579
PRECEDING
PAGE
BLANK
NOT
CONCEPTUAL
DESIGN OF A LUNAR
THERMAL
CONTROL
SYSTEM
Lisa
F_LMED
BASE
N93-14
C. Simonsen
NASA Langley
Research
Hampton
VA 23665-5225
Center
Marc J. DeBarro
Rockwell
Internat/ona/
12214
Lakewood
Bk_L
Downey
CA 90241
Jeffery
T. Farmer
NASA Langley
Research
Hampton
VA 23665-5225
Center
Space station
and alternate
thermal
control
technologies
u_ere evaluated
for lunar
base applications.
The space station
technologies
consisted
of singlephase,
pumped
water
loops for sensible
and latent
heat removal
from
the cabin internal
environment
and tuophase
ammonia
loops for the train
and rejection
of these heat loads to the external
envimmment.
Alternate
technologies
were identified
for those areas where space station
technologies
proted
to be incompalffole
with the lunar environment.
Areas were also identified
where lunar resources
could enhance
the thermal
control
system.
The internal
acquisition
subsystem
essentially
remained
the same,
while moak'fications
uere needed for the transport
and
rejection
subsystems
because
of the extreme
temperature
variations
on the lunar
surface.
The
alternate
technologies
examined
to accommodate
the high daytime
temperatures
incorporated
lunar
surface
in,wMating
blanket_
heat pump
systen_
shack'ng
and
lunar
soil. Other
heat management
techrdques,
such as louvers,
were examined
to pret_ent
the radiators
from
free_'ng.
The impact
of the
geographic
location
of the lunar base and the orientation
of the radiators
mas also examined
A baseline
design was generated
that included
weight, pou_,
and volume
estimates.
INTRODUCTION
Absorptivity
Emissivity
Permanent
by
the
manned
National
initiatives
(Rk/e,
NASA
langley
Center
(JSC)
riate
on
the
.space
surface.
options
were
sections
of
temperature
in
the
lower
conceptual
design.
was
used
baseline
as the
for
The
the
NASA
control
elements
system.
station
in developing
the
_)lar
study
between
Johnson
extended
(TCS)
in
regions
were
thermal
control
the
Angle
T
Horizon
(Deg.)
was
Aluminum
Al
N
rad
design
active
Normal
Radiator
reg
sink
Environmental
l
surface
Inner
2
in
technology
design.
Height
Transfer Coefficient
Thermal Conductivity
P
r
Lunar
Regolith
Sink
Module
Surface
Wall
of MU
3
Inner
Surface
of Aluminum
Structure
4
Outer
Surface
of Aluminum
Structure
Lunar
5
Surface
APPROACH
(m)
(W/mZ-K)
(W/m-K)
Pressure
Q
q
Sun is Above
sub_ripts:
manned
lunar
control
H
Heat
(Deg.)
Efficiency
Latitude
(Deg.)
Stefan-Boltzmann
Constant
LIST OF SYMBOLS
h
k
Flux on the Radiator
lsentropic
(')
lunar
addressed
thermal
of the Solar
o
durations
of the
the
tff Incidence
approp-
of a conceptual
Both
passive
and
of
Angle
_
Space
the
control
the
settle
system
variations
latitudinal
new
operation
temperature
3'
bold
determining
for
identified
the
of
and
and
in
been
systems
efficient
extreme
Space
one
survive
thermal
the major
control
base.
the
to
for
considered
the
man
aid
has
explore
(LaRC)
to
The
element
This paper
di_usses
a lunar
base
thermal
of
to
as
a joint
Center
by
Moon
Space
station
conducted
required
as a key
on
the
Accordingly,
Research
was
lunar
identified
base.
the
1987).
systems
on
Commission
beyond
system
presence
facility
(ki_)
Flux (W/m
2)
Radius (m)
Temperature
configuration
(K)
of
requirements
environment
Heat (kW)
Heat
The
meet
on
were
thermal
technologies.
the
habitat
evaluated
control
A baseline
developed
the
lunar
established
to
base
by
and
JSC.
the
determine
habitat
The
was
designed
impact
proposed
design
of
to
the
activities
specifications
lunar
in
the
for
the
s3_tem.
configuration
using
The
the
for
current
acquisition
the
thermal
space
technology
control
station
for
system
thermal
the
internal
was
control
heat
580
2rid
Conference
loads
in the
loops
that
and
space
heat
pipe
to consist
If
(NASA,
space
application,
environment
was
the
thermal
lunar
tested
modified
were
technologies
for
generated
using
as
the
an
covered
transports
ammonia
was
of
heat
technology.
for
the
using
applicable.
for
lunar
The
the
lunar
possible
first
phases
as many
control
base
lunar
on
of
known
the
available
the
a
and
determine
base
an
the
habitat
operations.
initial
phase
and
will
days.
materials
be
growth
utilization.
This
The
phase
will
of
will
have
4
phase
to
addressed,
will
The
approximately
for
and
larger
habitat
and
Modules
4.5
m
cylindrical
in
The
nodes,
and
three
habitat
modules,
observatory.
facilities
from
were
airiocks.
were
station
in diameter
6.0
airlock
phase
a laboratory
The
m
by
An
initial
space
4.5
diameter
structures.
in diameter.
an
laboratory
entirely
airlocks.
were
lunar
with
m
long.
was
consisted
The
an
of
growth
module,
configurations
by
Both
two
with
crew
They
Apollo
from
changes
14
(Earth
the
day
7)
plots
from
McKay
resulting
effects
in the
of
lunar
sunlight
can
to
120
identified
four
(87.5°W,
(30°E,
were
of
generated
the
and
range
20°N),
days
lunar
an
darkness.
K during
night.
day
empirically
at
the
Figure
2
at different
was
flux
to night
of
374
equation
solar
day
approximately
lunar
using
varying
14
the
The
lasts
from
the
over
(1963).
from
day
K during
variations
These
the
dramatically
The
days
temperature
equation
In
be
there
have
The
derived
modified
different
to
latitudes
following
addition,
sphere
3.7
m
three
consisted
of
four
airlocks,
phases
are
base
= 373.9(cost_)
two
and
shown
of
features
from
may
be
low
excellent
approximately
The
regolith
a stable
night
features
the
severe
2_(sin0)
167
shadowed
could
be
insulator
could
used
with
W/m-K
immediately
thermal
environment
temperatures
0.004
surface
lunar
temperature
permanently
regolith
lunar
of
these
consistently
it is an
aluminum
gradient
that
enhance
the
and
thermal
design.
N-6
AL-2
N-I
AL-3
_3
_
Lunar base
m(rdule
configurations.
N-3
N-Z
that
1972
because
conductivity
Hohmann,
surface
a
poles
Lucas,
1972).
could
insensitive
The
(b)
N-4--
the
thermal
and
lunar
protect
For example,
protection
average
is relatively
variations.
a TCS
near
(Dalton
below
temperature
regions
(Stfmpson
as
an
could
variations.
