Path: Orbit/OrbitMechanics
% Finds the inclination rate and orbit normal vector.
Computes the inclination change rate and orbit normal vector. This
shows where in the orbit inclination changes fastest with a normal
acceleration.
Type InclinationRate for a demo.
--------------------------------------------------------------------------
Form:
[dI, uN, dIMax] = InclinationRate( x, mu )
--------------------------------------------------------------------------
------
Inputs
------
x (6,:) [r;v]
mu (1,1) Gravitational potential (km^3/s^2)
-------
Outputs
-------
dI (1,:) Inclination rate (rad/sec)
uN (3,:) Orbit normal
dIMax (1,1) Maximum inclination rate (rad/sec)
--------------------------------------------------------------------------
Reference: Robert Falck and Leon Gefert," A Method of Efficient
Inclination Changes for Low-Thrust Spacecraft,"
Astrodynamics Specialist Conference and Exhibit,
Monterey, CA, United States, 2002.
--------------------------------------------------------------------------
Orbit: OrbitCoord/SLR Orbit: OrbitMechanics/RVOrbGen SC: BasicOrbit/CP2I SC: BasicOrbit/E2M SC: BasicOrbit/E2Nu SC: BasicOrbit/M2E SC: BasicOrbit/M2EApp SC: BasicOrbit/M2EEl SC: BasicOrbit/M2EHy SC: BasicOrbit/M2Nu SC: BasicOrbit/M2NuPb SC: BasicOrbit/Nu2E SC: BasicOrbit/Nu2M SC: BasicOrbit/Period SC: BasicOrbit/RV2El Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/DeBlankLT Common: General/MatToCell Common: General/Watermark Common: Graphics/Axis3D Common: Graphics/Mesh2 Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Common: Graphics/TimeLabl Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Graphics/ZLabelS Math: Linear/Cross Math: Linear/DupVect Math: Linear/Mag Math: Linear/Unit
Back to the Orbit Module page