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Space Shuttle: Difference between revisions
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→Avionics and guidance systems
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== Avionics and guidance systems == | == Avionics and guidance systems == | ||
As of | As of October 2015, work on the avionics and displays of the Shuttle has started, and a limited number of functions is available - see the dedicated article on [[Space Shuttle Avionics]] for an overview. These include routines to monitor the various systems as well as automatic pointing and orbital maneuvering routines. | ||
The primary display is the HUD. This has four different modes - ascent, orbit, entry and approach, and dependent on the HUD mode, different information relevant for the mission phase is displayed. In all cases, the current CSS DAP is identified in the upper left. | [[File:Shuttle avionics disp19.jpg|600px|thumbnail|none|GNC SYS SUMM 2 display of the Space Shuttle]] | ||
The primary display usable for flight nevertheless is the HUD. This has four different modes - ascent, orbit, entry and approach, and dependent on the HUD mode, different information relevant for the mission phase is displayed. In all cases, the current CSS DAP is identified in the upper left. | |||
There is a calculator for orbital elements available, determining perigee and apogee, orbital inclination and longitude of the ascending node (the latter is currently not so useful as it is obtained in an inertial coordinate system). Based on these orbital elements, the groundtrack map displays current position of the Space Shuttle, selected landing site, ground track history and a prediction of the future orbit - if the perigee is below the surface of Earth, the prediction ends at the estimated ballistic impact point (note that due to the aerodynamical capabilities of the Shuttle, the actual landing site can be within a cross range of about 1000 miles around that point dependent on how the trajectory is managed during the entry phase). | There is a calculator for orbital elements available, determining perigee and apogee, orbital inclination and longitude of the ascending node (the latter is currently not so useful as it is obtained in an inertial coordinate system). Based on these orbital elements, the groundtrack map displays current position of the Space Shuttle, selected landing site, ground track history and a prediction of the future orbit - if the perigee is below the surface of Earth, the prediction ends at the estimated ballistic impact point (note that due to the aerodynamical capabilities of the Shuttle, the actual landing site can be within a cross range of about 1000 miles around that point dependent on how the trajectory is managed during the entry phase). | ||