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HUD overhaul.

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Amatsugu
2026-05-03 04:14:03 -04:00
parent 1895386fdf
commit 73868e47db
27 changed files with 397 additions and 178 deletions
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ayame.ks
+3 -1
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@@ -8,7 +8,7 @@ if status = "PRELAUNCH" {
set profile to 0.7.
set turn_start to 1000.
set target_orbit to 120000.
set target_orbit to 100000.
when altitude > 80000 then {
ag1 on.
@@ -16,6 +16,8 @@ if status = "PRELAUNCH" {
Ascent(target_orbit, turn_start, profile, 3).
wait 30.
SET V0 TO GETVOICE(0).
V0:PLAY( NOTE(400, 2.5) ).
ayame.ksm
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defaults.ks
+6 -3
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@@ -1,4 +1,7 @@
set terminal:charheight to 20.
copyPath("0:/library/lib_import", "1:/library/lib_import").
run "library/lib_import".
if status = "PRELAUNCH"
{
compile "0:/library/lib_import.ks" to "0:/library/lib_import.ksm".
copyPath("0:/library/lib_import.ksm", "1:/library/lib_import.ksm").
}
runOncePath("library/lib_import").
genericOrbit.ks
+2 -3
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@@ -10,20 +10,19 @@ if status = "PRELAUNCH" {
print "Verical Ascent: ".
set turn_start to terminal_input_number(16, 1, 6, 1000).
print "Target Orbit: ".
set target_orbit to terminal_input_number(14, 2, 8, 120000).
set target_orbit to terminal_input_number(14, 2, 8, 96000).
print "Inclination: ".
set inclination to terminal_input_number(13, 3, 8, 0).
print "Circularization: ".
set circ to terminal_input_number(17, 4, 8, 3).
print "Waiting for Engine Start...".
WaitForEngineStart().
clearScreen.
sas off.
Ascent(target_orbit:toscalar(0), turn_start:toscalar(0), profile:toscalar(0), circ:toscalar(0), inclination:toscalar(0)).
wait 30.
CORE:PART:GETMODULE("kOSProcessor"):DOEVENT("Close Terminal").
sas on.
SHUTDOWN.
genericOrbit.ksm
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hazuki.ks
+3 -1
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@@ -7,7 +7,7 @@ if status = "PRELAUNCH" {
set profile to 0.7.
set turn_start to 1000.
set target_orbit to 100000.
set target_orbit to 960000.
when altitude > 80000 then {
ag1 on.
@@ -15,6 +15,8 @@ if status = "PRELAUNCH" {
Ascent(target_orbit, turn_start, profile, 3).
wait 30.
print "Orbit Achieved, Releasing Controls".
CORE:PART:GETMODULE("kOSProcessor"):DOEVENT("Close Terminal").
SHUTDOWN.
hazuki.ksm
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library/defaults.ks
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@@ -0,0 +1,4 @@
set terminal:charheight to 20.
compile "0:/library/lib_import.ks" to "0:/library/lib_import.ksm".
copyPath("0:/library/lib_import.ksm", "1:/library/lib_import.ksm").
run "library/lib_import".
library/lib_ascent.ks
+197 -29
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@@ -2,57 +2,69 @@ import("library/lib_staging").
import("library/lib_math").
import("library/lib_vessel_utils").
import("library/lib_orbits").
import("library/lib_num_to_formatted_str").
import("library/lib_gui").
declare ASCENT_STATE is "Pre-Launch".
declare function Ascent{
parameter targetOrbit is 100000.
parameter vericalAscent is 1000.
parameter ascentProfile is 1.2.
parameter circ is 1.
parameter inc is 0.
parameter targetOrbit is 100000,
vericalAscent is 1000,
ascentProfile is 1.2,
circ is 1,
inc is 0.
print "Params (" + targetOrbit + ", " + vericalAscent + ", " + ascentProfile + ", " + circ + ", " + inc + ")".
print "Vertical Climb to " + vericalAscent.
// local tgtOrbitSI is si_formatting(targetOrbit, "m").
local vericalAscentSI is si_formatting(vericalAscent, "m").
set tgtPitch to 90.
set isDone to false.
local head to 90 + inc.
lock throttle to 1.
local head to 90 + inc.
PrepareHUD(targetOrbit, vericalAscent, ascentProfile, circ, inc).
when true then {
RenderHUD(vericalAscentSI, tgtPitch).
wait 0.01.
if ASCENT_STATE <> "DONE" {
preserve.
