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index.html
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index.html
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<!DOCTYPE HTML>
<!DOCTYPE html PUBLIC "" ""><HTML lang="en">
<HEAD>
<META content="IE=11.0000"http-equiv="X-UA-Compatible">
<META charset="UTF-8">
<META name="viewport" content="width=device-width, user-scalable=no, initial-scale=1.0, maximum-scale=1.0, minimum-scale=1.0">
<meta name="description" content="An open source orbital launch vehicle (rocket) payload calculator by Launcher" />
<meta property="og:site_name" content="Launcher Calculator"/>
<meta property="og:image" content="https://launchercalculator.com/Launcher-Calculator-ogimage.png" />
<link rel="shortcut icon" type="image/png" href="favicon.png"/>
<TITLE>Launcher Calculator</TITLE>
<link href="https://fonts.googleapis.com/css2?family=Montserrat:wght@300;400;500;700;900&display=swap" rel="stylesheet">
<STYLE>
input[type=range] {
-webkit-appearance: none;
margin: 10px 0;
width: 100%;
}
input[type=range]:focus {
outline: none;
}
input[type=range]::-webkit-slider-runnable-track {
width: 100%;
height: 1px;
cursor: pointer;
animate: 0.2s;
box-shadow: 0px 0px 0px #000000;
background: #eeeff1;
border-radius: 6px;
border: 1px solid #eeeff1;
}
input[type=range]::-webkit-slider-thumb {
box-shadow: 0px 0px 1px #000000;
border: 0px solid #000000;
height: 15px;
width: 15px;
border-radius: 42px;
background: #000000;
cursor: pointer;
-webkit-appearance: none;
margin-top: -9px;
}
input[type=range]:focus::-webkit-slider-runnable-track {
background: #eeeff1;
}
input[type=range]::-moz-range-track {
width: 100%;
height: 1px;
cursor: pointer;
animate: 0.2s;
box-shadow: 0px 0px 0px #000000;
background: #eeeff1;
border-radius: 6px;
border: 1px solid #eeeff1;
}
input[type=range]::-moz-range-thumb {
box-shadow: 0px 0px 1px #000000;
border: 0px solid #000000;
height: 15px;
width: 15px;
border-radius: 42px;
background: #000000;
cursor: pointer;
}
input[type=range]::-ms-track {
width: 100%;
height: 1px;
cursor: pointer;
animate: 0.2s;
background: transparent;
border-color: transparent;
color: transparent;
}
input[type=range]::-ms-fill-lower {
background: #eeeff1;
border: 1px solid #eeeff1;
border-radius: 12px;
box-shadow: 0px 0px 0px #000000;
}
input[type=range]::-ms-fill-upper {
background: #eeeff1;
border: 1px solid #eeeff1;
border-radius: 12px;
box-shadow: 0px 0px 0px #000000;
}
input[type=range]::-ms-thumb {
box-shadow: 0px 0px 1px #000000;
border: 0px solid #000000;
height: 15px;
width: 15px;
border-radius: 42px;
background: #000000;
cursor: pointer;
}
input[type=range]:focus::-ms-fill-lower {
background: #eeeff1;
}
input[type=range]:focus::-ms-fill-upper {
background: #eeeff1;
}
/* The Modal (background) */
.modal {
display: none; /* Hidden by default */
position: fixed; /* Stay in place */
z-index: 1; /* Sit on top */
padding-top: 100px; /* Location of the box */
left: 0;
top: 0;
width: 100%; /* Full width */
height: 100%; /* Full height */
overflow: auto; /* Enable scroll if needed */
background-color: rgb(0,0,0); /* Fallback color */
background-color: rgba(0,0,0,0.4); /* Black w/ opacity */
}
/* Modal Content */
.modal-content {
background-color: #fefefe;
margin: auto;
padding: 20px 0;
border: 1px solid #888;
width: 80%;
position: fixed;
top: 5%;
left: 0;
right: 0;
/* overflow-y: scroll; */
height: calc(100% - 20%);
}
#modelContentGroup{
overflow-y: auto;
height: calc(100% - 30px);
width: 100%;
}
#modelTitle{margin: 0;
float: left;
padding: 0 0 16px 20px;}
.model-header{
width: 100%;
border-bottom: 1px solid #cccc;
height: auto;
overflow: hidden;
}
/* The Close Button */
.close {
color: #aaaaaa;
float: right;
font-size: 28px;
font-weight: bold;
margin: -10px 20px 0px 0;
}
#popupContent{
padding: 0 30px;
text-align: justify;
}
#popupContent p{ font-size: 16px;}
.close:hover,
.close:focus {
color: #000;
text-decoration: none;
cursor: pointer;
}
h8 {display:inline-block; text-align:right; width:128px;padding: 10px 0;}
h9 {display:inline-block; text-align:right;padding: 4px 0;width:128px}
body {
font-family: 'Montserrat', sans-serif !important;
font-weight: 500;
margin: 0;
padding: 0;
background-color: #fafbff;
background-position: top;
background-repeat: repeat;
background-attachment: fixed;
font-family: "Verdana", sans-serif;
font-size: 1.2em;
text-align: center;
}
html, body {
min-height: 100%;
height: 100%;
}
.content {
background-color: #ffffff;
display: inline-block;
text-align: left;
max-width:1800px;
height: auto;
overflow: hidden;
}
input{width:64px; text-align: right; font-size: 1.1em;}
input[type=range]{width:96px;}
select{font-size: 1.1em;}
.info {
background-color: gainsboro;
padding: 15px;
position: fixed;
bottom: 0;
right: 0;
}
table {
border-collapse: collapse;
}
ul {
margin: 0;
}
.preview {
background-color: black;
color: #fff;
text-align: center;
padding: 5px 5px;
border-radius: 6px;
position: fixed;
}
.launcher-header{
display: block;
list-style: none;
height: auto;
overflow: hidden;
padding: 0;
margin-bottom: 0;
padding: 20px 20px 8px 20px;
border-bottom: 1px solid #eeeff1;
}
.headerTitle{padding-right: 20px;width: calc(40% - 35px);max-width: 530px;float: left;}
.secondHeader{padding-right: 40px !important;float: left; width:calc(30% - 30px);}
.lastChild{width: 30%;float: right;}
.secondHeader font, .lastChild font{font-weight: 600;}
.logoContent font{display: inline-flex;}
.logoContent font img{width:30px;height:30px;margin: 0 7px 0px 7px;}
.logoContent span{font-size: 16px; font-weight: 400;}
.lastChild h8{padding: 2px;text-align: right;}
#RocketDescription{margin: 0;width: 99%;overflow: hidden;font-weight: 400;line-height: 1.5; font-size: 16px;}
.launcher-header p{
margin: 5px 0 10px 0;
line-height: 1;
padding: 0;
font-size: 16px;
letter-spacing: -0.5px;
color: #000000;
}
.launcher-header p FONT{
font-weight: 600;
}
.logoContent{font-size: 26px !important;}
.headerBG{background-color: #EFF3F6;height: auto;overflow: hidden;}
.hyper-content{font-size: 14px !important;color: #6e6e6e !important;padding:3px 0 !important;}
.launcher-header li a{color: #5c00f7;font-size:14px;font-weight: 500;text-decoration:none;}
select{border-radius: 3px;background-color:#fff !important;border: solid 0.5px #688093;font-size:14.5px;padding:5px 10px;font-weight: 600;min-width: 170px;height: 32px;margin: 2px 0px;
background: url("dropdown.png") no-repeat right;
-webkit-appearance: none;
background-position-x: 96%;}
.right-select{float:right;}
#Rocket{margin-top: 5px;width: 100%;max-width:400px}
.headerTable{font-size:14px;}
.headerTable tr{font-size: 16px;font-weight: 400;}
.heighlightBG{border-radius: 2px;background-color: #5c00f7;padding: 5px;color:#fff;font-size: 18px;}
.highlightprice{padding: 0px 0 5px 0;text-align: right;}
.borderTable{border:1px solid #eeeff1;width: 100%;}
table{width: 100%;}
.borderTable tr{font-size: 15px;font-weight: 400;}
.borderTable td{padding:0px 10px;line-height: 1;}
input[type=checkbox]{width: 20px;background-color: #fff;}
input[type="text"]{border-radius: 1.5px;
border: solid 0.5px #688093;margin: 2px 0;text-align: right;
padding: 4px 8px 4px 8px;}
.tableResultContent input[type="text"]{width:85px;}
.tableResultContent .mobilelayout_r1{padding-right: 10px;}
.inputstyle-1{width:150px;text-align: left;}
.spacetitle{height: auto;overflow: hidden;background-color: #ffffff;padding: 5px 10px;border: 1px solid rgba(216, 216, 216, 0.25);}
.spacetitle select{margin-left: 15px;}
