ACorbit

PARAMETER Targetheight. // Prograde burn only!
PARAMETER Targetheightx.
SET SMA TO (APOAPSIS + 600000 + PERIAPSIS + 600000)/2.
SET SMAF TO (Targetheight + 600000 + APOAPSIS + 600000)/2. // APOAPSIS MAY HAS TO BE CHANGED TO PERIAPSIS!!!!!!
SET Transfer1 TO SQRT(3531600000000*((2/(APOAPSIS + 600000))-(1/SMA))).
SET Transfer2 TO SQRT(3531600000000*((2/(APOAPSIS + 600000))-(1/SMAF))).
print transfer1.
print transfer2.
SET APKM TO ROUND(APOAPSIS/1000).
SET TARKM TO ROUND(Targetheight/1000).
SET PEKM TO ROUND(PERIAPSIS/1000).
SET DeltaVneeded TO Transfer2-Transfer1.

//node creation

SET n to NODE(TIME:SECONDS + ETA:APOAPSIS, 0, 0, DeltaVneeded).
ADD n.

SET n TO NEXTNODE.
LOCK STEERING TO n:BURNVECTOR.

//calculations of burn time

SET a0 TO maxthrust / mass.

SET eIsp TO 0.
LIST engines IN my_engines.
FOR eng IN my_engines {
SET eIsp TO eIsp + eng:maxthrust / maxthrust * eng:isp.
}

SET Ve TO eIsp * 9.80665.

SET final_mass TO mass*CONSTANT():e^(-1*n:BURNVECTOR:MAG/Ve).

SET a1 TO maxthrust / final_mass.

SET t TO n:BURNVECTOR:MAG / ((a0 + a1) / 2).

SET start_time TO TIME:SECONDS + n:ETA - t/2.
SET end_time TO TIME:SECONDS + n:ETA + t/2 - 0.5.

WAIT UNTIL TIME:SECONDS >= start_time.
LOCK throttle TO 1.
WAIT UNTIL TIME:SECONDS >= end_time.
LOCK throttle TO 0.

    remove n.
    unlock steering.
    unlock throttle.


 WAIT 10.
 HUDTEXT ("We are go", 15, 2, 50, WHITE, false).


//
// AP INCREASE
//

SET SMA2 TO (APOAPSIS + 600000 + PERIAPSIS + 600000)/2.
SET SMAF2 TO (Targetheightx + 600000 + APOAPSIS + 600000)/2.
SET Transfer3 TO SQRT(3531600000000*((2/(APOAPSIS + 600000))-(1/SMA2))).
SET Transfer4 TO SQRT(3531600000000*((2/(APOAPSIS + 600000))-(1/SMAF2))).
print transfer3.
print transfer4.
SET APKM2 TO ROUND(APOAPSIS/1000).
SET TARKM2 TO ROUND(Targetheightx/1000).
SET PEKM2 TO ROUND(PERIAPSIS/1000).
SET DeltaVneeded2 TO Transfer4 - Transfer3.
Print (DeltaVneeded2) + " DeltaV needed to go into " + TARKM2 + "Km by " + APKM2 + "Km orbit".
HUDTEXT(ROUND(DeltaVneeded2) + " DeltaV needed to go into " + TARKM2 + "Km by " + APKM2 + "Km orbit", 15, 2, 50, WHITE, false).


//node creation

SET m to NODE(TIME:SECONDS + ETA:APOAPSIS, 0, 0, DeltaVneeded2).
ADD m.

SET m TO NEXTNODE.
LOCK STEERING TO m:BURNVECTOR.

//calculations of burn time

SET a2 TO maxthrust / mass.

SET eIsp2 TO 0.
LIST engines IN my_engines.
FOR eng IN my_engines {
SET eIsp2 TO eIsp2 + eng:maxthrust / maxthrust * eng:isp.
}

SET Ve2 TO eIsp2 * 9.80665.

SET final_mass2 TO mass*CONSTANT():e^(-1*m:BURNVECTOR:MAG/Ve2).

SET a3 TO maxthrust / final_mass2.

SET t2 TO m:BURNVECTOR:MAG / ((a2 + a3) / 2).

SET start_time2 TO TIME:SECONDS + m:ETA - t2/1.75.
SET end_time2 TO TIME:SECONDS + m:ETA + t2/2 - 1.

WAIT UNTIL TIME:SECONDS >= start_time2.
LOCK throttle TO 1.
WAIT UNTIL TIME:SECONDS >= end_time2.
LOCK throttle TO 0.

if TargetHeightx >= periapsis {
    set throt to 0. // variable to hold current throttle value
    set scalefactor to 1.2. // scalefactor is some value based on the power of your engine
    lock throttle to thrott. // lock the throttle to follow the value of the variable
    until periapsis + 200 >= TargetHeightx {
        set thrott to min(((TargetHeightx - periapsis)/Targetheightx) * scalefactor, 0.01). // use min to prevent it going completely to zero
        wait 0.01. // wait one tick before recalculating
    }
}

    lock throttle to 0. // kill throttle

Remove m.
unlock steering.
unlock throttle.

LOCK STEERING TO PROGRADE.
WAIT 10.
STAGE.
WAIT 3.
LOCK STEERING TO RETROGRADE.
WAIT 10.
RUN ADORBIT(88624, 749500).