The Mission 1-A is conceived as an optimum method of obtaining early experience of selected earth resources, meteorological, and orbital experiments. The candidate experiments emphasize earth resources and include verification of remote sensing techniques while also providing large-scale regional mapping of geological features indicative of resource reserves, synoptic surveys of agricultural and forestry resources, water surveys potentially applicable to pollution studies, oceanographical data on sea state, temperature currents, and possible location of marine life.

The mission involves a launch of a single uprated Saturn I from KSC with a Block II command and service module and a crew of three. The orbit would be circular at about 140 nautical miles at an inclination of about 50° with the primary earth resources target area being the Zone of Interior. Recovery of the command module would occur after 14 days. The experiments and their supporting subsystems would be contained in an experiments carrier that is docked to the front of the command module in orbit, much like the lunar module is in the lunar mission.

The experiments carrier (see fig. 9) structure consists of a tube frame with a conical pressure shell to enable necessary astronaut functions to be performed without extra vehicular actions. Power (both DC and AC) is provided the experiments, as well as a "real time" and "delayed transmission" data management system. Thermal control of the experiments is provided both passively and actively. Life support for the crew is provided from the command and service module; target pointing is provided by the command and service module with a backup system in the experiments carrier.

The experiments carrier makes maximum usage of hardware developed by NASA for programs such as Gemini and Apollo. The impact to the command and service module has been minimized and consists chiefly of minor wiring interfaces.

THE LOCKHEED MISSILES & SPACE CO. BRIEFING

SUNNYVALE, CALIF., OCTOBER 31, 1967

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

SUMMARY OF LOCKHEED MISSILES & SPACE CO. PARTICIPATION IN THE APOLLO APPLICATIONS PROGRAM

The Lockheed Missiles & Space Co. participated in the Apollo Applications Program under contract to Marshall Space Flight Center for Phase C final definition, a study of payload integration. The effort was one of two competitive contracts awarded by Marshall in June of 1966. Prior to that award, Lockheed had been active in preproposal activities dating back to January of 1965. During the 1-year term of the Payload Integration study, Lockheed made significant contributions to the evolution of the AAP earth-orbital and pending lunar missions. These contributions are summarized in the succeeding abstracts.

Lockheed was not successful in its competition to win the Phase D (development operations phase) of payload integration. We do retain an interest in the Apollo Applications Program and in succeeding manned space flight programs. Accordingly prior to, during, and subsequent to our activities in payload integration, we have pursued potential experiment systems that might be incorporated in AAP and subsequent manned earth-orbital programs, as well as developed advanced technology relating to future space flight. The presentations beyond AAP deal with this type experiments and technology.

An area of principal interest to Lockheed pertaining to manned space flight has been lunar exploration. We have conducted an extensive amount of advanced lunar planning, both under contract to NASA and on our own resources. One of the tasks undertaken in the Payload Integration study was Advanced Lunar Missions. Since completing the AAP Payload Integration contract we have continued our in-house and contracted studies in support of post-Apollo missions. Considerable effort is currently being expended in support of the concepts for lunar flying vehicles to transport astronauts over the lunar surface and with a concept for deploying logistics to the moon in support of manned missions. This work is complementary to past efforts on the Lunar Scientific Survey Module and various configurations of lunar logistics vehicles and payload equipments to be carried.

In the early 1960's Lockheed recognized that a key to its participation in future manned flight activities was the development of a capa

bility in bioastronautics. An excellent capability has since been built in this area, including both qualified staff and appropriate facilities. We have pursued contract and in-house efforts that directly relate to man's capability to live in space. Two of these efforts potentially can become a part of Apollo Applications. The first is a competitive study of the Integrated Medical and Behavioral Laboratory System (IMBLMS). This is a system to permit flexibility in conducting biomedical experiments in space. It is expected that this system will provide data from man in space that are not attainable in earth-based laboratories. It is currently planned that the system will fly as a part of a future S-IVB Workshop.

