Rectifying Structural Body for Ramjet Inlet Thermal Management
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Solution Overview
Problem
Flying vehicles with ramjet engines face challenges in achieving high thermal insulation and strength due to aerodynamic heating and high air pressure at the inlet, where traditional metal-based thermal insulation structures fail to effectively manage heat transfer and airflow adjustment.
Innovation Solution
A rectification structure body comprising a rectification section, a heat input control section, and a vacuum thermal insulation section, where the rectification section is formed with a rigid metal plate for airflow rectification, the heat input control section is a hollow rigid body or honeycomb structure to manage heat transfer, and the vacuum thermal insulation section is filled with thermal insulation material to reduce heat transfer within the structure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If metal plates are used to form the surface of thermal insulation material to achieve high strength, then structural strength is improved, but thermal insulation performance deteriorates because metal plates transfer heat to the interior
Solution Approach 1:
The structure is divided into multiple functional sections: a rectification section with metal plate surface for strength, a vacuum thermal insulation section for heat blocking, and a heat input control section to manage heat flow. This segmentation allows each part to optimize its specific function without compromising the others.
Solution Approach 2:
The invention uses a composite structure combining metal plates (for strength and aerodynamic heating resistance) with vacuum thermal insulation materials (for heat blocking) and heat resistant materials (for thermal management). This composite approach achieves both high strength and effective thermal insulation.
2Temperature
If traditional thermal insulation structures are used to protect from aerodynamic heating, then thermal insulation performance is improved, but structural strength deteriorates under high air pressure at the inlet
Solution Approach 1:
The structure is divided into multiple functional sections: a rectification section with metal plate surface for strength, a vacuum thermal insulation section for heat blocking, and a heat input control section to manage heat flow. This segmentation allows each part to optimize its specific function without compromising the others.
Solution Approach 2:
The invention uses a composite structure combining metal plates (for strength and aerodynamic heating resistance) with vacuum thermal insulation materials (for heat blocking) and heat resistant materials (for thermal management). This composite approach achieves both high strength and effective thermal insulation.
3Stress or pressure
If metal plates are used for the inlet surface to withstand high air pressure, then structural strength is improved, but thermal insulation performance deteriorates due to heat transfer through the metal
Solution Approach 1:
A vacuum thermal insulation section is introduced as an intermediary layer between the metal plate rectification section (exposed to high pressure and aerodynamic heating) and the interior components. This intermediary layer blocks heat transfer while the metal plate handles the mechanical stress.
Solution Approach 2:
The invention uses a composite structure combining metal plates (for strength and aerodynamic heating resistance) with vacuum thermal insulation materials (for heat blocking) and heat resistant materials (for thermal management). This composite approach achieves both high strength and effective thermal 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 solution provides enhanced thermal insulation performance and structural strength, effectively reducing heat transfer to the interior of the flying vehicle while maintaining airflow rectification and strength under high-pressure conditions.
Implementation Method 1
a vacuum thermal insulation section connected to the heat input control section, characterized in that a surface of the vacuum thermal insulation section is formed of a rigid body
Data Source
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AI summary
This rectifying structural body 100 of a flying object is provided with a rectifying part 30, a heat input control part 20, and a vacuum heat insulated part 10. The rectifying part 30 has a rectifying surface 30a and a rear surface 30b. The rectifying surface 30a rectifies an air flow 5 from the advancing direction. The rear surface 30b is disposed on the opposite side of the rectifying surface 30a. The heat input control part 20 is connected to the rear surface 30b. The vacuum heat insulated part 10 is connected to the heat input control part 20 and has an outer surface formed as a rigid body. In addition, the heat input control part 20 is interposed between the rear surface 30b and the vacuum heat insulated part 10.