Launcher Refueling Module Separation Mechanism
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Solution Overview
Problem
Current systems for separating the onboard and ground parts of a launcher refueling module are inefficient, requiring pre-ignition separation, leading to costly and stressful emergency drainage procedures, and irreversible valve plates that need replacement after each launch attempt.
Innovation Solution
A mechanical separation device using a locking system with a locking finger and pin, actuated by a drive lever and extraction lever, which separates the parts during vertical launcher movement, allowing for post-ignition separation and reducing the need for emergency drainage and part replacement.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If electrical control systems are used to separate the onboard and ground parts before ignition, then the separation can be controlled, but the separation must occur during negative chronological time which limits operational flexibility and requires emergency drainage procedures
Solution Approach 1:
The patent replaces electrical control systems with a purely mechanical separation system. The locking pin and locking finger mechanism, actuated by the drive lever and extraction lever, eliminates the need for electrical commands transmitted before ignition. This mechanical system allows separation to occur at any time during vertical movement, providing temporal flexibility while maintaining reliable separation control through physical interlocking and actuation mechanisms.
2Reliability
If the valve plates have an irreversible function, then separation is ensured, but the parts must be replaced before initiating a new launch chronology, increasing cost and preparation time
Solution Approach 1:
The patent implements a recoverable locking mechanism where the locking pin and locking finger can be reused. After separation, the locking pin remains on the onboard part and the locking finger on the ground part, both intact and ready for subsequent operations. This eliminates the need to discard or replace valve plates between launches, allowing quick reconfiguration and improving launch preparation efficiency while maintaining separation reliability through the persistent mechanical locking design.
3Device complexity
If a single actuating means is used, then the device complexity is reduced, but the reliability of separation is compromised in case of malfunction or blockage
Solution Approach 1:
The patent segments the actuation system into two independent actuating means: a drive lever for normal operation and an extraction lever for safety/critical situations. This segmentation allows the system to maintain simplicity in each individual component while achieving enhanced overall reliability through redundancy. The drive lever handles routine separation, while the extraction lever provides a backup path that can be activated independently if the drive lever malfunctions or becomes blocked, ensuring separation reliability without excessive complexity.
Data Source
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AI summary
The invention relates to a device for separating two portions, i.e. Edge and Self portions, of a launcher refueling module comprising a locking system comprising a locking pin (50) mounted on the Self portion (22) and having a blocking portion (523), and a locking axle (42) on the Edge portion (21), engaging by insertion with the blocking portion (523) so as to retain the Edge portion (21) and the Self portion (22) in a locked position. The separating device also includes an actuating system which, by means of the vertical movement of the launcher (10), enables the blocking portion (523) to be released from the locking axle (42), resulting in the Edge portion (21) being separated from the Self portion (22). The invention also relates to a method for separating the Edge and Self portions of a launcher refueling module implemented by means of such a separation device.