Asymmetric Aircraft Hydraulic Control System Routing
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Solution Overview
Problem
Conventional aircraft hydraulic systems require extensive and complex routing of hydraulic lines to meet the flow demands of elevators and rudder, leading to increased weight, installation effort, and pressure drop.
Innovation Solution
An asymmetric hydraulic control system with a hydraulic pump connected to two hydraulic lines of different diameters, where the first hydraulic line supplies both a primary actuator and a secondary actuator downstream, while the second line exclusively supplies a second actuator, reducing pipework and allowing for flexible routing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a conventional symmetric hydraulic architecture is used to supply pressure and flow to both elevators, then symmetric supply is achieved, but the system requires rather long hydraulic lines extending from the center to the tail region, increasing routing complexity and weight
Solution Approach 1:
The patent applies asymmetry by connecting the left and right elevators to different ports of the hydraulic pump through separate hydraulic lines, rather than using a symmetric single-line architecture. This asymmetric configuration allows for optimized routing that reduces the length and complexity of hydraulic lines while maintaining symmetric pressure and flow supply to both elevators
2Adaptability or versatility
If hydraulic lines are routed extensively from the center to the tail region to reach all control surfaces, then all actuators can be supplied, but routing complexity increases and requires more and longer hydraulic lines to be installed
Solution Approach 1:
The patent segments the hydraulic supply system by providing separate hydraulic lines from the pump to different control surfaces (elevators and rudder). This segmentation allows each line to be optimized independently for its specific route, reducing overall routing complexity while ensuring all actuators receive adequate hydraulic supply
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 minimizes pipework, reduces weight and installation effort, and maintains actuator functionality even in failure cases by ensuring asymmetric flow distribution, thereby reducing pressure drop and enabling efficient hydraulic system design.
Implementation Method 1
a hydraulic pump (26), a first hydraulic line (28), a second hydraulic line (30), at least one first actuator (18) connected to the first hydraulic line (28) and coupled with a first control surface (12), at least one second actuator (20) connected to the second hydraulic line (30) and coupled with a second control surface (14)
Data Source
Figure 1~2
AI summary
A control system for an aircraft is proposed, comprising a hydraulic pump, a first hydraulic line, a second hydraulic line, at least one first actuator coupled with a first control surface, at least one second actuator coupled with a second control surface, and at least one third actuator coupled with a third control surface, wherein the first control surface and the second control surface are arranged at a distance to each other and symmetrically relative to a symmetry axis, wherein the third control surface is arranged substantially on the symmetry axis, wherein the first hydraulic line and the second hydraulic line are connected to the hydraulic pump, wherein the at least one first actuator is connected to the first hydraulic line, wherein the at least one second actuator is connected to the second hydraulic line, wherein the at least one third actuator is connected to the first hydraulic line downstream of the at least one first actuator at a junction point, and wherein the first hydraulic line at least partially comprises a larger diameter than the second hydraulic line.