PART 3 (D)
Lunar Orbit Rendezvous: Mode and Module
July 1962 through September 1962
1962
July
1962
August
1962
September
July 1-7
The delta V (rate of incremental change in velocity)
requirements for the lunar landing mission were established and coordinated with
NAA by the Apollo Spacecraft Project Office.
Apollo Spacecraft Project Office, MSC, Weekly Activity Report, July l-7,
1962.
July 2
NASA awarded three contracts totaling an estimated $289 million
to NAA's Rocketdyne Division for the further development and production of the
F-1 and J-2 rocket engines.
Wall Street Journal, July 3, 1962.
July 6
The document entitled "Charter of the MSFC-STG Space Vehicle
Board," adopted on October 3, 1961, was revised to read "Spacecraft Launch
Vehicle Coordination Charter for the Apollo Program MSFC-MSC." The reasons for
the revision were: to include the recently formed Management Council, to include
the Electrical Systems Integration Panel and Instrumentation and Communications
Panel responsibilities, and to establish Integration Offices within MSC and
Marshall Space Flight Center (MSFC) to manage the Panels.
MSF Management Council Minutes, June 25, 1963, Agenda Item 6.
July 6
Employment at NAA's Space and Information Systems Division
reached 14,119, an increase of 7,000 in seven months.
Oakley, Historical Summary, S&ID Apollo Program, p. 7.
July 10
The first Apollo spacecraft mockup inspection was held at NAA's
Space and Information Systems Division. In attendance were Robert R. Gilruth,
Director, MSC; Charles W. Frick, Apollo Program Manager, MSC; and Astronaut
Virgil I. Grissom.
Oakley, Historical Summary, S&ID Apollo Program, p. 7.
July 10-11
At the monthly Apollo spacecraft design review meeting with
NAA, MSC officials directed NAA to design the spacecraft atmospheric system for
5 psia pure oxygen. From an engineering standpoint, the single-gas atmosphere
offered advantages in minimizing weight and leakage, in system simplicity and
reliability, and in the extravehicular suit interface. From the standpoint of
physiological considerations, the mixed-gas atmosphere (3.5 psia oxygen, 3.5
psia nitrogen) had the advantages of offering protection against dysbarism and
atelectasis, whereas the single-gas atmosphere afforded greater decompression
protection. The atmosphere validation program demonstrated the known fire hazard
of a pure oxygen atmosphere. Two fires occurred, one at the Air Force School of
Aerospace Medicine, Brooks Air Force Base, Tex., on September 10 and the other
at the U.S. Naval Air Engineering Center, Philadelphia, Penna., on November 17.
The answer to this problem appeared to be one of diligent effort on the part of
spacecraft designers to be aware of the fire hazard and to exercise strict
control of potential ignition sources and material selection. The official
authorization was issued to NAA by NASA on August 28.
Apollo Spacecraft Project Office, MSC, Weekly Activity Report, July 8-14,
1962; Apollo Quarterly Status Report No. 1, p. 13 ; Edward L.
Michel, George B. Smith, Jr., and Richard S. Johnston, Gaseous Environment
Considerations and Evaluation Programs Leading to Spacecraft Atmosphere
Selection, NASA Technical Note TN D-2506 (1965), pp. 1-6; letter, C. D.
Sword, MSC, to NAA, Space and Information Systems Division, "Contract Change
Authorization No. 1," August 28, 1962.
July 10-11
Charles W. Frick, MSC Apollo Project Office Manager, assigned
MIT Instrumentation Laboratory to report on a simulated lunar landing trainer
using guidance and navigation equipment and other displays as necessary or
proposed.
Ralph Ragan, notes, 4th Apollo Design Review Meeting, NAA, S&ID, Downey,
Calif., July 10 and 11, 1962.
July 11
NASA officials announced at a Washington, D.C., press conference
that the lunar orbit rendezvous (LOR) technique had been selected as the primary
method of accomplishing the lunar landing mission. The launch vehicle would be
the Saturn C-5, with the smaller two-stage Saturn C-1B (S-IVB as second stage)
used in early earth orbital spacecraft qualification flights. Requests for
industrial proposals would be issued immediately on the lunar excursion module,
The reasons for the decision on lunar orbit rendezvous were explained:
- A higher probability of mission success with essentially equal mission
safety was provided by this technique.
- The method promised mission success some months earlier than other modes.
- LOR costs would be ten to 15 percent less than other techniques.
- LOR would require the least amount of technical development beyond
existing commitments while advancing significantly the national
technology.
In addition, it was announced that:
- Studies would continue on the feasibility of using the Saturn C-5 to
launch a two-man spacecraft in a direct ascent approach to the moon or in an
earth orbit rendezvous mode.
- An in-depth study would be made on a lunar logistics vehicle.
- Investigations would continue on the development of the Nova launch
vehicle.
NASA, "Lunar Orbit Rendezvous: News Conference on Apollo Plans
at NASA Headquarters on July 11, 1962," pp. 1, 3, 4.
July 16
Beech Aircraft Corporation was selected by NASA to build the
spherical pressure vessels that would be used to store in the supercritical
state the hydrogen-oxygen reactants for the spacecraft fuel cell power supply.
Apollo Quarterly Status Report No. 1, p. 23; Oakley,
Historical Summary, S&ID Apollo Program, p. 6.
July 17
Joseph F. Shea, NASA Deputy Director of Manned Space Flight
(Systems) , told an American Rocket Society meeting in Cleveland, Ohio, that the
first American astronauts to land on the moon would come down in an area within
ten degrees on either side of the lunar equator and between longitudes 270 and
260 degrees. Shea said that the actual site would be chosen for its apparent
scientific potential and that the Ranger and Surveyor programs would provide
badly needed information on the lunar surface. Maps on the scale of two fifths
of a mile to the inch would be required, based on photographs which would show
lunar features down to five or six feet in size. The smallest objects on the
lunar surface yet identified by telescope were about the size of a football
field.
MSC Space News Roundup, August 22, 1962, p. 8.
July 17
In an address to the American Rocket Society lunar missions
meeting in Cleveland, Ohio, James A. Van Allen, Chairman of the Department of
Physics and Astronomy, State University of Iowa, said that protons of the inner
radiation belt could be a serious hazard for extended manned space flight and
that nuclear detonations might be able to clean out these inner belt protons,
perhaps for a prolonged period, making possible manned orbits about 300 miles
above the earth.
New York Times, July 18, 1962.
July 20
NASA Administrator James E. Webb announced that the Mission
Control Center for future manned space flights would be located at MSC. The
Center would be operational in time for Gemini rendezvous flights in 1964 and
later Apollo lunar missions. The overriding factor in the choice of MSC was the
existing location of the Apollo Spacecraft Project Office, the astronauts, and
Flight Operations Division at Houston.
New York Times, July 22, 1962; NASA News Release, 62-172, July
20, 1962; memorandum, Robert C. Seamans, Jr., to Administrator, "Location of
Mission Control Center," July 10, 1962.
