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Columbus, present programme status
COLlllUS, P ~ T I ~ J O ~
F. E n ~ t r ~ ¢
STATUS
end G. a l t m ~
Directorate ot Sp~e Station e~l Plati'or~ ~ r ~ e e n S ~ c e Agency, P a r i s
Abatract Station.
The Coltmbus
progrP~me
The status of the
description
of
the
includes Europe's
contribution
present activities is described in
candidate
free-flyer, and polar platform.
hardware
elements
-
Also, an enhanced
considered as an Earth-based co-orbiter is
to the
international
Space
this paper.
It includes a
brief
attached
pressurised
module,
man-tended
version of the baseline Eureca which is
described.
Attendant programmatic data are
being
discussed
using Europe's long-term aim of eventual autonomy as a back-cloth. The role of the potential users of Space Station elements is stressed in the paper and
plans
for ensuring good use of the new capabilities available are presented.
I.
Introduction
E u r o p e ' s i n v o l v ~ e n t w i t h man-in-space s t a r t e d with Spacelab.
Its highly successful first
flight
in November 1983 r e p r e s e n t e d an important m i l e s t o n e in Europe's commitment to manned
spaceflight.
Through this programme, the European SpsceAgency
considerable
experience in manned space activities and in space project. systm
(ESA) and its Member States gained
the management and conduct of a large
international
It also produced a solid industrial structure for the development of manned
and generated a class of potential
users that embraced the old established
space
experimenters
(such an astronomy and space physics) and new ones such as those in the microgravity sciences. Following the invitation of President Reagan to the US in
creating an internatianal
america's "friends and allies" to join
space station, ESA
.~k~ber States in this
exciting venture.
Eased
respond positivelyand
to join the progremme as a
took over the
with
role of representing
on its Spacelab experience,
Europe was ready
its to
reliable and inventive partner.
Initial work carried out by ESA as part of its long term planning and in its Member States particularly Germany and Italy - led to early concepts for Space Station participation. armed with these results, the ESA Council met at 1984.
This meeting provided an
Ministers recognised
successes of
Agency's programmes should be enlarged.
* **
Ministerial level in Rome at the end of
opportunity to review past
the previous
Suitably
ESA and
In particular
and possible future activities. considered that
the scope
The
of all
the
the Ariane V heavy launcher programme
was
ProgrmDirector, Paris, France Head, Columbus Systems and Projects Department, Noordwijk, Holland
601
January
approved emd t h e u n d e r t a k i n g o f a Coltmbun Space S t a t i o n
was
endorsed.
~uropean f a c i l i t i e s
One
P r e p a r a t o r y Progresme towards p a r t i c i p a t i o n in t h e
important
objective stated
was
"...
to
prepare
US
autonomous
f o r t h e s u p p o r t o f m a n - i n - s p a c e , f o r t h e t r a n s p o r t o f equipment end crews
end
f o r making u s e o f low-Earth o r b i t s " . To meet progrsme.
the goals
expressed
at the
Europe.
The
results will
m e e t i n g p l a n n e d f o r l a t e r t h i s y e a r when
2.
SSA e n t e r e d phase
B of
the
Columbus
The aim was to e v a l u a t e l i k e l y c a n d i d a t e s and t o d e t e r m i n e t h e t e c h n o l o g y and
implications for
made.
Rone m e e t i n g ,
be
presented to
a further
funding
Minister~level
Council
a commitment t o s p e c i f i c hardware c o n t r i b u t i o n s will
be
T h i s paper p r e s e n t s t h e s t a t u s o f t h e Progresme a s o f J u l y 1987.
| l e m m t s of t h e Col~bum P r o g r s m e
The work c a r r i e d o u t areas.
These
iceaaries,
in phase B of
include
t h e Coltmbus P r e p a r a t o r y programme h a s covered many
utilisation
potential,
operations
supporting
technology
related
end
a s w e l l a s d e s i g n end c o s t e n a l y e e s o f t h e c a n d i d a t e e l e m e n t s themBelves.
mission
In p a r a l l e l ,
t h e importance o f r e l e v a n t r e l a t e d p r o g r m m e s s u c h a s Ariene V, Hermes and u s e r d i s c i p l i n e s t u d i e s was e v a l u a t e d
and n e g o t i a t i o n s
w i t h NASA end
fellow participants
initiated
and
a
continuing
d i a l o g u e n e t up. As a r e s u l t o f
these diverse studies,
three basic candidates
have been f i r m l y
identified,
viz. : a
A p r e s a u r i s e d l a b o r a t o r y module p e r m a n e n t l y a t t a c h e d t o t h e main Space S t a t i o n .
D
A man-tended f r e e - f l y e r c o n s i s t i n g o f a p r e s s u r i s e d module and a r e s o u r c e s module.
It
o p e r a t e s i n a f r e e - f l y i n g mode and i n p e r i o d i c a l l y s e r v i c e d . A p o l a r p l a t f o r m , which o p e r a t e s mmanned in p o l a r o r b i t end be s e r v i c e d p e r i o d i c a l l y by t h e S h u t t l e (depends on t h e r e - o p e n i n g o f t h e Western T e s t Range t o S h u t t l e l a u n c h e s ) . In a d d i t i o n , a s m a l l , g r o u n d - b a s e d p l a t f o r m b a s e d on Euroca t e c h n o l o g y i s b e i n g e v a l u a t e d
as
a possible co-orbiting platform. Theme v a r i o u s f l i g h t e l e m e n t s a r e d e s c r i b e d below.
2. I
A t t a c h e d P r e e s u r i a e d Module (AIM)
Nssmed m i s s i o n s a t t h e Space S t a t i o n c o r e a r e s u p p o r t e d by t h e A t t a c h e d P r e s s u r i s e d Module.
This
I s b u r a t o r y module o f f e r s r e s e a r c h o p p o r t u n i t i e s
t h e p r e s e n c e o f man
over
O b s e r v a t i o n beve i n t e r e s t i n
this
l o n g p e r i o d s o f time.
Although
S c i e n c e , Technology end E a r t h
a l e a m a t , t h e u s e o f t h e AIM i s p r i m a r i l y mad L i f e S c i e n c e s .
in a l l a r e a s r e q u i r i n g
These a c t i v i t i e s
in t h e d i s c i p l i n e s o f F l u i d S c i e n c e s , M a t e r i a l
Sciences
span a wide r a n g e , c o n t r i b u t i n g s i g n i f i c a n t l y t o b a s i c ground
rqmearch and improved p r o c e s s i n g , end c o u l d even l e a d , e v e n t u a l l y , to t h e c o m e r c i a l p r o d u c t i o n o f high cost e~otic m a t e r i a l s in space. The APM, b a s e d structure. studied.
on t h e Spaceleb
Although e n v i s a g e d a s
module c o n f i g u r a t i o n c o n s i s t s
a 4-safgmmt module, 2 -
o f en a l l - w e l d e d
cylindrical
end 3-segment c o n f i g u r a t i o n s a r e
being
The Module ires a Space S t a t i o n c o m p a t i b l e docking p o r t i n each o f i t s two end cones; one
602
w i l l be u s e d f o r
docking t o t h e node
growth o r c o n t i n g e n c y docking.
interface, whilst the other
The AIM i s maunted
relains available for
along the flight path
n e a r t o t h e c e n t r e o f g r a v i t y , f o r t h e b e e t m i c r o g r a v i t y enviromme~t.
station
o f t h e Space
Station,
F i g u r e 1 shows t h e e x t o r m a l
end i n t e r n a l l a y o u t Of t h e APM w h i l e t h e main t e c h n i c a l d a t a a r e g i v e n in Table 1. Launched by t h e Space S h u t t l e , t h e APM w i l l be Shuttle Orbiter. operations.
EVA and t h e Remote
The p o s s i b i l i t y
s e r v i c e d e v e r y 90 days (or on demand) by
M a n i p u l a t o r System w i l l
be u s e d t o
support the
the
servicing
o f u s i n g Hermes and a l o g i s t i c s v e r s i o n o f A r l e n e f o r s u p p o r t o f
the
APM i s b e i n g s t u d i e d .
2.2
Man-Tended F r e e - F l y e r (MTFF)
The MTFF i s ccmq~oeed o f t h e f o l l o w i n g two e l e m e n t s : -
A 2-segMent P r e n s u r i s e d Module f o r accommodating p a y l o a d s . A d e d i c a t e d u n p r e s s u r i s e d Resource Module which p r o v i d e s a l l o f t h e u t i l i t i e s
and
s e r v i c e s r e q u i r e d by t h e MTFF end its p a y l o a d s . The P r e s s u r i s e d Module i s o f A t t a c h e d P r e s s u r i s e d Module. t h e Resource Module ~ t e d
the sale general construction
layout as
the
I t h a s a Space S t a t i o n c o m p a t i b l e docking p o r t i n one end cone w h i l e
is attached at
t h e o t h e r end
u n d e r t h e f l o o r end i n s t a n d a r d
under-floor subsystegm
end a r c h i t e c t u r a l
equipment
and t h e
cone.
