Advanced Design, Fabrication, and Testing
February 1965
1965
February 1
Pacific Crane and Rigging Company received a NASA contract,
worth $8.3 million, to install ground equipment at Kennedy Space Center's Saturn
V facility, Launch Complex 39. On the following day, the Army Corps of Engineers
awarded a $2,179,000 contract to R. E. Carlson Corporation, St. Petersburg,
Fla., to modify Launch Complex 34 to handle the Saturn IB.
Astronautics and Aeronautics, 1965, pp. 48, 52.
February 2-3
The Apollo-Saturn Crew Safety Panel decided on a number of
emergency detection system (EDS) and abort procedures for the early Apollo
flights:
- If any of the three redundant automatic abort circuits so indicated, the
launch vehicle would not be released.
- The EDS would be flight-tested on the SA-201 and SA-202 missions.
- Unmanned Apollo flights should be aborted from the ground only under the
most severe conditions.
- Liftoff permitted automatic abort without manual backup.
- To ensure a successful abort, a redundant mode of EDS-commanded engine
shutdown was mandatory.
After hearing the results of several supporting
studies, the Panel further agreed that Saturn IB flights would be automatically
aborted if the vehicle's roll rate reached 20 degrees per second; if two engines
should fail during the first 30 seconds of flight, the Saturn IB must be capable
of aborting automatically, and the Saturn V must have the same capability for
the first 60 seconds of flight; and, finally, the Panel stated that during the
Saturn V's initial stages, automatic abort might be required if even one engine
shut down.
"Summary of Proceedings, Apollo-Saturn Crew Safety Panel Meeting No. 11, 2-3
February, 1965," February 4, 1965.
February 3
ASPO established radiation reliability goals for Apollo.
These figures would be used to coordinate the radiation program, to define the
allowable dosages, and to determine the effect of radiation on mission success.
The crew safety goal (defined as the probability of a crewman's not suffering
permanent injury or worse, nor his being incapacitated and thus no longer able
to perform his duties) was set at 0.99999. The major hazard of a radiation
environment, it was felt, was not the chance of fatal doses. It was, rather, the
possibility of acute radiation sickness during the mission. The second
reliability goal, that for success of the mission (the probability that the
mission would not be aborted because of radiation environment), was placed at
0.98.
These values, ASPO Manager Joseph F. Shea emphasized, were based on the
8.3-day reference mission and on emergency dose limits previously set forth.
They were not to be included in overall reliability goals for the spacecraft,
nor were they to be met by weight increases or equipment relocations.
Memorandum, Joseph F. Shea, MSC, to Assistant Director for E. and D., "Apollo
Radiation Reliability Goals," February 3, 1965.
February 4
A device to maintain the spacecraft in a constant attitude
was added to the LEM's primary attitude control system (ACS). The feature
brought with it some undesirable handling characteristics, however: it would
cause the vehicle to land long. Although this overshoot could be corrected by
the pilot, and therefore was not dangerous operationally, it would require
closer attention during final approach. The attitude hold, therefore, hardly
eased the pilot's control task, which was, after all, its primary function.
Instead of moving the device to the backup ACS (the abort section), the
Engineering Simulation Branch of MSC's Guidance and Control Division recommended
that the system be modified so that, if desired, the pilot could disengage the
hold mechanism.
Memorandum, Clarke T. Hackler, MSC, to Chief, Guidance and Control Division,
"Evaluation of LEM modified (zero overshoot) rate command-attitude hold control
mode," February 4, 1965.
February 4-11
After considering possible impacts, MSC directed North
American to implement real-time commands to the up-data link equipment on
command modules 012 and 014.
MSC, "ASPO Weekly Management Report, February 4-ll, 1965."
February 4-11
MSC questioned the necessity of using highly purified (and
expensive) fuel-cell-type oxygen to maintain the cabin atmosphere during manned
ground testing of the spacecraft. The Center, therefore, undertook a study of
the resultant impurities and effect on crew habitability of using a commercial
grade of aviation oxygen.