July 21
NASA announced plans for an advanced Saturn launch complex to be
built on 80,000 acres northwest of Cape Canaveral. The new facility, Launch
Complex 39, would include a building large enough for the vertical assembly of a
complete Saturn launch vehicle and Apollo spacecraft.
Washington Sunday Star, July 22, 1962.
July 25
MSC invited 11 firms to submit research and development
proposals for the lunar excursion module (LEM) for the manned lunar landing
mission. The firms were Lockheed Aircraft Corporation, The Boeing Airplane
Company, Northrop Corporation, Ling-Temco-Vought, Inc., Grumman Aircraft
Engineering Corporation, Douglas Aircraft Company, General Dynamics Corporation,
Republic Aviation Corporation, Martin- Marietta Company, North American
Aviation, Inc., and McDonnell Aircraft Corporation.
The Statement of Work distributed to the prospective bidders described the
contractor's responsibilities:
- Detail design and manufacture of the LEM and related test articles,
mockups, and other hardware with the exception of certain government-
furnished equipment [navigation and guidance system (excepting the rendezvous
radar and radar altimeter), flight research and development instrumentation
system, scientific instrumentation system, and certain components of the crew
equipment system (space suits, portable life support systems, and personal
radiation dosimeters.)]
- Integration of government-furnished equipment into the LEM; development of
specifications for equipment performance, interfaces, and design environment;
and maintenance of interface control documentation in a state of validity and
concurrence.
- Detailed trajectory analysis from lunar orbit separation until lunar orbit
rendezvous directly related to the contractor's area of responsibility.
- Specification of the mission environment on the lunar surface and
assessment of the effects of the spacecraft adapter environment on the LEM.
- Detail design of the LEM-mounted equipment for repositioning and mating
the LEM to the command module CM.
- Design of the LEM-mounted equipment within the overall specification of
the Principal Contractor NAA.
- Determination of the desirability of checkout or operation of the LEM
during the translunar period of the flight.
- Identification of crew tasks related to the LEM before and during
separation, whether actually performed in the LEM or CM.
- Design and manufacture of the ground support equipment directly associated
with the hardware for which the contractor was responsible and ensurance of
compatibility of all ground support equipment involved with the LEM.
- Design and manufacture of certain LEM training equipment for flight or
ground personnel as required by NASA.
- Prelaunch preparation and checkout of the LEM, working with the other
contractors in the same manner as during systems testing.
- Coordination of all LEM activities with the overall spacecraft prelaunch
requirements.
- Planning and implementation of a reliability and quality assurance
program.
- Provision of adequate logistic support for the equipment furnished by the
contractor.
The mockups to be delivered by the contractor would include
but not be limited to:
- Complete LEM
- Cabin interior arrangement
- Cabin exterior equipment
- Docking system
- Environmental control system
- Crew support system
- Antenna radiation pattern
- Handling and transportation
- Module interface
Before the first translunar midcourse correction,
the LEM would be transferred from its stowed position in the spacecraft adapter
to a docked configuration with the command and service modules (CSM). At a later
point in the mission, the two-man LEM crew would enter the LEM from the CSM by
means of a hatch without being exposed to the environment of space. Another
hatch would allow access to the LEM during countdown and egress into space while
docked with the CSM.
The LEM systems were to operate at their normal design performance level for
a mission of two days without resupply. Equipment normally operated in the
pressurized LEM cabin environment would be designed to function for a minimum of
two days in vacuum without failure. The LEM pressurization system would be
capable of six complete cabin repressurizations and a continuous leak rate as
high as 0.2 pound per hour. Provision would be made for a total of six recharges
of the portable life support system which had a normal operating time without
resupply of four hours. Under usual conditions in the LEM cabin, the crew would
wear unpressurized space suits. Either crewman would be able, alone, to return
the LEM to the CSM and successfully perform the rendezvous and docking maneuver.
Of the overall crew safety goal of 0.999, the goal apportioned to the LEM was
0.995.
The LEM would be capable of independently performing the separation from the
CSM, lunar descent, landing, ascent, rendezvous, and docking with the CSM. It
would allow for crew exploration in the vicinity of lunar touchdown but would
not be required to have lunar surface mobility.
Lunar landing would be attempted from a lunar orbit of 100 nautical miles.
After separation, the LEM would transfer from the circular orbit to an
equal-period elliptical orbit which would not intersect the lunar surface. The
hovering, final touchdown maneuvers, and landing would be performed by the LEM
from the elliptical orbit.
Normally there would not be a requirement to reposition the LEM attitude
before lunar launch. To rendezvous and dock with the CSM, the LEM would transfer
from an elliptical to a circular orbit after lunar launch.
The LEM would not be recoverable.
Included in the Statement of Work was a description of the major LEM systems:
- Guidance and control system
- The navigation and guidance system would provide steering and thrust
control signals for the stabilization and control system, reaction control
system, and the lunar excursion propulsion system. Its basic components were:
- Inertial measurement unit
- Optical measurement unit
- Range-drift measurement unit (reticle)
- Computer Power and servo assembly
- Control and display unit
- Displays and controls
- Cabling and junction box
- Chart book and star catalog
- Rendezvous radar and radar altimeter
The stabilization and control system would meet the attitude
stabilization and maneuver control requirements and would include:
- Attitude reference
- Rate sensors
- Control electronics assembly
- Manual controls
- Displays
- Power supplies
- Lunar excursion propulsion system
- The system would use storable hypergolic bipropellants and a pressurized
propellant feed system. Variable thrust would be required from a propulsion
system to be designed.
- Propellants
- The fuel would be monomethylhydrazine or a mixture of 50 percent hydrazine
and 50 percent unsymmetrical dimethylhydrazine. Nitrogen tetroxide with
nitrous oxide, added to depress the freezing point if necessary, would be used
as oxidizer.
- Reaction control system
- The system comprised two independent, interconnectable, pulse- modulated
subsystems, each capable of meeting the total torque and impulse requirements
and providing two-directional control about all axes. The same propellant
combination would be used as for the LEM propulsion system.
- Lunar touchdown system
- Attached to the LEM by hard points which would accommodate variations of
landing gear geometrics, the system would have load distribution capabilities
compatible with anticipated landing gear loads and would include meteoroid
protection and radiation protection inherent in its structure, Normally, the
system would be deployed from within the spacecraft but could be operated
manually by the crew in spacesuits outside the spacecraft.
- Crew systems
- The flight Crew would consist of the Commander and Systems Engineer. The
crew equipment system would include an adjustable seat for each crewman,
restraint system for each seat, food and water, first aid equipment, space
suits, portable life support systems for each crewman, and personal radiation
dosimeters.