The P r e s s u r i s e d
Module s u b s y s t e m s
s i n g l e or doable s i d e - w o u n t e d equipment r a c k s . standard
s i n g l e and
doable
equipment r a c k s
can
are All be
exchanged o n - o r b i t . The Resource Nodule commmications ment(s).
i s an u n p r e s s u r i s e d All
box c o n s t r u c t i o n w i t h
other subsystems,
s t a n d a r d ORUs ( O r b i t a l R e p l a c e a b l e
including the
Unit) s l o t t e d i n t o t h e
deployable s o l a r arrays
propulsion units,
primL~ structure.
a r e mounted
It is
end in
perms~mntly
a t t a c h e d t o t h e P r e s s u r i s e d Nodule by an i n t e r f a c e a d a p t o r , and i s not s e p a r a b l e o n - o r b i t . Power, c m m u n i c a t i o n s , p r o p u l s i o n , g u i d a n c e , n a v i g a t i o n r e q u i r e d by t h e
NTFF i s
p r o v i d e d by
t h e Resource Module,
and c o n t r o l and e l l t h e r m a l t h e Data
d i s t r i b u t e d between t h e Resource Nodule and t h e P r e s s u r i s e d Module.
control
Management s u b s y s t e m b e i n g The Resource Hodule
provides
t h e RIP up/down d a t a end communications l i n k s r e q u i r e d by t h e NTFF v i a TDRSS (Ku-band and
S-band),
Buropean Data Relay System, EDRS, (Ka-bend Global P o s i t i o n i n g System, GPS, (L-band).
and S-band), S-band ( L o c a l - and D i r e c t - t o - G r o u n d ) The
p r o p u l s i o n s u b s y s t e m p r o v i d e s s t o r a g e f o r 2400
end kg
o f b i p r o p e l l e n t and 80 kg o f N2 and u s e s two 400 N and s e v e r a l lO N e n g i n e s t o a c h i e v e t h e o r b i t a l manoeuvres r e q u i r e d f o r t h e ~frFF m i s s i o n .
The p r o p e l l a n t s t o r a g e i s s u f f i c i e n t
for
approximately
two y e a r s o f nominal biTFF o p e r a t i o n s , a f t e r which r e p l e n i s l m e n t i s r e q u i r e d . The NTFF c o n f i g u r a t i o n
i s shown
in Figure
2 and t e c h n i c a l
i n f o r m a t i o n on
t h e concept
is
p r e s e n t e d i n Table 2. The l a u n c h o f t h e NTFF w i l l be a c c o m p l i s h e d e i t h e r a t t h e Space
S t a t i o n or by
Hermes.
u s i n g an Ariane V.
Both I r a and
crew.
503 AA 1 5 / ? - B
EVA w i l l be
S e r v i c i n g w i l l be
performed
required of the
servicing
2.3
Polar Platform
The P o l a r
Platform
ccuprises a
equipment, s o l a r a r r a y s and
Utilitias
Module s t r u c t u r e
p r o p u l s i o n u n i t s and
a l~load
for
mounting t h e
C a r r i e r beaus
major
subsystem
s t r u c t u r e on which
the
p a y l o a d s a r e mounted. The a n a l y s i s
of several
o p t i n i s e d t o make nmxiw-, years.
design
options resulted
use of the Shuttle
The t e c h n i c a l d a t a o f t h i s
in
a dedicated
platform
s e r v i c i n g c a p a b i l i t y end w i t h
c o n f i g u r a t i o n i s g i v e n i n Table
3.
confil~aration,
a design life of
30
The p l a t f o r m i s shown
in
F i g u r e 3. The P o l a r P l a t f o r m
has the c a p a b i l i t y
to access both
TDRSS (Ku-band and
S-band) end
EDRS
(Ka-band and S-band) f o r up/down d a t a and command l i n k s and a l s o s u p p o r t s l o c a l S-bend a s w e l l S-bend end
E-bend
direct-to-ground
links.
Ground t r a c k
and
payloads, are acquired
position,
via the
which
are
us
important
parameters for the
Earth Observation
Global P o s i t i o n i n g
System
(GPS) L-bend l i n k .
The p r o p u l s i o n s u b s y s t e m p r o v i d e s s t o r a g e f o r 5000 kg o f p r o p e l l m l t end u s e s 2
x 400 N and 16 x 10 N e n g i n e s to a c h i e v e t h e o r b i t a l manoeuvres r e q u i r e d f o r t h e PPF m i s s i o n . The P o l a r P l a t f o r m w i l l be l a u n c h e d by a vehicle). servicing. launches.
Since
the payload
c a p a b i l i t y of
d e d i c a t e d Ariene V ( T i t a n IV i s t h e back-up Hermes
is limited,
the Orbiter
w i l l be
used
However, t h i s does depend on t h e Western T e s t Range b e i n g a v a i l a b l e f o r Space The s e r v i c i n g c y c l e w i l l
dock w i t h t h e
Shuttle.
be i n i t i a t e d by t h e
The r e n d e z - v o u s
altitude is
launch for
Shuttle
platform d e - o r b i t i n g to rendez-vous
276 k s .
The
servicing operation
and
foresees
p l a t f o r m s u b s y s t e m e n d / o r p a y l o a d ORU exchange by t h e u s e o f t h e remote l a n i p u l a t o r s y s t e m s o f t h e servicing vehicle. servicing tasks
The a v a i l a b l e upload c a p a b i l i t y o f t h e S h u t t l e allows a l l c u r r e n t l y i d e n t i f i e d
to
be
accomplished,
including
propellant
replenishment
by
propulsion
unit
exchange. On completion o f t h e
servicing activities,
back up t o i t s o p e r a t i o n a l s t a t i o n ,
2.4
the platform
usdocks fro,, S h u t t l e e~d
transfers
r e - e s t a b l i s h i n g i t s o r i g i n a l t r a c k end p o s i t i o n .
Enhanced Eureca
Based on t h e e x p e r i e n c e g a i n e d
from d e s i g n i n g and o p e r a t i n g
well placed for applying the c o - o r b i t i n g platform. polar platforl, previously Jentioned.
kg and a c o n t i n u o u s
launched and r e t r i e v e d by t h e
This c l a s s of f r e e - f l y e r
particularly
is smaller than
The p r e s e n t Eureca (a f u l l - s c a l e module i s shown in Fig.
i s devoted mainly t o m i c r o g r a v i t y e x p e r i m e n t s and i s payload c a p a b i l i t y o f 1000
Eureca, Europa w i l l be
power l e v e l t o t h e
It
s is the
Space S t a t i o n b u t i f a ground-based v e r s i o n i s used i t could be p u t i n t o any o r b i t d e s i r e d by
the
For t h e Space
Station scenario, the
The p l a t f o r m i s
e x p a r i m e ~ t s o f 1000W.
4)
e n v i s a g e d as f l y i n g a l o n g s i d e
users.
Space S h u t t l e .
2.35m in l e n g t h and 4.Sm in d i a m e t e r wi~h
the
c u r r e n t Eureca would be
improved - p a r t i c u l a r l y
bF
p r o v i d i n g a movable s o l a r a r r a y , improved d a t a h a n d l i n g and more a c c u r a t e p o i n t i n g .
T h i s enhanced
Eureca would a l s o s a t i s f y t h e r e q u i r e m e n t s f o r s p a c e and E a r t h viewing.
impression of
An a r t i s t ' s
t h i s v e h i c l e (Eureca-B) i s shown in F i g u r e 5 and i t s main t e c h n i c a l f e a t u r e s p r e s e n t e d in Table 4, t o g e t h e r w i t h t h o s e o f t h e e x i s t i n g v e r s i o n (Eureca-A).
604
The e x i s t i n g techniques, would b e
Eureca will be used for
Space Station
such as rendez-voua and docking end fluid extremely
ccipatibility
useful for
this
purpose.
technology support.
transfer
With
in orbit,
possible
Finally,
s p a c e - b a s e d E u r e c a b e i n g d e v e l o p e d / ' r a n t h e mere c o n v e n t i o n a l r e t r i e v a b l e
the user a foretaste
flight
o f t h i n g s t o come.
opportunities
until
t h e end
certain
must be mastered.
European autonc~
o f E u r e c a w i t h A r i a n e e n d Hermes i s a l s o b e i n g s t u d i e d .
E u r e c a - A a n d -E w i l l p r o v i d e
For lhnmpo,
in
~wecs
mind,
the
one c a n i m a g i n e
a
carrier.
o f t h e c e n t u r y and
permits
T h u s , E u r e c a may t r u l y b e r e g a r d e d a s a " s t e p p i n g
stone H
to the Space Station.
2.5
C o h e r e n c e o f European I n f r a s t r u c t u r e
R e c e n t l y , ESA hoe e s t a b l i s h e d involved,
i n a European
well suited
servicing
Space Station
for routine
maintenance (external
a Task F o r c e
maintenance
servicing)
to investigate
effort.
The r e s u l t s
indicate
(internal
servicing,
every
being performed at
f o r EVA and d o c k i n g p o r t e ,
of the various
that
with
vehicle
external
element
(called
is
exceptional
For t h e f u t u r e ,
b y a d d i n g an i n t e r - c o n n e c t i n g and a logistics
systems
t h e Hermes v e h i c l e
six months)
the Space Station.
u s i n g E u r o p e a n means o n l y c a n b e v i e u a l i s e d
w h i c h p r o v i d e s an a i r l o c k
the cohere~-e
(ICE)
LOW) w i t h
a
6 to 7 toane payload.
2.6
Complete Space S t a t i o n P l a n s
A representation and l i v i n g
of the total
quarters
Space S t a t i o n
provided
by the
i s g i v e n i n F i g u r e 6 w h i c h shows t h e c o r e l a b o r a t o r i e s
progrmme partners.