Ibid.; memorandum, Robert E. Smylie, MSC, to Chief,
Environmental Physiology Branch, "Breathing oxygen for Apollo Command Module
ground testing in Airframe 008," March 15, 1965.
February 5
SM 001's service propulsion engine was static-fired for 10
sec at White Sands. The firing was the first in a program to verify the mission
profiles for later flight tests of the module. (SM 001 was the first major piece
of flight-weight Apollo hardware.)
MSC News Release 65-18, February 5, 1965; TWX, M. L. Raines, WSMR, to NASA
Headquarters, MSC, MSFC, and ASPO Field Test Office, Cape Kennedy, Fla.,
"Airframe 001 First Firing," February 6, 1965.
February 8
MSC deleted the requirement for a rendezvous radar in the
CSM.
MSC, "Minutes, Configuration Control Board Meeting No. 5," February 8, 1965.
February 8
MSC, North American, and Grumman reviewed the results of
Langley Research Center's LEM-active docking simulation. While the overhead mode
of docking had been found to be acceptable, two items still caused some concern:
(1) propellant consumption could exceed supply; and (2) angular rates at contact
had occasionally exceeded specifications. Phase B (Grumman's portion) of the
docking simulations, scheduled to begin in about two weeks, would further
investigate these problems. Langley researchers also had evaluated several
sighting aids for the LEM and recommended a projected image collimated (parallel
in lines of direction) reticle as most practicable. Accordingly, on March 9, MSC
directed Grumman to incorporate this type of sighting device into the design of
their spacecraft.
Letter, W. F. Rector III, MSC, to GAEC, Attn: R. S. Mullaney, "Contract NAS
9-1100, Results of LEM active docking simulation at Langley Research Center,"
March 9, 1965.
February 8
Development tests recently completed by AiResearch on the
water evaporator control system for the space suit heat exchanger disclosed its
inadequacy because of its slow response time. To solve this problem, AiResearch
and North American proposed an alternate control system approach similar to the
glycol evaporator scheme used elsewhere in the environmental control system.
This alternate design, which was tested and appeared a more desirable approach,
would be incorporated on airframes 008 and 012 through Block II spacecraft. No
schedule impact was anticipated.
"ASPO Weekly Management Report, February 4-11, 1965"; memorandum, Frank E.
Samonski, Jr., MSC, to Chief, Test Division, "A14-033 requirements for Airframe
008 testing," February 8, 1965.
February 8
NASA invited 113 scientists and 23 national space
organizations to a conference at MSC to brief them on the Gemini and Apollo
missions. As a result of the conference, NASA hoped to receive proposals for
biomedical experiments to be performed in Gemini and Apollo spacecraft.
MSC News Release 65-21, "Foreign Scientists Invited to Conference on Apollo
Experiments," February 8, 1965.
February 9
North American completed the first ground test model of the
S-II stage of the Saturn V.
Space Business Daily, February 9, 1965, p. 195.
February 10
ASPO and the MSC Instrumentation and Electronic Systems
Division (IESD) formulated a program for electromagnetic compatibility testing
of hardware aboard the CSM and LEM. The equipment would be mounted in spacecraft
mockups, which would then be placed in the Center's anechoic chamber. In these
tests, scheduled to begin about the first of September, IESD was to evaluate the
compatibility of the spacecraft in docked and near-docked configurations, and of
Block I spacecraft with the launch vehicle. The division was also to recommend
testing procedures for the launch complex.
Memorandum, R. S. Sawyer, MSC, to Chief, Systems Engineering Division, "Test
Philosophy for CSM/ LEM Electromagnetic Compatibility Test to be performed in
the Anechoic Chamber Test Facility at MSC," February 10, 1965.