- Environmental control system
- The following conditions would be provided:
- Total cabin pressure: Oxygen, 5 +/_ 0.2 psia
- Relative humidity : 40 to 70 percent
- Carbon dioxide partial pressure (maximum): 7.6 mm Hg
- Temperature: 75 degrees ±5 degrees F
- Electrical power system
- Selection of the source was still to be made and would depend largely on
the time contingency allowed for various mission events, especially during
rendezvous maneuvers.
- Instrumentation system
- The operational instrumentation system would consist of a clock, tape
recorder system, display and control system, sensors, calibration system,
cameras, and telescope.
The flight research and development instrumentation system would be made up
of telemetry systems (including transmitters), clock and tape recorder system,
sensors and signal conditioning, calibration system, power supply, radar
transponder, and antennas.
The scientific instrumentation system would comprise a lunar atmosphere
analyzer, gravitometer, magnetometer, radiation spectrometer, specimen return
container, rock and soil analysis equipment, seismographic equipment, and soil
temperature instrument.
NASA, Project Apollo Lunar Excursion
Module Development Statement of Work (MSC, July 24, 1962), pp. 2-5, A-89
to A-108; Astronautical and Aeronautical Events of 1962, p. 130.
July 25
Wesley F. Messing was designated as Acting Resident MSC Manager
at White Sands Missile Range, N. Mex., to coordinate MSC test programs at that
site.
MSC Announcement No. 67, Establishment of Resident MSC Manager at White Sands
Missile Range, July 25, 1962.
July 29-August 4
As a result of an MSC in-house technical review, NAA
was directed to investigate the adaptation of the Gemini-type heatshield to the
Apollo spacecraft.
Apollo Spacecraft Project Office, MSC, Weekly Activity Report.
July 30
The Office of Systems under NASA's Office of Manned Space Flight
summarized its conclusions on the selection of a lunar mission mode based on
NASA and industry studies conducted in 1961 and 1962:
- There were no significant technical problems which would preclude the
acceptance of any of the modes, if sufficient time and money were available.
[The modes considered were the C-5 direct ascent, C-5 earth orbit rendezvous
(EOR), C-5 lunar orbit rendezvous (LOR), Nova direct ascent, and solid-fuel
Nova direct ascent.]
- The C-5 direct ascent technique was characterized by high development risk
and the least flexibility for further development.
- The C-5 EOR mode had the lowest probability of mission success and the
greatest development complexity.
- The Nova direct ascent method would require the development of larger
launch vehicles than the C-5. However, it would be the least complex from an
operational and subsystem standpoint and had greater crew safety and initial
mission capabilities than did LOR.
- The solid-fuel Nova direct flight mode would necessitate a launch vehicle
development parallel to the C-5. Such a development could not be financed
under current budget allotments.
- Only the LOR and EOR modes would make full use of the development of the
C-5 launch vehicle and the command and service modules. Based on technical
considerations, the LOR mode was distinctly preferable.
- The Directors of MSC and Marshall Space Flight Center had both expressed
strong preference for the LOR mode.
On the basis of these conclusions,
the LOR mode was recommended as most suitable for the manned lunar landing
mission. [The studies summarized in this document were used by the Manned Space
Flight Management Council in their mission mode decision on June 22.]
Office of Systems, Office of Manned Space Flight, "Manned Lunar Landing
Program Comparison," July 30, 1962, pp. 145-146.
July 31
The Manned Space Flight Management Council decided that the
Apollo spacecraft design criteria should be worked out under the guidance of the
Office of Manned Space Flight (OMSF) Office of Systems. These criteria should be
included in the systems specifications to be developed. A monthly exchange of
information on spacecraft weight status should take place among the Centers and
OMSF. Eldon W. Hall of the Office of Space Systems would be responsible for
control of the detailed system weights.
MSF Management Council Minutes, July 31, 1962, Agenda Item 16.
During the Month
The Hamilton Standard Division of United Aircraft
Corporation was selected by NASA as the prime contractor for the Apollo space
suit assembly. Hamilton's principal subcontractor was International Latex
Corporation, which would fabricate the pressure garment. The contract was signed
on October 5.
Apollo Quarterly Status Report No. 1, p. 29.
During the Month
The control layout of the command module aft
compartment was released by NAA. This revised drawing incorporated the new
umbilical locations in the lower heatshield, relocated the pitch-and-yaw engines
symmetrically, eliminated the ground support equipment tower umbilical, and
showed the resulting repositioning of tanks and equipment.
NAA, Apollo Monthly Progress Report, SID 62-300-5, July 31,
1962, p. 96.
During the Month
NAA completed control layouts for all three command
module windows, including heatshield windows and sightlines. Structural
penalties were investigated, window-panes sized, and a weight-comparison chart
prepared.
Apollo Monthly Progress Report, SID 62-300-5, p. 98.
During the Month
NAA's evaluation of the emergency blow-out hatch study
showed that the linear-shaped explosive charge should be installed on the
outside of the command module, with a backup structure and an epoxy-foam-filled
annulus on the inside of the module to trap fragmentation and gases. Detail
drawings of the crew hatch were prepared for fabrication of actual test
sections.
Apollo Monthly Progress Report, SID 62-300-5, pp. 97-98.
During the Month
After the determination of the basic design of the
spacecraft sequencer schematic, the effect of the deployment of the forward
heatshield before tower jettison was studied by NAA. The sequence of events of
both the launch escape system and earth landing system would be affected, making
necessary the selection of different sequences for normal flights and abort
conditions. A schematic was prepared to provide for these sequencing
alternatives.
Apollo Monthly Progress Report, SID 62-300-5, p. 123.
During the Month
NAA completed the analysis and design of the Fibreglass
heatshield. It duplicated the stiffness of the aluminum heatshield and would be
used on all boilerplate spacecraft.
Apollo Monthly Progress Report, SID 62-300-5, p. 93.
During the Month
Final design of the command module forward heatshield
release mechanism was completed by NAA.
Apollo Monthly Progress Report, SID 62-300-5, p. 79.
During the Month
Air recirculation system components of the command
module were rearranged to accommodate a disconnect fitting and lines for the
center crewman's suit. To relieve an obstruction, the cabin pressure regulator
was relocated and a design study drawing was completed.
Apollo Monthly Progress Report, SID 62-300-5, p. 73.
During the Month
A study was made by NAA to determine optimum location
and configuration of the spacecraft transponder equipment. The study showed
that, if a single deep space instrumentation facility transponder and power
amplifier were carried in the command module instead of two complete systems in
the service module, spacecraft weight would be reduced, the system would be
simplified, and command and service module interface problems would be
minimized. Spares in excess of normal would be provided to ensure reliability.
Apollo Monthly Progress Report, SID 62-300-5, p. 84.
During the Month
A modified method of cooling crew and equipment before
launch and during boost was tentatively selected by NAA. Chilled,
ground-support-equipment-supplied water-glycol would be pumped through the
spacecraft coolant system until 30 seconds before launch, when these lines would
be disconnected. After umbilical separation the glycol, as it evaporated at the
water boiler, would be chilled by Freon stored in the water tanks.
