Nuclear thermal propulsion - Revision history

RichardWSmith: spelling.

2024-12-05T13:42:24Z

spelling.

Michel Lamontagne: /* Disadvantages */

2024-11-05T15:51:29Z

Disadvantages

Michel Lamontagne: /* Disadvantages */

2024-11-05T15:50:56Z

Disadvantages

Michel Lamontagne at 15:49, 5 November 2024

2024-11-05T15:49:34Z

Michel Lamontagne: /* Types */

2024-11-05T15:48:33Z

Types

RichardWSmith: removed redundant reference (listed again below.)

2023-01-24T11:36:09Z

removed redundant reference (listed again below.)

RichardWSmith: Added Wave Rotor to list.

2023-01-24T11:35:19Z

Added Wave Rotor to list.

RichardWSmith at 11:32, 24 January 2023

2023-01-24T11:32:36Z

RichardWSmith: Added 'Propulsion' category to this page.

2023-01-24T11:29:46Z

Added 'Propulsion' category to this page.

RichardWSmith: Removed redundant sentence, and pointed out that Wave Rotor NTP is still theoretical.

2023-01-24T11:28:54Z

Removed redundant sentence, and pointed out that Wave Rotor NTP is still theoretical.

@@ Line 8: / Line 8: @@
 In the late 1960's NASA explored nuclear propulsion with the NERVA program.  It was expected that such nuclear rockets could achieve efficiencies of 900 seconds ISP.  (This is twice the efficiency of chemical rockets where efficiently engineered hydrogen-oxygen engines are around 450 seconds ISP.)
-However, a little know technology, the wave rotor, can be used to further compress the hot gas from a nuclear rocket before it enters the rocket nozzle.  This can boost the ISP to 1,400 to 2,000 seconds.  If such a rocket with an ISP or 1,800 seconds could be created, missions to Mars would need 1/2 the reaction mass of a NERVA rocket, or 1/4 the reaction mass of a chemical rocket.  This would allow much more payload to be sent to Mars, and increase the safety, and efficiency of such missions.<ref>https://www.egr.msu.edu/mueller/NMReferences/HirceagaIancuMueller_2005Timisoara_WaveRotorsTechnologyAndApplications.pdf</ref><ref>https://www.nextbigfuture.com/2023/01/nuclear-wave-rotor-propulsion-could-get-ten-times-chemical-rocket-speeds.html</ref>  Wave Rotor Nuclear Thermal Propulsion (WRNTP) is an extremely interesting technology, but as of 2023, no working motors have been demonstrated.
+However, a little known technology, the wave rotor, can be used to further compress the hot gas from a nuclear rocket before it enters the rocket nozzle.  This can boost the ISP to 1,400 to 2,000 seconds.  If such a rocket with an ISP or 1,800 seconds could be created, missions to Mars would need 1/2 the reaction mass of a NERVA rocket, or 1/4 the reaction mass of a chemical rocket.  This would allow much more payload to be sent to Mars, and increase the safety, and efficiency of such missions.<ref>https://www.egr.msu.edu/mueller/NMReferences/HirceagaIancuMueller_2005Timisoara_WaveRotorsTechnologyAndApplications.pdf</ref><ref>https://www.nextbigfuture.com/2023/01/nuclear-wave-rotor-propulsion-could-get-ten-times-chemical-rocket-speeds.html</ref>  Wave Rotor Nuclear Thermal Propulsion (WRNTP) is an extremely interesting technology, but as of 2023, no working motors have been demonstrated.
 __NOTOC__

@@ Line 77: / Line 77: @@
 *Lower ISP than electric
 *Low public trust
-*Thrust to weight ratio close to 1 (cannot take off from Earth with a significant payload).  Although MITTEE, if ever developed, should have a thrust to weight ratio of 10.
+*Thrust to weight ratio close to 1, so it cannot take off from Earth with a significant payload.  Although MITTEE, if it was ever developed, should have a thrust to weight ratio of 10.
 ===Types===

@@ Line 77: / Line 77: @@
 *Lower ISP than electric
 *Low public trust
-*Thrust to weight ratio close to 1 (cannot take off from Earth with a significant payload)
+*Thrust to weight ratio close to 1 (cannot take off from Earth with a significant payload).  Although MITTEE, if ever developed, should have a thrust to weight ratio of 10.
 ===Types===

