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{{Space Shuttle navigation}} | {{Space Shuttle navigation}} | ||
This tutorial is following the Deorbit Preparation: [[Flying the Shuttle - Deorbit Preparation Advanced]] | This tutorial is following the Deorbit Preparation: [[Flying the Shuttle - Deorbit Preparation Advanced]] | ||
We will see now the final Burn preparation, the Burn, and the Entry final preparation to be fully ready for the Entry. | We will see now the final Burn preparation, the Burn, and the Entry final preparation to be fully ready for the Entry. | ||
We will use from now on the Entry Checklist annotated from here : [[Flying the Shuttle - Space Shuttle Checklists]] | We will use from now on the Entry Checklist annotated from here : [[Flying the Shuttle - Space Shuttle Checklists]] | ||
__TOC__ | |||
== Deorbit Burn preparation and Burn == | |||
We gonna use now the Entry Checklist which starts in real 45 mn before the burn ( 15 mn in our situation) | |||
We are nicely catching the time with good use of time compression | We are nicely catching the time with good use of time compression | ||
1) We check once again the burn solution: Velocity, inertial attitude BURN ATT, length of the burn TGO and total velocity DVTOT. | |||
Also, check the target Apogee and Perigee (TGT HA HP) | |||
As there is still a mistake from my part here, TGO is 5:42 instead of 3 min ish with 2 engines burn (it is what you should see as we are doing a 2 engines burn). | |||
As there is still a mistake from my part here, TGO is 5:42 instead of 3 | |||
[[File:Spec 50 check.jpg|1000px]] | [[File:Spec 50 check.jpg|1000px]] | ||
2) We check that nozzles can move freely (Gimbal) | |||
'''Item 34''' A star * appears right of GMBL CK and disappears once the check is completed. | '''Item 34''' A star * appears right of GMBL CK and disappears once the check is completed. | ||
Line 42: | Line 33: | ||
3) APU Pre Start | |||
Mainly checks to do | |||
Hyd Pump on Low, APY controller On et Boiler N2 Supply On (Nitrogen pressurizing Water Tanks that will cool down Hydro and Oil from APU gearbox) | |||
Hyd Pump on Low, | |||
[[File:APU prestart 1.jpg|1000px]] | [[File:APU prestart 1.jpg|1000px]] | ||
4) We check on Spec 50 the good data and configuration for final entry phase (TAEM). | |||
Good runway here is KSC 15. | |||
Normally, nothing to change, just some checks. | Normally, nothing to change, just some checks. | ||
Line 64: | Line 51: | ||
5) One more step to verify burn solution (a bit redundant, but mistakes can happen fast and after OMS ignition, it is hard to recover) | |||
5)One more step to verify burn solution ( a bit redundant, but mistakes can happen fast and after OMS ignition, it is hard to recover) | |||
[[File:OMS burn check.jpg|1000px]] | [[File:OMS burn check.jpg|1000px]] | ||
6) We check that the RCS:OMS valves are in correct position | |||
Here, we just have to close the OMS He Press/vapor isol | |||
It allows to isolate the propellant tanks from the Helium tank that pressurizes them during a burn. We avoid like that to loose all the Helium in case of leak in the pipes between two OMS burn. | |||
No Helium, no burn (Pressure feed combustion chamber) | |||
No Helium, no burn ( Pressure feed combustion chamber) | |||
[[File:OMS burn check 2.jpg|1000px]] | [[File:OMS burn check 2.jpg|1000px]] | ||
7) We close the ventilation doors ( 10 around the Orbiter, linking non pressurized part of the Orbiter to the exterior pressure condition) | |||
'''Item 44''' | '''Item 44''' | ||
Line 95: | Line 74: | ||
We transition to '''OPS 302 PRO''', similar page than previous one used for the Deorbit Burn. | |||
Burn solution is saved during the transition hopefully. | Burn solution is saved during the transition hopefully. | ||
Line 102: | Line 81: | ||
8) We will now put the Orbiter into the correct Inertial attitude for the burn. | |||
DAP Auto mode and '''ITEM 27''' | |||
It will put the Orbiter in a good burn attitude and update that one until we perform the burn. | It will put the Orbiter in a good burn attitude and update that one until we perform the burn. | ||
[[File:Item 27.jpg|1000px]] | [[File:Item 27.jpg|1000px]] | ||
9) Reconfiguration of RCS/OMS heaters (all Off except crossfeed lines) | |||
9)Reconfiguration of RCS/OMS heaters ( all Off except crossfeed lines) | |||
[[File:OMS RCSheaters.jpg|1000px]] | [[File:OMS RCSheaters.jpg|1000px]] | ||
10) 5 min before the burn, we start one APU. | |||
Aim is to have at least one APU working after the burn in case of malfunction of the two others. | |||
Being without Hydraulic power for Entry is not an option, and would lead to a crash for sure. So better to be sure to have a working APU before to decrease the Perigee :) | |||
Being without | |||
[[File:Single APU.jpg|1000px]] | [[File:Single APU.jpg|1000px]] | ||