.padd2{padding:5px 10px}
.spacetitle font, .padd2 font{font-weight: 600;}
.spaceheder2cont font{font-size: 16px;font-weight: 400;}
.topspace{margin-top: 5px;}
.tdpadd1{padding: 0px 10px !important;}
.tablecontent{padding: 10px 30px 40px 30px;height:100%;overflow:hidden;}
.number-text1{padding: 4px 8px 4px 8px;margin-top: 5px;min-width: 80px;}
.kgtext{padding-left: 5px;}
.tableRocketContent{
float: left;
width: calc(55% - 15px);
padding-bottom: 3px;
}
.tableResultContent{float: left;
width: calc(45% - 15px);
margin-left: 30px;}
.right-content{float:right;border:none;padding: 6px 0 !important;}
.right-content01{padding: 2px 0 !important;}
.adwacedContent{width:100%;padding-bottom: 20px;}
.engineText{float: left;width: calc(100% - 170px);padding-top: 8px;}
.nopadd{padding-top: 0;}
.spaceheder2cont, .leftTitle{float: left;}
.layout_wt_content{text-align: right;float: right;}
.layout_wt_content input{float: left;}
.layout_wt_content span{display: inline-block;width: 20px;text-align:left;padding-left:5px;margin-top: 10px;}
.layout_wt_content h8 span{margin-top: 0;}
.adwacedContent button{margin:0 auto;display:block;font-size:16px;width: 170px;height: 30px;border-radius: 2px;border: solid 0.5px #b5bdcd;background-color: #fff;;}
.mobilelayout_r2, .mobilelayout_r2 h8{text-align:right;width: 100%;}
.mobilelayout_r1, .mobRight{text-align: right;}
.mobRight select, .mobpadd select, .mobpadd input{margin-right: 25px;}
.mobilelayout_r2 input[type="range"]{margin-top: 15px;width:calc(100% - 115px)}
.mobileinner-r1 input{margin-left: 5px;}
.rocketnewview{display: flex;float: right;}
.rocketnewview input{width: 30px;min-width: 28px;}
.rocketnewview .inputstyle-1, #Second_stage_engine_thrust{width: 60px;}
.rocketnewview span{padding-top: 7px;padding-left: 5px;}
.rocketnewview .kgtext{padding-right: 5px;}
@media only screen and (max-width: 980px) {
.tableRocketContent{float: none;width: 100%;max-width: 100%;}
.tableResultContent{float: none;width: 100%;max-width: 100%;margin: 0;}
.secondHeader{padding-right: 30px !important;}
}
@media only screen and (max-width: 768px) {
.headerTitle, .lastChild{padding: 0;width: 100%;}
.secondHeader{padding-bottom: 30px;padding-right: 0 !important;width: 100%;}
}
@media only screen and (max-width: 600px) {
#RocketDescription{width: 100%;}
.tablecontent{padding: 5px 15px 20px 5px;}
.spacetitle{display: block;}
.borderTable, .spacetitle, .borderTable td{border: none;}
.secondHeader{padding-bottom: 30px;}
.right-select{float:none;}
.borderTable tr {display: inline-block;font-size: 14px; width:100%;border-bottom:0.5px solid #eeeff1}
.borderTable td { display: inline-block;line-height: 1.3; width:calc(100%);padding: 0 5px;}
.borderTable td[hidden=true]{display: none !important;}
select{width:50%;margin: 10px 0;}
input[type="text"]{width:50%;margin: 10px 0;}
h8, h9 {padding: 6px 0;}
.right-content{float:right;text-align: right;padding: 5px 0 10px 0 !important;}
.dummy-node{display: none !important;}
input[type=range]{margin-right: 20px;}
.tableResultContent{margin:0;margin-top: 5px;}
.spacetitle{display: grid;}
.spacetitle select {margin: 15px 0 0 0;}
select {font-size: 13px;background-size: 10px;}
.mobLeft select{float: left;min-width: 49%;width: 49%;margin-bottom: 0;}
.mobRight select{float: right;min-width: 49%;width: 49%;margin-bottom: 0;margin-top: -42px;}
.engineText{padding-top:5px;line-height: 1;height: auto;width: 100%;}
.mobilelayout_l1{width: 65%;float: left;padding-top: 4px;}
.mobilelayout_r1{width: 30%;float: right;}
.mobilelayout_r1 input{width: 82%;margin: 0;float: right;margin-top: -28px;}
.mobilelayout_r1 select{width: 100%;min-width:80px;margin: 4px 0;float: right;margin-top: -15px;}
.mobilelayout_r2{width: 30%;float: right;margin-top: -23px;}
.mobilelayout_r2 h8{padding: 2px 10px;text-align: right !important;}
.padd2, .spacetitle{padding: 5px;margin-bottom:5px;border-bottom:0.5px solid #eeeff1}
.layout_wt_content{margin-top:-26px ;}
.layout_wt_content input{float: left;margin: 0;width: calc(100% - 50px) !important;}
.layout_wt_content span{float: left;padding-left: 5px;}
.layout_wt_content h9 span { margin-top: 0px;}
.layout_wt_content h8, .layout_wt_content h9{display: flex;}
.mobilelayout_l2{width: 50%;float: left;padding-top: 4px;}
.mobilelayout_r2{width: 50%;float: right;display: inline-flex;margin: 0;}
.mobilelayout_r2 input[type="range"]{width: 70px;margin: 0;float: left;margin-top: -28px;}
.mobileinner-r1{margin-left: 8px;margin-top: -25px;}
.mobRight select, .mobpadd select, .mobpadd input{margin-right: 0;}
.rocketnewview span{padding-top: 10px;padding-left: 5px;}
}
@media only screen and (max-width: 480px) {
.launcher-header{padding:10px}
.logoContent span{font-size: 14px;}
.launcher-header p FONT{font-size: 21px;}
.logoContent font img {width: 25px;margin: 0 3px 0px 3px;height: 25px;}
.hyper-content{line-height: 1.5 !important;}
.tdright{text-align: right;}
.tdright h8{text-align: right;}
}
.mobilelayout_r2{padding:0px 0;}
@media (-webkit-min-device-pixel-ratio: 2),
(min-resolution: 192dpi) {
select{background: url("[email protected]") no-repeat right;}
}
@media only screen
and (min-device-width: 320px)
and (max-device-width: 480px)
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<META name="GENERATOR" content="MSHTML 11.00.9600.17842"></HEAD>
<BODY>
<DIV class="content">
<div class="headerBG">
<ul class="launcher-header">
<li class="headerTitle">
<P title="All parameters in the Launcher Calculator have 
Hints that appear when hovering over." class="logoContent"><FONT>Launcher <img src="rocketlogo.png"> Calculator</FONT>
<BR><span>An open source orbital launch vehicle payload calculator by </span><a href="https://launcherspace.com">Launcher</a><BR>
<p class="hyper-content"><a href="https://medium.com/@launcherspace/introducing-the-launcher-rocket-calculator-f9e0ce3730d4">Blog</a> | <a href="https://youtu.be/XOZQGQaA3Hw">Tour</a> | <a class="hyper-content"><a href="#" onclick="openAbout()">About</a> | <a href="#" onclick="openLicense()">MIT License</a
> | <a href="https://github.com/LauncherSpace/Launcher-Calculator" target="_new">Github</a> | <a href="https://discord.gg/2rcRQTK" target="_new">Discord</a>
<label title="Software version number">  v36</FONT></p><center></p>
</li>
<li class="secondHeader">
<FONT size="5" title="Choose a preset Rocket or create a Custom one">Select Rocket</FONT></FONT><SELECT id="Rocket" title="Rocket name"></SELECT>
<br><h6 id="RocketDescription"></h6>
</li>
<li class="lastChild">
<FONT size="5" title="Payload mass is the main calculation result">Result</FONT>
<TABLE class="headerTable" border="0">
<TBODY>
<TR class="NegativePayload">
<TD title="Payload mass calculated by an approximate method.">Payload mass (calculated)</TD>
<TD width="300" class="tdright"><h9 class="highlightprice"><b><span class="heighlightBG"><LABEL id="Payload_mass_calculated"></LABEL> kg </span></TD>
<TR class="NegativePayload">
<TD title="The percentage ratio of payload mass to the initial rocket mass." width="600">Payload to Lift-off mass ratio</TD>
<TD width="120" class="tdright"><h8><LABEL id="Payload_to_Lift_off_mass_ratio"></LABEL> % </TD></TR>
<TR class="ProjectingH">
<TD title="The percentage ratio of assumed payload mass to the calculated payload mass.">Payload change</TD>
<TD class="tdright"><h8><LABEL id="Payload_change"></LABEL> % </TD></TR>
<TR>
<TD title="This is the complexity of the rocket development estimated on a 12-point scale. 
