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  • 1
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    The long term behaviour of Earth orbits and the implications for debris control (1985)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: GEO orbits with inclinations which remain less than 45 degrees are very stable. Although the inclination of the orbital plane may vary as much as 15 degrees over a period of about 50 years, the orbit altitude will always remain within a few hundred kilometers of geosynchronous altitude, GEO orbits with inclinations greater than 45 degrees exhibit remarkable instabilities ir the eccentricity due to gravitational resonance. Over a period of a century the eccentricity can reach such a large value that reentry is a possibility. The combined effects of the Sun, Moon, and oblate Earth play a significant role in determining the lifetime of a GEO transfer orbit. Depending on the initial orientation of the orbital plane with respect to the Sun and Moon, lifetimes may vary from under 6 months to over several hundred years. Transfer orbits with inclinations over 45 degrees show strong instabilities in the perigee altitude resulting in generally short lifetimes of less than a few years. All transfer orbits can be designed to decay within one year if the initial perigee altitude is less than 231 km. However, there are restrictions on orbit plane placement and time of year of launch.
    Keywords: ASTRODYNAMICS
    Type: NASA. Lyndon B. Johnson Space Center Orbital Debris; p 332-348
    Format: text
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  • 2
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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
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  • 3
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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
    Format: application/pdf
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  • 4
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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
    Format: application/pdf
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  • 5
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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
    Format: application/pdf
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  • 6
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    Recursive analytical solution describing artificial satellite motion perturbed by an arbitrary number of zonal terms (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: An analytical first order solution has been developed which describes the motion of an artificial satellite perturbed by an arbitrary number of zonal harmonics of the geopotential. A set of recursive relations for the solution, which was deduced from recursive relations of the geopotential, was derived. The method of solution is based on Von-Zeipel's technique applied to a canonical set of two-body elements in the extended phase space which incorporates the true anomaly as a canonical element. The elements are of Poincare type, that is, they are regular for vanishing eccentricities and inclinations. Numerical results show that this solution is accurate to within a few meters after 500 revolutions.
    Keywords: ASTRODYNAMICS
    Type: Astrodynamics Specialist Conference; Sept. 7-9, 1977; Jackson Hole, WY; US
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  • 7
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    A study of the lifetimes of geosynchronous transfer orbits (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The study concerns the orbit lifetimes of spent upper stages that are used to boost NASA Space Transportation System payloads into geosynchronous transfer orbits. A semi-analytical method of trajectory computation was developed and applied to these particular orbits. It was found that gravitational perturbations of the sun, moon and oblate earth cause large changes in the perigee altitude. The following parameters have a strong influence on orbit lifetimes: Time of year of launch; Inertial orientation of orbital plane; Inclination of orbital plane.
    Keywords: ASTRODYNAMICS
    Type: AAS 79-105 , Astrodynamics 1979; Jun 25, 1979 - Jun 27, 1979; Provincetown, MA
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  • 8
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    An analytical state transition matrix for an orbit perturbed by oblateness (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A new analytical state transition matrix is presented. This transition matrix contains the two-body terms and the secular and short periodic terms due to the J2 oblateness perturbation. The matrix is derived from a satellite theory which uses a set of 8 canonical elements with the true anomaly as the independent variable. This theory was chosen because of its accuracy and concise formulation. It presents no problems concerning the accuracy of the mean motion, which is typical for classical satellite theories. Numerical experiments show the J2 transition matrix to be superior to the simple two-body matrix.
    Keywords: ASTRODYNAMICS
    Type: AIAA PAPER 76-156 , Aerospace Sciences Meeting; Jan 26, 1976 - Jan 28, 1976; Washington, DC
    Format: text
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