(a)
1.
radiation
Veris
site
m
was
ENVIRONMENT
location.
Trmxm (K)
Nodes
module,
Fig.
cosmic
Lacus
landing
2
regolith
at JSC
were
17
under
lunar
10°S).
temperature
latitudes.
and
to
long,
were
a habitat
phase
the
m
the
buried
of
Division
( 10°W,
to
surface
noon
shows
a crew
nodes,
aluminum
six nodes,
for
13.3
days
lunar
scale
assumed
modules,
the
base.
environment
location
Earth
lunar
The
Pole,
Nubium
m
oxygen
of eight.
constructed
protect
first
directly
2
10
liquid
manned
or
Exploration
the
South
from
include
support
research.
facilities
permanently
used
to sustain
were
for
research,
be
was
required
initial
for
Mare
The
lunar
base
System
to
LUNAR
technologies
JSC
Solar
the
The
materials
a crew
closed-loop
phase
lunar
limited
by
from
facilities
the
phase.
and
operated
The
of
a growth
research,
received
laboratory
phases
exploration
facilities
Earth
and
Two
preliminary
analysis
1985).
sites
regolith
observatory.
structure
then
BASE DESCRIFFION
functional
sufficient
system
were
28
base
lunar
was used
to model
the
either
under
a supporting
Approximately
et al.,
the
and
A lunar
of
node
to be
and
selected.
LUNAR
as
13°S),
this
2 m
regolith.
estimated
assumed
Using
Thermal
of
by
lunar
(Duke
accommodate
systems
areas
sensible
inadequate
to
alternate
information
loop
in Fig. 1. A space
station
The base
was assumed
water
for
insulation.
established
habitable
21°C
control
proved
control
base
summaries
thetanal
multilayer
by
pumped
and
ammonia
Passive
either
Activities
of individual
technology
replaced
2°C
a series
1984).
Space
single-phase,
two-phase
of standard
or
permanent
of
and
of
to
station
it
approach,
A
modules
primarily
the
consists
removal.
the
radiators
Bases
at temperatures
heat
from
Lunar
station
operate
latent
the
on
utilization
to
provide
the
of
day/
these
).
Simonsen
et al.: A lunar
base
thermal
CONCEPTUAL
380 F
_
360F
340 [-
system
581
DESIGN
Equator
t"
/#"
_
The
Lacus Veris (13"5°)
_
"_,
ol-/y
Lacus
for
.07
the
lower
the
base
since
•
12
16
20
were
the
at
the
rejection
evaluated
to
The
the
acquire
TCS
used
at
all
become
Pole
site
will
Therefore,
were
South
the
for
internal
a
Pole
heat
loads
and
South
Pole
and
the
thermal
requirements
essentially
environments
for
be
variations
South
of
one
environment.
environment
locations
systems
could
the
benign
sites
because
Therefore,
regions
designed
sites.
these
Nubium
needed.
lunar
latitudinal
rejection
were
8
into
be
Mare
temperature
latitudes,
more
the
environments
equator.
surface
may
TCSs
them
the
higher
design
and
thermal
latitudinal
lunar
at
Conceptual
'°°V
"°k/
lower
a different,
TCS
landing,
from
the
pronounced
separate
Y=o
4
the
Since
experience
reject
17
identical
distances
sites.
less
\\
\AW
i7i/ /
similar
three
Apollo
essentially
designed
\\
/
Veris,
experience
their
300
l-I/I
120 _
0
control
identical.
are
unique
and
the
to
for
However,
location,
lower
the
latitudinal
sites
separately.
28
Time (Earlh Days)
Acquisition
Fig. 2.
Lunar
surface
temperature
profile
at different
Considerations
The
ambient
heat
The
TCS
maintain
the
24°C
and
for
and
to
To
must
must
be
The
acquired
heat
heat
based
(NASA,
at
designed
between
18°C
the
and
external
to
between
4°C
metabolic
heat
gains
and
to each
the
1984).
2°C
and
module,
specified
These
21°C.
(crew)
heat
gains
and
were
calculated
losses
for
requirements
system.
protected
and
regolith,
gains
on
(3)
and
losses
of
in Table
these
loads
(humidity)
and
there
module
kW
will
on
over
1.7 kW.
aluminum
of
a
as
cool
the
charged
for
modules
module
during
be
a heat
loss
surface
at
entire
day
These
added
loads
system.
The
lunar
both
latitudinal
gain
of
the
on
1.7 kW
be
details
during
Pole,
in
analysis
be
an
the
added
lunar
will
are
South
day,
night.
loss
the
of
(i.e.,
the
heat
excluding
active
no
node
TCS)
active
65kW
load
heat
and
TCS),
at 21°C
for
the
growth
loads
3
listed
(assumed
airlock
the
and
in Table
to
4 (used
maximum
30kW.
phase
be
be
at
design
is 135
2°C.
kW
load
Likewise,
at 21°C
for
base
and
accommodate
capacity
loads
was
system
heat
loads
was
not
kW
for
2.36
designed
(Table
2)
to
and
control
phase
relative
in operation
sensible
site,
heat
unit
loads
nodes
and
in
1 and
nodes
If
in
heat
to
humidity
exchangers
requirements.
the
and
1.
node
Selected
heat
loads
were
6 would
also
Heat Load
2°C
be
(kW/m(xlule)
2 I°C
M(xlule
lO
15
Module
10
4
4
15
10
10
4
10
of
2.
Metabolic
,sensible
and latent
with
the
initial
maximum
no
with
phase
at 2°C.
is
heat
heat
loads.
Load
Sensible
Latent
Swt_at and respiration
water
H)gienc
w-ater
F(x_l preparation
water
Experiment
water
Laundry water
0.086
kW/man
1,82
0,44
0.03
0.45
0.06
kg/man
kg/man
kg/man
kg/man
kg/man
be
located
areas.
Laboratory
Node
Airlock
TABLE
the
6 will
base
in the habitable
6
heat
5, while
in node
the
and
sensible
Habitation
the
to
were
5
a
modules,
observatory
66kW.
latent
to
this
in the
the
and
were
modules
a heat
of
module
to the
base
control
initial
Two
Observatory
For
night
explained
all the
a logistics
as access
heat
at
1 for
the
sized
these
humidity
the
Module
Metal_dic
the
base.
distributions
of emergency.
haven
latitudinal
space
latitudinal
the
there
addressed
of the
of
safe
the
lunar
The
at the
will
part
meet
in
and
remain
TABI£
2 m
2 m
surface
there
a maximum
will
lower
to
was
humidity
and
and
power
the
with
surface.
and
the
hottest
South
with
at the
used
and
phase.
will
and
of
for
1, although
Included
1 for
humidity
at a lower
active
Appendix.
