Nuclear fusion - Revision history

RichardWSmith: /* Advantages on Mars */ Limited sources of high quality energy on Mars.

2024-10-30T00:17:00Z

Advantages on Mars: Limited sources of high quality energy on Mars.

RichardWSmith: /* Advantages on Mars */ Mars can fuel fusion powered ships in inner solar system.

2024-10-30T00:08:48Z

Advantages on Mars: Mars can fuel fusion powered ships in inner solar system.

RichardWSmith: /* Advantages on Mars */ Added a link.

2024-10-29T23:07:42Z

Advantages on Mars: Added a link.

Michel Lamontagne at 14:04, 9 September 2024

2024-09-09T14:04:44Z

Michel Lamontagne: /* Advantages on Mars */

2024-09-04T13:50:16Z

Advantages on Mars

Michel Lamontagne at 13:47, 4 September 2024

2024-09-04T13:47:27Z

Michel Lamontagne: /* General Physical Characteristics of Fusion Propulsion Systems */

2024-09-04T13:45:59Z

General Physical Characteristics of Fusion Propulsion Systems

Michel Lamontagne: /* General Physical Characteristics of Fusion Propulsion Systems */

2024-09-04T13:34:51Z

General Physical Characteristics of Fusion Propulsion Systems

Michel Lamontagne at 13:33, 4 September 2024

2024-09-04T13:33:57Z

Michel Lamontagne at 13:33, 4 September 2024

2024-09-04T13:33:33Z

@@ Line 6: / Line 6: @@
 ==Advantages on Mars==
-*Fusion may use Deuterium, an [[Isotopes |Isotope]] of hydrogen with one proton and one neutron.  Deuterium is rare, and expensive to concentrate.  However, Deuterium on Mars is 5 times more common than on Earth, so this concentration step would be 5 times cheaper.  (In fact, deuterium is so expensive, it might be worth exporting concentrated deuterium to Earth.)  If [[Fusion Propulsion]] space craft are built, Mars may be a spot to inexpensively refuel them.  (Mars' low gravity makes getting fuel into space cheaper than on Earth.)
+*Fusion may use Deuterium, an [[Isotopes |Isotope]] of hydrogen with one proton and one neutron.  Deuterium is rare, and expensive to concentrate.  However, Deuterium on Mars is 5 times more common than on Earth, so this concentration step would be 5 times cheaper.  (In fact, deuterium is so expensive, it might be worth exporting concentrated deuterium to Earth.)
 *If fission fuel happens to be rare on mars, the relative abundance of fusion fuel might make it more favorable.  This is for the very long term, however.
-*If fusion powered ships are created, Mars will be the best place to refuel in the inner solar system.  (Deuterium is common on Mars, and Mars' low gravity makes it easy to ship Deuterium fuel off world to fusion powered craft.
+*If fusion powered ships are created, Mars will be the best place to refuel in the inner solar system.  (Deuterium is common on Mars, and Mars' low gravity makes it easy to ship Deuterium fuel off world to fusion powered craft.  There is no other place in the inner solar system where Deuterium can be supplied so cheaply.)
 *Fusion powered ship should be faster than chemical ones, making the transit to Mars faster and easier.  See [[Fusion Propulsion]] for more information.

@@ Line 8: / Line 8: @@
 *Fusion may use Deuterium, an [[Isotopes |Isotope]] of hydrogen with one proton and one neutron.  Deuterium is rare, and expensive to concentrate.  However, Deuterium on Mars is 5 times more common than on Earth, so this concentration step would be 5 times cheaper.  (In fact, deuterium is so expensive, it might be worth exporting concentrated deuterium to Earth.)  If [[Fusion Propulsion]] space craft are built, Mars may be a spot to inexpensively refuel them.  (Mars' low gravity makes getting fuel into space cheaper than on Earth.)
 *If fission fuel happens to be rare on mars, the relative abundance of fusion fuel might make it more favorable.  This is for the very long term, however.
 *Fusion powered ship should be faster than chemical ones, making the transit to Mars faster and easier.  See [[Fusion Propulsion]] for more information.

