fixed burn time calculations for multi stage burns

an.ks

@@ -1,9 +1,4 @@
-import("library/lib_vessel_utils").
 import("library/lib_ascent").
-import("library/lib_orbits").
-
-
-
 
 WaitForEngineStart().
 
@@ -11,9 +6,9 @@ CORE:PART:GETMODULE("kOSProcessor"):DOEVENT("Open Terminal").
 
 set profile to 1.2.
 set turn_start to 1000.
-set target_orbit to 100000.
+set target_orbit to 150000.
 
-Ascent(target_orbit, turn_start, profile).
+Ascent(target_orbit, turn_start, profile, 0).
 
 print "Orbit Achieved, Releasing Controls".
 CORE:PART:GETMODULE("kOSProcessor"):DOEVENT("Close Terminal").

boot/faris3Boot.ks

@@ -0,0 +1,6 @@
+wait until ship:unpacked.
+clearscreen.
+copyPath("0:/defaults", "").
+run "defaults".
+
+import("faris3").

boot/itsukiBoot.ks

@@ -0,0 +1,6 @@
+wait until ship:unpacked.
+clearscreen.
+copyPath("0:/defaults", "").
+run "defaults".
+
+import("itsuki").

boot/koyukiBoot.ks

@@ -0,0 +1,6 @@
+wait until ship:unpacked.
+clearscreen.
+copyPath("0:/defaults", "").
+run "defaults".
+
+import("koyuki").

boot/testBoot.ks

@@ -0,0 +1,6 @@
+wait until ship:unpacked.
+clearscreen.
+copyPath("0:/defaults", "").
+run "defaults".
+
+import("tests").

faris.ks

@@ -1,8 +1,6 @@
 
 
-import("library/lib_vessel_utils").
 import("library/lib_ascent").
-import("library/lib_orbits").
 
 WaitForEngineStart().
 
@@ -12,9 +10,8 @@ set profile to 1.2.
 set turn_start to 1000.
 set target_orbit to 100000.
 
-Ascent(target_orbit, turn_start, profile).
+Ascent(target_orbit, turn_start, profile, 1).
 
 print "Orbit Achieved, Releasing Controls".
-print "Circ DV" + CalculateCircularizationDV().
 CORE:PART:GETMODULE("kOSProcessor"):DOEVENT("Close Terminal").
 SHUTDOWN.

faris3.ks

@@ -0,0 +1,39 @@
+
+
+import("library/lib_ascent").
+
+WaitForEngineStart().
+
+CORE:PART:GETMODULE("kOSProcessor"):DOEVENT("Open Terminal").
+
+set profile to 1.2.
+set turn_start to 1000.
+set target_orbit to 100000.
+
+Ascent(target_orbit, turn_start, profile, 1).
+wait 3.
+
+lock steering to retrograde.
+wait 10.
+lock throttle to 1.
+wait until ship:deltav:current <= 0.
+wait 0.01.
+stage.
+
+set kuniverse:timewarp:rate to 10.
+wait until kuniverse:timewarp:rate = 0.
+
+lock steering to srfRetrograde.
+
+wait until surfaceSpeed < 1000.
+
+unlock steering.
+set kuniverse:timewarp:rate to 5.
+
+wait until ship:status = "LANDED" or ship:status = "SPLASHED".
+
+SET V0 TO GETVOICE(0). 
+V0:PLAY( NOTE(400, 2.5) ).
+
+CORE:PART:GETMODULE("kOSProcessor"):DOEVENT("Close Terminal").
+SHUTDOWN.

itsuki.ks

@@ -0,0 +1,19 @@
+
+
+import("library/lib_vessel_utils").
+import("library/lib_ascent").
+import("library/lib_orbits").
+
+WaitForEngineStart().
+
+CORE:PART:GETMODULE("kOSProcessor"):DOEVENT("Open Terminal").
+
+set profile to 1.2.
+set turn_start to 1000.
+set target_orbit to 120000.
+
+Ascent(target_orbit, turn_start, profile, 0, 73).
+
+print "Orbit Achieved, Releasing Controls".
+CORE:PART:GETMODULE("kOSProcessor"):DOEVENT("Close Terminal").
+SHUTDOWN.

