Portable Missile Ejection Device Separation Mechanism
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Solution Overview
Problem
Existing separation devices for portable missiles are either complex and expensive or cause excessive impulsive shock to the gunner due to their mechanical structure, and they require additional propellant and ignition systems, which is undesirable for weight and safety reasons.
Innovation Solution
A separable ejection device with a simplified structure that uses a piston unit and combustion pipes to generate a cutting force for shearing bolts, eliminating the need for additional separation devices and minimizing weight and space, while also using a spring connection to prevent premature separation from environmental shocks.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a PAD (Propellant Actuated Device) is used for separation, then the ejection system can be separated from the missile, but the device becomes very complicated and expensive, and requires additional gunpowder and ignition system
Solution Approach 1:
The patent combines the ejection function and separation function into a single integrated device. The ejection rocket motor serves dual purposes: propelling the missile during ejection and providing combustion gas to drive the piston for separation. This eliminates the need for separate PAD components, additional gunpowder, and ignition systems, thereby reducing structural complexity while maintaining reliable separation functionality
Solution Approach 2:
The ejection rocket motor is designed to perform multiple functions: (1) generate thrust for missile ejection, (2) provide combustion gas for piston-driven separation, and (3) serve as the separation actuator itself. This multi-functionality eliminates the need for dedicated separation components, resolving the contradiction between achieving separation reliability and reducing device complexity
2Device complexity
If mechanical components are used for separation by interfering with the launch tube, then the structure is simple, but the gunner receives excessive impulsive shock
Solution Approach 1:
The patent replaces traditional mechanical interference-based separation with a pneumatic system. Instead of using mechanical components that physically interfere with the launch tube and generate shock, the invention uses combustion gas pressure acting on a piston to drive the separation. This substitution of mechanical system with a controlled pneumatic system reduces impulsive shock to the gunner while maintaining structural simplicity
Solution Approach 2:
The separation mechanism uses pneumatic pressure from combustion gas to drive the piston, which in turn separates the ejection device from the missile. This pneumatic approach provides controlled, gradual separation force rather than sudden mechanical impact, eliminating excessive shock to the gunner while keeping the device structure simple
3Reliability
If additional separation devices are used, then the separation function is achieved, but the missile weight and space increase
Solution Approach 1:
The patent merges the ejection rocket motor with the separation mechanism into a single integrated device. The same combustion chamber and nozzle that provide ejection thrust also generate the combustion gas needed to drive the separation piston. This integration eliminates the need for additional separation devices, gunpowder, and ignition systems, thereby reducing missile weight and space while ensuring reliable separation function
Solution Approach 2:
The separation mechanism components (piston, combustion chamber, nozzle) are nested within the ejection rocket motor structure. The piston is positioned inside the combustion chamber, and the entire separation mechanism is contained within the ejection device housing. This nested arrangement minimizes the space occupied by separation components and reduces overall missile weight
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 device enables both ejection and separation of the missile without additional devices, reducing weight and space, minimizing recoil force, and allowing ejection in confined spaces by reducing the exhaust plume length, thus enhancing safety and efficiency.
Implementation Method 1
configured to provide an external force for cutting off the shearing bolts by a pressure generated by a part of the combustion gas
Implementation Method 2
a combustion chamber and a nozzle for discharging combustion gas generated from the combustion chamber
Implementation Method 3
a spring compression-supported between the end of the connection ring and the supporting member, and configured to provide an elastic force to the frame unit toward the missile
Implementation Method 4
a combustion chamber and a nozzle for discharging combustion gas generated from the combustion chamber
Implementation Method 5
capable of ejecting a missile and then being separated from the missile
Data Source
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AI summary
Disclosed is a separation device (100) of an ejector motor (130) for a portable missile (1), capable of being separated from a missile (1) without any additional separation devices after ejecting the missile (1). An ejection rocket motor (130) and a separation device are integrally formed. Ejection is performed by a thrust generated while the ejection rocket motor (130) is combusted, and separation is performed by cutting off shearing bolts (113) with using a force generated from a separation cylinder (141) when the combustion of the ejection rocket motor (130) has been completed. This operation and configuration may minimize a weight and a space occupied by a general ejection and separation device (100) in a missile system.