Aircraft Peripheral Assembly Breakaway Mechanism for Collision Damage

Resolve Bottlenecks,
Find Innovative Solutions
Generate Solutions

Solution Overview

Problem

Aircraft components that protrude or extend from the surface are prone to catastrophic failure upon collision, requiring substantial repair resources and design constraints for collision avoidance.

Innovation Solution

Incorporation of a breakaway mechanism that allows peripheral assemblies, such as sensor probes, to detach from the aircraft upon receiving a threshold force, maintaining the integrity of the main structure and enabling controlled operation and easy replacement.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Strength

If peripheral assemblies are rigidly connected to the aircraft, then structural strength is improved, but collision damage resistance deteriorates

Engineering Contradiction:
Improvestructural strengthVSAvoidcollision damage
Core Design Contradiction:
StrengthVSObject-affected harmful factors

Solution Approach 1:

The aircraft structure is divided into a main body and detachable peripheral assemblies. The peripheral assemblies (sensors, antennas, etc.) are connected through breakaway mechanisms that allow them to separate upon collision, preventing damage propagation to the main aircraft structure.

Inventive Principle:
Principle #1Segmentation

Solution Approach 2:

The vulnerable peripheral components are extracted as separate, detachable assemblies from the main aircraft structure. These assemblies can be removed or broken away independently, isolating them from the critical aircraft systems and preventing catastrophic failure.

Inventive Principle:
Principle #2Taking out (Extraction)

2Object-affected harmful factors

If peripheral assemblies are made detachable, then collision damage resistance is improved, but connection reliability deteriorates

Engineering Contradiction:
Improvecollision damageVSAvoidconnection reliability
Core Design Contradiction:
Object-affected harmful factorsVSReliability

Solution Approach 1:

The connection mechanism transitions from a static rigid connection to a dynamic breakaway connection. The connecting features are designed to maintain a secure connection during normal operation but automatically release when subjected to collision forces exceeding a predetermined threshold.

Inventive Principle:
Principle #15Dynamics

Solution Approach 2:

The connection strength parameter is designed to change based on applied force. During normal operation, the connection maintains high strength for reliable attachment. Upon collision, the connection force drops to zero as the breakaway mechanism activates, allowing separation.

Inventive Principle:
Principle #35Parameter changes

3Ease of repair

If breakaway mechanisms are incorporated, then ease of repair is improved, but device complexity increases

Engineering Contradiction:
Improverepair efficiencyVSAvoidmechanism complexity
Core Design Contradiction:
Ease of repairVSDevice complexity

Solution Approach 1:

The peripheral assemblies with breakaway mechanisms are designed as replaceable units. Rather than repairing complex mechanisms, the entire peripheral assembly can be quickly removed and replaced with a new one, simplifying the repair process and reducing downtime.

Inventive Principle:
Principle #27Cheap short-living objects (Disposable)

Solution Approach 2:

The design allows for the controlled discarding of peripheral assemblies that have experienced collision damage. The breakaway mechanism ensures clean separation, and the detached assemblies can be recovered, inspected, and replaced as needed, improving operational efficiency.

Inventive Principle:
Principle #34Discarding and recovering

Data Source

PatentUS12365482B2Structures to limit collision damage for aircraft
Publication Date: 2025.07.22 SCI APPL & RES ASSOCS
  • US12365482B2 patent drawing
  • US12365482B2 patent drawing
  • US12365482B2 patent drawing

AI summary

Described herein is an aircraft. The aircraft includes a peripheral assembly, such as a sensor probe. The aircraft further includes a release assembly connecting the peripheral assembly to a portion of the aircraft. The release assembly is configured to separate the peripheral assembly and the portion upon receipt of a threshold force. The release assembly may be configured to allow for the quick release, such as via a snap-fit connection, between the peripheral assembly and the portion of the aircraft.