}
}
WaitForEngineStart().
lock steering to heading(head, tgtPitch, 270).
local lock asccent_prog to Map(apoapsis, 0, targetOrbit, 0.0, 1.0).
SetState("Vertical Ascent").
wait until altitude > vericalAscent and asccent_prog > 0.
print "Start Gravity turn. Target Apoapsis: " + targetOrbit.
SetState("Gravity Turn").
local lock ease to EaseOutExp(asccent_prog, ascentProfile).
local lock tgtPitch to (1 - ease) * 90.
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, 3).
print "Ap: " + round(apoapsis, 2) + " Pe:" + round(periapsis, 2) + " Alt: " + round(altitude, 2) + " " at(0, 4).
wait 0.1.
if not isDone{
preserve.
}
}
//Auto Staging
when periapsis < targetOrbit then{
AutoStage().
wait 0.01.
if not isDone{
if ASCENT_STATE <> "DONE" {
preserve.
}
}
wait until apoapsis >= targetOrbit.
lock throttle to 0.
unlock tgt_pitch.
lock tgtPitch to 0.
unlock steering.
SetState("Circularization").
if circ = 1 {
CircularizeBrute(targetOrbit, head).
}else if circ = 2{
@@ -60,12 +72,9 @@ declare function Ascent{
}else if circ = 3 {
lock steering to heading(head, 0, 270).
CreateCircularizationNode(apoapsis).
// if periapsis < targetOrbit and eta:apoapsis < orbit:period / 2{
// CreateCircularizationNode(apoapsis).
// }
}
set isDone to true.
SetState("Done").
unlock steering.
unlock throttle.
@@ -73,8 +82,7 @@ declare function Ascent{
}
local function Circularize{
parameter tgt.
parameter head.
parameter tgt, head.
lock throttle to 0.
lock steering to heading(head, 0, 270).
@@ -104,8 +112,7 @@ local function Circularize{
}
local function CircularizeBrute{
parameter tgt.
parameter head.
parameter tgt, head.
lock throttle to 1.
lock steering to heading(head, 0, 270).
wait until periapsis >= tgt.
@@ -116,13 +123,33 @@ local function CreateCircularizationNode{
parameter tgt.
lock throttle to 0.
local c is terminal:width /2.
PrepareCircNodeHUD().
local burnDvSI is " ---".
local burnDurationSI is " ---".
local burnDuration is 0.
when true then {
PrintRightAligned(2, 12, c - 4, burnDvSI).
PrintRightAligned(c, 12, c - 2, burnDurationSI).
if hasNode {
PrintRightAligned(2, 13, c - 4, si_formatting(nextNode:deltav:mag, "m/s")).
PrintRightAligned(c, 13, c - 2, time_formatting(circNode:eta - burnDuration /2, 0, 0, true, false)).
}
wait 0.01.
if ASCENT_STATE = "Circularization" {
preserve.
}
}
wait until altitude > 80000.
local burnDv is CalculateCircularizationDV(tgt, orbit:semimajoraxis).
set burnDvSI to si_formatting(burnDv, "m/s").
local circNode is Node(time:seconds + eta:apoapsis, 0, 0, burnDv).
add circNode.
wait 0.01.
lock steering to circNode:burnvector.
local burnDuration is CalculateMultiStageBurnDuration(burnDv).
set burnDuration to CalculateMultiStageBurnDuration(burnDv).
set burnDurationSI to time_formatting(burnDuration).
wait until circNode:eta <= burnDuration /2.
lock throttle to 1.
wait until nextNode:deltav:mag <= 10.
@@ -134,3 +161,144 @@ local function CreateCircularizationNode{
wait 0.01.
wait until throttle = 0.
}
local function PrepareHUD{
parameter targetOrbit,
vericalAscent,
ascentProfile,
circ,
inc.
clearScreen.
DrawWindow(0, 0, terminal:width, terminal:height, " Air Tako OS ").
print "Ascent: " + si_formatting(vericalAscent, "m") + " with a " + ascentProfile + " ascent profile." at (2, 1).
print "Orbit: " + si_formatting(targetOrbit, "m") + " at " + inc + "°" at (2, 2).
local circText is "None".
if circ = 1 {
set circText to "Brute Force".
}else if circ = 2{
set circText to "Blind Calculated".
