Optical Munition Guidance Canard Control System
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Solution Overview
Problem
Current guided mortars are expensive and lack accuracy, leading to high collateral damage and increased costs due to low precision, while unguided mortars result in poor accuracy and excessive rounds required to hit targets, exposing crews to counterbattery fire.
Innovation Solution
A computationally efficient optical guidance system using an infrared seeker, photodetectors, and a low-volume stability augmentation system to control canards for precise steering, combined with a Ram Air Turbine for flight time estimation and MEMS gyros for stabilization, enabling accurate and cost-effective guidance of small caliber munitions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If current guided mortar systems are used, then guidance capability is provided, but cost is excessively high and accuracy is insufficient
Solution Approach 1:
The patent replaces expensive mechanical guidance systems with an optical detection system using photodetectors and an infrared seeker. The control system processes optical signals from the target to generate steering commands, substituting complex mechanical guidance mechanisms with a more cost-effective optical-mechanical hybrid approach that achieves superior accuracy.
Solution Approach 2:
The patent uses an optical copy (infrared image) of the target instead of direct mechanical or radar-based detection. The infrared seeker captures thermal radiation patterns from the target, creating an optical representation that the control system processes to guide the munition, reducing costs while maintaining precision.
2Measurement precision
If unguided mortars are used, then cost is low, but accuracy is poor and collateral damage is high
Solution Approach 1:
The patent implements a closed-loop feedback system where photodetectors continuously monitor the infrared signature of the target, the control system processes this information to determine positional error, and steering commands are generated to correct the trajectory. This real-time feedback enables precise target acquisition while minimizing collateral damage from misfires.
3Productivity
If current guided systems are used, then guidance is provided, but the quantity of rounds required is still excessive
Solution Approach 1:
The patent changes the detection parameter from visible light or radar to infrared thermal radiation. This parameter change enables the system to detect targets with high contrast in the infrared spectrum, significantly improving accuracy and reducing the number of rounds needed to achieve the desired effect.
4Reliability
If expensive guided systems are used, then some accuracy is achieved, but crew survivability is reduced due to extended exposure time
Solution Approach 1:
The patent employs preliminary action by pre-processing infrared images and storing reference target patterns before the munition reaches the target. The control system uses these pre-prepared references to quickly compare against real-time detection data, enabling rapid guidance decisions that reduce flight time and crew exposure while maintaining high accuracy.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
Significantly reduces the Circular Error Probability (CEP), decreases the number of rounds needed to hit targets, lowers overall costs, and minimizes collateral damage by providing precise and robust guidance compatible with existing munitions.
Implementation Method 1
The photodetectors receive tracking signals from an illuminator at a target
Implementation Method 2
A Ram Air Turbine is provided for generating power during flight of the munition to an estimated time of flight to a target
Implementation Method 3
A plurality of canards are provided for controlling a ballistic path of the munition
Implementation Method 4
MEMS gyros for stabilization
Data Source
AI summary
An optically guided munition and control system has a replacement fuse assembly mounted on the front of a munition body or shell casing. An optical seeker subsystem detects an illuminated target and supplies signals to a processor. The processor develops steering commands sent to a flight control subsystem having a plurality of guidance canards which are actuated by drive motors through gear assemblies. The roll of the munition is established and left/right and up/down steering commands are sent to the canard drive motors based upon the optical seeker subsystem detection of the target illuminator. Range adjustment is based upon bore sight lockdown angle and cross range control is based upon left/right centering error. A code is contained in the optical radiation received from the illuminated target which must be validated by a preset code in the system processor to arm the munition.