Scenario File Options

The Project Apollo scenarios have a vast number of options that you can specify. Some of the more useful are:

General options

These are options specifying things such as the CSM and LM call signs, various masses, fuel masses and other parameters.

Option	Function
TCP	Specifies the height of the rocket above the ground in meters prior to launch. This can be adjusted if the mission is flown from a different launch pad to the default for the spacecraft (e.g. the Skylab 'milk stool' for the Saturn 1b).
APOLLONO	Apollo mission number. This is used to provide mission-specific events such as mission audio or system failures.
VECHNO	The Saturn vehicle number: typically this will be in the 200s for a Saturn 1b, and 500s for a Saturn V. This is used to name the separated stages and components of the spacecraft.
REALISM	Sets the realism level from 0 (lowest) to 10 (highest). Lower realism level missions will be easier to fly. Quickstart mode is level 0, Virtual AGC mode is level 5.
DLS	Set to 1 to delete the launch site when the spacecraft passes out of visible range. This can give a significant performance boost on slow machines.
FDAIDISABLED	Set to 1 to disable the OpenGL FDAI rendering. This can give a significant performance boost on slow machines.
MISSNTIME	Current mission time in seconds since launch.
IGMST	Inertial Guidance Mode start: set to the time in seconds after launch at which the autopilot switches to inertial guidance mode and starts trying to hit the target orbit rather than follow the pre-planned pitch program.
SIFUELMASS	Specifies the mass in kilograms of the fuel in the first stage (S-IC or S-IB).
SIEMPTYMASS	Specifies the empty mass in kilograms of the first stage (S-IC or S-IB).
SICSHUT	Specifies the mission time of center engine shutdown of the first stage (S-IC or S-IB).
SISHUT	Specifies the mission time of shutdown of the remaining engines of the first stage (S-IC or S-IB).
SIIFUELMASS	Specifies the mass in kilograms of the fuel in the second stage (S-IVB for Saturn 1B or S-II for Saturn V). This is not used for the INT-20.
SIIEMPTYMASS	Specifies the empty mass in kilograms of the second stage (S-IVB for Saturn 1B or S-II for Saturn V). This is not used for the INT-20.
SIICSHUT	Specifies the mission time of the center engine shutdown of the S-II stage of Saturn V and derivatives.
SIIPUT	Specifies the mission time of the PU-shift (change of mixture ratio) the second stage (S-IVB for Saturn 1B or S-II for Saturn V).
SIISHUT	Specifies the mission time of shutdown of the remaining engines of the S-II stage of Saturn V and derivatives.
S4FUELMASS	Specifies the mass in kilograms of the fuel in the S-IVB stage of Saturn V and derivatives.
LMASCFUEL	Specifies the mass in kilograms of the fuel in the LEM ascent stage, if appropriate.
LMDSCFUEL	Specifies the mass in kilograms of the fuel in the LEM descent stage, if appropriate.
SMMASS	Empty mass of the Service Module, in kilograms.
CMMASS	Empty mass of the Command Module, in kilograms.
S4PL	Specifies the payload of the SIVb stage. Current values are: 0 Standard LEM 1 ASTP 2 LTA LEM test article 3 LM1 test LEM 4 LTA8 LEM test article 5 Docking target 6 LTA6 LEM test article 7 Empty 8 Docking adapter for an SIVb 'wet workshop'
AUTOSLOW	Set to 1 to slow to 1x time acceleration when 'something important' happens. For manned flights, this is typically when a piece of mission audio is played, for unmanned flights it is typically a stage separation, engine burn, etc.
LANDFAIL	Landing failures. Set to 1 to disable all random landing failures in your scenario, or 0 to create a random set of failures.
LAUNCHFAIL	Launch failures. Set to 1 to disable all random launch failures in your scenario, or 0 to create a random set of failures.
SWITCHFAIL	Switch failures. Set to 1 to disable all random switch failures in your scenario, or 0 to create a random set of failures.
UNMANNED	Set to 1 for an unmanned mission.
ATTACHSTATE	Specifies which 'things' are attached to the spacecraft. This is a bit-field, created by combining the following values as appropriate. 1 The interstage is attached. 2 The LES is attached. 4 There is a docking probe. 8 The Apex Cover is attached. 16 The parachutes are attached. 32 There is a CSM on the launcher. 64 If there is no CSM, there is a nosecap on the SLA panels. Defaults are generally safe to use, but you may need to specify the value in the scenario for unusual missions (e.g. Apollo 5 with no LES or CSM and a nosecap uses 93).
HASPROBE	Allows you to override the default docking probe state. Set to 1 if the spacecraft has a docking probe, or 0 if it doesn't. This value is not saved in scenarios written out by orbiter, it is purely intended to allow you to set the docking probe state in initial scenarios without having to specify the full value for ATTACHSTATE. If you specify both HASPROBE and ATTACHSTATE in the same scenario, then whichever value comes second will be used for the docking probe state.
SLASTATE	Specifies the state of the SLA panels on the SIVB. Bit 8 should be set to 1 if the panels are hinged, or 0 if they separate from the SIVB. Bits 0-7 specify the angle to which they will open if hinged, defaulting to 45 degrees with an upper limit of 150 degrees; if they're not hinged, they currently always separate at 45 degrees. In most cases the default will work fine (hinged to 45 degrees on Saturn 1b, not hinged on Saturn V), but special missions may require manually setting this state. For example for hinged panels opening to 150 degrees use "SLASTATE 150" in the scenario.
PAYN	Sets the payload vessel name (e.g. Eagle for the Apollo 11 LEM). This is the name the SIVB payload will be given when it is created; LEMN can be used as a synonym.
MCC_MT_Enabled	Set to 1 to enable the ground and mission tracking of the Mission Control Center. This parameter is only used for initializing the MCC before launch and is not saved again in a scenario.