Using
growth
used
the
those
therefore,
was
system
sensible
node
and
to
system.
temperature
to
modules
similar
(1)a
with
Nubium)
sites,
the
the
under
protected
directly
heat
the
on
Mare
if
structure
the
Fatimates
base
were
modules;
in Table
in case
lunar
configuration
acquisition
temperature
air
the
the
acquisition
metalx)lic
relative
and
of
equipment
The
the
volume,
required.
air
remove
listed
were
buried
modules
17, and
upon
considered
directly
directly
the
lower
imposed
Design
modules
station
specified
immediately
the
are
heat,
supporting
a module
for
the
acquisition
an
Apollo
at the
2.2
cases
a module
for
observatory)
be
three
System
technology
module's
loads
the
space
weight,
of the
heat
1 for
between
the modules
three
cases
to determine
would
(2)
negligible
Versis,
However,
of
top,
and
were
(Lacus
load
layout
Each
airlock
listed
in
The
under
regolith
regolith
because
exchangers
load
of
different
the
losses
requirements
are
Included
latent
node,
load
loads
and
control
module
the
the
and
2.
thermal
loss
was
temperature
equipment
and
assigned
upon
sensible
additional
Pole.
modules
point
the
removed,
loads
The
external
the environment
sites
dew
this,
base
the
However,
in
in
acquisition
each
station
in Table
heat
the
the
minimized.
metabolic
of
the
actively
acquired
2 m
inside
of
for
station's
REQUIREMENTS
areas
accomplish
selected
space
habitable
maintain
be
total
were
the
temperature
16°C.
loads
CONTROL
environment
loads
projected
THERMAL
and
latitudes.
day
day
day
day
day
used
582
2nd Conference
to provide
the
requirements
day. If the
exchangers
would
to provide
heat
to meet
to provide
heat
lunar
heat
during
heat
TABLE 3.
heating
losses
the
to the
steel
located
near
through
another
module
lengths
of external
Figs. 4a and
4b
in the initial
The
cooled
require-
arranged
in
(Fig. 3). The
by either
cold
pumped
transport
lines.
initial
to
transport
the heat
the
plates
the
line.
acquired
to the bus heat
and growth
are
conditions
available
main
and power
cooling
plates
2°C
growth
estimates
Application
Technology
data
modules
location
to reduce
layout
et al.,
from
in
respectively.
acquisition
are shown
the
for
contained
relative
separator,
and redundant
It also included
by LaRC and
1986;
systems
in Tables 4 and
humidity
and fan packages.
The
loops
packages,
redundant
liquid
valves, flex hoses, controllers,
estimates
for the
lines,
fittings,
Heat
Rejection
support
controllers,
control
and
system
3
4
3
4
2
4
l
4
2
3
2
4
2.0
4.0
2.0
4.0
2.0
2.5
1.6
2.5
2.0
5.0
2.0
2.5
Node(2,4)
Node(l,5,6)
Airlock(1,2,3)
loops
contained
redundant
redundant
transducers,
temperature
drop
The
pump
transport
environment,
average
of 100 W/m 2 at -6°C and 160 W/m 2 at 13°C.
The
thermal
the
radiators
environment
resulting
from direct
lunar surface.
These
capability
is more
of the radiators.
The rejection
phase
module
ammonia
heat
loads
bus heat
loops
on
the
space
at 2°C
and
station
via separate
21°C
are
transported
pumped
to aluminum
heat
twopipe
where
In some
capability
q is the radiator
is the effective
ature
IR flux from
were
heat
the
to reject
on the
instances
lunar
these
from the
rejection
effects
prevent
them
to gain heat
was estimated
effects
using
.......
surface.
The
assumed
0.80 and an absorptivity
Computer
in the heat
for various
considered.
ular
to
heat
the
sided
sink
temperature
presented
in Dal/as
and orientation
surface
sink temper-
solar
from
the
et al. (1971
of the
properties.
( 1 ) a vertical
solar
ecliptic,
of the ecliptic,
lunar
surface
in the
meter
radiator
had
heat
to the
shown
emissivity
a heat
flux
(Fig. 5). The
That
200W/m
flux
were
calculated,
the
radiator
If, however,
would
the
radiator
a horizontal
total
radiator
heat
the
rejection
amount
is, if a vertical
2, it would
radiator
a negative
gain heat.
perpendic-
vertical
represented
panel.
of
radiator
(2)a
and (3)
program
of radiator
environment.
rejectfon
rejection
at the
capability
wall temperatures
horizontal
radiators
is continuously
module.
of
These
of
two-
reject
had a heat
one side
If
would
heat
radiate
flux were
conventions
are
in Fig. 6.
Heat
heat
).
radiators,
The radiators
to" have an end-of-life
included
of the
calculated
square
calculated,
flux, and
calculations
of 0.30 (NASA, 1984).
They
plane
to the plane
per
The
space,
programs
were generated
to calculate
the _ariations
rejection
capability
of the radiators
over the lunar day
orientations
at different
latitudes.
Three
orientations
were
heat
for an integrated
the
in W/m e and Tsink
(K).
of cold
on the latitude
were
capability
temperature
on the methodology
depend
a positive
Typical cold plate configuration
surface,
flux
heat
100W/m
2 per side. Likewise,
if a horizontal
radiator
flux of 200 W/m 2, it would
reject 200 W/m e from
Fig. 3.
an
- T4sir_)
rejection
added
the lunar
based
capability
'\.\
I
oriented
and may cause
of the radiators
environmental
represents
insulated
Equipment Heat Excha_
2,5°0
be
severe
q = _o(T4rad
parallel
..........................
20
4-
the
equation
in this analysis
exchangers
can
solar flux and infrared
(IR)
factors
degrade
the average
the radiators
from emitting
heat
from the external environment.
following
0.0
3.0
O0
3.0
0.0
2.5
0.0
25
0.0
0.0
O0
2.5
between
station
They will
and sensors.
Considerations
acquired
the
assumed
4.0
4.0
4.0
4.0
0.0
2.5
0.0
2.5
0.0
2.5
0.0
2.5
plates and the heat pipe radiators,
resulting
in
temperatures
of -6°C and 13°C. In the space
the time of day, and the radiator's
from
was
4.0
4.0
4.0
4.0
2.0
2.5
0.0
2.5
2.0
2.5
2.0
2.5
intake
water
transport
loops,
disconnects,
transducers,
sensors, etc. The above
disconnects,
8°
at 2°C.
for the equipment
plates,
An
acquisition
cold
radiator
rejection
Load on Each (kW)
2
3
4
a water
operating
of ducting,
estimates
cold
of
(MSFC).
exchangers,
lines
composed
above
contained
1988)
Center
heat
transport
system
Hartley,
humidity
and sensible
water
Institute
Flight
and
using
Space
Georgia
and
Space
air temperature
a ventilation
acquisition
ColweU
Marshall
Estimates
heat
2
21
2
21
2
21
2
21
2
21
2
21
H_i_tion
radiators.
the
is shown
and power estimates
were computed
Thermal
Control
Model
for
developed
(Hall
obtained
filters,
1
ex-
in one
phases,
for the
heat
Some
exchanger
A typical
and
configurations
The weight, volume,
Emulation-Simulation
Station
Number of
Cold Plates
in each
bus
loads in each module.
