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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.

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.

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.

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.