Miniaturized space rendezvous and docking laser emission circuit

A technology of laser emission and laser transmitter, which is applied in the direction of circuits, lasers, phonon exciters, etc., can solve the problems of light and small size, space environment application, complex circuit, high power consumption, etc., and improve reliability and stability , simplify the circuit, and solve the effect of large temperature difference

Pending Publication Date: 2022-01-18
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

In general, the laser drive circuit adopts the constant current source and other methods. This method has complex circuits and high power consumption, and it is difficult to meet the requirements of light, small and space environment applications.

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  • Miniaturized space rendezvous and docking laser emission circuit

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Embodiment Construction

[0020] The present invention will be described in further detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, but not to limit the present invention. In addition, it should be noted that, for the convenience of description, only some structures related to the present invention are shown in the drawings but not all structures.

[0021] like figure 1 As shown, the embodiment of the present invention provides a miniaturized space rendezvous and docking laser emitting circuit, which is a key circuit in a laser radar detector for miniaturized aerospace applications. The laser emitting circuit of the present invention includes: a laser emitter module (1), a drive signal enhancement module (2), a high-speed switch module (3), a temperature control and acquisition module (4), and a heat conduction and heat dissipation module (5);

[0022] Among...

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Abstract

In a miniaturized space rendezvous and docking laser emission circuit, a driving signal enhancement module shapes, filters and amplifies a driving signal and then transmits the driving signal to a high-speed switch module, and under the control of the driving signal, the high-speed switch module powers on and off a laser emitter module, so that the laser emitter module is powered off, and the laser emitter module emits surface laser with a preset frequency to a target area; and a temperature control and acquisition module controls the working temperature of the laser emission circuit within a normal range, and a heat conduction and heat dissipation module transfers and releases heat generated by the laser emitter module and the high-speed switch module. The space rendezvous and docking light source emission circuit integration under a laser radar technology system is realized, the problems of large temperature difference, slow heat dissipation and the like in a space environment are effectively solved, and the reliability and the stability are improved while the device size is reduced and the circuit is simplified.

Description

technical field [0001] The invention relates to electronic circuit technology, in particular to a miniaturized space rendezvous and docking laser emitting circuit. Background technique [0002] The laser drive circuit is an important part of the laser radar, which directly affects the operating distance, power consumption, ranging accuracy and other indicators of the laser radar. In general, the laser drive circuit adopts a constant current source and other methods. This method has complex circuits and high power consumption, and it is difficult to meet the requirements of light and small applications in space environments. Contents of the invention [0003] The purpose of the present invention is to provide a miniaturized space rendezvous and docking laser emitting circuit, which has the characteristics of simple structure and high efficiency, and is suitable for space environment applications. [0004] In order to achieve the above object, the technical solution of the ...

Claims

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Application Information

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IPC IPC(8): H01S5/042H01S5/024G01S7/484
CPCH01S5/042H01S5/024G01S7/484
Inventor 赵旸杨逸峰姜丽辉杨世坤左乐余路伟
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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