B-plane Coordinate Type

The B-plane (BPlane in the UI) coordinate type is primarily used for hyperbolic arrival trajectories to specify the spacecraft’s state relative to the arrival central body. The initial state formulation uses the B-plane definition, which is a plane perpendicular to the incoming velocity asymptote direction. The B-vector that lies in the plane gives the intersection of the incoming velocity asymptote with the B-plane. The B-vector is typically defined in the context of two other vectors, R and T, that lie in the B-plane. The B-plane coordinates have four main parts:

the incoming asymptote definition
the B-vector definition
the orbital energy definition
a time-varying quantity

For more information about the details of the B-plane, see the technical note on B-plane targeting. You must use an inertial coordinate system to use this coordinate type.

Incoming Asymptote definition

You must specify both of these values to define the incoming asymptote.

Element	Description
Right Ascension of B-Plane Normal	This is the right ascension of the hyperbolic incoming asymptote in the selected coordinate system. Enter a value in the selected angle unit.
Declination of B-Plane Normal	This is the declination of the hyperbolic incoming asymptote in the selected coordinate system. Enter a value in the selected angle unit.

B-vector definition

You must specify two of the four elements below. You can only select B Magnitude with B Theta in order to fully define the B-vector.

Element	Description
B dot R	This is the result of the dot product of the B-vector with the R vector. Enter a value in the selected distance unit.
B dot T	This is the result of the dot product ofthe B-vector with the T vector. Enter a value in the selected distance unit.
B Theta	This is the angle between the T-vector and B-vector. Enter a value in the selected angle unit.
B Magnitude	This is the length of the B-vector. Enter a value in the selected distance unit.

In general, changing one of the six values specified on the initial state panel will not change any of the others, except for numerical noise. There is some unique behavior if you select B Theta for the first B-vector definition parameter and either B dot R or B dot T for the second B-vector definition parameter. Both the value of B theta and the sign of B dot R and B dot T control the quadrant that the B-vector is in. When one of the two values changes in this configuration such that it puts the B-vector in a different quadrant inconsistent with the current definition, then the other value also changes.

For example, if B Theta is between 0 and 90 degrees and you select B dot T with a positive value, then:

Changing the value of B dot T to a negative value changes B Theta to be between 90 and 180 degrees, consistent with the new value of B dot T and the old implicit value of B dot R (B dot R is kept constant).
Changing the value of B Theta to be between 90 and 270 degrees changes B dot T to be a negative value consistent with the new value of B Theta and the old implicit value of B Magnitude (B Magnitude is kept constant).

Orbital Energy definition

There are four options to specified the orbital energy. Only two, Orbital C3 Energy and Semimajor Axis, are available for closed orbits with eccentricity less than 1. Additionally, when the eccentricity is less than 1, then the magnitude of the B-vector cannot be greater than the value of the semimajor axis.

Element	Description
Orbital C3 Energy	Represents the characteristic energy for the orbit. Enter in the selected distance squared per time squared unit.
Semimajor Axis	Measures half the length of the major (longest) axis of the parabola or hyperbola. Enter a value in the selected distance units.
Hyperbolic V Infinity	This is the magnitude of the velocity infinitely far away from the central body. Enter a value in the selected velocity units.
Hyperbolic Turning Angle	Represents the angle between the hyperbolic asymptotes, which is 180 degrees minus the angle between the incoming and outgoing asymptotes. See δ in the diagram below. Enter a value in the selected angle units.

Time-varying quantity definition

There is only one option that you must specify for the time-varying quantity.

Element	Description
True Anomaly	Represents the angle from the eccentricity vector, which points toward perigee, to the satellite’s position vector, measured in the direction of satellite motion in the orbit plane. There are restrictions on valid values for the true anomaly, based on the eccentricity of the hyperbolic trajectory. Changes to other parts of the initial state may give errors if they cause the specified true anomaly to be outside the valid range for the new hyperbola. In these cases, first change True Anomaly to 0 before changing the other part of the initial state. Enter the True Anomaly value in the selected angle units.

Element

Description

True Anomaly

Represents the angle from the eccentricity vector, which points toward perigee, to the satellite’s position vector, measured in the direction of satellite motion in the orbit plane. There are restrictions on valid values for the true anomaly, based on the eccentricity of the hyperbolic trajectory. Changes to other parts of the initial state may give errors if they cause the specified true anomaly to be outside the valid range for the new hyperbola. In these cases, first change True Anomaly to 0 before changing the other part of the initial state. Enter the True Anomaly value in the selected angle units.