Some news of the entry/TAEM and fdm update.

FDM-Addition of datas for High Mach ( above 4) and High altitude ( above 300 kft) concerning the Basic Drag and Lift Coefficient (Cl / Cd)

Better accuracy for first part of entry.

Lift/Drag Ratio almost on par with real one ( 1.1 ish up to mach 10).

Below mach 4, the previous parametrization of Cl/Cd implemented by Thorsten from this article

https://www.researchgate.net/publication/259900872_Dynamic_Trajectory_Control_of_Gliders kicks in and works better than interpolated datas.

Very Low energy entry ( Entry Interface up to 6000 Nm ) will be possible now, and entertaining with exotic procedures from Non Normal documentations.

-Addition of a deeper table for BodyFlap Pitch moment ( Mach, BF deflection, Alpha dependant).

That allows a better trimming of the pitch jets during first part of entry and elevons then (interesting to save RCS fuel)

-Addition of slightly improved Lift and Drag coefficient for the gear

-Addition of deeper coefficients for SpeedBrakes Lift and Drag, mach dependant now.

Shuttle is now maintaining far better 300 kts ( speed targeted for final part of approach) on a 19 ° path.

In red the new L/D ratio with speedbrakes extended ( smaller than with previous coefficients used,SB are 20 % ish more efficient)

TAEMI finished the rework of the Vertical Traj 1 ( from 80 kfeet up to 30 kfeet)

Horizontally: Range to runway

Vertically: Altitude

Both are linear scales, no quadratic range scale there.

It took me time to find solid datas to feed well the right scale, indicating our Energy state basically.

Energy / Weight = altitude + TAS² /2gPicture below to illustrate.

In White, triangle indicating our Actual Energy, almost matching the nominal energy for the TAEM chosen.

Sturn is the upper energy boundary // above, we would need more track miles hence some S-turn

MEP is the lower energy boundary // below, we would need less track miles hence some shedding with a minimal entry point ( a few miles shorter)

In blue, the EAS we should have if on the path and on energy

That scale is dynamical, parameters depend of distance to go mainly.

The Nose High/Low scale and triangle are useful in case of bad datas from Probes.

It is a kind of airspeed unreliable thing, where we have to fly the basics ( pitch settings pre determined to stay within a good flight envelop).

In the present situation and in case of loss of Air datas, we would have to maintain a pitch angle between -6° (red) and -19°(purple).

A quick glance if your are interested of some of the datas implemented.

There are good explanations in Thorsten manual and SCOM about TAEM Energy logic, and I will update manual/wiki with those few additions.