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Example Orbital Elements. Consider the following inertial radius and velocity vectors of a spacecraft measured at t = 0: ri(0) v(0) = = {-4777.8, 4862.6; 1760.13 km {-6.7782, -4.8929, 0.9174} km/s (77a) (77b) Determine all the orbital elements and plot the orbit in 3 dimensions. Also obtain Tp, Ta, Up and va. Given μ = μ = 3.986004 × 10¹4 m³/s².

Example Orbital Elements. Consider the following inertial radius and velocity vectors of a spacecraft measured at t = 0: ri(0) v(0) = = {-4777.8, 4862.6; 1760.13 km {-6.7782, -4.8929, 0.9174} km/s (77a) (77b) Determine all the orbital elements and plot the orbit in 3 dimensions. Also obtain Tp, Ta, Up and va. Given μ = μ = 3.986004 × 10¹4 m³/s².

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: Example Orbital Elements. Consider the following inertial radius and velocity vectors of a spacecraft measured at t = 0: rz(0) = {-4777.8, 4862.6; 1760.1}T km vž(0) (77a) {-6.7782, –4.8929, 0.9174}T km/s (77b) Determine all the orbital elements and plot the orbit in 3 dimensions. Also obtain rp, ra, V, and va. Given µ = µe = 3.986004 × 1014 m³ /s².
Transcribed Image Text:: Example Orbital Elements. Consider the following inertial radius and velocity vectors of a spacecraft measured at t = 0: rz(0) = {-4777.8, 4862.6; 1760.1}T km vž(0) (77a) {-6.7782, –4.8929, 0.9174}T km/s (77b) Determine all the orbital elements and plot the orbit in 3 dimensions. Also obtain rp, ra, V, and va. Given µ = µe = 3.986004 × 1014 m³ /s².
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