Apollo Monthly Progress Report, SID 62-300-5, p. 75.
During the Month
NAA selected the lunar landing radar and completed the
block diagram for the spacecraft rendezvous radar. Preliminary design was in
progress on both types of radar.
Apollo Monthly Progress Report, SID 62-300-5, p. 57.
During the Month
A 70-mm pulse camera was selected by NAA for mission
photodocumentation. The camera was to be carried in the upper parachute
compartment. Because of the lack of space and the need for a constant power
supply for a 35-watt heating element, NAA was considering placing the camera
behind the main display panel. The advantages of this arrangement were that the
camera would require less power, be available for changing magazines, and could
be removed for use outside the spacecraft.
One 16-mm camera was also planned for the spacecraft. This camera would be
positioned level with the commander's head and directed at the main display
panel. It could be secured to the telescope for recording motion events in real
time such as rendezvous, docking, launch and recovery of a lunar excursion
module, and earth landing; it could be hand-held for extravehicular activity.
Apollo Monthly Progress Report, SID 62-300-5, p. 81.
During the Month
NAA investigated several docking methods. These
included extendable probes to draw the modules together; shock-strut arms on the
lunar excursion module with ball locators to position the modules until the
spring latch caught, fastening them together; and inflatable Mylar and
polyethylene plastic tubing. Also considered was a system in which a crewman,
secured by a lanyard, would transfer into the open lunar excursion module.
Another crewman in the open command module airlock would then reel in the
lanyard to bring the modules together.
Apollo Monthly Progress Report, SID 62-300-5, p. 99.
During the Month
Command module (CM) flotation studies were made by NAA,
in which the heatshield was assumed to be upright with no flooding having
occurred between the CM inner and outer walls. The spacecraft was found to have
two stable attitudes: the desired upright position and an unacceptable
on-the-side position 128 degrees from the vertical. Further studies were
scheduled to determine how much lower the CM center of gravity would have to be
to eliminate the unacceptable stable condition and to measure the overall
flotation stability when the CM heatshield was extended.
Apollo Monthly Progress Report, SID 62-300-5, p. 27.
A recent Russian article discussed various
methods which the Soviet Union had been studying for sending a man to the moon
during the decade. The earth orbital rendezvous method was reported the most
reliable, but consideration also had been given to the direct ascent method,
using the "Mastodon" rocket.
Astronautical and Aeronautical Events of 1962, p. 1 36.
August 1
At MSC, J. Thomas Markley was appointed Project Officer for the
Apollo spacecraft command and service modules contract, and William F. Rector
was named Project Officer for the lunar excursion module contract.
MSC Space News Roundup, August 22, 1962, p. 1.
August 2
NASA's Office of Manned Space Flight issued Requests for
Proposals for a study of the lunar "bus" and studies for payloads which could be
handled by the C-1B and C-5 launch vehicles. Contract awards were expected by
September 1 and completion of the studies by December 1.
MSF Management Council Minutes, July 31, 1962, Agenda Item 7.
August 2
The heatshield for Apollo command module boilerplate model 1
was completed five days ahead of schedule.
Oakley, Historical Summary, S&ID Apollo Program, p. 8.
August 6
The MIT Instrumentation Laboratory ordered a Honeywell 1800
electronic computer from the Minneapolis- Honeywell Regulator Company's
Electronic Data Processing Division for work on the Apollo spacecraft navigation
system. After installation in 1963, the computer would aid in circuitry design
of the Apollo spacecraft computer and would also simulate full operation of a
spaceborne computer during ground tests.
Astronautical and Aeronautical Events of 1962, p. 141.
August 7
The first completed boilerplate model of the Apollo command
module, BP- 25, was subjected to a one- fourth-scale impact test in the Pacific
Ocean near the entrance to Los Angeles Harbor. Three additional tests were
conducted on August 9.
Oakley, Historical Summary, S&ID Apollo Program, p. 8; MSC,
Weekly Activity Report for the Office of the Director, Manned Space Flight,
August 5-11, 1962.
August 8
NASA awarded a $141.1 million contract to the Douglas Aircraft
Company for design, development, fabrication, and testing of the S-IVB stage,
the third stage of the Saturn C-5 launch vehicle. The contract called for 11
S-IVB units, including three for ground tests, two for inert flight, and six for
powered flight.
Astronautical and Aeronautical Events of 1962, p. 144.
August 8
Representatives of the MSC Gemini Project Office and Facilities
Division inspected the proposed hangar and office facilities to be refurbished
at El Centro Naval Air Facility, Calif., for joint use in the Apollo and Gemini
drop-test programs.
MSC, Project Gemini Quarterly Status Report No. 2 for Period Ending
August 31, 1962, p. 14.
August 8
At a bidders' conference held at NASA Headquarters, proposals
were requested from Centers and industry for two lunar logistic studies: a
spacecraft "bus" concept that could be adapted for use first on the Saturn C-1B
and later on the Saturn C-5 launch vehicles and a variety of payloads which
could be soft-landed near manned Apollo missions. The latter study would
determine how a crew's stay on the moon might be extended, how human capability
for scientific investigation of the moon might be increased, and how man's
mobility on the moon might be facilitated.
Astronautical and Aeronautical Events of 1962, p. 144.
August 10
MSC requested the reprogramming of $100,000 of Fiscal Year
1963 funds for advance design on construction facilities. The funds would be
transferred from Launch Operations Center to MSC for use on the Little Joe II
program at White Sands Missile Range, N. Mex., and would cover Army Corps of
Engineers design work on the launch facility.
MSC, Weekly Activity Report for the Office of the Director, Manned Space
Flight, August 5-11, 1962.
August 10
NASA selected the Aerojet-General Algol solid-propellant motor
to power the Little Joe II booster, which would be used to flight-test the
command and service modules of the Apollo spacecraft.
Astronautical and Aeronautical Events of 1962, p. 146.
August 11
A NASA program schedule for the Apollo spacecraft command and
service modules through calendar year 1965 was established for financial
planning purposes and distributed to the NASA Office of Manned Space Flight,
Marshall Space Flight Center, and MSC. The key dates were: complete service
module drawing release, May 1, 1963; complete command module drawing release,
June 15, 1963; manufacture complete on the first spacecraft, February 1, 1964;
first manned orbital flight, May 15, 1965. This tentative schedule depended on
budget appropriations.
MSC, Weekly Activity Report for the Office of the Director, Manned Space
Flight, August 5-11, 1962, pp. 4, 5.
August 11
Of the 11 companies invited to bid on the lunar excursion
module on July 25, eight planned to respond. NAA had notified MSC that it would
not bid on the contract. No information had been received from the McDonnell
Aircraft Corporation and it was questionable whether the Northrop Corporation
would respond.
MSC, Weekly Activity Report for the Office of the Director, Manned Space
Flight, August 5-11, 1962, p. 4.
