Aircraft Hydraulic Systems with Shared Return Lines
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Solution Overview
Problem
Aircraft hydraulic systems often employ multiple independent hydraulic circuits with redundant components, leading to increased weight, cost, and space occupancy, as they perform similar functions.
Innovation Solution
A hydraulic system with two or more subsystems that share components, including a shared return line and reservoir, where one subsystem is powered by the engine and the other by an auxiliary power unit, allowing for efficient fluid circulation and component sharing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple independent hydraulic circuits with redundant components are used, then system reliability is improved, but aircraft weight increases
Solution Approach 1:
The patent merges the return lines and reservoir of multiple hydraulic subsystems into shared common infrastructure. Specifically, multiple hydraulic subsystems (e.g., flight essential and non-flight essential subsystems) utilize a common return line and common reservoir, eliminating redundant return lines and reservoirs while maintaining independent pressure systems and reliability.
Solution Approach 2:
The common return line and common reservoir serve multiple hydraulic subsystems simultaneously, performing the function of fluid return and storage for several independent systems through a single universal infrastructure, thereby reducing overall system weight without compromising individual subsystem reliability.
2Reliability
If multiple independent hydraulic circuits with redundant components are used, then system reliability is improved, but aircraft cost increases
Solution Approach 1:
The patent combines redundant components (return lines and reservoirs) into shared common infrastructure across multiple hydraulic subsystems, directly reducing the quantity of materials required and simplifying manufacturing processes while preserving system reliability through maintained independence of pressure-generating components.
3Reliability
If multiple independent hydraulic circuits with redundant components are used, then system reliability is improved, but space occupancy increases
Solution Approach 1:
The patent merges multiple separate return lines into a single common return line and consolidates multiple reservoirs into one common reservoir, significantly reducing the volume occupied by hydraulic infrastructure while maintaining independent operation of each hydraulic subsystem through separate pumps and pressure lines.
4Reliability
If redundant hydraulic components are used, then system reliability is improved, but device complexity increases
Solution Approach 1:
The patent merges redundant return lines and reservoirs into shared common infrastructure, reducing the total number of components and simplifying system architecture while preserving reliability through maintained independence of critical pressure-generating and distribution elements.
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
This configuration reduces the weight and cost of the aircraft by eliminating unnecessary components and plumbing, while maintaining system reliability and flexibility through independent operation of shared components.
Implementation Method 1
a first hydraulic pump powered by the engine to pump shared hydraulic fluid to the first set of hydraulic-powered components
Implementation Method 2
a second hydraulic pump powered by the auxiliary power unit to pump the shared hydraulic fluid to the second set of hydraulic-powered components
Implementation Method 3
a shared return line subsystem in fluid communication with the first and second hydraulic subsystems to return the shared hydraulic fluid from the first and second sets of hydraulic-powered components to the first and second hydraulic pumps
Data Source
AI summary
A hydraulic system for an aircraft having an engine and an auxiliary power unit includes a first hydraulic subsystem including a first hydraulic pump and a first set of hydraulic-powered components in fluid communication with the first hydraulic pump. The first hydraulic pump is powered by the engine to pump shared hydraulic fluid to the first set of hydraulic-powered components. The hydraulic system includes a second hydraulic subsystem including a second hydraulic pump and a second set of hydraulic-powered components in fluid communication with the second hydraulic pump. The second hydraulic pump is powered by the auxiliary power unit to pump the shared hydraulic fluid to the second set of hydraulic-powered components. A shared return line subsystem and reservoir is in fluid communication with the first and second hydraulic subsystems to return the shared hydraulic fluid to the first and second hydraulic pumps.