@@ Line 8: / Line 8: @@
 *Fusion may use Deuterium, an [[Isotopes |Isotope]] of hydrogen with one proton and one neutron.  Deuterium is rare, and expensive to concentrate.  However, Deuterium on Mars is 5 times more common than on Earth, so this concentration step would be 5 times cheaper.  (In fact, deuterium is so expensive, it might be worth exporting concentrated deuterium to Earth.)  If [[Fusion Propulsion]] space craft are built, Mars may be a spot to inexpensively refuel them.  (Mars' low gravity makes getting fuel into space cheaper than on Earth.)
 *If fission fuel happens to be rare on mars, the relative abundance of fusion fuel might make it more favorable.  This is for the very long term, however.
-*Fusion powered ship should be faster than chemical ones, making the transit to Mars faster and easier.
+*Fusion powered ship should be faster than chemical ones, making the transit to Mars faster and easier.  See [[Fusion Propulsion]] for more information.

← Older revision		Revision as of 14:04, 9 September 2024
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	*If fission fuel happens to be rare on mars, the relative abundance of fusion fuel might make it more favorable. This is for the very long term, however.		*If fission fuel happens to be rare on mars, the relative abundance of fusion fuel might make it more favorable. This is for the very long term, however.
	*Fusion powered ship should be faster than chemical ones, making the transit to Mars faster and easier.		*Fusion powered ship should be faster than chemical ones, making the transit to Mars faster and easier.
−
−	~~==Fusion propulsion==~~
−	~~===General Physical Characteristics of Fusion Propulsion Systems===~~
−	Fusion rockets use a propellant, which in most systems is comprised of the reaction products, unspent fuel, and other material directly involved in the underlying fusion reaction. These materials are contained within a reaction chamber and ejected via a magnetic nozzle. The nozzle typically includes an energy recovery system that is used to power the ignition system, called the ‘‘driver’’. A secondary energy production system is usually required to enable start-up of the propulsion system.
−
−	~~In some variations, the driver may be powered by an external source.~~
−
−	~~The power flow within a fusion propulsion system is shown in the following graph. The graph also shows the physical systems that are required to produce fusion propulsion system.~~
−	~~[[File:Fusiondrive.png\|left\|thumb\|1000x1000px\|This diagram shows a flowchart for a fusion drive]]~~
−
−	~~====Fusion drive example====~~
−
−	Pf= Fusion power, Pf=Feṁ*bf
−	*Pp= Plasma power, Pp=Pf-Pn-Pb
−	*Pn= Neutron losse s
−	*Pb= Bremsstrahlung losses
−	Pt= Thrust power, Pt=(Pp-Pr-Pnl)ηn
−	*Pnl= Nozzle (reaction chamber) power losses
−	*Pr= Recovered power, Pr=Prl-Ps
−	*Prl= Energy recovery system power losses
−	*Ps= Power to ship services
−	*Pi= Driver power (ignition power)
−	*Es= Energy stored in energy recovery system
−	Pth= Thermal power loads from radiation losses, Pth=(Pn+Pb)area ratio
−	*ηn= Nozzle efficiency
−	*bf= Burnup fraction
−	*ṁ= Mass flow of propellant
−	*G= Gain, G=Pf/Pi
−	Fusion power = fusion energy releasemass flowburnup fraction, Pf=Efṁ*bf
−	*Plasma power = Fusion power-Neutron losses-bremsstrahlung losses, Pp=(Pf-Pn-Pb)ηn
−	Thrust power = (Plasma power-Recovered power-Nozzle power losses)nozzle efficiency, Pt=(Pp-Pr-Pnl)ηn
−	*Ignition power = Power recovery-Power recovery system losses- Ship services, Pi=Pr-Prl-Ps
−
−	~~Recovered power may be replaced by an external source. Project Longshot() used a separate nuclear reactor to power ignition.~~
−
−	~~Fusion gain = Fusion power/ Recovered power, G=Pf / Pr~~
−
−	~~According to Newton’s laws of motion the vehicle thrust (F) is equal to the mass flow rate (ṁ) times the exhaust velocity(ve) and the efficiency of the nozzle (ηn):~~
−	F=ṁve*ηn
−
−	~~Since for a rocket the power (P) can be related to the thrust by the following equation:~~
−	~~Pt=1/2ṁve2 or~~
−	*ve =√(2Pt/ṁ)
−
−	~~It follows that the thrust is related to the power by:~~
−	F=ṁ√(2Pt/ṁ)*ηn or
−	F=√(ṁ2Pt)*ηn
−
−	~~The rocket equation uses the exhaust velocity Ve to find the mass ratio of the vehicle and the final rocket velocity:~~
