Advanced Design, Fabrication, and Testing
October 1965
1965
October 1
At a Customer Acceptance Readiness Review at North American, NASA
formally accepted spacecraft 002. The vehicle was then demated and
shipped to White Sands.
"Apollo Monthly Progress Report," SID 62-300-42, p. 1.
October 1
Homer E. Newell, Associate Administrator for Space Science and
Applications, notified Houston of the first two experiments selected for
early Apollo landing flights:
- a lunar gravimeter, which would measure variations in the moon's
gravitational field; and
- a seismic experiment. MSC informed Newell on November 2 that
negotiations were being initiated.
Letter, Newell, NASA, to Director, MSC, "Selection of Scientific
Investigations for Early Apollo Lunar Landing Missions," October
1, 1965; letter, Director, MSC, to Newell, NASA Headquarters, November
2, 1965.
October 1
MSC informed Grumman that the Center had awarded a contract to AC
Electronics for the development of an optical tracking system for the
LEM (as a possible alternative to the rendezvous radar). Until MSC
reached a final decision on which mode to use, Grumman should continue
building the LEM to accept either of these navigational devices. Flight
Crew Operations Directorate requested the decision be deferred pending
evaluation of an operational paper.
Letter, R. Wayne Young, MSC, to GAEC, Attn: R. S. Mullaney,
"Contract NAS 9-1100, Item 3; Selection of Rendezvous Radar or
Optical Tracker for LEM Navigation Requirement," October 1, 1965;
memorandum, Donald K. Slayton, MSC, to Manager, ASPO, "LEM Optical
Tracker," October 1, 1965.
October 1
In the absence of a firm requirement, and because of limited utility,
reported Robert C. Duncan, Chief of the Guidance and Control Division,
the horizon photometer and star tracker were being deleted from the
primary guidance system in Block I CSMs. (Block II guidance systems
would still contain the devices.)
Memorandum, Robert C. Duncan, MSC, to Distr., "Apollo primary
guidance system star tracker and horizon photometer," October 1,
1965.
October 3-9
The U.S. Geological Survey cooperated with Crew Systems Division (CSD)
in testing the extravehicular mobility unit under simulated lunar
conditions at Flagstaff, Arizona. As a result, CSD technicians
determined a number of deficiencies in the thermal meteoroid garment,
and recommended a number of changes to make the garment more functional
and more durable, as well as better fitting and more comfortable.
Memorandum, James H. O'Kane, MSC, to Chief, Crew Systems Division,
"Report of trip for USGS Apollo support in Arizona," November
1, 1965.
October 4
MSC ordered Grumman to halt work on both linear-shaped charges and
gas-driven guillotines as a method for severing the LEM's interstage
umbilical. Instead, the contractor should use two mild-detonation
guillotines or one dual-blade device.
Letter, James L. Neal, MSC, to GAEC, Attn: John C. Snedeker,
"Contract NAS 9-1100, Contract Change Authorization No. 142, Mild
Detonating Fuse Driven Guillotine," October 4, 1965.
October 5
As a result of a design meeting on September 2, MSC ordered North
American to make a number of detailed hardware changes in the CM
uprighting system for Block I spacecraft.
TWX, C. L. Taylor, MSC, to NAA, Space and Information Systems Division,
Attn: J. C. Cozad, subject: "Flotation Uprighting System Meeting
Conducted at NAA September 2, 1965," October 5, 1965.
October 5
ASPO Manager Joseph F. Shea recommended to Apollo Program Manager Samuel
C. Phillips that experiment M-5A (Bioassays Body Fluids) not be
incorporated on mission AS-204, based on schedule impact resulting from
structural modifications necessary to support the Urine Volume Measuring
System. Redesign and rework of existing spacecraft hardware would have a
schedule impact of two to four weeks.
Letter, Shea to Phillips, "Apollo In-Flight Experiments, Flight
AS-204," October 5, 1965.
October 6
MSC requested that Grumman study the feasibility of a "fire-till-
touchdown" landing procedure for the LEM. Grumman was to investigate
especially performance factors surrounding crushing of the descent
engine skirt, or possibly jettisoning the skirt, and was to recommend
hardware modifications required for this landing mode.
