WorstCasePerturbations:
--------------------------------------------------------------------------
Worst-case differential accelerations for spacecraft in formation.
Assumes fixed maximum and minimum area differences, which could in
practice be different for drag and solar pressure based on mission
attitude profiles.
The relative accelerations are due to :
1) Earth's Gravitational potential (geopotential)
2) Atmospheric drag
3) Sun
4) Moon
4) Solar radiation pressure
5) Linearization of equations of motion
Since version 7.
--------------------------------------------------------------------------
Form:
[aDiff, aTerms] = WorstCasePerturbations( h, dR, mSC, Cd, Cr );
--------------------------------------------------------------------------
------
Inputs:
-------
h (1) altitude of (circular) orbit (km)
dR (1) distance between the spacecraft (km)
mSC (1) spacecraft mass (kg)
Cd (1) drag coefficient
Cr (1) reflectivity of s/c: 0.0 for translucent; 1.0 for black-body;
2.0 for flat mirror
-------
Outputs:
--------
aDiff (3,2) sum of all the terms (m/s/s)
aTerms (.) data structure containing the individual differential
accelerations
- J2 (3,1) earth's oblateness
- drag (3,1) drag
- sun (3,1) effect of sun
- moon (3,1) effect of moon
- solar (3,1) solar radiation
- linear (3,1) linearization approximation error
--------------------------------------------------------------------------
Copyright (c) 2004 Princeton Satellite Systems, Inc.
All rights reserved.
--------------------------------------------------------------------------
Children:
AeroUtils: AtmosphericCalculations/AtmDens2
Common: Database/Constant