koyuki.ks

@@ -0,0 +1,17 @@
+
+
+import("library/lib_ascent").
+
+WaitForEngineStart().
+
+CORE:PART:GETMODULE("kOSProcessor"):DOEVENT("Open Terminal").
+
+set profile to 1.2.
+set turn_start to 1000.
+set target_orbit to 130000.
+
+Ascent(target_orbit, turn_start, profile, 0).
+
+print "Orbit Achieved, Releasing Controls".
+CORE:PART:GETMODULE("kOSProcessor"):DOEVENT("Close Terminal").
+SHUTDOWN.

library/lib_ascent.ks

@@ -5,16 +5,23 @@ import("library/lib_orbits").
 
 
 declare function Ascent{
-	parameter targetOrbit is 100.
+	parameter targetOrbit is 100000.
 	parameter vericalAscent is 1000.
 	parameter ascentProfile is 1.2.
+	parameter circ is 1.
+	parameter inc is 0.
 
+
+	print "Params (" + targetOrbit + ", " + vericalAscent + ", " + ascentProfile + ", " + circ + ", " + inc + ")".
 	print "Vertical Climb to " + vericalAscent.
 
-	set tgtPitch to 90. 
+	set tgtPitch to 90.
+	set isDone to false. 
 
 	lock throttle to 1.
-	lock steering to heading(90, tgtPitch, 270).
+	local head to 90 + inc.
+
+	lock steering to heading(head, tgtPitch, 270).
 
 	local lock asccent_prog to  Map(apoapsis, 0, targetOrbit, 0.0, 1.0).
 
@@ -25,17 +32,21 @@ declare function Ascent{
 	local lock tgtPitch to (1 - ease) * 90.
 
 	when periapsis < targetOrbit then {
-		print "P: " + round(asccent_prog, 2) + " T:" + round(ease, 2) + " Pitch: " + round(tgtPitch, 2) + "      " at(0, 2).
+		print "P: " + round(asccent_prog, 2) + " T:" + round(ease, 2) + " Pitch: " + round(tgtPitch, 2) + "      " at(0, 3).
-		print "Ap: " + round(apoapsis, 2) + " Pe:" + round(periapsis, 2) + " Alt: " + round(altitude, 2) + "      " at(0, 3).
+		print "Ap: " + round(apoapsis, 2) + " Pe:" + round(periapsis, 2) + " Alt: " + round(altitude, 2) + "      " at(0, 4).
 		wait 0.1.
-		preserve.
+		if not isDone{
+			preserve.
+		}
 	}
 
 	//Auto Staging
 	when periapsis < targetOrbit then{
 		AutoStage().
 		wait 0.01.
-		preserve.
+		if not isDone{
+			preserve.
+		}
 	}
 
 	wait until apoapsis >= targetOrbit.
@@ -44,44 +55,57 @@ declare function Ascent{
 	lock tgtPitch to 0.
 	unlock steering.
 
+	if circ = 1 {
+		CircularizeBrute(targetOrbit, head).
+	}else if circ = 2{
+		Circularize(targetOrbit, head).
+	}
 
-	CircularizeBrute(targetOrbit).
+	set isDone to true.
-
-
 	unlock steering.
 	unlock throttle.
+
+	wait until throttle = 0.
 }
 
 
 local function Circularize{
 	parameter targetOrbit.
+	parameter head.
 
 	lock throttle to 0.
-	lock steering to heading(90, 0, 270).
+	lock steering to heading(head, 0, 270).
 	
 	local warpTime is eta:apoapsis.
 
