Ejectable Sensor Cover for Missile Front Lens Rain Erosion

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Solution Overview

Problem

The front lens of optronic assemblies in missiles is susceptible to rain erosion, degrading optical performance, and existing solutions to use less erosion-sensitive materials have not provided adequate protection.

Innovation Solution

A removable cover is mounted over the optronic sensor, retained by tie rods and released by a pyrotechnic member controlled by the electronic guidance circuit, ensuring the lens is protected during flight and ejected before terminal phase to maintain detection performance without altering aerodynamics.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If the front lens is exposed during flight, then the sensor can detect the target, but the lens is subjected to rain erosion that degrades optical performance

Engineering Contradiction:
Improvedetection performanceVSAvoidrain erosion
Core Design Contradiction:
ReliabilityVSObject-affected harmful factors

Solution Approach 1:

A removable cover is introduced as an intermediary element between the rain environment and the front lens. The cover protects the lens during flight and is deactivated near the target to allow detection, thus mediating between the conflicting requirements of protection and detection

Inventive Principle:
Principle #24Intermediary (Mediator)

2Object-affected harmful factors

If a removable cover is added to protect the sensor, then rain erosion is prevented, but the device complexity increases

Engineering Contradiction:
Improverain erosion protectionVSAvoidstructure complexity
Core Design Contradiction:
Object-affected harmful factorsVSDevice complexity

Solution Approach 1:

The optronic assembly is segmented into two parts: a protected front lens and a removable cover. This segmentation allows the lens to be protected during flight while enabling easy access for detection, resolving the contradiction between protection and functionality

Inventive Principle:
Principle #1Segmentation

3Object-affected harmful factors

If the cover remains attached during terminal phase, then the sensor is protected, but the aerodynamic performance is altered and detection is blocked

Engineering Contradiction:
Improvesensor protectionVSAvoiddetection capability
Core Design Contradiction:
Object-affected harmful factorsVSProductivity

Solution Approach 1:

The cover transitions from a static attached state during flight to a dynamic ejected state during terminal phase. This dynamic behavior allows the system to adapt to different flight phases, providing protection when needed and enabling detection when required

Inventive Principle:
Principle #15Dynamics

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

The solution effectively prevents rain erosion of the lens while ensuring the sensor's detection performance and maintaining aerodynamic stability, with minimal mass and drag impact.

Implementation Method 1

a pyrotechnic member arranged to generate a force on the cover sufficient to break the retaining members

Methodology Applied
Scientific EffectPyrotechnic explosion: Explosion

Implementation Method 2

retaining members arranged to retain the cover against aerodynamic forces exerted on the cover during flight

Methodology Applied
Scientific EffectAerodynamic force: Drag

Data Source

PatentUS20260036410A1Air vehicle having a protected front optical element
Publication Date: 2026.02.05 SAFRAN ELECTRONICS & DEFENSE (FR)
  • US20260036410A1 patent drawing
  • US20260036410A1 patent drawing

AI summary

An aerial vehicle having a fuselage having a front portion provided with an optronic sensor and a cover for protecting the sensor, the cover being removably mounted and held on the fuselage by at least one retaining member arranged to retain the cover against aerodynamic forces exerted on the cover during flight. The aerial vehicle includes a member for deactivating the retaining member and an electronic control circuit arranged to control the deactivation member in flight to allow the cover to be ejected.