It takes into account only the technical complexity of achieving the performance
objectives but not the the rocket scale.">Aggressivity index</TD>
<TD class="tdright"><h8><LABEL id="Aggressivity"></LABEL> pts</TD></TR></TBODY></TABLE>
</li>
</ul>
</div>
<div class="tablecontent">
<div class="tableRocketContent">
<TABLE border="0">
<TBODY>
<TR>
<TD valign="top">
<TABLE border="0">
<TBODY>
<TR>
<TD>
<TABLE border="1" class="borderTable">
<TBODY>
<div class="borderTable"> <FONT size=5" title="Basic rocket data"><b> Rocket</FONT><div class="right-content"><div class="spaceheder2cont" title="When choosing this item, the stages mass and engines thrust are considered 
unchangeable (it is good for Payload calculation of the existing rocket), 
otherwise the relative characteristics will be used that is better for the new 
launchers designing 
This option may switch automatically if you change the parameter 
corresponding to a specific calculation type."><font size="2">Fixed design</font><INPUT id="Abs_Calculation" type="checkbox"><div class="spaceheder2cont" title="Returnable and Reusable first stage of SpaceX type. 
It should be borne in mind that Reusability requires 
certain capabilities for the first stage Engines, 
which are difficult to achieve of the most existing 
Launchers."><font size="2">Reusability</font><INPUT id="Reusable" type="checkbox"></div></TD></TR>
<TR class="Projecting">
<TD width="460" title="Choose an engine for the first stage"><div class="engineText">1st engine</div><SELECT class="right-select" id="Engine1" title="First stage engine name. 
If you select a new engine for the first time, the software will automatically 
assign a second-stage engine and the number of engines corresponding to 
an existing launch vehicle. For example - choosing F-1 you will get Saturn-V."> </TD>
<TD width="220"><div class="rocketnewview"><INPUT type="text" class="inputstyle-1" id="First_stage_engine_thrust" title="First stage engine thrust"><span class='kgtext'>kgf</span><INPUT id="First_stage_engines_number" type="text" class="number-text1" title="Quantity of engines on the first stage"><span>Qty</span></div></TD></TR>
<TR>
<TD class="mobLeft" title="
Changing the fuel or cycle in this menu only changes
the maximum and minimum limits. To compare
launchers with different fuels select 'Set averages'" width="460"><div class="engineText">1st stage Fuel & Cycle   </div><SELECT class="right-select" id="Fuel"></SELECT></TD>
<TD class="mobRight" title="Changing the cycle in this menu only changes
the maximum and minimum limits. To compare
launchers with different cycles select 'Set averages'" width="220"><SELECT id="Cycle"></SELECT> </TD></TR>
<TR class="Projecting">
<TD width="460" title="Choose an engine for the second stage"><div class="engineText">2nd engine </div><SELECT class="right-select" id="Engine2" title="Second stage engine name"> </TD>
<TD width="220"><div class="rocketnewview"><INPUT id="Second_stage_engine_thrust" type="text" class="number-text1" title="Second stage engine thrust"><span class='kgtext'>kgf</span><INPUT id="Second_stage_engines_number" type="text" class="number-text1" title="Quantity of engines on the second stage"><span>Qty</span></div></TD></TR>
<TR>
<TD class="mobLeft" title="Second stage rocket engine fuel and cycle"><div class="engineText">2nd stage Fuel & Cycle     </div><SELECT class="right-select" id="Fuel2" title="Second stage engine fuel"></SELECT></TD>
<TD class="mobRight" title="Second stage rocket engine cycle"> <SELECT id="Cycle2"></SELECT> </TD></TR>
<TR class="f3stages">
<TD class="mobLeft" title="Third stage rocket engine fuel"><div class="engineText">3rd stage Fuel & Cycle    </div><SELECT class="right-select" id="Fuel3"></SELECT></TD>
<TD class="mobRight" title="Third stage rocket engine cycle"> <SELECT id="Cycle3"></SELECT> </TD></TR>
<TR>
<TD title="Having more stages increases efficiency - but also increases the complexity and the cost of the rocket"><div class="engineText mobilelayout_l1 nopadd">Stages</div></TD>
<TD class="mobpadd"><div class="mobilelayout_r1"><SELECT id="Stages" title="Number of stages"></SELECT> </div></TD></TR>
<TR>
<TD title="Dimensionless ratio of engine thrust to start weight of the rocket stages"><div class="mobilelayout_l1">Thrust-to-weight ratio</div> </TD>
<TD style="text-align:right">1st <INPUT id="Thrust_to_weight_ratio" style="width:45px" title="Thrust to weight ratio of the 1st stage"> 2nd <INPUT id="Thrust_to_weight_ratio_2nd" style="width:45px" title="Thrust to weight ratio of the 2nd stage">  </div></TD>
<TR>
<TD title="The initial mass of a rocket"><div class="mobilelayout_l1">Lift-off mass</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="Lift_off_Mass"></LABEL> kg</div></TD></TR>
<TR class="ProjectingH">
<TD title="The initial mass of a rocket excluding payload and fairing"><div class="mobilelayout_l1">Rocket mass (Lift off excluding Payload and Fairing)</div></TD>
<TD><div class="mobilelayout_r1 layout_wt_content"><INPUT id="Rocket_Mass" class="inputstyle-1" type="text"><span>kg</span></div></TD></TR>
<TR>
<TD title="The maximum diameter midsection of the rocket, which determines the aerodynamic drag. 
For modern rockets this is usually the fairing diameter."><div class="mobilelayout_l1">Max Rocket Body Diameter</div></TD>
<TD><div class="mobilelayout_r1 layout_wt_content"><INPUT class="inputstyle-1" type="text" id="Max_midsection_D"> <span>m</span></div></TD></TR>
<TR>
<TD title="The fairing is a nose cone used to protect a spacecraft against the
aerodynamic influence during launch through an atmosphere. 
The fairing is usually separated after the vehicle has traversed
the densest part of the atmosphere."><div class="mobilelayout_l1">Fairing mass</div></TD>
<TD><div class="mobilelayout_r1 layout_wt_content"><INPUT class="inputstyle-1" type="text" id="Fairing_mass"> <span>kg</span></div></TD></TR>
<TR class="Expanding">
<TD title="A predetermined velocity, which corresponds to a flight altitude
where the separation of the fairing is permissible. 
This method is used to simplify the calculations."><div class="mobilelayout_l1">Fairing jettison velocity</div></TD>
<TD><div class="mobilelayout_r1 layout_wt_content"><INPUT id="Fairing_jettison_velocity" class="inputstyle-1" type="text"> <span>m/s</span></div></TD></TR>
<TR class="Expanding">
<TD title="Delta velocity required to achieve actual fairing separation velocity
taking into account losses."><div class="mobilelayout_l1">Fairing jettison delta-v</div></TD>
<TD><div class="mobilelayout_r1 layout_wt_content"><h8><LABEL
id="Fairing_jettison_delta_v"></LABEL> <span>m/s</span></h8></div></TD></TR>
<TR class="Electric">
<TD title="Mass of the dropped batteries of the second stage to improve payload. 
