Guided Missile Topographical Interference Determination
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Guided missiles often face the risk of being lost due to topographical interference before reaching their targets, which can lead to interception at incorrect locations or exposure of friendly launchers to enemy fire.
Innovation Solution
A method and apparatus for determining topographical interference with guided missiles by obtaining pre-calculated expected trajectory information and extracting topographic elevations from stored information, allowing for real-time determination of interference and control of missile launch.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If guided missiles are launched without topographical interference determination, then launch time is reduced and operation is simpler, but missiles may be lost due to topographical interference
Solution Approach 1:
The system performs preliminary determination of topographical interference by comparing pre-stored expected trajectory information with actual topographical data before missile launch. This advance assessment allows the launcher to identify potential interference zones and adjust launch parameters or abort launch before the missile is fired, preventing loss due to topographical interference without adding complex real-time intervention systems.
2Reliability
If real-time topographical interference determination is performed, then missile delivery reliability is improved, but determination time and processing complexity increase
Solution Approach 1:
Expected trajectory information including trajectory data, elevation data, and interference determination results are pre-calculated and stored in a database before launch. When a missile is launched, the system only needs to retrieve and compare this pre-computed data with actual topographical information, significantly reducing real-time processing requirements while maintaining accurate interference determination.
Solution Approach 2:
The determination system dynamically adjusts its operation mode based on mission requirements. For time-critical missions, it uses simplified comparison with pre-stored data. For non-time-critical missions, it performs more comprehensive analysis. This dynamic approach optimizes the balance between determination accuracy and processing time.
3Measurement precision
If comprehensive trajectory information including error factors is used, then determination accuracy is improved, but data processing complexity increases
Solution Approach 1:
The system pre-calculates expected trajectory information by incorporating various error factors such as manufacturing tolerances, environmental variations, and system uncertainties. This comprehensive trajectory data including multiple possible trajectories (e.g., nominal, worst-case scenarios) is stored in advance, allowing the determination system to assess interference risk across the full range of expected variations without performing complex real-time simulations.
Data Source
AI summary
A method of determining topographical interference with a guided missile is proposed. The method may include obtaining a pre-calculated expected trajectory of a guided missile. The method may also include extracting topographic elevations with respect to a topography corresponding to the pre-calculated expected trajectory from stored topographical information. The method may further include determining presence or absence of topographical interference with the guided missile based on bottom trajectory elevation values in the pre-calculated expected trajectory and topographic elevation values corresponding to the bottom trajectory elevation values. The pre-calculated expected trajectory may include top, bottom, left, and right trajectories with respect to a launch direction of the guided missile, calculated based on an error factor for the guided missile, and the error factor includes manufacturing error values with respect to at least one of a weight, center of gravity, a thrust, or a moment of inertia of the guided missile.