focussuite focusgeo: the ultimate flight dynamics solution for GEO satellite operation

focusgeo is a member of GMV's focussuite and brings to satellite operators a solution to the domain of flight dynamics operation of geostationary satellites. focusgeo is a completely integrated application that provides full life cycle support of Geostationary satellites through an unsurpassed collection of mission independent and mission specific functionality that brings to satellite operators a perfect combination of professional off-the-shelf solutions with the flexibility and customer focus of a world leading supplier of flight dynamics custom solutions. The computation layer of focusgeo is based in part on ESA´s PEPSOC technology.

Supported Satellite Platforms and Satellite Missions

  • Thales Alenia Space’s Spacebus 3000, 4000 and Satelcom
  • Astrium’s Eurostar 2000, 2000+ and 3000
  • Boeing Satellite Systems’ 376
  • Orbital Sciences Corporation’s STAR-2
  • NPO/PM´s Express
  • Space Systems/Loral’s 1300
  • Isro I3000 
  • Boeing BSS601
  • Lockheed Martin A2100
  • Loral LS1300
  • OHB Luxor
  • Mitsubishi Electric DS-2000

Flight Dynamics Functions Supported by focusgeo computational Layer

Mission Specific Functions

Providing full lifecycle support of the corresponding satellite platform with a degree of accuracy 100% compatible with native systems, focusgeo supports all mission specific needs, such as:

  • Maneuver Implementation
  • Disturbance Torque Prediction
  • Fuel Mass Evolution
  • Station Keeping Maneuver Preparation
  • AOCS Support Functions
  • Contingency

Mission Independent Functions

  • Pre-Processing of Tracking Data
    This module process is the first step of the orbit determination, and it is run to transfer the latest ranging measurements and antenna pointing elements stored in a history file to the file of pre-processed tracking data where they can be processed by the orbit determination program. It reads the raw tracking data, soothes, reduces it, and applies calibration. The calibration factor shall be read from the parameter file. It soothes/reduces the data in that it converts a sequence of measurements obtained in a short time interval to one distance between satellite and the TCR station or to one direction from the TCR station to satellite. The tracking is converted to physical measurements of distance and angles and written to the pre-processed tracking file.


  • Orbit Determination and Maneuver Estimation (GORDAM)
    GORDAM is a program in charge of determining the position and velocity of the spacecraft and sometimes also less accurately known parameters of the mathematical model for the forces acting on the spacecraft from observations consisting of ranging measurements and pointing elements (azimuth and elevation measurements). GORDAM allowances shall be made within for known measurement biases, tropospheric errors, external perturbations of the orbit, and maneuver occurring during period in which measurements are being processed. An important aspect that deserves special attention is the issue of frequent and long-duration thrusts
  • Orbit Prediction
    This process computes the evolution of a geosynchronous orbit forward in time. Planned impulsive and continuous maneuvers on the maneuver files are taken into account and the orbit is written to the orbit file every half-hour.
  • Events Generation (INFO)
    This module is constituted by a number of modules that are capable to generate a complete list of important events: eclipses, apses crossing, nodes crossing, IRES blinding, Sun-Satellite-Station collinear situations, Sun-Earth-Satellite collinear situations, and AOS/LOS and AOS0/LOS0 crossings.
  • Antenna Pointing Elements
    This module writes polynomial coefficients sets for range, azimuth and elevation to the Antenna Pointing Elements file. The lengths of the intervals covered by each coefficient set are determined by the target accuracy TACC and the timing of the maneuvers. It is run to produce pointing elements for steering a ground antenna azimuth and elevation automatically. It generates an Antenna Pointing Elements (APES) file with the dates, coefficients of third order polynomials for the range, azimuth and elevation and the duration of the interval covered by these coefficients.
  • Station Keeping and Maneuver Planning
    This module calculates a North or South maneuver thrust for inclination station keeping. If the Orbit Prediction module execution indicates that the latitude deadband will be violated during the prediction period, it is run to prepare the station-keeping maneuver. It uses the Orbit File produced by the Orbit Prediction module and calculates the execution time and size of the North thrust according to the options specified in the input file. The new predicted orbit is printed along with maneuver data. The appropriate maneuver direction, maneuver mid-point time and maneuver size are automatically written to the maneuver file.
  • Longitude Station Keeping
    This module calculates one, two or three burn longitude maneuver for longitude station keeping with eccentricity control and longitude shift and stop burns. When the operator detects that the longitude deadband will be violated during the prediction period, the first step in the planning of the station-keeping maneuver is to run it. It uses the Orbit File produced by the Orbit Prediction module and calculates the execution time and size of the tangential burn according to the options specified in the input file. It also calculates the new predicted orbit and this is printed along with the maneuver data. It includes the capability of supporting longitude maneuver planning for collocated satellites by allowing the user to define the center (E0X, E0Y) of the circle subscribed by the eccentricity vector.
  • Proximity Monitoring and Maneuver Sensitivity Assessment
    This module performs a proximity check for a collocated satellite group. It reads the appropriate orbit files and prints the inter-satellite separations for all combinations of pairs of satellites with a warning message if they become too close (when distance and/or angle fall below specified threshold values). Apart, from numerical information, a graphical output is also provided, showing the evolution in time of: inter-satellite distance for all combinations of pairs of satellites; and inter-satellite angular separations for all combinations of pairs of satellites. In addition, it can assess the impact on the inter-satellite separation (distance and angle) of a planned maneuver, either under-performing and/or over-performing by specified factors.


  • Station Keeping Reports
    The DB Reports process provides the user with the facility for plotting information coming from the database: Orbital elements, Mass evolution, Station tracking information, and Maneuvers report.