Wing-Integrated Backup Hydraulic Pump Cooling
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Solution Overview
Problem
Aircraft actuator hydraulic systems face inefficiencies due to increased temperature and weight when the central hydraulic power source fails, leading to drag and reduced aircraft performance, as existing cooling devices increase drag and require large piping systems.
Innovation Solution
An aircraft actuator hydraulic apparatus with a backup hydraulic pump, electric motor, and driver installed inside the wing, utilizing a cooling device such as a fan or oil pipe to efficiently cool these components, reducing size and weight by integrating them within the wing or body and sharing cooling resources.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If a cooling device is added to cool the pump, electric motor, and driver during continuous operation, then temperature increase is suppressed, but device complexity and weight increase
Solution Approach 1:
The patent combines the cooling functions for the pump, electric motor, and driver into a single integrated cooling device. This merging approach suppresses temperature increases in all three components while avoiding the complexity and weight of multiple separate cooling systems, directly resolving the technical contradiction between temperature control and device complexity.
2Temperature
If a cooling device that guides outside air is used, then cooling effect is achieved, but drag increases and aircraft efficiency decreases
Solution Approach 1:
The patent extracts the harmful drag-generating function from the cooling system by eliminating the need to guide outside air through the aircraft body. Instead, it uses an alternative cooling method that achieves temperature control without creating aerodynamic drag, thereby removing the harmful factor while maintaining the beneficial cooling effect.
3Temperature
If separate cooling devices are provided for pump, electric motor, and driver, then each component is cooled effectively, but size and weight of the system increase
Solution Approach 1:
The patent merges the cooling functions for the pump, electric motor, and driver into a single integrated cooling device, thereby achieving effective cooling for all components while significantly reducing the overall weight compared to using separate cooling devices for each component.
4Reliability
If a large piping system is used to supply pressure oil, then pressure oil can be supplied reliably, but size and weight of the apparatus increase
Solution Approach 1:
The patent segments the pressure oil supply system into multiple smaller units (multiple pumps distributed throughout the aircraft), each supplying oil to local actuators. This segmentation approach maintains reliable pressure oil supply while reducing the volume and weight of individual piping systems compared to a single large centralized system.
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 continued actuator operation during central hydraulic power source failures, suppresses temperature increases, and reduces the system's size and weight, preventing efficiency losses and drag, while maintaining aircraft performance.
Implementation Method 1
a cooling device that is installed inside at least one of the wing and a body of the aircraft and that simultaneously cools the backup hydraulic pump, the electric motor, and the driver
Data Source
AI summary
A hydraulic pump is installed inside a wing at which a control surface is provided, and supplies pressure oil to an actuator when a loss or degradation occurs in the function of aircraft central hydraulic power sources. An electric motor is installed inside the wing and drives the backup hydraulic pump. A driver is installed inside the wing and drives the electric motor. A cooling device is installed inside the wing and simultaneously cools the backup hydraulic pump, the electric motor, and the driver.