The p o s i t i o n
of the
APM i s
clearly
depicted. ESA's p l a n n e d c o n t r i b u t i o n a complete,
long term
data rate
transfer
Satellite
(DRS).
p l a n f o r Europe and
f o r Europe
test
of
an e s s e n t i a l
o u r ECS ( E u r o p e a n
the system,
Space S t a t i o n m u s t b e v i e w e d i n t h e l i g h t
possible,
The DRS s y s t e m m i g h t c o n s i s t
on e x p e r i e n c e g a i n e d w i t h first
to the international
u s i n g Olympus a n d
element
e v e n t u a l autonomy. o f an
an o n - b o a r d
e n s u r e a good
autoncnotm system is
of 2 or 3 satellites Cc~amication
To
the Data
and u s i n g
high Relay
in geosynchronous orbit
Satellite)
of
based
t h e Ka b a n d .
experiment, is planned
for the
A
first
Eureca flight. For t h e f u t u r e , mentioned
above
experience in
t h e u s e o f t h e MTFF, t o g e t h e r w i t h ICE, LOVE and t h e European s u p p o r t s y s t e m s
would
permit
manned
crew and
safety
fields
missions would
completely
permit permanent
under
European
occupancy.
control. It is
Further
against
this
b a c k g r o u n d t h a t t h e p r e s e n t Columbus programme m u s t b e v i e w e d .
3.
Ground I n f n u t r u c t u r e
The o p e r a t i o n o f t h e European I n - O r b i t b e s o l v e d , be i t f o r interface
with several
Infrastructure
carries
the complexity of the interrelations international
partners,
t h e demands
i n v e s t m e n t s r e q u i r e d on t h e g r o u n d . 605
a new d i m e n s i o n i n t h e p r o b l e m s
to
between various elements, the need
to
on human r e n o u r c e e o r t h e s i z e o f
the
The l u t
two a s p e c t s , i n
implementation of the
particular,
Buropean ground
have r e s u l t e d i n
infrastructure,
the consideration of a
drawing from
facilities
decentralised
and
capabilities
from Member S t a t e s wherever t h e y e x i s t or a r e p l a n n e d . The Columbns ground
seE•eat has,
therefore, a
decentralised configuration,
y e t under
the
o v e r a l l c o n t r o l o f a c e n t r a l p l a n n i n g and m o n i t o r i n g a u t h o r i t y . In a d d i t i o n
to the
ground f a c i l i t i e s
r e s u l t i n g from
t h e development
programme, t h e
main
elemm~ts o f t h e ground segment a r e : •
t h e C e n t r a l M i s s i o n C o n t r o l C e n t r e (CMCC),
•
the ~
•
t h e MTFF C o n t r o l C e n t r e ,
•
t h e PPF C o n t r o l C e n t r e ,
•
Amtronauts' t r a i n i n g and s i m u l a t i o n f a c i l i t i e s .
Control Centre,
Theme c e n t r e • w i l l be t y p i c a l l y equipped with: •
The
Telecommunications
tel~ication•
Interface
networks, i n c l u d i n g
Subsystem
DRS, which w i l l
and video l i n k • between t h e e l e m e n t s end ground. •
The M i s s i o n
Control
which
and Support
provides
the
interface
with
c a r r y t e l e m e t r y , telecommand,
voice
T h i s may i n c l u d e a l o c a l DP~ u s e r t e r m i n a l .
Subsystem which
provides all
r e a l t i m o and n o n - r e a l t i m e f u n c t i o n s , i n c l u d i n g , in p a r t i c u l a r ,
data
processing
t h e t e l e m e t r y and
for
telecommand
p r o c e s s i n g and t h e element f l i g h t dynamics s u p p o r t . s
The S i m u l a t i o n end
T r a i n i n g Subsystem w i t h
s u p p o r t p r e - m i s s i o n ground s t a f f and crew
l o c a l hardware end
software simulators
to
t r a i n i n g , f l i g h t procedures v a l i d a t i o n as well
as
i n - o r b i t f a u l t a n a l y s i s and c o n t i n g e n c y r e - p l a n n i n g s u p p o r t . a
The i n t e g r a t e d Software Support Subsystem which s u p p o r t s s o f t w a r e development,
and m a i n t e n a n c e
for both
on-ground and
on-board
s o f t w a r e and
ensure• the
testing
integrity
and
coherence of a l l software elements. •
The C o o r d i n a t i o n
ground f a c i l i t i e s
and P l a n n i n g
Subsystem which i s
responsible for
mission
planning,
ones ( • i n g l e s y s t e m
trainers:
c o o r d i n a t i o n and t h e c o n t r o l room.
Regarding t h e A B t r o n a u t s ' t r a i n i n g Crew Work S t a t i o n , ECLS, p a y l o a d CNOC, e t c . ) w i l l be l o c a t e d w i t h i n
facilities,
t h e most u s e d
i n t e r f a c e ; Low-Fi mockup; l i n k s to an ESA A s t r o n a u t Crew C e n t r e ,
Space S t a t i o n to APM CC and
t o be r e a l i s e d d u r i n g t h e
last
p a r t o f Phase C/D. The o t h e r t r a i n i n g f a c i l i t i e s , t h e o r i g i n o f e x p e r t i s e " , can
f o l l o w i n g t h e g u i d e l i n e f o r d e c e n t r a l i s a t i o n end f o r " g o i n g t o
be d e c e n t r a l i s e d (such as EVA immersion f a c i l i t y )
i n d u s t r y ( e n g i n e e r i n g models) or u s e r s i t e s
4.
or found
within
(experiments).
Col~bns ~ t i e m
An o v e r a l l progreume s c h e d u l e i s g i v e n i n F i g u r e 7.
Eureca w i l l be f i r s t
enhanced v e r s i o n c o u l d be a v a i l a b l e f o r f l i g h t in 1993.
launched in 1991 end t h e
Elements o f t h e Space S t a t i o n proper w i l l
be developed i n t h e e a r l y - 1 9 9 0 • and become o p e r a t i o n a l towards t h e end o f t h e decade. 606
5.
O~watlonal Aspects
T h i s s u b j e c t i s a d d r e s s e d i n d e t a i l e l s e w h e r e i n t h i s p u b l i c a t i o n ( s e e Trades and Problems i n Definition of Col~us
operations
Concepts - Page 697).
All t h a t needs t o
the
be s a i d h e r e i s
that
t h i s t o p i c i n b e i n g i n t e n s i v e l y s t u d i e d and t h a t European c o n t r o l o v e r European f l i g h t e l e m e n t s i s delirnble.
Initial
operations
preparation will
cover m i s s i o n
control, sustaining
engineering,
o p e r a t i o n s p l a n s end p r o c e d u r e s ( i n c l u d i n g r o b o t i c s ) and t h e t r a i n i n g o f f l i g h t and ground crews.
6.
1~
Use o f C o l m b u s BlemeRts
6.1
Potential uses
F i g u r e 8 p r e s e n t s s c a e g e n e r a l e x p e r i m e n t u s e s o f t h e Space S t a t i o n , many o f which u s e t h e characteristics
p r o v i d e d by t h e Space S t a t i o n e l e m e n t s .
perform e x p e r i m e n t s i n a u n i q u e
In
unique
summary, we w i l l be in a p o s i t i o n
s p a c e e ~ v i r o m m n t and we w i l l
fully exploit these conditions
f u r t h e r o u r knowledge o f b a s i c s c i e n c e and a p p l i c a t i o n s and, where p o s s i b l e , b u i l d on t h e pined
to to
insight
t o improve i n d u s t r i a l p r o c e s s e s and g e n e r a l l y u s e s p a c e f o r t h e b e n e f i t o f a l l .
During t h e p r e p a r a t o r y p h a s e s o f Columbus, i n t e n s i v e e f f o r t s have been made t o i d e n t i f y u s e r s end s a t i s f y t h e i r n e e d s in t h e d e s i g n . As e a r l y an 1982, a s t u d y was p l a c e d w i t h DFVLR a s prime c o n t r a c t o r on "European A s p e c t s " (EU&),
which i d e n t i f i e d
end d e f i n e d
European model
These were r e f i n e d i n two f o l l o w - o n c o n t r a c t s and
p a y l o a d s and
Utilisation
reference
missions.
r e s u l t e d i n t h e i n p u t s a s used i n t h e
Columbus
Phene-B P r o g r m m e . S e v e r a l i n p u t s from t h e ESA u s e r - D i r e c t o r a t e s , t h e ~
(Columbus U t i l i s a t i o n P r o j e c t
Group)
l o c a t e d a t DFVLR i n Cologne, n a t i o n a l workshops h e l d in Germany, t h e Anglo-French working group on the use of
t h e ESA end NASA p o l a r
Payload Working Group (COPA) and
platforms, the
n a t i o n a l UK u t i l i s a t i o n
others identified the following
study, the
Coltubun
main d i s c i p l i n e s f o r u s i n g
the
Space S t a t i o n e l m m m t a : @
Major u s e r o f
the prassurised
modules (AIM and
which i n c l u d e s L i f e S c i e n c e , F l u i d S c i e n c e
NTFF) i s
the Microgravity
end M a t e r i a l S c i e n c e .
discipline
t4icrogravity missions
are
also planned for ka-eca. @
Space S c i e n c e
particular structure
interest
has a in
major i n t e r e s t using
in co-orbiting
instruments
platform
externally attached
to
and
has also
parts
of
expressed
the
Station
(attached payloads).
s
The m a j o r i n t e r e s t
of the Earth Observation ccmaunity i s in the polar platform.
@
I d e n t i f i e d Space Technology
dmaonstration candidates are
nmstly located externally
to
the laboratories. •
Space C c s m u n i c s t i o n h a s
expressed interest
i n same
accommodation s p a c e
on t h e
polar
platform. •
The p o t e n t i a l
of the
Space S t a t i o n
system for
comercial users
M i c r o g r a v i t y , E a r t h O b s e r v a t i o n o r Space C o m u n i c s t i o n s .
