Projectile Guiding Fin Assembly With Adaptive Pitch Control
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Solution Overview
Problem
Existing projectile guiding kits face challenges in balancing cost and accuracy, as high-cost kits dissipate less kinetic energy but are inefficient, while low-cost kits dissipate more energy, shortening the projectile's range and reducing accuracy due to fixed fin angles that fail to adapt to changing flight parameters.
Innovation Solution
A guiding fin assembly with pivotally connected fins and adjustable pitch angles, controlled by relative speed control units and springs, allowing for dynamic adjustment of aerodynamic forces and torque to maintain stability and accuracy across varying flight conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If fixed angle fins are used in low-cost guiding kits, then cost is reduced, but energy dissipation increases and accuracy deteriorates
Solution Approach 1:
The fin assembly incorporates pivotally connected fins that can dynamically adjust their pitch angles during flight. The relative speed control units and springs enable the fins to automatically adapt to changing flight parameters (airspeed and density), transforming the static fin structure into a dynamic one that optimizes aerodynamic performance throughout the trajectory, thereby reducing energy dissipation while maintaining low cost.
Solution Approach 2:
The invention changes the pitch angle parameter of the fins dynamically during flight. By using springs and relative speed control units, the system automatically adjusts the fin angles to match changing airspeed and density conditions, optimizing the balance between lift and drag at different phases of flight, which reduces overall energy dissipation.
2Device complexity
If fixed angle fins are used, then device complexity is reduced, but adaptability to changing flight parameters deteriorates
Solution Approach 1:
The fin assembly is designed to automatically adapt to changing flight conditions without external control systems. The springs and relative speed control units create a self-regulating mechanism where the fins naturally adjust their angles in response to aerodynamic forces and speed changes, providing adaptability through passive self-adjustment rather than active control.
Solution Approach 2:
The pivotally connected fins create a dynamic structure that passively responds to flight conditions. As airspeed and density change during trajectory, the aerodynamic forces on the fins cause them to naturally adjust their pitch angles, providing continuous adaptation to varying flight parameters without adding complex control systems.
3Reliability
If high anti-rotational power is provided at trajectory beginning, then spin control is improved, but energy dissipation increases
Solution Approach 1:
The relative speed control mechanism provides spin control in a periodic or phased manner rather than continuously at maximum power. The springs and controllable units adjust the anti-rotational power delivery to match the actual needs at different trajectory phases, providing high power when needed (initial spin control) and reducing power as flight progresses, thereby minimizing overall energy dissipation.
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 solution provides a cost-effective and accurate guiding system that maintains consistent torque and lift, reducing energy dissipation and extending the projectile's range by dynamically adjusting fin angles to match changing airspeed and density, thereby improving the CEP and cost ratio.
Implementation Method 1
two return springs, each spring being operably connected to a respective guiding fin, wherein said springs are configured to allow movement correspondingly to aerodynamic pressure on said fins
Implementation Method 2
a relative speed control unit operable between said rear main unit and said front main unit and capable of providing spin braking force to slow the relative speed of rotation
Data Source
Figure 1A~1D
Figure 2A~2C
Figure 3
AI summary
A guiding assembly is adapted to be connected to a projectile and comprising a rear main unit adapted to be connected to the front end of the projectile, and a front main unit rotatably connected at its rear end to the front end of the rear main unit. The front main unit is adapted to rotate about a central longitudinal axis. A relative speed control unit is operable between the rear main unit and the front main unit and capable of providing spin braking force to slow the relative speed of rotation of the front main unit. An at least one guiding fin radially extends from the front main unit. The pitch angle of the fin is controllable by a return spring connected to the fin so that the pitch angle of the fin is growing as the aerodynamic pressure on the fin lowers and it is growing smaller as the aerodynamic pressure on the fin gets bigger.