Passive Solder Separation Mechanism for Spacecraft Re-entry
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Solution Overview
Problem
Existing spacecraft separation mechanisms, both active and passive, face challenges in reliability, complexity, and cost, particularly during earth atmospheric re-entry, where aerodynamic heating and drag can cause fragmentation and debris issues, and existing passive mechanisms may not ensure complete demise of large spacecraft components.
Innovation Solution
A passive separation mechanism using conical connecting surfaces with a solder joint that melts between 100°C to 300°C, triggered by re-entry heat, allowing for reliable and controlled separation of spacecraft components without electrical signals, reducing manufacturing complexity and costs.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If active separation mechanisms are used to separate spacecraft components, then separation reliability can be controlled, but device complexity and cost increase due to electrical signals and control systems
Solution Approach 1:
The separation mechanism uses the spacecraft's own re-entry heat as the activation energy source, eliminating the need for external control systems, electrical signals, or additional power sources. The solder joint automatically melts when exposed to re-entry temperatures, causing passive separation without human intervention or complex control mechanisms.
Solution Approach 2:
The mechanism exploits the phase transition of solder from solid to liquid at its melting point during re-entry. This phase change is triggered by aerodynamic heating, causing the joining material to fail and separate the spacecraft components automatically, converting thermal energy into mechanical separation action.
2Device complexity
If passive separation mechanisms are used to reduce complexity, then device complexity decreases, but separation reliability may be compromised as they rely on natural phenomena
Solution Approach 1:
The mechanism is designed with specific material parameters - the solder joint's melting point is selected to fall within the expected re-entry temperature range. This parameter matching ensures that the separation trigger is reliably activated by the natural thermal environment during re-entry, converting an uncontrollable natural phenomenon into a predictable separation event.
3Object-affected harmful factors
If large spacecraft are de-orbited using propulsion systems to avoid debris, then debris risk to people and property is reduced, but mission costs and additional debris increase
Solution Approach 1:
The mechanism divides the spacecraft into separable components using the solder joint as a weak link. During re-entry, the solder melts and causes the spacecraft to break into smaller pieces, ensuring complete atmospheric demise of each fragment. This segmentation approach eliminates the need for costly propulsion systems while achieving the same debris mitigation goal.
Solution Approach 2:
The mechanism converts the harmful aerodynamic heating during re-entry, which could cause uncontrolled fragmentation, into a beneficial controlled separation event. By designing the solder joint to melt at re-entry temperatures, the thermal stress that would otherwise be damaging is harnessed to achieve reliable component separation and complete demise.
4Strength
If conventional joining methods are used for spacecraft components, then structural strength is maintained, but separation capability during re-entry is lost
Solution Approach 1:
The joining system uses different material properties in different locations: the solder joint is specifically selected to have a melting point within the re-entry temperature range, while other structural joints use materials with much higher melting points. This local differentiation allows the solder joint to fail at the appropriate time during re-entry while maintaining structural integrity during normal operation.
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 complete demise of spacecraft components during re-entry by utilizing heat-induced solder melting, enhancing design freedom, compatibility, and operational capabilities while minimizing performance and reliability risks, ensuring safe disposal and reducing debris.
Implementation Method 1
Aerodynamic heating and atmospheric drag are two phenomena experienced by the object during atmospheric re-entry
Implementation Method 2
The joining means is solder meltable at a temperature in the range of 100°C to 300°C. By choosing a solder having such a melting temperature, the first and second structural elements separate from each other when a temperature in the range of 100°C to 300°C is experienced by the separation mechanism
Implementation Method 3
Aerodynamic heating and atmospheric drag are two phenomena experienced by the object during atmospheric re-entry, which can cause its loss of mass and its fragmentation into smaller objects
Data Source
Figure 1~2
Figure 3
AI summary
A separation mechanism (100) for passive separation of a first spacecraft component (200) from a second spacecraft component (300) comprises a first structural element (10), a second structural element (20) and joining means (30) for mechanically joining the first and second structural elements (10, 20). The first structural element (10) has a receiving hole with an inner first connecting surface (11) and is adapted to be mounted to the first spacecraft component (200). The second structural element (20) is adapted to be at least in part received within the receiving hole of the first structural element (10) and has an outer second connecting surface (21) facing the inner first connecting surface (11) when the second structural element (20) is at least in part received within the receiving hole of the first structural element (10). The second structural element (20) is adapted to be mounted to the second spacecraft component. The joining means (30) is adapted to mechanically join the first and second structural elements (10, 20) together via their first and second connecting surfaces (11, 21). The joining means (30), in a joint state of the passive separation mechanism (100), is sandwiched between and connects the inner first connecting surface (11) and the outer second connecting surface (21) together when the second structural element (20) is at least in part received within the receiving hole of the first structural element (10). The joining means (30) is solder meltable at a temperature in the range of 100°C to 300°C so as to separate the first and second structural elements (10, 20) when a melting temperature, i.e., a temperature in the range of 100°C to 300°C, is experienced by the separation mechanism (100).