Temp of
Loop (°C)
by cold
5, respectively.
the
Module
Equipment
Ob_rvato_
to pump
for the
volume,
equipment
and are
were
the
loops
accommodated
cold
operating
loads
support
were
The
isothermal
contain
Weight,
and
heating
for the
all normal
needs.
are stainless
module
changers
cooling
additional
loads
or 2 I°C pumped
water loop.
module are listed in Table 3.
The
added
Activities
and coldest
times of the
at the South
Pole, the
to compensate
customer
plates
the
and Space
Labomto_
and
parallel
with
module
designed
ments
Bases
hottest
located
need
day/night
remaining
plates
cold
observatory
during
the
base
were
entire
lunar
environment.
The
on Lunar
of a space
Pole.
the lunar
Figure 7 shows
day and night
of -6°C and 13°C. Figure7a
would provide
the base with
above
station
South
over
the
radiator
100 W/m 2 average
at -6°C.
The
indicates
a capability
rejection
other
radiator
for r_adiator
that
that
capability
orientations
fall
Simonsen
et al.: A lunar
base
thermal
control
system
583
(a)
Main Thermal
Bus
mm_mmmmmmlmmm_mmmn_l
I
..q
N-3
6
J
I
,,.,I,
r-N-]
N kW Heat Exchanger
4 ......................
4
2oC
21 °C
(b)
I
........
_............................
,_ J! %!iJ<L_
..............................
',J_
................
"k__3 k_
.....
|
!
?_--_ .... :....... _',,.,....,__
..................
..............
.........................................
_, '_
[-I _
.....
_"i' J
m_
mN
m_
/
N kW Heal Exchanger
Fig. 4.
(a)
Initial
phase
layout
of acquisition
_%ystem (b)
Growth
41 ....................
2oC
4
21 °C
phase
layout
of acquisition
,,,3_tcm.
584
2nd
Conference
on
Lunar
Bases
and
Space
Activities
TABLE 4.
Acquisition
summary:
Initial
phase.
Habitation
Item
Module-I
Weight (kg)
Air Temperature
and Humidity
Equipment
Heat Acquisition
Control
2oC
21°C
Support
Loop
Total
Volume
(2°C
and
21°C)
Control
2°C
21°C
Support Loop
Total
(2°C
Power ( kW )
Air Temperature
Equipment
and
Humidity
and
21°C)
Control
Heat Acquisition
2°C
21°C
Support Loop
Total
(2°C
and
21°C)
TABLE 5.
Acquisition
Weight
(kg)
Air Temperature
Equipment
Heat
and Humidity
Acquisition
Control
2 °C
21°C
(2°C
Support
Loop
Total
Volume ( m _)
Air Temperature
and Humidity
Equipment
Heat Acquisition
and Humidity
Acquisition
the
Figure
W/m
all orientations
constant
flux.
The
results
major
of
perature
the
capability
a
and
8a
and
at
8b,
lower
Air Lock-2
Air hock-3
143
68
200
57
104
191
57
1O0
195
57
1 O0
195
_,7
1(_0
195
81
975
73
484
146
498
0
352
0
352
352
1.73
0.21
0.22
0.71
0.07
O. 10
0.40
0.09
0.10
0.40
0.08
O. !0
0.40
0.08
O. 10
0.40
0.08
O. I0
0.04
2.20
0.03
0.91
0.07
0.66
0
0.58
0.58
0.58
0.49
1.04
O. 15
O. 15
0.15
O. ! 5
0.32
0.29
0.02
0.18
0.07
0.18
0.07
0.19
0.07
0.19
0.07
0.19
0.03
1.13
0.03
1.27
0.06
0.46
0
0.41
0.41
0
for
that
the
that
to the
at Lacus
As indicated
lOOW/m
by
temperature
2 level
Veils
the
loop
for
the
57
104
191
0
352
143
68
191
0
402
143
68
191
146
548
57
0
0
46
103
0.40
0.09
0.10
0.71
0.07
0.10
0.71
0.07
0.10
0.40
0
0
0.40
0.09
0.10
0.02
0.42
0
0.59
0.48
0.32
0.29
0.48
0.22
0.29
0.15
0
0
0.15
0.07
0.18
1.04
0.02
0.18
1.04
0.02
0.18
0.15
0
0
0.15
0.07
0.18
0.03
1. ! 3
0.03
1.13
0
O. 15
0
0.40
0
1.24
0.06
1.30
0.03
O. 18
0
0.40
IR
fact,
the
lunar
the
heat
day.
identified.
using
reflective
the
The
none
The
a
In
tbr
areas
lunar
capability
factor
long
storage
thermal
because
heat
is a function
of
the
and
radiator
was
to
lower
storage
durations
to
technology
(NASA,
affecting
of
to
the
the
lunar
surface,
a
and
capability
the
lunar
the
using
a
in
1985).
rejection
The
radiator's
temperature,
the
pump
the
a massive
extremely
radiator
by
IR flux
heat
however,
vertical
surface
disfunction.
elevate
result
the
lead
temperature
reduce
storage
may
require
of its low conductance.
flux
sink
considered;
would
of
can
rejection
temperature
was
portions
control
the
which
57
1 04
191
0
352
radiators
improve
was
sink
large
the
thermal
to
second
the
for
by
blankets,
The
Thermal
current
first
insulating
for
negative
experienced
temperatures
above
regolith
transfer
become
gain
enhancements
radiators.
loads
using
shown
day.
radiator
assembly.
tem-
heat
possible
temperature
without
provides
fluxes
The
were
on
rejection
entire
57
0
0
0
57
0.07
0.95
Two
figures,
Observatory
0
0.88
to elevated
are
Air
Ix)ck-4
0
0.59
for
wall
Node-6
0
0.40
heat
The
Node-5
0.04
2.20
could
a -6°C
Node-4
0.04
2.20
system.
sites.
with
Node-3
0
0
capability
Pole
phase.
