Missile Canister Lateral Support System
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Solution Overview
Problem
Existing lateral support systems for canister-launched missiles allow relative movement between the missile and the canister, causing vibrations and shocks during transportation and handling, which can lead to missile breakdown.
Innovation Solution
A lateral support device system comprising sabots with a travel lock bar and bolt mechanism, a position adjustment pin, and a spring-loaded load support plate that securely attaches the missile to the canister during transport and automatically releases during launch, minimizing friction and preventing gap formation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If sabots are installed to support the missile and guide it within the canister, then the missile can be guided and supported during launch, but a gap is created between the missile and canister causing vibrations and shocks during transportation and handling
Solution Approach 1:
The support system is divided into multiple sabots distributed around the missile circumference, with each sabot independently capable of engaging with the canister. This segmentation allows the system to provide comprehensive support while minimizing gap formation through coordinated engagement of multiple points.
Solution Approach 2:
The sabots are pre-positioned on the missile before insertion into the canister. The travel lock bar and bolt mechanism are pre-configured to automatically engage with the canister inner surface upon insertion, eliminating the need for manual adjustment and ensuring immediate support without gap formation.
2Adaptability or versatility
If a gap is allowed between the missile and canister to prevent the missile from being caught, then the missile can move freely during launch, but the gap causes vibrations and shocks during transportation and handling
Solution Approach 1:
The support system transitions from a static gap-allowing configuration to a dynamic engagement system. The travel lock bolt can be selectively engaged or disengaged based on operational requirements, allowing the system to adapt between providing rigid support during transport and allowing free movement during launch.
Solution Approach 2:
The travel lock bar acts as an intermediary element between the sabot and the canister. It transmits the locking action of the travel lock bolt to the sabot, which then contacts the canister inner surface, providing controlled support that eliminates gaps while maintaining missile stability.
3Object-affected harmful factors
If the missile is tightly secured to eliminate gaps, then vibrations and shocks are reduced, but resistance force increases during launch
Solution Approach 1:
The travel lock bolt is selectively engaged or disengaged from the travel lock bar based on operational phase. During transport and handling, the bolt is engaged to eliminate gaps and reduce vibrations. During launch, the bolt is disengaged to remove the constraint and minimize resistance force, allowing the missile to accelerate freely.
Solution Approach 2:
The support system employs dynamic engagement mechanisms where the travel lock bolt can be selectively engaged or disengaged. This allows the system to transition between a tightly secured state during transport (reducing vibrations) and a free-moving state during launch (minimizing resistance force).
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 system effectively restrains lateral movement of the missile during transport and handling, ensuring stability and minimizing impact, while allowing for smooth launch with negligible resistance, as the sabots separate automatically after launch due to the spring's restoration force.
Implementation Method 1
the sabots separate automatically after launch due to the spring's restoration force
Data Source
AI summary
A lateral support device system of a canister-launched missile of the present invention is provided for eliminating the clearances between missile and the canister in 4 places by 90 degrees interval, and therefore no relative movement occurs between the missile and the canister. Therefore, the missile and the detent is free from shocks and vibrations that occurs during the handling, transportation and operation. In addition, when the missile is fired, those lateral lock become free with a little energy loss.