TWX, R. Wayne Young, MSC, to GAEC, Attn: R. S. Mullaney, October 6,
1965.
October 7-14
MSC's Reliability and Quality Assurance Division reported in August
that, because beryllium would corrode in the humid environment of the
spacecraft's cabin, the metal thus posed a toxicological hazard to the
crew of the CM. During subsequent meetings with the Health and Physics
Group, and Guidance and Control and Structures and Mechanics Divisions,
it was agreed that, because of crew safety, beryllium surfaces in the
guidance and control system must be coated to protect the metal from the
humid atmosphere inside the cabin of the spacecraft.
"ASPO Weekly Management Report, August 12-19, 1965"; MSC,
"Minutes of Senior Staff Meeting, October 1, 1965," p. 1;
MSC, "ASPO Weekly Management Report, October 7-14, 1965";
memorandum, Joseph N. Kotanchik, MSC, to Chief, Guidance and Control
Division, "Protective coating to prevent beryllium corrosion
inside the Apollo Command Module," November 4, 1965.
October 7-14
The Instrumentation and Electronic Systems Division (IESD) proposed that
the LEM's inflight VHF antenna might be used as a link to astronauts on
the surface of the moon as well. (LEM communications had to provide VHF
contact with the crew outside the spacecraft at ranges up to three
nautical miles. The VHF antenna, however, had been designed only for the
flight portions of the mission, and to meet this communications
requirement another antenna was being added to the LEM at a cost of
between 1.36 and 2.26 kg [3 and 5 lbs].) IESD offered to study the
coverage and range of the inflight antenna while on the lunar surface,
and suggested that the three-mile range requirement might be relaxed.
The additional VHF antenna might thereby be obviated.
Also, IESD attended a preliminary design review at Autonetics on the
signal conditioning equipment (SCE) for the Block II CSM. IESD concurred
in several modifications to the Block I design (adding a redundant power
supply; hermetic sealing of equipment; and repackaging to fit the
equipment bay in Block II CMs). These changes reduced the SCE's weight
from 22 to 19 kg (47.5 to 41 lbs) and, because of more efficient power
supply, lowered its power consumption from 65 to 35 watts. North
American was studying ways of perhaps lightening the SCE even further.
"ASPO Weekly Management Report, October 7-14, 1965."
October 7-14
Crew Systems Division (CSD) established vibration limits for the crew of
the LEM. This action followed the final LEM vibration test with human
subjects at Wright-Patterson AFB and a review of the test program by CSD
and Grumman engineers.
Also, in what CSD described as "the start of a long range program
for familiarizing Apollo suit technicians with field and launch
operations," the Division reported that it had sent an Apollo suit
technician to Cape Kennedy to take part in the forthcoming Gemini VI
mission.
Ibid.
October 8
A drop in the boilerplate 6A series, using flight-qualifiable earth
landing system (ELS) components, failed because the braking parachute
(not a part of the ELS) did not adequately stabilize the vehicle. MSC
invited North American and Northrop-Ventura to Houston to explain the
failure and to recommend corrective measures.
Ibid.
October 8
Because of the less-than-perfect firing of its retrorockets, Luna
VII, another Russian moon probe, was destroyed on impact. The
craft, launched four days earlier, was thus the third failure, Western
observers believed, in Russia's attempt to soft-land a spacecraft on
the moon.
Space Business Daily, October 11, 1965, pp. 190, 194;
Astronautics and Aeronautics, 1965, pp. 460, 463, 464-465,
467.
October 8
A test model of the Lunar Landing Research Vehicle, designed to simulate
lunar landings, was flown by former NASA X-15 pilot Joseph Walker to an
altitude of 91 m (300 ft). Built by Bell Aerosystems Company under
contract to NASA, the research craft had a jet engine that supported
five-sixths of its weight. The pilot manipulated solid-fuel lift rockets
that supported the remaining one-sixth, and the craft's attitude was
controlled with jets of hydrogen peroxide.
