Electric Thrust Reverser Actuator Synchronization
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Solution Overview
Problem
Traditional aircraft thrust reverser systems rely on hydraulic actuators, which are heavy, less reliable, and inefficient compared to electric motor systems, leading to suboptimal performance in deploying and retracting thrust reversers during landing.
Innovation Solution
The implementation of a thrust reverser actuator system utilizing multiple electric motors, each controlled by a respective controller communicating with flight computers, enabling synchronous deployment and retraction of thrust reversers through closed-loop electrical synchronization.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If hydraulic actuators are used to deploy and retract thrust reversers, then the system is proven reliable, but the system becomes heavy and less efficient
Solution Approach 1:
The patent replaces hydraulic actuators with electric motor actuators to actuate the thrust reverser. This substitution eliminates the need for hydraulic fluid, reservoirs, pumps, and associated plumbing, thereby significantly reducing system weight while maintaining actuation functionality. The electric motor system provides direct mechanical drive without the intermediary hydraulic fluid transmission.
Solution Approach 2:
The patent extracts and removes the hydraulic system components (hydraulic fluid, reservoir, pumps, valves, and plumbing) from the actuation system, retaining only the essential electric motor and control components. This extraction eliminates the weight penalty associated with hydraulic systems while preserving the core actuation function.
2Reliability
If hydraulic actuators are used to deploy and retract thrust reversers, then the system is established, but the deployment and retraction speed is reduced
Solution Approach 1:
The electric motor actuation system provides faster response times and higher acceleration compared to hydraulic systems. Electric motors can rapidly change torque output and reach full speed quickly, enabling faster deployment and retraction of the thrust reverser blocks. This substitution directly addresses the speed limitation of hydraulic actuators.
3Weight of moving object
If multiple electric motors are used to actuate the thrust reverser, then the system becomes lighter and faster, but the synchronization control becomes complex
Solution Approach 1:
The patent implements feedback control mechanisms where each electric motor is equipped with sensors (such as encoders or resolvers) that provide real-time position and speed information to the control system. The control system continuously monitors the state of each motor and adjusts their operation to maintain synchronization, thereby managing the complexity through intelligent control rather than mechanical coupling.
Solution Approach 2:
The control system serves multiple functions simultaneously: it commands each motor to move, monitors their positions, detects synchronization status, and adjusts operation in real-time. This multi-functional control approach consolidates what could be multiple separate control systems into a single integrated unit, reducing overall system complexity despite the presence of multiple motors.
4Device complexity
If traditional hydraulic systems are used, then the system is simple in design, but it is less efficient and more maintenance-intensive
Solution Approach 1:
The electric motor system eliminates hydraulic fluid transmission, removing the need for hydraulic reservoirs, pumps, filters, and plumbing. This substitution improves efficiency by eliminating energy losses associated with hydraulic fluid compression, leakage, and heat generation, while also reducing maintenance requirements for fluid changes and contamination management.
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 solution provides a lighter, more reliable, and efficient thrust reverser actuation system that is at least 25% lighter and potentially two times faster than traditional hydraulic systems, enhancing aircraft deceleration and reducing brake wear during landing.
Implementation Method 1
a first electrical actuator coupled to the thrust reverser... a second electrical actuator coupled to the thrust reverser
Data Source
AI summary
Thrust reverser actuator systems are disclosed herein. An example apparatus disclosed herein includes a first controller to communicate with a first flight computer and a second flight computer of an aircraft. The example apparatus also includes a second controller to communicate with the first flight computer and the second flight computer. The example apparatus further includes a thrust reverser and a first electrical actuator coupled to the thrust reverser. The first electrical actuator is to be communicatively coupled to the first controller and the second controller. The example apparatus also includes a second electrical actuator coupled to the thrust reverser. The second electrical actuator is to be communicatively coupled to the second controller. The first electrical actuator and the second electrical actuator are to synchronously actuate the thrust reverser.