It is estimated that it is 2/3 of the total battery mass."><div class="mobilelayout_l1">Jettisoned battery mass</div></TD>
<TD><div class="mobilelayout_r1 layout_wt_content"><INPUT id="Jettisoned_battery_mass" class="inputstyle-1" type="text"><span> kg</span></div></TD></TR>
<TR class="ProjectingH">
<TD title="Estimated payload mass for the initial approximation at the beginning of the calculation"><div class="mobilelayout_l1">Assumed payload mass</div></TD>
<TD><div class="mobilelayout_r1 layout_wt_content"><INPUT id="Assumed_payload_mass" class="inputstyle-1" type="text"> <span>kg</span></div></TD></TR>
<TR>
<TD title="The percentage ratio of the second and third stage mass to the rocket mass"><div class="mobilelayout_l1">2nd stage to Rocket mass ratio</div></TD>
<TD><div class="mobilelayout_r1 layout_wt_content"><INPUT id="_2nd_Stage_mass_ratio" class="inputstyle-1" type="text"> <span>%</span></div></TD></TR>
<TR class="f3stages">
<TD title="The percentage ratio of the third stage mass to the rocket mass"><div class="mobilelayout_l1">Transfer Orbit stage to Rocket mass ratio</div></TD>
<TD><div class="mobilelayout_r1 layout_wt_content"><INPUT id="_3rd_Stage_mass_ratio" class="inputstyle-1" type="text"><span> %</span></div></TD></TR>
<TR class="ProjectingH">
<TD class="tdpadd1" title="Moving the sliders to the right increases efficiency but is more difficult to achieve" align="center">Decrease Payload <-- --> Increase Payload</TD>
<TD class="tdpadd1 right-content right-content01" title="Reasonable restrictions on the rocket characteristics"></SELECT>Limit to reasonable<INPUT id="Limitation" type="checkbox"></TD></TR>
<TR>
<TD class="tdpadd1" title="Set all sliders to minimum or maximum values." align="center"><INPUT style="width:30px" id="Set_AllMin" type="checkbox">Set all to Min <-- --> Set all to Max<INPUT style="width:30px" id="Set_AllMax" type="checkbox"></TD>
<TD class="right-content" title="Using the averaged characteristics mode"></SELECT>Set averages<INPUT id="Set_averages" type="checkbox"></TD></TR>
<TR>
<TD title="The percentage ratio of the rocket's dry mass (vehicle plus contents)
to its wet mass (vehicle plus contents plus propellant). 
Mass ratio is a measure of the efficiency of a rocket."><div class="mobilelayout_l2">1st stage Dry to Wet mass ratio</div></TD>
<TD title="Easy to reach <-- --> Hard to reach"><div class="mobilelayout_r2 layout_wt_content"><INPUT class="slider" id="_1st_Dry_to_Wet_mass_ratio_Range"
type="range" min="1" max="100" value="50"><section class="mobileinner-r1">
<INPUT id="_1st_Dry_to_Wet_mass_ratio" type="text"> <span>%</span></section></div></TD></TR>
<TR>
<TD title="The percentage ratio of the rocket's dry mass (vehicle plus contents)
to its wet mass (vehicle plus contents plus propellant). 
Mass ratio is a measure of the efficiency of a rocket."><div class="mobilelayout_l2">2nd stage Dry to Wet mass ratio</div></TD>
<TD title="Easy to reach <-- --> Hard to reach"><div class="mobilelayout_r2 layout_wt_content"><INPUT class="slider" id="_2nd_Dry_to_Wet_mass_ratio_Range"
type="range" min="1" max="100" value="50"><section class="mobileinner-r1">
<INPUT type="text" id="_2nd_Dry_to_Wet_mass_ratio"> <span>%</span></section></div></TD></TR>
<TR class="f3stages">
<TD title="The percentage ratio of the rocket's dry mass (vehicle plus contents)
to its wet mass (vehicle plus contents plus propellant). 
Mass ratio is a measure of the efficiency of a rocket."><div class="mobilelayout_l2">Transfer Orbit stage Dry to Wet mass ratio</div></TD>
<TD title="Easy to reach <-- --> Hard to reach"><div class="mobilelayout_r2 layout_wt_content"><INPUT class="slider" id="_3rd_Dry_to_Wet_mass_ratio_Range"
type="range" min="1" max="100" value="50"><section class="mobileinner-r1">
<INPUT type="text" id="_3rd_Dry_to_Wet_mass_ratio"> <span>%</span></section></div></TD></TR>
<TR>
<TD title="Any unused propellant trapped in the propulsion system
(rocket engine, plumbing, and tanks) at thrust cutoff. 
It is a factor contributing significantly to the total dead weight
of a vehicle and restricting its maximum performance"><div class="mobilelayout_l2">Unused propellant of 1st stage</div></TD>
<TD title="Easy to reach <-- --> Hard to reach"><div class="mobilelayout_r2 layout_wt_content"><INPUT class="slider" id="Unused_propellant_of_1st_Stage_Range"
type="range" min="1" max="100" value="50"><section class="mobileinner-r1">
<INPUT type="text" id="Unused_propellant_of_1st_Stage"> <span>%</span></section></div></TD></TR>
<TR>
<TD title="Any unused propellant trapped in the propulsion system
(rocket engine, plumbing, and tanks) at thrust cutoff. 
It is a factor contributing significantly to the total dead weight
of a vehicle and restricting its maximum performance"><div class="mobilelayout_l2">Unused propellant of 2nd stage</div></TD>
<TD title="Easy to reach <-- --> Hard to reach"><div class="mobilelayout_r2 layout_wt_content"><INPUT class="slider" id="Unused_propellant_of_2nd_Stage_Range"
type="range" min="1" max="100" value="50"><section class="mobileinner-r1">
<INPUT type="text" id="Unused_propellant_of_2nd_Stage"> <span>%</span></section></div></TD></TR>
<TR class="f3stages">
<TD title="Any unused propellant trapped in the propulsion system 
(rocket engine, plumbing, and tanks) at thrust cutoff. 
It is a factor contributing significantly to the total dead weight
of a vehicle and restricting its maximum performance"><div class="mobilelayout_l2">Unused propellant of Transfer Orbit stage</div></TD>
<TD title="Easy to reach <-- --> Hard to reach"><div class="mobilelayout_r2 layout_wt_content"><INPUT class="slider" id="Unused_propellant_of_Transfer_Orbit_Stage_Range"
type="range" min="1" max="100" value="50"><section class="mobileinner-r1">
<INPUT type="text" id="Unused_propellant_of_Transfer_Orbit_Stage"> <span>%</span></section></div></TD></TR>
<TR>
<TD title="The generated thrust divided by the propellant mass flow rate, 
 resulting in units of time (seconds). Specific impulse is
a measure of how effectively a jet engine uses fuel. 
At sea level, the thrust of a rocket engine is reduced due to
the influence of atmospheric pressure."><div class="mobilelayout_l2">1st stage Isp sea level or at the start altitude</div></TD>
<TD title="Easy to reach <-- --> Hard to reach"><div class="mobilelayout_r2 layout_wt_content"><INPUT class="slider" id="First_stage_isp_sea_level_Range"
type="range" min="1" max="100" value="50"><section class="mobileinner-r1">
<INPUT type="text" id="First_stage_isp_sea_level"> <span>s</span></section></div></TD></TR>
<TR>
<TD title="The generated thrust divided by the propellant mass flow rate, 
 resulting in units of time (seconds). Specific impulse is
a measure of how effectively a jet engine uses fuel."><div class="mobilelayout_l2">1st stage Isp vacuum</div></TD>
<TD title="Easy to reach <-- --> Hard to reach"><div class="mobilelayout_r2 layout_wt_content"><INPUT class="slider" id="First_stage_isp_vac_Range" type="range"
min="1" max="100" value="50"><section class="mobileinner-r1">
<INPUT type="text" id="First_stage_isp_vac"> <span>s</span></section></div></TD></TR>
<TR>
<TD title="The generated thrust divided by the propellant mass flow rate, 
 resulting in units of time (seconds). Specific impulse is
a measure of how effectively a jet engine uses fuel. 