11) OMS valves reconfiguration before the burn, Helium is now feeding both propellant tanks in each OMS system | |||
11)OMS valves reconfiguration before the burn, Helium is now feeding both propellant tanks in each OMS system | |||
[[File:Burn1.jpg|1000px]] | [[File:Burn1.jpg|1000px]] | ||
Last verification of front switch (Frame in LVLH, Medium error and rate for monitoring) | |||
OMS Eng checked on ARM/PRESS, if not, no Nitrogen to open bi-valves that separate propellant from combustion chamber. | OMS Eng checked on ARM/PRESS, if not, no Nitrogen to open bi-valves that separate propellant from combustion chamber. | ||
Line 144: | Line 116: | ||
Next screen will show normal behavior on 2 engines (I corrected the small mistake )and we have 3 min of burn TGO. Good. | |||
REI is around 4000 NM, so we press EXEC and monitor the burn. | |||
Monitoring of: Valves well opened at 100% and Pc combustion full white and above 80% | |||
Also, we can check the ENG IN P (engine inlet pressure) that indicates the pressure of either the fuel or oxidant before the combustion chamber | |||
Value should be lower than the on in respective tanks due to propellant suction into the chamber. | |||
That is an important parameter to detect an engine failure. | |||
That is an important parameter to detect an engine failure. | |||
For example, if the ENG IN P of the oxidizer is high and the Pc parameter is below 80% , we can deduce that something is blocking the oxidizer after the engine inlet line. | |||
Hence, that engine is lot, but we can still use the remaining fuel to do a cross feed and finish the burn on one engine. | |||
Hence, that engine is lot, but we can still use the remaining fuel to do a cross feed and | |||
Same stuff with ENG IN P Ox low that time, we can deduce that there is a leak somewhere between the oxidizer tank and the main chamber, so both the engine and remaining propellant is lost. | |||
[[File:Burn new.jpg|1000px]] | [[File:Burn new.jpg|1000px]] | ||
Line 172: | Line 142: | ||
Burn is over , we check the results (REI, HA and HP) | |||
REI of 3900 NM , and HP of 22 NM, perfect and in accordance with the map (circle indicates the estimated EI. It will move a bit before stabilizing) | |||
[[File:Burn result.jpg|1000px]] | |||
[[File:Burn result.jpg|1000px]] | |||
[[File:Burn result.jpg|1000px]] | [[File:Burn result.jpg|1000px]] | ||
== Final Entry Preparation == | |||
12) Final reconfiguration of OMS, Helium valves are closed once for good | |||
= | |||
12)Final | |||
[[File:Post burn.jpg|1000px]] | [[File:Post burn.jpg|1000px]] | ||
We switch in '''OPS 303 PRO''', Coasting phase between Deorbit Burn and Entry software OPS 304 | |||
We go in the correct attitude for entry. | |||
Autopilot will maintain an inertial attitude, and we want to be in 20 min in LVLH frame at: Pitch of 40°, no yaw or roll at Entry Interface. | |||
Autopilot will maintain an inertial attitude, and we want to be in 20 | |||
So a Pitch attitude of 330° (-30° in the game) should bring us at an attitude of 40 ° in 20 min of inertial attitude. | |||
[[File:OPS 303.jpg|1000px]] | [[File:OPS 303.jpg|1000px]] | ||
Event Time set to time before EI interface (TFF), 20 min in our case | |||
Event Time set to time before EI interface ( TFF), 20 | |||
[[File:Timer TFF.jpg|1000px]] | [[File:Timer TFF.jpg|1000px]] | ||
Line 225: | Line 177: | ||
14) We gonna dump to remaining propellant in Forward RCS tank | |||
We want to avoid potential hazard during entry. | |||
Moreover, only the aft RCS are used during entry for shuttle control. | Moreover, only the aft RCS are used during entry for shuttle control. | ||
[[File:Forward dump.jpg|1000px]] | [[File:Forward dump.jpg|1000px]] | ||
Line 242: | Line 191: | ||
15) Check that the switches linked to navigation and monitoring for entry are in the good position | |||
[[File:FWD ENTRY CHECK.jpg|1000px]] | |||
[[File:FWD ENTRY CHECK.jpg|1000px]] | |||
[[File:OVERHEAD CHECKS.jpg|1000px]] | [[File:OVERHEAD CHECKS.jpg|1000px]] | ||
16) 13 min before entry, we start the remaining APU (2 and 3) | |||
Fuel tank opened and Starter On | Fuel tank opened and Starter On | ||
Line 265: | Line 205: | ||
17) Pressurization of the SSME with hydraulic liquid to allow their repositioning of the nozzles for Drag chute opening | |||
'''Hyd Pumps switch on Norm (3000 PSI)''' | |||
'''Hyd Pumps switch on Norm ( 3000 PSI)''' | |||
[[File:MPS repress.jpg|1000px]] | [[File:MPS repress.jpg|1000px]] | ||
Checklist in game to verify that everything was done | Checklist in game to verify that everything was done | ||
[[File:Pre deorbit burn check in game.jpg|1000px]] | [[File:Pre deorbit burn check in game.jpg|1000px]] | ||
Voila, Rendez vous 5 | Voila, Rendez vous 5 min before the Entry Interface for the final Countdown |