Aerospace Engineering > GATE 2018 > Orbital Mechanics
Equation of the trajectory of a typical space object around any planet, in polar coordinates (r, θ) (i.e. a general conic section geometry), is given as follows. (h is angular momentum, μ is gravitational parameter, e is eccentricity, r is radial distance from the planet center, θ is angle between vectors e and r.
A
r=(h2/μ)/(1−e cos θ)
B
r=(h2/μ)/(e−cosθ)
C
r=(h2/μ)/(1+e cos θ)
D
r=(h2/μ)/(e+cos θ)

Correct : c

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Aerospace Engineering GATE 2018 GATE 2018 Question 10 orbital mechanics equation trajectory equation polar coordinates conic section geometry orbit space object trajectory gravitational parameter eccentricity Kepler's orbit equation

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