Hall effect thruster with cooling of the internal ceramic
View Patent ↗The invention relates to the field of Hall effect thrusters. The invention provides a Hall effect thruster having a discharge channel of annular shape extending along an axis, the discharge channel being defined by an outer wall of annular shape and an inner wall of annular shape situated inside the space defined by the outer wall, a cathode situated outside the discharge channel, and an injector system situated at the upstream end of the discharge channel and also forming an anode, the downstream end of the discharge channel being open, wherein the thruster includes a heat sink device comprising a heat sink in contact with the inner wall and of thermal conductivity that is greater than the thermal conductivity of the inner wall, the heat sink being a sleeve and the heat sink device being suitable for discharging heat from the inner wall to the outside of the thruster so as to reduce the temperature difference between the inner wall and the outer wall.
1. A Hall effect thruster having a discharge channel of annular shape extending along an axis, said discharge channel being defined by an outer wall of annular shape and an inner wall of annular shape situated inside a space defined by said outer wall, a cathode situated outside said discharge channel, and an injector system situated at an upstream end of said discharge channel and also forming an anode, a downstream end of said discharge channel being open, wherein said thruster includes a heat sink device comprising a heat sink in contact with said inner wall and of thermal conductivity that is greater than the thermal conductivity of said inner wall, said heat sink being a sleeve, being distinct from a central core, and said heat sink device being suitable for discharging heat from said inner wall to the outside of said thruster so as to reduce the temperature difference between said inner wall and said outer wall, wherein said thruster further comprises a set of thermal barriers that are positioned along at least part of said heat sink device, said set comprising a first thermal barrier that is a sleeve extending axially along said axis and covering the inside face of the heat sink so that said heat sink is situated in the annular spaced defined by said inner wall and said first thermal barrier, so as to reduce the fraction of the heat that dissipates toward said central core.
2. A Hall effect thruster according to claim 1 , wherein said heat sink is in contact with an inside face of the downstream end of said inner wall and is surrounded by said inner wall.
3. A Hall effect thruster according to claim 1 , wherein a downstream end of said heat sink is in contact with an inside face of the downstream end of said inner wall.
4. A Hall effect thruster according to claim 1 , wherein said heat sink extends towards an upstream end of said thruster, and wherein said heat sink device further includes a link element and an external radiator, an upstream end of said heat sink being connected by said link element to said radiator.
5. A Hall effect thruster according to claim 1 , wherein said heat sink is fastened directly to said inner wall by brazing, the coefficients of thermal expansion of said heat sink and of said inner wall being substantially equal.
6. A Hall effect thruster according to claim 1 , wherein said heat sink is made of carbon.
7. A Hall effect thruster according to claim 6 , wherein said heat sink is coated at least in part in a coating material of thermal conductivity that is at least equal to that of carbon.
8. A Hall effect thruster according to claim 7 , wherein said coating material is selected from a group comprising copper, polycrystalline cubic carbon, and nickel.
9. A Hall effect thruster according to claim 1 , wherein a material of said inner wall is a ceramic.
10. A Hall effect thruster according to claim 9 , wherein said ceramic is boron nitride with silica BNSiO 2 .