre
w w
ill in
stal
l IFM
har
dwar
e an
d pr
e-co
nfig
ure
nece
ssar
y sw
itche
s•
The
Orb
iter i
s re
ady
to b
e co
mm
ande
d, re
-ent
er, a
nd la
nd re
mot
ely,
via
gro
und
cont
rol o
nce
the
RC
O IF
M is
inst
alle
d•
Aut
olan
dfu
nctio
nalit
y is
NO
T af
fect
ed
Page
25
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
ject
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
RC
O T
imel
ine
Even
tTi
me
Task
Pre-
Und
ock
Prep
arat
ion
Pre-
Und
ock
IFM
Inst
alla
tion
Con
figur
e D
PS, G
PC 5
to S
M O
PS 2
(SM
MM
201
)
Ku-B
and
Ante
nna
Stow
APU
Con
fig
Dea
ctiv
ate
Star
Tra
cker
s an
d cl
ose
door
s
H2O
Loo
p C
onfig
FES
Che
ckou
t
OM
S/R
CSC
onfig
NW
S E
nabl
e
FES/
NH
3 C
onfig
Con
figur
e fo
r Pay
load
Bay
Doo
r clo
sing
Con
figur
e TC
S
Hyd
raul
ic S
ys C
onfig
Clo
se H
atch
es
Sepa
ratio
n M
aneu
ver
Und
ock
Fire
Aft
Pitc
h R
CS
jets
bur
st -
atta
in 0
.22
fps
vel
Und
ock
+ 9
sec
Uni
vers
al P
oint
ing
Item
21
at 2
ft s
epar
atio
n
Und
ock
+ 2
min
Ope
n D
AP d
eadb
ands
to c
onfig
ure
for f
ree
drift
Und
ock
+ 32
min
Clo
se D
AP d
eadb
ands
Reb
oost
Man
euve
rM
aneu
ver t
o re
boos
tbur
n at
titud
e
Und
ock
+ 42
min
Perfo
rm p
osig
rade
+X re
boos
tbur
n
Man
euve
r to
com
mat
titud
eTI
G -
80 m
inM
aneu
ver t
o co
mm
unic
atio
ns a
ttitu
de
Con
figur
e D
PS fo
r Ent
ryTI
G -
70 m
inG
NC
GPC
sto
MM
301
Page
26
SPA
CE
SHU
TTLE
PR
OG
RA
MO
rbite
r Pro
ject
Offi
ceN
ASA
Joh
nson
Spa
ce C
ente
r, H
oust
on, T
exas
RC
O T
imel
ine
Con
t’dU
plin
k D
eorb
itTa
rget
sTI
G -
30 m
inU
plin
k de
orbi
ttar
gets
Upl
ink
SPC
sU
plin
k SM
Sto
red
Prog
ram
Com
man
ds
Tran
sitio
n to
GN
C M
M 3
02TI
G -
25 m
inU
plin
k C
md
GN
C G
PCs
to M
M 3
02
Tran
sitio
n to
SM
MM
202
TIG
-24
min
Upl
ink
Cm
dSM
GPC
to M
M 2
02
Load
Deo
rbit
Targ
ets
TIG
-20
min
Upl
ink
Load
deo
rbit
targ
ets
Man
euve
r to
Deo
rbit
Attit
ude
Man
euve
r to
deor
bita
ttitu
de
Clo
se P
aylo
ad B
ay D
oors
TIG
-15
min
Upl
ink
SM O
PS 2
02 C
md
to c
lose
Pay
load
Bay
doo
rs
Star
t APU
1, 2
and
3TI
G -
5 m
inC
md
APU
1, 2
, and
3 S
tart
–U
plin
k R
TC
Deo
rbit
Burn
Exe
cTI
G -
60 s
ecU
plin
k de
orbi
tbur
n E
xec
Cm
d
TIG
Perfo
rm d
eorb
itbu
rn
Tran
sitio
n to
GN
C M
M 3
03EI
-15
min
Upl
ink
Cm
dG
NC
GPC
sto
MM
303
Upl
ink
Cm
dG
PS to
Nav
Auto
Tran
sitio
n to
SM
MM
201
EI -
14 m
inU
plin
k C
md
SM G
PC to
MM
201
APU
sPr
ess
EI -
13 m
inAP
Us
to N
orm
Pre
ss –
uplin
k R
TC
Man
euve
r to
EI -
5 At
titud
eEI
-10
min
Upl
ink
Cm
dto
man
euve
r to
EI -
5 at
titud
e
Cm
dG
NC
GPC
sto
MM
304
EI -
5 m
inU
plin
k C
md
GN
C G
PCs
to M
M 3
04
Entry
Inte
rface
EIEn
try In
terfa
ce, h
= 4
00,0
00 ft
Dep
loy
Air D
ata
Prob
eM
= 5
Arm
and
Dep
loy
Air D
ata
Prob
e -S
M S
PC
TAEM
Inte
rface
M =
2.5
TAEM
Inte
rface
Appr
oach
and
Lan
ding
Inte
rface
TD -
80 s
ecAp
proa
ch a
nd L
andi
ng In
terfa
ce
Arm
/Dep
loy
Land
ing
Gea
rh
= 20
00 ft
Arm
and
Dep
loy
Land
ing
Gea
r -SM
SPC
Touc
hdow
nTD
Touc
hdow
n
Arm
/Dep
loy
Dra
g C
hute
TD +
7 s
ecAr
m/D
eplo
y D
rag
Chu
te -
SM S
PC
Orb
iter P
ower
dow
nR
ollo
ut c
ompl
ete
Cm
dFu
el C
ell R
eact
ant V
alve
s C
lose
d -S
M S
PC
