ProjectApolloMFD - Revision history

Indy91 at 15:57, 5 March 2022

2022-03-05T15:57:07Z

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	A number of system failures are supported in NASSP, mainly concerning the [SECS] in the CSM and engine or guidance failures in the Saturn vehicle. There are two pages with the status of the failure simulation which can be cycled with the '''PAG''' button. Using the '''RAN''' a random selection of failures can be generated.		A number of system failures are supported in NASSP, mainly concerning the [SECS] in the CSM and engine or guidance failures in the Saturn vehicle. There are two pages with the status of the failure simulation which can be cycled with the '''PAG''' button. Using the '''RAN''' a random selection of failures can be generated.

	The first page contains the SECS failures Enter the corresponding number of the failure using the '''SEQ''' button. The second page shows the engine failures on the S-IB/S-IC and S-II stages. Also supported are a IU reference failure and a failure of the S-II interstage to ~~separation~~.		The first page contains the SECS failures Enter the corresponding number of the failure using the '''SEQ''' button. The second page shows the engine failures on the S-IB/S-IC and S-II stages. Also supported are a IU reference failure and a failure of the S-II interstage to separate.

Indy91: Add failure section

2022-03-05T15:56:56Z

Add failure section

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	== Failure Simulation (FAIL) ==		== Failure Simulation (FAIL) ==

			A number of system failures are supported in NASSP, mainly concerning the [SECS] in the CSM and engine or guidance failures in the Saturn vehicle. There are two pages with the status of the failure simulation which can be cycled with the '''PAG''' button. Using the '''RAN''' a random selection of failures can be generated.

			The first page contains the SECS failures Enter the corresponding number of the failure using the '''SEQ''' button. The second page shows the engine failures on the S-IB/S-IC and S-II stages. Also supported are a IU reference failure and a failure of the S-II interstage to separation.

Indy91: Add LGC section

2022-03-05T15:51:06Z

Add LGC section

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	== Lunar Guidance Computer (LGC) ==		== Lunar Guidance Computer (LGC) ==

			The LGC screen contains a number of helpful tools for LM activation. In the upper half of the screen it shows the TEPHEM (launch time) from the CMC. Below that are IMU attitudes of the CSM and the corresponding required docked alignment of the LM.

			After the docked coarse alignment using the display attitude a fine alignment for Verb 42 can be calculated using the '''V42''' button. In almost all the cases the attitude reference (REFSMMAT) will be the same for CSM and LM. Only during Apollo 9 for the rendezvous day were local vertical, local horizontal attitude references used, which has a different definition for CSM versus LM. In this case only use the '''REF''' button and set the alignment reference to LVLH.

			Two buttons for clock initialization are included on the screen. To initialize the AGS clock using the backup method start Verb 47 on the DSKY and enter 377+00000 on the DEDA without pressing ENTRS. The '''V47''' button then causes an simultaneous ENTR press on both DSKY and DEDA. In the LGC this stores the current time as a AGS time reference. In the AGS this sets the clock time to zero.

			The second clock procedure is for comparing CMC and LGC clock. Enter Verb 06 Noun 65 on both the CSM and the LM DSKYs. The '''ENT''' button then presses ENTR on both DSKYs at the same time. The difference between the CMC and LGC clock times can then be used to enter a time increment (Verb 55) for the LGC.

	== Failure Simulation (FAIL) ==		== Failure Simulation (FAIL) ==

Indy91: Update TELE section

2022-03-05T15:08:14Z

Update TELE section

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	*S-IVB/IU Lunar Impact. This type of uplink is used to schedule a burn for a course correction for lunar impact of the S-IVB. The calculation for this burn can be found in the RTCC MFD under Utilities. After the burn parameters have been calculated input them with the '''TIG''', '''BT''', '''PIT''' and '''YAW''' buttons and uplink the maneuver.		*S-IVB/IU Lunar Impact. This type of uplink is used to schedule a burn for a course correction for lunar impact of the S-IVB. The calculation for this burn can be found in the RTCC MFD under Utilities. After the burn parameters have been calculated input them with the '''TIG''', '''BT''', '''PIT''' and '''YAW''' buttons and uplink the maneuver.
	*Remove Inhibit Maneuver No. 4. This Apollo 9 only command allows the S-IVB to maneuver back to orb rate tracking after having been in attitude hold for TD&E.		*Remove Inhibit Maneuver No. 4. This Apollo 9 only command allows the S-IVB to maneuver back to orb rate tracking after having been in attitude hold for TD&E.