Looking forward to longer duration manned flights, either in earthorbital space or on planetary missions, the biomedical community is interested in obtaining additional data on the effects of very long periods of weightlessness. One concept being studied under contract is the Orbiting Primate Experiment, which proposes to fly two primates in zero-g for up to 1 year. The current approach provides for flying this mission in conjunction with the Apollo Applications Program. The spacecraft can operate as a part of, or separate from, the AAP cluster. In either event, the recovery and return to earth of the primates is a function of astronaut retrieval in space and return via the Apollo command module. It is hoped that this system will fly in the early 1970's.

Another potential AAP experiment that Lockheed is studying in support of a NASA contract to the Perkin-Elmer Corp., is the Optical Telescope Experiment System (OTES). This is a system for establishing the technology to be used in large optical observatories in space. The study involves development of the types and sizes of telescopes to be used, the participation by man in the setup, and implementation of the observatory and its subsequent maintenance. As currently conceived, OTES can fly as an AAP experiment late in the earth-orbital program. One of the primary functions the astronauts would perform in the Perkin-Elmer/Lockheed concept is the substitution of segments of the primary mirror to evaluate the efficiency of different materials. Looking forward to the long-term (1-year) manned space flight, Lockheed recognized the desirability and need for two-gas regenerative life-support systems. We have undertaken in-house development of such a system for application to future missions. We now have that system in operation and have recently completed a 30-day simulation wherein the device was operative over the whole period for 24 hours a day. As it is currently configured, the system is not flightworthy; however, almost all components are capable of functioning in zero-g. If there were a requirement, such a system could be flight rated in a very short time.

Another area that was initially studied as a part of the integration contract was the investigation of carrying out earth-resources measurements from AAP spacecraft. Mission 1-A is being considered as a test bed for numerous earth-resources sensors. Under the integration contract, we studied potential equipment arrangements, carrier vehicles, and various mission plans. After the contract expired we continued our in-house efforts, examining the potential of space measurements of earth resources. We have been investigating the potential usefulness to the various categories of users and some of the problems

inherent in making space-acquired data available in useful form. We also investigated the interrelationships between a space system, an airplane system, and acquiring the resources data on the earth's surface. We believe that all three types of systems have a role and that the best total system will be a combination of all three types of dataacquisition platforms.

AAP PAYLOAD INTEGRATION

Lockheed was one of two contractors selected to conduct 1-year final-definition phase studies of Apollo Applications Payload Integration. Our contract was awarded by the NASA Marshall Space Flight Center in June of 1966. The principal task of the payload integration contractor was to design and provide the interface between the carrier equipments and the experiments in AAP. The two study contractors provided direct engineering inputs to the AAP design concept and submitted proposals for accomplishing the development-operations phase (Phase D) of the program. Some of the work performed by both contractors under the study was comparable. About 70 percent of each contractor's effort was concerned with the performance of different engineering tasks. The other contractor's assignment dealt with the S-IVB Orbital Workshop, while Lockheed provided support in the design of the Apollo Telescope Mount. We believe that we made significant contributions to the ATM design.

In addition to the ATM work, we provided support in the area of the Workshop primary power, currently planned to be a solar-array system. Lockheed was particularly well qualified to provide this assistance, based on the Company's extensive flight experience with solar arrays. The array requirements evolved from an initial size of 500 to 800 square feet (and eventually up to the current configuration of almost 1,200 square feet). Involved was the design of the attach and extension mechanisms, as well as the basic array system.

Our responsibilities on the ATM program included all phases of its development-design, thermal analysis, mission operations, and astronaut activities. Specific problem areas in which we participated included pointing control of the instrument, simulation, thermal control, mission planning, and data retrieval. The ATM is a cylindrical container in which all the solar astronomy experiments are located. It is attached to the major structural frame. Stabilization for accurate pointing (22 arc-sec pointing accuracy and 1 arc-sec stability over a 15-minute observation period) is critical. Marshall's current design for stabilization is based on concepts evolved at LMSC.

Another contribution was in the area of dynamic simulation of the pointing stability and control systems when attached to the telescope mount and then to the big cluster. This involved developing a computer program to simulate the entire assembly, together with the control systems involved. As a result, we were able to demonstrate the stability of the control system and identify the structural requirements. Another challenging design problem was to arrange the electrical cables that cross gimbal points in such a way that they do not impart too much spring torque to the system. The magnitude of the spring torque is a measure of the accuracy and speed at which maneuvering can be accomplished.