Self-Deploying Missile Dome Cover via Aerodynamic Drag
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Solution Overview
Problem
Containerized guided missiles face dome contamination during launch due to exposure to harsh chemicals and exhaust materials, which can block or attenuate electromagnetic signals, and existing solutions add complexity, cost, and weight, or produce high-energy debris.
Innovation Solution
A self-deploying dome cover that deploys in response to aerodynamic forces during flight, eliminating the need for actuators or timing electronics, and is designed to be compact, lightweight, and produce minimal debris, using a flexible shroud that unfolds when the missile surpasses a predetermined airspeed.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If a dome cover is used to prevent contamination during launch, then dome contamination is reduced, but the dome cover must be removed during flight which requires additional deployment systems adding complexity and weight
Solution Approach 1:
The dome cover is designed to automatically deploy and jettison using aerodynamic forces generated during missile flight. The cover includes drag tabs that create differential drag to initiate deployment, and frangible members that break apart upon deployment to allow the cover to be shed without active control systems. This self-service mechanism eliminates the need for actuators, timing electronics, or other complex deployment systems.
Solution Approach 2:
The invention replaces active mechanical deployment systems (actuators, motors, electronic controls) with passive aerodynamic forces. The drag tabs utilize the missile's flight airflow to create the necessary forces for deployment, substituting complex mechanical actuation with simple aerodynamic principles. This substitution dramatically reduces system complexity while maintaining effective dome cover deployment.
2Reliability
If actuator deployment systems are used to remove the dome cover, then deployment timing is controlled, but weight and cost increase
Solution Approach 1:
The dome cover deployment system uses the missile's own flight aerodynamics to provide the deployment force, eliminating the need for separate actuator systems. The drag tabs and frangible members work passively with the airflow to achieve deployment at the appropriate time, making the system self-sufficient without adding weight for active deployment mechanisms.
Solution Approach 2:
The dome cover and its deployment mechanism (drag tabs, frangible members) are designed as disposable components that are discarded after single use. This approach reduces the need for heavy, reusable actuator systems while maintaining reliable deployment functionality. The frangible members are designed to break apart once, serving their purpose and then being discarded, which is more weight-efficient than reusable mechanical actuators.
3Device complexity
If tether-pull dome cover systems are used, then no actuator is required, but the tether must be lengthy to clear exhaust plume which increases weight and bulk
Solution Approach 1:
The invention replaces the tether-pull mechanical system with an aerodynamic deployment mechanism. Instead of using a long tether to pull the cover off, the system uses drag tabs that create differential aerodynamic forces to initiate and complete deployment. This substitution eliminates the need for lengthy tethers while still achieving actuator-free operation.
Solution Approach 2:
The invention extracts the essential deployment function from the tether-pull system and implements it through aerodynamic forces acting directly on the dome cover structure. By taking out the tether component entirely and using the missile's flight airflow to provide the deployment force, the system achieves the same result with significantly reduced length and weight.
4Reliability
If non-frangible actuator-deployed dome covers are used, then deployment is controlled, but high-energy debris is produced upon deployment
Solution Approach 1:
The invention changes the material parameter of the dome cover from non-frangible to frangible, and changes the deployment mechanism from actuator-driven to aerodynamic. This parameter change allows the cover to break apart into low-energy fragments upon deployment rather than producing high-energy debris. The frangible members are designed to break in a controlled manner using aerodynamic forces, transforming the deployment characteristics to eliminate harmful debris generation.
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
Effectively prevents dome contamination during launch and flight, ensuring reliable operation of electromagnetic radiation sensors without adding bulk or complexity, and minimizing the risk of high-energy debris.
Implementation Method 1
The self-deploying dome cover is configured to deploy and expose the seeker dome during munition flight in response to aerodynamic forces acting on the self-deploying dome cover
Data Source
AI summary
Embodiments of a guided munition are provided, as are embodiments of a method for equipping a guided munition with a self-deploying dome cover. In one embodiment, the guided munition includes a munition body, a seeker dome coupled to the munition body, and a self-deploying dome cover disposed over the seeker dome. The self-deploying dome cover is configured to deploy and expose the seeker dome during munition flight in response to aerodynamic forces acting on the self-deploying dome cover.