Mortar Projectile Propellant Optimization for Extended Range
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Solution Overview
Problem
Current weapon equipment, such as the Fly-K mortar, has a limited range of 650 m and requires modifications to the projectile and propellant charge to increase range, which can compromise the launcher's integrity and operator safety.
Innovation Solution
Increasing the propellant charge mass to between 2.4 g and 3.7 g, with a loading density of 0.9 g/cm³, while maintaining a constant loading density, and optimizing the piston's recess volume to enhance the projectile's range without damaging the launcher or risking operator safety.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Length of moving object
If the propellant charge mass is increased to increase the range, then the range is improved, but the launcher integrity and operator safety deteriorate
Solution Approach 1:
The patent applies parameter changes by precisely controlling the propellant charge mass within the range of 2.4 g to 3.7 g and optimizing the recess volume in the piston, allowing the range to be extended to 1000 m while maintaining launcher integrity and operator safety through optimized physical parameters rather than structural modifications
Solution Approach 2:
The patent introduces a recess in the piston with optimized volume to create localized propellant concentration, allowing the propellant charge to be concentrated in a specific region (the recess) rather than uniformly distributed, which enables increased range while controlling pressure distribution to protect launcher integrity
2Length of moving object
If the propellant charge mass is increased, then the range is improved, but the propellant liveliness must be reduced
Solution Approach 1:
The patent maintains propellant liveliness by changing the parameter of charge mass distribution through the recess design, allowing the use of high-liveness propellant (heat of combustion 3500-4000 J/g) with optimized mass (2.4-3.7 g) rather than reducing liveliness, thus achieving extended range while preserving propellant performance characteristics
3Length of moving object
If the propellant charge mass is increased, then the range is improved, but the launcher structure must be modified
Solution Approach 1:
The patent segments the propellant charge into two functional zones: propellant placed in the recess of the piston and additional propellant in the propulsion chamber, allowing the existing launcher structure to be used without modification while achieving extended range through optimized propellant distribution in segmented regions
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 allows for a significant increase in the range of the weapon equipment up to 1000 m, maintaining effectiveness and safety, by increasing the propellant charge alone, without altering the launcher or reducing the propellant's liveliness.
Implementation Method 1
a propulsion charge placed in the propulsion chamber when the piston is at the first location and activatable by the primer of the piston to move the piston resting on the bearing surface of the free end of the launch rod from the first location towards the second location, the propellant charge comprising a powder having a heat of combustion of between 3500 J/g and 4000 J/g
Implementation Method 2
This provisions make it possible to contain the flame and the fumes resulting from the ignition of the propulsion charge inside the hermetically closed propulsion chamber
Data Source
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AI summary
Armament equipment comprising a launcher and a projectile (25), the projectile (25) having a weight between 750 g and 1000 g, the projectile (25) comprising a warhead (26) and a tail (40), the tail (40) comprising: - an aluminum alloy tube (41) having an internal diameter (Di) between 21.5 mm and 22.5 mm, a stroke (c) between the first (E1) and second (E2) positions between 110 mm and 120 mm, and a thickness (e) in the vicinity of the first position (E1) between 4.6 mm and 5 mm, - a piston (60) movable between the first (E1) and second (E2) positions and defining with the tube (41) a hermetically sealed propulsion chamber (65), - a propellant charge (70) placed in the propulsion chamber (65), the propellant charge (70) comprising a powder having a heat of combustion between 3500 J/g and 4000 J/g, the propellant charge (70) having a mass strictly greater than 2.4 g and less than 3.7 g.