February 10
ASPO evaluated Grumman's proposal for an "all battery"
system for the LEM descent stage. ASPO was aiming at a 35-hour lunar stay for
the least weight; savings were realized by lessening battery capacities, by
making the water tanks smaller, and by reducing some of the spacecraft's
structural requirements.
Letter, Thomas J. Kelly, GAEC, to MSC, Attn: W. F. Rector III, "Submittal of
Additional Information Relative to the Lem 'All-Battery' Study," February 10,
1965, with enclosures.
February 11
A drop test at EI Centro, Calif., demonstrated the ability
of the drogue parachutes to sustain the ultimate disreefed load that would be
imposed upon them during reentry. (For the current CM weight, that maximum load
would be 7,711 kg [17,000 lbs] per parachute.) Preliminary data indicated that
the two drogues had withstood loads of 8,803 and 8,165 kg (19,600 and 18,000
lbs). One of the drogues emerged unscathed; the other suffered only minor damage
near the pocket of the reefing cutter.
"Apollo Monthly Progress Report," SID 62-300-35, pp. 3-4; MSC, "ASPO Weekly
Management Report, February 11-18, 1965."
February 11-18
MSC modified its bubble helmet design to fit on an
International Latex "state-of-the-art" space suit. A mockup of the helmet was
used in don doff tests. Mean donning time was 4.2 sec; doff time averaged 1.47
sec. Further tests would be performed when a prototype helmet was completed
(expected by February 26).
"ASPO Weekly Management Report, February 11-18, 1965."
February 11-18
Hamilton Standard, the extravehicular mobility unit
contractor, completed a two-week wearing test of the Apollo liquid-cooled
undergarment. Investigators found that the garment could be worn for the entire
lunar mission without any serious discomfort.
Ibid.
February 11-18
To make room for a rendezvous study, MSC was forced to
end, prematurely, its simulations of employing the LEM as a backup for the
service propulsion system. Nonetheless, the LEM was evaluated in both manual and
automatic operation. Although some sizable attitude changes were required,
investigators found no serious problems with either steering accuracy or dynamic
stability.
Ibid.
February 11-18
North American selected the Ordnance Division of General
Precision Link Group to supply the panel thrusters for the spacecraft lunar
adapter.
Ibid.
February 11-18
Evaluations of the three-foot probes on the LEM landing
gear showed that the task of shutting off the engine prior to actual touchdown
was even more difficult than controlling the vehicle's rate of descent. During
simulated landings, about 70 percent of the time the spacecraft was less than
0.3 m (1 ft) high when shutdown came; on 20 percent of the runs, the engine was
still burning at touchdown. Some change, either in switch location or in
procedure, thus appeared necessary to shorten the delay between contact light
and engine cutoff (an average of 0.7 sec).
Ibid.
February 12
MSC relayed to NASA Headquarters North American's cost
estimates for airlocks on the Apollo CM:
| Spacecraft |
Development |
Unit Cost |
| Block I |
$840,000 |
$185,000 |
| Block II |
$960,000 |
$112,000 |
| Blocks I & II |
$1,050,000 |
$111,000 |
(The unit costs presumed two flight items
for Block I and 12 for Block II spacecraft.)
During late February and early March, North American completed a conceptual
design study of an airlock for the Block I CMs. Designers found that such a
device could be incorporated into the side access hatch. A substitute cover for
the inner hatch and a panel to replace the window on the outer hatch would have
to be developed, but these modifications would not interfere with the basic
design of the spacecraft.
TWX, Joseph F. Shea, MSC, to NASA Headquarters, Attn: Samuel C. Phillips,
February 12, 1965; "Apollo Monthly Progress Report," SID 62-300-35, pp. 17-18.
February 12
MSC's Systems Engineering Division (SED) requested support
from the Structures and Mechanics Division in determining the existence or
extent of corrosion in the coolant loops of the SM electrical power subsystem
(EPS) and the CM and LEM environmental control subsystems (ECS), resulting from
the use of water glycol as coolant fluid. Informal contact had been made with W.
