Description
Represents the osculating value of the semi-latus rectum of the Spacecraft's orbit. The value of the semi-latus rectum is equal to the square of the specific angular momentum of the orbit (angular momentum per unit mass) divided by the central body's gravity constant m.
Timing Precision Mode
This page describes functionality in millisecond timing precision mode. Millisecond timing precision mode is deprecated and will be removed in a future release. We recommend that you migrate your Mission Plans to nanosecond timing precision mode.
Attributes
Type: |
number |
Access: |
read |
Units: |
km |
Syntax
myVariable1 = mySpacecraft1.P; |
See also
Coverage and Contact Analysis Guide