607
is vast,
be i t
for
6.2
The Columbus U t i l i e a t i o n
To e n s u r e t h a t t h e
Preparation P r o ~
userm a r e readF end
Columbus U t i l i s a t i o a
Pre~ration
Space S t a t i o n u s e r s .
trained in the
Progress
Experimenters,
sounding rockets,
opportunities.
it is
mimsions.
aircraft
flights,
also intended to
on
etc.
basis,
end even
a all
p e r s o n n e l mast l e a r n
how
systems
create
new
d a t a , b u t a l s o t o t e s t new
techniques.
a non-intrusive
make f u l l u s e
to cover
we p l a n t o u s e a l l a v a i l a b l e
S p a c e l a b s , Eureca,
novel o p e r a t i o n a l
participate,
In
in
the execution
" f r o z e n " end
of available tent-beds
of
the
"non-frozen"
end p r o v i d e
experiment
( e q u i v a l e n t t o a b o u t two S p e c e l a b s ) t o s i - , u l a t e Space S t a t i o n e x p e r i m e n t c o n d i t i o n s .
Two c o n d i t i o n s m m t be f u l f i l l e d -
To do t h i s ,
we a r e p r o p o s i n g
w i l l be egtended
a s t r e n a u t m , end ground o p e r a t i o n s
equipment end
hoped t o
It is
opportunities
we hope
These s y s t e n s w i l l be u s e d , n o t o n l y t o g i v e s c i e n t i f i c
wethodologies, suitable p r o ~
Og
u s e o f Space S t a t i o n
(CUPP) which
b e s t t o o p e r a t e t h e new and e g p e n s i v e h a r d w a r e . such as
(CUPP)
d u r i n g t h e Space S t a t i o n o p e r a t i o n a l e r a :
A " u s e r " e x p e c t ; t o be r e a d y i n t h e mid-1990e, t h e u s e r s mast have a s many o p p o r t u n i t i e s
as p o s s i b l e to c arry
out experiments before
this date.
This
i s the only
way t o keep
the
p r e s e n t u s e r s end t o o b t a i n new o n e s . -
A "utilisation"
which r a i s e s
aspect;
the problesm
operatioms ...
this of
includes
the definition
payload c o m ~ a t i b i l i t i e s
of
a mission
( f o r launch,
element-by-element
integration,
in-orbit
i n t e r m s o f mass, power, d a t a r a t e EMC, e t c . )
I t i s o u r i n t e n t i o n t o d e v e l o p t h e s e two a s p e c t s o f Space S t a t i o n u s e s o t h a t , when t h e c~s,
b o t h e x p e r i m e n t e r and t h e
advantage o f the c a p a b i l i t i e s
s u p p o r t i n g o r g a n i s a t i o n e end f a c i l i t i e s
are ready to take
full
available.
I f t h i s approach to the preparation for the
u s e o f Space S t a t i o n i s a c c e p t a b l e ,
t h a t t h e c o n c e p t o f CUPP w i l l be e n l a r g e d t o s a t i s f y w i l l be p r e p a r e d t o u s e a l l e l e ~ m t s
7.
time
international
users.
it is
hoped
I n t h i s way, a l l
users
o f t h e Space S t a t i o n .
CGmcludtng m l s r k s
Europe's space a s p i r a tions p r e s e n c e o f man in s p a c e . It includes
include the
structures.
in
the international
ESA h a s
the
meeningYully t o t h i s n e x t s t e p i n t o Space is essential
that
experimentation.
our Both
up o f an
infrastructure
The Colmabus p r o g r m m e r e p r e s e n t s t h e
the participation
non-premsurised
setting
experimenters are these
aspects
Space S t a t i o n
management
exploration. fully
of the
608
end
and
technical
permanent
s t e p s towards t h i s the use skills
of to
goal.
us-manned, contribute
In a d d i t i o n to p r o v i d i n g the hardware
prepared
Columbus
preparatory studies.
first
to support the
to
use this
progrsmme
new
have been
concept addressed
in
it
space in
our
Figure I .
External and Internal Features of the Attached Pressurised Module
4 - S ~ t ~ ' f PIHSSUIUSD HOOULI 0verB11 dlmeasion8
12.6 • ) e o l t h . 4.0 • d i l l l t l r
I+unch m s
13,O00-18,O00 k2 (~memdind ~ n T S
Operlt tonal m s
+
P r / l oad m s
0-3000 k l l t ~ . . b , olX.ltiOeS1
F~ylold voltam
22 c u . i . 1] ~ ItorllO
Power
20 IN t o t a l , 120 V.nC.
Dlta
100 Mbpl d o . l i n k 25 Nb~l uplink
Operatiol~ll o r b i t
4SO"im clrcul~, ~
perf--) to 25,000 k l
up to 10,000 k l
(40 s~J~lle r l r . ~ l ) p i l l / up to f o r 2ener~l Spice S t l t i o o 10 IN Ivermlrl to Imyloed,
i~:li.~io~
(pemmxmtly a t t l c l x l d to Space Station )eSil~ l i f e
30 ]Pearl, v i a M i a ~ e e ~ c e a~d s e r v t e S n |
Leum~b v e b l c l e
liSTS
Table ]. Attached Pressurlsed Moule Main Technical Data
609
Figure
2.
The Man-Tended Free-Flyer Docked to Hermits
14M~T~I[D l q ~ - r ' L Y l l q CthIISTI'NG OF .4 2S3Gqb'Y IqWSSt~IS]~ MODULZ AND A MODOI.I
~era/l dimmsions undeployed
11.4 • length, 4.0 • d i d e r o t
~veral 1 d/mensions deployed
11.4 • x 55.? • x 21.8 •
haunch m s
18,500 kg
~perat lone] m S
up to 21,500 k4
Payload m s
2000 kg launch, up t o 5000 k g o p e r a t i o n a l
Payload volume
10.5 cU.m (20 o i n l l e ;~¢lw)
Pc~er
9 kW t o t a l , 120V. DC.
5 kW averale to payload,
100 Nbt~ do~mlL~k 25 Nbpe u p l i n k ~perlt lone] o r b i t
b o o n e r a n g o r b i t centred oal Space Station o r b i t (450 I(I c i r c u l a r , 28" tDcllnation)
~esi~
30 y e a r s , v l s Imintenl®ce and r e f u r b l s l l e n t , s e r v i c i n l ' c y c l e 180 days
life
Launch v e h i c l e
Table
Ariane 5
2. Man-Tended Main Technical
Free-Flyer Data
610
-
YYn
~
JSq-l~YINg I ~ L ~ PLAYt~M
I It
O~ll •
dtummiom8
g . 4 • lem~th z 4 . 1 • x 4 . 2 •
undeelo,~t
Overall d i m ~ l o m dwlo'~d ames Operltt(aal ms
m.O • x 3?.0 • x 15.0 • 1 2 , 0 0 0 W8
ws
11,ooo
k f laumch, up to 3000 kit o p e r a t i ~
~load Power
10.~ W t o t a l , 3 kW s u n l i J h t / ~ . 3 W eelipee average to 1~71oad~ 120 V . ~ .
hte
Nbpe (TESS) end SO0 N~pe (DB) do~ltnk, 1 ~ upltnk
Operational o r b i t
MO ks c i r c u l a r . W i n c l / n a t i o n
Deslp l i f e
30 ~ i f JESTSservicing i s feasible, lm~er l i f e t i ~ I f NSTS s e r v l e l n g i s not f u s i b l e . ( I k . s t r l c t i ~ : reopening o f Western Test ~mge to S h u t t l e launches)
Launch Vehicle
Ar4.al~e 5
Table ). Polar P l a t f o r m Main T e c h n i c a l D a t a
ERN MAST (RELOCATED S-BkNI)/EPS ANTENNAE)
COMMONSINGLE ~DRIJMARRAY
I000K6 ADD-ON PAYLOADCARRIER
RECONFIBUREDS/~ (ARRAY IMPACT)
INCREASEDSIZE GNC ACTUATORS
2,500KG PAYLOAD CAPACITY CARRIER
ADD-ON PROPULSIONORU
Figure 3.
The Polar Platform Configuration
611
Figure 4. Full-Scale Model of EURECA-A
Figure 5. EURECA-B Flight Configuration
612
gtureCl-A
Pro/load n e u a t i n ~ volumf T o t a l 8yStlm Imas - Payload ms T o t a l e l e c t r i c a l power -..fmtlnm nevload mr Data I m n a a m n t - ~ d J t | r a t e t o ImylolJd - Data storolle f o r =eylolKI Data t r l n s m t s s i o u t o ground - VIa S - b e n d -- V | a K/A~band O r b i t end a t t i t u d e c o n t r o l - Pointing dtrectiaa - Detnttnl accuracy Operational orbit Mission durlticm Design life
. 8.,~ It~ . 4.200 k l 1,Q0O k f S IN 1 I~
lurecl-B 0 , 5 ms 4,200 kll 1.000 kl 5 0 , 0 t 9 I I~w
1,5 kblm 128 14)
45 kbpa t o be eDl&elad
258 kbps
256 kblm planned via |0~
t o sun -÷/- I dee circular, initial a l t i t u d e f~S k s . L~8• Incllzmtio1~ 6 Im e p e r s t i o ~ t l , 3 Im r e t r i e v e ] S liuiorm or 20 y e a r s
celestltl * / - I a r c otl~ clreular Inltlol a l t i t u d e 52S kn, ~ Lnelinst~ more t h i n cme year. ol=erat:lo~=] 5 ltlsaions or I0 veers
Table 4. Existing (A) and Enhanced Eurece ( B ) Main Characteristics and Payload Capabilities
.LJ
Figure 6.
Space Stat[on Ensemble
613
Figure 8.
Experiment Uses of the Space Station and Platforms
FiGure 7.