Mission parameter options

These are options specifying things such as the earth parking orbit parameters, lunar landing site, various mission time parameters etc.

Option	Function
TOAPO	Specifies the desired launch apogee altitude in kilometers.
TOPER	Specifies the desired launch perigee altitude in kilometers.
TOHDG	Specifies the desired launch azimuth in degrees.
TLIMJD	Specifies the desired MJD of the TLI burn.I
LOIMJD	Specifies the desired MJD of the first LOI burn.I
FREERETURNPECMJD	Specifies the desired MJD of the free return pericynthion.I (currently unused)
FREERETURNPECALT	Specifies the desired altitude (in meters) of the free return pericynthion.I (currently unused)
TLIOFFSETLON	Specifies the longitude of desired target offset (in radian) of the TLI burn.I
TLIOFFSETLAT	Specifies the latitude of desired target offset (in radian) of the TLI burn.I
TLIOFFSETRAD	Specifies the radius of the desired target offset (in meters) of the TLI burn.I
MOONMJD	Specifies the desired MJD of the lunar landing.I
MOONBASE	Orbiter base name of the planned landing site on the Moon, if any.I
MOONLAT	Latitude (in degrees) of the planned landing point on the Moon, if any.
MOONLONG	Longitude (in degrees) of the planned landing point on the Moon, if any.
MOONALT	Altitude (in meters) of the planned landing point on the Moon, if any.
EARTHEIMJD	Specifies the desired MJD of the Earth landing entry interface, if any.I
SPLASHLAT	Latitude (in degrees) of the planned splashdown site on the Earth, if any.I
SPLASHLONG	Longitude (in degrees) of the planned splashdown site on the Earth, if any.I

Audio options

Option	Function
LANG	Set to the appropriate string for the audio language you want to use. Currently we only ship English audio, but if, say, you downloaded a French audio add-on you could set this to French instead and the French files would take precedence.

AGC options

AGC options are specified between AGC_BEGIN and AGC_END. Options outside those lines will be ignored.

Option	Function
EMEM	Set an AGC erasable memory location to a specified value. Addresses and values are both specified in octal (base-8), so to set address 10 (decimal) to 17 (decimal) you would specify EMEM0012 21. LMPAD and CMPAD should be used in prelaunch scenarios.

Virtual AGC options

These options are set in the standard CSM configuration, not between the AGC_BEGIN and AGC_END lines. If you try to set them inside the AGC configuration they will be ignored.

