FreeFlyer

home > FreeFlyer > FreeFlyer Tiers > FreeFlyer Features Overview

FreeFlyer Features Overview

Output/Visualization Design Engineer Mission
Full 2D and 3D visualization with customizable view points x x x
Customizable view points x x
Custom/user defined XY plots, polar plots x x x
Custom/user defined ASCII reports x x x
Monitor window for "strip chart" type data x x x
Watch window for real-time constraint checking x x
Over 1300 parameters available for reporting and plotting x x x
Ground station masking and sensor swaths x x x
3D Proximity Zone for station keeping/relative motion visualization x x
Spacecraft Modeling Design Engineer Mission
Full mass properties definition x x x
Sensors (see sensor features for more information) x x x
Tanks (spherical, interpolated, or electrical) x x
Thrusters (mono-propellant, bi-propellant, ion) x x
Antennas (conical FOV) x x x
Antennas (irregular polygon FOV, obscuration masking) x x x
Transceivers x
Collision avoidance calculations (Proximity Zones) x x
Multi-spacecraft x x x
Formation modeling x x
Sensors Design Engineer Mission
Simple conic x x x
Complex conic, irregular polygon, rectangular x x x
Obscuration masking x x x
Scanning sensor x x
Custom/user-defined sensor patterns x x
Attitude Design Engineer Mission
LVLH (nadir pointing with orbit-normal constraint), Mean of J2000 Earth Equator, Geodetic (geodetic pointing with orbit-normal constraint) x x x
User defined / Custom Coordinate Systems x x
Euler angles x x x
Quaternion, Attitude matrix, Spinner x x x
Target pointing attitude x x
Attitude history file (AHF) x x x
Maneuvers Design Engineer Mission
Impulsive maneuvers x x x
Finite maneuvers x x
Maneuver targeting/optimization x x x
Orbit Propagation Design Engineer Mission
Fixed or Variable Step (step size is user definable) x x x
Runge Kutta 4(5), VOP, Two Body, NORAD/SGP4 x x x
Runge Kutta 7(8), 8(9), Bulirsch Stoer, J2 Mean Elements x x
Use Air Force Space Command supplied SP & SGP4 DLL x
Planetary ephemeris (DE200 or DE405) x x x
SPICE ephemeris x x
Atmospheric drag/lift, Solar radiation pressure x x x
Atmospheric density - Analytic x x x
Atmospheric density - Jacchia Roberts, Harris Priester x x
Earth potential & Moon potential up to 100x100 x x x
NORAD two line elements (TLEs), FreeFlyer ephemeris/state, STK ephemeris/state x x x
User-defined ephemeris/state x
Orbit Calculations Design Engineer Mission
Over 150 orbit/trajectory parameters calculated at each integration step x x x
Unlimited user defined parameters using embedded math libraries or MATLAB connection x x
Dynamic real-time feedback available during each run x x x
Ground Station Modeling Design Engineer Mission
User defined location and masking or read from geodetics file x x x
Station bias parameters x
Station antenna parameters x
Ground Network Modeling x x
Visibility/Access Analysis Design Engineer Mission
Visibility period calculations between any objects (s/c to s/c, s/c to ground station, s/c to ground region, etc.) x x x
Field of view, elevation angle, azimuth angle, range & range rate x x x
Solar and lunar constraints /Lighting constraints / Beta angle constraints x x x
Temporal constraints (interval, duration, GMT, mean local time) x x x
Cross track, along track, range, and all associated rates x x x
AOS/LOS x x x
Sensor to sensor, sensor to s/c, sensor to ground station constraints x x x
Sensor tracking x x
Magnetic field regions x x x
Celestial object interference (all planets & star catalog) x x
Rapid performance coverage analysis for coverage and revisit statistics x x
Rapid performance close approach analysis x x
Logic Control Design Engineer Mission
Logic engine to control actions based on any calculated parameter x x x
Full-featured Scripting Language x x
For, If , While, Pause, Stop, Achieve, Target, Vary commands x x x
Fuzzy logic engine for conflicting constraint resolution x x
Orbit Determination Design Engineer Mission
Extended Kalman Filter, Batch Least Squares x
Orbit Determination error analysis x
Tracking Data filtering x
Ground based range/ range rate/ azimuth/ elevation tracking data x
TDRS tracking two-way range/ two-way Doppler tracking data x
GPS tracking data x
Spacecraft X, Y, Z, Vx, Vy, Vz, Cd, Cr, Transponder delay Solve-fors x
Ground station location, antenna bias Solve-fors x
Coordinate System Types Design Engineer Mission
Mean of J2000 Earth Equator/Earth Ecliptic, True of Date Earth Equator, NORAD x x x
Launch Vehicle Coordinates (user definable to ELV vendor specs) x x x
Cartesian, Keplerian/nonsingular Keplerian, Spherical/Spherical Lat/Long x x x
True Equator Mean Equinox, Equinoctial, Brouwer-Lyddane Mean/ J2 Brouwer-Lyddane, Mean of 1950 x x
Conversion functions to convert between systems x x
User defined / Custom Coordinate System x x
External Interfaces Design Engineer Mission
MATLAB interface x x
TCP/IP socket interface x
SQL 92 database compliant interface x
Run command to spawn external applications x
Customizable graphic user interface (GUI) x
Generic ASCII & Binary File Reader x
Automatic e-mail notification based on user defined rules x
Links to External Code x
Usability/User Interface Design Engineer Mission
Drag & Drop Mission Design Sequence x x x
Wizards and samples for quick problem set up x x x
Ephemeris browser and compare utilities x x x
Batch run/Command Line capability x x
Fuzzy set designer for fuzzy logic problem set-up x x
Miscellaneous Design Engineer Mission
Independently validated and verified x x x
On-line help files with context sensitive searching x x x
Automated parametric studies x x x
Monte-Carlo analysis x x
Unlimited window tiling output for dynamic user feedback x x x
Any parameter can be set/reset real-time during runs x x
PRINTER FRIENDLY VERSION

Our Company| FreeFlyer| Our Services| Library| News| Events| Contract Vehicles © 2007 a.i. solutions. All rights reserved.