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Astrogator Launch:
Astrogator can model space missions from the launch to the reentry phase. This is an example of how Astrogator can be used to model a spacecrafts launch from Earth into orbit. Highly defined models can be used to portray accurate stage separations during launch through the Mission Control Sequence (MCS) as individual assets, or through model articulations.
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Earth Mapping Mission:
The objective of this scenario is to show the use of STK/AVO to aid in orbit design, and systems analysis of a hypothetical Earth space environment mapping mission. This mission needs an orbit design which will allow for complete data collection of the space radiation environment from 400 km to 8000 km over a period of 3 years for the primary mission.
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Error Covariance with ODTK
This scenario demonstrates the ability to bring covariance data computed in ODTK into STK for visualization. In this scenario, the truth, filter, and smoother covariance spheres computed in ODTK for a LEO satellite are shown in the 3-D window. The errors in the position data of the satellite are much smaller when in view of tracking stations, thus the error covariance spheres for all three models shrink considerably when the satellite has access to the ground stations.
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Geo Drift
A geostationary satellite is positioned at -100 degree longitude and must maintain it's slot position of 0.1 degrees North-to-South and East-to-West. Two satellites are modeled in this scenario to show the differences in a satellite using a two-body model propagator for its orbit and one using Astrogator to model the stationkeeping burn (TargetDV). The Astrogator propagator is using a custom internal propagator which includes a variation of parameters and all perturbations over time to model the drift of the satellite. As the TargetDV satellite approaches its western boundary limit, a thruster fires to reposition its location in the geo slot. Heads up dynamic data displays RIC range information between the two satellites.
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SapphireOD
This scenario shows the operation of an earth-orbiting observation platform (Sapphire) to perform orbit determination for other earth-orbiting vehicles (one GEO and one MEO in this example). For each of the three platforms, the scenario shows the position of the actual platform (truth), the perceived position of the platform based on ground observations only (with covariance ellipsoid), and the perceived position of the platform based on both ground and space observations (with covariance ellipsoid). The satellites use vectors to point to observation platforms (ground and space) when observations are made to the satellites. At those times, you can see the covariance ellipsoids shrink and then expand as the uncertainties propagate. You also notice that the uncertainties are smaller with combined space and ground observations, and this applies for the OD for the observation platform (Sapphire) as well as the MEO and GEO.
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Shuttle Re-entry
This scenario illustrates the flight path of the STS-121 mission shuttle re-entry and landing.
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Shuttle/ISS Docking
This scenario depicts the use of STK/Astrogator to calculate the shuttle's trajectory as it maneuvers to dock with the ISS. Watch as the shuttle performs a 360-degree rotational pitch maneuver 600 ft below the ISS, enabling crew members aboard the station to photograph the belly of the Shuttle. Then, follow the Shuttle as it moves 400 ft in front of the ISS and backs toward it for docking.
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STS-128 Launch
STS 128 launched from Kennedy Space Center at
23:59:35.000 EDT on August 28, 2009. To help illustrate
the event, this AGI Viewer file was created by CSSI to
show the ascent portion of the launch trajectory--from
liftoff to main engine cutoff (MECO)--using data obtained
from NASA.
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