THE ARTEMIS PROJECT
PRIVATE ENTERPRISE ON THE MOON
Reference Mission
Section 4.1.1.
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Reference Mission Timeline

This is a reference mission timeline, used for costing, feasibility studies, and mission analysis. The final mission design may be quite different.

The trajectory and landing site are based on the Apollo 16 flight profile. Apollo 16 landed near Descartes Crater in April 1972. The mission profile assumes we loiter in Earth orbit for two days to stack and check out the vehicle at the start of the flight.

Launch to Low Earth Orbit

                      Date & Time  Delta T    Velocity  Delta V   Applied
Event              Phase Complete      Sec      ft/sec   ft/sec   to...
----------------   --------------  -------    --------  -------   -------
Launch                 4/08:00:00        0           0        0
LEO Insertion          4/08:11:57      717       25604   ~35000   Stack

Flight to the Moon

                      Date & Time  Delta T    Velocity  Delta V   Applied
Event              Phase Complete      Sec      ft/sec   ft/sec   to...
----------------   --------------  -------    --------  -------   -------
Translunar Injection   6/08:11:57   172800       25631       27   Stack
TLI Burn Termination   6/08:17:32      335       35649    10018   Stack

Lunar Orbit Operations

                      Date & Time  Delta T    Velocity  Delta V   Applied
Event              Phase Complete      Sec      ft/sec   ft/sec   to...
----------------   --------------  -------    --------  -------   -------
LUNO Insertion         8/22:03:20   222348                 2807   Stack
Descent Orbit Init     9/12:14:12    51052        5486        -
DOI burn termination   9/12:14:36       24        5280      206   Stack
Undock and sep        10/05:52:13    63457           -        -

LTV Lunar Orbit Circularization

                      Date & Time  Delta T    Velocity  Delta V   Applied
Event              Phase Complete      Sec      ft/sec   ft/sec   to...
----------------   --------------  -------    --------  -------   -------
LTV circ. burn Init   10/07:20:27     5294        5724        -    
LTV circ. burn term   10/07:20:32        5        5344      100   LTV

Landing on the Moon

                      Date & Time  Delta T    Velocity  Delta V   Applied
Event              Phase Complete      Sec      ft/sec   ft/sec   to...
----------------   --------------  -------    --------  -------   -------
Descent ignition      10/08:13:23     3171        5571        -   Desc
     High gate        10/08:22:43      560         355        -
     Low gate         10/08:24:05       82          80        -
     Vertical descent 10/08:24:45       40          10        -
     Landing          10/08:25:24       39           0     6696   Desc

LTV Lunar Orbit Establishment

                      Date & Time  Delta T    Velocity  Delta V   Applied
Event              Phase Complete      Sec      ft/sec   ft/sec   to...
----------------   --------------  -------    --------  -------   -------
LTV plane change #1   12/14:07:30   193326        5356        -   LTV
   Burn termination   12/14:07:39        9        5355      159   LTV

Lunar Surface Operations

Lunar surface         20/08:25:24   864000           -        -
operations

Ascent and Rendezvous

                      Date & Time  Delta T    Velocity  Delta V   Applied
Event              Phase Complete      Sec      ft/sec   ft/sec   to...
----------------   --------------  -------    --------  -------   -------
Ascent stage liftoff  20/08:25:24                    0        -   Asc
    Insertion         20/08:25:24      434        5339     6048   Asc
Rendezvous - TPI      20/08:32:38     2820        5339       50   Asc
    Braking           20/09:19:38     2453        5339       33   Asc
    Docking           20/10:00:31     1184        5339        -   Asc

Transearth Injection

                      Date & Time  Delta T    Velocity  Delta V   Applied
Event              Phase Complete      Sec      ft/sec   ft/sec   to...
----------------   --------------  -------    --------  -------   -------
TEI Prep              20/10:20:15     7200        5339        -   
Transearth injection  20/10:20:15        -        5339        -   
TEI Burn termination  22/10:20:15      150        8521     3212   LTV/Asc

Return to Earth

                      Date & Time  Delta T    Velocity  Delta V   Applied
Event              Phase Complete      Sec      ft/sec   ft/sec   to...
----------------   --------------  -------    --------  -------   -------
LEO Arrival                         172800       36176        -
LEO Rendezvous                                   25604    10572   LTV/Asc


Definitions

Notes

  1. The time listed is what the clock reads at the end of each mission phase. Delta T is the elapsed time for that mission phase, in seconds.

  2. Velocity is measured relative to Earth up to Translunar Injection at the beginning of the mission, and after Transearth Injection at the end of the mission. Otherwise, velocity is relative to the moon.

  3. Velocities are given in feet per second. To convert to meters per second, multiply feet per second by 0.3048 (exactly).

  4. The date for this timeline is tentative -- proper moon phasing is not considered. We would like to land on the moon at Angus Bay just after sunrise and spend an entire lunar day (two weeks on earth) on the surface.

  5. This mission timeline assumes we use rockets, rather than an aerobrake, to slow the spacecraft to Earth orbital velocity when we get home. This maneuver uses almost 9,000 lbs of fuel; but the additional weight of a spacecraft capable of atmospheric braking might be considerably more. Compare, for example, the anticipated weight of the Lunar Transfer Vehicle at about 7,000 lbs total dry weight (command module plus service module) to the Apollo 16 command module's weight of 27,000 lbs.

  6. Velocity and delta V numbers don't add up in some places because the value for delta V include effects not related to changing the vehicle's gross velocity. For example, the delta V budget for braking and rendezvous numbers might be expended in any direction to match orbit, so it does not affect nominal velocity. Delta V for ascent from the earth and the moon includes inefficiencies such as thrusting against the lunar gravity before achieving orbital velocity as well as altitude change, so the total delta V required for this flight is greater than the final orbital velocity.

  7. The masses of the spaceraft and the fuel required for each engine burn are available in section 4.2 of the Artemis Data Book. Detailed mass properties are in the system engineering data, in section 4.2.0.1.

Reference Mission

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