August 11-12
The Soviet Union launched Vostok III into orbit at 11:30
a.m. Moscow time, the spacecraft piloted by Andrian G. Nikolayev. At 11:02 a.m.
Moscow time the next day, the Soviet Union launched the Vostok IV spacecraft
into orbit with Pavel R. Popovich as pilot. Within about an hour, Cosmonaut
Popovich, traveling in nearly the same orbit as Vostok III, made radio contact
with Cosmonaut Nikolayev. Nikolayev reported shortly thereafter that he had
sighted Vostok IV. In their official report, Nikolayev and Popovich said their
spacecraft had been within a little over three miles of each other at their
closest approach. This was the first launching of two manned spacecraft within a
24-hour period. Popovich and Nikolayev landed safely in Kazakhstan, U.S.S.R., on
August 15,
New York Times, August 14 and 22, 1962.
August 13
Ten Air Force pilots emerged from a simulated space cabin in
which they had spent the previous month participating in a psychological test to
determine how long a team of astronauts could work efficiently on a prolonged
mission in space. Project Director Earl Alluisi said the experiment had "far
exceeded our expectations" and that the men could have stayed in the cabin for
40 days with no difficulty.
New York Herald Tribune, August 14, 1962.
August 13-14
NAA suggested that the pitch, roll, and yaw rates required
for the Apollo guidance and navigation system would permit reduction in the
reaction control thrust.
MSC-NAA Apollo Spacecraft Design Review No. 5, August 13-14, 1962, Downey,
Calif., Item 5-6.
August 14
The NAA spacecraft Statement of Work was revised to include
the requirements for the lunar excursion module (LEM) as well as other
modifications. The LEM requirements were identical with those given in the LEM
Development Statement of Work of July 24.
The command module (CM) would now be required to provide the crew with a
one-day habitable environment and a survival environment for one week after
touching down on land or water. In case of a landing at sea, the CM should be
able to recover from any attitude and float upright with egress hatches free of
water.
The service propulsion system would now provide all major velocity increments
required for translunar midcourse velocity corrections, for placing the
spacecraft into a lunar orbit, for rendezvous of the command and service modules
CSM with the LEM on a backup mode, for transfer of the CSM from lunar orbit into
the transearth trajectory, and for transearth midcourse velocity corrections for
lunar missions.
Three FIST-type drogue parachutes would replace the original two called for
in the earth landing system.
The CM camera system was revised to require one for monitoring the crew,
displays, and spacecraft interior; the other for lunar photography and stellar
studies. The latter camera could be used in conjunction with the telescope or
independently at the crew's discretion.
A new communication concept was described in which all voice, telemetry,
television, and ranging information for near-earth and lunar distances would be
transmitted over a unified frequency system.
All references to the lunar landing module and space laboratory module were
dropped. Among other deletions from the previous Statement of Work were:
- Parawing and other earth landing systems instead of parachutes
- The "skip" reentry technique
- HF beacon as recovery aid
- Radar altimeter from CSM communication system
- Crew recreational equipment
- Engineering and Development Test Plan
NASA, Project Apollo
Spacecraft Development Statement of Work (MSC, December 18, 1961, Revised
August 14, 1962), Part 3, Technical Approach, pp. 3, 7, 12, 61, 84, and 88.
Mid-August
The first Apollo boilerplate command module, BP-25, was
delivered to MSC for water recovery and handling tests. Flotation, water
stability, and towing tests were conducted with good results. J. Thomas Markley
of MSC described all spacecraft structural tests thus far as "successful."
Apollo Quarterly Status Report No. 1, p. 41; Astronautical
and Aeronautical Events of 1962, p. 167; Apollo Spacecraft Project
Office, Weekly Activity Report, Period Ending August 18, 1962.
August 16
The second stage (S-IV) of the Saturn C-1 launch vehicle was
successfully static-fired for the first time in a ten-second test at the
Sacramento, Calif., facility by the Douglas Aircraft Company.
Astronautical and Aeronautical Events of 1962, p. 156.
August 17
Carl Sagan, University of California astronomer, warned
scientists at a lunar exploration conference, Blacksburg, Va., of the need for
sterilization of lunar spacecraft and decontamination of Apollo crewmen,
pointing out that Lunik II and Ranger IV probably had deposited terrestrial
microorganisms on the moon. Even more serious, he said, was the possibility that
lunar microorganisms might be brought to earth where they could multiply
explosively.
Washington Post, August 18, 1962.
August 22
Responsibility for the design and manufacture of the reaction
controls for the Apollo command module was shifted from The Marquardt
Corporation to the Rocketdyne Division of NAA, with NASA concurrence.
Oakley, Historical Summary, S&ID Apollo Program, p. 7.
August 22
The length of the Apollo service module was increased from 11
feet 8 inches to 1 2 feet 11 inches to provide space for additional fuel.
Oakley, Historical Summary, S&ID Apollo Program, p. 7.
During the Month
Robert R. Gilruth, Director of MSC, presented details
of the Apollo spacecraft at the Institute of the Aerospace Sciences meeting in
Seattle, Wash. During launch and reentry, the three-man crew would be seated in
adjacent couches; during other phases of flight, the center couch would be
stowed to permit more freedom of movement. The Apollo command module cabin would
have 365 cubic feet of volume, with 22 cubic feet of free area available to the
crew: "The small end of the command module may contain an airlock; when the
lunar excursion module is not attached, the airlock would permit a
pressure-suited crewman to exit to free space without decompressing the cabin.
Crew ingress and egress while on earth will be through a hatch in the side of
the command module."
Astronautical and Aeronautical Events of 1962, p. 167.
During the Month
The first tests incorporating data acquisition in the
Apollo test program were conducted at El Centro, Calif. They consisted of
monitoring data returned by telemetry during a parachute dummy-load test.
Oakley. Historical Summary, S&lD Apollo Program, p. 7.
During the Month
The revised NAA Summary Definitions and Objectives
Document was released. This revision incorporated the lunar orbit rendezvous
concept, without lunar excursion module integration, and a revised master
phasing schedule, reflecting the deletion of the second-stage service module.
The NAA Apollo Mission Requirements and Apollo Requirements Specifications were
also similarly re-oriented and released.
NAA, Apollo Monthly Progress Report, SID 62-300-6, August 31,
1962, p. 24.
During the Month
The establishment of a basic command module (CM)
airlock and docking design criteria were discussed by NAA and NASA
representatives. While NASA preferred a closed-hatch, one-man airlock system,
NAA had based its design on an open-hatch, two-man airlock operation.
Another closed-hatch configuration under consideration would entirely
eliminate the CM airlock. Astronauts transferring to and from the lunar
excursion module would be in a pressurized environment constantly.
Apollo Monthly Progress Report, SID 62-300-6, p. 97.