Possible Columbus Programme Development Scenario
614
F. E n ~ t r ~ ¢
STATUS
end G. a l t m ~
Directorate ot Sp~e Station e~l Plati'or~ ~ r ~ e e n S ~ c e Agency, P a r i s
Abatract Station.
The Coltmbus
progrP~me
The status of the
description
of
the
includes Europe's
contribution
present activities is described in
candidate
free-flyer, and polar platform.
hardware
elements
-
Also, an enhanced
considered as an Earth-based co-orbiter is
to the
international
Space
this paper.
It includes a
brief
attached
pressurised
module,
man-tended
version of the baseline Eureca which is
described.
Attendant programmatic data are
being
discussed
using Europe's long-term aim of eventual autonomy as a back-cloth. The role of the potential users of Space Station elements is stressed in the paper and
plans
for ensuring good use of the new capabilities available are presented.
I.
Introduction
E u r o p e ' s i n v o l v ~ e n t w i t h man-in-space s t a r t e d with Spacelab.
Its highly successful first
flight
in November 1983 r e p r e s e n t e d an important m i l e s t o n e in Europe's commitment to manned
spaceflight.
Through this programme, the European SpsceAgency
considerable
experience in manned space activities and in space project. systm
(ESA) and its Member States gained
the management and conduct of a large
international
It also produced a solid industrial structure for the development of manned
and generated a class of potential
users that embraced the old established
space
experimenters
(such an astronomy and space physics) and new ones such as those in the microgravity sciences. Following the invitation of President Reagan to the US in
creating an internatianal
america's "friends and allies" to join
space station, ESA
.~k~ber States in this
exciting venture.
Eased
respond positivelyand
to join the progremme as a
took over the
with
role of representing
on its Spacelab experience,
Europe was ready
its to
reliable and inventive partner.
Initial work carried out by ESA as part of its long term planning and in its Member States particularly Germany and Italy - led to early concepts for Space Station participation. armed with these results, the ESA Council met at 1984.
This meeting provided an
Ministers recognised
successes of
Agency's programmes should be enlarged.
* **
Ministerial level in Rome at the end of
opportunity to review past
the previous
Suitably
ESA and
In particular
and possible future activities. considered that
the scope
The
of all
the
the Ariane V heavy launcher programme
was
ProgrmDirector, Paris, France Head, Columbus Systems and Projects Department, Noordwijk, Holland
601
January
approved emd t h e u n d e r t a k i n g o f a Coltmbun Space S t a t i o n
was
endorsed.
~uropean f a c i l i t i e s
One
P r e p a r a t o r y Progresme towards p a r t i c i p a t i o n in t h e
important
objective stated
was
"...
to
prepare
US
autonomous
f o r t h e s u p p o r t o f m a n - i n - s p a c e , f o r t h e t r a n s p o r t o f equipment end crews
end
f o r making u s e o f low-Earth o r b i t s " . To meet progrsme.
the goals
expressed
at the
Europe.
The
results will
m e e t i n g p l a n n e d f o r l a t e r t h i s y e a r when
2.
SSA e n t e r e d phase
B of
the
Columbus
The aim was to e v a l u a t e l i k e l y c a n d i d a t e s and t o d e t e r m i n e t h e t e c h n o l o g y and
implications for
made.
Rone m e e t i n g ,
be
presented to
a further
funding
Minister~level
Council
a commitment t o s p e c i f i c hardware c o n t r i b u t i o n s will
be
T h i s paper p r e s e n t s t h e s t a t u s o f t h e Progresme a s o f J u l y 1987.
| l e m m t s of t h e Col~bum P r o g r s m e
The work c a r r i e d o u t areas.
These
iceaaries,
in phase B of
include
t h e Coltmbus P r e p a r a t o r y programme h a s covered many
utilisation
potential,
operations
supporting
technology
related
end
a s w e l l a s d e s i g n end c o s t e n a l y e e s o f t h e c a n d i d a t e e l e m e n t s themBelves.
mission
In p a r a l l e l ,
t h e importance o f r e l e v a n t r e l a t e d p r o g r m m e s s u c h a s Ariene V, Hermes and u s e r d i s c i p l i n e s t u d i e s was e v a l u a t e d
and n e g o t i a t i o n s
w i t h NASA end
fellow participants
initiated
and
a
continuing
d i a l o g u e n e t up. As a r e s u l t o f
these diverse studies,
three basic candidates
have been f i r m l y
identified,
viz. : a
A p r e s a u r i s e d l a b o r a t o r y module p e r m a n e n t l y a t t a c h e d t o t h e main Space S t a t i o n .
D
A man-tended f r e e - f l y e r c o n s i s t i n g o f a p r e s s u r i s e d module and a r e s o u r c e s module.
It
o p e r a t e s i n a f r e e - f l y i n g mode and i n p e r i o d i c a l l y s e r v i c e d . A p o l a r p l a t f o r m , which o p e r a t e s mmanned in p o l a r o r b i t end be s e r v i c e d p e r i o d i c a l l y by t h e S h u t t l e (depends on t h e r e - o p e n i n g o f t h e Western T e s t Range t o S h u t t l e l a u n c h e s ) . In a d d i t i o n , a s m a l l , g r o u n d - b a s e d p l a t f o r m b a s e d on Euroca t e c h n o l o g y i s b e i n g e v a l u a t e d
as
a possible co-orbiting platform. Theme v a r i o u s f l i g h t e l e m e n t s a r e d e s c r i b e d below.
2. I
A t t a c h e d P r e e s u r i a e d Module (AIM)
Nssmed m i s s i o n s a t t h e Space S t a t i o n c o r e a r e s u p p o r t e d by t h e A t t a c h e d P r e s s u r i s e d Module.
This
I s b u r a t o r y module o f f e r s r e s e a r c h o p p o r t u n i t i e s
t h e p r e s e n c e o f man
over
O b s e r v a t i o n beve i n t e r e s t i n
this
l o n g p e r i o d s o f time.
Although
S c i e n c e , Technology end E a r t h
a l e a m a t , t h e u s e o f t h e AIM i s p r i m a r i l y mad L i f e S c i e n c e s .
in a l l a r e a s r e q u i r i n g
These a c t i v i t i e s
in t h e d i s c i p l i n e s o f F l u i d S c i e n c e s , M a t e r i a l
Sciences
span a wide r a n g e , c o n t r i b u t i n g s i g n i f i c a n t l y t o b a s i c ground
rqmearch and improved p r o c e s s i n g , end c o u l d even l e a d , e v e n t u a l l y , to t h e c o m e r c i a l p r o d u c t i o n o f high cost e~otic m a t e r i a l s in space. The APM, b a s e d structure. studied.
on t h e Spaceleb
Although e n v i s a g e d a s
module c o n f i g u r a t i o n c o n s i s t s
a 4-safgmmt module, 2 -
o f en a l l - w e l d e d
cylindrical
end 3-segment c o n f i g u r a t i o n s a r e
being
The Module ires a Space S t a t i o n c o m p a t i b l e docking p o r t i n each o f i t s two end cones; one
602
w i l l be u s e d f o r
docking t o t h e node
growth o r c o n t i n g e n c y docking.
interface, whilst the other
The AIM i s maunted
relains available for
along the flight path
n e a r t o t h e c e n t r e o f g r a v i t y , f o r t h e b e e t m i c r o g r a v i t y enviromme~t.
station
o f t h e Space
Station,
F i g u r e 1 shows t h e e x t o r m a l
end i n t e r n a l l a y o u t Of t h e APM w h i l e t h e main t e c h n i c a l d a t a a r e g i v e n in Table 1. Launched by t h e Space S h u t t l e , t h e APM w i l l be Shuttle Orbiter. operations.
EVA and t h e Remote
The p o s s i b i l i t y
s e r v i c e d e v e r y 90 days (or on demand) by
M a n i p u l a t o r System w i l l
be u s e d t o
support the
the
servicing
o f u s i n g Hermes and a l o g i s t i c s v e r s i o n o f A r l e n e f o r s u p p o r t o f
the
APM i s b e i n g s t u d i e d .
2.2
Man-Tended F r e e - F l y e r (MTFF)
The MTFF i s ccmq~oeed o f t h e f o l l o w i n g two e l e m e n t s : -
A 2-segMent P r e n s u r i s e d Module f o r accommodating p a y l o a d s . A d e d i c a t e d u n p r e s s u r i s e d Resource Module which p r o v i d e s a l l o f t h e u t i l i t i e s
and
s e r v i c e s r e q u i r e d by t h e MTFF end its p a y l o a d s . The P r e s s u r i s e d Module i s o f A t t a c h e d P r e s s u r i s e d Module. t h e Resource Module ~ t e d
the sale general construction
layout as
the
I t h a s a Space S t a t i o n c o m p a t i b l e docking p o r t i n one end cone w h i l e
is attached at
t h e o t h e r end
u n d e r t h e f l o o r end i n s t a n d a r d
under-floor subsystegm
end a r c h i t e c t u r a l
equipment
and t h e
cone.
