in terms of Natural Resources it is
unlikely that the earth can support an
ever-growing population was
progressively higher living standards
forever by giving man the necessary
exploitation and transportation systems
he can make the entire solar system and
raumati of sorts and cultivate earth is
the biological center of a growing
mankind
initial studies of the first manned
flight to Venus and Mars during the
early nineteen seventies very weird
internet business program history shows
that such ambitions can be realized the
first age of discovery began when Henry
the Navigator covered 1,200 miles
between party go and the Azores only 90
years thereafter Magellan had circled
our world our presentation of discovery
began for centuries later
now we have progressed to a point where
we expect to reach the moon in this
decade limited man interplanetary flight
can then come in the seventies by the
end of the eighties we should have
covered the entire solar system with
instrumented probes this then offers the
realistic possibility that a magellan
could reach Prudhoe by 1995 just 53
years after the first last year our
flight
it may be considered part of the answer
to why we should now be preparing to
development interplanetary flight
capability they come to questions
what do we want to do how and when our
first objective is to demonstrate the
actual accomplishment the feasibility of
manned flights to Venus and Mars we want
to conduct low altitude reconnaissance
of these planets in summary we want to
leave the foundations for the man
planning expeditions to follow we have a
choice of three mission types flyby
where we simply make a hyperbolic
encounter with the planet path through
its activities fear and return to Earth
capture where we stay near the planet as
a satellite for anywhere from 10 to 50
days before returning DTF planetary
reconnaissance involves many types of
artillery speak of for example from Mars
we have studied members
floaters Landers and return to of which
also serve as Mark excursion vehicles
for an optional limited man landing
operation if Jack feasible by the
expedition the martian moons will be
brought by separate probes the third
choice of course is surface landing
involving a major assault on the planet
with longer stay time and mobile
exploratory capability in terms of
overall effort the difference between
flyby and captures small the same ships
the same unknown and the same risks are
involved capture is somewhat more
expensive energy wise and fly by
but here's the greatest return in terms
of information and progress toward a
major landing mission which must be the
ultimate objective so I studies
primarily based on the capture mission
we're landing as possible but not
required for mission success effect and
trade-offs are established iterated and
reiterated until they can be integrated
into a balanced program among the
criteria are planetary constellations or
the schedule and if your requirements or
proposing systems Mission periods and
period distances wait considerations
roses radiation shielding requirements
capture period and acura vehicles
orbital words into our ability to
assembly vs launch the requirements for
emergency capabilities brother's birth
rescue capabilities and finally mission
flexibility reliability and overall
economy
this calls for integration of the
planetary into the total national space
program especially the orbital and the
lunar programs for the mutual benefit
now we have constructed maps for the
interplanetary navigator to use in
charting his cars to be innocent much
doing all suitable constellations in the
seventies
absolutely so the earth departure and
arrival date the ordinate the target
planet arrival and departure date this
date is upset with respect to the Exeter
by the minimum transfer time to time the
planet considered the two data messed
around the equal Dateline these lines
here represent lines of constant
transfer period from the entire planet
please entire plan to Earth by
connecting an earth departure date and a
transfer period the transfer orbit to
the target planet is defined in terms of
its orbital elements transferring levity
and hyperbolic access velocity of
departure entire plant arriver but the
first portion of a given mission profile
is defined by connecting a selected
departure date with a given transfer
period our capture period is measured
here return orbit is again defined by
selecting a target planet departure date
and a transfer period for the return
flight now the complete mission profile
is defined on the mission map the
profile is represented by this line
great date instant there is an infinite
number of transfer orbit of varying
periods selecting discreet dates and
transfer p it we obtain a number of
discrete one-way orbit out and make each
represented by a thought on the t1 or t2
line some of these orbits are more some
are less expensive in terms of transfer
energy either for us escape and target
can't capture or for target plant escape
and birth recaptured
not only does the absolute energy level
very the energy distribution between
Earth escape and target plant capture as
well as that for the return transfer
there is also for an earth-mass round
trip in 1973 75 this energy pleasantries
out obviously the wide variation of
energy levels impose constraints on the
feasibility of certain mission profile
some waters are just not meddle in the
early seventies because the available
providers and systems are inadequate
these regions then look the most of our
profiles for that time an additional
constraints imposed by practical
limitations in minimum solar distance
during the mission for the present we
assume that period distances of less
than points6 astronomical units will be
avoided
