Satellite Ejection Rail Clamping for Vibration-Free Launch Holding
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Solution Overview
Problem
Existing ejection units for satellites face challenges in securely fixing and damping satellites during high accelerations and loads encountered during rocket launches and separations, while maintaining a simplified design.
Innovation Solution
A clamping mechanism that applies force diagonally and perpendicularly to the satellite via angled rails, distributing the clamping force uniformly, combined with a carriage system on rollers for deflection and multiplication of forces, and a spring-loaded conical bolt for controlled ejection.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If a clamping mechanism applies force to angled rails in a diagonal direction (bisecting line), then the clamping force is uniformly distributed over the satellite and high clamping forces are achieved, but the design complexity increases
Solution Approach 1:
The clamping mechanism applies force in a diagonal direction (along the bisecting line of the angled rail) rather than symmetrically from adjacent sides. This asymmetric force application optimizes the distribution of clamping force over the satellite surface, achieving extraordinarily high clamping forces while maintaining a simplified design with only one clamping mechanism per angled rail
2Reliability
If multiple clamping mechanisms are used to hold larger satellites, then reliable holding and damping is achieved, but the forces may work against one another reducing effectiveness
Solution Approach 1:
The patent applies different clamping configurations to different angled rails based on local requirements. One angled rail has a clamping mechanism that applies diagonal force, while another angled rail has its leg spaced outwardly to contact the satellite with only one leg. This local differentiation ensures that clamping forces are transmitted perpendicular to the satellite surface without working against each other, achieving reliable holding for larger satellites
3Stability of the object's composition
If the ejection unit is designed for secure fixation during high accelerations, then vibration-free fixation is ensured, but the ejection mechanism complexity increases
Solution Approach 1:
The ejection carriage is preloaded into a blocking position by a spring-loaded conical bolt before ejection. The locking pin holds the conical bolt in this blocking position during transport, ensuring secure fixation. When ejection is required, the locking pin is released, allowing the conical bolt to move and release the ejection carriage, which then propels the satellite outward. This preliminary positioning ensures stability during high accelerations while maintaining a relatively simple ejection mechanism
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
Ensures secure and vibration-free fixation of satellites, allowing for reliable holding and damping of larger satellites without counteracting forces, while simplifying the design and facilitating easy ejection.
Implementation Method 1
a carriage supported on rollers, said carriage supporting a displaceable slot rail that is in turn supported on rollers of the carriage
Implementation Method 2
a spring-loaded conical bolt can be provided and secures an ejection carriage of the ejection unit in a blocking position when the ejection carriage is in a preloaded position
Data Source
AI summary
An ejection unit for a satellite comprises a housing which is closed by a door and in which a guide for the satellite is provided. The guide comprises angled rails and a clamping apparatus to fixedly clamp the satellite by means of a clamping mechanism.