Missile Folding Wing Self-Locking Mechanism
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Solution Overview
Problem
Existing folding wing designs for missiles are not mechanically robust, reliable, and simple enough, and lack adaptability to different missile types, often requiring complex mechanisms and additional securing devices to prevent unfolding during flight.
Innovation Solution
A folding wing design featuring a wing root with a receiving groove and an elastically pre-stressed force element, combined with a guiding device, which ensures the upper wing part is securely folded into a working position without additional securing mechanisms, utilizing materials like precision extrusion and 3D printing for manufacturing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If complex mechanisms with additional securing devices are used to prevent unfolding during flight, then reliability is improved, but device complexity increases
Solution Approach 1:
The folding wing mechanism is designed to be self-securing through the interaction between the profile foot and the receiving groove. The geometric design of these components automatically prevents unfolding during flight without requiring additional securing devices or complex mechanisms. The system serves itself by using the structural interaction between existing components to achieve the securing function.
Solution Approach 2:
The folding wing is divided into distinct functional segments: the wing root with the receiving groove and the upper wing part with the profile foot. This segmentation allows each component to perform its specific function independently, with the profile foot engaging with the receiving groove to provide automatic securing without needing additional complex mechanisms.
2Reliability
If additional securing devices are added to prevent unfolding, then reliability is improved, but manufacturing complexity increases
Solution Approach 1:
The securing function is achieved through the self-interaction of the profile foot and receiving groove components. This eliminates the need for additional securing devices that would require separate manufacturing processes, assembly steps, and quality control procedures, thereby simplifying manufacturing while maintaining reliability.
Solution Approach 2:
The securing function is merged into the existing structural components (profile foot and receiving groove) rather than being added as a separate system. This integration reduces the total number of parts and manufacturing operations required, making the system easier to manufacture while achieving the same reliability goal.
3Device complexity
If a mechanically simple folding mechanism is used, then device complexity is reduced, but reliability may worsen
Solution Approach 1:
The simple folding mechanism achieves high reliability through self-service functionality. The profile foot and receiving groove are designed to automatically engage and secure the upper wing part during folding and deployment, eliminating the need for complex securing devices while maintaining secure storage and deployment through the inherent geometric interaction of the components.
4Reliability
If complex mechanisms are used to ensure reliable folding, then reliability is improved, but adaptability to different missiles decreases
Solution Approach 1:
The folding mechanism is designed with universal applicability through the standardized interaction between the profile foot and receiving groove. This geometric design can be adapted to different missile types without requiring complex reconfiguration, as the core securing mechanism remains the same. The system provides reliable folding functionality that can be universally applied across different missile platforms.
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 design achieves a mechanically simple, reliable, and lightweight folding mechanism that automatically deploys the upper wing part into a working position, ensuring secure storage and deployment without the risk of unfolding during flight, leveraging material properties and geometric leverages for self-locking.
Implementation Method 1
an elastically pre-stressed force element (48), which is coupled with the wing root (4) and the upper wing part (6) and urges the upper wing part (6) into the receiving groove (12) through the pre-stress
Data Source
AI summary
A folding wing comprises a wing root, an upper wing part foldable relative to the wing root, at least one guiding device, and an elastically pre-stressed force element. The upper wing part comprises an end edge and a profile foot, wherein the wing root comprises a base and an opposing receiving groove, which is designed to receive the profile foot in a flush manner and is delimited by two delimiting edges having a separation distance that at least equals the maximum profile thickness of the profile foot. The guiding device is arranged at one of the upper wing part and the wing root and is designed for guiding the profile foot in a variable distance to the ground of the receiving groove. The force element is coupled with the wing root and the upper wing part and urges the upper wing part into the receiving groove through the pre-stress.