except in emergencies and that on the
other hand the ships are insensitive to
danger down 20 point nine astronomical
units for Mars we have avoided to even
distances of less than open a technology
unit
this then is a distribution of the
intermediate region here we see that
most of the desirable energy regions do
not coincide with regions of dangerous
serious centric distances in many cases
we do not pass through the period at all
so this constraint is not involved so
here at a glance of the earth mars
mission windows were not in 73 75 this
is the most of our mass period in the
decade in 75 77 the conditions are
comparatively less favored in 70-79 the
energy requirements for fast
reconnaissance missions are very sevilla
but if we could capture during the 73 75
pn we would now be prepared to take
advantage of these conditions he could
be our first major landing where we
would not have to worry about immediate
return
Andres avoid the high energy
requirements connected with this
constellation our state time would now
be approximately 360 days with a very
inexpensive flight home at certain
constellations we transfer orbit our
steeply inclined with respect to the
ecliptic to avoid the associated high
energy requirement it is necessary to
make a plane change our route
this raises a number of major maneuvers
during one transfer 23 the practical
implications of this depend mainly on
the type of engines available
constellations of this type are rare
between 1775 Venus offers monthly over
conditions in terms of both reduce
energy requirements and mission period
in addition the Sun is quiet making
Venus runs all the more attractive
during these constellations mission
velocities for Venus are roughly sixty
to eighty five percent of those for Mark
mission p it's a generally one year less
for Venus and range from 372 for 50 days
from Mars the how is dominated by two
major questions we don't know just what
mission links man can stand so we have
selected the shortest trips consistent
with mission objectives and propulsion
energy proportion of the second question
our mission capability will be
profoundly influenced by whether we have
a medical ID reactor engine of hi mrs.
versatility and long lifetime the best
approach involves a highly modular lized
ship with a high Flash nucleus Cape
booster and an interplanetary ship with
a crew of preferably eight persons the
expedition would be flown by a convoy of
one cool vehicle and one or two service
vehicles that serve as their cruise
ships and carry propellant reserves
spare part and most of the actual
vehicles to reduce crew risk and
standardized parts and operations this
concept is based on complete
interchangeability of propellant
thanks life the process two modules and
other essential subsystems in this phase
the escape booster and the
interplanetary ship are handled and
checked out a separate units the escape
booster requires the first about 700,000
pounds which could be generated by
either 17 okay engine or for fevers
engines cluster 25 feet apart to prevent
excessive react interaction specific
impulse would be about eight hundred
forty-five seconds the interplanetary
ship has a mission engine of 30 to
50,000 pounds trust experimental is
included both units are made in the last
area for complete checkout and systems
testing since the equal sizes vary with
planet and our planetary constellation
the tanks are custom-made for different
missions the modular design takes
requirement into account prior to launch
the units are mated cured and otherwise
made operational
put into orbit by post set on the eager
of 750,000 21 million pounds table
capability they are made it again and
Flight Readiness tested so assembled
they are self-sufficient for the entire
mission automating of such massive units
can be avoided if the crew because get
to the planet into sections one being a
life-support system and our capture
module the other the target planet
escape module so each section would be
launched into the pouch orbit as payload
of a completely with earth escape
booster and target plane capture module
attached
this mode then requires making
operations in the target plan capture
orbit the life-support system protected
by eleven thousand five hundred pounds
of polyethylene feeling is highly
modular alized here we have formation
modules containing 42 minerals and
observatory food sanitation and Sarge
facilities a gymnasium a scientific and
medical lab library and Recreation Area
and repair shop the heart of the
life-support system the command module
is immersed in the maneuver for hydrogen
tank continuing our control and other
key equipment
it also serve as irrigation storm
shelter for the entire cruel by virtue
of combined polyethylene and hydrogen
ceiling and utility shaft with a system
of locks provides access to the mission
modules to space texas which are used to
intervene for travel and what you
exchange operations and to the eight men
Apollo type of entry module front
sections of the servicing of kelly
opportunity equals of comparable wait
only one accompanies the cruise ship
back to earth now it has almost no
payload but enough propellant to carry
the crew and if life-support system
during the target plant escape and earth
capture maneuvers in case the original
crew video is incapacitated the
life-support system except the earth
entry module is dead isn't prior to have
capture the other energy of the cruise
ship is then reduced to a slightly
negative value to retain earth capture
giving expected Apollo conditions for
atmospheric entry
this is the weight distribution of a
self-sufficient proving come for a
typical reference mission to mars in
1973
now assuming mark for the first capture
mission and taking 1973 opposed the
