Space Shuttle Avionics: Difference between revisions

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Space Shuttle Avionics (view source)

Revision as of 16:45, 29 December 2020

2,836 bytes added ,  29 December 2020
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=== A/E PFD ===
=== A/E PFD ===


[[File:Shuttle avionics meds pfd.jpg|600px|PFD of the Space Shuttle in ascent/entry mode]]


The primary flight display provides a summary of all GNC relevant parameters. Its core is the ADI ball on which the attitude of the Shuttle in the selected coordinate system is shown, surrounded by tapes for velocity, alpha, altitude and vertical speed. In the lower half, an accelerometer and the course deviation indicator are provided along with mission-phase specific alphanumerics.
The primary flight display provides a summary of all GNC relevant parameters. Its core is the ADI ball on which the attitude of the Shuttle in the selected coordinate system is shown, surrounded by tapes for velocity, alpha, altitude and vertical speed. In the lower half, an accelerometer and the course deviation indicator are provided along with mission-phase specific alphanumerics.
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The PFD is a complicated instrument in which the meaning of various readings depends on switch settings and mission phase (for instance, the ADI reference can be standard pitch/heading/roll as for an aircraft in the final phase of the flight as well as inertial or LVLH in orbit; the range of the error rate display is also selectable, the accelerometer will show Nz during entry and TAEM rather than linear acceleration during launch,...) - so make sure you understand what it is showing before using its information.
The PFD is a complicated instrument in which the meaning of various readings depends on switch settings and mission phase (for instance, the ADI reference can be standard pitch/heading/roll as for an aircraft in the final phase of the flight as well as inertial or LVLH in orbit; the range of the error rate display is also selectable, the accelerometer will show Nz during entry and TAEM rather than linear acceleration during launch,...) - so make sure you understand what it is showing before using its information.


Compare the following PFD in the gliding part of an RTLS abort with the above PFD during launch to appreciate the differences:
Most of the original functionality is implemented in FG.


[[File:Shuttle avionics meds pfd rtls.jpg|600px|PFD of the Space Shuttle for RTLS abort]]
As stated above, PFD is complex and informations displayed on it differ quite a lot depending of the phase of flight and abort mode.


Most of the original functionality is implemented in FG.
A complete explanation about that is available in [https://www.nasa.gov/centers/johnson/pdf/359895main_DPS_G_K_7.pdf DPS dictionnary Section 6].
 
We will go through the different modes implemented so far ( Dev version December 2020).
 
 
Major Mode 101 ( before SSME Ignition)
 
ADI is driven by nav software 4 mn before launch
 
[[File:Mm101.jpg|600px|PFD of the Space Shuttle in MM101]]
 
 
SRB ignition , MM 102
 
[[File:Mm102.jpg|600px|PFD of the Space Shuttle in MM102]]
 
 
SRB sep, MM 103
 
Beta and Vrel pointer (relative velocity) vanished above 200 kfeet
 
[[File:Mm103.jpg|600px|PFD of the Space Shuttle in MM103]]
 
 
 
In case of TAL declared, MM 103 T.
 
Now, distance to TAL runway and bearing is displayed , some other informations are removed.
 
[[File:Mm103tal.jpg|600px|PFD of the Space Shuttle in MM103 TAL]]
 
 
External Tank separation, MM 104.
 
[[File:Mm104.jpg|600px|PFD of the Space Shuttle in MM104]]
 
 
PFD MM105 through 303 is normally just displaying the ADI ball.
However, some relevants informations were kept for On orbit better management ( rendez vous, ...)
 
[[File:Mm105.jpg|600px|PFD of the Space Shuttle in MM105 through MM 303]]
 
 
 
Entry mode now, MM 304 or MM 602.
 
New layout for Pitch and Roll/yaw Auto or CSS and speebrake shown now below MM on the right ( Yellow rectangle when switched to Manual or CSS above mach 1).
 
Also HAC bearing and runway distance only displayed, with vertical acceleration.
 
[[File:Mm_304_602.jpg|600px|PFD of the Space Shuttle in MM304]]
 
 
 
TAEM interface ( mm 305 or 603)
 
Heading Alignement Cone (HAC) H pointer for WP1 (entry in the HAC) and C for HAC center.
 
Both distance to runway and to HAC center are displayed.
Glideslope only and no vertical acceleration displayed anymore.
 
[[File:Mm_305_603.jpg|600px|PFD of the Space Shuttle in MM305]]
 
 
 
 
Entering the HAC.
 
DAz (Delta Azimuth) is replaced by HTA ( Hac turn angle). It displays remaining degrees in HAC before runway alignement.
 
[[File:Entering_hac_HTA.jpg|600px|PFD of the Space Shuttle in MM305 entering the HAC]]
 
 
 
 
Once in final Approach Landing mode (A/L), the only things remaining are Runway Bearing and Distance to Runway
 
[[File:AL_305.jpg|600px|PFD of the Space Shuttle in MM305 entering A/L]]
 
 
 
 
Below Mach 0.9, Speed tape switches to EAS ( with still mach ladder behind) and Speed box switches to Mach.
 
Yellow Altimeter tape below 2000 feet ( either AGL or Baro depending if Radar altimeters are available or not).
 
[[File:Subsonic_mm_305.jpg|600px|PFD of the Space Shuttle in MM305 Subsonic]]
 
 
 
 
A special Abort mode that changes a bit the different layouts.
 
If RTLS declared, MM 601.
 
Vrel pointer and Beta display appeared again.
 
Pre Pitch Power Around (PPA), Inertial Speed is displayed.
Post PPA, Relative Speed is displayed and Bearing to runway with Earth relative tail pointer.
 
MM 601 Pre PPA
 
[[File:Mm_601_pre_ppa.jpg|600px|PFD of the Space Shuttle in MM601 pre PPA]]
 
 
MM 601 Post PPA


[[File:Mm_601_post_ppa.jpg|600px|PFD of the Space Shuttle in MM601 post PPA]]


=== ORBIT PFD ===
=== ORBIT PFD ===
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