Vertical Launch System Heavy Inert Gas Insulation for Heat Control
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Solution Overview
Problem
Existing vertical launch systems face challenges in managing thermal insulation, which affects the reusability, compactness, and thermal stability of missiles due to high external temperatures, leading to premature desensitization of energetic materials.
Innovation Solution
Integration of heavy inert gas insulation layers with a density of at least 1.5 Kg/m³ and thermal conductivity no greater than two-thirds of air into the launch system components or as inserts, using gases like Argon, Krypton, or Xenon, held at 1 atmosphere, to form a sealed void space for enhanced thermal protection.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If air-filled double-walled construction is used for thermal insulation, then the structure provides basic insulation, but the thermal protection is insufficient against high external temperatures
Solution Approach 1:
The patent replaces air with heavy inert gases (xenon, krypton, or argon) in the sealed void space between double walls of missile cells and exhaust components. These gases have lower thermal conductivity than air, providing superior thermal insulation that protects energetic materials from high external temperatures, preventing premature desensitization while maintaining structural integrity.
Solution Approach 2:
The patent employs a composite insulation system combining double-walled structural construction with inert gas filling. This composite approach integrates the mechanical strength of metal walls with the thermal insulation properties of inert gases, creating a multi-layered thermal barrier that effectively resists heat transfer from exhaust gases to missile components.
2Object-affected harmful factors
If thicker insulation layers are used to protect against high temperatures, then thermal protection improves, but the launch system becomes less compact and dense
Solution Approach 1:
The patent uses heavy inert gases with superior insulation properties compared to air, achieving the same thermal protection with reduced insulation layer thickness. This allows maintaining compact launch system volume while providing adequate thermal protection against high external temperatures.
Solution Approach 2:
The patent changes the physical parameters of the insulation medium by replacing air with inert gases having lower thermal conductivity. This parameter change enables more efficient thermal insulation, reducing the required insulation thickness and maintaining system compactness while improving thermal protection.
3Device complexity
If conventional air insulation is used, then the system structure is simple, but the thermal conductivity is too high allowing heat transfer to energetic materials
Solution Approach 1:
The patent replaces air with heavy inert gases in the insulation void space, significantly reducing thermal conductivity and heat transfer to energetic materials. This substitution maintains the simple double-walled structural design while dramatically improving thermal insulation performance.
Solution Approach 2:
The patent modifies the thermal parameters of the insulation medium by introducing inert gases with lower thermal conductivity than air. This parameter change reduces heat transfer while maintaining structural simplicity, as the same double-walled configuration provides superior insulation.
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 heavy inert gas insulation delays premature reaction of energetic materials, allowing for more compact and dense missile configurations and improved reusability of the launch system.
Implementation Method 1
The space between the walls is filled with air... filled with an inert gas that has a density of at least 1.5 Kg/m3 and a thermal conductivity (Tcond_gas) of no greater than two-thirds of a thermal conductivity of air (Tcond_air) to form a heavy inert gas insulation layer
Data Source
AI summary
Heavy inert gas insulation layers are provided for one or more components of a launch system for a plurality of missiles. The layer may be integrated into the walls of the components or provided in inserts attached to the components. An inert gas fills a sealed void space in the walls or the insert. The inert gas has a density of at least 1.5 Kg/m3 and a thermal conductivity (Tcond_gas) of no greater than two-thirds of a thermal conductivity of air (Tcond_air) to form the heavy inert gas insulation layer. The inert gas may be Argon, Krypton, Xenon or a synthetic gas and is suitably held at a pressure of 760 Torr (1 atmosphere) or greater at sea level. The heavy inert gas insulation layer delays desensitization or inhibits premature reaction of the energetic materials inside the missiles due to high external temperatures. The insulation layers allow for more compact and dense configurations of the launch system and missiles.