Landing Gear Breaker Strut with Integrated Linear Actuator
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current aircraft landing systems with counterfeits require complex and bulky devices using multiple actuators to stabilize and retract the landing gear, which complicates the activation sequence and increases weight.
Innovation Solution
A simplified aircraft landing system with a broken counterfeit design, where a single linear actuator integrated into one of the counterfeit elements allows for both stabilization and retraction, eliminating the need for additional articulations and using a sliding rod to align and retract the landing gear.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple actuators are used to unlock and retract the landing gear, then the landing gear can be stabilized and retracted, but the device becomes complex and bulky
Solution Approach 1:
The patent combines the functions of the release actuator and control actuator into a single linear actuator. This single actuator performs both the unlocking function (moving the strut from aligned to broken position) and the retraction function (raising the landing gear), thereby reducing the number of components and simplifying the overall device while maintaining reliable operation
Solution Approach 2:
The single linear actuator is designed to perform multiple functions: it acts as both the release actuator (unlocking the strut) and the control actuator (retracting the landing gear). This multi-functional design eliminates the need for separate actuators and reduces system complexity while ensuring both stabilization and retraction capabilities
2Ease of operation
If multiple actuators and additional articulations are used, then the landing gear can be controlled, but the weight and bulk increase
Solution Approach 1:
By merging the release actuator and control actuator into a single linear actuator unit, the patent significantly reduces the weight of the moving components. The integrated design eliminates redundant parts, connections, and articulations that would otherwise add weight, while maintaining full control capability over the landing gear operation
Data Source
Figure 1
Figure 2
Figure 3
AI summary
The invention relates to an aircraft landing gear (100) comprising a leg (1) intended to be mounted on a structure of the aircraft so as to be able to move between a deployed position and a retracted position, the landing gear being provided with a breaker strut (2) comprising two articulated elements (2A, 2B) therebetween at a knee, with a first element (2A) intended to be coupled to the structure of the aircraft and a second element (2B) intended to be coupled to the landing gear, a return member (12) being arranged between the two elements and returning them to a substantially aligned position defined by respective end stops (11A, 11B). According to the invention, one of the elements of the strut includes a linear actuator (4) comprising a sliding rod (7) which is coupled to the other element of the strut by means of a link rod (9), the entire assembly being arranged such that movement of the sliding rod of the actuator in a single direction successively breaks the alignment of the elements of the strut and moves the landing gear from the deployed position to the retracted position. Drawing_references_to_be_translated