High-temperature heater for spacecraft electric propulsion system

The invention discloses a high-temperature heater for an electric propulsion system of a spacecraft, and relates to the technical field of electric propulsion systems of spacecrafts, and the heater adopts a closed shell structure formed by combining titanium alloy and aluminum oxide ceramic, a high-temperature ceramic electric heating slurry heating wire and an aluminum oxide ceramic structure heat conduction substrate. Compared with a traditional heater, the heater has the advantages of being capable of resisting the high temperature of 250 DEG C, high in structural strength, light, small, long in service life, high in reliability and the like. 本发明公开了一种航天器电推进系统用高温加热器，涉及航天器电推进系统技术领域，该加热器采用钛合金、氧化铝陶瓷相组合的封闭壳体结构、高温陶瓷电热浆料加热丝和氧化铝陶瓷结构导热基底。该加热器相比传统加热器具有能够耐受250℃高温、结构强度高、轻小、长寿命、高可靠等特点。