Missile Airframe Cooling Channels for Hypersonic Electronics Heat
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Solution Overview
Problem
Hypersonic missiles face thermal management challenges due to high heating effects and heat generation by electronic equipment, necessitating complex and expensive materials and separate cooling systems, which add weight and space requirements.
Innovation Solution
An integrated cooling system within the airframe uses coolant channels to cool both the airframe and electronic equipment, utilizing fuel as a coolant, eliminating the need for separate cooling systems and reducing weight and space.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If traditional materials are used for missile airframe, then manufacturing cost is reduced, but the airframe cannot withstand high temperatures at hypersonic speeds
Solution Approach 1:
The patent converts the harmful heat generated by aerodynamic friction at hypersonic speeds into a useful cooling mechanism by directing this heat toward cooling the electronic equipment that generates it, thereby allowing the use of conventional materials without incurring additional cooling system costs
Solution Approach 2:
The airframe serves multiple functions: it provides structural support, acts as a heat sink for electronic equipment, and the external heating from aerodynamic friction is utilized to cool the electronics, eliminating the need for separate cooling systems and reducing overall system complexity
2Temperature
If separate cooling system is added for electronic equipment, then electronic equipment temperature control is improved, but missile weight increases
Solution Approach 1:
The cooling system for electronic equipment is merged with the airframe structure itself, using the airframe as the heat sink and the coolant circulation system to transfer heat from electronics to the airframe, thereby eliminating the need for separate dedicated cooling components and reducing overall weight
Solution Approach 2:
The airframe is given the additional function of serving as a heat sink for electronic equipment, while the coolant system serves dual purposes of cooling both the airframe and the electronic equipment, reducing the need for separate cooling systems and associated weight
3Temperature
If separate cooling system is added for electronic equipment, then electronic equipment temperature control is improved, but missile complexity increases
Solution Approach 1:
The cooling systems for the airframe and electronic equipment are merged into a single integrated system, using common coolant circulation pathways and the airframe structure as a shared heat sink, thereby reducing the number of separate cooling components and simplifying the overall system architecture
Solution Approach 2:
The coolant circulation system performs multiple cooling functions simultaneously - cooling the airframe and cooling the electronic equipment - through a single integrated system, eliminating the need for separate dedicated cooling systems and reducing overall system complexity
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 integrated cooling system allows the use of inexpensive materials for the airframe, maintains electronic equipment within a suitable operating temperature, and enhances the effectiveness of the technical solution by providing effective solutions to the technical problem of the airframe as a heat sink, while optimizing the airframe as a heat sink for the airframe, thus effectively managing the thermal management of the missile.
Implementation Method 1
a coolant channel in fluid communication with the tank, and a pump operable to pump coolant from the tank through the coolant channel, wherein the coolant channel is defined within the airframe and arranged to cool the airframe and the electronics equipment
Data Source
Figure 1a~1d
Figure 2~3
Figure 4a~4b
AI summary
A missile is disclosed. The missile comprises an airframe, electronics equipment proximate to a portion of the airframe, a tank for coolant, a coolant channel in fluid communication with the tank, and a pump operable to pump coolant from the tank through the coolant channel. The coolant channel is defined within the airframe and arranged to cool the airframe and the electronics equipment.