Modular environmental control chamber
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Solution Overview
Problem
Current methods for testing aircraft interior moisture management systems are ineffective as they require installation on an aircraft and testing under actual flight conditions, leading to difficulties in developmental evaluation and late-stage corrections.
Innovation Solution
A modular environmental control chamber (MECC) that simulates temperature and humidity conditions, comprising an outer and inner chamber with airflow delivery and return systems, allowing for controlled testing of moisture accumulation and management systems.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If moisture management systems are tested under actual flight conditions after aircraft interior is designed and built, then the systems can be evaluated in real operational environment, but developmental corrections and improvements cannot be implemented early in the design phase
Solution Approach 1:
The patent creates a scaled-down replica chamber (approximately 1/10th the size of an actual aircraft interior) that copies the essential geometric features, insulation layers, and moisture management components of a full aircraft interior. This miniature model allows developmental testing and iterative improvements to be made quickly and efficiently, without requiring actual flight tests, thereby resolving the contradiction between reliable performance evaluation and development time loss.
2Measurement precision
If moisture management design is installed on an aircraft and tested under actual flight conditions, then real operational data is obtained, but the testing process is complex and requires actual aircraft deployment
Solution Approach 1:
The patent extracts the essential testing function from the complex context of full-scale aircraft flight testing. By removing the moisture management system from the full aircraft and placing it in a controlled, scaled-down chamber environment, the system maintains measurement precision for moisture accumulation while dramatically reducing testing complexity. The chamber can be operated in a laboratory setting without requiring actual aircraft deployment, flight operations, or complex aviation infrastructure.
3Ease of manufacture
If a scaled-down model is used for testing, then testing complexity is reduced and developmental iterations are enabled, but the model must accurately represent full-scale aircraft interior geometry and conditions
Solution Approach 1:
The patent applies local quality by maintaining accurate geometric representation only in critical areas where moisture management performance is evaluated, such as insulation layer thicknesses, gap dimensions, and component placements. Non-critical areas can be simplified, allowing the chamber to be easily assembled and disassembled for iterative testing while still providing manufacturing precision where it matters most for validating moisture management system performance.
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
Enables developmental testing and refinement of moisture management systems under simulated flight and ground conditions, facilitating early-stage design improvements and reducing the need for in-service troubleshooting.
Implementation Method 1
an outer chamber blower for directing temperature-controlled air to the outer chamber through the air inflow aperture of the outer chamber housing section
Implementation Method 2
an inner chamber blower for directing humidity-controlled air to the inner chamber through the air inflow aperture of the inner chamber housing section
Implementation Method 3
the section of the fuselage separates the outer chamber and the inner chamber
Data Source
Figure 1
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Figure 3
AI summary
Amodular environmental control chamber (MECC) (100) includes an outer chamber (101) formed by an outer chamber housing section (102) enclosing an outer face (302) of a section of fuselage (301) and an inner chamber (201) formed by an inner chamber housing section (202) enclosing an inner face (303) of the section of fuselage (301). An outer chamber airflow delivery and return system (401) includes an outer chamber blower (402) for directing temperature-controlled air to the outer chamber (101) through an air inflow aperture (103) of the outer chamber housing section (102) and an outer chamber air return duct (403) connected to an air outflow aperture (104) of the outer chamber housing section (102). An inner chamber airflow delivery and return system (501) includes an inner chamber blower (502) for directing humidity-controlled air to the inner chamber (201) through an air inflow aperture (203) of the inner chamber housing section (202) and an inner chamber air return duct (503) connected to an air outflow aperture (204) of the inner chamber housing section (202).