An energy-saving cooling device for space optical remote sensor CCD components

Abstract

The present invention relates to the field of space photoelectric measurement and control, and in particular to an energy-saving heat dissipation device for space optical remote sensor CCD components, including: a hot end, a heat conduction section, a positioning rod and a cold end, and the heat conduction section is placed on the Between the hot end and the cold end, the hot end is fixedly connected to the heat conducting section, the positioning rod is placed inside the heat conducting section, and the two ends of the positioning rod are respectively connected to the hot end and the heat conducting section. The cold end is connected by thread, the heat conduction section and the cold end are arranged in a gap, the hot end and the cold end are made of high thermal conductivity materials, and the heat conduction section adopts high thermal conductivity and high linear expansion coefficient The positioning rod is made of a material with low thermal conductivity and low linear expansion coefficient, and the linear expansion coefficient of the material used in the heat conduction section is greater than that of the positioning rod material. The energy-saving heat dissipation device of the present invention has the advantages of compact structure, simple assembly, strong thermal conductivity, good energy-saving effect and low cost.

Description

technical field [0001] The invention belongs to the field of space photoelectric measurement and control, and in particular relates to an energy-saving heat dissipation device for a CCD component of a space optical remote sensor. Background technique [0002] The CCD component is the core component of the space optical remote sensor. Its good working condition is the key to ensure the imaging quality. The CCD component has very strict requirements on its own working temperature. Too high or too low temperature will reduce its photoelectric conversion ability. Due to the special working requirements of space optical remote sensors, CCD components have the characteristics of small size, high heat generation, and intermittent work. The compensatory heating to prevent its temperature from being too low poses a special problem in the thermal control of CCD components, namely the conflicting requirements of heat dissipation and temperature compensation. [0003] When the space op...

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Problems solved by technology

Due to the strong heat conduction ability of the heat pipe, this thermal control measure can effectively dissipate the heat of the CCD components, but it will also bring about the problem of temperature compensation, that is, when the space optical remote sensor is in a non-working period, due to heat dissipation With the existence of the channel, the CCD component will be in a low temperature state under the action of the lower temperature external radiator

Although the low temperature state can reduce the thermal noise and dark current in the electronic signal, the CCD device not only cannot guarantee its normal start-up temperature in the low temperature state, but also black spots will appear, which will affect the image quality.

The current solution is usually to perform compensation heating to maintain the temperature of the CCD component, but its biggest disadvantage is that the power consumption of the CCD component is usually very large, so the required compensation heating power consumption is also very large, which not only causes a waste of energy, especially For spacecraft with frequent maneuvers, drastic changes in the external environment, and energy shortages, excessive compensation for heating power consumption is even impossible

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