Grounding Sabot with Expanding Deflector for Low-Drag Perforation
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Solution Overview
Problem
Conventional perforation systems are inefficient in transferring propellant ignition forces to projectiles and suffer from aerodynamic drag, leading to reduced kinetic energy and perforation effectiveness.
Innovation Solution
A grounding sabot with conductive components, including a body, divider, ignition pass through, ground terminal, deflector, gas valve, and compensator, that enhances force transfer and minimizes aerodynamic drag, allowing for higher projectile velocities and kinetic energies.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If conventional perforation systems are used, then the structure is simple and easy to manufacture, but the force transfer from propellant ignition to projectile is inefficient
Solution Approach 1:
The sabot is divided into multiple functional segments including a driver section with gas ports, a transition section, and a nose section. This segmentation allows each portion to perform its specific function optimally - the driver section manages propellant gas flow, the transition section ensures smooth aerodynamic transition, and the nose section provides streamlined projectile engagement, collectively improving force transfer efficiency.
Solution Approach 2:
The sabot acts as an intermediary component between the propellant charge and the projectile. It receives the impulsive force from propellant ignition and efficiently transfers it to the projectile through its specially designed interface and aerodynamic shape, serving as a mediator that optimizes the energy transfer process.
2Speed
If conventional projectiles are used, then manufacturing is simpler, but aerodynamic drag reduces velocity and kinetic energy
Solution Approach 1:
The sabot and projectile feature streamlined, curved aerodynamic contours rather than sharp edges or flat surfaces. The nose section of the sabot and the projectile body incorporate rounded transitions that reduce flow separation and minimize pressure drag, allowing the projectile to cut through air with less resistance and maintain higher velocities.
3Use of energy by moving object
If conventional perforation systems are used, then the system is simpler, but kinetic energy available for perforation is reduced
Solution Approach 1:
The sabot incorporates dynamic features including expandable or flexible elements that adapt during flight, and aerodynamic surfaces that optimize performance at different velocity regimes. These dynamic characteristics allow the system to maximize kinetic energy transfer to the projectile while maintaining stability throughout the perforation process.
Solution Approach 2:
The system utilizes parameter changes in the propellant charge configuration, sabot mass distribution, and projectile geometry to optimize kinetic energy generation. By carefully controlling these parameters, the system achieves maximum energy transfer from the chemical energy of the propellant to the kinetic energy of the projectile, enhancing perforation capability.
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 sabot ensures efficient energy transfer and reduced drag, resulting in improved perforation capabilities and reliability by maintaining higher velocities and kinetic energies of projectiles.
Implementation Method 1
a deflector having a cup-shaped configuration that is partly defined by a bottom portion of the divider, and the deflector is configured to expand diametrically upon ignition of a propellant in the propellant chamber
Implementation Method 2
an ignition stack electrically connected to the ignition pass through
Data Source
AI summary
A sabot that includes a body configured to be partly received within a propellant chamber of a perf gun, and the body includes an interface configured to engage a projectile, a divider that defines part of the interface, an ignition pass through that extends through the divider, an ignition stack electrically connected to the ignition pass through, a ground terminal electrically connected to the ignition pass through, a deflector defined by the divider and having a cup-shaped configuration, and the deflector is configured to expand diametrically upon ignition of a propellant in the propellant chamber when the sabot is positioned within the propellant chamber, a gas valve configured and arranged to be actuated by expansion of the deflector, and a compensator positioned between the interface and the gas valve.