During the Month
The launch escape thrust-vector-control system was
replaced by a passive system using a "kicker" rocket as directed by NASA at the
June 10-11 design review meeting, The rocket would be mounted at the top of the
launch escape system tower and fired tangentially to impart the necessary
pitchover motion during the initial phase of abort. The main motor thrust was
revised downward from 180, 000 to 155, 000 pounds and aligned 2.8 degrees off
the center line. A downrange abort direction was selected; during abort the
spacecraft and astronauts would rotate in a heels over head movement.
Apollo Monthly Progress Report, SID 62-300-6, p. 4.
During the Month
A preliminary NAA report was completed on a literature
search concerning fire hazards in 100 percent oxygen and oxygen-enriched
atmospheres. This report showed that limited testing would be warranted.
Apollo Monthly Progress Report, SID 62-300-6, p. 12.
During the Month
A final decision was made by NAA to redesign the
command module fuel cell radiator and associated tubing to accommodate a 30-psi
maximum pressure drop. Pratt & Whitney Aircraft Division agreed to redesign
their pump for this level.
Apollo Monthly Progress Report, SID 62-300-6, p. 109.
During the Month
Layouts of a command module (CM) telescope installation
in the unpressurized upper parachute compartment were completed by NAA. The
concept was for the telescope to extend ten inches from the left side of the
spacecraft. The light path would enter the upper bulkhead through the main
display panel to an eyepiece presentation on the commander's side of the
spacecraft. A static seal (one-half-inch-thick window) would be used to prevent
leakage in the pressurized compartment. The installation was suitable for use in
the lunar orbit rendezvous mission and would allow one man in the CM to
accomplish docking with full visual control.
Apollo Monthly Progress Report, SID 62-300-5, pp. 81, 83;
Apollo Monthly Progress Report, SID 62-300-6, pp. 72-73.
During the Month
NAA established design criteria for materials and
processes used in food reconstitution bags. An order was placed for
polypropylene material with a contoured mouthpiece. This material would be
machined and then heat-fused to a thermoplastic bag.
Apollo Monthly Progress Report, SID 62-300-6, p. 56.
During the Month
Preliminary studies were made by NAA to determine
radiation instrument location, feasibility of shadow-shielding, and methods of
determining direction of incidence of radiation. Preliminary requirements were
established for the number and location of detectors and for information
display.
Apollo Monthly Program Report, SID 62-300-6, p. 72.
During the Month
An NAA study indicated that the effects of crew motions
on spacecraft attitude control would be negligible.
Apollo Monthly Progress Report, SID 62-300-6, p. 53.
During the Month
The command module waste management system analysis,
including a new selection valve, revised tubing lengths, odor removal filter,
and three check valves, was completed by NAA for a 5 psia pressure. There was
only a small change in the flow rates through the separate branches as a result
of the change to 5 psia.
Apollo Monthly Progress Report, SID 62-300-6, p. 12.
During the Month
NAA completed attitude orientation studies, including
one on the control of a tumbling command module (CM) following high-altitude
abort above 125,000 feet. The studies indicated that the CM stabilization and
control system would be adequate during the reentry phase with the CM in either
of the two possible trim configurations.
Apollo Monthly Progress Report, SID 62-300-6, p. 5.
During the Month
NAA finished structural requirements for a lunar
excursion module adapter mating the 154-inch diameter service module to the
260-inch diameter S-IVB stage.
Apollo Monthly Progress Report, SID 62-300-6, p. 107.
An interim Apollo flight operation plan
for Fiscal Year 1963, dated August 28, calling for funding of $489.9 million,
was transmitted to NASA Headquarters from MSC. System requirements were under
study to determine the feasibility of cost reduction to avoid schedule slippage.
MSC, Weekly Activity Report for the Office of the Director, Manned Space
Flight, September 2-8, 1962, p. 4.
September 4
Nine industry proposals for the lunar excursion module were
received from The Boeing Company, Douglas Aircraft Company, General Dynamics
Corporation, Grumman Aircraft Engineering Corporation, Ling-Temco-Vought, Inc.,
Lockheed Aircraft Corporation, Martin-Marietta Corporation, Northrop
Corporation, and Republic Aviation Corporation. NASA evaluation began the next
day. Industry presentations would be held on September 13 and 14 at Ellington
Air Force Base, Tex. One-day visits to company sites by evaluation teams would
be made September 17-19. After evaluation of the proposals, NASA planned to
award the contract within six to eight weeks.
Apollo Spacecraft Project Office, MSC, Weekly Activity Report, September 2-8,
1962; Wall Street Journal, September 6, 1962.
September 5
Two three-month studies of an unmanned logistic system to
aid astronauts on a lunar landing mission would be negotiated with three
companies, NASA announced. Under a $150,000 contract, Space Technology
Laboratories, Inc., would look into the feasibility of developing a
general-purpose spacecraft into which varieties of payloads could be fitted.
Under two $75,000 contracts, Northrop Space laboratories and Grumman Aircraft
Engineering Corporation would study the possible cargoes that such a spacecraft
might carry. NASA Centers simultaneously would study lunar logistic:
trajectories, launch vehicle adaptation, lunar landing touchdown dynamics,
scheduling, and use of roving vehicles on the lunar surface.
Wall Street Journal, September 6, 1962; Astronautical and
Aeronautical Events of 1962, pp. 173-174.
September 5
Apollo Spacecraft Project Office requested NAA to perform a
study of command module-lunar excursion module (CM-LEM) docking and crew
transfer operations and recommend a preferred mode, establish docking design
criteria, and define the CM-LEM interface. Both translunar and lunar orbital
docking maneuvers were to be considered. The docking concept finally selected
would satisfy the requirements of minimum weight, design and functional
simplicity, maximum docking reliability, minimum docking time, and maximum
visibility.
The mission constraints to be used for this study were :
- The first docking maneuver would take place as soon after S-IVB burnout as
possible and hard docking would be within 30 minutes after burnout.
- The docking methods to be investigated would include but not be limited to
free fly-around, tethered fly-around, and mechanical repositioning.
- The S-IVB would be stabilized for four hours after injection.
- There would be no CM airlock. Extravehicular access techniques through the
LEM would be evaluated to determine the usefulness of a LEM airlock.
- A crewman would not be stationed in the tunnel during docking unless it
could be shown that his field of vision, maneuverability, and communication
capability would substantially contribute to the ease and reliability of the
docking maneuver.
- An open-hatch, unpressurized CM docking approach would not be considered.
- The relative merit of using the CM environmental control system to provide
initial pressurization of the LEM instead of the LEM environmental control
system would be investigated.
Apollo Spacecraft Project Office, MSC,
Weekly Activity Report, September 2-8, 1962; letter, C. D. Sword, MSC, to NAA,
"Contract Change Authorization No. 4," September 22, 1962.
September 6
NASA deleted five Apollo mockups, three boilerplate
spacecraft, and several ground support equipment items from the NAA contract
because of funding limitations.
