|
SUPPORT SITE |
|
|
|
SUPPORT SITE |
|
Path: Orbit/RHSOrbit
% Orbit model for Launch and Early Orbit Operations.
This model is compatible with ode113. It includes an event for
apogee. If events are on it will stop at apogee unless a burn is
underway. Its companion function is FOrbLEOPStopping
--------------------------------------------------------------------------
Form:
xDot = FOrbLEOP( t, x, d )
--------------------------------------------------------------------------
------
Inputs
------
t Time
x (7,1) The state vector [r;v;m]
d (1,1) Data structure
.thrust (1,1) Engine thrust (N)
.mu (1,1) Gravitational parameter
.uE (1,1) Exhaust velocity (m/s)
.cDA (1,1) Drag area product
.burnStart (1,1) Start time of burn
.burnEnd (1,1) End time of burn
-------
Outputs
-------
xDot (7,1) The state vector derivative d[r;v;m]/dt
--------------------------------------------------------------------------
AerospaceUtils: AtmosphericCalculations/AtmDens1 Math: Linear/Mag
Back to the Orbit Module page