Quartz accelerometer semiconductor heat dissipation structure for inertial platform

Abstract

The invention discloses a quartz accelerometer semiconductor heat dissipation structure for an inertial platform, relates to the field of mechanical structure design of an inertial measurement deviceand is mainly used for realizing high-precision inertial navigation in the fields of aviation and spaceflight. The structure is characterized in that a heating rod is arranged in the center of a temperature control body, a temperature measuring sensor is arranged on the temperature control body, so heating and temperature monitoring of the temperature control body are realized, a semiconductor bottom plate is pressed on a mounting surface of a table body, the temperature control body is pressed on the semiconductor bottom plate and is used for refrigerating and cooling the temperature controlbody through a one-way heat transfer function of the semiconductor bottom plate, a semiconductor shell plate is arranged on an outer surface of a wind shielding shell, the temperature control body, and the quartz accelerometer, the heating rod and the temperature measuring sensor are wrapped in the shell. The structure is advantaged in that influence of air disturbance around the table body is avoided, the semiconductor shell plate is used for refrigerating and cooling the wind shielding shell, temperature stability and rapidity of the temperature control body are guaranteed; good heat conduction gas helium is filled into a gap between the wind shielding shell and the table body, gap thermal resistance between the temperature control body and the wind shielding shell is reduced, and the heat dissipation capacity of the temperature control body is improved.

Description

technical field [0001] The invention relates to the field of mechanical structure design of an inertial measurement device, in particular to a semiconductor heat dissipation structure of a quartz accelerometer for an inertial platform, which is mainly used for high-precision inertial navigation in the fields of aviation and aerospace. Background technique [0002] The inertial stable platform system generally uses three high-precision quartz accelerometers installed orthogonally as a measurement combination to measure the linear acceleration of the carrier in the navigation coordinate system, and obtain the carrier velocity and position through two integrations to realize the navigation function. The measurement accuracy of the high-precision quartz accelerometer measurement combination directly affects the system navigation accuracy, and the temperature stability of the high-precision quartz accelerometer measurement combination is an important factor affecting its measureme...

AI Technical Summary

Problems solved by technology

However, the disadvantage of this method is that when the ambient temperature rises or the heat generated by the mechanical gyroscope increases, it is easy to cause overheating of the quartz accelerometer on the platform.

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