Onboard Missile Guidance via Real-Time Flight Path Simulation
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Solution Overview
Problem
Current surface-to-air missile guidance systems rely on uplink communication, which can fail, leading to course corrections being unavailable, especially with longer-range missiles, resulting in potential misses or unnecessary destruction.
Innovation Solution
An onboard computer system that numerically simulates the missile's flight path in real time using a 3-degree-of-freedom model to adjust the aim point and intercept point iteratively, accounting for variations in rocket motor performance, allowing for autonomous course corrections and serving as a backup to remote guidance systems.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If uplink communication is used for missile guidance, then centralized control and coordination are improved, but system reliability deteriorates due to communication failure risk
Solution Approach 1:
The missile's onboard computer autonomously calculates its own flight path, impact point, and course corrections without requiring continuous external guidance. The system serves itself by using onboard sensors and an iterative numerical simulation process to determine guidance commands independently.
Solution Approach 2:
The onboard computer pre-calculates multiple potential flight paths and impact points before communication failure occurs. By having guidance algorithms and simulation models ready in advance, the missile can immediately switch to autonomous operation without interruption.
2Measurement precision
If individualized guidance is provided for each missile, then guidance accuracy is improved, but system complexity increases
Solution Approach 1:
Each missile carries its own guidance computer that independently calculates individualized flight paths based on its specific rocket motor characteristics. This eliminates the need for complex external tracking and calculation systems, as each missile performs its own guidance computations autonomously.
Solution Approach 2:
The patent replaces complex mechanical tracking systems with onboard numerical simulations. The iterative calculation process uses mathematical models to substitute for physical tracking infrastructure, reducing system complexity while maintaining individualized guidance accuracy.
3Measurement precision
If computational resources are increased for more accurate simulation, then aim point precision is improved, but resource consumption increases
Solution Approach 1:
The system performs iterative calculations only to the extent necessary to achieve convergence within acceptable error margins. The numerical simulation continues iterating until the aim point stabilizes, performing just enough computation to achieve required precision without excessive resource consumption.
Solution Approach 2:
The iterative process dynamically adjusts computational parameters, refining the aim point calculation step-by-step. By changing parameters incrementally and stopping when convergence criteria are met, the system achieves high precision without requiring maximum computational resources from the start.
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AI summary
A guidance method for a powered ballistic missile (10) involves using an onboard computer to numerically simulate the flight path of the missile in real time, using a model with at least 3 degrees of freedom. The results of this simulation are used to update in real time an aim point and/or a predicted intercept point. An iterative process may be used in adjusting the aim point and/or the predicted intercept point. The process may be carried out until a specified number of steps have been completed, and/or until a specified heading error threshold of the aim point and a specified time of flight threshold have been achieved. The use of real time updating of an aim point of the missile advantageously takes into account variations in missile velocity and position due to individual variations in the rocket motor of the missile.