The configuration of the Airlock Module consists of a tunnel and truss structure forming the central "engine room" of the cluster. It incorporates the electric power conditioning, storage, and distribution system for the entire cluster; the central Environmental Control System; and the central command and instrumentation center for the orbital workshop. (Fig. 1-10.)

Multiple Docking Adapter.-The Multiple Docking Adapter (MDA) was being developed and fabricated in-house by NASA at MSFC. The preliminary design review was held on this item in January. In April, a task force was established to determine the feasibility of conducting key medical experiments within 24 hours after launch in the MDA and prior to activation of the spent stage. Studies established the feasibility of this proposal without a major change of the MDA design. Early medical experimentation was incorporated in the new mission profile. (Fig. 1-11.)

Apollo Telescope Mount.-Work on the Apollo Telescope Mount (ATM) was continuing at MSFC. In January, the preliminary requirements review was held on the ATM Pointing Control System. Similar reviews of the remaining ATM subsystems were being planned. Two scientist-astronauts took part in a simulated operation of the ATM during May, using the computer driven ATM simulator at MSFC.

Five experiments are currently planned for the Apollo Telescope Mount (ATM). These were being fabricated by the High Altitude Observatory, Boulder, Colorado; the Naval Research Laboratory (NRL), Washington, D.C.; the American Science and Engineering Company, Cambridge, Massachusetts; the Goddard Space Flight Center (GSFC), Greenbelt, Maryland; and the Harvard College Observatory, Cambridge, Massachusetts.

Lunar Module.-The earth orbital missions for the AAP employ the ascent stage of the Apollo Lunar Module (LM-A). The changes required to modify this stage for AAP use were being designed at the contractor's facility in Bethpage, Long Island, New York.

In May, the preliminary requirements review meeting was held. An astronaut-walk-through exercise was performed on a mockup model of the Lunar Module. Final definition work will result in a preliminary design review, planned for late September (1968).

Command and Service Modules.-To enable man to exist in space for extended durations, up to 56 days, it is necessary to make certain modifications to the basic Apollo Command Module and Service Module. Prelimintary design work was being performed to define what these modifications should be. These efforts were being concentrated in the areas of trade-off studies and definition.

Launch Vehicles.-Launch vehicles procurement is under the cognizance of MSFC. The initial flight missions of the AAP will use those Saturn IB Launch Vehicles procured within the Apollo Program but not needed to accomplish the manned lunar landing. The current AAP mission plan assumes availability of Apollo Saturn IB vehicles 206 through 212 for initial AAP use.

Advanced Manned Missions

The Advanced Manned Missions Program continued studying three major areas during this reporting period: Future Space Stations, Space Transportation Systems, and Space Safety.

Previous Space Station Studies examined concepts that used the S-IVB stage structure and/or envelope and required the full capability of the Saturn V vehicle for launch. These Saturn V stations represented a full integrated "all up" design approach with experiments and equipment being launched with the station along with most of the consumables required for the operational lifetime of the station. While this approach has some attractive features, it is highly inflexible from both management and mission operations viewpoints. The need for a concept that could provide a high degree of program and mission flexibility led to the conduct of three independent studies, by the Langley Research Center, the Manned Spacecraft Center, and the Marshall Space Flight Center during May and June 1968. These efforts yielded several future space station concepts which are better suited to the prevailing planning atmosphere than alternatives previously available for management consideration.

Certain desirable characteristics were formulated as general guidelines for the studies. The space station should provide for a nominal crew size of six with growth capability to nine men; it should, however, be operational with a crew of three. It should have a two-year operational lifetime. Subsystems should be designed, and components packaged, to facilitate maintenance, repair, and onboard checkout. The station should possess a high degree of mission and operational flexibility and provide for the conduct of useful science and applications programs including the demonstration of man's contribution. The system should be potentially capable of becoming operational in the mid-1970's.