0.40
station-type
South
0
0.41
1.73
0.21
0.22
for
orientation
0
1.73
0.21
0.22
comparatively
a space
of the
latitudinal
either
a
Laboratory
Module- 1
0
149
355
390
81
975
and
rejection
radiator
temperature
respectively.
orientations
meets
indicate
solar
Growth
0
149
355
390
81
975
capability
rejection
heat
orientations
wall
large
provides
enhancements
radiator
13°C
The
also
21°C)
rejection
2 average
environment
or
three
a
13°C.
horizontal
thermal
rejection
for
W/m
at
and
of
radiator
160
analysis
with
modifications
Heat
Figs.
this
the
capabilities
periods
the
configuration
assembly
accommodate
the
radiator
radiator
radiator
during
that
is above
station
horizontal
of
2 level
7b indicates
21°C)
2°C
21°C
(2°C
100
a space
and
Control
Support
Loop
Total
fluxes.
21°C)
2° C
21°C
(2°C
Power ( kW )
Air Temperature
Equipment
Heat
below
and
Control
Support
Loop
Total
in
Air Lock-I
149
355
390
summary:
Habitation
Module-2
Item
any
Node-2
(m -_)
Air Temperature
and Humidity
Equipment
Heat Acquisition
of
Node-1
large
system
use
of
large
lunar
heat
rejection
the
view
emissivity.
Strnonsen
By covering
highly
the
surface
reflective,
temperature
can
sink temperature
produce
reduction
results
radiator
in the
low solar
reduced,
enough
the radiator
be traded
from solar
surface.
of
below
radiation
radiator
with
lunar surface
may reduce
the
wall temperature
This surface
an increase
reflecting
the
which
capability.
against
the
blankets,
be significantly
rc._Lsonable rejection
must
proximity
absorptivity
to
temperature
in solar flux, which
off the
blankets
onto
the
et al.: A lunar
A computer
blanket
model
was
size required
computer
model
parallel
to the
solar
could
reflective
insulating
ecliptic.
to radiator
From
significantly
system
to determine
and
minimum
radiator
blanket
at any latitude
were
the
585
sink temperatures.
two-sided
Radiator
blankets
on
assumed
The
oriented
surface
the
tem-
Moon.
The
to be adiabatic,
with
conductivity.
Blanket size was measured
on
width to radiator
length (W/L),
vs. radiator
length
the above
control
favorable
a vertical,
be calculated
a very low thermal
the basis of blanket
height
generated
to produce
simulated
peratures
base thermal
(H/L)
model,
reduced
as defined
it was found
the
radiator
in Fig. 9.
that
sink
the reflective
temperature
blankets
for radiator
height to blanket width (H/W)
ratios above 0.3 (H/L divided by
W/L from Fig. 10). If the insulation
area were increased
further,
only a slight
Solar Flux
Based
on
reduction
in Tsi_ would
a H/'W
ratio
of 0.3,
occur.
sink
temperatures
of radiators
surrounded
by reflective
insulating
blankets
were calculated
Lacus Veris over the length of the lunar day. The blanket was
sumed
to have
atures
were
shown
in Fig. 1I. From the figure,
a 50°C
"-- Solar Flux
,z/_ equal
compared
temperature
the
sink
rejection
temperature
reflected
solar
for parts
of the
sufficient
improvement
This
.If
Lunar Surface
(c) L.-._
sink
coupled
gain
blankets
the
a heat
pump
a cascaded
space
station
Radiator orientations.
2
- q TOT
system.
vapor
cycle
ammonia
heat
A schematic
of a two-loop
(S. T Worley,
personal
working
enters
fluid
pressurized
cascaded
communication,
VCS is shown
1988).
the VCS in a superheated
by the
compressor.
The
The
state
in Fig. 12
central
and
refrigerant
(b)
_
+qTOT
- q TOT
2
- q TOT
Fig. 6.
the
sink
Heat flux conventions
used.
+qTOT
bus
is then
is then
cooled to a saturated
liquid state in the evaporator/condensor
then subcooled
before
finally returning
to the central
bus.
(a)
+qTOT
do not
capability.
is to raise
was
in
is still
existing
by using
standard
low
above
be done
with
heat
the
increase
temperature
in this study
as
noon,
temperature.
than
of the
insulating
in the rejection
the
sink
higher
a radiator
day. The
case,
pipe radiators.
further
Fig. 5.
could
in the
because
significantly
evaluated
,system (VCS)
L ............
to lowering
temperature
system
lunar
temper-
that at lunar
still remains
primarily
sink
uninsulated
it is shown
Consequently,
provide
The
from
loop,
calculated
for the
is achieved
present
temperature.
The
those
temperature
flux.
An alternative
_-Insulated
drop
However,
radiator
t_"
to 0.1/0.9.
with
at
as-
and
The
586
2nd
working
Conference
fluid
condensor
heat
in the
and
is removed
more
from
stage
over
be
run
reject
to
the
lunar
constant
from
vertical
lunar
day
2 and
be
day.
and
This
heat
Lacus
flux.
the
while
days
3-11
during
days
second
the
both
15-
are
20.5
kW
of
based
on
the
rejected.
each
loop.
The
that
is,
the
of the
13.
During
cascaded
loops
was
would
would
be
be
0-
would
in
The
in
working
fluid
however,
6
operation,
the
These
rejection
extra
be
of
temperatures
(257,
rejected
heat
the
the
and
of
be
heat
imparted
portions
The
to
to
operation
minimum
heat
initial
K,
radiator
rejection,
phase.
the
would,
the
extra
the
lunar
2)
loop
the
total
similar
a final
temperature
operating
require
226m
rejection
and
By selecting
a midstage
effective
will
kW.
heat
equals
requirements
for
an
242,
of
bypassed.
the
360
required
29.5
amount
are
power
compressor
the
and
for
phase
increase
required
during
were
for
initial
A stagewise
required
rejected
loop
plus
maximum
obtained
areas
to
the
would
the
power
loops
areas
be
be
load
rejected
both
temperature
system.
in operation.
or
first
increase
areas
be
VCS
compressor
compressors.
the
(q),
K can
kW. The
also
the
for
the
loop
heat
to
lists
to
50
of
habitable
by
one
loads
311
total
heat
capabilities
heat
to
minimize
day when
use
would
the
of
requirements
The
second
VCS
rejection
bypassed,
the
the
Table
the
days
system
compressor
compressors
over
14.
by up
and
amount
with
power
Fig.
acquired
variations
ecliptic)
in Fig.
was
to operate
capability
solar
illustrated
added
encountered
radiator
rejection
cascaded
each
temperature
temperature
the
compressor
allow
selected
first-stage
28 no
to
use
enable
stage
in
requirements
VCS
radiator
to
coinciding
shown
the
in
heat
the
over
sink
The
The
where
temperature.
operation,
(parallel
evaporator/
ratios
increased
would
Veris
12-14,
operating
during
an
in the
process,
temperature
were
increasing
radiators
at
days
as
heat
Activities
a single-loop
and
stagewise
the
Space
at an elevated
over
involved
for
to
a more
radiator
refrigerants
allow
up
a similar
selected
excursions
and
picks
compression
could
needed
loop
the
The
would
Bases
through
was
efficient
compressors.
system
second
VCS
temperature
Lunar
proceeds
A cascaded
for
on
range
maximum
during
of
of
file
radiator
minimum
rejection
800
600
a)
600
r© Horizontal
q
(W/m 2)
400
(b)
400
X Perpendicular
q
A Parallel
(W/m
2)
X Perpendicular
200
_ Parallel
O Horizontal
I
5
0
I
10
I
15
I
20
I
25
200
I
30
0
I
5
Time (Earth Days)
Fig.
