Optimization Design Method of a New Stabilized Platform Based on Missile-borne Semi-Strap-down Inertial Navigation...

Area of Science:

• Aerospace Engineering
• Mechanical Engineering
• Navigation Systems

Background:

• Existing Micro-Electro-Mechanical-Systems (MEMS) inertial sensors for missile navigation have limitations in precision.
• Directly measuring high-rotation motion requires large-range sensors, impacting overall system performance.
• There is a need for enhanced precision in missile-borne inertial navigation systems.

Purpose of the Study:

• To propose a novel Semi-strap-down Stabilized Platform (SSP) for missile-borne inertial navigation.
• To reduce sensor range requirements by isolating the missile's high-rotational motion.
• To provide theoretical guidance for selecting optimal SSP quality for improved positioning accuracy.

Main Methods:

• Development of a dynamic model for the SSP in a missile-borne environment.
• Analysis of SSP quality's influence on gyro range using the dynamic model.
• Optimization of SSP quality using the Runge-Kutta method and mass gradient control for minimum roll angular rate amplitude.
• Experimental validation using a high-precision, tri-axial flight simulation turntable.

Main Results:

• The optimized SSP reduced angular velocity to 1/3 and measured roll angle error to 60% compared to unoptimized designs.
• The novel SSP effectively segregates high-speed rotational motion.
• The proposed SSP quality selection method offers a new approach for enhancing positioning accuracy.

Conclusions:

• The novel SSP demonstrates superior performance in isolating high-speed rotational motion for missile navigation.
• The findings support the use of high-precision, small-range sensors over low-precision, wide-range sensors.
• This research provides valuable theoretical guidance for improving missile navigation accuracy in challenging environments.