The specific impulse of the upper stage engines is usually higher, 
since due to the absence of amospheric pressure a higher
expansion ratio can be achieved (longer nozzle)."><div class="mobilelayout_l2">2nd stage Isp</div></TD>
<TD title="Easy to reach <-- --> Hard to reach"><div class="mobilelayout_r2 layout_wt_content"><INPUT class="slider" id="Second_stage_isp_vac_Range"
type="range" min="1" max="100" value="50"><section class="mobileinner-r1">
<INPUT type="text" id="Second_stage_isp_vac"> <span>s</span></section></div></TD></TR>
<TR class="f3stages">
<TD title="The generated thrust divided by the propellant mass flow rate, 
 resulting in units of time (seconds). Specific impulse is
a measure of how effectively a jet engine uses fuel."><div class="mobilelayout_l2">Transfer Orbit stage Isp</div></TD>
<TD title="Easy to reach <-- --> Hard to reach"><div class="mobilelayout_r2 layout_wt_content"><INPUT class="slider" id="Transfer_Orbit_Stage_isp_Range"
type="range" min="1" max="100" value="50"><section class="mobileinner-r1">
<INPUT type="text" id="Transfer_Orbit_Stage_isp"> <span>s</span></section></div></TD></TR>
<TR class="ProjectingH">
<TD title="Percentage change in the specific impulse of engines of all stages 
to demonstrate its effect on the rocket performance."><div class="mobilelayout_l2">Specific Impulse variation</div></TD>
<TD><div class="mobilelayout_r2 layout_wt_content"><INPUT class="slider" id="Specific_Impulse_Variation_Range"
type="range" min="90" max="110" value="100"><section class="mobileinner-r1">
<INPUT type="text" id="Specific_Impulse_Variation"> <span>%</span></section></div></TD></TR></TBODY></TABLE></TD></TR>
</TBODY></TABLE></TD>
</TR></TBODY></TABLE>
</div>
<div class="tableResultContent">
<TABLE border="0">
<TBODY>
<TR>
<TD valign="top">
<TABLE border="0">
<TBODY>
<TR>
<TD>
<div class="spacetitle"><FONT class="leftTitle" size=5" title="Choose the Launch point">Spaceport</FONT><div class="spaceheder2cont"> <SELECT title="Spaceport name"
id="StartingPoint"></SELECT> <id="Air Launch" title="Launch of an existing rocket from an airplane"><font size="2">Air Launch</font><INPUT id="Air_Launch" type="checkbox"></div>
</div>
<TABLE border="1" class="borderTable">
<TBODY title="">
<TR>
<TD title="Spaceport or (in case air launch) airplane altitude above sea level" width="460"><div class="mobilelayout_l1">Launch point Altitude</div></TD>
<TD width="220"><div class="mobilelayout_r1 layout_wt_content"><INPUT type="text" id="Starting_point_Altitude"> <span>km</span></div></TD></TR>
<TR>
<TD title="Speed added to rocket speed when starting from an airplane."><div class="mobilelayout_l1">Additional velocity (Air Launch)</div></TD>
<TD><div class="mobilelayout_r1 layout_wt_content"><INPUT type="text" id="Additional_Speed"><span> m/s</span></div></TD></TR>
<TR>
<TD title="An angle which ranges from 0 deg at the Equator to 90 deg (North or South)"><div class="mobilelayout_l1">Spaceport Latitude</div></TD>
<TD><div class="mobilelayout_r1 layout_wt_content"><INPUT type="text" id="Spaceport_latitude"> <span>deg</span></div></TD></TR>
<TR class="Expanding">
<TD title="An approximate azimuth calculated by spherical trigonometry."><div class="mobilelayout_l1">Auxiliary angle</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="Intermediate_angle"></LABEL> <span>deg</span></h8></div></TD></TR>
<TR>
<TD title="The angle between the north direction and the projection
of the initial orbital plane onto the launch location."><div class="mobilelayout_l1">Launch Azimuth</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="Launch_azimuth"></LABEL> <span>deg</span></h8></div></</TD></TR>
<TR>
<TD title="The speed of the Earth surface due to the Earth's rotation
at the latitude of the Spaceport."><div class="mobilelayout_l1">Earth rotation velocity</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="Launch_point_speed"></LABEL> <span>m/s</span></h8></div></TD></TR>
<TR class="Expanding">
<TD title="The imaginary satellite velocity at the starting point altitude, which is necessary
for calculating the Hohmann Transfer to Low Earth Orbit."><div class="mobilelayout_l1">Launch point altitude orb. velocity (imaginary)</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL
id="Starting_point_Altitude_orbital_velocity"></LABEL> <span>m/s</span></h8></div></TD></TR>
<TR class="Expanding">
<TD title="The absolute orbital speed of the satellite"><div class="mobilelayout_l1">Absolute orbital velocity</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="Absolute_orbital_velocity"></LABEL> <span>m/s</span></h8></div></TD></TR>
<TR class="Expanding">
<TD title="The orbital speed of the satellite relative to the Earth surface."><div class="mobilelayout_l1">Relative orbital velocity</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="Orbital_velocity"></LABEL><span> m/s</span></h8></div></TD></TR>
<TR class="Expanding">
<TD title="Increment of speed depending on the direction of launch relative to
the direction of Earth's rotation."><div class="mobilelayout_l1">Orbital velocity gain due to the Earth rotation</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="Orbital_velocity_increment_due_to_the_Earth_rotation"></LABEL><span> m/s</span></h8></div></TD></TR>
<TR class="Expanding">
<TD title="Auxiliary delta-v for orbital maneuver calculation."><div class="mobilelayout_l1">Delta-v for circular orbit (ideal)</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL
id="Vsp_for_circular_orbit"></LABEL> <span>m/s</span></h8></div></TD></TR>
<TR class="Expanding">
<TD title="Auxiliary delta-v for losses calculation."><div class="mobilelayout_l1">Delta-v for LEO (losses calc.)</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL
id="Vsp_for_LEO"></LABEL> <span>m/s</span></h8></div></TD></TR></TBODY></TABLE></TR>
<TR >
<TD>
<div class="spacetitle topspace">
<FONT class="leftTitle" size="5" title="Choose the Orbit you want to reach. 
 Orbits for flights to planets only 
mean reaching these planets, 
not arrival in their orbits or landing.">Orbit</FONT><div class="spaceheder2cont"> <SELECT id="Orbit" title="Orbit or Planet to reach"></SELECT>
<FONT size="2"><LABEL id="OrbitDescription"></LABEL></div></FONT>
</div>
<TABLE border="1" class="borderTable">
<TBODY>
<TR>
<TD title="The point of the orbit closest to Earth" width="460"><div class="mobilelayout_l1"><LABEL id="Reference"></LABEL> Orbit Perigee</div></TD>
<TD width="220"><div class="mobilelayout_r1 layout_wt_content"><INPUT type="text" id="Orbit_Perigee"> <span>km</span></div></TD></TR>
<TR>
<TD title="The point of the orbit farthest from Earth"><div class="mobilelayout_l1">Orbit Apogee (0 means a circular orbit)</div></TD>
<TD><div class="mobilelayout_r1 layout_wt_content"><INPUT type="text" id="Orbit_Apogee"> <span>km</span></div></TD></TR>
<TR class="fGEOI">
<TD title="The angle between the Earth's equatorial plane and the satellite's orbital plane. 
The inclination of an orbit is always greater than the spaceport latitude. 
Decreasing the orbit inclination requires a special maneuver and leads
to a significant enegry expenditure."><div class="mobilelayout_l1">Orbit Inclination</div></TD>
<TD><div class="mobilelayout_r1 layout_wt_content"><INPUT type="text" id="Orbit_Inclination"><span> deg</span></div></TD></TR>
<TR class="Expanding">
<TD title="Orbital speed at perigee (maximum)"><div class="mobilelayout_l1">Perigee velocity</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="Perigee_velocity"></LABEL> <span>m/s</span></h8></div></TD></TR>
<TR class="Expanding">
<TD title="Orbital speed at apogee (minimum)"><div class="mobilelayout_l1">Apogee velocity</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="Apogee_velocity"></LABEL><span> m/s</span></h8></div></TD></TR>
<TR>
<TD title="The time a given satellite takes to complete one orbit around Earth"><div class="mobilelayout_l1">Orbital Period</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="Orbital_period"></LABEL><span> min</span></h8></div></TD></TR>
<TR class="fGEO">
<TD title="Velocity increment needed to achieve zero inclination within a Geosynchronous orbit
if the inclination of the Geosynchronous Transfer Orbit is not a zero. 
Usually this velocity increment is added at the apogee of the Geosynchronous Transfer Orbit."><div class="mobilelayout_l1">Delta-v for change orbit inclination to 0</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL
id="Vsp_for_inclination_change"></LABEL> <span>m/s</span></h8></div></TD></TR>
<TR class="Expanding">
<TD title="Delta velocity needed for injection into target orbit without
taking into account the effect of the Earth's rotation."><div class="mobilelayout_l1">Orbital (injection) velocity</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="Injection_velocity"></LABEL><span> m/s</span></h8></div></TD></TR>
<TR>
<TD title="Delta-v, as used in spacecraft flight dynamics, is a measure of the impulse per unit of 
spacecraft mass that is needed to perform a maneuver, such as launching from or landing
on a planet or moon, or an in-space orbital maneuver. It is a scalar that has the units of speed. 
