High-temperature integrated armored heater for satellite green high-energy non-toxic thruster

Abstract

The invention discloses a high-temperature integrated armored heater for a satellite green high-energy non-toxic thruster, and belongs to the technical field of armored heating devices. The integratedarmored heater is of an annular structure, the size of the inner wall of the integrated armored heater is matched with that of a catalytic bed, and the heater comprises three parts including a working section, a transition section and a leading-out section; the working section is a main heating and heat conduction part and comprises a double-path heating body, an armored shell, a heating body framework and ceramic powder; the heating body is made of PtRh alloy, and the PtRh alloy is tightly wound to form a spiral heating body; the integrated armored heater is internally provided with two paths of spiral heating bodies which comprise a path of high-power heating body and a path of low-power heating body; and the rated power of the high-power heating body can reach 30 W, the rated power ofthe low-power heating body is 3 W, when the catalytic bed needs to be heated rapidly, the two paths work at the same time to guarantee the temperature of the bed body, and when low-temperature keepingis needed, only a low-power device works, and on-satellite energy is saved.

Description

technical field [0001] The invention relates to the technical field of armored heating devices, in particular to a high-temperature integrated armored heater for star green high-energy non-toxic thrusters. Background technique [0002] In satellites, green thrusters have gradually replaced hydrazine thrusters with their advantages of safety and non-toxicity, but they also face many problems during the use of green thrusters. For example, green propellants (ammonium dinitramide and hydroxylamine nitrate ) has a high preheating temperature, and the general preheating temperature of the propellant must reach above 350°C; secondly, the combustion temperature of the green propellant is above 1500°C, and the increase of the combustion temperature makes other parts of the thruster (thrust chamber, catalyst , armored heaters, etc.) the conditions of use have changed, the thrust chamber and the catalyst are a single material, only need to change the shape and quality, and the armored...

AI Technical Summary

Problems solved by technology

Due to the low strength of platinum-rhodium alloy, the area of ​​the elastic region in the tensile curve is small, and the alloy wire is prone to plastic deformation under low stress. After repeated plastic bending, the heating wire will break. Therefore, platinum-rhodium alloy is currently used as the armor of the heating wire. Installing a heater is rarely reported

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