Partial stabilization-based guidance.

Area of Science:

• Aerospace Engineering
• Control Systems Theory
• Nonlinear Dynamics

Background:

• Traditional missile guidance laws often assume unrealistic stability conditions for all system states.
• Real-world engagements with maneuvering targets necessitate guidance systems that adapt to dynamic and complex scenarios.
• Achieving asymptotic or exponential stability for every state in a guidance system is often impractical.

Purpose of the Study:

• To design a novel nonlinear missile guidance law based on partial stability principles.
• To develop a guidance law that ensures system states behave realistically during engagement with maneuvering targets.
• To validate the proposed guidance law's performance against a sliding mode guidance law.

Main Methods:

• Design of a nonlinear guidance law utilizing the partial stability theorem.
• Development of a closed-loop guidance system where state behaviors conform to realistic collision scenarios.
• Comparative numerical simulations to evaluate interception time and control effort.

Main Results:

• The proposed guidance law demonstrates effective control over system states, aligning with practical engagement dynamics.
• Simulations indicate favorable performance in terms of reduced interception time and control effort compared to the sliding mode guidance law.
• The partial stability approach provides a more realistic framework for missile guidance system design.

Conclusions:

• The novel nonlinear guidance law based on partial stability offers a more practical and effective solution for engaging maneuvering targets.
• The developed guidance law ensures realistic state behaviors, leading to successful collision scenarios.
• This research contributes a new perspective on missile guidance design by incorporating partial stability for improved performance.