-	local burnDv is CalculateCircularizationDV().
+	local burnDv is CalculateCircularizationDV(targetOrbit, orbit:semimajoraxis).
 	local burnDuration is CalculateMultiStageBurnDuration(burnDv).
-	print "Warping to Circularization. " + round(burnDv) + "m/s. T: " + round(burnDuration, 2) + "s" at(0, 4).
+	local remDv is ship:deltav:current - burnDv.
-	set warpTime to warpTime - burnDuration.
+	print "Warping to Circularization. " + round(burnDv) + "m/s. T: " + round(burnDuration, 2) + "s" at(0, 5).
+	print "Final Dv expected: " + remDv + "m/s".
+	set warpTime to warpTime - burnDuration /2.
 	if warpTime > 0 {
 		wait until throttle = 0.
 		wait 0.01. //Wait for accelleration to stop
-		warpTo(time:seconds + warpTime).
+		set warpmode to "physics".
+		warpTo(time:seconds + warpTime - 3).
+		wait until eta:apoapsis >= burnDuration /2.
 	}
-	wait until eta:apoapsis <= burnDuration.
 
 	lock throttle to 1.
+	// wait burnDuration.
 	wait until periapsis >= targetOrbit.
 	lock throttle to 0.
+
+	wait 0.01.
 }
 
 
 local function CircularizeBrute{
 	parameter targetOrbit.
+	parameter head.
 	lock throttle to 1.
-	lock steering to heading(90, 0, 270).
+	lock steering to heading(head, 0, 270).
 	wait until periapsis >= targetOrbit.
 	lock throttle to 0.
 }

library/lib_orbits.ks

@@ -5,84 +5,22 @@ declare function CreateDeorbit{
 	parameter offsetX is 0.0.
 	parameter offsetZ is 0.0.
 
-	local tol to 100.
-
-	lock steering to retrograde.
-	local lock align to vDot(ship:facing:vector, retrograde:vector).
-	wait until align > 0.95.
-	print align.
-
-	if dv > 0 {
-		set dv to dv * -1.
-	}
-
-	local tr to ADDONS:TR.
-	if not tr:AVAILABLE {
-		print "Trajectoris is not available".
-		return.
-	}
-
-	tr:settarget(target).
-
-
-	local deorbit to NODE(time:seconds + 200, 0, 0, dv).
-
-	until not hasNode{
-		remove nextNode.
-		wait 0.001.
-	}
-
-	add deorbit.
-	wait until tr:hasimpact.
-
-	local ipos to tr:impactpos.
-	local lock offset to (ipos:ALTITUDEPOSITION(0) - target:ALTITUDEPOSITION(0)).
-	local lock xDist to offset:x.
-	local lock zDist to ipos:lat - target:lat.
-	local dt is 60.
-	when xDist < 500000 then{
-		set dt to 30.
-	}
-	when xDist < 100000 then{
-		set dt to 5.
-	}
-	when xDist < 10000 then{
-		set dt to 1.
-	}
 	
-	when xDist < 5000 then{
-		set dt to 0.5.
-	}
-	until xDist < offsetX + tol {
-		remove nextNode.
-		wait 0.001.
-		set deorbit:eta to deorbit:eta + dt.
-		add deorbit.
-		wait until tr:hasimpact.
-		set ipos to tr:impactpos.
-		wait 0.001.
-	}
-	until abs(zDist) < offsetZ + tol{
-		remove nextNode.
-		wait 0.001.
-		if zDist > 0 {
-			set deorbit:normal to deorbit:normal - 0.1.
-		} else{
-			set deorbit:normal to deorbit:normal + 0.1.
-		}
-		add deorbit.
-		wait until tr:hasimpact.
-		set ipos to tr:impactpos.
-	}
-
-	unlock steering.
 }
 
 declare function CalculateCircularizationDV{
+	parameter ap is 0.
+	parameter sma is 0.
 	local mu is body:mu.
+	if ap = 0 {
+		set ap to apoapsis.
+	}
+	if sma = 0 {
+		set sma to orbit:semimajoraxis.
+	}
 
