Orbital Parameters
This feature contains all the information needed to define the spacecraft orbit.
Select an Orbit type among Elliptical (default), Equatorial elliptical, Circular, and Equatorial circular.
Elliptical is the most general option. It defines the orbit of the spacecraft from the six Keplerian elements as in Figure 6-4:
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Semimajor axis, a (SI unit m, default value otl.R_planet+1000[km] assuming otl is the interface name,
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Eccentricity, e (dimensionless, default value 0) which is a value between 0 (included) and 1 (excluded),
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Inclination, i (SI unit radians, default value 0 deg), which is a positive angle between 0 and 180°,
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The ascending node can be defined either from the Longitude of ascending node, Ω (SI unit radians, default value 0 deg), or from the Local time at ascending node, tΩ (SI unit seconds, default value 0 h)
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Argument of periapsis, ω (SI unit radians, default value 0 deg), and
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True anomaly at start time, ν0 (SI unit radians, default value 0 deg).
Figure 6-4: Definition of Keplerian elements.
Equatorial elliptical is similar to the Elliptical option with Inclination, i, and the Longitude of Ascending Node, Ω, are zero. In this configuration the Argument of periapsis is referred as Longitude of periapsis.
The Circular option is another option with four orbital parameters. The Eccentricity, e, and the Argument of periapsis, ω, are zero. In this configuration the Radius, R, is equivalent to the semi-major axis, and the True anomaly at start time, ν0 is referred as the Argument of latitude at start time.
The Equatorial circular choice is the simplest option with only two parameters: the Radius, R, and True anomaly at start time, ν0. true longitude (SI unit rad, default value 0 deg).
Location in User Interface
Context Menus
Orbital Thermal Loads>Orbital Parameters
Ribbon
Physics tab with Orbital Thermal Loads selected:
Global>Orbital Parameters