High Temperature Flexible Insulation for Aerospace Decelerators
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Solution Overview
Problem
Deployable aerodynamic decelerators for aerospace vehicles require lightweight, thin, and flexible thermal insulation to protect against aerodynamic heating, while also being compact enough for packaging in small launch fairings.
Innovation Solution
Development of a high-temperature flexible insulation material comprising a reflective mat of high-temperature fibers, such as carbon and silicon carbide, with a binder component that enhances durability and flexibility, and incorporates additives like aerogel and fumed silica to reduce heat transfer.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If a thick layer of thermal insulation is used to protect the structural wall from aerodynamic heating, then the heat protection performance is improved, but the mass and volume of the insulation increase
Solution Approach 1:
The patent uses a composite insulation structure combining multiple materials: a carbon felt layer for high-temperature resistance, a silica aerogel layer for low thermal conductivity, and a silicon carbide fabric layer for structural integrity and radiation resistance. This composite approach achieves superior heat protection with reduced overall mass compared to single-material solutions.
Solution Approach 2:
The patent applies different insulation materials with specific properties to different regions and layers of the thermal protection system. The carbon felt provides baseline insulation, while silica aerogel is placed in specific zones requiring enhanced thermal resistance, and silicon carbide fabric is applied where radiation protection is critical. This localized material selection optimizes mass efficiency.
2Object-affected harmful factors
If a thick layer of thermal insulation is used to protect the structural wall from aerodynamic heating, then the heat protection performance is improved, but the volume and flexibility of the insulation increase
Solution Approach 1:
The patent employs flexible fabric-based insulation layers, specifically carbon felt and silicon carbide fabric, that can be folded and packaged into compact volumes. These flexible materials maintain their insulating properties while enabling the decelerator to be stored in a small launch fairing and deployed in situ, preserving both heat protection and operational flexibility.
Solution Approach 2:
The combination of flexible carbon felt with rigid silica aerogel beads creates a composite that balances flexibility for packaging with thermal insulation performance. The fabric structure provides mechanical flexibility while the aerogel filling delivers superior thermal resistance, enabling compact storage without sacrificing heat protection capability.
3Volume of stationary object
If thin insulation is used to maintain compact packaging volume, then the packability is improved, but the heat protection capacity decreases
Solution Approach 1:
The patent utilizes silica aerogel, a highly porous material with extremely low thermal conductivity and low density. This allows the insulation to provide high heat protection capacity in a thin, lightweight layer that packs efficiently. The porous structure traps air pockets that resist heat transfer, delivering superior insulation performance per unit thickness.
Solution Approach 2:
The patent combines thin layers of high-performance materials: a carbon felt layer for structural flexibility, a silica aerogel layer for maximum insulation per unit thickness, and a silicon carbide fabric layer for radiation resistance. This multi-layer composite achieves adequate heat protection with minimal total thickness, enabling compact packaging while maintaining protective capacity.
4Ease of manufacture
If traditional insulation materials are used, then the manufacturing simplicity is maintained, but the high-temperature resistance and radiation protection are insufficient
Solution Approach 1:
The patent employs a composite structure of carbon felt, silica aerogel, and silicon carbide fabric that collectively provides high-temperature resistance and radiation protection. While the composite nature increases manufacturing complexity compared to single materials, each component is a well-established material that can be applied using standard aerospace manufacturing techniques, balancing performance requirements with manufacturing feasibility.
Solution Approach 2:
The patent selects materials with specific thermal and mechanical parameters optimized for high-temperature environments. The silicon carbide fabric provides structural stability at temperatures exceeding 1000°C, while the carbon felt and silica aerogel provide thermal insulation. These parameter-optimized materials maintain resistance to aerodynamic heating and radiation while being manufacturable using established processes.
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 insulation material effectively reduces radiative heat transfer, maintains structural integrity at high temperatures, and can be compactly packaged for deployment in aerospace applications, enabling efficient heat shielding for vehicles entering planetary atmospheres.
Implementation Method 1
The radiation may be attenuated through the thickness of the deployable high temperature flexible insulation, or through individual layers of insulation mats thereof. The insulation mat may have optical properties to produce a transmittance of no more than 5% over a range of temperature from 500° C. to 5000° C.
Implementation Method 2
The insulation mat may include high temperature fibers such as carbon and/or silicon carbide, among others, and these fibers may be coupled by a binder in a non-woven fabric. The radiation may be scattered to prevent it from passing through the high temperature flexible insulation material. By these methods, and by adjusting the volume fraction of fibers per unit volume, the extinction coefficient of the insulation mat may be optimized for a specific application.
Data Source
AI summary
A flexible insulation material may be configured to substantially reduce the amount of radiation transmitted therethrough by incorporating a reflective mat of high temperature fibers that withstand temperatures of at least 500° C. The flexible insulation may be stored and used over temperatures ranging from −270° C. to 5000° C. The mat may have optical properties to produce a transmittance of no more than 5% over a range of temperature from 500° C. to 5000 vC. The mat may include high temperature fibers such as carbon and/or silicon carbide and these fibers may be coupled by a binder in a non-woven fabric. The flexible insulation material may be configured in the Flexible Thermal Protection System of a deployable aerodynamic decelerator or a Hypersonic Inflatable Aerodynamic Decelerator and may be durably flexible.