R. Downs of the Structures and Mechanics Division and he had been given copies
of contractor reports and correspondence between MSC, North American, and MIT
pertaining to the problem. The contractors had conflicting positions regarding
the extent and seriousness of glycol corrosion.
SED requested that a study be initiated to:
- determine the existence or extent of corrosion in the EPS and ECS coolant
loops; and
- make recommendations regarding alternate materials, inhibitors, or fluids,
and other tests or remedial actions if it were determined that a problem
existed.
Memorandum, Owen E. Maynard, MSC, to Chief, Structures and
Mechanics Division, "Water/glycol Corrosion," signed Harry W. Byington, February
12, 1965.
February 15
A study by General Electric affirmed the necessity for the
steerable S-band antenna for communications between the spacecraft and the
ground at lunar distances. Communications margins were so small that, at those
distances, any degradation of equipment would seriously affect the spacecraft's
contact with earth.
Letter, E. J. Merrick, GE, to William A. Lee, "S-Band Communications
Requirements Study," February 15, 1965, with enclosure: "CSM-LEM Directional
Communications Antenna Relationship to Communications Margins and Mission
Requirements."
February 16
Crew Systems Division (CSD) informed the Astronaut Office
that the requirements submitted by Astronaut Michael Collins on February 5 had
been included in the Block II suit program plans. Those requirements for
astronaut training suits were:
| Suit Quantity |
Type |
Date Available |
| 1 |
A-5H |
June 1965 |
| 6 |
A-5H |
December 1965 (or sooner if possible) |
| 6 |
A-6H1 |
March 1966 |
| 14 |
A-6H2 |
August 1966 |
CSD requested the Astronaut Office to
provide the type and schedule of training programs in which suit use was
anticipated, stating: "This information will be of value in assessing suit
support requirements and the type of suit interface information to be gained
from astronaut participation in these programs."
Memorandum, Richard S. Johnston, MSC, to Assistant Director for Flight Crew
Operations, Attn: D. K. Slayton, "Apollo Block II training suits," signed E. L.
Hays, February 16, 1965.
February 16
In the first of a series of manufacturing review meetings at
Bethpage, N.Y., it was learned that Grumman's tooling program was behind
schedule (caused primarily by engineering changes). Tool manufacturing might
recoup much of the lost time, but this process was highly vulnerable to further
design changes. Completion of tooling for the ascent stage of LTA-3 was now set
for late April, a production delay of about two months.
Letter, W. F. Rector III, MSC, to GAEC, Attn: R. S. Mullaney, "LEM
Manufacture Review Meetings Minutes," March 3, 1965, with enclosure: "Minutes,
LEM Manufacturing Review Meeting, February 16, 1965."
February 16
In a memorandum to ASPO, Samuel C. Phillips, Apollo Program
Director, inquired about realigning the schedules of contractors to meet revised
delivery and launch timetables for Apollo. Phillips tentatively set forth
deliveries of six spacecraft (CSM/LEMs) during 1967 and eight during each
succeeding year; he outlined eight manned launches per year also, starting in
1969.
Memorandum, Samuel C. Phillips, NASA, to MSFC, MSC, and KSC, Attn: Directors,
"Apollo Delivery and Launch Schedules," February 16, 1965, with enclosures.
February 16
A Saturn I vehicle SA-9 launched a multiple payload into a
high 744 by 496 km (462 by 308 mi) earth orbit. The rocket carried a boilerplate
(BP) CSM (BP-16) and, fitted inside the SM, the Pegasus I meteoroid
detection satellite. This was the eighth successful Saturn flight in a row, and
the first to carry an active payload. BP-16's launch escape tower was jettisoned
following second-stage S-IV ignition. After attaining orbit, the spacecraft were
separated from the S-IV. Thereupon the Pegasus I's panels were
deployed and were ready to perform their task, i.e., registering meteoroid
impact and relaying the information to the ground.
