초록 ▼

An exhaust valve downstream of a diesel engine splits exhaust gasses between two catalysts. In one position, most of the exhaust gasses go to a first catalyst, and the remaining exhaust gasses, along with injected reductant go to a second catalyst. In a second position, most of the exhaust gasses go

An exhaust valve downstream of a diesel engine splits exhaust gasses between two catalysts. In one position, most of the exhaust gasses go to a first catalyst, and the remaining exhaust gasses, along with injected reductant go to a second catalyst. In a second position, most of the exhaust gasses go to the second catalyst, and the remaining exhaust gasses, along with injected reductant go to the first catalyst. In this way, a reduced cost system is achieved.

대표청구항 ▼

An exhaust valve downstream of a diesel engine splits exhaust gasses between two catalysts. In one position, most of the exhaust gasses go to a first catalyst, and the remaining exhaust gasses, along with injected reductant go to a second catalyst. In a second position, most of the exhaust gasses go

An exhaust valve downstream of a diesel engine splits exhaust gasses between two catalysts. In one position, most of the exhaust gasses go to a first catalyst, and the remaining exhaust gasses, along with injected reductant go to a second catalyst. In a second position, most of the exhaust gasses go to the second catalyst, and the remaining exhaust gasses, along with injected reductant go to the first catalyst. In this way, a reduced cost system is achieved. nt is an oxidizer, and said precombustion chamber includes said second solid reactant which is a fuel. 15. A hybrid rocket motor according to claim 13, wherein: said second fluid reactant is an oxidizer, and said precombustion chamber includes said at least one inlet, wherein said third fluid reactant is a fuel. 16. A hybrid rocket motor according to claim 15, further comprising: e) a second fluid reactant tank including said second fluid reactant, said second fluid reactant tank in communication with said first inlet. 17. A hybrid rocket motor according to claim 16, further comprising: f) a third fluid reactant tank including said third fluid reactant, said third fluid reactant tank in communication with said second inlet. 18. A hybrid rocket motor according to claim 16, further comprising: f) said second inlet is in communication with said container, wherein said third fluid reactant is said first fluid reactant. 19. A hybrid rocket motor, comprising: a) a container having a first fluid reactant therein and an outlet; b) a main combustion chamber containing a solid reactant therein; c) a main injector between said container and said main combustion chamber, said main injector having a face with a plurality of pathways through which said first fluid reactant is injected into said main combustion chamber to be combusted with said solid reactant; d) a second fluid reactant; e) a third fluid reactant stored separately from said second fluid reactant; f) a precombustion chamber at a head end of said main combustion chamber, said second and third reactants being combined and combusted in said precombustion chamber to generate heat adjacent said face of said main injector. 20. A hybrid rocket motor according to claim 19, wherein: said first fluid reactant is an oxidizer, and said solid reactant is a fuel. 21. A hybrid rocket motor according to claim 19, wherein: said second fluid reactant is an oxidizer, and said third fluid is a fuel. 22. A hybrid rocket motor according to claim 20, wherein: said first and second fluid reactants are the same. 23. A hybrid rocket motor according to claim 22, wherein: said second fluid reactant is stored in said first container. 24. A hybrid rocket motor according to claim 19, wherein: said second fluid reactant is selected from the group of gaseous oxygen, liquid oxygen, triethyl aluminum, trimethlyl aluminum, and triethyl borine, and said third fluid reactant is selected from the group of propane, ethane and ethylene. 25. A hybrid rocket motor according to claim 19, wherein: a mixture of said second and third fluid reactants is hypergolic. 26. A hybrid rocket motor according to claim 25, wherein: said second fluid reactant is nitric acid and said third fluid reactant is aniline. 27. A hybrid rocket motor according to claim 19, wherein: said main injector extends substantially through an entirety of a length of said precombustion chamber such that an annular exit nozzle for said precombustion chamber is defined about said face of said main injector. 28. A hybrid rocket motor according to claim 19, wherein: said precombustion chamber includes a recirculation zone forward of said face of said main injector. 29. A hybrid rocket motor according to claim 19, wherein: said second and third fluid reactants are swirled together. 30. A projectile, comprising: a) a motor having a forward end and an aft end, said motor including, i) a container having a first fluid reactant therein and an outlet, ii) a main combustion chamber containing a first solid reactant therein, iii) a first fluid reactant injector between said container and said main combustion chamber through which said first fluid reactant is injected into said main combustion chamber to be combusted with said first solid reactant, iv) a precombustion chamber at a head end of said main combustion chamber, v) a second fluid reactant which is injected into said precombustion chamber, and vi) a third reactant which is contacted with said second fluid reactant in said precombustion chamber to form a combustible propellant, wherein heat generated from combustion of combustible propellant heats said injected first fluid reactant; b) a tubular body around said motor; c) a nose portion coupled to said forward end of said motor; and d) a nozzle coupled to said aft end of said motor. 