@@ Line 8: / Line 8: @@
 In the late 1960's NASA explored nuclear propulsion with the NERVA program.  It was expected that such nuclear rockets could achieve efficiencies of 900 seconds ISP.  (This is twice the efficiency of chemical rockets where efficiently engineered hydrogen-oxygen engines are around 450 seconds ISP.)
-However, a little know technology, the wave rotor, can be used to further compress the hot gas from a nuclear rocket before it enters the rocket nozzle.  This can boost the ISP to 1,400 to 2,000 seconds.  If such a rocket with an ISP or 1,800 seconds could be created, missions to Mars would need 1/2 the reaction mass of a NERVA rocket, or 1/4 the reaction mass of a chemical rocket.  This would allow much more payload to be sent to Mars, and increase the safety, and efficiency of such missions.<ref>https://www.egr.msu.edu/mueller/NMReferences/HirceagaIancuMueller_2005Timisoara_WaveRotorsTechnologyAndApplications.pdf</ref><ref>https://www.nextbigfuture.com/2023/01/nuclear-wave-rotor-propulsion-could-get-ten-times-chemical-rocket-speeds.html</ref>
+However, a little know technology, the wave rotor, can be used to further compress the hot gas from a nuclear rocket before it enters the rocket nozzle.  This can boost the ISP to 1,400 to 2,000 seconds.  If such a rocket with an ISP or 1,800 seconds could be created, missions to Mars would need 1/2 the reaction mass of a NERVA rocket, or 1/4 the reaction mass of a chemical rocket.  This would allow much more payload to be sent to Mars, and increase the safety, and efficiency of such missions.<ref>https://www.egr.msu.edu/mueller/NMReferences/HirceagaIancuMueller_2005Timisoara_WaveRotorsTechnologyAndApplications.pdf</ref><ref>https://www.nextbigfuture.com/2023/01/nuclear-wave-rotor-propulsion-could-get-ten-times-chemical-rocket-speeds.html</ref>  Wave Rotor Nuclear Thermal Propulsion (WRNTP) is an extremely interesting technology, but as of 2023, no working motors have been demonstrated.
 __NOTOC__

@@ Line 88: / Line 88: @@
 *Wave Rotor NTP<ref>https://www.nasa.gov/directorates/spacetech/niac/2023/New_Class_of_Bimodal/</ref>
 *Nuclear salt water rockets<ref>http://www.path-2.narod.ru/design/base_e/nswr.pdf</ref>
 ==References==
 <references />

@@ Line 1: / Line 1: @@
 [[Category:Propulsion]]
-Nuclear Thermal Propulsion (NTP) uses a nuclear reactor to heat [[propellant]] directly and exhaust it through a rocket nozzle.  The nuclear reactor core is the hottest element in the engine and limits the effectiveness of the drive.  (Tho nuclear reactors could be made to run hotter, removing waste heat is a great concern to prevent the reactor from melting.  Radiating heat in space is of great concern.)
+Nuclear Thermal Propulsion (NTP) uses a nuclear reactor to heat [[propellant]] directly and exhaust it through a rocket nozzle.  The nuclear reactor core is the hottest element in the engine and limits the effectiveness of the drive.  (Tho nuclear reactors could be made to run hotter, removing waste heat is a great concern to prevent the reactor from melting.  Radiating heat in space is more difficult than on a planet since there is no mass to dump heat into via convection.)
 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]]. An animated illustration of nuclear thermal rockets can be found at <ref>https://www.youtube.com/watch?v=3aBOhC1c6m8</ref>.

← Older revision		Revision as of 11:29, 24 January 2023
Line 1:		Line 1:
		+	[[Category:Propulsion]]
	Nuclear Thermal Propulsion (NTP) uses a nuclear reactor to heat [[propellant]] directly and exhaust it through a rocket nozzle. The nuclear reactor core is the hottest element in the engine and limits the effectiveness of the drive. (Tho nuclear reactors could be made to run hotter, removing waste heat is a great concern to prevent the reactor from melting. Radiating heat in space is of great concern.)		Nuclear Thermal Propulsion (NTP) uses a nuclear reactor to heat [[propellant]] directly and exhaust it through a rocket nozzle. The nuclear reactor core is the hottest element in the engine and limits the effectiveness of the drive. (Tho nuclear reactors could be made to run hotter, removing waste heat is a great concern to prevent the reactor from melting. Radiating heat in space is of great concern.)