Convert planet orbiting initial conditions to heliocentric coordinates using spice.
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#include <lunar_to_eci.h>
Inherits dsim_model.
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| lunar_to_eci (dsim_model_setup *setup) |
| | Constructor.
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| ~lunar_to_eci () |
| | Destructor.
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void | initialize_data () |
| | Initialize outlets and output variables.
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void | initialization_complete () |
| | Finish initialization.
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dsim_variable | planet_dsim |
| | Fix to this planet.
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These variables are referenced from the parent object.
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dsim_variable | position_dsim |
| | Position.
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dsim_variable | velocity_dsim |
| | Velocity.
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These outlets provide the interface to the SPICE model for defining the planet frame.
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dsim_variable | observer_dsim |
| | Reference center.
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dsim_variable | positionBody_dsim |
| | Planet positions outlet.
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dsim_variable | velocityBody_dsim |
| | Planet velocities outlet.
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dsim_variable | planetIndex_dsim |
| | SPICE planet index outlet.
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dsim_variable | rotationMatrixBody_dsim |
| | Planet rotation matrix.
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dsim_variable | planetAngularRate_dsim |
| | Planet angular rate matrix.
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Convert planet orbiting initial conditions to heliocentric coordinates using spice.
Adding this model to your rigid body spacecraft allows you to specify the vehicle initial state in the planet orbit frame rather than the ECI frame. The position, velocity, quaternion, and bodyRate initial values are all overwritten after being converted.
This module has outlets which must be connected to the SPICE model.
The documentation for this class was generated from the following files:
- lunar_to_eci.h
- lunar_to_eci.cc