NASA News Release 65-38, "Saturn I to Launch Pegasus Meteoroid," February 15,
1965; TWX, E. R. Mathews, KSC, to NASA Headquarters, MSFC, MSC, and MSFC
Resident Manager, Sacramento, California, subject: "CLN SA-9 Apollo Flash Report
No. 2," February 18, 1965; Astronautics and Aeronautics, 1965, pp.
71-72.
February 16
NASA awarded an $8,879,832 fixed-price contract to the
Univac Division of Sperry Rand Corporation for digital data processors for the
Apollo project. Univac also would assist in modifying extant computer programs
to meet Apollo requirements.
NASA News Release 65-50, "NASA Buys Univac Data Processing for Moon Project,"
February 16, 1965.
February 16
MSC announced a realignment of specialty areas for the 13
astronauts not assigned to forthcoming Gemini missions (GT 3 through 5) or to
strictly administrative positions:
- Operations and Training
- Edwin E. Aldrin, branch chief - mission planning
Charles A. Bassett - operations handbooks, training, and simulators
Alan L. Bean - recovery systems
Michael Collins - pressure suits and extravehicular activity
David R. Scott - mission planning and guidance and navigation
Clifton C. Williams - range operations, deep space instrumentation, and
crew safety.
- Project Apollo
- Richard F. Gordon, branch chief - overall astronaut activities in Apollo
area and liaison for CSM development
Donn F. Eisele - CSM and LEM
William A. Anders - environmental control system and radiation and thermal
systems
Eugene A. Cernan - boosters, spacecraft propulsion, and the Agena stage
Roger B. Chaffee - communications, flight controls, and docking
R. Walter Cunningham - electrical and sequential systems and non-flight
experiments
Russell L. Schweickart - in-flight experiments and future
programs.
MSC News Release 65-27, February 16, 1965.
February 16-March 15
The CM's waste management system demonstrated its
feasibility under zero-g conditions during flights from Wright-Patterson Air
Force Base. The system successfully contained both solid and liquid wastes and
did not leak even when filled to capacity.
"Apollo Monthly Progress Report," SID 62-300-35, p. 7.
February 17
The U.S. Navy Air Crew Equipment Laboratory began testing
the Gemini Block I Apollo space suit in a wide range of environmental
temperatures to determine the comfort and physiological responses of the wearer.
The program, delayed because of difficulties with humidity control, was to be
completed in three to four weeks.
"ASPO Weekly Management Report, February 11-18, 1965."
February 17
Ranger VIII, a lunar probe carrying six
television cameras, was launched from Cape Kennedy by an Atlas- Agena B vehicle.
The spacecraft's trajectory was nearly perfect; only minor midcourse corrections
were required to place the craft squarely in the target area, in the Sea of
Tranquillity.
Cameras in Ranger VIII were turned on 23 minutes before impact,
and the spacecraft transmitted pictures back to earth until it struck the
surface and was destroyed. The flight's product would be intensively studied by
a panel of noted lunar scientists, among them Gerard P. Kuiper and Ewen A.
Whitaker of the University of Arizona and Harold C. Urey of the University of
California.
Astronautics and Aeronautics, 1965, pp. 73-74, 84-85.
February 17
MSC directed North American to delete the rendezvous radar
from Block II CSMs. On those spacecraft North American instead would install LEM
rendezvous radar transponders. Grumman, in turn, was ordered to halt its work on
the CSM rendezvous radar (both in-house and at RCA) as well as all support
efforts. At the same time, however, the company was directed to incorporate a
tracking light on the LEM (compatible with the CSM telescope sextant) and to
modify the spacecraft's VHF equipment to permit range extraction in the CSM.
(See February 8 and March 15.)
Letter, H. P. Yschek, MSC, to NAA, Space and Information Systems Div.,
"Contract NAS 9-150, CCA to Cover Removal of Rendezvous Radar Installation on
CSM (MSN 150-508)," February 16, 1965; letter, Yschek, to NAA, S&ID,
"Contract Change Authorization No. 303," February 17, 1965; letter, J. B.