7.
with
a wall temperature
(a)
Heat
rejec'tion
capability
of 13°C
I
10
I
15
I
20
I
25
I
30
Time (Earth Days)
for
radiators
at the South
with
a wall
temperature
of
-6°C
at the
South
Pole.
(b)
Heat
rejection
capability
for
radiators
Pole.
750
(b)
750
5OO
I
50o
(a)
0-----
250
25O
q
q
(W/m 2)
0
-250
©
Horizontal
X
Perpendicular
A
Parallel
(W/m2)
0
O
Horizontal
X
Perpendicular
Parallel
-250
-500
-750
0
I
5
[
10
[
15
I
20
I
25
1
30
-500
0
i
5
Time (Earth Days)
Fig. 8.
(a) Heat
a wall temperature
rejection
of 13°C
capability
for
at Lacus Veris.
radiators
i
10
Time
with
a wall
temperature
of
-6°C
at Lacus
Veris.
(b)Heat
I
15
I
20
I
25
J
30
(Earth Days)
rejection
capability
for
radiators
with
Simonsen
times.
This
amount
As
shown
results
(420
on
temperature
of total
in
W/m
the
larger
in
Fig.
fairly
to
than
imbalances
13,
wide
e to 900
minimum
a radiator
selection
radiator
the
stagewise
rejection
or
four-stage
to
provide
further
level.
reduce
and
operation
the
the
times
This
the
the
the
power
still
capability
is based
potential
cause
heat
VCS
radiators
the
ms the
exists
radiator
thermal
and
is
fluid
the
effects
be
for
considered
the
requirements.
of
of
the
radiators
peaks
However,
tance)
of
the
function
by
on
heat
pipes.
the
louver
radiator.
This
concept
in Fig.
during
the
over
or
13 by
would
highly
the
be
the
when
the
to
a/e
use
emisssive
to
flux
of
the
by opening
radiator
effective
used
louvers
and
louvers
ratio
accomplished
the
could
maintenance
of minimizing
be
effective
be
587
increase,
means
decreasing
closing
times
to
13
could
blades
increasing
the
the
This
system
expected
Other
Fig.
changing
control
increases,
are
peaks
1986).
thereby
shown
system
to decrease.
high
(Agrawal,
thermal
stages
the
conductance
closing
base
refrigeration
is expected
Louvers
radiator
surface,
may
flux
reliability
or
of
complexity
the
for
flux
number
the
or variable
TCS.
system
constant
overall
the
when
of the
the
rejection
of the
can
rest
refrigeration
a more
reduce
of
heat
area
capability,
during
radiator
therefore
and
in
2 ). Since
design
in the
A three-
to
the
over-reject
as a means
and
required.
excursions
W/m
heat
would
area
et al.: A lunar
emittance
help
reduce
the
(reducing
the
emit-
capability
is significantly
35O
300
25O
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Uninsulated
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200
150
100
I
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7.5
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12.5
15
Time (Earth Days)
Fig. 9.
Radiator
and reflective
insulation
blanket
Fig. 11.
Uninsulated
vs. insulated
for a radiator at Lacus Veils.
model.
sink
temperatures
over
the
lunar
,,4
o
34°
I
320_
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6
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Fig. 10.
amounts
1042
Loop 2
R 12
260
Width/Radiator
Effective
sink temperatures
of reflective
insulation
bl'_ets
Length
at mxm for a radiator
at Lacus Veils.
To Central
(W/L)
with
Bus
From
Central
varying
Fig.
12.
Two-loop
cascaded
vapor
cycle
system
270
Bus
day
588
2rid
Conference
on
Lunar
Bases
and
Space
Activities
50I000
1
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30--
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Time (Earth Days)
400
I
I
I
I
I
I
I
0
5
10
15
20
25
30
Time
Fig.
13.
loop
cascaded
Rejection
capability
vapor
cycle
(Eadh
of the radiator
system
the lunar day for
over
design
operation.
level
The
and
in
response
ranges
in
type
be
which
An
the
The
gas
concept
that
is pressurized
fluid
Reay,
level,
a
at
1978).
of the
gas
into
back
heat
slight
the
If the
heat
is,
the
rejection
temperature
were
radiator
pipe
in
the
rejection
as
the
area
a
result
radiator
for
transportation
and
rejection
more
opposite
would
of
with
of
of
the
temperature
the
push
to
inert
area
for
restabilize.
would
An
occur,
increase
external
would
reduction
in
then
rejected
was
to
the
designed
must
be
of the
be
Minimum
(m z)
Area
done
types
of heaters.
Heat
Rejection
active
radiator
match
fluid
heating
System
at
the
inert
Design
Since
operating
the
inert
saturation
different
gas
heat
rejection
different
changing
This
the
the
operation),
at these
the
area.
reducing
three
stagewise
to
working
by
levels.
function
from
adjusted
rejection
imbalances
appropriate
to
by
154
161
154
226
prevent
(resulting
pressure
q
2)
750
900
750
420
would
The
weight,
_rt
volume,
and
In
both
gas
vapor
temperatures.
using
electrical
This
or
other
Eatimates
extra
the
transport
working
aluminum
and
sized
load
kW)
redundant
packages,
rejection
heat
were
when
set
system
loads
sink
the
radiator
also
exchangers.
of
of
the
to the
lines
clamp
lines
radiators.
installed.
for
designed
base.
results
the
The
to
included
The
rejection
La,'us
the
in
growth
system
along
the
heat
the
an
lines
were
phase
heat
included
loop,
both
with
summary
bus
also
temperature
In
the
Veris.
Fig. 6 plus
transport
the
and
for
and
shown
sensors.
evolve
mechanisms,
Pole
The
each
and
calculated
South
to accommodate
valves,
was
panels,
and
initially
disconnects,
were
at the
system
fluid,
out
(201
power
systems
m of lines
a
10.0
and
rejection
cases,
exchangers,
design
radiator
decrease.
reduced
the
increase
would
effect
a
reduction
an
inert
(Dunn
from
(W/m
reject
pressure
temperataure
pipe
to
filled
would
fluid
exposing
allow
reduced,
rise
working
thus
heat
temperature
should
produce
pressure
controlling
Maximum
2)
257
242
257
226
could
reservoir
vapor
(m
temperatures
some
used
radiator
temperature
The
summary
phase.