			To access, press '''IU''' on the main menu.

	== Telemetry (TELE) ==		== Telemetry (TELE) ==

			The telemetry page can be used for uplinking data to the Apollo Guidance Computer. The available options are:

			*State vector update. First select the source vessel using the '''SRC''' button and the reference body (Earth or Moon) using the '''REF''' button. Also choose in which state vector slot in the AGC the uplink will occur, using the '''SLT''' button. Then press the '''SV''' button twice to start the uplink.
			*Clock update. To update the clock in either AGC use the '''CLK''' button to start the uplink.
			*Ascent Engine Arming. This LM only can be used to remotely arm of the Ascent Propulsion System. Press the '''AEAA''' button and choose the relays to set or reset.
			*Apollo 5 abort. Two buttons are included to start two abort sequences in the Apollo 5 LGC software. The first, for a suborbital abort, is started with the '''SAB'''. For a late ascent abort, following an attempt by the LM to reach orbit, use the '''COI''' button for Contingency Orbit Insertion.

	== Lunar Guidance Computer (LGC) ==		== Lunar Guidance Computer (LGC) ==

	== Failure Simulation (FAIL) ==		== Failure Simulation (FAIL) ==

Indy91: Update IU section

2022-03-05T14:57:00Z

Update IU section

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	== Instrument Unit (IU) ==		== Instrument Unit (IU) ==

	~~This program utilizes~~ the ~~[[w:Saturn_V_Instrument_Unit\|S-IVB~~ IU~~]] to perform a Trans-Lunar Insertion burn (TLI)~~.		The IU screen can be used to send various commands to the Instrument Unit. Before this can be done, select the vessel with the IU using the '''SRC''' button. The uplink options are:

	~~To use:~~		*Switch Selector. This option sends specific discrete signals to any of the Saturn stages. This can be anything from starting or stopping engines to setting or resetting single relays. A full list of available commands will be provided on the [Launch Vehicle Digital Computer] page. Use the '''STA''' button to select the stage for the command and the '''CHA''' button for the specific command identification.
	* ~~Calculate time~~ to ~~ejection and delta velocity as usual and as you do for~~ the [~~[Simple AGC~~]~~] P15 program (see [[TLI_checklist_(Quickstart) \| TLI Checklist]])~~.		*Timebase Update. Many of the events on the Saturn stages are following a precise schedule, relative to time bases (e.g. time base 7, time since TLI cutoff). It can be necessary to postpone future events. This can be done by sending a time base update. The time increment is equal to the change in event times after the update. Input a delta time with the '''TIM''' button.
			*LM Abort (Apollo 5). This Apollo 5 only commands starts the sequence of events to jettison the Lunar Module in case of an abort (e.g. S-IVB engine failure).
	* Select Project Apollo MFD.		*TD&E Enable. On a lunar mission this command enables the sequence of events for performing Transposition, Docking and Extraction in Earth orbit, following a decision to not go ahead with the TLI maneuver. The S-IVB will go into attitude hold at a preprogrammed time. This command permamently disables the TLI maneuver.
			*Restart Maneuver Enable. This command enables the Apollo 9 restart maneuver, following the separation of the CSM and LM from the S-IVB.
	* Press '''~~TLI~~''' on the ~~main menu.~~		*Timebase 8 Enable. For Apollo 10 and later the sequence of events in the S-IVB following TD&E is not enabled until this ground command is send. During Apollo 10 and 11 this command should be send shortly after LM ejection (MCC scenarios send it automatically). Timebase 8 is then started automatically 2 hours after TLI. On Apollo 12 and later sending this command immediately starts the S-IVB APS Evasive Maneuver.
			*Evasive Yaw Maneuver Enable. On Apollo 12 and later the S-IVB perform a yaw maneuver to get into an attitude pointing away from the CSM+LM stack for the evasive burn. This command should be send shortly after LM ejection, or as scheduled in the flight plan.
	* Press '''V''' ~~and enter calculated delta velocity in m/s~~.		*Execute Comm Maneuver. After the S-IVB has performed all its maneuvers for lunar slingshot or impact it can be desirable to get into an attitude that is optimal for communication with Earth. Sending this command will start an attitude maneuver to that preprogrammed attitude.
	* ~~Press '''T''' and enter~~ the time ~~until burn commences~~ (ex. ~~'''1200''' for 1200s~~).		*S-IVB/IU Lunar Impact. This type of uplink is used to schedule a burn for a course correction for lunar impact of the S-IVB. The calculation for this burn can be found in the RTCC MFD under Utilities. After the burn parameters have been calculated input them with the '''TIG''', '''BT''', '''PIT''' and '''YAW''' buttons and uplink the maneuver.
			*Remove Inhibit Maneuver No. 4. This Apollo 9 only command allows the S-IVB to maneuver back to orb rate tracking after having been in attitude hold for TD&E.
	* Wait until time to ~~ejection is exactly 1200s and press '''RUN''',~~ the ~~status changes to ''WAITING''~~. ~~You can stop~~ the ~~burn by pressing~~ '''~~STP~~'''.