}else if circ = 3 {
set circText to "Manuever Node".
}
print "Circularization Method: " + circText at (2, 3).
//Orbit Separator
DrawHorizontalLineCapped(0, 4, terminal:width, "┉").
PrintCentered(0, 5, terminal:width, "Orbit").
PrepareOrbitHUD().
//Guidance Separator
DrawHorizontalLineCapped(0, 10, terminal:width, "┉").
PrintCentered(0, 11, terminal:width, "Guidance - " + ASCENT_STATE).
//Status Bar
DrawHorizontalLineCapped(0, terminal:height - 4, terminal:width, "┉").
PrepareGuidanceHUD().
}
local function PrepareOrbitHUD{
local c is terminal:width /2.
print "Altitude:" at (2, 6).
print "Surface Alt:" at (c, 6).
//Ap
print "Ap:" at (2, 7).
print "ETA:" at (c, 7).
//Pe
print "Pe:" at (2, 8).
print "ETA:" at (c, 8).
//Speeds
print "Air Speed:" at (2, 9).
print "Orbit Speed:" at (c, 9).
}
local function PrepareGuidanceHUD{
local c is terminal:width /2.
if ASCENT_STATE = "Pre-Launch" {
print "Waiting for engine start..." at (2, 12).
}else if ASCENT_STATE = "Vertical Ascent" {
print "Vertical Ascent:" at (2, 12).
}else if ASCENT_STATE = "Gravity Turn" {
print "Target Pitch:" at (2, 12).
print "Current Pitch:" at (c, 12).
print "Deviation:" at (2, 13).
print "AoA:" at (c, 13).
}else if ASCENT_STATE = "Circularization" {
}else if ASCENT_STATE = "Done" {
if periapsis > 80000 {
print "Orbit Achieved" at (2, 12).
} else{
print "Not yet in orbit! Perform corrections manually!" at (2, 12).
}
}
}
local function PrepareCircNodeHUD{
local c is terminal:width /2.
print "Delta V:" at (2, 12).
print "Duration:" at (c, 12).
print "Burn:" at (2, 13).
print "ETA:" at (c, 13).
}
local function RenderHUD{
parameter veriticalAscSI.
parameter tgtPitch.
local c is terminal:width /2.
//Orbit Section
//altitude
PrintRightAligned(2, 6, c - 4, si_formatting(altitude, "m")).
PrintRightAligned(c, 6, c - 2, si_formatting(alt:radar, "m")).
//Ap
PrintRightAligned(2, 7, c - 4, si_formatting(apoapsis, "m")).
if airspeed < constant:e {
PrintRightAligned(c, 7, c - 2, "Inf" ).
}else{
PrintRightAligned(c, 7, c - 2, time_formatting(eta:apoapsis) ).
}
//Pe
PrintRightAligned(2, 8, c - 4, si_formatting(periapsis, "m")).
PrintRightAligned(c, 8, c - 2, time_formatting(eta:periapsis)).
//Speeds
PrintRightAligned(2, 9, c - 4, si_formatting(airspeed, "m/s")).
PrintRightAligned(c, 9, c - 2, si_formatting(ship:velocity:orbit:mag, "m/s")).
if ASCENT_STATE = "Pre-Launch" {
}else if ASCENT_STATE = "Vertical Ascent" {
print si_formatting(altitude, "m") + " of " + veriticalAscSI at (2 + 16, 12).
}else if ASCENT_STATE = "Gravity Turn" {
local curPitch is 90 - VANG(ship:up:forevector, ship:facing:forevector).
local aoa is vAng(ship:facing:vector, ship:velocity:surface).
local dPitch is tgtPitch - curPitch.
PrintRightAligned(2, 12, c - 4, round(tgtPitch, 2) + "°").
PrintRightAligned(c, 12, c - 2, round(curPitch, 2) + "°").
PrintRightAligned(2, 13, c - 4, round(dPitch, 2) + "°").
PrintRightAligned(c, 13, c - 2, round(aoa, 2) + "°").
}else if ASCENT_STATE = "Circularization" {
}else if ASCENT_STATE = "Done" {
}
RenderStatusBar().
}
local function SetState{
parameter stateText.
set ASCENT_STATE to stateText.
ClearArea(2, 11, terminal:width - 4, 6, " ").
PrintCentered(0, 11, terminal:width, "Guidance - " + ASCENT_STATE).
