Amatsugu/kOS
1
0
Fork 0
Code Issues Pull Requests Actions Packages Projects Releases Wiki Activity

fixed burn time calculations for multi stage burns

Browse Source
This commit is contained in:
Amatsugu
2026-04-19 21:52:07 -04:00
parent 9a4ae5e472
commit 7431ab7946
13 changed files with 221 additions and 155 deletions
Download Patch File Download Diff File Expand all files Collapse all files
an.ks
+2 -7
View File
@@ -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
+6
View File
@@ -0,0 +1,6 @@
wait until ship:unpacked.
clearscreen.
copyPath("0:/defaults", "").
run "defaults".
import("faris3").
boot/itsukiBoot.ks
+6
View File
@@ -0,0 +1,6 @@
wait until ship:unpacked.
clearscreen.
copyPath("0:/defaults", "").
run "defaults".
import("itsuki").
boot/koyukiBoot.ks
+6
View File
@@ -0,0 +1,6 @@
wait until ship:unpacked.
clearscreen.
copyPath("0:/defaults", "").
run "defaults".
import("koyuki").
boot/testBoot.ks
+6
View File
@@ -0,0 +1,6 @@
wait until ship:unpacked.
clearscreen.
copyPath("0:/defaults", "").
run "defaults".
import("tests").
faris.ks
+1 -4
View File
@@ -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
+39
View File
@@ -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
+19
View File
@@ -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
+17
View File
@@ -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
+41 -17
View File
@@ -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 "Ap: " + round(apoapsis, 2) + " Pe:" + round(periapsis, 2) + " Alt: " + round(altitude, 2) + " " at(0, 3).
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, 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).
set warpTime to warpTime - burnDuration.
local remDv is ship:deltav:current - burnDv.
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
+10 -72
View File
@@ -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
+45 -52
View File
@@ -16,8 +16,8 @@ declare function GetDragDir{
}
declare function AnyEngineActive{
list engines in allEngines.
for eng in allEngines{
list engines in egs.
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.
local totalThrust is GetThrustOfStage(engineState).
LIST ENGINES IN egs.
local totalThrust is GetThrustOfStage(engineStage, pressure).
if totalThrust = 0{
return 0.
}
local sum is 0.
local weights is 0.
for eng in allEngines{
if eng:stage = engineState {
local w is eng:POSSIBLETHRUST / totalThrust.
for eng in egs{
if eng:stage = engineStage {
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 {
print "one stage" at (0, 5).
return GetBurnTime(dv, ship:maxthrust, ship:mass).
if ship:STAGEDELTAV(ship:stagenum):current >= dv {
return CalculateBurnDuration(dv, GetIsp(), ship:mass, GetMaxMassFlow()).
}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.
for eng in allEngines{
LIST ENGINES IN egs.
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
+23 -3
View File
@@ -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 "Burn Duration" + CalculateBurnDuration(300, 350, 5000, 3000).
print "Waiting for Engine start".
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).