ProjectApolloMFD

ProjectApolloMFD ECS screen.

The ProjectApolloMFD provides users with important mission information, which cannot otherwise be accessed from within the simulation. Mission time, guidance parameters, environmental variables, and a TLI program are included. To access ProjectApolloMFD, activate it from the Modules tab of Orbiter's launchpad.

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.

Guidance, Navigation & Control (GNC)

This screen displays relevant flight information:

• Velocity (ft/s)
• Vertical Velocity (ft/s)
• Altitude (nm)
• Apoapsis Altitude (nm)
• Periapsis Altitude (nm)
• Inclination (deg)
• Latitude (deg)
• Longitude (deg)

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 yaAGC in order to debug the AGC flight software for example.

To access, press GNC on the main menu.

Environmental Control System (ECS)

For the CSM this screen contains two parameters:

• Crew Status
• 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, CO₂ levels, and cabin/suit pressurization. Exposing the crew to inhospitable conditions will affect their life functions, and result in an appropriate warning displayed in the Crew Status field. The number of crew members can be changed by pressing CRW and a number from 0 (no crew) to 3.

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.

Instrument Unit (IU)

This program utilizes the S-IVB IU to perform a Trans-Lunar Insertion burn (TLI).

To use:

• Calculate time to ejection and delta velocity as usual and as you do for the Simple AGC P15 program (see TLI Checklist).

• Select Project Apollo MFD.

• Press TLI on the main menu.

• Press V and enter calculated delta velocity in m/s.
• Press T and enter the time until burn commences (ex. 1200 for 1200s).

• 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...