Difference between revisions of "Nuclear thermal propulsion"
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Nuclear thermal propulsion uses a nuclear core to heat a propellant and provide propulsion to a space vehicle. | Nuclear thermal propulsion uses a nuclear core to heat a propellant and provide propulsion to a space vehicle. | ||
− | + | Liquid hydrogen is usually used as the propellant as it has a higher velocity for the same input power, and therefore produces a faster final velocity according to the [[Propulsion|rocket equation]]. | |
− | |||
− | == | + | __NOTOC__ |
+ | ==History of nuclear thermal propulsion== | ||
− | + | ===American=== | |
− | + | Nerva<ref>Nerva on Wikipedia: https://en.wikipedia.org/wiki/NERVA</ref> | |
− | + | {| class="wikitable" | |
− | + | !Propellant | |
+ | |Liquid hydrogen | ||
+ | |- | ||
+ | ! colspan="2" |Performance | ||
+ | |- | ||
+ | !Thrust (vac.) | ||
+ | |246,663 N (55,452 lb<sub>f</sub>) | ||
+ | |- | ||
+ | !Chamber pressure | ||
+ | |3,861 kPa (560.0 psi) | ||
+ | |- | ||
+ | !''I''<sub>sp</sub> (vac.) | ||
+ | |841 seconds (8.25 km/s) | ||
+ | |- | ||
+ | !''I''<sub>sp</sub> (SL) | ||
+ | |710 seconds (7.0 km/s) | ||
+ | |- | ||
+ | !Burn time | ||
+ | |1,680 seconds | ||
+ | |- | ||
+ | !Thrust to weigh ratio | ||
+ | !1.36 | ||
+ | |- | ||
+ | !Restarts | ||
+ | |24 | ||
+ | |- | ||
+ | ! colspan="2" |Dimensions | ||
+ | |- | ||
+ | !Length | ||
+ | |6.9 meters (23 ft) | ||
+ | |- | ||
+ | !Diameter | ||
+ | |2.59 meters (8 ft 6 in) | ||
+ | |- | ||
+ | !Dry weight | ||
+ | |18,144 kilograms (40,001 lb) | ||
+ | |} | ||
− | + | * | |
− | * Cost | + | * |
− | * Cost of development | + | |
− | * Risk of accident | + | ===Russian=== |
+ | |||
+ | ==Analysis of use== | ||
+ | |||
+ | ===Advantages=== | ||
+ | |||
+ | *Higher ISP than chemical | ||
+ | *Higher power energy source | ||
+ | *Shorter travel time | ||
+ | *Oberth effect | ||
+ | *Self cooling | ||
+ | |||
+ | ===Disadvantages=== | ||
+ | |||
+ | *Cost | ||
+ | *Cost of development | ||
+ | *Risk of accident | ||
+ | *Lower ISP than electric | ||
+ | *Low public trust | ||
+ | *Thrust to weight ratio close to 1 (cannot take off from Earth with a significant payload) | ||
+ | |||
+ | ===Types=== | ||
+ | |||
+ | *Solid core | ||
+ | *Gas core | ||
+ | *Nuclear light bulb, open and closed | ||
+ | |||
+ | ==References== | ||
+ | <references /> |
Revision as of 10:38, 9 August 2019
Nuclear thermal propulsion uses a nuclear core to heat a propellant and provide propulsion to a space vehicle.
Liquid hydrogen is usually used as the propellant as it has a higher velocity for the same input power, and therefore produces a faster final velocity according to the rocket equation.
History of nuclear thermal propulsion
American
Nerva[1]
Propellant | Liquid hydrogen |
---|---|
Performance | |
Thrust (vac.) | 246,663 N (55,452 lbf) |
Chamber pressure | 3,861 kPa (560.0 psi) |
Isp (vac.) | 841 seconds (8.25 km/s) |
Isp (SL) | 710 seconds (7.0 km/s) |
Burn time | 1,680 seconds |
Thrust to weigh ratio | 1.36 |
Restarts | 24 |
Dimensions | |
Length | 6.9 meters (23 ft) |
Diameter | 2.59 meters (8 ft 6 in) |
Dry weight | 18,144 kilograms (40,001 lb) |
Russian
Analysis of use
Advantages
- Higher ISP than chemical
- Higher power energy source
- Shorter travel time
- Oberth effect
- Self cooling
Disadvantages
- Cost
- Cost of development
- Risk of accident
- Lower ISP than electric
- Low public trust
- Thrust to weight ratio close to 1 (cannot take off from Earth with a significant payload)
Types
- Solid core
- Gas core
- Nuclear light bulb, open and closed
References
- ↑ Nerva on Wikipedia: https://en.wikipedia.org/wiki/NERVA