Alldredge, MSC, to NAA, S&ID, "Contract Change Authorization No. 303,
Revision 1," March 11, 1965; letter, W. F. Rector III, MSC, to GAEC, Attn: R. S.
Mullaney, "Contract NAS 9-1100, Item 3, Contractor Responsibilities, Rendezvous
Radar and Transponder," March 8, 1965, with enclosure.
February 17
North American proposed an idea for increasing the CM's land
landing capability. This could be done, the company asserted, by raising the
water impact limits (thus exceeding normal tolerances) and stiffening the shock
struts. Presently, the spacecraft was incapable of a land landing within
established requirements (i.e., in a 46-km [25-nm] wind). While even approximate
figures were not available, the maximum wind velocity in which the CM could land
- without exceeding crew tolerances - was probably between 19 and 28 km (10 and
15 nm) per hr. (No precise data on land and water landings would be available
until after the drop tests of boilerplate 28 late in the year.)
Personnel of the ASPO Crew Integration Branch, however, were pessimistic
about the North American scheme. They doubted that shock attenuation could be
readily increased, nor did they see as likely any relaxation of crew tolerances.
Further, the probability of a land landing introduced tighter constraints on
wind conditions at the launch site. As they viewed it, the only feasible way to
improve the spacecraft's ground capability was through some mechanism that would
further absorb the landing impact.
Memorandum, Joseph P. Loftus, Jr., MSC, to Chief, Systems Engineering
Division, "Command Module land impact capability," February 17, 1965.
February 17
ASPO Manager Joseph F. Shea clarified the manned unmanned
capabilities required of Block I CSM spacecraft to ensure that end-item
specifications appropriately reflect those capabilities.
CSMs 017 and 020 would fly unmanned entry tests on the Saturn V and need not
be capable of manned missions. CSMs 012 and 014 were to be delivered to KSC for
manned orbital missions on the Saturn IB but must be capable of being modified
to fly unmanned missions.
The planning for CSM 012 should be such that the mission type could be
selected 5½ months prior to the scheduled launch of the 204 mission, yet not
delay the launch.
Memorandum, Shea, MSC, to Chief, Systems Engineering Division, "Block I CSM
Mission Capabilities," February 17, 1965.
February 18
LEM Test Article 2 was shipped to Marshall Space Flight
Center to undergo a series of Saturn booster vibration tests.
"Monthly Progress Report No. 25," LPR-10-41, March 10, 1965, p. 1.
February 18
MSC's Crew Systems Division decreed that the extravehicular
mobility unit (EMU) would employ a single garment for both thermal and meteoroid
protection. By an earlier decision, the penetration probability requirement had
been lowered from 0.9999 to 0.999. This change, along with the use of newer,
more efficient materials, promised a substantial lightening of the garment
(hopefully down to about 7.7 kg [17 lbs], excluding visors, gloves, and boots).
The division also deleted the requirement for a separate meteoroid visor,
because the thermal and glare visors provided ample protection against
meteoroids as well. Tests by Ling-Temco-Vought confirmed the need for thermal
protection over the pressure suit during extravehicular transfer by the LEM
crewmen.
Memorandum, Robert E. Smylie, MSC, to Chief, Systems Engineering Division,
"Extravehicular Mobility Unit (EMU) thermal anti meteoroid protection," February
18, 1965.
February 18-25
Because of the CM's recent weight growth, the launch
escape system (LES) was incapable of lifting the spacecraft the "specification"
distance away from the booster. The performance required of the LES was being
studied further; investigators were especially concerned with the heat and blast
effects of an exploding booster, and possible deleterious effects upon the
parachutes.
MSC, "ASPO Weekly Management Report, February 18-25, 1965."
February 19
NASA selected Philco's Aeronutronic Division to design a
penetrometer for possible use in the Apollo program. Impacting on the moon, the
device would measure the firmness and bearing strength of the surface. Used in
conjunction with an orbiting spacecraft, the system could provide scientific
information about areas of the moon that were inaccessible by any other means.