PrepareGuidanceHUD().
}
local function RenderStatusBar{
// ClearArea(2, terminal:height - 3, terminal:width - 4, 1, " ").
print "Status: " + status + " " at (2, terminal:height - 3) .
PrintRightAligned(2, terminal:height - 3, terminal:width - 4, ship:NAME + " - " + ship:type).
}
library/lib_ascent.ksm
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library/lib_gui.ks
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@@ -0,0 +1,89 @@
function DrawWindow{
parameter x,y,w,h,title.
DrawBox(x, y, w, h).
PrintCentered(x,y, w, title).
}
function DrawBox{
parameter x,y,w,h.
if h < 0 or y + h >= terminal:height {
set h to max(1,min(terminal:height - 2 - y,h)).
}
DrawHorizontalLineCapped(x, y, w, "━", "┏", "┓").
DrawHorizontalLineCapped(x, y+h, w, "━", "┗", "┛").
set i to 0.
until i > h - 2 {
set i to i + 1.
print "┃" at (x, y + i).
print "┃" at (x + w, y + i).
}
}
function DrawHorizontalLine{
parameter x,y,w,lineChar is "━".
DrawHorizontalLineCapped(x,y,w,lineChar, lineChar, lineChar).
}
function DrawHorizontalLineCapped{
parameter x,y,w,lineChar is "━", capCharLeft is "┣", capCharRight is "┫".
set i to 0.
local line is "".
until i > w - 1 {
set line to line + lineChar.
set i to i + 1.
}
print line at (x, y).
print capCharLeft at (x, y).
print capCharRight at (x + w -1, y).
}
function DrawVerticalLineCapped{
parameter x,y,h,lineChar is "┃", capCharTop is "┳", capCharBottom is "┻".
if h < 0 or y + h >= terminal:height {
set h to max(1,min(terminal:height - 1 - y,h)).
}
set i to 1.
until i > h - 2 {
print lineChar at (x, y+i).
set i to i + 1.
}
print capCharTop at (x, y).
print capCharBottom at (x, y + h - 1).
}
function PrintCentered {
parameter x, y,
w,
text.
set l to text:length.
print text at (x + (w/2) - (l/2), y).
}
function PrintRightAligned {
parameter x, y, w, text.
set l to text:length.
print text at (x + w - l, y).
}
function ClearArea{
parameter x, y, w, h, clearChar is " ".
set j to 0.
local line is "".
until j > w - 1 {
set line to line + clearChar.
set j to j + 1.
}
set i to 0.
until i > h - 1 {
print line at (x,y + i).
set i to i + 1.
}
}
library/lib_gui.ksm
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library/lib_gui_box.ks
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@@ -10,30 +10,22 @@ function draw_custom_gui_box {
vertical_char,
corner_char.
// Start Input Sanitization
if x < 0 or x >= terminal:width {
set x to max(0,min(terminal:width - 1,x)).
HUDTEXT("Error: [draw_custom_gui_box] X value outside terminal.", 10, 2, 30, RED, FALSE).
}
if y < 0 or y >= (terminal:height - 1) {
set y to max(0,min(terminal:height - 2,y)).
HUDTEXT("Error: [draw_custom_gui_box] Y value outside terminal", 10, 2, 30, RED, FALSE).
}
if w < 1 or x + w > terminal:width {
set w to max(1,min(terminal:width - x,w)).
HUDTEXT("Error: [draw_custom_gui_box] W value outside terminal.", 10, 2, 30, RED, FALSE).
}
if h < 1 or y + h >= terminal:height {
set h to max(1,min(terminal:height - 1 - y,h)).
HUDTEXT("Error: [draw_custom_gui_box] H value outside terminal.", 10, 2, 30, RED, FALSE).
}
// End Input Sanitization
local horizontal_str is "".
local i is 1.
until i > w {
library/lib_gui_box.ksm
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library/lib_import.ks
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@@ -1,6 +1,20 @@
declare function import {
parameter import_path.
copyPath("0:/" + import_path, "1:/" + import_path).
runOncePath(import_path).
parameter p, compileImport is true.
if status = "PRELAUNCH" {
if compileImport {
hudtext("Compiling " + p + " to ksm...", 5, 3, 21, yellow, false).
compile "0:/" + p + ".ks" to "0:/" + p + ".ksm".
SET ks TO archive:OPEN(p + ".ks").
