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  • Other Sources  (4,627)
  • LUNAR AND PLANETARY EXPLORATION  (3,679)
  • AIRCRAFT DESIGN, TESTING AND PERFORMANCE  (948)
  • Chemical Engineering
  • 1975-1979  (4,627)
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  • 1
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    Some unique meteorites found in Antarctica and their relation to asteroids (1979)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: Two unique meteorites were identified by means of a mineralogical examination of the smaller-sized Yamato achondrites. Yamato-74130 is the most iron-rich ureilite with Na, Cr-rich augite instead of pigeonite. Yamato-74160 was extensively recrystallized, but the composition and proportion of olivine, orthopyroxene, augite, and plagioclase is consistent with LL7 chondrites. ALHA77005 is a unique achondrite with olivine, possibly three pyroxene assemblages, and maskelynite. These meteorites provide evidence that there may be other 'thermalized' asteroids than the howardite parent body. Detailed petrologic descriptions of the unique achondrites, recrystallized diogenite Yamato-74013, and the rapidly cooled eucrite Yamato-74450 with pyroxene phenocrysts are given. It is inferred from the bulk chemistry and the mineralogical reexamination of Yamato-75028 that it is composed of the H5-type clasts and chondrule-rich H(L)3-like matrix with the H5 fragments. A close relationship in the collisional evolution of some asteroids with these materials is inferred.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: National Institute of Polar Research, Memoirs (ISSN 0386-0744); 15, 1; 54-76
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  • 2
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    The maturation of lunar dust grains (1975)
    In:  CASI
    Details
    Publication Date: 2005-02-24
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Res. in the Space Sci., Vol. 2, No. 1; 3 p
    Format: text
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  • 3
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    Application of numerical optimization techniques to high speed inlet bleed system design (1977)
    In:  CASI
    Details
    Publication Date: 2006-01-10
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Inlet Workshop; p 280-287
    Format: text
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  • 4
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    Selected topics from the structural acoustics program for the B-1 aircraft (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-02
    Description: The major elements of the structural acoustics program for the B-1 aircraft are considered. Acoustic pressures measured at 280 sites on the surface of the vehicle were used to develop pressure models for a resizing of airframe components for aircraft No. 4 (A/C4). Acoustical fatigue design data for two dynamically complex structural configurations were acquired in laboratory programs, the conceptions for and executions of which detailed significant departures from the conventional. Design requirements for mechanical fasteners for configurations other than these two made use of analytical extensions of regrettably limited available information.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Shock and Vibration Inform. Center The Shock and Vibration Bull., Pt. 3; p 55-68
    Format: text
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  • 5
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    Meteoroid protection for the Comet Halley probe (1979)
    In:  CASI
    Details
    Publication Date: 2006-06-26
    Description: The high closing speed of 57km/s between the spacecraft and Halley poses special problems in the design of the required meteoroid protection. A double wall structure with a total thickness equal to 0.1 to 1 times the diameter of the largest meteoroid encountered is sufficient to stop that meteoroid. However, the unusually high number of meteoroid impacts on the Halley probe will cause significant erosion of the outer wall so that failure of the second wall is more likely to occur from a small meteoroid passing through a previously created hole in the outer wall and then penetrating the second wall. Calculations of the shielding required based on this failure mode, show that a double wall structure must actually have a total thickness 1.2 to 7.3 times the diameter of the largest meteoroid encountered, depending on the size distribution of the meteoroids.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: ESA Comet Halley Micrometeoroid Hazard Workshop; p 73-76
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  • 6
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    Vibration investigation of a large transport helicopter (1977)
    In:  CASI
    Details
    Publication Date: 2004-11-29
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Shock and Vibration Inform. Center The Shock and Vibration Bull. Part 3 Sept. 1977; p 139-147
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  • 7
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    A new formulation for the epsilon method applied to the minimum-time-to-climb problem (1978)
    In:  CASI
    Details
    Publication Date: 2006-03-02
    Description: Balakrishnan's epsilon technique is used to compute minimum-time profiles for the F-104 airplane. This technique differs from the classical gradient method in that a quadratic penalty on the error in satisfying the equation of motion is included in the cost function to be minimized as a means of eliminating the requirement of satisfying the equations of motion. Although the number of unknown independent functions is increased to include the state variables, the evaluation of the gradient of the cost function is simplified, resulting in considerable computational savings, thereby making it appear feasible to use the epsilon method for real-time application.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA, Washington Fourth Inter-Center Control Systems Conf.; p 423-434
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  • 8
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    In-flight three-dimensional boundary layer and wake measurements from a swept supercritical wing (1978)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: Three-dimensional boundary layer and wake velocity profiles were measured in flight on the supercritical wing of the F-111 transonic aircraft technology aircraft. These data, along with pressure distributions, were obtained to establish a data base with which data obtained by three-dimensional analytical techniques could be correlated. Only a brief summary of the total data base is given. The data presented represented one chord station at a wing leading-edge sweep angle of 26 deg. They cover an angle of attack range from 6 degs to 9 degs at free-stream Mach numbers from 0.85 to 0.90. A brief discussion of the techniques used to obtain the boundary layer and wake profiles is included.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 643-655
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  • 9
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    A fast DFT algorithm using complex integer transforms (1978)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: Winograd's algorithm for computing the discrete Fourier transform is extended considerably for certain large transform lengths. This is accomplished by performing the cyclic convolution, required by Winograd's method, by a fast transform over certain complex integer fields. This algorithm requires fewer multiplications than either the standard fast Fourier transform or Winograd's more conventional algorithms.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: The Deep Space Network; p 134-140
    Format: text
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  • 10
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    Proportioning the airplane for lateral stability (1976)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: Proportioning for lateral aircraft control included: (1) directional stability (slope of curve of yawing moment coefficient against sideslip), and (2) effective dihedral factor (slope of curve of rolling moment coefficient against sideslip). Basic forces influencing the directional stability of aircraft are indicated. Propeller side force, basic fuselage yaw, and vertical tail side force contributed to yaw moment about center of gravity.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Collected Works of Charles J. Donlan; 6 p
    Format: text
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