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Spin tunnel tests to determine effectiveness of deployable, flexible ventral fins for spin recovery device on fighter aircraft
The design, development, and fabrication of a feasibility model of a breathing bag life support system for extravehicular activity are discussed. The breathing vest and back pack portable life support system contains connectors which allow external water and gas supply. At a metabolic rate of 2000 BTU per hour, the two low pressure bottles provide 27 minutes of breathing gas for a total filled system weight of 30.5 pounds.
Discussion of the spectrum of remedial concepts and realistic mission constraints. A vehicle design is presented which is offered as the 'best' solution among a number of alternative designs in terms of its cost effectiveness. The probability of the safe reentry and recovery of one to three stranded astronauts is 0.80. The vehicle is symmetrical and lenticular in shape, and exhibits a modest lift-to-drag ratio of 0.5, allowing it to reenter a two-skip trajectory with minimal gravity forces on the astronauts. Attitude control, voice and beacon communication, and impact attenuation are also provided. The vehicle could be delivered in a docked position on the Apollo Applications Program multiple docking adapter.
Relatively simple inexpensive device uses reeled steel cable, is controlled by automotive-type shock absorber, and allows safe descent from burning building. Device is cheap to manufacture and assemble and requires neither skill, special knowledge, or athletic ability to operate. It is reliable and fireproof and can be deployed instantly.
The development is traced of a new federal policy for the support and use of technology. The premises underlying such a policy and forecasts likely future developments are analyzed. The first Presidential message on science and technology is included.
Incentives for broadening the present role of civilian nuclear power to include mobile nuclear power plants that are compact, lightweight, and safe are examined. Specifically discussed is the growing importance of: (1) a new international cargo transportation capability, and (2) the capability for development of resources in previously remote regions of the earth including the oceans and the Arctic. This report surveys present and potential systems (vehicles, remote stations, and machines) that would both provide these capabilities and require enough power to justify using mobile nuclear reactor power plants.
The economic aspects of Federal regulation of airlines are discussed. The problems involved in obtaining capital resources for airline operations and expansion are analyzed. The functions of various agencies and their impact on the economic status of the airlines are explained.
The behavior of the Lyman alpha 1216-A intensity on Mars is presented for a range of atomic hydrogen density distributions below 200 km. Two sets of radiative transfer calculations have been performed. The first is based on spherical geometry and includes the effect of pure absorption of the resonance photons by CO2. The second set is based on the simpler plane parallel geometry and includes the effects of both pure absorption and a varying Doppler width associated with the planetary Lyman alpha line. From the plane parallel solutions, we are able to estimate and account for the effect of a varying Doppler width on our spherical model results. When pure absorption and a varying Doppler width are incorporated in the theory, the maximum change in the Lyman alpha disc intensity is a factor of about 2 over the range of hydrogen density models considered.
Device includes cable wound on reel; special assembly enclosed in fluid medium controls unwinding speed of cable during descent. Device is compact and reliable. It can be rewound quickly because reel disengages from latches when it is turned in opposite direction.
A flexible fin device for mounting on an aircraft to effect spin recovery is described. The device may be selectively deployed to provide a triangular planform of flexible material to provide spin recovery, and retracted for compact storage during non-use. A single flexible fin may be deflected in a specific direction depending on direction of spin rotation, or two flexible fins forming an inverted V configuration may be used. The device is mounted on the underbody of the aircraft.
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The complete radiation field is calculated for scattering layers of various optical thicknesses. Results obtained for Rayleigh and haze scattering are compared. Calculated radiances show differences as large as 23% compared to the approximate scalar theory of radiative transfer, while the same differences are approximately 0.1% for a continental haze phase function. The polarization of reflected and transmitted radiation is given for various optical thicknesses, solar zenith angles, and surface albedos. Two types of neutral points occur for aerosol phase functions. Rayleigh-like neutral points arise from zero polarization that occurs at scattering angles of 0 deg and 180 deg. For Rayleigh phase functions, the position of these points varies with the optical thickness of the scattering layer. Non-Rayleigh neutral points are associated with the zeros of polarization which occur between the end points of the single scattering curve, and are found over a wide range of azimuthal angles.
Portable compact device includes resuscitation, inhalation, and aspiration modes. Device reduces extra time required to carry larger apparatus.
Recent trends and problems in technology assessment are discussed briefly. The Congressional Office of Technology Assessment and its performance are reviewed along with technology assessment activity in the National Science Foundation.
An analysis was made to show the relative effectiveness of streamline external fuel tanks, a fuel tank in the form of a wing mounted in a biplane position, and auxiliary wing panels attached at the wing tips to increase the span as temporary means for increasing the range of a fighter-type airplane. Figures and charts for the various devices considered show the results of calculations of range, duration of flight, and take-off distance for both land base and carrier operation. The results indicated that the wing tip extensions were the most promising of the devices considered.
As a result of the investigation following the January 1967 fire, which took the lives of three astronauts, materials were developed, flight hardware was modified, and test procedures were rewritten in order to establish the framework within which a more effective rescue concept could be developed. Topics discussed include breathing units, improved life support equipment, miniresuscitators, and hazardous tasks during space shuttle launch and landing operations.
Specimens of super-hybrids and advanced fiber composites were subjected to extensive tests to determine their mechanical properties, including impact and thermal fatigue. The super-hybrids were fabricated by a procedure similar to that reported by Chamis et al., (1975). Super-hybrids subjected to 1000 cycles of thermal fatigue from -100 to 300 F retained over 90% of their longitudinal flexural strength and over 75% of their transverse flexural strength; their transverse flexural strength may be as high as 8 times that of a commercially supplied boron/1100-Al composite. The thin specimen Izod longitudinal impact resistance of the super-hybrids was twice that of the boron/110-Al material. Super-hybrids subjected to transverse tensile loads exhibited nonlinear stress-strain relationships. The experimentally determined initial membrane (in-plane) and bending elastic properties of super-hybrids were predicted adequately by linear laminate analysis.
The matrix operator method was used to calculate the polarization of radiation scattered on layers of various optical thicknesses, with results compared for Rayleigh scattering and for scattering from a continental haze. In both cases, there are neutral points arising from the zeros of the polarization of single scattered photons at scattering angles of zero and 180 degrees. The angular position of these Rayleigh-like neutral points (RNP) in the sky shows appreciable variation with the optical thickness of the scattering layer for a Rayleigh phase matrix, but only a small variation for haze L phase matrix. Another type of neutral point exists for non-Rayleigh phase functions that is associated with the zeros of the polarization for single scattering which occurs between the end points of the curve. A comparison of radiances calculated from the complete theory of radiative transfer using Stokes vectors with those obtained from the scalar theory shows that differences of the order of 23% may be obtained for Rayleigh scattering, while the largest difference found for a haze L phase function was of the order of 0.1%.