Missile Ejection System Gas Generator Canister Design
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Solution Overview
Problem
Existing missile launching systems risk damaging ground equipment and peripheral missiles due to high temperature and pressure flames from missile propulsion engines, and suffer thrust loss during initial launch when using propulsion engines.
Innovation Solution
A missile ejection system that uses a gas generator to propel the missile from a canister without a propulsion engine, featuring a cylindrical canister with a partition wall, obturator, and guides to prevent damage to ground equipment and reduce friction, and is manufactured using a combination of tubes for ease of assembly and handling.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If a missile propulsion engine is used to release the missile from the canister, then the missile can be launched with sufficient thrust, but ground equipment and peripheral missiles may be damaged by high temperature and pressure flames
Solution Approach 1:
The harmful propulsion engine is extracted from the missile and replaced with a separate gas generator system. The gas generator is mounted on the launcher rather than the missile, and its exhaust is directed away from sensitive equipment through a nozzle, thereby separating the harmful launch function from the missile itself
Solution Approach 2:
A gas generator acts as an intermediary device between the launcher and the missile. It provides the necessary thrust through gas pressure without requiring the missile's own propulsion engine to be ignited, thus mediating the launch process to avoid direct flame contact with the missile and surrounding equipment
2Force
If a missile propulsion engine is used during the initial launch period, then the missile can be ejected from the canister, but thrust loss occurs due to detent unlocking and release mechanisms
Solution Approach 1:
The detent unlocking and missile release actions are performed in advance by the gas pressure system before the propulsion engine is activated. This preliminary mechanical release eliminates the thrust loss that would otherwise occur during the transition from restrained to free-flight conditions
Solution Approach 2:
The mechanical detent and release mechanisms are replaced with a gas pressure-driven system. Gas pressure simultaneously unlocks the detents, pushes the missile off the launcher, and provides continuous thrust, eliminating the sequential mechanical operations that cause thrust loss
3Object-affected harmful factors
If a flame treatment device or protective measure is added to protect ground equipment, then equipment damage is prevented, but device complexity and manufacturing cost increase
Solution Approach 1:
The harmful flames are extracted and redirected away from the missile and surrounding equipment through a dedicated nozzle on the gas generator. This eliminates the need for additional flame treatment devices or protective shielding around the missile and launcher
Solution Approach 2:
The harmful high-temperature flames from the gas generator are redirected to serve a useful function by being exhausted through a nozzle in a controlled direction. This converts the potentially harmful thermal energy into a directed exhaust flow that provides thrust while protecting surrounding equipment, eliminating the need for separate protective measures
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
Effectively releases missiles without damaging ground equipment or peripheral missiles, reduces manufacturing costs and complexity, and ensures smooth ejection by using gas pressure to propel the missile, minimizing the risk of damage and thrust loss.
Implementation Method 1
a gas generator secured to the partition wall in the second chamber so that a gas outlet thereof faces in an opposite direction from the first chamber, and wherein the missile is propelled by the pressure of the gas discharged out of the gas generator from the second chamber to the first chamber through the hole
Data Source
AI summary
The present invention discloses a missile ejection system and a canister thereof. The missile ejection system comprises: comprising: a canister formed as a cylindrical shell, a partition wall protruding from an inner wall of the canister so as to divide the canister into a first chamber for housing a missile therewithin and a second chamber, and having at least one hole therethrough for allowing the flowing of gas through the partition wall, a gas generator secured to the partition wall in the second chamber so that a gas outlet thereof faces in an opposite direction from the first chamber, and an obturator including a sealing plate formed with a concave surface toward a fore-end of the missile for enclosing a tail end of the missile, and a radially extending skirt plate extended from the circumference of the sealing plate to the inner wall of the canister and inclined toward the fore-end of the missile for covering the space between the missile and the inner canister, wherein the missile is propelled by the pressure of the gas discharged out of the gas generator from the second chamber to the first chamber through the hole, being pressurized by the flown-in gas in the first chamber, pushing upon the obturator. Thereby, the system is able to effectively release a missile from a canister by a gas generator without using a missile propulsion engine, thereby fundamentally preventing the damage of ground equipments or peripheral missiles.