Hyperbolic orbit equations
[DOC File]6 - University of Arizona
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Since a beam of light travels at such a high speed, it will be in a shallow hyperbolic orbit around an ordinary massive object like the Sun. Letting r0 denote the closest approach (the perihelion) of the beam to the gravitating body, at which v = vt, we have ... These equations of motion describe the paths of light rays in a spherically ...
[DOC File]PHYS 228 Astronomy & Astrophysics - Widener University
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Sidereal period- time taken by planet to complete one orbit w/ respect to stars. Equations relating synodic and sidereal periods of a planet: Let S = synodic period of planet, P = sidereal period of planet, E = sidereal period of Earth = 365.26 d ... hyperbolic orbits PHYS 228 Astronomy & Astrophysics. Lecture Notes from Zeilik et al. Chap. 3 ...
[DOC File]ROCKET EQUATIONS
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HYPERBOLIC EXCESS VELOCITY. V = V — Ve. Once beyond the influence of the star, a ship will cruise indefinately. at the hyperbolic excess velocity in aproximately a straight line. RELATIVISITIC MOTION = 1 / sqrt ( 1— ((v2) / (c2))) For two inertial (unaccelerated) frames of reference, if frame S' is moving with respect
[DOC File]Astrodynamics and Mission Geometry:
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Hohmann transfer orbit Hyperbolic transfer orbit Semi-major axis, a 1.262 AU 1.89*108 km 1 AU 1.49*108 km Transfer orbit energy, En -0.396 (AU/TU) 2 0.5 (AU/TU) 2 Velocity at transfer orbit perigee, V1 1.099 AU/TU 32.7km/s 1.73 AU/TU 51.6 km/s Velocity at transfer orbit arrival, V2 0.721 AU/TU 21.5 km/s 1.52 AU/TU 45.3 km/s Velocity change from ...
[DOC File]Relating the Turn Angle to the Change in Longitude
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Utilizing this information, the eccentricity of the hyperbolic orbit can be found using Equations (1) and (2), and defining the angle β in Figure 10: (1) (2) The point in space in which the hyperbolic trajectory passes closest to the planet is known as periapsis. An imaginary line, known as the line of apsides, may be drawn from the center of ...
[DOC File]Scattering Cross Sections - Texas Tech Physics & Astronomy
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Therefore if the angle can be solved for, then the angle θ will be known. From Equation 7 the angular change of the orbit in the central field problem is equal to the angle in Figure 1.2. The integral will be from rmin to , since the orbit is of a hyperbolic form. The value rmin is as stated previously the root of the radical in Equation 4.
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