Projectile Fin Deployment via Centrifugal and Aerodynamic Forces
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Solution Overview
Problem
Existing projectile systems require complex and fault-prone mechanisms, such as springs or active drive elements, to deploy fins for stabilization during flight, which increase costs and susceptibility to malfunctions.
Innovation Solution
The use of centrifugal and aerodynamic forces generated by the projectile's spin and flight through air to rotate and deploy fins, eliminating the need for additional drive elements, with fin designs optimized for aerodynamics and geometric fit to enhance this process.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If springs or active drive elements are used to deploy fins, then the fins can be reliably deployed, but the device complexity and cost increase
Solution Approach 1:
The fin deployment mechanism utilizes the projectile's own rotational motion and aerodynamic forces to deploy the fins, eliminating the need for separate drive elements. The centrifugal force generated by rotation and aerodynamic pressure during flight automatically push the fins from a folded to a deployed position, making the system self-actuating and reducing mechanical complexity.
Solution Approach 2:
The patent replaces traditional mechanical spring-based deployment systems with a combination of centrifugal force and aerodynamic pressure. This substitution eliminates complex mechanical components like torsion springs and drive mechanisms, using instead the natural physical forces present during projectile flight to achieve fin deployment.
2Ease of operation
If springs or active drive elements are used to deploy fins, then the fins can be deployed, but the susceptibility to malfunctions increases
Solution Approach 1:
The system uses the projectile's inherent rotational motion and aerodynamic environment to deploy fins, eliminating vulnerable mechanical components that could fail. By relying on self-service forces (centrifugal and aerodynamic), the system reduces points of failure associated with springs, motors, or other active drive elements.
3Ease of manufacture
If fins are deployed using traditional mechanisms, then deployment is achieved, but costs increase
Solution Approach 1:
The patent extracts and eliminates unnecessary drive mechanism components from the fin deployment system. By removing springs, motors, and other active elements, the design reduces both material quantity and manufacturing complexity, retaining only the essential hinge connections and fin structures.
4Device complexity
If centrifugal and aerodynamic forces are used for fin deployment, then the design is simplified, but the projectile must achieve sufficient spin and flight speed
Solution Approach 1:
The projectile is given rotational motion during the loading or launch process, preparing the system for fin deployment before flight begins. This preliminary action ensures that sufficient centrifugal force is available from the start of flight to initiate fin deployment, eliminating the need for complex trigger mechanisms.
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
This approach simplifies the projectile design, reduces the risk of mechanical failures, and lowers costs by leveraging inherent forces for fin deployment, ensuring reliable flight stabilization without additional components.
Implementation Method 1
The force is exclusively a centrifugal force acting on the fin, caused by its spin and intrinsic mass
Implementation Method 2
the force is an aerodynamic force acting on the fin, caused by the air flowing towards or past the fin during the projectile's flight
Data Source
Figure 1
Figure 2~3
Figure 4
AI summary
In a projectile section (2) as at least part of a projectile (6) as intended, with a projectile body (8) extending along a central longitudinal axis (10) of the projectile (6), which, in the case of a projectile (6) in its intended flight after its launch, has a spin (16) about the central longitudinal axis (10), with at least one fin (18) which is rotatably mounted on the projectile body (8) about an axis of rotation (20) between a launch position (A) adjacent to the projectile body (8) and a flight position (F) projecting from the projectile body (8), wherein the axis of rotation (20) extends in the direction of the central longitudinal axis (10), wherein, in the flight of the projectile (6), a force (K) is generated which causes a rotational movement (22) of the fin (18) from the launch position (A) to the flight position (F) about the axis of rotation (20),The force (K) is not caused by the relaxation of a pre-stressed spring or by an electrically, pneumatically, hydraulically, or detonatively operated active drive element in the projectile (6). A projectile (6) contains a projectile section (2). In a method for generating the force (K) on the projectile section (2), the force (K) is not caused by the relaxation of a pre-stressed spring or by an electrically, pneumatically, hydraulically, or detonatively operated active drive element in the projectile (6).