Astronautics and Aeronautics, 1965, p. 465.
October 12
On August 26, the attachments for the pilot parachute mortar had failed
during static testing on CM 006. The fittings had been redesigned and
the test was not repeated. This test, the final one in the limit load
series for the earth landing system, certified the structural interface
between the CM and the earth landing system for the 009 flight.
Memorandum, Joseph N. Kotanchik, MSC, to Manager, ASPO, "Launch
configuration of SC 009," October 19, 1965; MSC, "ASPO Weekly
Management Report, October 21-28, 1965."
October 12
To ensure compatibility with the spacecraft, MSC specified weight and
storage details for the extravehicular visors. The devices, two of which
would be carried on each mission and transferred from the CM to the LEM,
would afford impact, thermal, and ultraviolet protection for the crew
during operations in space or on the lunar surface.
Letter, R. Wayne Young, MSC, to GAEC, Attn: R. S. Mullaney,
"Contract NAS 9-1100, EMU EV Visor Assembly," October 12,
1965.
October 14
NASA was negotiating with General Electric Company to provide 56-watt
isotopic power generators for the Apollo Lunar Surface Experiment
Packages. The Atomic Energy Commission would manage detailed design and
development of the unit based on MSC studies of prototypes.
Astronautics and Aeronautics, 1965, p. 476.
October 15
Owen E. Maynard, Systems Engineering Division chief, summarized for ASPO
Manager Joseph F. Shea the recovery requirements for Apollo spacecraft.
The CM must float in a stable, apex-up attitude, and all of the
vehicle's recovery aids (uprighting system, communications, etc.) must
be operable for 48 hrs after landing. In any water landing within 40
degrees north or south latitude, the Landing and Recovery Division had
determined, the crew either would be rescued or recovery personnel would
be in the water with the CM within this 48-hr period. Thereafter,
Maynard said, the spacecraft had but to remain afloat until a recovery
ship arrived - at most, five days.
Memorandum, Maynard, MSC, to Manager, ASPO, "Post-landing
flotation requirements," October 15, 1965.
October 15
NASA announced that it had selected Lockheed Electronics Company of
Houston, Texas, to provide broad data-handling support at MSC.
Negotiations on the contract (valued at more than $3 million) began
shortly thereafter.
MSC News Release 65-93, "NASA to Negotiate with Lockheed
Electronics Go. for Computer Programming Support," October 15,
1965; letter, George E, Mueller, NASA, to Robert R. Gilruth, MSC,
October 29, 1965.
October 18
MSC ordered Grumman to discontinue use of zinc and cadmium on all
production LEMs. This action followed performance studies by the
Reliability and Quality Assurance Division that showed a deleterious
effect of space environments upon these metals.
Letter, R. Wayne Young, MSC, to GAEC, Attn: R. S. Mullaney,
"Contract NAS 9-1100, The use of Cadmium or Zinc Plate in the
Apollo Spacecraft," October 18, 1965.
October 18
To solve the problem of controlling bacteria in the LEM's waste
management system (WMS), Crew Systems Division (CSD) recommended some
type of passive control rather than periodically adding a germicide to
the system. CSD described two such passive techniques, both of which
relied on chemicals upstream from the WMS (i.e., in the urine collection
device in the space suit). MSC began studying the feasibility of this
approach, and ordered Grumman also to evaluate passive control in the
contractor's own investigation of the bacteriological problem.
Letter, R. Wayne Young, MSC, to GAEC, Attn: R. S. Mullaney,
"Contract NAS 9-1100, Bacteriological Control for LEM Waste
Management Subsystem," October 18, 1965, with enclosure.
October 19-22
A meeting was held at Flight Research Center to discuss several items
relating to the Lunar Landing Research Vehicle (LLRV) and Lunar Landing
Training Vehicle (LLTV). Attending were Dean Grimm, Robert Hutchins,
Warren North, and Joseph Algranti of MSC; Robert Brown, John Ryken, and
Ron Decrevel of Bell Aerosystems Company; and Gene Matranga, Wayne
Ottinger, and Arlene Johnson of Flight Research Center.
