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  • SPACE VEHICLES  (161)
  • AIRCRAFT  (113)
  • 1980-1984
  • 1970-1974  (274)
  • 1950-1954
  • 1973  (147)
  • 1970  (127)
Collection
Keywords
Years
  • 1980-1984
  • 1970-1974  (274)
  • 1950-1954
Year
  • 1
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    The applications of satellites to communications, navigation and surveillance for aircraft operating over the contiguous United States (1970)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The objective was to determine on a priority basis the satellite applications to communications, navigation, and surveillance requirements for aircraft operating beyond 1975 over the contiguous United States and adjacent oceanic transition regions, and to determine if and how satellite technology can meet these requirements in a reliable, efficient, and economical manner. Major results and conclusions are as follows: (1) The satellite applications of greatest importance are surveillance and rapid collision warning communications; and (2) The necessary technology is available as demonstrated by an attractive system concept.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-132794 , TRW-14671-6009-R0-00
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    AE-C attitude determination and control prelaunch analysis and operations plan (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A description of attitude control support being supplied by the Mission and Data Operations Directorate is presented. Included are descriptions of the computer programs being used to support the missions for attitude determination, prediction, and control. In addition, descriptions of the operating procedures which will be used to accomplish mission objectives are provided.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-70535 , X-581-73-369
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Evaluation of a metal shear web selectively reinforced with filamentary composites for space shuttle application. Phase 2: summary report: Shear web component fabrication (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The fabrication of two shear web test elements and three large scale shear web test components are reported. In addition, the fabrication of test fixtures for the elements and components is described. The center-loaded beam test fixtures were configured to have a test side and a dummy or permanent side. The test fixtures were fabricated from standard extruded aluminum sections and plates and were designed to be reuseable.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-132321 , D180-15323
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Development and in-flight performance of the Mariner 9 spacecraft propulsion system (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: On November 14, 1971, Mariner 9 was decelerated into orbit about Mars by a 1334 N (300 lbf) liquid bipropellant propulsion system. This paper describes and summarizes the development and in-flight performance of this pressure-fed, nitrogen tetroxide/monomethyl hydrazine bipropellant system. The design of all Mariner propulsion subsystems has been predicted upon the premise that simplicity of approach, coupled with thorough qualification and margin-limits testing, is the key to cost-effective reliability. The qualification test program and analytical modeling are also discussed. Since the propulsion subsystem is modular in nature, it was completely checked, serviced, and tested independent of the spacecraft. Proper prediction of in-flight performance required the development of three significant modeling tools to predict and account for nitrogen saturation of the propellant during the six-month coast period and to predict and statistically analyze in-flight data.
    Keywords: SPACE VEHICLES
    Type: Astronautical research 1972; Oct 08, 1972 - Oct 15, 1972; Vienna; Austria
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Nonlinear aerodynamic characteristics of sounding rockets (1970)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Sounding rockets nonlinear aerodynamic characteristics from full scale and supersonic wind tunnel free flight data, using wobble analysis
    Keywords: SPACE VEHICLES
    Type: AIAA PAPER 70-1383 , SOUNDING ROCKET TECHNOLOGY CONFERENCE; Dec 07, 1970 - Dec 09, 1970; WILLIAMSBURG, VA
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Action on mission evaluation and flight anomalies (1970)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Apollo Program mission evaluation and flight anomalies team to indentify and understand unforeseen peculiarities and systems problems during spacecraft mission
    Keywords: SPACE VEHICLES
    Type: ; DIOTEKHNIKA (
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Introduction (1970)
    In:  CASI
    Details
    Publication Date: 2012-05-22
    Description: Saturn launch vehicle configurations, stages, and guidance and control systems, and wind effects on vehicle design
    Keywords: SPACE VEHICLES
    Type: AGARD WIND EFFECTS ON LAUNCH VEHICLES FEB. 1970; P 13-32
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Wind tunnel investigation of a large-scale 25 deg swept-wing jet transport model with an external blowing triple-slotted flap (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation has been conducted to determine the aerodynamic characteristics of a large-scale subsonic jet transport model with an externally blown triple-slotted flap. The lift of the model was augmented by the turbofan engine exhaust impingement on the flap surface. The model had a 25 deg swept wing of aspect ratio 7.28 and four turbofan engines. The model was tested with two flap extents. One extended from 0.11 to 1.00 of the wing semispan, and the other extended from 0.11 to 0.75 of the wing semispan with a single-slotted aileron from 0.75 to 1.00 of the wing semispan. The results were obtained for several flap deflections with and without the horizontal tail at gross thrust coefficients from 0 to 4.0. Longitudinal and lateral data are presented with three and four engines operating.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62197
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Acoustic characteristics of a large-scale augmentor wing model at forward speed (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The augmentor wing concept is being studied as one means of attaining short takeoff and landing (STOL) performance in turbofan powered aircraft. Because of the stringent noise requirements for STOL operation, the acoustics of the augmentor wing are undergoing extensive research. The results of a wind tunnel investigation of a large-scale swept augmentor model at forward speed are presented. The augmentor was not acoustically treated, although the compressor supplying the high pressure primary air was treated to allow the measurement of only the augmentor noise. Installing the augmentor flap and shroud on the slot primary nozzle caused the acoustic dependence on jet velocity to change from eighth power to sixth power. Deflecting the augmentor at constant power increased the perceived noise level in the forward quadrant. The effect of airspeed was small. A small aft shift in perceived noise directivity was experienced with no significant change in sound power. Sealing the lower augmentor slot at a flap deflection of 70 deg reduced the perceived noise level in the aft quadrant. The seal prevented noise from propagating through the slot.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-2940 , A-4964
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Point and path performance of light aircraft: A review and analysis (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The literature on methods for predicting the performance of light aircraft is reviewed. The methods discussed in the review extend from the classical instantaneous maximum or minimum technique to techniques for generating mathematically optimum flight paths. Classical point performance techniques are shown to be adequate in many cases but their accuracies are compromised by the need to use simple lift, drag, and thrust relations in order to get closed form solutions. Also the investigation of the effect of changes in weight, altitude, configuration, etc. involves many essentially repetitive calculations. Accordingly, computer programs are provided which can fit arbitrary drag polars and power curves with very high precision and which can then use the resulting fits to compute the performance under the assumption that the aircraft is not accelerating.
    Keywords: AIRCRAFT
    Type: NASA-CR-2272
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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