Passive Stage Separation Clamp Using Engine Gas Pressure
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Solution Overview
Problem
Active stage separation mechanisms in aerospace vehicles, such as rockets, increase complexity, weight, and cost due to the use of pyrotechnic elements.
Innovation Solution
A passive mechanical separation mechanism using a drive stage connection with a controllably detachable connecting element and a clamping device that fails under defined overload, utilizing gas pressure from the engine to separate propulsion stages.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If active pyrotechnic separation mechanisms are used, then reliable stage separation is achieved, but device complexity increases
Solution Approach 1:
The patent extracts the active control system from the separation mechanism, retaining only the passive mechanical clamping elements and predetermined breaking points. The pyrotechnic charge is removed entirely, and separation is achieved through pure mechanical failure of the clamping elements under gas pressure, eliminating complex control systems while maintaining reliability
Solution Approach 2:
The separation mechanism serves itself by using the engine's own gas pressure to fail the predetermined breaking points in the clamping elements. The system automatically separates when the clamping elements reach their breaking point under pressure, without requiring external active control or pyrotechnic initiation
2Reliability
If active pyrotechnic separation mechanisms are used, then controlled separation is achieved, but weight increases
Solution Approach 1:
The clamping elements are designed as disposable components with predetermined breaking points that fail once under defined overload. These simple mechanical elements replace heavy pyrotechnic systems, providing controlled separation through one-time use mechanical failure rather than complex active mechanisms
Solution Approach 2:
The patent removes the heavy pyrotechnic charge and active control components, retaining only the essential mechanical clamping elements. This extraction of unnecessary weight while maintaining controlled separation capability directly addresses the weight increase problem
3Reliability
If active pyrotechnic separation mechanisms are used, then stage separation is achieved, but cost increases
Solution Approach 1:
The clamping elements with predetermined breaking points are simple, inexpensive mechanical components that can be manufactured economically. They replace costly pyrotechnic systems and active control mechanisms, achieving the separation function at lower manufacturing cost while maintaining reliability
Solution Approach 2:
By extracting the expensive pyrotechnic and electronic control systems, the patent leaves only simple mechanical clamping elements that are easier and cheaper to manufacture, directly reducing production costs while preserving the essential separation function
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
Enables safe, controlled, and cost-effective separation of propulsion stages without active triggers, reducing complexity and weight.
Implementation Method 1
utilizing the pressure of the gas mass flow generated when a pyrotechnic gas source is ignited in the engine of the continuing, i.e., preferably upper, propulsion stage of the aerospace aircraft. The gas pressure is used by means of pressure control within the propulsion stage to induce structural failure of the clamping element
Data Source
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AI summary
The present invention relates to an aerospace device (10) with a propulsion stage connection comprising a first lower propulsion stage (11) and at least one second, upper propulsion stage (12) connected to the first, wherein the propulsion stage connection has a passive separation mechanism (13) with a controllably detachable connecting element (14) and wherein the connecting element (14) is arranged on the circumference of mutually facing end regions (16a, b) of the propulsion stages (11, 12) and is held by a circumferential clamping element (15) and the clamping element (15) has at least one form-fit and force-fit structural connection and/or predetermined breaking point (26) that fails under defined overload, and a method for controlled separation of a propulsion stage connection of an aerospace device (10).