-	local apR is apoapsis + body:radius.
+	local apR is ap + body:radius.
 	local circVel is sqrt(mu / apR).
-	local apVel is sqrt(mu * ((2 / apR) - (1 / orbit:semimajoraxis))).
+	local apVel is sqrt(mu * ((2 / apR) - (1 / sma))).
 	return circVel - apVel.
 }

library/lib_vessel_utils.ks

@@ -16,8 +16,8 @@ declare function GetDragDir{
 }
 
 declare function AnyEngineActive{
-	list engines in allEngines.
+	list engines in egs.
-	for eng in allEngines{
+	for eng in egs{
 		if eng:ignition {
 			return true.
 		}
@@ -26,11 +26,11 @@ declare function AnyEngineActive{
 }
 
 declare function GetIsp{
-	LIST ENGINES IN allEngines.
+	LIST ENGINES IN egs.
 	declare local totalThrust is ship:maxThrust.
 	local sum is 0.
 	local weights is 0.
-	for eng in allEngines{
+	for eng in egs{
 		if eng:IGNITION and not eng:flameout{
 			local w is  eng:AVAILABLETHRUST / totalThrust.
 			local ispW is eng:isp * w.
@@ -42,15 +42,18 @@ declare function GetIsp{
 }
 
 declare function GetIspForStage{
-	parameter engineState.
+	parameter engineStage.
 	parameter pressure is 0.
-	LIST ENGINES IN allEngines.
+	LIST ENGINES IN egs.
-	local totalThrust is GetThrustOfStage(engineState).
+	local totalThrust is GetThrustOfStage(engineStage, pressure).
+	if totalThrust = 0{
+		return 0.
+	}
 	local sum is 0.
 	local weights is 0.
-	for eng in allEngines{
+	for eng in egs{
-		if eng:stage = engineState {
+		if eng:stage = engineStage {
-			local w is eng:POSSIBLETHRUST / totalThrust.
+			local w is eng:POSSIBLETHRUSTAT(pressure) / totalThrust.
 			local ispW is eng:ispat(pressure) * w.
 			set sum to sum + ispW.
 			set weights to weights + w.
@@ -60,9 +63,9 @@ declare function GetIspForStage{
 }
 
 declare function GetMaxMassFlow{
-	LIST ENGINES IN allEngines.
+	LIST ENGINES IN egs.
 	local sum is 0.
-	for eng in allEngines{
+	for eng in egs{
 		if eng:IGNITION and not eng:flameout{
 			set sum to sum + eng:maxmassflow.
 		}
@@ -70,6 +73,18 @@ declare function GetMaxMassFlow{
 	return sum.
 }
 
+declare function GetMaxMassFlowForStage{
+	parameter engineStage.
+	LIST ENGINES IN egs.
+	local sum is 0.
+	for eng in egs{
+		if eng:stage = engineStage {
+			set sum to sum + eng:maxmassflow.
+		}
+	}
+	return sum.
+}
+
 
 
 
@@ -86,9 +101,12 @@ declare function CalculateBurnDuration
 	parameter initialMass.
 	parameter massFlow.
 
+	if burnIsp = 0 {
+		return 0.
+	}
 	set dv to abs(dv).
 	local exp is -dv / (burnIsp * constant:g0).
-	local massRatio is ApproximateExp(-exp).
+	local massRatio is constant:e ^ (-exp).
 	local finalMass is initialMass / massRatio.
 	local fuelUsed is initialMass - finalMass.
 