31. A method of igniting a hybrid rocket motor, comprising: a) providing a hybrid rocket motor having a forward end and an aft end, said motor including, i) a container having a fluid first reactant therein and an outlet, ii) a combustion chamber containing a solid second reactant combustible with said fluid first reactant and having a head end and an aft end, iii) an injector between the container and the head end of the combustion chamber; b) providing third and fourth reactants which when mixed together form a propellant; c) mixing the third and fourth reactants at the head end of the combustion chamber to form the propellant; d) combusting the propellant such that the head end of the combustion chamber is heated; e) injecting the fluid first reactant through the injector; f) heating the fluid first reactant by combustion of the propellant; and g) combusting the heated fluid first reactant with the solid first reactant such that the hybrid rocket motor is ignited. 32. A method according to claim 31, wherein: the fluid first reactant is an oxidizer and the solid second reactant is a fuel. 33. A method according to claim 31, wherein: the second and third reactants are fluids. 34. A method according to claim 33, wherein: said mixing includes swirling the second and third reactants together. 35. A method according to claim 31, wherein: the second reactant is a fluid and the third reactant is a solid. of said engine to a target air-fuel ratio based on the detected air-fuel ratio, and increase the feedback control gain to increase the amplitude of air-fuel ratio fluctuation. 5. An exhaust emission control device as defined in claim 1, wherein said microprocessor is further programmed to control the average value of the air-fuel ratio to the stoichiometric air-fuel ratio when the temperature of said rear three-way catalyst is raised. 6. An exhaust emission control device as defined in claim 1, wherein the oxygen storage capacity of said front three-way catalyst is less than the oxygen storage capacity of said rear three-way catalyst. 7. An exhaust emission control device as defined in claim 1, wherein said rear three-way catalyst is a catalyst which traps and reduces NOx according to the air-fuel ratio of the exhaust gas flowing into said rear three way catalyst. 8. An exhaust emission control device as defined in claim 7, wherein said microprocessor is further programmed to: determine whether or not conditions for discharging SOx stored in said rear three-way catalyst are satisfied, and raise the temperature of said rear three-way catalyst when conditions for discharging SOx stored in said rear three-way catalyst are satisfied. 9. An exhaust emission control device as defined in claim 8, further comprising a sensor for detecting start-up of said engine, and said microprocessor is further programmed to determine that conditions for discharging SOx stored in said rear three-way catalyst are satisfied when start-up of said engine is detected. 10. An exhaust emission control device as defined in claim 8, wherein said microprocessor is further programmed to estimate an SOx amount stored in said rear three-way catalyst, and determine whether or not conditions for discharging SOx stored in said rear three-way catalyst are satisfied based on said estimated SOx storage amount. 11. An exhaust emission control device as defined in claim 8, further comprising a sensor which detects an NOx concentration in the exhaust gas flowing out of said rear three-way catalyst, and wherein said microprocessor is further programmed to: estimate a NOx storage amount stored in said rear three-way catalyst and determine that conditions for discharging SOx stored in said rear three-way catalyst are satisfied based on the detected NOx concentration and estimated NOx storage amount. 12. An exhaust emission control device as defined in claim 11, wherein said microprocessor is further programmed to determine that conditions for discharging SOx stored in said rear three-way catalyst are satisfied when the estimated NOx storage amount stored in said rear three-way catalyst is greater than a predetermined amount, and the detected NOx concentration is greater than a predetermined concentration. 13. An exhaust emission control device as defined in claim 8, further comprising a sensor which detects running conditions and wherein said microprocessor is further programmed to stop raising the temperature of said rear three-way catalyst when the detected running conditions are outside a predetermined SOx discharge running region, regardless of whether the conditions for discharging SOx stored in said rear three-way catalyst are satisfied or not. 14. An exhaust emission control device as defined in claim 8, further comprising a sensor which detects a temperature of said rear three-way catalyst, and wherein said microprocessor is further programmed to stop raising the temperature of said rear three-way catalyst when the detected temperature of said rear three-way catalyst is greater than a predetermined temperature greater than the SOx discharge temperature, regardless of whether the conditions for discharging SOx stored in said rear three-way catalyst are satisfied or not. 15. An exhaust emission control device as defined in claim 8, further comprising a sensor which detects the temperature of said rear three-way catalyst, and wherein said microprocesso