Maximum
Area
system
technique
by
being
a large
operating
input
would
increased
area
saturation
heat
fluid.
capability
or
the
reservoir,
which
input
capability
rise
working
rejection,
conductance
to
expand
baseline
used.
variable
appropriate
If the
resulting
pressure
to
the
be
q
2)
actually
temperature
rejection
a heat
by
Consequently,
could
connected
or
actuation
the
of
fluid
level
actuated
multiple
operate.
surface
design
single
the
radiator
consists
working
working
and
of
the
a
for the initial
450
600
450
420
contract
this
must
Minimum
(W/m
usually
from
of
requirements
(kW)
during
are
that
actuator
control
amount
appropriate
because
radiators
help
louvers
louvers
application,
concept,
could
actual
base
controlled
alternative
heat.
in
the
Q
differences
acceptable
of electrically
radiator,
that
lunar
area
115.5
145.0
115.5
95.0
springs
temperature
For
not
the
bimetallic
to
temperature.
would
opening
spacecraft
temperature-sensitive
Radiator
311
360
311
262
by
standard
power
a two-
Total
Trio(K)
0-2
3-11
12-14
15-28
phase
operation.
TABLE 6.
Tune
(Earth
Days)
Initial
14.
systems.
Days)
over
in stagewise
Fig.
pump
cases,
the
increasing
results
bus/radiator
included
heat
Simonsen
System
station
design
heat
adapted
estimates
rejection
for
a
lunar
transportation
loops
estimates
included
provides
7a,b).
The
system
lines
weight
and
system,
such
as
equator;
of
the
farther
System
the
Fig.
initial
the
14.
Each
phase
phase
interstage
temperature
the
the
oriented
stage
to
however,
they
and
The
system
system
The
other
lower
were
system
section.
latitude
latitudes
not
summaries
estimates
previous
a
bypass
This
Heat pump
Transport
Rejection
Total
The
transport
and
heat
increase
selected
heat
pipe
as the
the
A lunar
in
will
are
be
shown
obtained
were
,system
locations,
would
with
Table
the
sized
also
the
was
station
8.
The
as
be
estimates
the
nate
each
be
adequate
the
in
for
sink
system
The
2°C
21°C
Rejection
Total
only
encountered
to
formulated
and
be
adapted
will
the
include
for
a base
alter-
high
environ-
equator.
A vapor
function.
weight,
at
trans-
require
the
this
located
station
sites
near
provide
heat
Space
a base
space
accommodate
was
selected
for
base
minimize
Conceptual
power,
and
volume
passive
if the
protect
The
space
MLI
having
habitable
station
modules
225
considered
night.
Case
One
areas
of
(from
heat
large
gains
heat
to
be
W/m2-K
the
losses
from
was
assumed
structure
with
space
protected
the
and
an
at 310
K and
Three
cases
station's
module
will
environ-
1984)
correlation).
the
into
(MLI)
lunar
(NASA,
0.16
Apollo
if
the
assumed
0.8/0.8
between
evaluated
insulation
from
were
ratio
was
capability
multilayer
determine
large
prevent
lunar
K
to
prevent
and
ode
conductance
at
control
station's
the
an
thermal
thermal
space
insulation
during
the
modules
lunar
during
the
(kW)
0.33
0.33
4
6
27
O
O
0.66
2/oC
21°C
1,518
1,755
17
19
0.66
0.66
2°C
21°C
2,920
4,488
10,681
8
13
57
0
0
1.32
Growth
Transport
to
temperatures
W/m2-K
day
1,319
2,167
5,007
Total
techniques
module's
would
Initial
Rejection
could
showed
evaluated.
environment.
whereas
latitudinal
for
compatible
that
to
lunar
adequate
equator,
identified
not
were
insulator
of
latitude
other
and rejection
sutmamr'y for initial
phases at the South Pole.
8
9
Lower
were
were
concept
the
was
the
low
resources
an
to
and
APPENDIX:
PASSIVE THERMAL
CONTROL ANALYSIS
0.05
696
825
as
technology
Pole.
were
the
were
2°C
21°C
used
modules
near
rejection
cycle
average
T_rt
or
rejection
ment
as the
Power
was
base
site
from
impact
pump
decreasing
(m 3)
Pole
technologies
thermal
derived
The
technologies
station
technology
Pole
heat
ment.
Volume
Alternate
space
regolith
South
with
(kg)
a South
Lunar
Corporation.
discussed
both
design
presented.
estimates.
operation.
heat
been
control
from
designs
Evaporator
conceptual
has
the
and
for
control
environment.
lunar
the
REMARKS
lunar
adequately
Weight
100.0
0.66
0
100.66
for
acquisition
port
at
increase.
Phase
2
15
21
38
to enhance
to determine
TABLE 7. Transport
and growth
150
2044
6979
9173
selection
where
South
selected
radiators;
stagewise
Stmstrand
the
The
may
the
estimates.
for
with
transfer
a single.
pipes
from
these
in
fi'om
heat
was
heat
(kW)
50.0
0.33
O
50.33
thermal
discussed.
areas
the
plus
by
was
those
potential
growth
obtainable
flux
used
The
at -3 ° C. A vertical
conductance
Power
1
7
10
18
technology
site
sites
estimates
The
ecliptic
capability
included
the
VCS
system
operating
constant
at Lacus
base
station
landing
as shown
and
fluid.
solar
(m _)
75
902
3338
4315
CONCLUDING
site
lOOkW.
rejection
the
rejection
loops
use
subeooler,
working
12 loop
more
for
radiators
The
for the initial
regions.
re-
latitudinal
system
Volume
589
thermal
The
lower
and
the
components
base
the
valves,
accommodate
11
Variable
were
compressor
the
internal
was
(kg)
summaries
latitudinal
system
Growth
size
1986).
station.
systems.
to
to
heat
provide
to
JSCs
cycle
Freon
Freon
larger
to
cycle
modules
temperature.
required
VCS
vapor
parallel
of the
Emulation-
used
in
the
evaporator,
two-phase
radiator
because
one
vapor
and
from
at
sized
compressor,
line
transported
The
would
ammonia
was
two
7.
Hartley,
space
night
required.
space
ca,seaded
included
the
the
and
using
data
from
JSC. This
configlocations
more
than 70 ° from
the
estimates
station
VCS
included
included
B of
day
insulation,
using
Weight
Heat pump
Transport
Rejection
Total
that
was
and
Phase
control
Initial
system
radiator
were
equipment
estimates
space
Table
The
pole.
A two-loop
with
in
Pole.
rejection
lunar
program
exchangers,
system
the
design
reg/ons.
Veris
Phase
the
easily
thermal
TABLE 8.