The P r e s s u r i s e d
Module s u b s y s t e m s
s i n g l e or doable s i d e - w o u n t e d equipment r a c k s . standard
s i n g l e and
doable
equipment r a c k s
can
are All be
exchanged o n - o r b i t . The Resource Nodule commmications ment(s).
i s an u n p r e s s u r i s e d All
box c o n s t r u c t i o n w i t h
other subsystems,
s t a n d a r d ORUs ( O r b i t a l R e p l a c e a b l e
including the
Unit) s l o t t e d i n t o t h e
deployable s o l a r arrays
propulsion units,
primL~ structure.
a r e mounted
It is
end in
perms~mntly
a t t a c h e d t o t h e P r e s s u r i s e d Nodule by an i n t e r f a c e a d a p t o r , and i s not s e p a r a b l e o n - o r b i t . Power, c m m u n i c a t i o n s , p r o p u l s i o n , g u i d a n c e , n a v i g a t i o n r e q u i r e d by t h e
NTFF i s
p r o v i d e d by
t h e Resource Module,
and c o n t r o l and e l l t h e r m a l t h e Data
d i s t r i b u t e d between t h e Resource Nodule and t h e P r e s s u r i s e d Module.
control
Management s u b s y s t e m b e i n g The Resource Hodule
provides
t h e RIP up/down d a t a end communications l i n k s r e q u i r e d by t h e NTFF v i a TDRSS (Ku-band and
S-band),
Buropean Data Relay System, EDRS, (Ka-bend Global P o s i t i o n i n g System, GPS, (L-band).
and S-band), S-band ( L o c a l - and D i r e c t - t o - G r o u n d ) The
p r o p u l s i o n s u b s y s t e m p r o v i d e s s t o r a g e f o r 2400
end kg
o f b i p r o p e l l e n t and 80 kg o f N2 and u s e s two 400 N and s e v e r a l lO N e n g i n e s t o a c h i e v e t h e o r b i t a l manoeuvres r e q u i r e d f o r t h e ~frFF m i s s i o n .
The p r o p e l l a n t s t o r a g e i s s u f f i c i e n t
for
approximately
two y e a r s o f nominal biTFF o p e r a t i o n s , a f t e r which r e p l e n i s l m e n t i s r e q u i r e d . The NTFF c o n f i g u r a t i o n
i s shown
in Figure
2 and t e c h n i c a l
i n f o r m a t i o n on
t h e concept
is
p r e s e n t e d i n Table 2. The l a u n c h o f t h e NTFF w i l l be a c c o m p l i s h e d e i t h e r a t t h e Space
S t a t i o n or by
Hermes.
u s i n g an Ariane V.
Both I r a and
crew.
503 AA 1 5 / ? - B
EVA w i l l be
S e r v i c i n g w i l l be
performed
required of the
servicing
2.3
Polar Platform
The P o l a r
Platform
ccuprises a
equipment, s o l a r a r r a y s and
Utilitias
Module s t r u c t u r e
p r o p u l s i o n u n i t s and
a l~load
for
mounting t h e
C a r r i e r beaus
major
subsystem
s t r u c t u r e on which
the
p a y l o a d s a r e mounted. The a n a l y s i s
of several
o p t i n i s e d t o make nmxiw-, years.
design
options resulted
use of the Shuttle
The t e c h n i c a l d a t a o f t h i s
in
a dedicated
platform
s e r v i c i n g c a p a b i l i t y end w i t h
c o n f i g u r a t i o n i s g i v e n i n Table
3.
confil~aration,
a design life of
30
The p l a t f o r m i s shown
in
F i g u r e 3. The P o l a r P l a t f o r m
has the c a p a b i l i t y
to access both
TDRSS (Ku-band and
S-band) end
EDRS
(Ka-band and S-band) f o r up/down d a t a and command l i n k s and a l s o s u p p o r t s l o c a l S-bend a s w e l l S-bend end
E-bend
direct-to-ground
links.
Ground t r a c k
and
payloads, are acquired
position,
via the
which
are
us
important
parameters for the
Earth Observation
Global P o s i t i o n i n g
System
(GPS) L-bend l i n k .
The p r o p u l s i o n s u b s y s t e m p r o v i d e s s t o r a g e f o r 5000 kg o f p r o p e l l m l t end u s e s 2
x 400 N and 16 x 10 N e n g i n e s to a c h i e v e t h e o r b i t a l manoeuvres r e q u i r e d f o r t h e PPF m i s s i o n . The P o l a r P l a t f o r m w i l l be l a u n c h e d by a vehicle). servicing. launches.
Since
the payload
c a p a b i l i t y of
d e d i c a t e d Ariene V ( T i t a n IV i s t h e back-up Hermes
is limited,
the Orbiter
w i l l be
used
However, t h i s does depend on t h e Western T e s t Range b e i n g a v a i l a b l e f o r Space The s e r v i c i n g c y c l e w i l l
dock w i t h t h e
Shuttle.
be i n i t i a t e d by t h e
The r e n d e z - v o u s
altitude is
launch for
Shuttle
platform d e - o r b i t i n g to rendez-vous
276 k s .
The
servicing operation
and
foresees
p l a t f o r m s u b s y s t e m e n d / o r p a y l o a d ORU exchange by t h e u s e o f t h e remote l a n i p u l a t o r s y s t e m s o f t h e servicing vehicle. servicing tasks
The a v a i l a b l e upload c a p a b i l i t y o f t h e S h u t t l e allows a l l c u r r e n t l y i d e n t i f i e d
to
be
accomplished,
including
propellant
replenishment
by
propulsion
unit
exchange. On completion o f t h e
servicing activities,
back up t o i t s o p e r a t i o n a l s t a t i o n ,
2.4
the platform
usdocks fro,, S h u t t l e e~d
transfers
r e - e s t a b l i s h i n g i t s o r i g i n a l t r a c k end p o s i t i o n .
Enhanced Eureca
Based on t h e e x p e r i e n c e g a i n e d
from d e s i g n i n g and o p e r a t i n g
well placed for applying the c o - o r b i t i n g platform. polar platforl, previously Jentioned.
kg and a c o n t i n u o u s
launched and r e t r i e v e d by t h e
This c l a s s of f r e e - f l y e r
particularly
is smaller than
The p r e s e n t Eureca (a f u l l - s c a l e module i s shown in Fig.
i s devoted mainly t o m i c r o g r a v i t y e x p e r i m e n t s and i s payload c a p a b i l i t y o f 1000
Eureca, Europa w i l l be
power l e v e l t o t h e
It
s is the
Space S t a t i o n b u t i f a ground-based v e r s i o n i s used i t could be p u t i n t o any o r b i t d e s i r e d by
the
For t h e Space
Station scenario, the
The p l a t f o r m i s
e x p a r i m e ~ t s o f 1000W.
4)
e n v i s a g e d as f l y i n g a l o n g s i d e
users.
Space S h u t t l e .
2.35m in l e n g t h and 4.Sm in d i a m e t e r wi~h
the
c u r r e n t Eureca would be
improved - p a r t i c u l a r l y
bF
p r o v i d i n g a movable s o l a r a r r a y , improved d a t a h a n d l i n g and more a c c u r a t e p o i n t i n g .
T h i s enhanced
Eureca would a l s o s a t i s f y t h e r e q u i r e m e n t s f o r s p a c e and E a r t h viewing.
impression of
An a r t i s t ' s
t h i s v e h i c l e (Eureca-B) i s shown in F i g u r e 5 and i t s main t e c h n i c a l f e a t u r e s p r e s e n t e d in Table 4, t o g e t h e r w i t h t h o s e o f t h e e x i s t i n g v e r s i o n (Eureca-A).
604
The e x i s t i n g techniques, would b e
Eureca will be used for
Space Station
such as rendez-voua and docking end fluid extremely
ccipatibility
useful for
this
purpose.
technology support.
transfer
With
in orbit,
possible
Finally,
s p a c e - b a s e d E u r e c a b e i n g d e v e l o p e d / ' r a n t h e mere c o n v e n t i o n a l r e t r i e v a b l e
the user a foretaste
flight
o f t h i n g s t o come.
opportunities
until
t h e end
certain
must be mastered.
European autonc~
o f E u r e c a w i t h A r i a n e e n d Hermes i s a l s o b e i n g s t u d i e d .
E u r e c a - A a n d -E w i l l p r o v i d e
For lhnmpo,
in
~wecs
mind,
the
one c a n i m a g i n e
a
carrier.
o f t h e c e n t u r y and
permits
T h u s , E u r e c a may t r u l y b e r e g a r d e d a s a " s t e p p i n g
stone H
to the Space Station.
2.5
C o h e r e n c e o f European I n f r a s t r u c t u r e
R e c e n t l y , ESA hoe e s t a b l i s h e d involved,
i n a European
well suited
servicing
Space Station
for routine
maintenance (external
a Task F o r c e
maintenance
servicing)
to investigate
effort.
The r e s u l t s
indicate
(internal
servicing,
every
being performed at
f o r EVA and d o c k i n g p o r t e ,
of the various
that
with
vehicle
external
element
(called
is
exceptional
For t h e f u t u r e ,
b y a d d i n g an i n t e r - c o n n e c t i n g and a logistics
systems
t h e Hermes v e h i c l e
six months)
the Space Station.
u s i n g E u r o p e a n means o n l y c a n b e v i e u a l i s e d
w h i c h p r o v i d e s an a i r l o c k
the cohere~-e
(ICE)
LOW) w i t h
a
6 to 7 toane payload.
2.6
Complete Space S t a t i o n P l a n s
A representation and l i v i n g
of the total
quarters
Space S t a t i o n
provided
by the
i s g i v e n i n F i g u r e 6 w h i c h shows t h e c o r e l a b o r a t o r i e s
progrmme partners.
