Experimental research on the characteristics of precision measurement system elements for spacecraft scientific payload

The primary function of a spacecraft scientific payload is to perform measurements. The voltage reference is a key component of a measurement system, determining its accuracy. During normal system operation, the reference voltage is subject to temperature-induced variations which, unlike initial error, cannot be eliminated by on-ground calibration. The performance of the ISL21090B-50 voltage reference was experimentally evaluated within the typical operating temperature range for space equipment. Its integral and differential temperature coefficients and thermal hysteresis were determined. Conclusions were drawn regarding the theoretically achievable resolution of a precision measurement system based on this integrated circuit, and methods for its improvement are described. The theoretical possibility of improving measurement system resolution is demonstrated for voltage references with a linear voltage-temperature relationship, using mathematical compensation based on the actual temperature of the reference element. The performance of radiation-hard 5306NT025 integrated temperature sensors was experimentally evaluated in a climate chamber for use as internal telemetry sensors in future space projects, and their error vs. temperature curves were obtained. An example of thermal drift compensation for the ISL21090B-50 reference is presented, utilizing the data acquired from the temperature sensors.