Raketni motor na tekoče gorivo: Razlika med redakcijama
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Vrstica 1:
[[File:LiquidFuelRocketSchematic.jpg|thumb|400px|Shematika rakete na tekoče gorivo]]
'''Raketni motor na tekoče gorivo''' je vrsta raketnega motorja, ki uporablja goriva v tekočem agregatnem stanju. Tekoča goriva imajo po navadi visoko gostoto (izjema [[tekoči vodik]]), zato so tanki sorazmerno majhni. Gorivu se pred vstopom v zgorevalno komoro po navadi poveča pritisk s pomočjo [[turbočrpalka|turbočrpalk]]. To omogoča, da se lahko gorivo in oksidator hrani pri manjšem tlaku in niso potrebno visokotlačni rezervoarji. Nekatera goriva, kot npr. vodik in kisik, ki so pri sobni temperaturi plini, se stisne in ohladi na kriogenično temperaturo, pri kateri postanejo tekoča in se zato smatrajo kot tekoča goriva.
{| class="wikitable" style="text-align:center;"
|+ '''Specifications'''
!
![[:en:RL-10|RL-10]]
![[:en:HM7B|HM7B]]
![[:en:Vinci (rocket engine)|Vinci]]
![[:en:KVD-1|KVD-1]]
![[:en:CE-7.5|CE-7.5]]
![[:en:CE-20|CE-20]]
![[:en:YF-75|YF-75]]
![[:en:YF-75D|YF-75D]]
![[:en:RD-0146|RD-0146]]
!ES-702
!ES-1001
![[:en:LE-5|LE-5]]
![[:en:LE-5#LE-5A|LE-5A]]
![[:en:LE-5#LE-5B|LE-5B]]
|-
!Country of origin
|{{USA}}
|{{FRA}}
|{{FRA}}
|{{USSR}}
|{{IND}}
|{{IND}}
|{{CHN}}
|{{CHN}}
|{{RUS}}
|{{JPN}}
|{{JPN}}
|{{JPN}}
|{{JPN}}
|{{JPN}}
|-
!Cycle
|[[:en:Expander cycle|Expander]]
|[[:en:Gas-generator cycle|Gas-generator]]
|[[:en:Expander cycle|Expander]]
|[[:en:Staged combustion cycle|Staged combustion]]
|[[:en:Staged combustion cycle|Staged combustion]]
|[[:en:Gas-generator cycle|Gas-generator]]
|[[:en:Gas-generator cycle|Gas-generator]]
|[[:en:Expander cycle|Expander]]
|[[:en:Expander cycle|Expander]]
|[[:en:Gas-generator cycle|Gas-generator]]
|[[:en:Gas-generator cycle|Gas-generator]]
|[[:en:Gas-generator cycle|Gas-generator]]
|[[:en:Expander cycle#Expander bleed cycle (open cycle)|Expander bleed cycle]]<br />（Nozzle Expander）
|[[:en:Expander cycle#Expander bleed cycle (open cycle)|Expander bleed cycle]]<br />（Chamber Expander）
|-
!Thrust (vac.)
|66.7 kN (15,000 lbf)
|62.7 kN
|180 kN
|69.6 kN
|73 kN
|200 kN
|78.45 kN
|88.26 kN
|98.1 kN (22,054 lbf)
|68.6kN (7.0 tf)<ref>without nozzle 48.52kN (4.9 tf)</ref>
|98kN (10.0 tf)<ref>without nozzle 66.64kN (6.8 tf)</ref>
|102.9kN (10.5 tf)
|r121.5kN (12.4 tf)
|137.2kN (14 tf)
|-
!Mixture ratio
|
|
|
|
|
|
|5.2
|6.0
|
|5.2
|6.0
|5.5
|5
|5
|-
!Nozzle ratio
|40
|
|
|
|
|100
|80
|80
|
|40
|40
|140
|130
|110
|-
![[:en:Specific impulse|I<sub>sp</sub>]] (vac.)
|433
|444.2
|465
|462
|454
|443
|438
|442
|463
|425<ref>without nozzle 286.8</ref>
|425<ref>without nozzle 291.6</ref>
|450
|452
|447
|-
!Chamber pressure :MPa
|2.35
|3.5
|6.1
|5.6
|5.8
|6.0
|3.68
|
|7.74
|2.45
|3.51
|3.65
|3.98
|3.58
|-
!LH<sub>2</sub> TP rpm
|
|
|
|
|
|
|
|
|125,000
|41,000
|46,310
|50,000
|51,000
|52,000
|-
!LOX TP rpm
|
|
|
|
|
|
|
|
|
|16,680
|21,080
|16,000
|17,000
|18,000
|-
!Length m
|1.73
|1.8
|2.2~4.2
|2.14
|2.14
|
|2.8
|
|2.2
|
|
|2.68
|2.69
|2.79
|-
!Dry weight kg
|135
|165
|280
|282
|435
|558
|550
|
|242
|255.8
|259.4
|255
|248
|285
|}
{{Raketni motorji}}
[[Kategorija:Raketni motorji]]
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