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    Orbital Mechanics II SNS 311: INTRO. & G. Revision SNS 206

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    ahmed mohamed hassan
    This document provides an overview of Orbital Mechanics II (SNS311), which builds upon Orbital Mechanics I (SNS206). SNS311 covers additional topics like the restricted three-body problem, orbital position frames, orbital elements, and the effect of Earth's oblateness. The six Keplerian orbital elements (semimajor axis, eccentricity, inclination, right ascension of the ascending node, argument of perigee, and true anomaly) define the size, shape, orientation, and location of a satellite's orbit. Examples of orbital elements for the International Space Station are provided.

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    Orbital Mechanics II SNS 311: INTRO. & G. Revision SNS 206

    Uploaded by

    ahmed mohamed hassan
    35 views24 pages
    This document provides an overview of Orbital Mechanics II (SNS311), which builds upon Orbital Mechanics I (SNS206). SNS311 covers additional topics like the restricted three-body problem, orbital position frames, orbital elements, and the effect of Earth's oblateness. The six Keplerian orbital elements (semimajor axis, eccentricity, inclination, right ascension of the ascending node, argument of perigee, and true anomaly) define the size, shape, orientation, and location of a satellite's orbit. Examples of orbital elements for the International Space Station are provided.

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    SNS311-L1-f1

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    This document provides an overview of Orbital Mechanics II (SNS311), which builds upon Orbital Mechanics I (SNS206). SNS311 covers additional topics like the restricted three-body problem, orbital position frames, orbital elements, and the effect of Earth's oblateness. The six Keplerian orbital elements (semimajor axis, eccentricity, inclination, right ascension of the ascending node, argument of perigee, and true anomaly) define the size, shape, orientation, and location of a satellite's orbit. Examples of orbital elements for the International Space Station are provided.

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    35 views24 pages

    Orbital Mechanics II SNS 311: INTRO. & G. Revision SNS 206

    Uploaded by

    ahmed mohamed hassan
    This document provides an overview of Orbital Mechanics II (SNS311), which builds upon Orbital Mechanics I (SNS206). SNS311 covers additional topics like the restricted three-body problem, orbital position frames, orbital elements, and the effect of Earth's oblateness. The six Keplerian orbital elements (semimajor axis, eccentricity, inclination, right ascension of the ascending node, argument of perigee, and true anomaly) define the size, shape, orientation, and location of a satellite's orbit. Examples of orbital elements for the International Space Station are provided.

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    Orbital Mechanics II

    SNS 311 1
    LECTURE
    INTRO. & G. Revision SNS 206

    Osama M. Shalabiea
    Course Data

    Course Name
    “ Orbital Mechanics 2 ”

    Course Code
    “ SNS311 ”

    Credit Hours
    “3 Hours”
    Course Lecture Hours: 2 Hours
    Course Tutorial Hours: 2 Hour
    Orb. Mech. I (SNS206)
    Course Syllabus SNS206
    Dynamics of point masses
    Equation of motion of two-body problem in inertial frame
    Angular momentum
    Energy low
    Circular orbits
    Elliptical orbits
    Parabolic trajectories
    Hyperbolic trajectories
    Earth-centered inertial frame (XYZ); earth-centered non-inertial X0 Y0 Z0 frame
    embedded in and rotating with the earth; and a non-inertial, topocentric-horizon
    frame xyz attached to a point O on the earth’s surface.
    Orb. Mech. II (SNS311)
    Course Syllabus SNS311
    - Perifocal plane -Lagrange Coefficients
    - Restricted Three-body problem
    - Orbital Position
    - Geocentric Right Ascension – Declination Frame
    - Geocentric Equatorial Frame
    -Orbital Elements
    -Coordinate Transformation
    - Effect of Earth Oblateness
    Keplerian Elements e, a, and v (3 of 6)
    e 150°
    120°
    90°
    Eccentricity
    (0.0 to 1.0)
    v
    True anomaly
    (angle)
    Apogee a Perigee
    180° 0°
    Semi-major
    axis
    (nm or km)
    e=0.8 vrs e=0.0

    Apo/Peri gee – Earth e defines ellipse shape


    Apo/Peri lune – Moon
    Apo/Peri helion – Sun a defines ellipse size
    Apo/Peri apsis – non-specific v defines satellite angle from perigee
    Inclination i (4th Keplerian Element)

    Intersection of the

    i
    equatorial and
    (above)
    Inclination
    orbital planes (angle)

    (below)
    Ascending
    Node
    Equatorial Plane
    ( defined by Earth’s equator )

    Sample inclinations
    Ascending Node is where a 0° -- Geostationary
    satellite crosses the equatorial 52° -- ISS
    plane moving south to north 98° -- Mapping
    Right Ascension [1] of the ascending node Ω
    and Argument of perigee ω (5th and 6th Elements)

    Ω = angle from
    vernal equinox to
    ascending node on
    the equatorial plane
    Perigee Direction
    ω = angle from
    ascending node to
    perigee on the
    orbital plane

    ω
    Ω
    Ascending
    Node

    [1]Right Ascension is the astronomical


    Vernal Equinox term for celestial (star) longitude.
    The Six Keplerian Elements
    a = Semi-major axis (usually in
    kilometers or nautical miles)

    e = Eccentricity (of the elliptical


    orbit)

    v = True anomaly The angle


    between perigee and satellite in
    the orbital plane at a specific time

    i = Inclination The angle between


    the orbital and equatorial planes
    Ω = Right Ascension (longitude)
    of the ascending node The
    angle from the Vernal Equinox
    vector to the ascending node on
    the equatorial plane

    w = Argument of perigee The


    Shape, Size,
    angle measured between the
    Orientation,
    ascending node and perigee and Satellite
    Location.
    Sample Keplerian Elements (ISS)
    TWO LINE MEAN ELEMENT SET - ISS
    1 25544U 98067A 09061.52440963 .00010596 00000-0 82463-4 0 9009
    2 25544 51.6398 133.2909 0009235 79.9705 280.2498 15.71202711 29176

    Satellite: ISS
    Catalog Number: 25544
    Epoch time: 09061.52440963 = yrday.fracday
    Element set: 900
    Inclination: 51.6398 deg
    RA of ascending node: 133.2909 deg
    Eccentricity: .0009235
    Arg of perigee: 79.9705 deg
    Mean anomaly: 280.2498 deg
    Mean motion: 15.71202711 rev/day (semi-major axis derivable from this)
    Decay rate: 1.05960E-04 rev/day^2
    Epoch rev: 2917
    Checksum: 315
    Thanks For Attention
    Thanks For Attention

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