Aircraft Thrust Reverser Electro-Hydrostatic Actuation Synchronization
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Solution Overview
Problem
Existing thrust reverser systems for aircraft turbojet nacelles require complex mechanical synchronization systems, which are heavy, complicated, and difficult to install, while also being dependent on hydraulic circuits.
Innovation Solution
An electro-hydrostatic actuation system is introduced, featuring a motor pump and a series of actuators connected via a volumetric flow divider, which ensures synchronization of the actuators without the need for mechanical synchronization systems, thus simplifying installation and reducing weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If mechanical synchronization systems are used to coordinate actuators, then the actuators can be synchronized, but the system becomes heavy and complicated
Solution Approach 1:
The patent replaces mechanical synchronization systems with an electro-hydrostatic actuation system. The motor pump converts electrical energy to hydraulic energy, driving actuators through fluid power transmission. This substitution eliminates complex mechanical linkages, gears, and synchronizing mechanisms while maintaining precise actuator coordination through the incompressibility of hydraulic fluid.
Solution Approach 2:
The patent employs hydraulic actuation where a motor pump generates hydraulic fluid under pressure that is distributed to multiple actuators. The hydraulic system provides inherent synchronization due to the incompressible nature of the fluid, ensuring all actuators move simultaneously and uniformly without requiring additional mechanical synchronization components.
2Reliability
If mechanical synchronization systems are used to coordinate actuators, then the actuators can be synchronized, but the installation becomes difficult
Solution Approach 1:
By replacing mechanical synchronization systems with an electro-hydrostatic system, the patent simplifies installation. The motor pump and hydraulic lines can be independently installed and connected to actuators without requiring precise mechanical alignment or complex assembly procedures. The hydraulic connections are more forgiving and easier to install than mechanical linkages.
3Power
If hydraulic circuits are used to actuate the thrust reverser, then the actuators can be powered, but the system becomes dependent on hydraulic circuits
Solution Approach 1:
The patent uses a motor pump that converts electrical energy directly to hydraulic energy at the point of use. This localized electro-hydrostatic conversion eliminates the need for extensive hydraulic circuits, reservoirs, and centralized hydraulic power systems. The actuators are powered by the hydraulic fluid generated on-demand by the motor pump, reducing hydraulic circuit dependency while maintaining actuator power.
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
The electro-hydrostatic actuation system provides precise synchronization of actuators, reduces installation complexity, and eliminates the need for hydraulic circuits, while maintaining safety and performance standards in the aeronautical field.
Implementation Method 1
electro-hydrostatic actuation system comprising a motor pump
Implementation Method 2
volumetric flow divider having an inlet connected to the motor pump and at least two outlets, each connected to an actuator, the volumetric flow divider being configured to receive a fluid and to supply the fluid to the actuators in a substantially equal flow manner
Data Source
Figure 1
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AI summary
The invention relates to a thrust reverser device for an aircraft turbojet engine nacelle, having an electro-hydrostatic actuation system, the electro-hydrostatic system comprising a motor pump (106) and a first actuation assembly (E) formed by: - a series of at least two actuators (A1, A2) intended to be attached to a movable cover of the thrust reverser and configured to move the movable cover or covers between a retracted position and a deployed position relative to the nacelle; and - a volumetric flow divider (120) having an inlet connected to the motor pump (106) and at least two outlets, each connected to an actuator (A1, A2), the volumetric flow divider (120) being configured to receive a fluid and to supply the fluid to the actuators with a substantially equal flow rate.