Three concepts evolving from the studies were selected for more detailed effort. All possess the desired characteristics. In addition, they are similar in their ability to operate with separately launched payload modules and in their ability to operate with a logistics system based on either a Gemini derivative spacecraft or the Apollo Command and Service Modules.

One concept is made up of one or more independent three to five man stations; each consists of a 22-foot diameter cylinder having the capability to dock with another station in orbit, or to be stacked together with another station and launched as a unit.

The second concept is a highly integrated station which could house a crew of three to nine men; it has a pressurized hangar/test compartment which serves for crew and cargo transfer as well as for a work area.

The third concept evolving from the studies consists of various combinations of subsystems, crew, logistics and experiment modules. Repeated launchings of manned and/or unmanned modules can build up an orbital station responsive to a variety of mission requirements. More detailed design and definition of these alternatives was being planned as part of the continuing effort to select the best approach to advance manned earth orbiting flight beyond the Saturn I Workshop.

Manned Space Flight transportation systems studies have emphasized inhouse work involving Headquarters, the Centers, and unfunded contractor participation. These studies have produced certain specific results. The Saturn V launch vehicle and its two-stage derivatives the S-IC + S-II, and the S-IC + S-IVB-offer a readily available, flexible and economical family of man-rated launch systems covering a broad range of missions and payloads. Considering the total cost to the Government and the projected launch rates, NASA believes the Saturn V system and its two-stage derivatives provide an economical launch vehicle stable. They can be used not only with the Apollo spacecraft systems but also with new or improved payload and flight systems while exploiting ground launch facilities already in existence.

Techniques for reducing space transportation costs of existing launch vehicle systems and derivative configurations were being identified. It was clear, however, that the viability and success of long duration orbital laboratories and space stations will be critically dependent on the availability of a more efficient and flexible round-trip transportation system.

Studies were initiated to develop space safety design criteria. These studies will provide guidance to future space station designers as to design features and practices which may affect astronaut safety. The criteria were being developed with respect to routine operational tasks, experiment activity, spacecraft control, materiel handling, and onboard systems maintenance. Astronaut activities, and possible hazards associated with them (both internal and external to the spacecraft) are being considered.

Previous studies established the desirability of providing low earth orbital escape or rescue systems. Escape vehicle concept studies investigated alternate designs for 3-man escape vehicles applicable to low earth orbit. Several ballistic shapes were evaluated in the course of the studies; these include spheres, modified spheres, and a number of conical shapes. It is the purpose of a recently initiated study to develop a concept, or concepts, which will be light enough and uncomplicated enough to provide astronaut safety in the event of a major space station failure. The information developed in the course of this study, together with previously developed data, will provide guidance in selecting an escape/rescue system for possible use with future low earth orbital space stations.

Mission Operations

The Agency's manned space flight mission operations activities were concerned with flight crew operations, support requirements, mission control systems, launch information systems, operational communications, and the Huntsville Operational Support Center.

Flight Crew Operations

The flight crews for the first three manned Apollo flights continued in their training programs. Each crew took part in the development testing of its spacecraft. By the end of June, the crew for AS-205 (first launch) was essentially in residence at Kennedy Space Center.

The scientist-astronauts selected for training in 1967 entered flight training at various USAF bases. One astronaut, finding that he did not care for flying, resigned. One of the pilot astronauts was grounded for physical reasons and has returned to his parent service for treatment.

The first lunar landing training vehicle was placed into full scale training operations early in 1968. After 50 training flights, the vehicle crashed and was destroyed. The pilot, astronaut Neil Armstrong, ejected safely and received only minor injuries. An accident investigation board was reviewing the circumstances surrounding the accident at the end of June.

At the time of the accident, the vehicle had flown almost 300 flights during the research program at the Flight Research Center and the training program at the Manned Spacecraft Center.

Two other vehicles for training purposes only were well on their way through ground test preparatory to flight test.

Operations Support Requirements

Satisfactory operations support of Apollo 5 and 6 was achieved through the Requirements/Support Documentation System.