Refueling Link Separation for Space Launchers
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Solution Overview
Problem
The reliability of connection modules for refueling launchers is limited, and existing solutions are complex and costly, requiring improvements in separation mechanisms for cryogenic propellants.
Innovation Solution
A high-pressure hydraulic connection link with specific junction designs, including a circular groove for incipient fracture and a longer, thinner annular wall section, combined with clamping means to secure and constrain the connection, allowing for axial tensile stress and torsional torque to facilitate reliable separation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a complex mechanism with struts and weakened areas is used for separation, then the connection can be maintained until liftoff, but the reliability of separation remains limited
Solution Approach 1:
The link is divided into three portions (first, second, and third portions) with the second portion being longer and thinner, creating a segmented structure that simplifies the separation mechanism while maintaining reliability. The junctions act as predetermined separation points between these segments.
Solution Approach 2:
The cross-sectional dimensions of the link are varied along its length, with the second portion having a smaller cross-section than the first and third portions. This parameter change creates a thinner section that separates more reliably under axial tensile stress during liftoff.
2Reliability
If multiple components and moving parts are used in the connection module, then the connection can be maintained, but the number of elements increases
Solution Approach 1:
The link is designed as a monobloc structure where the first, second, and third portions are integrated into a single piece. This merging of components reduces the number of parts while maintaining connection reliability through the varied cross-sectional design and junctions.
Solution Approach 2:
The link serves multiple functions: it maintains the fluid connection between ground and flight parts, provides structural support, and enables reliable separation. The varied cross-section and junctions allow it to perform all these functions with a single integrated component rather than multiple specialized parts.
3Strength
If the link maintains strong connection until liftoff, then fluid communication is preserved, but the separation mechanism becomes less reliable
Solution Approach 1:
The link has different local properties along its length: the first and third portions have larger cross-sections for strong connection, while the second portion has a smaller cross-section for reliable separation. The junctions represent transitions between these different local qualities, creating predetermined separation points.
Solution Approach 2:
The link is designed in advance with a second portion that has a smaller cross-section, pre-positioning the separation point. During liftoff, the axial tensile stress naturally concentrates at this predetermined weaker section, ensuring reliable separation without requiring additional separation mechanisms.
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 solution provides extreme separation reliability, reduces the number of elements and moving parts, ensures optimal sealing, and maintains fluid and mechanical connection until launch, while minimizing protrusions for aerodynamic preservation.
Implementation Method 1
the first portion and/or the second portion comprises an external surface with patterns configured to transmit an axial torsional torque to the linkage
Implementation Method 2
the first junction is a circular groove and/or a break initiation, with an axial length of less than 10.00 mm
Implementation Method 3
a first junction configured to separate under the action of a mechanical stress in axial tension
Implementation Method 4
clamping means configured to press the ground part and the flight part against each other and to mechanically constrain the link
Implementation Method 5
Its separation by rupture is caused by a mechanism exerting an axial tensile force
Data Source
Figure 1
Figure 2
Figure 3~4
AI summary
The invention relates to a link (24) for a connection module (12) for refueling a space launcher with cryogenic propellant. The module (12) comprises a ground portion (18) located on the launch pad mast side of the launcher; a flight portion (16) attached to the launcher; and the link (24) connecting the portions (16 and 18). The module (12) has a passage (20) passing through the ground portion (18), the flight portion (16), and the link (24). The link (24) has two junctions (42 and 44) interposed between three of its sections. One of the junctions (42) is a groove-shaped break point, and the other is an elastic zone. A lever (28), or torsion arm, is connected to a disconnect cable. During liftoff, the lever (28) exerts a torque on the link (24) that causes the break point (42) to rupture.