ing the conceptual design to a preliminary design during the Phase B program.

OTES, in its extended configuration, consists of a lunar module, an ATM rack, and the recommended 2-meter telescope. Extended, the overall spacecraft length is 480 inches, with 389 inches extending forward of the gimbal plane. This concept was evolved by combining desirable features of the several concepts considered previously. It accommodates a full 2-meter-diameter primary mirror and meets the requirement for integration of the system into the ATM rack developed for Apollo Applications. Experiment evolution of optical technology for space applications, early flights as a part of AAP, and relatively low costs are OTES goals that appear obtainable by utilizing the recommended 2-meter concept. (See fig. 5.)

The Lockheed two-gas regenerative life-support development program was initiated in 1964 for the purpose of applying advanced technology to the problem of providing a habitable environment for a four-man crew on space missions of 1 year or longer duration.

The system controls temperature, pressure, humidity, and the partial pressure of oxygen. It removes carbon dioxide and reduces it via the Sabatier reaction. The water formed is then electrolyzed, forming oxygen for breathing. Toxic contaminants are also removed. All drinking water required for the four-man crew is provided by filtering atmospheric condensate and vacuum-distilling urine. The various subsystems used are as follows:

Temperature control: Circulating fluid cooled in space radia

tor.

Pressure control: Regulation of inert-gas introduction by adjustable mechanical regulator.

LOCKHEED TWO-GAS REGENERATIVE LIFE-SUPPORT SYSTEM

Humidity control: Condensed excess moisture separated from atmosphere by nonrotating hydrophobic separator.

Oxygen partial-pressure control: Polarographic sensor operates oxygen inlet valve through adjustable automatic controller.

Carbon dioxide removal: Regenerable molecular-sieve/silica-gel system with thermal and vacuum desorption.

Carbon dioxide reduction: Sabatier process using nickel catalyst.

Water electrolysis: KOH electrolyte-absorbent matrices for zero-g operation.

Toxic contaminant removal: Basic sorbent plus vacuum desorbed acidified charcoal in combination with catalytic oxidation. Water reclamation: Atmospheric condensate filtration combined with vacuum distillation of urine followed by filtration.

In a flight configuration, this system would weigh less than 400 pounds, occupy approximately 50 cubic feet and require 1,800 watts of power.

The system has undergone extensive testing in the unmanned mode. During these tests, cabin and crew loads were simulated, including carbon dioxide, water vapor, toxic contaminants, and heat production, as well as oxygen consumption and leakage.

The longest unmanned test thus far has been of 30 days' duration and was successfully completed in November 1967. Other component, subsystem, and integrated system testing has resulted in a total test time of nearly 2,000 hours on critical items.

Tests also have been conducted using animal and human subjects; the

most significant of these involved a four-man crew in the Lockheed Space Environmental Chamber for a 3-day period.

Cabin total pressure can be maintained at any value between 5 and 14.7 pounds per square inch absolute with oxygen concentration between 5 and 3 pounds per square inch absolute. Any diluent gas can be used; however, the Lockheed testing has involved only nitrogen and helium. During the 30-day unmanned and 3-day manned tests, a cabin pressure of 7.5 pounds per square inch absolute (42 percent O2, 58 percent N2) was maintained. (See fig. 6.)

As a part of the Payload Integration study, Lockheed investigated the utilization of an AAP flight as a test bed for earth-resources sensors. NASA provided the candidate sensor experiments, and it was our job to investigate the carrier in which they should be accommodated and to recommend which experiments should be flown as a function of data return, cost, and availability. The suggested experiments provided by NASA were a combination of meteorology and earthresources instrumentation. Our recommendations to NASA suggested that the experiments should be installed in a pressurized carrier of very simple construction. This carrier would fly docked to the Apollo command module. The carrier would provide for habitation for two astronauts, one to assist in aiming the vehicle and the other to operate and adjust the experiments. The recommended attitude would be nose down, toward earth, rather than flying parallel to the earth's curvature.

Subsequent to completion of the integration contract, Lockheed has continued in-house efforts to examine the potential of space measurements of earth resources. In addition to work on potential spacecraft and experiments, we have investigated the problems associated with data retrieval and reduction. Considerable time has been spent in attempting to determine the usefulness of the data by persons other than experimenters. Direct contact has been made with users of such data, including geologists, foresters, agriculturists, and mapmakers. Tradeoffs have been made in various methods of acquiring earthresources data, including acquisition from space, from aircraft, and from the ground.

To date, several conclusions have been reached: (1) There currently are users, primarily in mapmaking, geology, and mineralogy, who can use information from space as quickly as it is available. (2) Earth-resources data-collection systems should consist of all three modes of data acquisitions, i.e., space vehicles, aircraft, and ground sensors. These systems should not be considered competitive, but complementary. (3) Sensor development test flights can usefully be accomplished in conjunction with manned flights. (4) Long term operational systems are likely to be unmanned spacecraft. (5) The problem of data reduction and dissemination needs much more attention. Providing usable information to users is the key to any future successful earth-resources program. (6) More attention should be devoted by Government agencies to making industrial users a part of the earthresources development program. Most of the emphasis to date has been on the spacecraft and on sensor development, and insufficient attention has been paid to the man who will put the information to work. (See Fig. 7.)

NORTH AMERICAN ROCKWELL

NOVEMBER 1, 1967

PRESENTATION TO THE SUBCOMMITTEE ON NASA OVERSIGHT, COMMITTEE ON SCIENCE AND ASTRONAUTICS, HOUSE OF REPRESENTATIVES

North American Rockwell Corp. Space Division, prime contractor for the command and service module, gave a presentation to the Committee Staff on November 1, 1967. Mr. Dale D. Myers, vice president and program manager for the Apollo command and service modules, gave the presentation.

Mr. Myers reviewed the Apollo flight chronology and enumerated the 13 previous successful Apollo flights during the period November 1963 through August 25, 1966 (slide 1). A review of the Apollo spacecraft fabrication assembly and systems installation program reflected that the CSM Program on January 26, 1967, was essentially on schedule on the whole program as far as flight spacecraft were concerned. CSM 2TV-1 was in checkout and was slightly behind schedule. CSM 020 was in final checkout and on schedule and CSM 017 had been delivered to KSC. The Block II (lunar configuration) command and service modules were proceeding on schedule (slide 2).