Transport and rejection
and growth
phases at lower
space
be
base
two-phase
pipe
techniques
determined
for
from
during
extra
heat
The
heat
Colwell
was
also
sized
be used
for base
however,
moves
1986;
the
bus
were
,system
could
flux
Model
et al.,
volume
database
jection
uration
in
(Hall
South
pumped,
2 I°C.
shown
Control
packages,
control
heat
are
Thermal
transport
and
The
could
the
ammonia
enhancement
summaries
Simulation
pump
constant
Pole.
separate,
at 2°C
rejection
on
be
a horizontal
No
South
technologies
located
would
operating
a nearly
(Figs.
the
transport
base
system
ammonia
at
and
et aL: A lunar
For
an
case
one,
aluminum
The
system
culations
conservative
shell"
was
(Fig.
around
temperature
Moon,
only
temperature
benign
the
module
supporting
modeled
as
concentric
A-l ). Calculations
results.
In this case
the
module
variations,
half
of
extremes.
temperature
the
will
cylinders
experience
when
module's
"sob
environment
of
protected
under
regolith
to
on
top.
simplify
cal-
using
this geometry
will provide
the entire
surface
area of the ".soil
whereas,
The
to be
2 m
other
half
several
the
extreme
actually
shell"
will
day/night
deployed
will
experience
meters
on
experience
below
the
the
the
more
the
lunar
590
2nd
Conference
on
Lunar
Bases
and
_.
,Space
/-
Activities
surface
Multilayer
(Fig.
determine
the
A-2).
the
following
The
maximum
environment
heat
at steady
equations
exchange
were
between
2mrlHa(T24
interior _
_
I - T2)
=
_+_
Fig.
A-1.
aluminum
5Aluminum Suppoding
__
_
Concentric
structure
2rrHkAl(T3
Structure
approximation
and
lunar
K
the
_-l
5
__Vacuum
and
T34)
'rl()
InsulatiOn
2
to
module
state
Q --- 2n-rlHh(T
Module
derived
the
for
a
lunar
module
- T4)
in
under
_
2rrHk_(T4
r4
r3
Ts)
in
r5
r4
an
regolith.
where
Ti
equator
T4
yields
of
0.17
are
equals
or
a heat
kW
gain
at
or
0.08
laboratory
Thus,
lunar
at
estimated
module
(0.3%
in
regolith
this
will
heat
and
gain
heat
system
provide
near
T z, 1"3, and
for
noon
of
the
374
Solving
lunar
amounts
to
either
night.
kW
These
).
with
T 5 equals
lunar
the
of
night.
respectively
Case
and
compared
a habitation
coupled
K
K during
negligible
load,
294
120
a heat
loss
heat
loss
and
loads
and
0.7%
the
space
adequate
already
of
the
in
25-kW
station's
MLI
protection.
Two
In this
below
case,
the
the
module
lunar
concentric
surface.
cylinders
derived
to
module
and
assumed
the
(Fig.
determine
the
was
Again,
A-3).
the
to be
The
maximum
environment
buried
system
can
2 m directly
be
following
heat
at steady
modeled
as
equation
exchange
was
between
the
state
2 rrHkreg(T2-Ts)
Q = 2rrrtHh(TI
- T2)
=
/nrs
fl
where
Ti
equals
the equator
force
of
the
thermal
Fig. A-2.
Actual
environment
of module's
Thus,
of
night
compared
habitation
or
Multilayer
Insulation
the
Interior
space
the
of this
The
kW.
must
situation
be
not
approximation
for
a lunar module
buried
directly
was
the
between
T1 equals
air
T2
heat
and
heat
loads
T_, resulting
gain
and
coupled
its
insulating
a maximum
and
already
(0.2%
near
increase
its
approaches
kW
the
MLI
in
heat
loss
are
acquired
0.4%,
with
in
a
respectively);
lunar
regolith
respectively,
temperature
module
will
gain
of
of
=
the
2.2
kW
latitudinal
the
control
and
region.
module's
will
lunar
be
total
needed
An example
be
on
determine
the
the
the
4
either
at
K at noon
near
for
gives
Solving
maximum
These
heat
load;
during
steady
T4sink)
358
night.
a
-
surface.
maximum
environment
2rrrlHOez(T
Tsm k equals
is directly
regolith.
would
to
and
l - T2)
a module
lunar
that
derived
K and
lower
where
by any
observatory
98 K during
heat
the
considered,
was
the
294
or
maximum
9%,
the
covered
equation
equator
1.7 kW
Fig. A-3.
Concentric
under the lunar surface.
Again,
station's
and
following
where
a
significantly
of 0.05
noon
compressive
decrease
that
module
Q = 2rrr]Hh(T
the
may
K at
The
protection.
case
surface
exchange
state
%
MLI
374
night.
therefore,
at noon
to
either
lunar
Three
A third
on
the
laboratory
adequate
equals
the
assumed
gain
0.11
negligible
provide
Module
it was
loss
therefore,
f
on
and,
heat
at
Ts
K during
regolith
in a maximum
Case
K and
120
conductance
capability.
"soil shell."
294
or
T2
heat
loads
are
therefore,
the
hottest
loss
7%
of
and
extra
parts
Simonsen
of
the
lunar
day
a comfortable
and
the
and
Tsink equals
lunar
nie, ht.
285
The
day/night,
with
night.
maximum
The
therefore,
during
the
environment.
extra
night
At
K during
module
the
maximum
will lose
a maximum
heat
heat
to
loss
loss
is 7%
air temperature
provide
South
Pole
the
crew
solar
flux or
heat
over
the
of
1.7 kW
will
be
Dalton
294
K
98 K during
entire
lunar
during
of a module's
control
with
T 1 equals
total
the
lunar
heat
load;
needed.
et al.: A lunar
C. and
Colony.
Hohmann
Sundstrand
heat
Corporation
pump
for
authors
their
wish
help
to express
Century
Houston.
in the
development
to the
of the
lunar
,system.
Dunn
1_ D. and
334
Rcay
D.
NA_
B. N. (1986)
Hall, Englewood
Colwell
G. T
Simulation
and
Design
Cliffs. 459
Hartley
Thermal
of
Geosynchronous
Spacecraft.
Prentice-
pp.
(1984)
Control
Detelopment
Model
for
of
the Space
an
Station
EmulationApplication.
pp.
NAG-I-551.88pp.
Dallas
T, Diaguila
Effects
Lunar
A_ J., and
of Orientation,
Radiators.
Saltsman
Lunation,
NASA TM-X-1846.
J. E (1971)Design
and
Space
19989,
Location
40 pp.
on
Studies
on
the Performance
the
of
Heat
Pipes,
Hartley
J. G. (1986)
and
2nd
Planetary
edition.
Institute,
Pergamon,
Proc.
Evaluation
lnter_)c.
Conf.
of space
Environ.
Sys.
station
16th,
Design
of
Space
Pou_r
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