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Extensive research conducted by the Langley Research Center has led to the development of a spacecraft control system employing three control moment gyros (CMG's). This Langley concept has been selected as the baseline control system for the Apollo Telescope Mount (ATM) which is being developed by the Marshall Space Flight Center. Langley is providing Marshall with the necessary supporting research to insure a successful ATM flight. A full-scale CMG unit has been procured to determine CMG hardware characteristics and nonlinearities. To evaluate the effects of these nonlinearities on the control capability of a CMG system, the unit has been incorporated into an analog simulation of spacecraft control for the ATM. This paper presents a description of the physical and hardware characteristics of the CMG unit, and discusses results obtained from the system simulations for ATM. These results indicate that the Langley CMG system can meet all ATM spacecraft pointing requirements.

The application of space-power technology to a possible progression of manned space flight requirements is presented. Of particular concern is the spectrum of mission requirements and constraints which strongly influence the selection and integration of a space-power concept with manned spacecraft, and the desire to “build-in” as much intrinsic value as possible into hardware decisions. An orderly progression of the manned space flight activity can be postulated which extends from immediate exploitation of Apollo earth-orbital capability to manned exploration of the planets. A multipurpose space station occupies a predominant role within this progression and will provide the major stimuli for the development of new and improved space-power concepts.

A generalized approach used in the thermal analysis of complex orbiting spacecraft is presented. The approach, consisting of the development of a mathematical model and its refinement, using verification testing, has allowed close predictions of actual spacecraft temperatures during flight. The application of this approach in the analysis of the Injun V (Explorer 40) spacecraft is presented as an example.

Through an examination of NASA functions and space program areas and their interrelationship, it is shown that the objectives of MSA earth orbital programs are: to develop space systems that will contribute to the solution of basic national problems by exploiting space for human welfare and knowledge, to exploit space for the advancement of science and technology, and to develop space capabilities precursor to planetary exploration. The role of a space station in the earth orbital program is that of a manned orbital research facility capable of exploiting the unique features of the space environment in combination with the capabilities of man as an onboard investigator to accomplish a broad spectrum of research and development in all areas of interest. Man's role in the orbiting research facility is similar to his role in a research laboratory on earth.

A number of zero-gravity liquid-gas phase separators such as rotating units, elbow type units, porous plate, and the hydrophobic-hydraulic type discussed in this paper are presently being developed for spacecraft use. The basic theory of this unit is presented and the application of surface tension phenomenon is discussed as they apply to the design. The materials of construction are covered, and the ultimate use on Apollo 11 is described.