A major update to the MFD, the full Deorbit Maneuver Processor has been implemented. Most of the coding for this was done last year already, I was working on it at a very slow rate this year, but I think it's finally in a state that can be released.
It is based on the 1980 Flight Design System version of the targeting, which has a small number of simplifications. The document about it has full flowcharts though:
https://web.archive.org/web/2010052...casi.ntrs.nasa.gov/19800070819_1980070819.pdf The likely superior version of the targeting would be found in the JSC requirements document, for which I know the memo number (76-FM-93), but it is not available on the Internet. It likely can be found at the National Archives and could be requested to be scanned though.
Here the section from the FDO Console Handbook about the targeting:
The DMP will generate a solution which conforms to the following guidelines:
1. The guidance targets calculated by the DMP processor are compatible with the onboard powered flight guidance.
2. The planned deorbit maneuver results in the achievement of a correlated V, gamma, and range set at EI. This target set is calculated by the Entry Target Generator (ETG) after being called by the DMP processor.
3. The deorbit maneuver is targeted to burn a specified amount of propellant, allowing achievement of landing weight or CG constraint.
4. The targeting is such that if the primary propulsion system fails to ignite, then a pre-designated backup propulsion system can perform the maneuver with no change in input guidance targets (including time of ignition (TIG)) and achieve nominal entry conditions.
5. In the TIG-free mode, the TIG is selected so that the same amount of Orbital Maneuvering System (OMS) propellant will be required for either prime or backup propulsion system with or without propellant wasting. A positive or zero propellant margin will result if the prime system fails during the burn.
6. The targeting ensures that minimal guidance and control transients will occur for a switchover from prime to backup thrusters anytime during the burn. Consequently, body attitude changes for fuel wasting must be small when reverting to the backup propulsion system.
7. If it is not desired to find the guidance targets that are biased for both prime and backup propulsion systems, a solution can be found for any single designated propulsion system by setting the backup equal to the primary.
8. Entry crossrange will be computed, and in the event that excess fuel is burned out-of-plane (OOP), it will be burned in a direction that will decrease crossrange.
9. The deorbit solution for any future orbit may be computed by inputting the appropriate TIG threshold time.
10. A TIG-free or TIG-fixed mode can be designated.
11. A minimum Time of Free Fall (TFF) (time from burnout to EI) constraint will be enforced by relaxing the requirement for equal OOP thrust angles until the TFF exceeds or equals the minimum TFF.
All of these apply to the implementation in the MFD, except for the Entry Target Generator, which is not implemented. It would require that a large section of the onboard entry guidance is implemented in the MFD, which I felt was a slightly excessive task for an initial release of the DMP. I might do it in the future though, if I can figure it out. Right now the reentry target line (flight path angle and range at as a function of velocity at EI) is based on a simple curve fit.
The output display contains just a minimum that is required for now. In reality there were a summary and a detailed display, but I felt it was a bit too much for the initial release.
I hope it is useful! Come at me with all the bugs you find haha.
Orbiter 2016:
https://github.com/indy91/Shuttle-F...4.0-alpha-O2016/ShuttleFDOMFD_O2016_0.4.0.zip