Landmark-Based Inertial Navigation System for Autonomous Navigation of Missile Platform

Area of Science:

• Aerospace Engineering
• Navigation Systems
• Robotics

Background:

• Autonomous navigation is crucial for modern aerospace applications.
• On-orbit landmark observation presents a new data source for enhancing positioning and attitude determination accuracy.
• Existing celestial-inertial navigation systems have limitations in certain operational scenarios.

Purpose of the Study:

• To develop and validate a novel autonomous navigation method for missile platforms.
• To improve the accuracy of state estimation (positioning and attitude determination) using landmark observations.
• To compare the proposed method against traditional and deeply integrated celestial-inertial navigation systems.

Main Methods:

• A new autonomous navigation scheme integrating on-orbit landmark observation with an inertial system.
• Derivation of an implicit observation equation for inertial system output deviations.
• Application of the Kalman filter for high-accuracy missile platform state estimation.
• Analysis of physical and mathematical observability of the navigation system.

Main Results:

• The proposed method achieves high-accuracy estimation of the missile platform state.
• Simulations demonstrate the effectiveness and advantages of the landmark-based autonomous navigation approach.
• The method shows superior performance compared to traditional and deeply integrated celestial-inertial navigation systems.

Conclusions:

• The novel autonomous navigation method effectively utilizes on-orbit landmark observations for precise state estimation.
• This approach offers a viable alternative to enhance the accuracy and robustness of missile platform navigation.
• Further research can explore real-world implementation and sensor fusion strategies.