Full Caliber Projectile with Ogival Tip and Folding Tail
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Solution Overview
Problem
Long-range anti-tank projectiles face challenges in achieving high payload volume, stable flight behavior, and low speed loss while maintaining accuracy, especially when fired from smoothbore guns, due to manufacturing deviations and sensitivity to disturbances.
Innovation Solution
A wing-stabilized, full-caliber projectile design combining shape stabilization, ogival tip contour, and a folding mechanism, featuring a sub-caliber spike for initial stability, ogival tip for payload volume, and a folding tail unit for aerodynamic stability, with a cylindrical body and progressively decreasing diameter to minimize velocity drop and flow resistance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If a full-caliber ogival projectile is used to maximize payload volume, then the payload capacity is improved, but the projectile becomes sensitive to disturbances and loses speed due to low stability
Solution Approach 1:
The projectile is divided into functionally distinct segments: a cylindrical body for payload, an ogival tip for aerodynamic efficiency, and a separate tail unit with wings for stabilization. This segmentation allows each part to optimize its specific function without compromising the others.
Solution Approach 2:
The tail unit with wings is designed to be dynamically deployed during flight. The wings can be folded during launch and then unfolded in flight to provide stabilization, allowing the projectile to transition from a compact launch configuration to a stabilized flight configuration.
2Reliability
If wing stabilization is used to improve flight stability, then the stability is improved, but the device complexity increases due to folding mechanisms
Solution Approach 1:
The stabilization system is segmented into modular components (tail unit, wings, folding mechanism) that can be independently optimized. This modularity reduces overall complexity by allowing each component to perform a specific function with minimal interference from other parts.
Solution Approach 2:
The folding mechanism transforms the rigid tail unit into a dynamic structure that adapts its configuration during flight. The wings are folded during launch to minimize interference with the barrel and then deployed in flight to provide stabilization, reducing complexity at each stage.
3Device complexity
If a rigid tail unit is used to simplify the structure, then the device complexity is reduced, but the available space for payload is limited
Solution Approach 1:
The tail unit transitions from a compact folded state during launch to an extended deployed state during flight. This dynamic transformation allows the payload compartment to maximize its volume during loading and transport, while the tail unit provides full stabilization functionality during flight.
Solution Approach 2:
The wings are nested within or alongside the cylindrical body during the launch phase, utilizing the available space efficiently. When deployed, the wings extend outward without requiring additional overall length, maximizing payload volume while maintaining stabilization capability.
4Speed
If the projectile diameter is reduced to minimize flow resistance, then the velocity maintenance is improved, but the payload volume decreases
Solution Approach 1:
The projectile features different diameters in different sections: a full-caliber cylindrical body for maximum payload volume, and a reduced-diameter ogival tip for minimized flow resistance. This local variation in geometry allows the projectile to maximize payload capacity while maintaining velocity through the aerodynamically optimized nose section.
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 ensures accurate and stable flight over distances greater than 2500 meters with minimal speed loss and enhanced aerodynamic stability, outperforming previous solutions by reducing velocity drop and maintaining stability during unfolding.
Implementation Method 1
a folding mechanism ensures aerodynamic stability even with decreasing projectile speeds
Implementation Method 2
The adjoining ogival tip area ensures sufficient payload volume and low speed loss
Data Source
AI summary
A long range large caliber tank shell (1) comprises a cylindrical body (2) with a primary section (11), a secondary section (12) at the front, a spike shaped tip (7), and a contact surface (8). The rear has a guide member. The outer diameter of the contact surface is smaller than the shell caliber.