The p o s i t i o n
of the
APM i s
clearly
depicted. ESA's p l a n n e d c o n t r i b u t i o n a complete,
long term
data rate
transfer
Satellite
(DRS).
p l a n f o r Europe and
f o r Europe
test
of
an e s s e n t i a l
o u r ECS ( E u r o p e a n
the system,
Space S t a t i o n m u s t b e v i e w e d i n t h e l i g h t
possible,
The DRS s y s t e m m i g h t c o n s i s t
on e x p e r i e n c e g a i n e d w i t h first
to the international
u s i n g Olympus a n d
element
e v e n t u a l autonomy. o f an
an o n - b o a r d
e n s u r e a good
autoncnotm system is
of 2 or 3 satellites Cc~amication
To
the Data
and u s i n g
high Relay
in geosynchronous orbit
Satellite)
of
based
t h e Ka b a n d .
experiment, is planned
for the
A
first
Eureca flight. For t h e f u t u r e , mentioned
above
experience in
t h e u s e o f t h e MTFF, t o g e t h e r w i t h ICE, LOVE and t h e European s u p p o r t s y s t e m s
would
permit
manned
crew and
safety
fields
missions would
completely
permit permanent
under
European
occupancy.
control. It is
Further
against
this
b a c k g r o u n d t h a t t h e p r e s e n t Columbus programme m u s t b e v i e w e d .
3.
Ground I n f n u t r u c t u r e
The o p e r a t i o n o f t h e European I n - O r b i t b e s o l v e d , be i t f o r interface
with several
Infrastructure
carries
the complexity of the interrelations international
partners,
t h e demands
i n v e s t m e n t s r e q u i r e d on t h e g r o u n d . 605
a new d i m e n s i o n i n t h e p r o b l e m s
to
between various elements, the need
to
on human r e n o u r c e e o r t h e s i z e o f
the
The l u t
two a s p e c t s , i n
implementation of the
particular,
Buropean ground
have r e s u l t e d i n
infrastructure,
the consideration of a
drawing from
facilities
decentralised
and
capabilities
from Member S t a t e s wherever t h e y e x i s t or a r e p l a n n e d . The Columbns ground
seE•eat has,
therefore, a
decentralised configuration,
y e t under
the
o v e r a l l c o n t r o l o f a c e n t r a l p l a n n i n g and m o n i t o r i n g a u t h o r i t y . In a d d i t i o n
to the
ground f a c i l i t i e s
r e s u l t i n g from
t h e development
programme, t h e
main
elemm~ts o f t h e ground segment a r e : •
t h e C e n t r a l M i s s i o n C o n t r o l C e n t r e (CMCC),
•
the ~
•
t h e MTFF C o n t r o l C e n t r e ,
•
t h e PPF C o n t r o l C e n t r e ,
•
Amtronauts' t r a i n i n g and s i m u l a t i o n f a c i l i t i e s .
Control Centre,
Theme c e n t r e • w i l l be t y p i c a l l y equipped with: •
The
Telecommunications
tel~ication•
Interface
networks, i n c l u d i n g
Subsystem
DRS, which w i l l
and video l i n k • between t h e e l e m e n t s end ground. •
The M i s s i o n
Control
which
and Support
provides
the
interface
with
c a r r y t e l e m e t r y , telecommand,
voice
T h i s may i n c l u d e a l o c a l DP~ u s e r t e r m i n a l .
Subsystem which
provides all
r e a l t i m o and n o n - r e a l t i m e f u n c t i o n s , i n c l u d i n g , in p a r t i c u l a r ,
data
processing
t h e t e l e m e t r y and
for
telecommand
p r o c e s s i n g and t h e element f l i g h t dynamics s u p p o r t . s
The S i m u l a t i o n end
T r a i n i n g Subsystem w i t h
s u p p o r t p r e - m i s s i o n ground s t a f f and crew
l o c a l hardware end
software simulators
to
t r a i n i n g , f l i g h t procedures v a l i d a t i o n as well
as
i n - o r b i t f a u l t a n a l y s i s and c o n t i n g e n c y r e - p l a n n i n g s u p p o r t . a
The i n t e g r a t e d Software Support Subsystem which s u p p o r t s s o f t w a r e development,
and m a i n t e n a n c e
for both
on-ground and
on-board
s o f t w a r e and
ensure• the
testing
integrity
and
coherence of a l l software elements. •
The C o o r d i n a t i o n
ground f a c i l i t i e s
and P l a n n i n g
Subsystem which i s
responsible for
mission
planning,
ones ( • i n g l e s y s t e m
trainers:
c o o r d i n a t i o n and t h e c o n t r o l room.
Regarding t h e A B t r o n a u t s ' t r a i n i n g Crew Work S t a t i o n , ECLS, p a y l o a d CNOC, e t c . ) w i l l be l o c a t e d w i t h i n
facilities,
t h e most u s e d
i n t e r f a c e ; Low-Fi mockup; l i n k s to an ESA A s t r o n a u t Crew C e n t r e ,
Space S t a t i o n to APM CC and
t o be r e a l i s e d d u r i n g t h e
last
p a r t o f Phase C/D. The o t h e r t r a i n i n g f a c i l i t i e s , t h e o r i g i n o f e x p e r t i s e " , can
f o l l o w i n g t h e g u i d e l i n e f o r d e c e n t r a l i s a t i o n end f o r " g o i n g t o
be d e c e n t r a l i s e d (such as EVA immersion f a c i l i t y )
i n d u s t r y ( e n g i n e e r i n g models) or u s e r s i t e s
4.
or found
within
(experiments).
Col~bns ~ t i e m
An o v e r a l l progreume s c h e d u l e i s g i v e n i n F i g u r e 7.
Eureca w i l l be f i r s t
enhanced v e r s i o n c o u l d be a v a i l a b l e f o r f l i g h t in 1993.
launched in 1991 end t h e
Elements o f t h e Space S t a t i o n proper w i l l
be developed i n t h e e a r l y - 1 9 9 0 • and become o p e r a t i o n a l towards t h e end o f t h e decade. 606
5.
O~watlonal Aspects
T h i s s u b j e c t i s a d d r e s s e d i n d e t a i l e l s e w h e r e i n t h i s p u b l i c a t i o n ( s e e Trades and Problems i n Definition of Col~us
operations
Concepts - Page 697).
All t h a t needs t o
the
be s a i d h e r e i s
that
t h i s t o p i c i n b e i n g i n t e n s i v e l y s t u d i e d and t h a t European c o n t r o l o v e r European f l i g h t e l e m e n t s i s delirnble.
Initial
operations
preparation will
cover m i s s i o n
control, sustaining
engineering,
o p e r a t i o n s p l a n s end p r o c e d u r e s ( i n c l u d i n g r o b o t i c s ) and t h e t r a i n i n g o f f l i g h t and ground crews.
6.
1~
Use o f C o l m b u s BlemeRts
6.1
Potential uses
F i g u r e 8 p r e s e n t s s c a e g e n e r a l e x p e r i m e n t u s e s o f t h e Space S t a t i o n , many o f which u s e t h e characteristics
p r o v i d e d by t h e Space S t a t i o n e l e m e n t s .
perform e x p e r i m e n t s i n a u n i q u e
In
unique
summary, we w i l l be in a p o s i t i o n
s p a c e e ~ v i r o m m n t and we w i l l
fully exploit these conditions
f u r t h e r o u r knowledge o f b a s i c s c i e n c e and a p p l i c a t i o n s and, where p o s s i b l e , b u i l d on t h e pined
to to
insight
t o improve i n d u s t r i a l p r o c e s s e s and g e n e r a l l y u s e s p a c e f o r t h e b e n e f i t o f a l l .
During t h e p r e p a r a t o r y p h a s e s o f Columbus, i n t e n s i v e e f f o r t s have been made t o i d e n t i f y u s e r s end s a t i s f y t h e i r n e e d s in t h e d e s i g n . As e a r l y an 1982, a s t u d y was p l a c e d w i t h DFVLR a s prime c o n t r a c t o r on "European A s p e c t s " (EU&),
which i d e n t i f i e d
end d e f i n e d
European model
These were r e f i n e d i n two f o l l o w - o n c o n t r a c t s and
p a y l o a d s and
Utilisation
reference
missions.
r e s u l t e d i n t h e i n p u t s a s used i n t h e
Columbus
Phene-B P r o g r m m e . S e v e r a l i n p u t s from t h e ESA u s e r - D i r e c t o r a t e s , t h e ~
(Columbus U t i l i s a t i o n P r o j e c t
Group)
l o c a t e d a t DFVLR i n Cologne, n a t i o n a l workshops h e l d in Germany, t h e Anglo-French working group on the use of
t h e ESA end NASA p o l a r
Payload Working Group (COPA) and
platforms, the
n a t i o n a l UK u t i l i s a t i o n
others identified the following
study, the
Coltubun
main d i s c i p l i n e s f o r u s i n g
the
Space S t a t i o n e l m m m t a : @
Major u s e r o f
the prassurised
modules (AIM and
which i n c l u d e s L i f e S c i e n c e , F l u i d S c i e n c e
NTFF) i s
the Microgravity
end M a t e r i a l S c i e n c e .
discipline
t4icrogravity missions
are
also planned for ka-eca. @
Space S c i e n c e
particular structure
interest
has a in
major i n t e r e s t using
in co-orbiting
instruments
platform
externally attached
to
and
has also
parts
of
expressed
the
Station
(attached payloads).
s
The m a j o r i n t e r e s t
of the Earth Observation ccmaunity i s in the polar platform.
@
I d e n t i f i e d Space Technology
dmaonstration candidates are
nmstly located externally
to
the laboratories. •
Space C c s m u n i c s t i o n h a s
expressed interest
i n same
accommodation s p a c e
on t h e
polar
platform. •
The p o t e n t i a l
of the
Space S t a t i o n
system for
comercial users
M i c r o g r a v i t y , E a r t h O b s e r v a t i o n o r Space C o m u n i c s t i o n s .
