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  • 1
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    Effects of flight instrumentation errors on the estimation of aircraft stability and control derivatives (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: An error analysis program based on an output error estimation method was used to evaluate the effects of sensor and instrumentation errors on the estimation of aircraft stability and control derivatives. A Monte Carlo analysis was performed using simulated flight data for a high performance military aircraft, a large commercial transport, and a small general aviation aircraft for typical cruise flight conditions. The effects of varying the input sequence and combinations of the sensor and instrumentation errors were investigated. The results indicate that both the parameter accuracy and the corresponding measurement trajectory fit error can be significantly affected. Of the error sources considered, instrumentation lags and control measurement errors were found to be most significant.
    Keywords: AERODYNAMICS
    Type: Parameter Estimation Tech. and Appl. in Aircraft Flight Testing; p 261-280
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    A Monte Carlo analysis of the effects of instrumentation errors on aircraft parameter identification (1975)
    In:  CASI
    Details
    Publication Date: 2012-05-22
    Description: An output error estimation algorithm was used to evaluate the effects of both static and dynamic instrumentation errors on the estimation of aircraft stability and control parameters. A Monte Carlo analysis, using simulated cruise flight data, was performed for a high performance military aircraft, a large commercial transport, and a small general-aviation aircraft. The effects of variations in the information content of the flight data, resulting from two different choices of control input maneuvers, were also determined. The results indicate that unmodeled instrumentation errors can cause inaccuracies in the estimated parameters which are comparable to their nominal values. Control input errors and angular accelerometer lags were found to be most significant of the instrumentation errors evaluated, and the perturbations they produce are much larger than those arising from the combined effects of static errors and white noise in the output response measurements.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AGARD Methods for Aircraft State and Parameter Identification; 19 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Influence of solar radiation pressure on orbital eccentricity of a gravity-gradient- oriented lenticular satellite (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Solar radiation pressure influence on orbital eccentricity of gravity gradient oriented lenticular satellite
    Keywords: SPACE SCIENCES
    Type: NASA-TN-D-2715
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Heat-transfer measurements in regions of flow separation and reattachment on two axisymmetric models at mach numbers from 2.65 to 4.50 (1961)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Heat transfer measurements in regions of flow separation and reattachment on two axisymmetric reentry models at Mach 2.65 to 4.50
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-596
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Influence of solar radiation pressure on orbital eccentricity of a gravity-gradient oriented lenticular satellite (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Solar radiation pressure effect on orbital eccentricity of gravity gradient oriented lenticular satellite
    Keywords: SPACE RADIATION
    Type: NASA-TM-X-56549
    Format: application/pdf
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  • 6
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    Comparison of analytical and flight test identified aerodynamic derivatives for a tandem-rotor transport helicopter (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Flight tests for verifying an analytical aerodynamic derivative model of a CH-47 helicopter were conducted for low cruise speeds and transition to hover portions of curved, decelerating landing approach trajectories. All testing was performed on a closed loop basis with the stability augmentation system of the helicopter operating, and response data were obtained using both manual and computer generated input maneuvers. The results indicate some differences between the measured response time histories and those predicted by both analytical and flight test identified derivatives. With some exceptions the discrepancies are not severe, and the overall agreement between the measured and computed time histories is reasonably good. No adverse effects attributable to closed loop testing were noted, and the use of computer generated inputs proved to be superior to manual ones.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-1581 , L-13228
    Format: application/pdf
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  • 7
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    Simulation of a navigator algorithm for a low-cost GPS receiver (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The analytical structure of an existing navigator algorithm for a low cost global positioning system receiver is described in detail to facilitate its implementation on in-house digital computers and real-time simulators. The material presented includes a simulation of GPS pseudorange measurements, based on a two-body representation of the NAVSTAR spacecraft orbits, and a four component model of the receiver bias errors. A simpler test for loss of pseudorange measurements due to spacecraft shielding is also noted.
    Keywords: AIRCRAFT COMMUNICATIONS AND NAVIGATION
    Type: NASA-TM-81778
    Format: application/pdf
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  • 8
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    Effect of environmental torques on short-term attitude prediction for a rolling-wheel spacecraft in a sun-synchronous orbit (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A numerical evaluation and an analysis of the effects of environmental disturbance torques on the attitude of a hexagonal cylinder rolling wheel spacecraft were performed. The resulting perturbations caused by five such torques were found to be very small and exhibited linearity such that linearized equations of motion yielded accurate results over short periods and the separate perturbations contributed by each torque were additive in the sense of superposition. Linearity of the torque perturbations was not affected by moderate system design changes and persisted for torque-to-angular momentum ratios up to 100 times the nominal expected value. As these conditions include many possible applications, similar linear behavior might be anticipated for other rolling-wheel spacecraft.
    Keywords: SPACE SCIENCES
    Type: NASA-TN-D-6583 , L-7359
    Format: application/pdf
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  • 9
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    Monte Carlo analysis of inaccuracies in estimated aircraft parameters caused by unmodeled flight instrumentation errors (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An output error estimation algorithm was used to evaluate the effects of both static and dynamic instrumentation errors on the estimation of aircraft stability and control parameters. A Monte Carlo error analysis, using simulated cruise flight data, was performed for a high-performance military aircraft, a large commercial transport, and a small general aviation aircraft. The results indicate that unmodeled instrumentation errors can cause inaccuracies in the estimated parameters which are comparable to their nominal values. However, the corresponding perturbations to the estimated output response trajectories and characteristics equation pole locations appear to be relatively small. Control input errors and dynamic lags were found to be in the most significant of the error sources evaluated.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TN-D-7712 , L-9411
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    VALT parameter identification flight test (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The paper describes a method of establishing the accuracy of previously developed analytical models of research vehicles for a program for developing avionics technology for VTOL aircraft. The research vehicle is a Boeing-Vertol CH-47 tandem rotor transport helicopter equipped with a fly-by-wire control system. The specialized flight test was designed to take into account the presence of winds at flight conditions from hover through transition to cruise. The test provided data to obtain estimates of derivatives by parameter identification.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: European Rotorcraft and Powered Lift Aircraft Forum; Sept. 13-15, 1978; Stresa; Italy
    Format: text
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    NASA TECHNICAL REPORTS
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