As used in this context, it is not the same as the physical change in velocity of the vehicle. 
The required delta-v to achieve a given orbit in this software is calculated according to the
Hohmann Transfer formula for the energy-optimal two burn maneuver which provides 
very good accuracy. However, these formulas do not take into account the losses associated
with the Earth's gravity and atmosphere."><div class="mobilelayout_l1">Delta-v for target orbit (ideal)</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL
id="Vsp_for_target_orbit"></LABEL><span> m/s</span></h8></div></TD></TR>
<TR>
<TD title="Delta velocity for injection to trans-planet orbit from a 200km reference orbit"><div class="mobilelayout_l1">Extra velocity for flight to the planets</div></TD>
<TD><div class="mobilelayout_r1 layout_wt_content"><INPUT type="text" id="Extra_speed_for_flight_to_the_planets"> <span>m/s</span></div></TD></TR></TBODY></TABLE></TD></TR >
<TR>
<TD><div class="spacetitle topspace padd2">
<FONT size="5" title="Empirically determined delta-v losses for injection into LEO">Losses<BR></FONT>
</div>
<TABLE border="1" class="borderTable">
<TBODY>
<TR class="Expanding">
<TD title="An estimate of gravitational losses during the vertical phase of a flight
which is used to determine the total gravitational losses."><div class="mobilelayout_l1">Gravity Losses at specific altitude</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="Gravity_losses_at_specific_altitude"></LABEL><span> m/s</span></h8></div></TD></TR>
<TR>
<TD title="A measure of the loss in the net performance of a rocket
while it is thrusting in a gravitational field"><div class="mobilelayout_l1">Gravity Losses</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="Gravity_losses"></LABEL> <span>m/s</span></h8></div></TD></TR>
<TR>
<TD title="A measure of the loss in the net performance of a rocket due to the
aerodynamic forces which are applied on both the body and the fins" width="460"><div class="mobilelayout_l1">Aerodynamic Losses</div></TD>
<TD width="220"><div class="mobilelayout_r2"><h8><LABEL
id="Aerodynamic_losses"></LABEL><span> m/s</span></h8></div></TD></TR>
<TR class="Expanding">
<TD title="Total losses including gravity, aerodynamic and control losses"><div class="mobilelayout_l1">Summary Losses</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="Summary_losses"></LABEL> <span>m/s</span></h8></div></TD></TR>
<TR>
<TD title="The percentage ratio of total losses to the delta velocity for Low Earth Orbit."><div class="mobilelayout_l1">Assumed Losses</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="Assumed_losses"></LABEL> <span>% </span></h8></div></TD></TR>
<TR>
<TD title="Delta-v needed to achieve a required calculated according to the Hohmann Transfer
formula plus losses calculated according to the Y. Lobanovsky approximation method. 
This speed would have a rocket in the absence of external forces. However, the actual
speed due to losses will be significantly lower."><div class="mobilelayout_l1">Required delta-v with Losses</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL
id="Vsp_with_losses"></LABEL> <span>m/s</span></h8></div></TD></TR></TBODY></TABLE></TD></TR>
<TR>
<TD><div class="spacetitle topspace padd2"><FONT size="5" title="The main characteristics of the Rocket">Output<BR></FONT></div>
<TABLE border="1" class="borderTable">
<TBODY>
<TR class="Expanding">
<TD title="The integral specific impulse of the engines of the first stage. 
This way back pressure losses are taken into account."><div class="mobilelayout_l1">1st stage average trajectory Isp</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="First_stage_average_trajectory_isp"></LABEL> <span>s </span></h9></div></TD></TR>
<TR>
<TD class="tdpadd1" title="The increment of the rocket velocity due to the thrust of the first stage engines
in the ideal case (the absence of external forces) calculated by the Tsiolkovsky formula." width="460"><div class="mobilelayout_l1">1st stage delta-v</div></TD>
<TD width="220"><div class="mobilelayout_r2"><h8><LABEL id="First_stage_delta_v"></LABEL> <span>m/s</span></h9></div></TD></TR>
<TR class="Expanding">
<TD class="tdpadd1" title="The total mass of the rocket at the shutdown of the first stage engines."><div class="mobilelayout_l1">1st stage final mass</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="First_stage_final_mass"></LABEL><span> kg </span></h9></div></TD></TR>
<TR class="Expanding">
<TD title="The total mass of the oxidizer and fuel of the first stage"><div class="mobilelayout_l1">1st stage propellant mass</div></TD>
<TD><div class="mobilelayout_r1 layout_wt_content"><INPUT type="text" id="First_stage_propellant_mass"> <span>kg</span></div></TD></TR>
<TR class="Expanding">
<TD title="The mass of the vehicle first stage plus contents."><div class="mobilelayout_l1">1st stage dry mass</div></TD>
<TD><div class="mobilelayout_r1 layout_wt_content"><INPUT type="text" id="First_stage_dry_mass"><span> kg</span></div></TD></TR>
<TR class="Expanding">
<TD title="The total thrust of the first stage engines."><div class="mobilelayout_l1">1st stage total thrust</div></TD>
<TD><div class="mobilelayout_r1 layout_wt_content"><INPUT type="text" id="First_stage_total_thrust"><span> kgf</span></div></TD></TR>
<TR class="Expanding">
<TD title="Approximate engines run time
This is usually less than the real time
because it does not take into account
the real thrust profile."><div class="mobilelayout_l1">1st stage engines run time</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="First_stage_run_time"></LABEL> <span>s </span></h9></div></TD></TR>
<TR class="Expanding">
<TD title="Fist stage Maximum Acceleration"><div class="mobilelayout_l1">1st stage Maximum Acceleration</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="First_stage_max_acc"></LABEL> <span>g </span></h9></div></TD></TR>
<TR>
<TD class="tdpadd1" title="The increment of the rocket velocity due to the thrust of the second stage engines
in the ideal case (the absence of external forces) calculated by the Tsiolkovsky formula."><div class="mobilelayout_l1">2nd stage delta-v <LABEL id="Required"></LABEL></div> </TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="Second_stage_delta_v"></LABEL> <span>m/s</span></h9></div></TD></TR>
<TR class="Expanding">
<TD title="The total mass of the rocket at the start of the second stage engines."><div class="mobilelayout_l1">2nd stage total (start) mass</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="Second_stage_total_Start_mass"></LABEL> <span>kg </span></h9></div></TD></TR>
<TR class="Expanding">
<TD><div class="mobilelayout_l1">2nd stage total mass before fairing jettison</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="Second_stage_total_mass_before_fairing_jettison"></LABEL> <span>kg </span></h9></div></TD></TR>
<TR class="ExpandingB">
<TD><div class="mobilelayout_l1">2nd stage total mass before battery jettison</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="Second_stage_total_mass_before_battery_jettison"></LABEL> <span>kg </span></h9></div></TD></TR>
<TR class="ExpandingB">
<TD><div class="mobilelayout_l1">2nd stage delta-v before batt. jettison</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="Second_stage_delta_v_before_battery_jettison"></LABEL> <span>m/s</span></h9></div></TD></TR>
<TR class="Expanding">
<TD class="tdpadd1" title="The total mass of the rocket at the shutdown of the second stage engines."><div class="mobilelayout_l1">2nd stage final mass</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="Second_stage_final_mass"></LABEL> <span>kg </span></h9></div></TD></TR>
<TR class="Expanding">
<TD title="The total mass of the oxidizer and fuel of the second stage"><div class="mobilelayout_l1">2nd stage propellant mass</div></TD>
