DANURI (KPLO) v.220807
Add-on for Orbiter2016 v.160828


Launch scenario requires:
"Falcon9 for Orbiter2016"
https://www.orbiter-forum.com/resources/falcon9-for-orbiter2016.291/

Recommended Add-Ons:
"InterplanetaryMFD (IMFD) 5.7" by Jarmonik
http://users.kymp.net/p501474a/Orbiter/Orbiter.html

"LagrangeMFD 1.5 for Orbiter2016" by ADSWNJ
https://www.orbithangar.com/showAddon.php?id=82a029d1-6e28-4947-944e-329372b895ea


Installation
Unzip into your Orbiter root folder, preserve file structure.


What's in this add-on?
The DANURI spacecraft, with optional Reaction Wheel attitude control, sun-tracking solar array, Earth-tracking HGA and Nadir-pointing function.

Launch scenario for 23:08 UTC, 04 August 2022, LC-40 Cape Canaveral.
Post-launch scenario using JPL Horizons trajectory data for 05 August 2022. 


The Mission
The Danuri mission is S.Korea's pathfinder Lunar mission, using a high-efficiency ballistic transfer to a 100km polar lunar orbit.

More info here:
https://en.wikipedia.org/wiki/Danuri
https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=KPLO
https://directory.eoportal.org/web/eoportal/satellite-missions/k/kplo


Scenarios
You will find the scenarios in the Danuri folder on your Orbiter scenario tab.

The launch scenario begins shortly after 23:00 UTC, 04 August 2022, nominal launch time 23:08 UTC.
Falcon9 auto-pilot is set for 257km parking orbit at 29.5deg inclination, ASDS and FRV are in position for core and fairing retrieval. TLI burn by Falcon9 upper stage must be initiated by user.

In-flight scenario uses JPL Horizons trajectory data for 09 August 2022, following a launch on 02 August 2022, and is included for general reference.


Flight Notes
From 257km parking orbit, use Falcon9 upper stage to make TLI burn. A high-efficiency ballistic transfer to the Moon using IMFD "Course - DeltaVelocity" together with IMFD "Map - Plan", or "LagrangeMFD".
LOI insertion to 100km circular orbit at 90deg inclination, requires aprox. dV 680m/s.


Spacecraft controls and Data
[G] = Deploy Solar Array
[K] = Deploy Magnetometer Boom
[N] = Moon Nadir-pointing attitude
[Shift + NumPad] = Reaction Wheel attitude control
[Shift + NumPad5] = Reaction Wheel Kill-Rotation function

Dry Mass 418kg
Propellant Mass 260kg
Main Engines ISP 2227 Ns/kg
Main Engines Thrust 127.2N (4 x 31.8N)
RCS Engines ISP 2139Ns/kg
Attitude Control RCS = 8 x 3.48N (3 axis, not balanced)
Linear RCS = 4 x 3.48N (+Z forward direction only)


Thanks to MartinS, Jarmonik, ADSWNJ and everyone else ;-)

Happy orbits!
BrianJ
August 2022