Langley Research Center would negotiate and manage the contract, estimated to be
worth $1 million.
NASA News Release 65-59, "NASA to Negotiate With Philco for Study of Moon
Penetrometer," February 19, 1965; Astronautics and Aeronautics,
1965, p. 82.
February 19
To eliminate interference between the S-IVB stage and the
instrument unit, MSC directed North American to modify the deployment angle of
the adapter panels. Originally designed to rotate 170 degrees, the panels should
open but 45 degrees (60 degrees during abort), where they were to be secured
while the CSM docked with and extracted the LEM.
But at this smaller angle, the panels now blocked the CM's four flush-
mounted omnidirectional antennas, used during near-earth phases of the mission.
While turning around and docking, the astronauts thus had to communicate with
the ground via the steerable high gain antenna. For Block II spacecraft,
therefore, MSC concurrently ordered North American to broaden the S-band
equipment's capability to permit it to operate within 4,630 km (2,500 nm) of
earth.
Letter, H. P. Yschek, MSC, to NAA, Space and Information Systems Division,
"Contract Change Authorization No. 304," February 19, 1965; letter, Yschek to
NAA, S&ID, "Contract Change Authorization No. 305," February 19, 1965.
February 23
NASA awarded a fixed-price contract (worth l.5 million) to
IBM to design a backup guidance and navigation computer for the Apollo CM.
MSC, "Quarterly Activity Report for the Office of the Associate
Administrator, Manned Space Flight, for the Period Ending April 30, 1965," p.
24.
February 23
William F. Rector III, MSC's LEM Project Officer, reported
at an ASPO Manager's Staff Meeting that the expected firing date for the
heavyweight ascent (HA) rig #3 at WSTF had been slipped from March 18, 1965,
until April 13. Grumman personnel at White Sands said the slip was necessary
because
- a propellant loading control assembly to be mounted on the rig could not
be used in the planned location because it was not accessible for checkout and
would require two weeks for refabrication of certain pipelines and further
checkout;
- checkout of various wiring between the HA-3 rig and the facilities did not
occur on schedule and two weeks would be required to complete the task; and
- adequate interfacing between the fluid and gaseous ground support
equipment (GSE) and various facility pipes was not maintained with many pieces
of GSE putting out higher pressure than the facility pipes design
allowed.
Memorandum, Rector to Distr., "First Firing of HA-3," February
23, 1965.
February 23-26
MSC and North American conducted Part 2 of the mockup
review of the CM's forward compartment and lower equipment bay. (Part 1 was
accomplished January 14-15. This staged procedure was in line with the
contractor's proposal for a progressive review program leading up to the
Critical Design Review scheduled for July 19-23.) Except for minor changes, the
design was acceptable.
"Apollo Monthly Progress Report," SID 62-300-33, p. 24; MSC, "ASPO Weekly
Management Report, February 25-March 4, 1965."
February 24
NASA awarded a $2,740,000 fixed-price contract to the
Collins Radio Company for S-band telemetry equipment. Collins would install the
equipment at three antenna facilities that supported Apollo lunar missions (at
Goldstone, Calif.; Canberra, Australia; and Madrid, Spain).
NASA News Release 65-63, "Collins to Make S-Band Systems for Three 85-Foot
Apollo Antennas," February 24, 1965; Space Business Daily, February
26, 1965, p. 286.
February 24
MSC's Procurement and Contracts Division notified ASPO that
John B. Alldredge had been assigned as the Contracting Officer for Contract NAS
9-150 (the North American contract), replacing Henry P. Yschek.
Memorandum, C. L. Taylor, MSC, to Distr., "Notification of new Contracting
Officer for C&SM Contract NAS 9-150," sgd. W. R. Kelly, February 24, 1965.