<TD><div class="mobilelayout_r1 layout_wt_content"><INPUT type="text" id="Second_stage_propellant_mass"><span>kg </span></div></TD></TR>
<TR class="Expanding">
<TD title="The mass of the second stage plus contents."><div class="mobilelayout_l1">2nd stage dry mass</div></TD>
<TD><div class="mobilelayout_r1 layout_wt_content"><INPUT type="text" id="Second_stage_dry_mass"> <span>kg </span></div></TD></TR>
<TR class="Expanding">
<TD title="The total thrust of the second stage engines."><div class="mobilelayout_l1">2nd stage total thrust</div></TD>
<TD><div class="mobilelayout_r1 layout_wt_content"><INPUT type="text" id="Second_stage_total_thrust"><span>kgf </span></div></TD></TR>
<TR class="Expanding">
<TD title="Approximate engine run time"><div class="mobilelayout_l1">2nd stage engine run time</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="Second_stage_run_time"></LABEL> <span>s </span></h9></div></TD></TR>
<TR class="Expanding">
<TD title="Second stage Maximum Acceleration"><div class="mobilelayout_l1">2nd stage Maximum Acceleration</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="Second_stage_max_acc"></LABEL> <span>g </span></h9></div></TD></TR>
<TR class="f3stages">
<TD class="tdpadd1" title="The increment of the rocket velocity due to the thrust of the third stage engines
in the ideal case (the absence of external forces) calculated by the Tsiolkovsky formula."><div class="mobilelayout_l1">Transfer Orbit stage delta-v (required)</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="Transfer_Orbit_stage_delta_v_required"></LABEL><span> m/s</span></h9></div></TD></TR>
<TR class="Expanding3">
<TD class="tdpadd1" title="The total mass of the rocket at the start of the third stage engines."><div class="mobilelayout_l1">Transfer Orbit stage total (start) mass</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL
id="Transfer_Orbit_stage_total_Start_mass"></LABEL> <span>kg </span></h9></div></TD></TR>
<TR class="Expanding3">
<TD class="tdpadd1" title="The total mass of the rocket at the shutdown of the third stage engines."><div class="mobilelayout_l1">Transfer Orbit stage final mass</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL
id="Transfer_Orbit_stage_final_mass"></LABEL> <span>kg </span></h9></div></TD></TR>
<TR class="Expanding3">
<TD title="The total mass of the oxidizer and fuel of the third stage"><div class="mobilelayout_l1">Transfer Orbit stage propellant mass</div></TD>
<TD><div class="mobilelayout_r1 layout_wt_content"><INPUT type="text" id="Transfer_Orbit_stage_propellant_mass"><span>kg </span></div></TD></TR>
<TR class="Expanding3">
<TD title="The mass of the third stage plus contents."><div class="mobilelayout_l1">Transfer Orbit stage dry mass</div></TD>
<TD><div class="mobilelayout_r1 layout_wt_content"><INPUT type="text" id="Transfer_Orbit_stage_dry_mass"><span> kg</span></div></TD></TR>
<TR>
<TD class="tdpadd1" title="The procedure error - it should not be equated with actual accuracy of the result."><div class="mobilelayout_l1">Calculation Error</div></TD>
<TD><div class="mobilelayout_r2"><h8><LABEL id="Calculation_Error"></LABEL><span> m/s</span></h9></div></TD></TR>
</TBODY></TABLE>
</TD>
</TR></TBODY></TABLE></TD>
</TR>
</TBODY>
</TABLE>
</div>
</div>
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</div>
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<SCRIPT>
var elStartingPoint = document.querySelector('#StartingPoint');
var elReusable = document.querySelector('#Reusable');
var elAir_Launch = document.querySelector('#Air_Launch');
var elStarting_point_Altitude = document.querySelector('#Starting_point_Altitude');
var elAdditional_Speed = document.querySelector('#Additional_Speed');
var elOrbit_Perigee = document.querySelector('#Orbit_Perigee');
var elOrbit_Apogee = document.querySelector('#Orbit_Apogee');
var elSpaceport_latitude = document.querySelector('#Spaceport_latitude');
var elOrbit_Inclination = document.querySelector('#Orbit_Inclination');
var elIntermediate_angle = document.querySelector('#Intermediate_angle');
var elLaunch_azimuth = document.querySelector('#Launch_azimuth');
var elLaunch_point_speed = document.querySelector('#Launch_point_speed');
var elStarting_point_Altitude_orbital_velocity = document.querySelector('#Starting_point_Altitude_orbital_velocity');
var elAbsolute_orbital_velocity = document.querySelector('#Absolute_orbital_velocity');
var elOrbital_period = document.querySelector('#Orbital_period');
var elApogee_velocity = document.querySelector('#Apogee_velocity');
var elPerigee_velocity = document.querySelector('#Perigee_velocity');
var elVsp_for_inclination_change = document.querySelector('#Vsp_for_inclination_change');
var elOrbital_velocity = document.querySelector('#Orbital_velocity');
var elOrbital_velocity_increment_due_to_the_Earth_rotation = document.querySelector('#Orbital_velocity_increment_due_to_the_Earth_rotation');
var elVsp_for_circular_orbit = document.querySelector('#Vsp_for_circular_orbit');
var elInjection_velocity = document.querySelector('#Injection_velocity');
var elVsp_for_target_orbit = document.querySelector('#Vsp_for_target_orbit');
var elVsp_for_LEO = document.querySelector('#Vsp_for_LEO');
var elOrbit = document.querySelector('#Orbit');
//=== ROCKET ===
var elRocket = document.querySelector('#Rocket');
var elAbs_Calculation = document.querySelector('#Abs_Calculation');
var elRocketDescription = document.querySelector('#RocketDescription');
var elOrbitDescription = document.querySelector('#OrbitDescription');
var elThrust_to_weight_ratio = document.querySelector('#Thrust_to_weight_ratio');
var elThrust_to_weight_ratio_2nd = document.querySelector('#Thrust_to_weight_ratio_2nd');
var elRocket_Mass = document.querySelector('#Rocket_Mass');
var elLift_off_Mass = document.querySelector('#Lift_off_Mass');
var elMax_midsection_D = document.querySelector('#Max_midsection_D');
var elFairing_mass = document.querySelector('#Fairing_mass');
var elFairing_jettison_velocity = document.querySelector('#Fairing_jettison_velocity');
var elFairing_jettison_delta_v = document.querySelector('#Fairing_jettison_delta_v');
var elJettisoned_battery_mass = document.querySelector('#Jettisoned_battery_mass');
var elAssumed_payload_mass = document.querySelector('#Assumed_payload_mass');
var elPayload_to_Lift_off_mass_ratio = document.querySelector('#Payload_to_Lift_off_mass_ratio');
var el2nd_Stage_mass_ratio = document.querySelector('#_2nd_Stage_mass_ratio');
var el3rd_Stage_mass_ratio = document.querySelector('#_3rd_Stage_mass_ratio');
var el1st_Dry_to_Wet_mass_ratio_Range = document.querySelector('#_1st_Dry_to_Wet_mass_ratio_Range');
var el1st_Dry_to_Wet_mass_ratio = document.querySelector('#_1st_Dry_to_Wet_mass_ratio');
var el2nd_Dry_to_Wet_mass_ratio_Range = document.querySelector('#_2nd_Dry_to_Wet_mass_ratio_Range');
var el2nd_Dry_to_Wet_mass_ratio = document.querySelector('#_2nd_Dry_to_Wet_mass_ratio');
var el3rd_Dry_to_Wet_mass_ratio_Range = document.querySelector('#_3rd_Dry_to_Wet_mass_ratio_Range');
var el3rd_Dry_to_Wet_mass_ratio = document.querySelector('#_3rd_Dry_to_Wet_mass_ratio');
var elUnused_propellant_of_1st_Stage_Range = document.querySelector('#Unused_propellant_of_1st_Stage_Range');
var elUnused_propellant_of_1st_Stage = document.querySelector('#Unused_propellant_of_1st_Stage');
var elUnused_propellant_of_2nd_Stage_Range = document.querySelector('#Unused_propellant_of_2nd_Stage_Range');
var elUnused_propellant_of_2nd_Stage = document.querySelector('#Unused_propellant_of_2nd_Stage');
var elUnused_propellant_of_Transfer_Orbit_Stage_Range = document.querySelector('#Unused_propellant_of_Transfer_Orbit_Stage_Range');
var elUnused_propellant_of_Transfer_Orbit_Stage = document.querySelector('#Unused_propellant_of_Transfer_Orbit_Stage');
var elFirst_stage_engine_thrust = document.querySelector('#First_stage_engine_thrust');
