Direct generation method of emitter trajectory based on space-based sensing signal

Abstract

The application belongs to the technical field of satellite communication, and discloses a radiation source trajectory direct generation method based on a space-based sensing signal, which comprises the following steps: initializing the value of a sampling particle and initializing a particle weight; performing time delay coarse capture on a radiation source signal to obtain a coarse time delay interval of the radiation source; calculating compensation time delay and Doppler frequency shift according to the coarse capture time delay, and calculating a compensation time delay matrix and a frequency shift matrix; calculating particle weight normalized particle weight of the particle according to the compensation time delay matrix and the frequency shift matrix; calculating a target estimation state of the present iteration according to the normalized particle weight; resampling the particle to obtain a resampled particle, and obtaining a next generation particle according to the resampled particle; if the iteration is terminated, taking a target estimation state sequence obtained through multiple iterations as an output result, otherwise, performing the next iteration. The application effectively reduces the search space and calculation complexity of particle filtering, and improves the trajectory generation accuracy in a large time delay uncertainty scene.

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