February 25
MSC and the David Clark Company reached an agreement on a
contract for Apollo Block I space suits. The first suits, expected by July 1,
would go to North American for testing.
Memorandum, Matthew I. Radnofsky, MSC, to Gemini and Flight Support
Procurement, Attn: Arc F. Lee, "Contract NAS 9-3642, Apollo Block I Suit, David
Clark Company," February 25, 1965.
February 25
KSC supplemented Chrysler Corporation's contract for support
services for the Saturn I and IB launch programs. Effective through June 30,
1968, the agreement would cost NASA $41 million plus an award fee.
Astronautics and Aeronautics, 1965, p. 94.
February 25
Using a mockup Apollo CM, MSC Crew Systems Division tested
the time in which an astronaut could don and doff the Block I pressure garment
assembly while at various stations inside the spacecraft. The two subjects'
average donning times were nine min 33 sec and 10 min; mean doffing times were
four min five sec and five min 23 sec.
MSC, "ASPO Weekly Management Report, February 25-March 4, 1965."
February 25-March 4
To determine thermal and vacuum effects on the CM's
parachutes, MSC Structures and Mechanics Division tested nylon samples in a
vacuum under varying temperature conditions. After two weeks of exposure to this
spacelike environment, the samples exhibited only a 16 percent loss of strength
(as against a design allowable of 25 percent).
Ibid.
February 25-March 4
DeHavilland completed deployment tests of the CM's
pop-up recovery antenna.
Ibid.
February 25-March 4
On the basis of in-house tests, Grumman recommended
a scheme for exterior lighting on the LEM. The design copied standard
aeronautical practice (i.e., red, port; green, starboard; and amber, underside).
White lights marked the spacecraft, both fore and aft; to distinguish between
the two white lights, the aft one contained a flasher.
Ibid.; "Monthly Progress Report No. 25," LPR-10-41, p. 22.
February 26
ASPO Manager Joseph F. Shea named William A. Lee as an
assistant program manager. Lee, who previously headed the Operations Planning
Division (which had been absorbed into Owen E. Maynard's Systems Engineering
Division), now assumed responsibility for Apollo Operations (both the
flight-test program and the lunar mission). Lee thus joined Harry L. Reynolds,
also an assistant manager, who was assigned to the LEM's development. Deputy
Manager Robert O. Piland continued overseeing the CSM's development and, along
with Shea, overall program management.
MSC News Release 65- 34, February 26, 1965.
February 26
Louis Walter, Goddard Space Flight Center geochemist,
reported that his research with tektites indicated the lunar surface may be
sandlike. Waiter had discovered the presence of coesite in tektites, believed to
be particles of the moon sent into space when meteorites impact the lunar
surface. Coesite, also found at known meteorite craters, is a form of silicon
dioxide - a major constituent of sand - produced under high pressure. "If we
accept the lunar origin of tektites," Walter said, "this would prove or indicate
that the parent material on the moon is something like the welded tuft that we
find in Yellowstone Park, Iceland, New Zealand, and elsewhere." Welded tuft was
said to have some of the qualities of beach sand.
Astronautics and Aeronautics, 1965, p. 96.
During the Month
Because of a change in the size of the entry corridor,
North American technicians sought to determine whether they might relax the
requirements for pointing accuracy of the stabilization and control system at
transearth injection. They could not. To ensure a delta-V reserve, the accuracy
requirement must remain unchanged.
"Apollo Monthly Progress Report," SID 62-300-35, p. 8.
During the Month
Grumman reported three major problems with the LEM:
- To enable the manufacturer to complete the design of the aft equipment
bay, NASA must define the ground support equipment that would be supported by
the LEM adapter platforms.
- Space Technology Laboratories' difficulties with the descent engine
injector (the combustion instability in the variable-thrust engine)
- The need for a lightweight thrust chamber for the descent engine, one that
would still meet the new duty cycle.
"Monthly Progress Report No. 25,"
LPR-10-41, p. 3.
