Difference between revisions of "Rocket Engines"
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[[Category:Rocketry]] | [[Category:Rocketry]] | ||
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+ | Rocket Engines give you their max output in kN with this you can calculate what they can reasonably carry into orbit depending on the planet or moon you are on. Force = Mass * Acceleration. Acceleration is equal to the planet's gravity, Mass is given in kg per part of the rocket, and Force is kN. If your thrust force listed below is less than the weight of the rocket in kN then you will not even take off. It is better to have a thrust much higher than the weight of the rocket or else you risk running out of fuel on launch and on landing. | ||
+ | |||
+ | Liquid propellants bring greater efficiencies. Using Nitrous Oxide as oxidizer provides excessive thrust values. Keep in mind that N2O fuel mix is 1.9375 times heavier while thrust boost is around 1.5-1.7. Engine efficiency determines "bonus" thrust multiplier, meaning engine with higher efficiency will give more thrust consuming same amount of fuel. Thus using liquid engines is more favorable if one can cool fuel down, moreover Pressure Fed Engines consume fuel inversely proportional to its temperature. On the other hand if [[Volatiles]] and [[Oxygen]] are in excess (e.g. farm on [[Vulcan]]) is may be much easier to opt for Pressure Fed Gas Engine. It will provide ~40kN at 20°C. | ||
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<div style="width:auto; overflow:auto;"> | <div style="width:auto; overflow:auto;"> | ||
{| class="wikitable sortable" style="width:100%;" | {| class="wikitable sortable" style="width:100%;" | ||
− | ! Name | + | ! rowspan=2 | Name |
− | ! Base Power Usage | + | ! rowspan=2 | Base Power Usage |
− | ! Rocket Mass Contribution | + | ! rowspan=2 | Rocket Mass Contribution |
− | ! Max Thrust | + | ! rowspan=2 | Max Thrust |
− | ! Efficiency | + | ! colspan=2 | Real Max Thrust |
− | ! Exhaust Velocity | + | ! rowspan=2 | Efficiency |
+ | ! rowspan=2 | Exhaust Velocity | ||
|- | |- | ||
− | ! | + | ! Using O2 |
− | + | ! Using N2O | |
− | |||
− | |||
− | |||
− | |||
|- | |- | ||
− | ! <b>[[ | + | ! <b>[[Pressure Fed Gas Engine]]</b> |
| 10W | | 10W | ||
| 500kg | | 500kg | ||
| 40,3kN | | 40,3kN | ||
+ | | 61,0kN | ||
+ | | 41,9kN<ref>N2O must be much hotter to avoid condensing therefore decreasing pumping rate</ref> | ||
| 96% | | 96% | ||
| 3,86km/s (Isp: 394s) | | 3,86km/s (Isp: 394s) | ||
|- | |- | ||
− | ! <b>[[ | + | ! <b>[[Pumped Gas Engine]]</b> |
| 200W | | 200W | ||
| 500kg | | 500kg | ||
| 16,2kN | | 16,2kN | ||
+ | | 16,5kN | ||
+ | | 24,5kN | ||
| 100% | | 100% | ||
| 4,02km/s (Isp: 411s) | | 4,02km/s (Isp: 411s) | ||
|- | |- | ||
− | ! <b>[[ | + | ! <b>[[Pumped Liquid Engine]]</b> |
| 200W | | 200W | ||
| 500kg | | 500kg | ||
| 17,6kN | | 17,6kN | ||
+ | | 18,7kN | ||
+ | | 31,3kN | ||
| 140% | | 140% | ||
| 5,47km/s (Isp: 559s) | | 5,47km/s (Isp: 559s) | ||
|- | |- | ||
− | ! colspan= | + | ! <b>[[Pressure Fed Liquid Engine]]</b> |
+ | | 20W | ||
+ | | 500kg | ||
+ | | 29,2kN | ||
+ | | 43,4kN - 38,1kN | ||
+ | | 74,5kN - 61,3kN | ||
+ | | 160% | ||
+ | | 6,18km/s (Isp: 631s) | ||
+ | |- | ||
+ | |||
+ | ! colspan=8 | <i>Update 0.2.4726.21691 - 18/01/2024</i> <span class="right">[[Rocket_Engines]]</span> | ||
|} | |} | ||
</div> | </div> |
Latest revision as of 10:22, 26 August 2024
Rocket Engines give you their max output in kN with this you can calculate what they can reasonably carry into orbit depending on the planet or moon you are on. Force = Mass * Acceleration. Acceleration is equal to the planet's gravity, Mass is given in kg per part of the rocket, and Force is kN. If your thrust force listed below is less than the weight of the rocket in kN then you will not even take off. It is better to have a thrust much higher than the weight of the rocket or else you risk running out of fuel on launch and on landing.
Liquid propellants bring greater efficiencies. Using Nitrous Oxide as oxidizer provides excessive thrust values. Keep in mind that N2O fuel mix is 1.9375 times heavier while thrust boost is around 1.5-1.7. Engine efficiency determines "bonus" thrust multiplier, meaning engine with higher efficiency will give more thrust consuming same amount of fuel. Thus using liquid engines is more favorable if one can cool fuel down, moreover Pressure Fed Engines consume fuel inversely proportional to its temperature. On the other hand if Volatiles and Oxygen are in excess (e.g. farm on Vulcan) is may be much easier to opt for Pressure Fed Gas Engine. It will provide ~40kN at 20°C.
Name | Base Power Usage | Rocket Mass Contribution | Max Thrust | Real Max Thrust | Efficiency | Exhaust Velocity | |
---|---|---|---|---|---|---|---|
Using O2 | Using N2O | ||||||
Pressure Fed Gas Engine | 10W | 500kg | 40,3kN | 61,0kN | 41,9kN[1] | 96% | 3,86km/s (Isp: 394s) |
Pumped Gas Engine | 200W | 500kg | 16,2kN | 16,5kN | 24,5kN | 100% | 4,02km/s (Isp: 411s) |
Pumped Liquid Engine | 200W | 500kg | 17,6kN | 18,7kN | 31,3kN | 140% | 5,47km/s (Isp: 559s) |
Pressure Fed Liquid Engine | 20W | 500kg | 29,2kN | 43,4kN - 38,1kN | 74,5kN - 61,3kN | 160% | 6,18km/s (Isp: 631s) |
Update 0.2.4726.21691 - 18/01/2024 Rocket_Engines |
- ↑ N2O must be much hotter to avoid condensing therefore decreasing pumping rate