607
is vast,
be i t
for
6.2
The Columbus U t i l i e a t i o n
To e n s u r e t h a t t h e
Preparation P r o ~
userm a r e readF end
Columbus U t i l i s a t i o a
Pre~ration
Space S t a t i o n u s e r s .
trained in the
Progress
Experimenters,
sounding rockets,
opportunities.
it is
mimsions.
aircraft
flights,
also intended to
on
etc.
basis,
end even
a all
p e r s o n n e l mast l e a r n
how
systems
create
new
d a t a , b u t a l s o t o t e s t new
techniques.
a non-intrusive
make f u l l u s e
to cover
we p l a n t o u s e a l l a v a i l a b l e
S p a c e l a b s , Eureca,
novel o p e r a t i o n a l
participate,
In
in
the execution
" f r o z e n " end
of available tent-beds
of
the
"non-frozen"
end p r o v i d e
experiment
( e q u i v a l e n t t o a b o u t two S p e c e l a b s ) t o s i - , u l a t e Space S t a t i o n e x p e r i m e n t c o n d i t i o n s .
Two c o n d i t i o n s m m t be f u l f i l l e d -
To do t h i s ,
we a r e p r o p o s i n g
w i l l be egtended
a s t r e n a u t m , end ground o p e r a t i o n s
equipment end
hoped t o
It is
opportunities
we hope
These s y s t e n s w i l l be u s e d , n o t o n l y t o g i v e s c i e n t i f i c
wethodologies, suitable p r o ~
Og
u s e o f Space S t a t i o n
(CUPP) which
b e s t t o o p e r a t e t h e new and e g p e n s i v e h a r d w a r e . such as
(CUPP)
d u r i n g t h e Space S t a t i o n o p e r a t i o n a l e r a :
A " u s e r " e x p e c t ; t o be r e a d y i n t h e mid-1990e, t h e u s e r s mast have a s many o p p o r t u n i t i e s
as p o s s i b l e to c arry
out experiments before
this date.
This
i s the only
way t o keep
the
p r e s e n t u s e r s end t o o b t a i n new o n e s . -
A "utilisation"
which r a i s e s
aspect;
the problesm
operatioms ...
this of
includes
the definition
payload c o m ~ a t i b i l i t i e s
of
a mission
( f o r launch,
element-by-element
integration,
in-orbit
i n t e r m s o f mass, power, d a t a r a t e EMC, e t c . )
I t i s o u r i n t e n t i o n t o d e v e l o p t h e s e two a s p e c t s o f Space S t a t i o n u s e s o t h a t , when t h e c~s,
b o t h e x p e r i m e n t e r and t h e
advantage o f the c a p a b i l i t i e s
s u p p o r t i n g o r g a n i s a t i o n e end f a c i l i t i e s
are ready to take
full
available.
I f t h i s approach to the preparation for the
u s e o f Space S t a t i o n i s a c c e p t a b l e ,
t h a t t h e c o n c e p t o f CUPP w i l l be e n l a r g e d t o s a t i s f y w i l l be p r e p a r e d t o u s e a l l e l e ~ m t s
7.
time
international
users.
it is
hoped
I n t h i s way, a l l
users
o f t h e Space S t a t i o n .
CGmcludtng m l s r k s
Europe's space a s p i r a tions p r e s e n c e o f man in s p a c e . It includes
include the
structures.
in
the international
ESA h a s
the
meeningYully t o t h i s n e x t s t e p i n t o Space is essential
that
experimentation.
our Both
up o f an
infrastructure
The Colmabus p r o g r m m e r e p r e s e n t s t h e
the participation
non-premsurised
setting
experimenters are these
aspects
Space S t a t i o n
management
exploration. fully
of the
608
end
and
technical
permanent
s t e p s towards t h i s the use skills
of to
goal.
us-manned, contribute
In a d d i t i o n to p r o v i d i n g the hardware
prepared
Columbus
preparatory studies.
first
to support the
to
use this
progrsmme
new
have been
concept addressed
in
it
space in
our
Figure I .
External and Internal Features of the Attached Pressurised Module
4 - S ~ t ~ ' f PIHSSUIUSD HOOULI 0verB11 dlmeasion8
12.6 • ) e o l t h . 4.0 • d i l l l t l r
I+unch m s
13,O00-18,O00 k2 (~memdind ~ n T S
Operlt tonal m s
+
P r / l oad m s
0-3000 k l l t ~ . . b , olX.ltiOeS1
F~ylold voltam
22 c u . i . 1] ~ ItorllO
Power
20 IN t o t a l , 120 V.nC.
Dlta
100 Mbpl d o . l i n k 25 Nb~l uplink
Operatiol~ll o r b i t
4SO"im clrcul~, ~
perf--) to 25,000 k l
up to 10,000 k l
(40 s~J~lle r l r . ~ l ) p i l l / up to f o r 2ener~l Spice S t l t i o o 10 IN Ivermlrl to Imyloed,
i~:li.~io~
(pemmxmtly a t t l c l x l d to Space Station )eSil~ l i f e
30 ]Pearl, v i a M i a ~ e e ~ c e a~d s e r v t e S n |
Leum~b v e b l c l e
liSTS
Table ]. Attached Pressurlsed Moule Main Technical Data
609
Figure
2.
The Man-Tended Free-Flyer Docked to Hermits
14M~T~I[D l q ~ - r ' L Y l l q CthIISTI'NG OF .4 2S3Gqb'Y IqWSSt~IS]~ MODULZ AND A MODOI.I
~era/l dimmsions undeployed
11.4 • length, 4.0 • d i d e r o t
~veral 1 d/mensions deployed
11.4 • x 55.? • x 21.8 •
haunch m s
18,500 kg
~perat lone] m S
up to 21,500 k4
Payload m s
2000 kg launch, up t o 5000 k g o p e r a t i o n a l
Payload volume
10.5 cU.m (20 o i n l l e ;~¢lw)
Pc~er
9 kW t o t a l , 120V. DC.
5 kW averale to payload,
100 Nbt~ do~mlL~k 25 Nbpe u p l i n k ~perlt lone] o r b i t
b o o n e r a n g o r b i t centred oal Space Station o r b i t (450 I(I c i r c u l a r , 28" tDcllnation)
~esi~
30 y e a r s , v l s Imintenl®ce and r e f u r b l s l l e n t , s e r v i c i n l ' c y c l e 180 days
life
Launch v e h i c l e
Table
Ariane 5
2. Man-Tended Main Technical
Free-Flyer Data
610
-
YYn
~
JSq-l~YINg I ~ L ~ PLAYt~M
I It
O~ll •
dtummiom8
g . 4 • lem~th z 4 . 1 • x 4 . 2 •
undeelo,~t
Overall d i m ~ l o m dwlo'~d ames Operltt(aal ms
m.O • x 3?.0 • x 15.0 • 1 2 , 0 0 0 W8
ws
11,ooo
k f laumch, up to 3000 kit o p e r a t i ~
~load Power
10.~ W t o t a l , 3 kW s u n l i J h t / ~ . 3 W eelipee average to 1~71oad~ 120 V . ~ .
hte
Nbpe (TESS) end SO0 N~pe (DB) do~ltnk, 1 ~ upltnk
Operational o r b i t
MO ks c i r c u l a r . W i n c l / n a t i o n
Deslp l i f e
30 ~ i f JESTSservicing i s feasible, lm~er l i f e t i ~ I f NSTS s e r v l e l n g i s not f u s i b l e . ( I k . s t r l c t i ~ : reopening o f Western Test ~mge to S h u t t l e launches)
Launch Vehicle
Ar4.al~e 5
Table ). Polar P l a t f o r m Main T e c h n i c a l D a t a
ERN MAST (RELOCATED S-BkNI)/EPS ANTENNAE)
COMMONSINGLE ~DRIJMARRAY
I000K6 ADD-ON PAYLOADCARRIER
RECONFIBUREDS/~ (ARRAY IMPACT)
INCREASEDSIZE GNC ACTUATORS
2,500KG PAYLOAD CAPACITY CARRIER
ADD-ON PROPULSIONORU
Figure 3.
The Polar Platform Configuration
611
Figure 4. Full-Scale Model of EURECA-A
Figure 5. EURECA-B Flight Configuration
612
gtureCl-A
Pro/load n e u a t i n ~ volumf T o t a l 8yStlm Imas - Payload ms T o t a l e l e c t r i c a l power -..fmtlnm nevload mr Data I m n a a m n t - ~ d J t | r a t e t o ImylolJd - Data storolle f o r =eylolKI Data t r l n s m t s s i o u t o ground - VIa S - b e n d -- V | a K/A~band O r b i t end a t t i t u d e c o n t r o l - Pointing dtrectiaa - Detnttnl accuracy Operational orbit Mission durlticm Design life
. 8.,~ It~ . 4.200 k l 1,Q0O k f S IN 1 I~
lurecl-B 0 , 5 ms 4,200 kll 1.000 kl 5 0 , 0 t 9 I I~w
1,5 kblm 128 14)
45 kbpa t o be eDl&elad
258 kbps
256 kblm planned via |0~
t o sun -÷/- I dee circular, initial a l t i t u d e f~S k s . L~8• Incllzmtio1~ 6 Im e p e r s t i o ~ t l , 3 Im r e t r i e v e ] S liuiorm or 20 y e a r s
celestltl * / - I a r c otl~ clreular Inltlol a l t i t u d e 52S kn, ~ Lnelinst~ more t h i n cme year. ol=erat:lo~=] 5 ltlsaions or I0 veers
Table 4. Existing (A) and Enhanced Eurece ( B ) Main Characteristics and Payload Capabilities
.LJ
Figure 6.
Space Stat[on Ensemble
613
Figure 8.
Experiment Uses of the Space Station and Platforms
FiGure 7.
Possible Columbus Programme Development Scenario
614