	* ~~At 900s before time~~ to ~~ejection~~ the ~~burn data is passed to~~ the IU. ~~Status changes to ''RUNNING''~~, ~~you cannot stop~~ the ~~burn with~~ the ~~MFD~~. ~~However, you can inhibit~~ the ~~TLI burn~~ sequence ~~by switching~~ the ~~XLUNAR INJECT switch to SAFE~~ until ~~18s before SIV-B ignition,~~ after ~~that you can do~~ this ~~by using~~ the S-~~II/~~S-IVB ~~LV STAGE switch (permanent inhibit when used 12s~~ after ~~SIV-B ignition~~ or ~~later)~~ as ~~usual~~. ~~Now~~ the ~~time~~ to ~~burn~~ is ~~displayed counting down~~.

	* ~~At T~~-~~0:00 the~~ IU ~~performs the burn~~. ~~Once it~~ is ~~complete,~~ the ~~status~~ in the MFD ~~changes to~~ ''~~OFF~~'', ~~press~~ '''~~BCK~~''' ~~to disable the IU TLI burn program.~~

	* If something goes wrong (if you try to do a TLI burn while sitting on the launch pad for instance) the status changes to ''~~ERROR~~''~~, press~~ '''~~STP~~''' and ~~try again~~...

	== Telemetry (TELE) ==		== Telemetry (TELE) ==

Indy91: Update ECS section

2022-03-05T14:28:56Z

Update ECS section

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	== Environmental Control System (ECS) ==		== Environmental Control System (ECS) ==

	~~This~~ screen contains two parameters:		For the CSM this screen contains two parameters:

	*Crew Status		*Crew Status
	*Glycol Cooling Loops		*Glycol Cooling Loops
			*Status of CSM O2 Hose

	The crew status parameter displays the number and status of the crew. Although basic, the simulation does take into account such variables as temperature, CO<sub>2</sub> levels, and cabin/suit pressurization. Exposing the crew to inhospitable conditions will		The crew status parameter displays the number and status of the crew. Although basic, the simulation does take into account such variables as temperature, CO<sub>2</sub> levels, and cabin/suit pressurization. Exposing the crew to inhospitable conditions will
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	The second parameter allows testing of the glycol coolant loops. These loops provide vital cooling to certain spacecraft systems, as well as to the cabin and the crew's suits. Using the '''PRIM''' and '''SEC''' buttons, one can input power output values from -3000W to 3000W for either or both loops. The simulation of these systems is accurate, and effects of various power outputs on spacecraft systems can be observed. See [[Environmental Control System (CSM)]] for more informations.		The second parameter allows testing of the glycol coolant loops. These loops provide vital cooling to certain spacecraft systems, as well as to the cabin and the crew's suits. Using the '''PRIM''' and '''SEC''' buttons, one can input power output values from -3000W to 3000W for either or both loops. The simulation of these systems is accurate, and effects of various power outputs on spacecraft systems can be observed. See [[Environmental Control System (CSM)]] for more informations.

