Single-Actuator Wing Deployment Mechanism for Glide Bombs
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Solution Overview
Problem
Existing wing deployment mechanisms for glide bombs and missiles are inefficient in terms of aerodynamic performance and storage space, as they often require long, slender wings that take up significant space and do not allow for optimal-length wings, leading to suboptimal performance and accuracy in targeting.
Innovation Solution
A wing deployment system using a single actuator that combines rotation and axial movement to deploy wings symmetrically and externally, freeing up fuselage space for additional fuel or payload, while minimizing aerodynamic disturbance and maintaining compact size and efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Length of moving object
If long, slender wings are used to increase glide distance, then flight distance is improved, but storage space in the bomb deployment racks increases significantly
Solution Approach 1:
The wing mechanism is nested within the fuselage structure, with wings stored in a compact configuration inside the bomb body and deployed outward when needed. This allows long wings to be accommodated during storage without increasing the overall volume significantly, as the wings are integrated into the existing fuselage space rather than requiring separate external storage volume.
Solution Approach 2:
The deployment mechanism transitions wings from a three-dimensional extended configuration during flight to a two-dimensional flat configuration during storage, folding the wings along the fuselage. This dimensional transformation allows the wings to occupy minimal space in the storage state while maintaining their full length and aerodynamic performance when deployed.
2Volume of moving object
If wings are folded along the fuselage for storage, then storage space is reduced, but aerodynamic performance and optimal wing positioning are compromised
Solution Approach 1:
The wing mechanism incorporates a deployable and storable configuration system that allows the wings to transition between a compact folded state during storage and a fully extended aerodynamic state during flight. The mechanism includes pivot points and support structures that enable smooth transformation between these states, ensuring optimal aerodynamic performance when deployed while maintaining compact storage when not in use.
Solution Approach 2:
The wing mechanism is divided into segmented sections that can be independently positioned and folded along the fuselage. This segmentation allows the wings to be stored in a compact configuration that minimizes volume while maintaining the ability to deploy each section to its optimal aerodynamic position when needed, thus resolving the contradiction between storage compactness and aerodynamic performance.
3Manufacturing precision
If multiple actuators are used to deploy wings symmetrically, then deployment precision is improved, but device complexity and part count increase
Solution Approach 1:
Multiple deployment functions are merged into a single integrated actuator mechanism that controls both wings symmetrically. The unified actuator system coordinates the deployment of left and right wings through a common control architecture and mechanical linkage, achieving precise symmetric deployment without requiring separate actuators for each wing, thus reducing overall system complexity while maintaining deployment precision.
Solution Approach 2:
The actuator mechanism is designed with multi-functional capability, serving both as a deployment actuator and a positioning control mechanism. This universal design allows a single actuator to perform multiple functions including wing deployment, symmetric positioning, and precision control, eliminating the need for additional specialized actuators and reducing the overall part count while maintaining high deployment precision.
Data Source
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AI summary
A deployment system, such as for deploying wings (14, 16), includes a pair of hub assemblies (34, 36) that transmit linear motion provided by an actuator (40) into a combination of rotational and axial motion. The actuator (40) works on both hub assemblies, rotating (for each wing) a slew ring (162, 164) that is coupled to a lift bar (121) that acts as a follower, following a pair of cam slots (90), to allow the wings to follow their desired course. In one embodiment the wings (14) move axially away from a fuselage (20) at the beginning of the deployment movement, followed by a primarily rotational movement, with the wings pulling in toward the fuselage at the end of the deployment process. The actuator includes a pair of threaded shafts (threaded in opposite directions) that rotate along with a pinion gear, driven by a motor (202), to translate a pair of retractor links (206, 208) that are coupled to the slew rings.