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  • 1
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    A singularity free analytical solution of artificial satellite motion with drag (1978)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: An analytical satellite theory based on the regular, canonical Poincare-Similar (PS phi) elements is described along with an accurate density model which can be implemented into the drag theory. A computationally efficient manner in which to expand the equations of motion into a fourier series is discussed.
    Keywords: ASTRODYNAMICS
    Type: NASA. Goddard Space Flight Center Flight Mechanics(Estimation Theory Symp.; p 33-36
    Format: text
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  • 2
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    Orbit decay analysis of STS upper stage boosters (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An orbit decay analysis of the space transportation system upper stage boosters is presented. An overview of the computer trajectory programs, DSTROB, algorithm is presented. Atmospheric drag and perturbation models are described. The development of launch windows, such that the transfer orbit will decay within two years, is discussed. A study of the lifetimes of geosynchronous transfer orbits is presented.
    Keywords: ASTRODYNAMICS
    Type: NASA-CR-160385 , ACM-TR-119
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  • 3
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    The method of averages applied to the KS differential equations (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A new approach for the solution of artificial satellite trajectory problems is proposed. The basic idea is to apply an analytical solution method (the method of averages) to an appropriate formulation of the orbital mechanics equations of motion (the KS-element differential equations). The result is a set of transformed equations of motion that are more amenable to numerical solution.
    Keywords: NUMERICAL ANALYSIS
    Type: NASA-CR-151607 , ACM-TR-109
    Format: application/pdf
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  • 4
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    Atmospheric density models (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An atmospheric model developed by Jacchia, quite accurate but requiring a large amount of computer storage and execution time, was found to be ill-suited for the space shuttle onboard program. The development of a simple atmospheric density model to simulate the Jacchia model was studied. Required characteristics including variation with solar activity, diurnal variation, variation with geomagnetic activity, semiannual variation, and variation with height were met by the new atmospheric density model.
    Keywords: GEOPHYSICS
    Type: NASA-CR-151604 , ACM-TR-106
    Format: application/pdf
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  • 5
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    A singularity free analytical solution of artificial satellite motion with drag (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The connection between the existing Delaunay-Similar and Poincare-Similar satellite theories in the true anomaly version is outlined for the J(2) perturbation and the new drag approach. An overall description of the concept of the approach is given while the necessary expansions and the procedure to arrive at the computer program for the canonical forces is delineated. The procedure for the analytical integration of these developed equations is described. In addition, some numerical results are given. The computer program for the algebraic multiplication of the Fourier series which creates the FORTRAN coding in an automatic manner is described and documented.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA-CR-151601 , ACM-TR-103
    Format: application/pdf
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  • 6
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    An Analytical State Transition Matrix for Orbits Perturbed by an Oblate Spheroid (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analytical state transition matrix and its inverse, which include the short period and secular effects of the second zonal harmonic, were developed from the nonsingular PS satellite theory. The fact that the independent variable in the PS theory is not time is in no respect disadvantageous, since any explicit analytical solution must be expressed in the true or eccentric anomaly. This is shown to be the case for the simple conic matrix. The PS theory allows for a concise, accurate, and algorithmically simple state transition matrix. The improvement over the conic matrix ranges from 2 to 4 digits accuracy.
    Keywords: ASTRODYNAMICS
    Type: NASA-CR-151602 , ACM-TR-104
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  • 7
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    An atmospheric density model for application in analytical satellite theories (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An atmospheric density model is developed and the implications of the model on the analytical drag theory are discussed. The ballistic number and coefficient of drag are assumed constant.
    Keywords: ASTRODYNAMICS
    Type: NASA-CR-151605 , ACM-TR-107
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  • 8
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    Noise measurements for a twin-engine commercial jet aircraft during 3 deg approaches and level flyovers (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Noise measurements have been made with a twin-engine commercial jet aircraft making 3 deg approaches and level flyovers. The flight-test data showed that, in the standard 3 deg approach configuration with 40 deg flaps, effective perceived noise level (EPNL) had a value of 109.5 effective perceived noise decibels (EPNdB). This result was in agreement with unpublished data obtained with the same type of aircraft during noise certification tests; the 3 deg approaches made with 30 deg flaps and slightly reduced thrust reduced the EPNL value by 1 EPNdB. Extended center-line noise determined during the 3 deg approaches with 40 deg flaps showed that the maximum reference A-weighted sound pressure level (LA,max)ref varied from 100.0 A-weighted decibels 2.01 km (108 n. mi.) from the threshold to 87.4 db(A) at 6.12 km (3.30 n. mi.) from the threshold. These test values were about 3 db(A) higher than estimates used for comparison. The test data along the extended center line during approaches with 30 deg flaps were 1 db(A) lower than those for approaches with 40 deg flaps. Flight-test data correlating (LA,max)ref with thrust at altitudes of 122 m (400 ft) and 610 m (2000 ft) were in agreement with reference data used for comparison.
    Keywords: ACOUSTICS
    Type: NASA-TM-X-3387 , L-10780
    Format: application/pdf
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  • 9
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    The development of the Poincare-similar elements with true anomaly as the independent variable (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: In reference 1, the Hamiltonian of the unperturbed two-body problem in extended phase space is established. Depending on the type of time transformation, eight canonical elements were developed with the true anomaly or the eccentric anomaly as the independent variable. These two new sets, DS(phi) and DS(u), however contain singularities for small eccentricities and inclinations. In reference 2, these singularities are removed by a transformation from DS(u) to eight canonical PS(u) elements. In reference 3, the DS(phi) variables are transformed to the PS(phi) elements to remove the singularities. However, no direct relation was established between the eight canonical PS(phi) elements and the Cartesian coordinates. It is the purpose of this report to establish those relations and to develop the perturbed equations of motion in the PS(phi) space. This report also demonstrates the accuracy of this new set when it is applied to numerical orbit prediction problems.
    Keywords: NUMERICAL ANALYSIS
    Type: NASA-TM-79454 , JSC-11550 , JSC-IN-76-FM-60
    Format: application/pdf
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  • 10
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    Baseline measurement of the noise generated by a short-to-medium range jet transport flying standard ILS approaches and level flyovers (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of baseline noise flight tests are presented. Data are given for a point 1.85 kilometers (1.0 nautical mile) from the runway threshold, and experimental results of level flyover noise at altitudes of 122 meters (400 feet) and 610 meters (2,000 feet) are also shown for several different power levels. The experimental data are compared with data from other sources and reasonable agreement is noted. A description of the test technique, instrumentation, and data analysis methods is included.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-72760
    Format: application/pdf
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