Click or drag to resize

SpecializedOrbitSolverCreateCriticallyInclinedOrbit Method

Creates a critically-inclined orbit with an argument of periapsis that remains constant under J2 Perturbations.

Namespace:  AGI.Foundation.Propagators
Assembly:  AGI.Foundation.Models (in AGI.Foundation.Models.dll) Version: 24.3.420.0 (24.3.420.0)
Syntax
Copy
public static J2Propagator CreateCriticallyInclinedOrbit(
	JulianDate orbitEpoch,
	ReferenceFrame inertialFrame,
	ReferenceFrame fixedFrame,
	double periapsisAltitude,
	double apoapsisAltitude,
	double longitudeAscendingNode,
	double gravitationalParameter,
	double j2UnnormalizedValue,
	double referenceDistance,
	bool isPosigrade
)

Parameters

orbitEpoch
Type: AGI.Foundation.TimeJulianDate
The epoch associated with the initial conditions of the propagated orbit.
inertialFrame
Type: AGI.Foundation.GeometryReferenceFrame
An inertial ReferenceFrame centered at the central body.
fixedFrame
Type: AGI.Foundation.GeometryReferenceFrame
A fixed ReferenceFrame centered at the central body.
periapsisAltitude
Type: SystemDouble
The distance of the periapsis of the orbit above the referenceDistance of the central body.
apoapsisAltitude
Type: SystemDouble
The distance of the apoapsis of the orbit above the referenceDistance of the central body.
longitudeAscendingNode
Type: SystemDouble
The longitude of the ascending node in the fixedFrame of the central body.
gravitationalParameter
Type: SystemDouble
The gravitational parameter of the central body.
j2UnnormalizedValue
Type: SystemDouble
The non-normalized J2 parameter of the central body.
referenceDistance
Type: SystemDouble
The equatorial radius of the central body that also serves as a reference distance for the J2 parameter.
isPosigrade
Type: SystemBoolean
Sets the inclination to about 63.435 degrees if true (for posigrade critically-inclined orbits) or about 116.565 degrees if false (for retrograde critically-inclined orbits).

Return Value

Type: J2Propagator
A J2Propagator object that is initialized at its ascending node with the desired orbit epoch, orbital elements, and gravity field.
Exceptions
ExceptionCondition
ArgumentNullException Thrown when inertialFrame or fixedFrame is .
ArgumentOutOfRangeException Thrown when periapsisAltitude or apoapsisAltitude is less than zero, or when periapsisAltitude is greater than apoapsisAltitude.
See Also