Option	Function
CMPAD	Set a Virtual AGC erasable memory location in the CM AGC to a specified value. Addresses and values are both specified in octal (base-8), so to set address 10 (decimal) to 17 (decimal) you would specify EMEM0012 21. If the scenario uses the C++ AGC rather than Virtual AGC, these values are ignored. CMPAD entries are used once to set up the values in the AGC when the scenario is loaded, then thrown away. So they will not be saved to a scenario file when you exit Orbiter.
LMPAD	Set a Virtual AGC erasable memory location in the LM AGC to a specified value. Addresses and values are both specified in octal (base-8), so to set address 10 (decimal) to 17 (decimal) you would specify EMEM0012 21. If the scenario uses the C++ AGC rather than Virtual AGC, these values are ignored. Note that the LEM PAD is loaded when the LEM is created, so setting these values when the LEM already exists in the scenario will have no effect.
LMPADCNT	Sets the number of LEM PAD entries. The LEM PAD is saved in a table until the LEM is created, so the DLL needs to know how large a table to create. Any values beyond this count will be ignored.

LVDC options

LVDC options are specified between LVDC_BEGIN and LVDC_END. Options outside those lines will be ignored.

Guidance Presettings For Boost to Earth Parking Orbit

Option	Function
LVDC_dV_B	Cutoff velocity bias for S-IVB first burn. Velocity in meters per second.
LVDC_eps_2	Constant time for selection of guidance option that enforces only terminal velocity. Time in seconds.
LVDC_fx[0]	Coefficients of parking orbit inclination polynomial. Values as degrees in LVDC_fx[0] to LVDC_fx[6].
LVDC_gx[0]	Coefficients of parking orbit descending nodal angle polynomial. Values as degrees in LVDC_gx[0] to LVDC_gx[6].
LVDC_H	Third zonal harmonic coefficient in gravitational potential model.
LVDC_J	Second zonal harmonic coefficient in gravitational potential model.
LVDC_Fx[1][0]	Coefficients for the four-segment first-stage tilt polynomial. LVDC_Fx[1][0] to LVDC_Fx[1][4] for the first segment, LVDC_Fx[2][0] to LVDC_Fx[2][4] for the second segment etc.
LVDC_Rho[0]	Atmospheric density mode polynomial coefficients.
LVDC_ROV	Constant for biasing terminal range-angle prediction in first S-IVB burn.
LVDC_T_ar	Time from Timebase 1 when tilt arrest occurs.
LVDC_tau2	Estimated time to burn up vehicle completely, from a selected time between T1I=0 and the end of the artificial tau mode.
LVDC_tau2N	Nominal tau, used in the S-IVB first-burn artificial tau mode.
LVDC_tau3	Estimated time to burn up S-IVB completely, constant during first and second stages of IGM.
LVDC_T_S1	Segment switch times for four-segment first-stage tilt polynomial reference to Timebase 1.LVDC_T_S1 to LVDC_T_S3.
LVDC_Tt_3	Estimated third-stage burn time.

Guidance Presettings for Translunar Injection Boost

Option	Function
LVDC_eps_2R	Constant time for selection of guidance option that enforces only terminal velocity end-conditions during S-IVB second burn.
LVDC_eps_3R	Constant time for selection of guidance option that freezes the terminal conditions during the second S-IVB burn.
LVDC_T_4N	Nominal time from TB4 to first GCS.