			The CSM O2 Hose can be connected when the LM is docked using the '''HOS''' button. A hose connected to the suit loop in the CSM pushes air to the LM cabin, which overpressurizes it, leading to an air circulation back to the CSM cabin. In reality and in the simulation this can be used to prevent CO2 building up in the LM without getting scrubbed, during times when the LM is still inactive.

			In the LM the additional parameters displayed are the specific status of the Commander (CDR) and Lunar Module Pilot (LMP). They can be in the cabin, suits or the PLSS. The '''CRW''' button only changes the number of crew in the cabin, so to move CDR and/or LMP into or out of the LM they first have to be moved to the cabin and then further moved into the suits or out of the LM.

			The '''EVA''' button can be used to start an EVA, provided the forward hatch is open. Due to some current limitations only one astronaut can be send outside.

	To access, press '''ECS''' on the main menu.		To access, press '''ECS''' on the main menu.

Indy91: Update GNC section

2022-03-05T14:18:53Z

Update GNC section

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	* Apoapsis Altitude (nm)		* Apoapsis Altitude (nm)
	* Periapsis Altitude (nm)		* Periapsis Altitude (nm)
			* Inclination (deg)
			* Latitude (deg)
			* Longitude (deg)

	Pressing the '''DMP''' button creates a [[Virtual AGC]] core memory dump file in the Orbiter directory. The file is named ''ProjectApollo CMC.core''~~, if~~ the file already exists it will be overwritten. The core dump file can be used with the [http://www.ibiblio.org/apollo/yaAGC.html yaAGC] in order to debug the AGC flight software for example.		Pressing the '''EMS''' button will save a bitmap of the current [[Entry Monitoring System]] scroll.

			Pressing the '''DMP''' button creates a [[Virtual AGC]] core memory dump file in the Orbiter directory. The file is named ''ProjectApollo CMC.core'' for the CMC or ''ProjectApollo LGC.core'' for the LGC. If the file already exists it will be overwritten. The core dump file can be used with the [http://www.ibiblio.org/apollo/yaAGC.html yaAGC] in order to debug the AGC flight software for example.

	To access, press '''GNC''' on the main menu.		To access, press '''GNC''' on the main menu.

Indy91: Add new PAMFD pages

2022-03-05T14:15:03Z

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	To access, press '''ECS''' on the main menu.		To access, press '''ECS''' on the main menu.

	== ~~TLI Burn Program~~ (~~TLI~~) ==		== Instrument Unit (IU) ==

	This program utilizes the [[w:Saturn_V_Instrument_Unit\|S-IVB IU]] to perform a Trans-Lunar Insertion burn (TLI).		This program utilizes the [[w:Saturn_V_Instrument_Unit\|S-IVB IU]] to perform a Trans-Lunar Insertion burn (TLI).
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	* If something goes wrong (if you try to do a TLI burn while sitting on the launch pad for instance) the status changes to ''ERROR'', press '''STP''' and try again...		* If something goes wrong (if you try to do a TLI burn while sitting on the launch pad for instance) the status changes to ''ERROR'', press '''STP''' and try again...

			== Telemetry (TELE) ==

			== Lunar Guidance Computer (LGC) ==

			== Failure Simulation (FAIL) ==

24.184.26.93 at 00:36, 24 July 2007

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	Current mission time is always displayed in the upper portion of the MFD.		Current mission time is always displayed in the upper portion of the MFD.

	All other information can be accessed on the various sub-screens, which are selectable from the main menu.		All other information can be accessed on the various sub-screens, which are selectable from the main menu.

24.184.26.93 at 00:36, 24 July 2007

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	== Mission Time ==		== Mission Time ==

	Current mission time is always displayed in the upper portion of the MFD. All other information can be accessed on the various sub-screens, which are selectable from the main menu.		Current mission time is always displayed in the upper portion of the MFD.
			All other information can be accessed on the various sub-screens, which are selectable from the main menu.

	== Guidance, Navigation & Control (GNC) ==		== Guidance, Navigation & Control (GNC) ==