SET ksm TO archive:OPEN(p + ".ksm").
if ks:size > ksm:size {
copyPath("0:/" + p + ".ksm", "1:/" + p).
} else{
copyPath("0:/" + p + ".ks", "1:/" + p).
}
} else{
copyPath("0:/" + p + ".ks", "1:/" + p).
}
}
runOncePath(p).
}
library/lib_import.ksm
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library/lib_math.ks
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@@ -1,22 +1,15 @@
declare function Lerp{
parameter a.
parameter b.
parameter t.
parameter a, b, t.
return a + (b - a) * t.
}
declare function Map{
parameter value.
parameter a1.
parameter a2.
parameter b1.
parameter b2.
parameter value, a1, a2, b1, b2.
return b1 + (b2 - b1) * ((value - a1) / (a2 - a1)).
}
declare function EaseOutExpo {
parameter x.
parameter p is 10.
parameter x, p is 10.
if x = 1 {
return 1.
} else{
@@ -30,7 +23,6 @@ declare function EaseOutCirc{
}
declare function EaseOutExp{
parameter x.
parameter n is 2.0.
parameter x, n is 2.0.
return x ^ (2.0 * n).
}
library/lib_math.ksm
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library/lib_num_to_formatted_str.ksm
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library/lib_orbits.ks
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@@ -1,6 +1,5 @@
declare function CalculateCircularizationDV{
parameter ap is 0.
parameter sma is 0.
parameter ap is 0, sma is 0.
local mu is body:mu.
if ap = 0 {
set ap to apoapsis.
library/lib_orbits.ksm
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library/lib_staging.ks
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@@ -1,5 +1,3 @@
declare function AutoStage{
if not EnginesInStageActive(ship:stagenum) {
stage.
@@ -7,7 +5,7 @@ declare function AutoStage{
}
}
local function EnginesInStageActive{
function EnginesInStageActive{
parameter targetStage.
list engines in allEngines.
@@ -21,12 +19,12 @@ local function EnginesInStageActive{
return true.
}
local function IsFairingStage{
function IsFairingStage{
parameter s.
}
local function StateHasEngines{
function StateHasEngines{
parameter s.
}
library/lib_staging.ksm
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library/lib_vessel_utils.ks
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@@ -4,14 +4,13 @@ declare function WaitForEngineStart{
}
declare function GetDrag{
parameter localGravity.
return ship:sensors:acc:mag + localGravity.
parameter lg.
return ship:sensors:acc:mag + lg.
}
declare function GetDragDir{
parameter localGravity.
parameter dir.
return vDot(ship:sensors:acc, dir) + localGravity.
parameter lg, dir.
return vDot(ship:sensors:acc, dir) + lg.
}
declare function AnyEngineActive{
@@ -41,19 +40,18 @@ declare function GetIsp{
}
declare function GetIspForStage{
parameter engineStage.
parameter pressure is 0.
parameter eS, p is 0.
LIST ENGINES IN egs.
local totalThrust is GetThrustOfStage(engineStage, pressure).
local totalThrust is GetThrustOfStage(eS, p).
if totalThrust = 0{
return 0.
}
local sum is 0.
local weights is 0.
for eng in egs{
if eng:stage = engineStage {
local w is eng:POSSIBLETHRUSTAT(pressure) / totalThrust.
local ispW is eng:ispat(pressure) * w.
if eng:stage = eS {
local w is eng:POSSIBLETHRUSTAT(p) / totalThrust.
local ispW is eng:ispat(p) * w.
set sum to sum + ispW.
set weights to weights + w.
}
@@ -73,70 +71,56 @@ declare function GetMaxMassFlow{
}
declare function GetMaxMassFlowForStage{
parameter engineStage.
parameter eS.
LIST ENGINES IN egs.
local sum is 0.
for eng in egs{
if eng:stage = engineStage {
if eng:stage = eS {
set sum to sum + eng:maxmassflow.
}
}
return sum.
}
declare function CalculateSuicideBurnDuration
{
declare function CalculateSuicideBurnDuration{
parameter isp.
return CalculateBurnDuration(verticalSpeed, isp, ship:mass, GetMaxMassFlow() * 1000).
}
declare function CalculateBurnDuration
{
parameter dv.
parameter burnIsp.
parameter initialMass.
parameter massFlow.
declare function CalculateBurnDuration{
parameter dv, burnIsp, iM, mF.
if burnIsp = 0 {
return 0.
