Aircraft Hydraulic Boost Pump Layout for Return-Line Pressure Loss
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Solution Overview
Problem
Aircraft hydraulic systems face challenges in efficiently supplying pressurized hydraulic fluid to flight control actuators, particularly during high load demands, leading to inefficiencies and energy losses due to pressure drops in return lines.
Innovation Solution
The hydraulic system incorporates an engine-driven pump delivering fluid at a first pressure, a boost pump delivering fluid at a higher second pressure, and an accumulator to supplement fluid supply, with a valve system that redirects fluid from the return line to the boost pump to enhance pressure support when needed, and an axial piston pump with an adjustable swashplate for pressure control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If hydraulic fluid is delivered through return lines to the engine driven pump, then the hydraulic system can reuse hydraulic fluid, but pressure drops occur in the return lines leading to energy losses
Solution Approach 1:
The hydraulic system is segmented into multiple pathways: a supply line from the engine driven pump, a return line back to the pump, and a spare line connecting the return line to the boost pump. This segmentation allows selective routing of hydraulic fluid to bypass pressure drop losses in the return line when high pressure is needed.
Solution Approach 2:
The boost pump acts as an intermediary device that receives hydraulic fluid from the return line via the spare line and delivers it at elevated pressure to the actuator. This intermediary pathway eliminates the need to overcome return line pressure drops while achieving the required high pressure output.
2Stress or pressure
If a single engine driven pump is used to supply hydraulic fluid, then the system is simpler, but it cannot provide sufficient pressure during high load demands
Solution Approach 1:
The system merges the output of two pumps (engine driven pump and boost pump) to supply hydraulic fluid to the actuator. The engine driven pump provides baseline pressure and flow, while the boost pump supplements pressure during high load demands, achieving higher overall pressure capability than either pump alone.
Solution Approach 2:
The boost pump is configured with variable displacement capability, allowing its output to be dynamically adjusted based on system pressure demands. During high load conditions, the boost pump increases its displacement to provide additional pressure; during normal operation, it operates at reduced displacement, optimizing system performance across varying conditions.
3Force
If hydraulic fluid is delivered at high pressure to meet load demands, then actuator performance is improved, but power consumption increases
Solution Approach 1:
The system changes the pressure parameter dynamically by switching between the engine driven pump's lower pressure output and the boost pump's higher pressure output based on actuator load demands. This parameter adjustment ensures high force capability when needed while reducing power consumption during normal operation.
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 ensures responsive and efficient hydraulic fluid supply to flight control actuators, reducing energy losses and weight by bypassing the return line pressure drop, allowing for higher flow rates and reduced actuator power consumption.
Implementation Method 1
the boost pump is an axial piston pump that includes an adjustable swashplate to control the pressure of the hydraulic fluid that is supplied by the boost pump
Implementation Method 2
An engine driven pump delivers hydraulic fluid to the actuator at a first pressure, and a boost pump delivers hydraulic fluid to the actuator at a second pressure that is higher than the first pressure
Data Source
AI summary
A hydraulic system for an aircraft. The hydraulic system can include a hydraulic actuator that is operatively coupled to a flight control member. Hydraulic fluid is moved through the hydraulic system by an engine driven pump that delivers hydraulic fluid to the actuator at a first pressure, and a boost pump that delivers hydraulic fluid to the actuator at a second pressure that is higher than the first pressure. The hydraulic system is configured such that the hydraulic fluid returning from the actuator to the engine driven pump can be delivered to the boost pump prior to reaching the engine driven pump.