High-specific stiffness supporting structure of space optical remote sensor

Abstract

The invention discloses a high-specific stiffness supporting structure of a space optical remote sensor, and belongs to the technical field of space optics. The supporting structure solves the problems that in the prior art, a supporting structure of the space optical remote sensor is heavy, poor in stability and low in inherent frequency. The supporting structure comprises a carbon fiber front cylinder, a carbon fiber rear cylinder, a secondary mirror embedded part, a carbon fiber secondary mirror support, a carbon fiber supporting ring, a plurality of supporting ring embedded parts, truss rod connectors, a plurality of carbon fiber truss rods, truss embedded parts, a carbon fiber matrix, primary mirror assembly embedded parts, a three-mirror embedded part and a carbon fiber rear cover. The carbon fiber front cylinder is connected to the carbon fiber rear cylinder, the secondary mirror embedded part adheres to the middle of the carbon fiber secondary mirror support, the supporting ring embedded parts are circumferentially and uniformly distributed on the carbon fiber supporting ring, the front ends of the carbon fiber truss rods are connected to the back surface of the carbon fiber supporting ring, the rear ends of the carbon fiber truss rods are connected to the truss embedded parts of a main backboard assembly, and the carbon fiber rear cover, the truss assembly embedded parts, the three-mirror assembly embedded part and the primary mirror assembly embedded parts are connected to the carbon fiber matrix.

Description

technical field [0001] The invention belongs to the technical field of space optics, and in particular relates to a support structure for a space optical remote sensor with high specific stiffness. Background technique [0002] Space optical remote sensors are widely used in many fields such as detailed survey and census of earth resources, topographic surveying and mapping, ocean research, urban construction, agricultural development, weather forecast, military reconnaissance, etc. Space optical remote sensors will be tested by various external loads and environmental conditions such as vibration, shock and noise during the development, testing and launch stages on the ground. Among them, the dynamic environment has the greatest impact on the remote sensor. The dynamic loads on the remote sensor mainly include accidental shocks and explosion shocks caused by adjustment and experimentation, ground transportation, separation of the fairing of the launch vehicle, separation o...

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to provide a support structure for space optical remote sensors with high specific stiffness, which solves

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