}
set dv to abs(dv).
local exp is -dv / (burnIsp * constant:g0).
local massRatio is constant:e ^ (-exp).
local finalMass is initialMass / massRatio.
local fuelUsed is initialMass - finalMass.
local mR is constant:e ^ (-exp).
local fM is iM / mR.
local f is iM - fM.
if massFlow <= 0{
if mF <= 0{
return 0.
}
return fuelUsed / massFlow.
return f / mF.
}
declare function CalculateSuicideBurnAltitude
{
parameter vertSpeed.
parameter localGravity.
parameter tgtAltitude is 0.0.
parameter drag is 0.0.
parameter vS, lg, cAlt is 0.0, drag is 0.0.
local vertAcc is CalculateAverageDecceleration(localGravity, drag).
local burnAltitude is ((vertSpeed^2) / (2 * (vertAcc))).
return burnAltitude + tgtAltitude.
local vertAcc is CalculateAverageDecceleration(lg, drag).
local burnAltitude is ((vS^2) / (2 * (vertAcc))).
return burnAltitude + cAlt.
}
declare function CalculateAverageDecceleration{
parameter localGravity.
parameter drag is 0.
local maxVertAcc is (ship:availablethrust / ship:mass) - localGravity.
parameter lg.
parameter d is 0.
local maxVertAcc is (ship:availablethrust / ship:mass) - lg.
return maxVertAcc + drag.
return maxVertAcc + d.
}
declare function GetLocalGravity{
@@ -149,20 +133,17 @@ declare function GetLocalGravity{
}
declare function CalculateTimeToImpact{
parameter vertSpeed.
parameter curAltitude.
parameter gravity.
parameter tgtAltitude is 0.0.
parameter vS, cAlt, cG, tAlt is 0.0.
if gravity <= 0 or curAltitude <= 0{
if cG <= 0 or cAlt <= 0{
return 0.0.
}
local vs is abs(vertSpeed).
local g is gravity.
local hRel is curAltitude - tgtAltitude.
local disc is ((vs^2) + (2 * g * hRel)).
return (vs + sqrt(disc)) / g.
set vS to abs(vS).
local g is cG.
local hRel is cAlt - tAlt.
local disc is ((vS^2) + (2 * g * hRel)).
return (vS + sqrt(disc)) / g.
}
function CalculateMultiStageBurnDuration{
@@ -170,54 +151,51 @@ function CalculateMultiStageBurnDuration{
if ship:STAGEDELTAV(ship:stagenum):current >= dv {
return CalculateBurnDuration(dv, GetIsp(), ship:mass, GetMaxMassFlow()).
}else{
local burnTime is 0.
local bT is 0.
local remDv is dv.
from {local s is ship:stagenum. } until s = -1 step { set s to s-1.} do {
if remDv <= 0 {
return burnTime.
return bT.
}
local cdv is ship:stagedeltav(s):current.
local cmass is GetMassOfStage(s).
local cflow is GetMaxMassFlowForStage(s).
local cisp is GetIspForStage(s).
local sdv is 0.
print cdv.
if cdv >= remDv {
set sdv to remDv.
}else{
set sdv to cdv.
}
set burnTime to burnTime + CalculateBurnDuration(sdv, cisp, cmass, cflow).
set bT to bT + CalculateBurnDuration(sdv, cisp, cmass, cflow).
set remDv to remDv - cdv.
}
return burnTime.
return bT.
}
}
function GetThrustOfStage {
parameter st.
parameter pressure is 0.
parameter st, p is 0.
local totalThrust is 0.
local tTh is 0.
LIST ENGINES IN egs.
for eng in egs{
if eng:stage = st {
set totalThrust to totalThrust + eng:POSSIBLETHRUSTAT(pressure).
set tTh to tTh + eng:POSSIBLETHRUSTAT(p).
}
}
return totalThrust.
return tTh.
}
function GetMassOfStage {
parameter st.
local total is 0.
local sum is 0.
LIST PARTS IN allP.
for p in allP {
if p:stage <= st and p:DECOUPLEDIN < st {
set total to total + p:mass.
set sum to sum + p:mass.
}
}
return total.
return sum.
}
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import("library/lib_vessel_utils").
import("library/lib_ascent").
CORE:PART:GETMODULE("kOSProcessor"):DOEVENT("Open Terminal").
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).
Ascent(95000, 1000, 0.7, 3).
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