easiest constellation and a prerequisite
for major landing later in the decade we
have been asked to investigate the
aspect of preparing for that mission
this schedule covering all directly and
indirectly involved key requirements is
an example of what would have to happen
if the 1973 date with marks were to be
met a great number of basic decisions on
which to base the planning must be from
imagine and 64 particularly the choice
of nuclear engine and mr. moulder using
the convoy vehicle s pacesetter
pre-designed should be completed in the
same time by basic testing proceeds to
lay the foundations for experimental
design which continues parallel to
experimental testing and is complete by
mid 66 final design requires
specification of all important
subsistence here and data from
supporting space research programs
interplanetary probes for example are
set into the system the ecological and
life-support systems must enter design
and hardware faces by with 64 to provide
the necessary specifications by mid 66
component testing proceed parallel to
final design following ground test the
life-support system is tested in orbit
providing at the same time and space
laboratory test articles and prototype
modules are manufactured during the 67th
470 period subsystem hardware must be
delivered during this time
test articles and prototype modules are
concurrently ground and orbit tested
changes resulting from evaluation of the
test in 68 and 69 can still be
incorporated into the operational system
which end of production mid-nineteen our
eternity in late 71 and the first half
of 72 the crew and the prototype we can
have a final operation rehearsal running
two or three lorna capture missions
involving saloon and transform the
flight path they simulate all essential
features of the interplanetary mission
and at the same time deliver life
support systems for the first lunar base
any significant deficiencies uncovered
during these flights could not be
rectified in time for the 1973 mass
capture postponing into 1975 but
assuming the rehearsals are successful
the road to our departure of the convoy
in April or May 1973 would be clear
since we assume that at least two car
dealerships will be launched at least
three ships must be brought to our flag
readiness involving six launches if they
are seventy-five percent success for a
total of eight mainlanders required plus
several supporting launches of smaller
vehicles for personnel transport repair
& whistling his tax with one once per
month from each of three complexes
delivery of all because it's
accomplished inside three months a total
hundred days from first launched already
part is postulated this time is slightly
more than twenty percent of the mission
period problem it can be reduced and the
confidence level in this realization
increased by the use of up strong launch
facilities in this case spare launch
platforms can quickly replace a platform
destroyed by a launch failure or spear
can be thrown into increase a large
density if necessary
obviously the schedule is very tight
requiring unprecedented this supreme and
success in its execution
its purpose is to show that a strong
sense of urgency is required if we are
to try for mass in 1973 this program at
the considerable owed to the strain of
the Luna and posts that are largely the
programs in view of the resulting stress
on manpower funds and facilities the
chances of missing the imaginal 73 miles
mission windows are very strong
however there are several things we can
do about the situation first we can work
toward a fully-integrated national
program for manned spaceflight taking a
modular eyes de proach to space station
Luna and Venus mass programs they are
not separate or even competitive
programs that can be helped as
individual combinations of common
element our present and future efforts
towards standardized instrument units
guidance communication and power
generation systems can be complemented
by standardizing space weaker sections
and space we go for use in all three
programs and for as many missions
possible life-support system and nuclear
power into a burrito development are
cases in point the life-support systems
for say an eight-man space station and
89 first-generation lunar base and an
eight-man first reconnaissance ship to
Venus or Mars enough alike that we could
plan the development of a single
long-duration life support system for
use directly or with some modification
and all three programs look at the power
space we go are a real necessity for
systems transportation and man planetary
flight the nerve engine speed the
important development of nuclear rocket
engine technology subsequent efforts are
expected to concentrate on improving
thrust specific impacts and operational
versatility
this should lead to an advanced Nerva
with higher specific impulse and to an
engine of higher thrust and higher
specific impart the letter which use the
reactor off the type designated Phoebus
by the Los Alamos scientific laboratory
for still higher fright previous reactor
engines could be trusted or an engine of
about four times higher thrust could be
considered in lieu of the few attention
from the vehicle systems you appoint the
letter would be more desirable for the
earth escape booster of an
interplanetary ship primarily because it
is lighter than in cluster of equal
pressed second we must carefully examine
alternative to the 19 attempts remark
capture mission the first alternative is
to continue to consider Mars and the
number-one target planet but to postpone
the first capture mission to 1975 773
the 1975 Mars mission requirements
three two large ships which for all
practical purposes call for the
availability of a post second birth
launch finger but now we have added two
years