The discussions centered around MSC's needs for two LLRVs and two LLTVs
and the critical nature of the proposed schedules; alternatives of
assembling a second LLRV ; clarifying the elements of the work
statement; and preliminary talks about writing specifications for the
LLTV.
From a schedule standpoint, it was decided that both LLRVs would be
delivered to MSC on September 1, 1966. MSC planned to check out and fly
the second LLRV (which needed additional systems checkout) with their
crew and pilot on a noninterference basis with LLRV No. 1, the primary
training vehicle.
NASA Internal Memorandum for those concerned, Gene J. Matranga, LLRV
Project Manager, "Meetings held during the week of October 17
relating to the LLRV," October 26, 1965.
October 20
The MSC Mission Constraints Control Panel (MCCP) held its initial
meeting. The panel's function was to resolve all conflicts between
launch vehicle, spacecraft, and operational constraints. Also, once the
preliminary reference trajectory was issued, the MCCP must approve all
constraint changes. These would then be included in the mission
requirements.
Memorandum, Robert V. Battey, MSC, to Distr., "Minutes of 1st
Mission Constraints Control Panel Meeting," October 26, 1965, with
enclosure.
October 20
To save weight, Crew Systems Division was studying the feasibility of
using three one-man liferafts and a composite set of survival gear in
Block I CMs.
Memorandum, R. E. Smylie, MSC, to Chief, Crew Integration Branch, Attn:
J. Marshall, "Block I composite kit study," October 20,
1965,
October 20
Apollo spacecraft 009, first of the type that would carry three
astronauts to the moon and back, was accepted by NASA during informal
ceremonies at North American. Spacecraft 009 included a CM, SM, launch
escape system, and adapter.
Astronautics and Aeronautics, 1965, p. 485.
October 20-21
To support studies on equipment stowage, North American agreed to
maintain mockups of the crew compartments in the two blocks of CMs. The
contractor's effort would be geared for the first manned flight for each
series of vehicles (spacecraft 012 and 101).
"ASPO Weekly Management Report, October 21-28, 1965."
October 21
Samuel C. Phillips, Apollo Program Director, notified the Center
directors and Apollo program managers in Houston, Huntsville, and Cape
Kennedy that OMSF's launch schedule for Apollo-Saturn IB flights had
been revised, based on delivery of CSMs 009 and 011:
- AS-201 - January 1966
- AS-202 - June 1966
Schedules for AS-203 through 205 (July and October 1966, and January
1967) were unchanged.
TWX, Phillips, NASA, to Kurt Debus, KSC, Robert Gilruth, MSC, and
Wernher von Braun, MSFC, subject: "Saturn IB Launch
Schedules," October 21, 1965.
October 21
MSC announced that the bubble-type helmet, designed by Crew Systems
Division (CSD) engineers Robert L. Jones and James O'Kane, had been
adopted for use in the Apollo extravehicular mobility unit. The new
helmet was smaller and lighter than earlier types; extensive studies by
CSD had demonstrated its superior comfort, visibility, and don/doff
characteristics.
MSC News Release 65-96, October 21, 1965.
October 21
To enable MSC's Mission Control Center (MCC) to handle Apollo flights,
MSC announced that NASA's contract with IBM for computer systems would
be extended. For an additional $80 million, IBM would convert the MCC to
newer equipment and would use more advanced support techniques. The
contract would contain provisions for conversion to an incentive fee
type.
MSC News Release 65-97, October 21, 1965.
October 21
North American completed static structural tests on the forward
heatshield for the Block I CM (part of the certification test network
for airframes 009, 011, and 012), thus demonstrating the heatshield's
structural integrity when jettisoned (at the start of the earth landing
system sequence).
"ASPO Weekly Management Report, October 21-28, 1965."
October 22
NASA announced that it had selected 10 areas on the moon as subjects for
Lunar Orbiter's cameras during 1966. These areas encompassed most major
types of lunar terrain. Most were suitable - and potential - landing
sites for Surveyor and Apollo spacecraft.
