A time-based polar coordinate space light field azimuth guiding device and method

By employing a temporal polar coordinate spatial optical field orientation guidance device in laser beam riding guidance, a circular optical field is formed by radial oscillation and circumferential rotation. Combined with detector time difference vector synthesis, the problems of coding complexity and high hardware cost in laser beam riding guidance are solved, achieving simplified calculation and cost reduction.

CN117433359BActive Publication Date: 2026-06-26NO 27 RES INST CHINA ELECTRONICS TECH GRP
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
NO 27 RES INST CHINA ELECTRONICS TECH GRP
Filing Date
2023-09-18
Publication Date
2026-06-26

AI Technical Summary

Technical Problem

In existing laser beam-riding guidance technologies, spatial coding methods suffer from problems such as a central dead zone, high requirements for laser repetition frequency, complex calculation algorithms, and high hardware costs.

Method used

A time-based polar coordinate spatial optical field orientation guidance device is adopted. A laser is mounted on a circumferential stepping rotation mechanism. Combined with radial oscillation and circumferential rotation driving mirrors, a circular optical field is formed. Vector synthesis guidance is performed by using the time difference of the laser signal received by the detector, which simplifies the solution process.

Benefits of technology

It reduces system complexity and hardware costs, simplifies the computation circuit, and achieves efficient laser beam guidance without the need for complex laser spatial polarization, intensity, and frequency modulation.

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Abstract

The application discloses a kind of polar coordinate space light field azimuth guiding device and method based on timing, including laser, reflector, radial swing mechanism and circumferential stepping rotation mechanism, laser is erected on the upper portion of circumferential stepping rotation mechanism, light emitting position is fixed relative to radial swing mechanism, by radial swing and circumferential rotation combined drive, make reflector do spatial periodic swing, and laser beam forms circular light field;From the timing angle, it is guaranteed that laser is always scanned from the center to the circumference;Solution module only needs to identify the spot time arriving at detector, and distributes weight according to timing, and synthesizes guide vector, and there is no information interaction with launch carrier;The method greatly reduces the system complexity and device cost of the existing laser pilot guidance system, without complex laser spatial polarization, light intensity, frequency modulation, etc., and the hardware solution circuit is simple and reliable.
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