this greatly reduces the burden of her
flat redevelopment schedules
we also stand a better chance of getting
a metrocard reactor mission engine which
would more than compensate for the
increased energy requirements of 75 / 73
postponing capture 275 however would
probably mean the abandonment of a major
landing expedition to Mars in the
seventies requiring launched in october
november 1937 this leaves insufficient
time for data reduction and evaluation
of the 75 capture the next opportunity
would be in november december 1939 in 79
80 we must expect a new peak and solar
activity which may far as a temporary
part in man planetary missions except
perhaps with week of like or I on the
second alternative is to consider venus
at first our planet which demonstrate
the technical and operational
feasibility of planetary capture
missions a 1973 mission to Venus is
quite compatible with a solar tiger
sinful activity should be a minimum
yes requirements are lower in terms of
both mission energy and mission period
for comparable capture p it's about 30
days internship of equal initial payload
weight and propulsion system will weigh
between thirty and fifty percent of the
corresponding Marcia pipe now it becomes
possible to consider 75 perhaps with
lightly operated f-1 engines is
principal Ashley go lift them would
disengage the first interplanetary
mission from the post 7ld development
program using Venus for the visibility
demonstration it is still necessary to
conduct detailed reconnaissance of Mars
to define and excite but large and
rugged instrument probes could furnish
this information with a high degree of
reliability by 1975 with both Burke
visits that's accomplished a major
marshal raining expedition could be
planned for 1977 the study so far has
produced considerable amount of results
which are reported separately five
principal conclusions and
recommendations can be presented here
first
comparisons have been made of different
types of main planetary
bigger the results show quantitatively
that nuclear propulsion in any form is
superior to chemical drives for the
missions considered not only with the
garden the size and performance but the
launch window requirements and required
level of-of pre-departure operations the
studies have also shown the advantages
of providing the planetary ship with a
nuclear mission engine of ready restart
capability and long operational life it
is suggested that the potential of metal
and metal carbides fast Neutron reactor
for entrance of the 30 to 50,000 pound
trust level before they explored second
if any man interplanetary flight to be
achieved in the seventies they're
planning and preparation must be
integrated into the national space
program within the next few years in
particular it is important to conduct an
intensive study program unsuitable post
nerve our engines this would provide the
information and recommendations required
for a decision soon as another program
has progressed adequately on the
second-generation nuclear engine using
the reactor of the serious power level
or higher a decision on this engine and
its development schedule is perhaps the
most important single input into the
system's planning of man planetary
flights for the first type of the 73rd
initially that is during the seventies
it appears to be the practical more
advisable to plan Venus or Mars missions
at a faster rate than every second
departure constellation otherwise the
results of the preceding mission could
not be evaluated in time to contribute
to the subsequent flight for Martha them
the earliest mission following in 1973
departure would begin in 1977 for a 1975
departure the next flight would be in
1979 university partners should be
planned for 1973 and late 76 or form
1975 and 78 increasing solar activity in
the second half of the seventies me well
in danger the feasibility of Venus runs
later than 1975 the same applies
tomorrow with the additional adversity
of increased energy requirements for
fast Martian mission student the
seventies and early eighties
just because the position of Earth Mars
opposition's move away from the nodal
line of the Martian orbit crossing
transfer orbit to be more steeply
inclined with respect to the plains of
the planet orbits involved for these
reasons conditions become appreciably
less favored for at least six years
following 1975 until the full activity
subside for the sex shop that is
worthwhile to attempt the first man
planetary flight in or before 1975 in
view of Luna task ahead
it appears unrealistic to plan a
planetary mission prior to nineteen
seventy-three on the other hand Mars
even in 73 and 75 requires appreciably
higher mission energies than Venus if a
post-secondary cannot be counted on for
1973 and as marginal for 925 a Venus
caption reason should be considered
seriously 473 using a second c5a zlv and
keeping the other launch weight of the
individual leadership inside 1 million
parts
this can be achieved in with a
combination of Nirvana and oxygen
hydrogen engines without losing the
capability of capture Andrea scraper on
Venus provided a capture orbit is
elliptical rather than circular since
the first one this mission may not
include an optional service excursion
capability an elliptic orbit is morally
acceptable fifth using moderately
elliptical capture orbits with an eps
assistance not more than four times the
period assistance which is assumed to
lie about thousand kilometers above the
Martian surface and allowing orbital
departure waits for camel nuclear
converse ships up to 1.5 million pounds
Mars could also be considered for 1973
or 75 in conjunction with 75 as the lv
without necessarily losing optional
surface excursion capability
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