ThirdBodyDisturbances.h

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/* 
*/

#ifndef __OSESSAME_THIRDBODY_PERTUBATIONS_H__
#define __OSESSAME_THIRDBODY_PERTUBATIONS_H__
#include "matrix/Matrix.h"
#include "Time.h"
#include "OrbitState.h"
#include "Attitude.h"
#include "Environment.h"
#include <vector.h>
using namespace std;
using namespace O_SESSAME;

Vector ThirdBodyForceDisturbance(const ssfTime &_currentTime, const OrbitState  &_currentOrbitState, const AttitudeState &_currentAttitudeState, const EnvFuncParamaterType &_parameterList)
{
    static Vector Forces(3);
    static Vector Position(3); 
    static CentralBody* pOrbCB, pThirdBody;
    pOrbCB = reinterpret_cast<CentralBody*>(_parameterList[0]);
    pThirdBody = reinterpret_cast<CentralBody*>(_parameterList[1]);
    
    static double massThirdBody = pThirdBody->GetMass();
    static Vector vectorOrbCB2ThirdBody = pOrbCB->GetVector2Body(pThirdBody);
    static Vector vectorThirdBody2Satellite(3); 
        vectorSat2ThirdBody = - pThirdBody->GetVector2Body(_currentOrbitState); // negative to "switch the head" around
    static double B = norm2(vectorOrbCB2ThirdBody) / norm2(vectorSat2ThirdBody) - 1;  
    static double beta = pow(1+B, 3);
    
    Position(_) = _currentOrbitState.GetState()(_(VectorIndexBase,VectorIndexBase+2));
    Forces = - c_GravitationalConstant * massThirdBody / pow(vectorOrbCB2ThirdBody, 3) * (Position(_) - beta * vectorSat2ThirdBody);
    return Forces;
}

#endif
// Do not change the comments below - they will be added automatically by CVS
/*****************************************************************************
*       $Log: ThirdBodyDisturbances.h,v $
*       Revision 1.1  2003/06/12 17:58:42  nilspace
*       Initial Submission.
*       
*       
******************************************************************************/

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