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Space Engineering I Part I Where are we? Slide 2 Slide 3 Slide 4 Where we going? Slide 5 Where are we relative to what? Slide 6 Johannes Kepler 1571-1630 Slide 7 Issac Newton 1642-1727 Newton's laws of motion and universal gravitation dominated scientists' view of the physical universe for the next three centuries. Newton derived Keplers laws of planetary motion from his mathematical description of gravity, removing the last doubts about the validity of the heliocentric model of the cosmos. Slide 8 Coordinate Systems (X,Y,Z) (R, , ) (R, , ) Origin? Center of Earth Sun or a Star Center of a planetary body Others. Reference Axes Axis of rotation or revolution Earth spin axis Equatorial Plane Plane of the Earths orbit around the Sun Ecliptic Plane Need to pick two axes and then 3 rd one is determined Slide 9 Ecliptic and Equatorial Planes Obliquity of the Ecliptic = 23.44 Vernal Equinox vector - Earth to Sun on March 21st - Planes intersect @ Equinox Slide 10 Inertial Coordinates Slide 11 Relationship between Coordinate Frames Slide 12 a - semi-major axis - right ascension of ascending node e - eccentricity - argument of perigee i - inclination - true anomaly Orbital Elements Slide 13 a is the semimajor axis; b is the semiminor axis; r MAX = r a, r MIN = r p are the maximum and minimum radius-vectors; c is the distance between the focus and the center of the ellipse; e = c/a is eccentricity 2p is the latus rectum (latus = side and rectum = straight) p semilatus rectum or semiparameter A = ab is the area of the ellipse Properties of Orbits Slide 14 Why do we need all this? Launch into desired orbit Launch window, inclination Ground coverage (ground track/swath) LEO/GEO Purpose of mission? Orbital Manoeuvers Feasible trajectories Minimize propulsion required Station keeping Tracking, Prediction Interplanetary Transfers Hyperbolic orbits Changing reference frames Orbital insertion Rendezvous/Proximity Operations Relative motion Orbital dynamics Slide 15 Birds Eye View A 3D Situational Awareness Tool for the Space Station Slide 16 Review of Orbital Elements Perigee 0 Apogee 180 e defines ellipse shape a defines ellipse size v defines satellite angle from perigee Semi-major axis True anomaly (angle) Eccentricity ( 0.0 to 1.0) 90 120 a e v 150 e =0.8 vs e =0.0 Slide 17 Inclination i Inclination (angle) Equatorial Plane ( defined by Earths equator ) Intersection of the equatorial and orbital planes (below) (above) Ascending Node Ascending Node is where a satellite crosses the equatorial plane moving south to north i Slide 18 Right Ascension of the ascending node and Argument of perigee Vernal Equinox Perigee Direction = angle from vernal equinox to ascending node on the equatorial plane = angle from ascending node to perigee on the orbital plane Ascending Node Slide 19 The Six Orbital 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 = Right Ascension (longitude) of the ascending node The angle from the Vernal Equinox vector to the ascending node on the equatorial plane = Argument of perigee The angle measured between the ascending node and perigee Shape, Size, Orientation, and Satellite Location. Slide 20 Computing Orbital Position Mean Anomaly Eccentric Anomaly True Anomaly Mean Motion Slide 21 Two Line Orbital Elements N ASA and NORAD Standard for specifying orbits of Earth-orbiting satellites I SS (ZARYA) 1 25544U 98067A 08264.51782528 .00002182 00000-0 -11606-4 0 2927 2 25544 51.6416 247.4627 0006703 130.5360 325.0288 15.72125391563537 Ref: http://en.wikipedia.org/wiki/Two-line_element_set Slide 22 Equations of Motion Slide 23 Equations of Motion (2) Slide 24 Equations of Motion (3) For a circular orbit, balancing the force of gravity and the centripetal acceleration Since or Conservation of Energy Slide 25 Equations of Motion (4) An orbit is a continually changing balance between potential and kinetic energy Potential Energy Kinetic Energy Using For any Kepler orbit (elliptic, parabolic, hyperbolic or radial), this is the Vis Viva equation Slide 26 P a 3 2 h = 160 n.mi P = 90 minutes High Earth Orbit H = 3444 n.mi P = 4 hours Geosynchronous Orbit h = 19,324 n.mi P = 23 h 56 m 4 s Orbital Period vs. Altitude Slide 27 h = 160n.mi V = 25,300 ft/s High Earth Orbit H = 3444 n.mi V = 18,341 ft/s Geosynchronous Orbit h = 19,324 n.mi V = 10,087 ft/s Orbital Velocity vs. Altitude Slide 28 h = 160 n.mi V = 33,320 ft/s h = 19,324 n.mi V = 5,273 ft/s Geosynchronous Transfer Orbit a = 13,186 n.mi e = 0.726 Orbital Velocity vs. Altitude (Elliptical Orbits) Slide 29 e=0 -- circle e1 -- hyperbola e < 1 Orbit is closed recurring path (elliptical) e > 1 Not an orbit passing trajectory (hyperbolic) Possible Orbital Trajectories Slide 30 Parabolic Trajectories Total Energy = 0 Slide 31 Hyperbolic Trajectories Total Energy > 0 As Slide 32 State Vectors Cartesian x, y, z, and 3D velocity Slide 33 Integrating Multi-Body Dynamics Slide 34 Solar and Sidereal Time The Sun Drifts east in the sky ~1 per day. Rises 0.066 hours later each day. (because the earth is orbiting) The Earth Rotates 360 in 23.934 hours (Celestial or Sidereal Day) Rotates ~361 in 24.000 hours (Noon to Noon or Solar Day) Satellites orbits are aligned to the Sidereal day not the solar day Slide 35 Ground Track Ground tracks drift westward as the Earth rotates below. 360 deg / 24 hrs = 15 deg/hr Slide 36 Perturbations - J2000 Inertial Frame Slide 37 Orbit Perturbations - Atmospheric Drag Effect is to lower the apogee of an elliptical orbit Perigee remains relatively constant Atmospheric density is a function of latitude, solar heating, season, land masses, etc. Drag also depends on spacecraft attitude Slide 38 Orbit Perturbations - Gravitational Potential Spherical Term Zonal Harmonics Tesseral HarmonicsSectorial Harmonics where =Universal Gravitational Constant X Mass of Earth r =Spacecraft Radius Vector from Center of Earth a e =Earth Equatorial Radius P()=Legendre Polynomial Functions =Spacecraft Latitude =Spacecraft Longitude J n = Zonal Harmonic Constants C n,m,S n,m = Tesseral & Sectorial Harmonic Coefficients Only the first 4X4 (n=4, m=4) elements are used in Space Shuttle software. J2 has 1/1000th the effect of the spherical term; all other terms start at 1/1000th of J2s effect. Slide 39 Orbit Perturbations - The J2 Effect h orbit J2 The Earths oblateness causes the most significant perturbation of any of the nonspherical terms. Right Ascension of the Ascending Node, Argument of Perigee and Time since Perigee Passage are affected. Nodal Regression is the most important operationally. Magnitude depends on orbit size (a), shape (e) and inclination (i). Posigrade orbits nodes regress Westward (0 < i < 90) Retrograde orbits nodes regress Eastward (90 < i