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== Avionics and guidance systems ==
== Avionics and guidance systems ==


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.
=== Avionics ===
 
The avionics of the Space Shuttle is fairly faithfully reproduced by the simulation, see the dedicated article on [[Space Shuttle Avionics]] for an overview. The implemented screens include routines to monitor the various systems as well as guidance navigation and control for all mission stages.


[[File:Shuttle avionics disp19.jpg|600px|thumbnail|none|GNC SYS SUMM 2 display of the Space Shuttle]]
[[File:Shuttle avionics disp19.jpg|600px|thumbnail|none|GNC SYS SUMM 2 display of the Space Shuttle]]


As of January 2016, all nine MDUs of the forward panel are usable and display the data processing system of the Shuttle - this includes launch and entry guidance routines, TAEM guidancs as well as orbital tracking and pointing management. In addition, HUDs for Commander and Pilot are provided.
All nine MDUs of the forward panel are usable and display the DPS and MEDS screens of the Shuttle - this includes launch and entry guidance routines, TAEM guidancs as well as orbital tracking and pointing management. In addition, HUDs for Commander and Pilot are provided.


[[File:Shuttle cockpit panorama01.jpg|800px|thumbnail|none|Space Shuttle cockpit]]
[[File:Shuttle cockpit panorama01.jpg|800px|thumbnail|none|Space Shuttle cockpit]]


An alternative display  for all phases of flight is provided by the FG-native the HUD (which also augments the original cockpit instrumentation where it is not yet complete). 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.
An alternative display  for all phases of flight is provided by the FG-native 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).


For the entry phase, there is also a guidance computer available which allows to select a landing site in orbit. The entry guidance can only be de-activated if the guidance can compute a halfway plausible de-orbit solution to the site - allow for no more than 10 degrees azimuth deviation and at least 3000 miles to site at the entry interface. If the entry guidance is active, target deceleration and azimuth deviation to site is displayed during the entry phase in the lower right of the HUD - by managing actual deceleration and azimuth of the trajectory the Shuttle can be aimed at the landing site (while the entry display is different in the real Shuttle, the guidance parameters are the same).
=== Automated flight ===
 
[[File:Shuttle-landing01.jpg|600px|thumbnail|none|Groundtrack map and entry guidance computer for the Space Shuttle]]


Apart from these, the Shuttle HUD contains a basic engine status display, speedbrake, body-flap and gear status indicators in the approach mode and yaw, pitch and roll rate indicators in orbit, as well as the normal pitch ladder and flightpath indicator of an airplane.
Automated flight is available for all nominal mission phases except for the final approach and touchdown (for which in reality no AP is available either) as well as all single engine loss intact aborts and all two engine out contingency aborts.


== Payload handling ==
== Payload handling ==
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