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An analysis is presented of current solar concentrator types when integrated into complete space power systems with various electrical conversion methods. Concentrator designs such as inflatable-rigidized, petal, one-piece, and Fresnel are treated in the paper and their size, weight, and packaging characteristics, when combined with dynamic and static conversion schemes, are illustrated. Information presented in the paper provides insight into the selection of concentrator designs for space power applications.

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.

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.

Flexible wings for transportation involves the use of flexible fabric-like lifting surfaces that can be folded or packaged before and after use. This paper is limited to uses of flexible wings for transportation of passengers and cargo from point to point on earth and to emergency use of flexible wings in connection with more conventional aircraft. It covers the following subjects: gliding and soaring, towing, powered flight, air-dropped wings, rocket-launched wings, and emergency wings.

Prospects for relief of the helicopter' s recognized problems by way of design changes as accompanied by, or resulting from, essential research-type information and understanding are examined. For example, the potential advantages of the nonarticulated rotor system are reviewed and the status of the required steps toward adequate knowledge of loads and dynamics is outlined. Other rotor configuration changes, as well as the basic topics of performance, dynamics, operating problems, and safety are similarly treated. It is concluded that many avenues are now available for basic improvements in helicopters via research and invention, while retaining the basic concept of low disc loadings.

Currently under investigation at the Langley Research Center in Hampton, Va., is a research test chamber to study and test life support subsystems for long-duration space missions. This system is designed to support four men for a period of 1 year in a near-earth circular orbit with resupply at a 90 day interval. Critical life support subsystems include the recovery of water from urine, waste management, and personal hygiene. Microbiological studies in support of the development and testing of a wick evaporator, water management subsystem are reported. The goal of this program is to produce water meeting the recommended standard of “essential sterility,” that is, no more than a sum total of 10 micro-organisms per ml. Modification of the wick evaporator system to permit the use of heat for sterilization will be described. Microbiological and chemical results obtained during research and development on a bench model and from two units inside the ILSS test chamber are presented.

This paper describes the NASA Langley Impact Dynamics Facility that will be used to crash test full-scale light aircraft under the Joint FAA/NASA General Aviation Crashworthiness Program. The aircraft are crashed into the ground as free bodies, using a pendulum swing method to obtain desired flightpath angles and velocities. The aircraft are unrestrained during impact to obtain realistic reactions. Accelerations and strains of the aircraft structure are measured during impact. The crash sequence and structural deformations are obtained by external and internal camera coverage.

The current joint NASA-FAA simulator program, designed to study the problems anticipated in the integration of the supersonic transport (SST) into the air traffic control (ATC) system, is explained. The initial tests have consisted of simulated departure and arrival operations of a variable-sweep SST configuration in the New York terminal area under high-density traffic flow conditions with as many as six SST operations per hour. Several types of separation standards and handling concepts were investigated while using an ATC system based on present-day concepts and procedures. Results describing the operating problems for the SST and the workload, delay, and capacity problems for the ATC system are discussed.