−
−	~~Rocket equation:~~
−	Vf=Veln(mo/mf)
−
−	~~If the mass flow is constant (as per most of these fusion designs) the distance crossed while under power is:~~
−	s=Ve(t-(m0/ṁ))*ln(m0/mf)+t(Vo-Ve)
−
−	~~where (t) is the time under power and Vo the initial velocity.~~
−
−	Using a mass flow (ṁ) of 1 kg/s and power (P) of 35 300 GW, and supposing an overall efficiency of 0,8, including fusion losses, the thrust from a fusion drive will be F=√(1kg/s35300GW2)*0,8= 8 403 000 N or 857 tonnes. This is about ¼ of the thrust of the Saturn 5 rocket. And a power level much greater than the entire energy production of present human civilization.
−	As can be seen, the mass flow of fusion products will be very low for lower powers. Therefore it is unlikely that fusion could be use for launching from planetary surfaces, but would be more appropriate for interplanetary travel.
−
−	~~Pure fusion is rather overpowered for Mars transportation. Fusion is more interesting when additional propellant is added to the drive, the power is reduced and the thrust increased.~~
−
−	~~===Possible fusion reactions===~~
−	D+T(Deuterium + Tritium) fusion is the easiest to ignite, though it ejects a high-energy (14.1 MeV) neutron that holds most of the energy and poses problems for engine design. Moreover, Tritium has a very short half-life, 13.5 years, so it radioactive and decays into He3. D+T works fine for Earth or Mars based power reactors, which is why it is used for most of the present research projects on fusion, and since the high energy neutron can combine with lithium to produce a new tritium atom, a D+T reactor can ‘breed’ its own fuel.
−
−	D+He3(Deuterium+Helium3) fusion is often favored as a space vehicle fuel because it is intrinsically aneutronic. However, any DHe3 mixture produces unavoidable DD(Deuterium+Deuterium) reactions as well, and at a higher rate in some temperature ranges(). The DD side-reactions produce their own neutrons, plus Tritium, which reacts immediately with available deuterium in the plasma to produce the aforementioned 14.1 MeV high energy neutrons. This all significantly limits the nominal aneutronic benefit. In addition, He3 is almost completely nonexistent on Earth or Mars, with most supplied from tritium decay, and is incredibly scarce in the potential resources of remote places like the Moon and the gas giants(3). Reactors producing He3 as byproducts would be useful. He3 might be produced on Earth using D-D breeder reactors. These could feed higher power D+He3 reactors, and in particular D+He3 engines for space vehicles that would require less shielding than equivalent D+D or D+Tritium engines.
−
−	D+D fusion is an interesting option since Deuterium is readily available via seawater separation, distillation and hydrogen isotope separation on Earth or on Mars, and can be stored cryogenically indefinitely, given an appropriate refrigeration system. It also isn’t radioactive when compared to Tritium. Its major downside is that there are two equally probable DD fusion reactions, one that produces Tritium and a proton, and one that produces He3 and a high energy neutron. The Tritium, with it’s lower fusion temperature, will fuse and create the 14.1 MeV neutron already mentioned. The waste energy of the high energy neutrons cannot be recaptured easily, but some drive designs manage to do it. The D+D mix is harder to ignite than D+T, but easier than D+He3. The cascade fusion of 6 Deuterium atoms (table 1, reaction 11) produces 2 He4 atoms, 2 protons and 2 neutrons. About 40% of the energy release is carried by the neutrons.
−
−	p+B11 is another interesting reaction that does not produce any neutrons. And it has the further benefit that there are no secondary reactions, as opposed to D-He3 mixes. It is very difficult to initiate, however, and may lose excessive amounts of energy through electromagnetic (bremstalhung) radiation for a drive. It is actively studied()() as a power source, however. Bremstralhung radiation might be recovered using x-ray tuned photocells. It’s also important to note that releases about a quarter of the energy per kg of other reactions, so a Boron powered spaceship might require more propellant, depending on the burnup fraction.