Oakley, Historical Summary, S&ID Apollo Program, p. 7.
September 7
Apollo command module boilerplate model BP-1 was accepted by
NASA and delivered to the NAA Engineering Development Laboratory for land and
water impact tests. On September 25, BP-1 was drop-tested with good results.
Earth-impact attenuation and crew shock absorption data were obtained.
Oakley, Historical Summary, S&ID Apollo Program, p. 7;
Apollo Quarterly Status Report No. 1, p. 41.
September 10
Apollo command module boilerplate model BP-3, showing the
arrangement of the cabin interior, was shipped to MSC.
Oakley, Historical Summary, S&ID Apollo Program, p. 7
September 10
Fire broke out in a simulated space cabin at the Air Force
School of Aerospace Medicine, Brooks Air Force Base, Tex., on the 13th day of a
14-day experiment to determine the effects of breathing pure oxygen in a
long-duration space flight. One of the two Air Force officers was seriously
injured. The cause of the fire was not immediately determined. The experiment
was part of a NASA program to validate the use of a 5 psia pure oxygen
atmosphere for the Gemini and Apollo spacecraft.
Washington Evening Star, September 10, 1962; Michel et al.,
Gaseous Environment Considerations and Evaluation Programs Leading to
Spacecraft Atmosphere Selection, pp. 5-6.
Early September
MSC reported that it had received a completed wooden
mockup of the interior arrangement of the Apollo command module (CM). An
identical mockup was retained at NAA for design control. Seven additional CM and
service module (SM) mockups were planned: a partial SM and partial adapter
interface, CM for exterior cabin equipment, complete SM, spacecraft for handling
and transportation (two), crew support system, and complete CSM's. A mockup of
the navigation and guidance equipment had been completed. A wooden mockup of the
lunar excursion module exterior configuration was fabricated by NAA as part of
an early study of spacecraft compatibility requirements.
Apollo Quarterly Status Report No. 1, p. 41.
September 11
J. Thomas Markley, command and service module Project
Officer at MSC, announced details of the space facility to be established by
NASA at White Sands Missile Range (WSMR). To be used in testing the Apollo
spacecraft's propulsion and abort systems, the WSMR site facilities would
include two static-test-firing stands, a control center blockhouse, various
storage and other utility buildings, and an administrative services area.
MSC Fact Sheet No. 97, Apollo at White Sands, September 1 1, 1962.
September 12
President John F. Kennedy spoke at Rice University,
Houston, Tex., where he said:
"Man, in his quest for knowledge and progress, is determined and cannot be
deterred. The exploration of space will go ahead, whether we join in it or not,
and it is one of the great adventures of all time, and no nation which expects
to be the leader of other nations can expect to stay behind in this race for
space. . . .
"We choose to go to the moon in this decade and do the other things, not
because they are easy, but because they are hard, because that goal will serve
to organize and measure the best of our energies and skills, because that
challenge is one that we are willing to accept, one we are unwilling to
postpone, and one which we intend to win, and the others, too.
"It is for these reasons that I regard the decision last year to shift our
efforts in space from low to high gear as among the most important decisions
that will be made during my incumbency in the office of the Presidency. . . ."
Senate Staff Report, Documents on International Aspects of the
Exploration and Use of Outer Space, 1954-1962, pp. 328-330.
September 17
NASA's nine new astronauts were named in Houston, Tex., by
Robert R. Gilruth, MSC Director. Chosen from 253 applicants, the former test
pilots who would join the original seven Mercury astronauts in training for
Projects Gemini and Apollo were: Neil A. Armstrong, NASA civilian test pilot;
Maj. Frank Borman, Air Force; Lt. Charles Conrad, Jr., Navy; Lt.Cdr. James A,
Lovell, Jr., Navy; Capt. James A. McDivitt, Air Force; Elliot M. See, Jr.,
civilian test pilot for the General Electric Company; Capt. Thomas P. Stafford,
Air Force; Capt. Edward H. White II, Air Force; and Lt. Cdr. John W. Young,
Navy.
Washington Daily News, September 18, 1962.
September 21
NASA contracted with the Armour Research Foundation for an
investigation of conditions likely to be found on the lunar surface. Research
would concentrate first on evaluating the effects of landing velocity, size of
the landing area, and shape of the landing object with regard to properties of
the lunar soils. Earlier studies by Armour had indicated that the lunar surface
might be composed of very strong material. Amour reported its findings during
the first week of November.
Astronautical and Aeronautical Events of 1962, p. 196.
September 23-October 6
Deletion of non-critical equipment and
improvement of existing systems reduced the weight of the command and service
modules by 1,239 pounds, with a target reduction of 1,500 pounds.
Among the items deleted from the command module (CM) were exercise and
recreation equipment, personal parachutes and parachute containers located in
the couches, individual survival kits, solar radiation garments, and eight-ball
displays. A telescope, cameras and magazines considered scientific equipment,
and a television monitor were deleted from the CM instrumentation system.
Apollo Spacecraft Project Office, MSC, Activity Report for the Period
September 23-October 6, 1962.
September 24
General Dynamics/Convair recommended and obtained NASA's
concurrence that the first Little Joe II launch vehicle be used for
qualification, employing a dummy payload.
Little Joe II Test Launch Vehicle, NASA Project Apollo: Final
Report, Vol. I, p. 1-4.
September 26
NASA announced that it had completed preliminary plans for
the development of the $500-million Mississippi Test Facility. The first phase
of a three-phase construction program would begin in 1962 and would include four
test stands for static-firing the Saturn C-5 S-IC and S-II stages; about 20
support and service buildings would be built in the first phase. A water
transportation system had been selected, calling for improvement of about 15
miles of river channel and construction of about 15 miles of canals at the
facility. Sverdrup and Parcel Company of St. Louis, Mo., was preparing design
criteria; the Army Corps of Engineers was acquiring land for NASA in cooperation
with the Lands Division of the Justice Department. The 13,500-acre facility in
southwestern Mississippi was 35 miles from NASA Michoud Operations, where Saturn
stages were fabricated.
Astronautical and Aeronautical Events of 1962, pp. 200-201.
During the Month
MSC reported that the reliability goal for design
purposes in the spacecraft Statement of Work for the Apollo mission was 0.9. The
probability that the crew would not be subjected to conditions in excess of the
stated limits was 0.9, and the probability that the crew would not be subjected
to emergency limits was 0.999. The initial Work Statement apportionment for the
lunar excursion module was 0.984 for mission success and 0.9995 for crew safety.
Other major system elements would require reapportionment to reflect the lunar
orbit mission.
Apollo Quarterly Status Report No. 1, p. 37.
During the Month
Release of the structural design of the Apollo command
module was 65 percent complete; 100 percent release was scheduled for January 1
963.
Apollo Quarterly Status Report No. 1, p. 11.