Targeting Presettings for Daily Launch Window

Option	Function
LVDC_ALFTSA	Desired angle between the S Vector (Nodal crossing of target ellipse and Earth Parking Orbit) and T (Unit Target) vector at restart preparation for first opportunity. (constant across daily launch window.)
LVDC_ALFTSB	Desired angle between the S Vector (Nodal crossing of target ellipse and Earth Parking Orbit) and T (Unit Target) vector at restart preparation for second opportunity. (constant across daily launch window.)
LVDC_BETAA	Angle between S Vector and Radius Vector at initiation of S-IVB restart preparations for first opportunity. (constant across launch window.)
LVDC_BETAB	Angle between S Vector and Radius Vector at initiation of S-IVB restart preparations for second opportunity. (constant across launch window.)
LVDC_CCSA0	LVDC_CCSA0 through LVDC_CCSA14 are values of a 15-point table of the cosine of the true anomaly of the target vector as a function of time into the launch window for first opportunity.
LVDC_CCSB0	LVDC_CCSB0 through LVDC_CCSB14 are values of a 15-point table of the cosine of the true anomaly of the target vector as a function of time into the launch window for second opportunity.
LVDC_C3A0	LVDC_C3A0 through LVDC_C3A14 are values of a 15-point table of twice the specific energy of the target ellipse as a function of time into the launch window for first opportunity.
LVDC_C3B0	LVDC_C3B0 through LVDC_C3B14 are values of a 15-point table of twice the specific energy of the target ellipse as a function of time into the launch window for second opportunity.
LVDC_DECA0	LVDC_DECA0 through LVDC_DECA14 are values of a 15-point table of target vector declination as a function of time into the launch window for first opportunity.
LVDC_DECB0	LVDC_DECB0 through LVDC_DECB14 are values of a 15-point table of target vector declination as a function of time into the launch window for second opportunity.
LVDC_dV_BR	Cutoff velocity bias for translunar injection (constant across daily launch window.)
LVDC_ENA0	LVDC_ENA0 through LVDC_ENA14 are values of a 15-point table of target ellipse eccentricity as a function of time into the launch window for first opportunity.
LVDC_ENB0	LVDC_ENB0 through LVDC_ENB14 are values of a 15-point table of target ellipse eccentricity as a function of time into the launch window for second opportunity.
LVDC_FA	True anomaly of the predicted cutoff radius vector for first opportunity (constant across daily launch window).
LVDC_FB	True anomaly of the predicted cutoff radius vector for second opportunity (constant across daily launch window).
LVDC_hx[0][0]	LVDC_hx[0][0] through LVDC_hx[0][4] are coefficients of the first-segment polynomial of launch azimuth versus time.
LVDC_hx[1][0]	LVDC_hx[1][0] through LVDC_hx[1][4] are coefficients of the second-segment polynomial of launch azimuth versus time.
LVDC_hx[2][0]	LVDC_hx[2][0] through LVDC_hx[2][4] are coefficients of the third-segment polynomial of launch azimuth versus time.
LVDC_hx[3][0]	LVDC_hx[3][0] through LVDC_hx[3][4] are coefficients of the fourth-segment polynomial of launch azimuth versus time.
LVDC_RASA0	LVDC_RASA0 through LVDC_RASA14 are values of a 15-point table of target vector right ascension as a function of time into the launch window for first opportunity.
LVDC_RASB0	LVDC_RASB0 through LVDC_RASB14 are values of a 15-point table of target vector right ascension as a function of time into the launch window for second opportunity.
LVDC_RNA	Predicted radius at reignition for first opportunity (constant across daily launch window).
LVDC_RNB	Predicted radius at reignition for second opportunity (constant across daily launch window).
LVDC_t_DS0	LVDC_t_DS0 through LVDC_t_DS3 are the partition times for launch azimuth polynomial segments.
LVDC_t_D1	LVDC_t_D1 through LVDC_t_DS3 are the initial times for the azimuth polynomial segments.
LVDC_TETEO	Angle between the inertial meridian of the vernal equinox and the Pad 39A meridian at Guidance Reference Release.
LVDC_T_LO	Time from midnight Greenwich Mean Time to GRR on day of launch.
LVDC_TPA0	LVDC_TPA0 through LVDC_TPA14 are values of a 15-point table of time since launch window opening. These time are values of all out-of-orbit targeting tables for first opportunity.
LVDC_TPB0	LVDC_TPB0 through LVDC_TPB14 are values of a 15-point table of time since launch window opening. These time are values of all out-of-orbit targeting tables for second opportunity.
LVDC_t_SD1	LVDC_t_SD1 through LVDC_t_SD3 are azimuth polynomial normalizing coefficients.
LVDC_TSTA	Time to begin testing for restart preparations referenced to Timebase 5 for first opportunity.
LVDC_TSTB	Time to begin testing for restart preparations referenced to Timebase 5 for second opportunity.
LVDC_XLunarAttitude	Roll, pitch and yaw attitude required for S/C separation maneuver.

Checklist Information

These values are defined between the lines <checklist> and </checklist>

Option	Function
FILE	This is the file name of the checklist file to use.
AUTO	This defines whether to automatically execute the checklists.

Additionally there are two items to define in the launch vehicle before the scenario starts. These are NOT defined between <checklist> and </checklist>

Option	Function
LEMCHECK	This is the file name of the checklist the LEM should use.
LEMCHECKAUTO	This defines whether the LEM should automatically execute the checklists.

Scenario information

These values aren't typically set in a newly created scenario, but are saved to the scenario from the DLL when exiting Orbiter.

Option	Function
NASSPVER	This gives the version number of the DLL which saved the scenario... for 7.0 it's 70000.

<biblio force=false>

#I This setting is automatically transferred to Interplanetary MFD (IMFD).
#References
</biblio>

See Also

• Config File Options