NASA News Release 65-335, "NASA Selects 10 Potential Photo Areas
for Lunar Orbiter," October 22, 1965.
October 23-26
The Pregnant Guppy aircraft, which was used extensively by NASA to transport spacecraft during all phases of the Apollo program.
While delivering Apollo SM 009, the Pregnant Guppy aircraft was delayed
at Ellington Air Force Base, Texas, for three-and-a-half days while
waiting for an engine change. In view of the delay of the SM, the
incident was reviewed during the succeeding weeks, and Aero Spacelines
was requested to place spare engines not only at Houston, but also at
other strategic locations on the normal air route from Long Beach,
Calif., to KSC.
Letter, Edmund F. O'Connor, MSFC, to MSC, Attn: Joseph F. Shea,
"Pregnant Guppy emergency engine change, October 23-26,
1965," November 18, 1965.
October 26
MSC authorized North American to modify the Block II CSM design to
provide for installation of a luminous beacon compatible with the LEM
tracking system. The CSM beacon could replace the rendezvous radar and
transponder.
Letter, J. B. Alldredge, MSC, to NAA, Space and Information Systems
Division, "Contract Change Authorization No. 455," October
26, 1965; memo, Owen E. Maynard, MSC, to Project Officer, CSM,
"Deletion of automatic actuation capability of VHF recovery beacon
(Block II)," October 8, 1965.
October 27
At a meeting with Grumman, MSC agreed with the contractor's basic design
of the LEM's descent-stage base heatshield and its installation and
access. MSC asked Grumman to demonstrate accessibility, installation,
and removal of the heatshield on the M-4 mockup.
Letter, R. Wayne Young, MSC, to GAEC, Attn: R. S. Mullaney,
"Contract NAS 9-1100, Implementation of Action Items,"
November 3, 1965, with enclosure, "Abstract of LEM Base Heat
Shield Review," undated.
October 29
Owen E. Maynard, Systems Engineering Division chief, advised his branch
managers of the U.S. Public Health Service's (PHS) growing concern that
Apollo spacecraft and crews might bring organisms back from the moon.
(See September 27.) PHS feared that such organisms would be
"capable of multiplying in the earth environment and [that]
precautionary measures must be undertaken to prevent global
exposure." Therefore, Maynard told his group, PHS believed that
the CM, its environment, and its crew must not be allowed to contact
the earth's environment. Maynard further advised that efforts were
already underway to define the design of an isolation facility, and
isolation facilities for the recovery ships were being contemplated.
As a result of this strong stand by PHS, Maynard said, "It appears
that ASPO will soon be requested to show what spacecraft measures are
being taken to assure that the CM environment will not be exposed to
the earth atmosphere. The spacecraft," Maynard told his group -
who already knew as much - "has not been designed to preclude CM
environment exposure." Actually, much the opposite had long been
assumed to be part of normal operating procedures. Maynard therefore
ordered subsystem managers to review their individual systems to
determine:
- If their system was potentially a carrier of moon germs
- What could be done to confine such organisms
- If a "strict no contamination edict" would affect the life and
operation of systems
- How postlanding procedures could be changed to prevent release of
organisms from the spacecraft
Maynard cautioned systems managers to "assume that ASPO is morally
obligated to prevent any possible contamination of the earth," and
not to reply with "the standard answer that no changes can be made
within present weight, cost, and schedule limitations.
Admittedly," he said, "our first look may prove to be
insurmountable." Nonetheless, review must be performed so that
recommendations can be made concerning all such systems.
Memorandum, Maynard, MSC, to PHS Branches, "Earth contamination
from lunar surface organisms," October 29, 1965.
During the Month
Seven flights were made with the Lunar Landing Research Vehicle at
Flight Research Center during October. The first three were in support
of X-15 conference activities, and the last four were for attitude
control research. Five of the landings were made in the lunar simulation
mode.
Letter, Office of Director, Flight Research Center, to NASA
Headquarters, "Lunar Landing Research Vehicle progress report No.
28 for the period ending October 31, 1965," sgd. Paul F. Bikle,
November 2, 1965.