During the Month
The lunar excursion module was defined as consisting of
12 principal systems: guidance and navigation, stabilization and control,
propulsion, reaction control, lunar touchdown, structure including landing and
docking systems, crew, environmental control, electrical power, communications,
instrumentation, and experimental instrumentation. A consideration of prime
importance to practically all systems was the possibility of using components
from Project Mercury or those under development for Project Gemini.
Apollo Quarterly Status Report No. 1, p. 26.
During the Month
MSC reported that renovation of available buildings at
the El Centro Joint Service Parachute Facility was required to support the
Apollo earth recovery tests. The Air Force's commitment of a C-133A aircraft to
support the qualification tests had been obtained.
Apollo Quarterly Status Report No. 1, p. 52.
During the Month
MSC reported that Arnold Engineering Development Center
facilities at Tullahoma, Tenn., were being scheduled for use in the development
of the Apollo reaction control and propulsion systems. The use of the Mark I
altitude chamber for environmental tests of the command and service modules was
also planned.
Apollo Quarterly Status Report No. 1, p. 52.
During the Month
MIT's Lincoln Laboratory began a study program to
define Apollo data processing requirements and to examine the problems
associated with the unified telecommunications system. The system would permit
the use of the lunar mission transponder during near-earth operations and
eliminate the general transmitters required by the current spacecraft concept,
thus reducing weight, complexity, and cost of the spacecraft system.
Apollo Quarterly Status Report No. 1, p. 47.
During the Month
MSC reported that Apollo training requirements planning
was 40 percent complete. The preparation of specific materials would begin
during the first quarter of 1964. The crew training equipment included earth
launch and reentry, orbital and rendezvous, and navigation and trajectory
control part-task trainers, which were special-purpose simulators. An early
delivery would allow extensive practice for the crew in those mission functions
where crew activity was time-critical and required development of particular
skills. The mission simulators had complete mission capability, providing visual
as well as instrument environments. Mission simulators would be located at MSC
and at Cape Canaveral.
Apollo Quarterly Status Report No. 1, p. 45.
During the Month
The Apollo wind tunnel program was in its eighth month.
To date, 2,800 hours of time had been used in 30 government and private
facilities.
Apollo Quarterly Status Report No. 1, p. 35.
During the Month
The external natural environment of the Apollo
spacecraft as defined in the December 18, 1961, Statement of Work had been used
in the early Apollo design work. The micrometeoroid, solar proton radiation, and
lunar surface characteristics were found to be most critical to the spacecraft
design.
Apollo Quarterly Status Report No. 1, p. 32.
During the Month
The freeze-dried food that would be used in the Gemini
program would also be provided for the Apollo program. Forty-two pounds of food
would be necessary for a 14-day lunar landing mission. Potable water would be
supplied by the fuel cells and processed by the environmental control system. A
one-day water supply of six pounds per man would be provided at launch as an
emergency ration if needed before the fuel cells were fully operative.
Apollo Quarterly Status Report No. 1, p. 1 3.
During the Month
The Apollo spacecraft weights had been apportioned
within an assumed 90,000pound limit. This weight was termed a "design
allowable." A lower target weight for each module had been assigned. Achievement
of the target weight would allow for increased fuel loading and therefore
greater operational flexibility and mission reliability. The design allowable
for the command module was 9,500 pounds; the target weight was 8,500 pounds. The
service module design allowable was 11,500 pounds; the target weight was 11,000
pounds. The S-IVB adapter design allowable and target weight was 3,200 pounds.
The amount of service module useful propellant was 40,300 pounds design
allowable; the target weight was 37,120 pounds. The lunar excursion module
design allowable was 25,500 pounds; the target weight was 24,500 pounds.
Apollo Quarterly Status Report No. 1, p. 31.
During the Month
MSC reported that the lunar excursion module guidance
system was expected to use as many components as possible identical to those in
the command and service modules. Studies at the MIT Instrumentation Laboratory
indicated that the changes required would simplify the computer and continue the
use of the same inertial measurement unit and scanning telescope.
Apollo Quarterly Status Report No. 1, p. 27.
During the Month
MSC reported that the three
liquid-hydrogen-liquid-oxygen fuel cells would supply the main and emergency
power through the Apollo mission except for the earth reentry phase. Two of the
fuel cells would carry normal electrical loads and one would supply emergency
power. Performance predictions had been met and exceeded in single-cell tests.
Complete module tests would begin during the next quarter. The liquid-hydrogen
liquid-oxygen reactants for the fuel cell power supply were stored in the
supercritical state in spherical pressure vessels. A recent decision had been
made to provide heat input to the storage vessels with electrical heaters rather
than the water-glycol loop. Three zinc-silver oxide batteries would supply power
for all the electrical loads during reentry and during the brief periods of peak
loads. One of the batteries was reserved exclusively for the postlanding phase.
Eagle Picher Company, Joplin, Mo., had been selected in August as subcontractor
for the batteries.
Apollo Quarterly Status Report No. 1, p. 23.
During the Month
MSC reported that meteoroid tests and ballistic ranges
had been established at the Ames Research Center, Langley Research Center, and
NAA. These facilities could achieve only about one half of the expected velocity
of 75,000 feet per second for the critical-sized meteoroid. A measured
improvement in the capability to predict penetration would come from a test
program being negotiated by NAA with General Motors Corporation, whose facility
was capable of achieving particle velocities of 75,000 feet per second.
Apollo Quarterly Status Report No. 1, p. 32.
During the Month
MSC outlined a tentative Apollo flight plan:
- Pad abort:
- Two tests to simulate an abort on the pad. The purpose of these tests was
to qualify the launch escape system and its associated sequencing.
- Suborbital (Little Joe II test launch vehicle):
- Three suborbital tests with the objective of development and qualification
of the launch escape system and qualification of the command module structure.
Test conditions would include maximum dynamic pressure for the launch escape
system and module structure testing and high atmospheric altitudes for launch
escape system testing. The latter test requirement was being reviewed.
- Saturn C-1:
- Current Apollo requirements for the Saturn developmental flights were to
determine launch exit environment on SA-6 with SA-8 as backup. Requirements on
launch vehicles SA-7, SA-9, and SA-10 were to flight- test components of or
the complete emergency detection system.
- Saturn C-1B:
- Four launch vehicle development flights prior to the manned flight. Flight
test objectives for the unmanned flights were one launch environment flight
with a spare and two launch vehicle emergency detection system flights.
- Saturn C-5:
- Six unmanned Saturn C-5 launch vehicle development flights. Flight test
objectives were two launch vehicle emergency detection system flights, one
spacecraft launch environment flight, and three reentry qualification flights.
Preliminary objectives of manned flights were completion of the lunar
excursion module qualification, lunar reconnaissance, and lunar exploration.
Although the first C-5 manned flight was scheduled as the seventh C-5, a
spacecraft suitable for manned flight would be available for use on the sixth
C-5 to take advantage of possible earlier development
success.
Apollo Quarterly Status Report No. 1, p. 48.