Missile Guidance Using Pre-calculated Trajectory Data
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Solution Overview
Problem
Modern air defense systems face challenges in efficiently guiding autonomously guided missiles to their targets, especially when the missile's detection range exceeds the target's location, requiring computationally intensive trajectory calculations that account for various boundary conditions, including energy efficiency, maneuverability, and optimal seeker conditions, especially when targeting moving or low-flying targets.
Innovation Solution
The method involves pre-calculating and storing trajectory data in a data memory that considers multiple boundary conditions before launch, allowing the processing means to select optimal trajectory data for guiding the missile, reducing computational effort during flight and enabling flexible adjustments for changing target positions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If trajectory calculations are performed in real-time during flight to account for boundary conditions and moving targets, then the missile can adapt to changing target positions and optimize flight path, but the computational effort and complexity of processing equipment increase significantly
Solution Approach 1:
The patent pre-calculates and stores optimal trajectories for various target positions and boundary conditions before the missile is deployed. During flight, the missile simply retrieves and follows the pre-computed trajectory corresponding to its current target position, eliminating the need for complex real-time trajectory optimization calculations while maintaining adaptability to moving targets.
Solution Approach 2:
The system performs comprehensive trajectory calculations offline, considering all possible boundary conditions (energy efficiency, maneuverability, seeker conditions) and stores them in a database. This preliminary computation allows the missile to operate with minimal onboard processing power during actual flight.
2Reliability
If comprehensive boundary conditions are considered in trajectory calculations to optimize energy efficiency, maneuverability, and seeker conditions, then the missile guidance becomes more effective and accurate, but the calculation time and computational resources required increase
Solution Approach 1:
All trajectory optimizations considering multiple boundary conditions (energy efficiency, maneuverability, seeker locking conditions) are performed beforehand and stored in a database. During flight, the missile only needs to retrieve the appropriate pre-optimized trajectory based on current conditions, achieving both high guidance effectiveness and fast response without real-time computation delays.
3Productivity
If the missile uses autonomous guidance with pre-stored trajectory data for multiple trajectories, then the computational effort during flight is minimized and the system design becomes more efficient, but the data storage requirements and complexity of trajectory selection increase
Solution Approach 1:
The guidance system divides the flight path into multiple discrete trajectory segments, each stored in the database with specific characteristics (energy-efficient, high-maneuverability, seeker-optimized). The missile selects and executes the appropriate segment based on current flight conditions, making the system manageable and efficient without requiring complex real-time optimization.
Data Source
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AI summary
The method involves storing path data describing flight paths of a guided missile in a data storage unit, and selecting the path data of one of the flight paths as control data from the storage unit using target data by a process unit. Flight of the missile is controlled by the control data, and the path data are calculated before deployment of the missile from a starting point (42) to end points (44, 44b), where the path data comprises trajectories (40-40c) of the flight paths. A model of the missile and impact conditions of the missile in a target are stored in the storage unit. An independent claim is also included for a device for controlling a guided missile.