Projectile Fin Deployment Mechanism for Reliable Stabilization
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Solution Overview
Problem
Existing projectile stabilization systems face challenges in reliable fin deployment due to aerodynamic forces and complexity, leading to potential malfunctions and incomplete deployments, especially when the projectile is inclined during flight.
Innovation Solution
A projectile with a wing or fin deployment device featuring a two-phase deployment mechanism, where wings or fins rotate from a tangential to a semi-deployed position around a perpendicular axis and then to a deployed position around a parallel axis, synchronized by a toothed wheel mechanism, driven by a single control engine and compression springs, ensuring reliable stabilization regardless of trajectory.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a complex deployment mechanism with multiple components (cams, springs, hinges) is used to deploy fins, then the fin deployment can be achieved, but the device complexity increases and reliability decreases due to potential malfunctions
Solution Approach 1:
The deployment mechanism is segmented into distinct functional components: a rotation engine for initiating movement, compression springs for providing deployment force, and cam mechanisms for guiding the two-phase rotation. This segmentation allows each component to be optimized independently and simplifies the overall system by breaking down the complex deployment process into manageable stages.
Solution Approach 2:
The mechanism employs dynamic elements including a rotation engine that can be activated at different flight phases, compression springs that dynamically adjust force during deployment, and cam profiles that dynamically guide the fin through two distinct rotation phases. This dynamic approach allows the system to adapt to varying aerodynamic conditions while maintaining reliability.
2Device complexity
If the fin deployment depends on projectile inclination and aerodynamic forces, then the deployment mechanism is simplified, but the deployment becomes unreliable when the projectile is inclined during flight
Solution Approach 1:
The rotation engine performs preliminary action by actively rotating the fin to a predetermined deployment angle before aerodynamic forces take full effect. This preliminary rotation ensures that the fin is properly positioned regardless of the projectile's inclination, making the deployment reliable without requiring complex inclination-sensing mechanisms.
Solution Approach 2:
The cam mechanism acts as an intermediary between the rotation engine and the fin, translating the engine's rotational output into the desired two-phase deployment motion. This intermediary ensures consistent deployment geometry independent of external aerodynamic variations, bridging the gap between simple actuation and reliable deployment.
3Reliability
If fins have larger surface area during deployment phase, then stabilization is improved, but aerodynamic constraints increase making deployment more difficult
Solution Approach 1:
The deployment occurs in two distinct periodic phases: first a rotation phase where the fin moves to an intermediate position, then a deployment phase where it reaches full extension. This periodic action allows the system to manage aerodynamic forces in stages, reducing peak constraints while achieving full stabilization benefit.
Solution Approach 2:
The cam mechanism dynamically adjusts the deployment trajectory, allowing the fin to follow an optimized path that minimizes aerodynamic resistance during deployment. The dynamic motion profile ensures that the fin transitions smoothly through high-stress regions, reducing peak aerodynamic constraints while still achieving full deployment for optimal stabilization.
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 provides a lightweight, reliable, and synchronized fin deployment system that improves flight characteristics and stabilization by counteracting aerodynamic forces, reducing the risk of malfunctions and ensuring complete deployment of wings or fins.
Implementation Method 1
at least one compression spring arranged between said lower wall and said piston
Implementation Method 2
said rotation of said wing or fin around said axis parallel to the longitudinal axis driving a toothing which meshes with a synchronizing toothed wheel arranged in a circular groove coaxial with the central chamber
Data Source
AI summary
The present invention relates to a projectile including a body having a longitudinal axis and an intermediate portion comprising a wing or fin deployment device including at least a number N, at least equal to three, of wings or fins able to be deployed, the deployment method comprising at least two phases, a first deployment phase in which each wing or fin switches from a position tangential to the body of the projectile and parallel to the longitudinal axis to a semi-deployed position, and a second deployment phase with the switching of each wing from the semi-deployed position to a deployed position in which it is perpendicular to the body of the projectile, said wing deployment device is configured to synchronize the deployment of wings or fins in the second phase.