@@ Line 7: / Line 7: @@
 ==Advantages on Mars==
 *Fusion may use Deuterium, an [[Isotopes |Isotope]] of hydrogen with one proton and one neutron.  Deuterium is rare, and expensive to concentrate.  However, Deuterium on Mars is 5 times more common than on Earth, so this concentration step would be 5 times cheaper.  (In fact, deuterium is so expensive, it might be worth exporting concentrated deuterium to Earth.)  If [[Fusion Propulsion]] space craft are built, Mars may be a spot to inexpensively refuel them.  (Mars' low gravity makes getting fuel into space cheaper than on Earth.)
 *Fusion powered ship should be faster than chemical ones, making the transit to Mars faster and easier.

@@ Line 1: / Line 1: @@
-Modern nuclear power generates energy by splitting apart rare, huge atoms releasing the binding energy.  This is called nuclear fission.
+Modern nuclear power generates energy by splitting apart large atoms, releasing some of the binding energy.  This is called nuclear fission.
 However, stars generate energy by joining small atoms into larger ones.  This is called fusion.  Fusion power plants have not been built on Earth yet.  But if such a power source is created, it might be a good source of power on Mars.
@@ Line 8: / Line 8: @@
 *Fusion may use Deuterium, an [[Isotopes |Isotope]] of hydrogen with one proton and one neutron.  Deuterium is rare, and expensive to concentrate.  However, Deuterium on Mars is 5 times more common than on Earth, so this concentration step would be 5 times cheaper.  (In fact, deuterium is so expensive, it might be worth exporting concentrated deuterium to Earth.)  If [[Fusion Propulsion]] space craft are built, Mars may be a spot to inexpensively refuel them.  (Mars' low gravity makes getting fuel into space cheaper than on Earth.)
 *Fusion powered ship should be faster than chemical ones, making the transit to Mars faster and easier.
-This is a stub.  Help Marspedia by expanding this article.
 ==Fusion propulsion==
 ===General Physical Characteristics of Fusion Propulsion Systems===

← Older revision		Revision as of 13:45, 4 September 2024
Line 70:		Line 70:

	Pure fusion is rather overpowered for Mars transportation. Fusion is more interesting when additional propellant is added to the drive, the power is reduced and the thrust increased.		Pure fusion is rather overpowered for Mars transportation. Fusion is more interesting when additional propellant is added to the drive, the power is reduced and the thrust increased.
		+
		+	===Possible fusion reactions===
		+	D+T(Deuterium + Tritium) fusion is the easiest to ignite, though it ejects a high-energy (14.1 MeV) neutron that holds most of the energy and poses problems for engine design. Moreover, Tritium has a very short half-life, 13.5 years, so it radioactive and decays into He3. D+T works fine for Earth or Mars based power reactors, which is why it is used for most of the present research projects on fusion, and since the high energy neutron can combine with lithium to produce a new tritium atom, a D+T reactor can ‘breed’ its own fuel.
		+
		+	D+He3(Deuterium+Helium3) fusion is often favored as a space vehicle fuel because it is intrinsically aneutronic. However, any DHe3 mixture produces unavoidable DD(Deuterium+Deuterium) reactions as well, and at a higher rate in some temperature ranges(). The DD side-reactions produce their own neutrons, plus Tritium, which reacts immediately with available deuterium in the plasma to produce the aforementioned 14.1 MeV high energy neutrons. This all significantly limits the nominal aneutronic benefit. In addition, He3 is almost completely nonexistent on Earth or Mars, with most supplied from tritium decay, and is incredibly scarce in the potential resources of remote places like the Moon and the gas giants(3). Reactors producing He3 as byproducts would be useful. He3 might be produced on Earth using D-D breeder reactors. These could feed higher power D+He3 reactors, and in particular D+He3 engines for space vehicles that would require less shielding than equivalent D+D or D+Tritium engines.
		+
		+	D+D fusion is an interesting option since Deuterium is readily available via seawater separation, distillation and hydrogen isotope separation on Earth or on Mars, and can be stored cryogenically indefinitely, given an appropriate refrigeration system. It also isn’t radioactive when compared to Tritium. Its major downside is that there are two equally probable DD fusion reactions, one that produces Tritium and a proton, and one that produces He3 and a high energy neutron. The Tritium, with it’s lower fusion temperature, will fuse and create the 14.1 MeV neutron already mentioned. The waste energy of the high energy neutrons cannot be recaptured easily, but some drive designs manage to do it. The D+D mix is harder to ignite than D+T, but easier than D+He3. The cascade fusion of 6 Deuterium atoms (table 1, reaction 11) produces 2 He4 atoms, 2 protons and 2 neutrons. About 40% of the energy release is carried by the neutrons.
		+
		+	p+B11 is another interesting reaction that does not produce any neutrons. And it has the further benefit that there are no secondary reactions, as opposed to D-He3 mixes. It is very difficult to initiate, however, and may lose excessive amounts of energy through electromagnetic (bremstalhung) radiation for a drive. It is actively studied()() as a power source, however. Bremstralhung radiation might be recovered using x-ray tuned photocells. It’s also important to note that releases about a quarter of the energy per kg of other reactions, so a Boron powered spaceship might require more propellant, depending on the burnup fraction.

@@ Line 57: / Line 57: @@
 The rocket equation uses the exhaust velocity Ve to find the mass ratio of the vehicle and the final rocket velocity:
 Rocket equation:
 *Vf=Ve*ln(mo/mf)

@@ Line 46: / Line 46: @@
 According to Newton’s laws of motion the vehicle thrust (F) is equal to the mass flow rate (ṁ) times the exhaust velocity(ve) and the efficiency of the nozzle (ηn):
-F=ṁ*ve*ηn
+*F=ṁ*ve*ηn
 Since for a rocket the power (P) can be related to the thrust by the following equation:
 Pt=1/2ṁve2  or
-ve =√(2Pt/ṁ)
+*ve =√(2Pt/ṁ)
 It follows that the thrust is related to the power by:
+*F=ṁ*√(2Pt/ṁ)*ηn   or
+*F=√(ṁ*2Pt)*ηn
 The rocket equation uses the exhaust velocity Ve to find the mass ratio of the vehicle and the final rocket velocity:
 Rocket equation:
-Vf=Ve*ln(mo/mf)
+*Vf=Ve*ln(mo/mf)
 If the mass flow is constant (as per most of these fusion designs) the distance crossed while under power is:
+*s=Ve*(t-(m0/ṁ))*ln(m0/mf)+t(Vo-Ve)
 where (t) is the time under power and Vo the initial velocity.