Rapid generation method for starlight/inertial composite guidance missile-borne fixed star database

Abstract

The invention discloses a rapid generation method for a starlight/inertial composite guidance missile-borne fixed star database, the rapid generation method fully considers storage and calculation speed conditions of a missile-borne computer, the missile-borne fixed star database is generated according to an order of nebula/star cluster, inertial platform limitation, ground level avoidance and strong light source avoidance, a celestial pole transformation method is used to achieve the ground level avoidance, less memory is occupied, and the calculation speed is faster. The avoidance calculation of the nebula/star cluster is completed before loading of a fixed star database onto a missile, the amount of calculation on the missile is reduced; when the missile-borne fixed star database is generated on the missile, the missile-borne fixed star database is generated according to the order of inertial platform limitation, ground level avoidance and strong light source avoidance, the amount of calculation of the missile-borne computer is minimized, and the storage limit of the computer is reduced; and the celestial pole transformation method is used to achieve the ground level avoidance,reduces the computational complexity of the existing algorithm and improves the calculation accuracy.

Description

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AI Technical Summary

Benefits of technology

This new technology allows for faster calculations by considering factors like storing data at different levels or calculating specific objects within certain limits without requiring too much RAM space. It also includes methods that can prevent sunlight from reaching sensitive components inside an aircraft during flight. Overall, this innovation helps improve efficiency and reliability of airplanes equipped with radar systems.

Problems solved by technology

This patented technical problem addressed in this patents relating to improving the precision and efficiency of guided rocket systems used for longer range missions involves accurately detecting and compensate any deviations due to various sources like external influences including stray impacts, inclination angles, and other disturbances. These can lead to reduced mission success rates and increased risk of collateral damage. Current methods involve complex calculations involving multiple components with limited capabilities.

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