var elFirst_stage_engines_number = document.querySelector('#First_stage_engines_number');
var elFirst_stage_isp_sea_level_Range = document.querySelector('#First_stage_isp_sea_level_Range');
var elFirst_stage_isp_sea_level = document.querySelector('#First_stage_isp_sea_level');
var elFirst_stage_isp_vac_Range = document.querySelector('#First_stage_isp_vac_Range');
var elFirst_stage_isp_vac = document.querySelector('#First_stage_isp_vac');
var elSecond_stage_engine_thrust = document.querySelector('#Second_stage_engine_thrust');
var elSecond_stage_engines_number = document.querySelector('#Second_stage_engines_number');
var elSecond_stage_isp_vac_Range= document.querySelector('#Second_stage_isp_vac_Range');
var elSecond_stage_isp_vac = document.querySelector('#Second_stage_isp_vac');
var elTransfer_Orbit_Stage_isp_Range = document.querySelector('#Transfer_Orbit_Stage_isp_Range');
var elTransfer_Orbit_Stage_isp = document.querySelector('#Transfer_Orbit_Stage_isp');
var elSpecific_Impulse_Variation_Range = document.querySelector('#Specific_Impulse_Variation_Range');
var elSpecific_Impulse_Variation = document.querySelector('#Specific_Impulse_Variation');
var elExtra_speed_for_flight_to_the_planets = document.querySelector('#Extra_speed_for_flight_to_the_planets');
var elEngine1 = document.querySelector('#Engine1');
var elEngine2 = document.querySelector('#Engine2');
var elCycle = document.querySelector('#Cycle');
var elCycle2 = document.querySelector('#Cycle2');
var elCycle3 = document.querySelector('#Cycle3');
var elFuel = document.querySelector('#Fuel');
var elFuel2 = document.querySelector('#Fuel2');
var elFuel3 = document.querySelector('#Fuel3');
var elStages = document.querySelector('#Stages');
//=== Losses ===
var elGravity_losses_at_specific_altitude = document.querySelector('#Gravity_losses_at_specific_altitude');
var elGravity_losses = document.querySelector('#Gravity_losses');
var elAerodynamic_losses = document.querySelector('#Aerodynamic_losses');
var elSummary_losses = document.querySelector('#Summary_losses');
var elAssumed_losses = document.querySelector('#Assumed_losses');
var elVsp_with_losses = document.querySelector('#Vsp_with_losses');
//=== Output ===
var elFirst_stage_average_trajectory_isp = document.querySelector('#First_stage_average_trajectory_isp');
var elFirst_stage_delta_v = document.querySelector('#First_stage_delta_v');
var elFirst_stage_final_mass = document.querySelector('#First_stage_final_mass');
var elFirst_stage_propellant_mass = document.querySelector('#First_stage_propellant_mass');
var elFirst_stage_dry_mass = document.querySelector('#First_stage_dry_mass');
var elFirst_stage_total_thrust = document.querySelector('#First_stage_total_thrust');
var elFirst_stage_run_time = document.querySelector('#First_stage_run_time');
var elFirst_stage_max_acc = document.querySelector('#First_stage_max_acc');
var elSecond_stage_delta_v = document.querySelector('#Second_stage_delta_v');
var elSecond_stage_total_Start_mass = document.querySelector('#Second_stage_total_Start_mass');
var elSecond_stage_total_mass_before_fairing_jettison = document.querySelector('#Second_stage_total_mass_before_fairing_jettison');
var elSecond_stage_total_mass_before_battery_jettison = document.querySelector('#Second_stage_total_mass_before_battery_jettison');
var elSecond_stage_delta_v_before_battery_jettison = document.querySelector('#Second_stage_delta_v_before_battery_jettison');
var elSecond_stage_final_mass = document.querySelector('#Second_stage_final_mass');
var elSecond_stage_propellant_mass = document.querySelector('#Second_stage_propellant_mass');
var elSecond_stage_dry_mass = document.querySelector('#Second_stage_dry_mass');
var elSecond_stage_total_thrust = document.querySelector('#Second_stage_total_thrust');
var elSecond_stage_run_time = document.querySelector('#Second_stage_run_time');
var elSecond_stage_max_acc = document.querySelector('#Second_stage_max_acc');
var elTransfer_Orbit_stage_delta_v_required = document.querySelector('#Transfer_Orbit_stage_delta_v_required');
var elTransfer_Orbit_stage_total_Start_mass = document.querySelector('#Transfer_Orbit_stage_total_Start_mass');
var elTransfer_Orbit_stage_final_mass = document.querySelector('#Transfer_Orbit_stage_final_mass');
var elTransfer_Orbit_stage_propellant_mass = document.querySelector('#Transfer_Orbit_stage_propellant_mass');
var elTransfer_Orbit_stage_dry_mass = document.querySelector('#Transfer_Orbit_stage_dry_mass');
var elCalculation_Error = document.querySelector('#Calculation_Error');
var elPayload_mass_calculated = document.querySelector('#Payload_mass_calculated');
var elAggressivity = document.querySelector('#Aggressivity');
var elPayload_change = document.querySelector('#Payload_change');
var elExpand = document.querySelector('#Expand');
var elsExpanding = document.querySelectorAll('.content tr[class="Expanding"]');
var elsExpandingB = document.querySelectorAll('.content tr[class="ExpandingB"]');
var elsExpanding3 = document.querySelectorAll('.content tr[class="Expanding3"]');
var els3stages = document.querySelectorAll('.content tr[class="f3stages"]');
var elsElectric = document.querySelectorAll('.content tr[class="Electric"]');
var elsGEO = document.querySelectorAll('.content tr[class="fGEO"]');
var elsGEOI = document.querySelectorAll('.content tr[class="fGEOI"]');
var elLimitation = document.querySelector('#Limitation');
var elSet_averages = document.querySelector('#Set_averages');
var elSet_AllMin = document.querySelector('#Set_AllMin');
var elSet_AllMax = document.querySelector('#Set_AllMax');
var elProjecting = document.querySelectorAll('.content tr[class="Projecting"]');
var elProjectingH = document.querySelectorAll('.content tr[class="ProjectingH"]');
var elNegativePayload = document.querySelectorAll('.content tr[class="NegativePayload"]');
var elReference = document.querySelector('#Reference');
var elRequired = document.querySelector('#Required');
// Abs_Calculation.checked = false;
// var Irremovable_Gravity_Losses;
var Vsp_for_target_orbit;
var Payload_mass;
var AirLaunch_Thrust_gain = 1.;
var Aggressivity = 0.;
var Specific_Impulse_Variation_old = 100.;
var Reus_corr = 0;
window.onload = onPageLoad;
window.onunload = onPageUnload;
var s_start_point_count = 18;
var s_start_point_data = [["Cape Canaveral", 28.5, -80.33, 0.1, 28.5, "USA East Coast"],
["Vandenberg", 34.72, -120.62,0.11, 34.72,"USA West Coast (basically polar orbit)"],
["Wallops", 37.94, -75.47, 0, 37.94,"Wallops Island USA"],
["Kodiak", 57.43, -152.33, 0, 57.43,"Kodiak Island Alaska"],
["Mojave", 35.0, -118, 0, 35., "California USA"],
["Rocket Lab LC-1", -39.26, 177.86, 0.1, 39.25,"New Zealand's Mahia Peninsula"],
["Omelek Island", 9.3, 167.73, 0, 9.3, "Republic of the Marshall Islands"],
["Puerto Rico", 18.26, 65.61, 0, 18.26,"USA (access to all orbital inclinations)"],
["BO Corn Ranch", 31.42,-104.76, 1.23, 31.42,"Blue Origin spaceport USA"],
["SpaceX Boca Chica", 26., -97.15, 0.1, 26.0,"SpaceX South Texas Launch Site"],
["Baikonur", 45.96, 63.30, 0.1, 51.6,"Kazakhstan (former USSR)"],
["Sea Launch (Equator)", 0., -154.0, 0.02, 0.0,"Best way to reach geosynchronous orbit"],
["Kuru (ESA)", 5.23, -52.77, 0.1, 5.23,"French Guiana"],
["Jiuquan (China)", 41.95, 100.28, 1., 40.95,"China"],
["Shriharikota (India)",13.79, 80.25, 0.1, 44., "India"],
["Alcantara (Brazil)", -2.28, -44.38, .05, 2.28,"Brazil"],
["Tanegashima (Japan)", 30.4, 131.7, 0.1, 30.4, "Japan"],
["Stornoway (UK)", 58.2, 6.3, 0, 58.2, "Isle of Lewis, Scotland"]];
var s_orbit_count = 9;
var s_orbit_data = [["LEO", 200, 0,-1, 0,"Low Earth orbit"],
["ISS", 409, 418,51.6,0,"International Space Station orbit"],
["SSO", 500, 0, 98, 0,"Sun-synchronous orbit"],
["MEO", 20200, 0, 55, 0,"Medium Earth orbit (GPS satellites)"],
["GTO", 200, 35786, -1, 0,"Geosynchronous transfer orbit"],