@@ -151,67 +169,43 @@ declare function CalculateTimeToImpact{
 
 function CalculateMultiStageBurnDuration{
 	parameter dv.
-	if ship:deltav:current >= dv {
+	if ship:STAGEDELTAV(ship:stagenum):current >= dv {
-		print "one stage" at (0, 5).
+		return CalculateBurnDuration(dv, GetIsp(), ship:mass, GetMaxMassFlow()).
-		return GetBurnTime(dv, ship:maxthrust, ship:mass).
 	}else{
-		print "multi stage" at (0, 5).
 		local burnTime is 0.
 		local remDv is dv.
-		from {local s is ship:stagenum. } until s = 0 step { set s to s-1.} do {
+		from {local s is ship:stagenum. } until s = -1 step { set s to s-1.} do {
 			if remDv <= 0 {
 				return burnTime.
 			}
 			local cdv is ship:stagedeltav(s):current.
 			local cmass is GetMassOfStage(s).
-			local cthrust is GetThrustOfStage(s).
+			local cflow is GetMaxMassFlowForStage(s).
 			local cisp is GetIspForStage(s).
+			local sdv is 0.
+			print cdv.
 			if cdv >= remDv {
-				set burnTime to burnTime + GetBurnTime(remDv, cmass, cthrust, cisp).
+				set sdv to remDv.
 			}else{
-				set burnTime to burnTime + GetBurnTime(cdv, cmass, cthrust, cisp).
+				set sdv to cdv.
 			}
+			set burnTime to burnTime + CalculateBurnDuration(sdv, cisp, cmass, cflow).
 			set remDv to remDv - cdv.
 		}
 		return burnTime.
 	}
 }
 
-// Burn time from rocket equation
-function GetBurnTime {
-    parameter deltaV.
-	parameter stagethrust is 0.
-	parameter stagemass is 0.
-    parameter isp is 0.
-    
-    if deltaV:typename() = "Vector" {
-        set deltaV to deltaV:mag.
-    }
-    if isp = 0 {
-        set isp to GetIsp().
-    }
-	if stagethrust = 0 {
-		set stagethrust to ship:thrust.
-	}
-	if stagemass = 0 {
-		set stagemass to ship:mass.
-	}
-    
-    local burnTime is -1.
-    if stagethrust <> 0 {
-        set burnTime to stagemass * (1 - CONSTANT:E ^ (-deltaV / isp)) / (stagethrust / isp).
-    }
-    return burnTime.
-}
 
 function GetThrustOfStage {
 	parameter st.
+	parameter pressure is 0.
 
 	local totalThrust is 0.
-	LIST ENGINES IN allEngines.
+	LIST ENGINES IN egs.
-	for eng in allEngines{
+	for eng in egs{
 		if eng:stage = st {
-			set totalThrust to totalThrust + eng:POSSIBLETHRUST.
+			set totalThrust to totalThrust + eng:POSSIBLETHRUSTAT(pressure).
 		}
 	}
 	return totalThrust.
@@ -219,12 +213,11 @@ function GetThrustOfStage {
 
 function GetMassOfStage {
 	parameter st.
-	
 
 	local total is 0.
 	LIST PARTS IN allP.
 	for p in allP {
-		if p:stage <= st {
+		if p:stage <= st and p:DECOUPLEDIN < st {
 			set total to total + p:mass.
 		}
 	}

tests.ks

@@ -1,6 +1,26 @@
-run "library/lib_vessel_utils".
+import("library/lib_vessel_utils").
 
 CORE:PART:GETMODULE("kOSProcessor"):DOEVENT("Open Terminal").
 
-print "impact " + CalculateTimeToImpact(300, 500, 9.8).
+print "Waiting for Engine start".
-print "Burn Duration" + CalculateBurnDuration(300, 350, 5000, 3000).
+WaitForEngineStart().
+
+
+function printStatge {
+	parameter s is ship:stagenum.
+	local curDv is ship:STAGEDELTAV(s):current.
+	local isp is GetIspForStage(s).
+	local smass is GetMassOfStage(s).
+	local flow is GetMaxMassFlowForStage(s).
+	local thrust is GetThrustOfStage(s).
+
+	print "------ Stage: " + s + " ------".
+	print "Thrust: " + thrust + "kN Mass: " + round(smass, 3) + "t".
+	print "DV: " + round(curDv, 2) + "m/s ISP: " + round(isp, 2) + "s Flow: " + round(flow, 4) + "Mg/s".
+	print "Burn Duration: " + round(CalculateBurnDuration(curDv, isp, smass, flow), 2).
+}
+
+// printStatge(ship:stagenum).
+// printStatge(ship:stagenum - 1).
+
+print "Total Burn Time: " + CalculateMultiStageBurnDuration(ship:deltav:current).