Thrust Reverser Actuation With Bi-Directional Pump Synchronization
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Solution Overview
Problem
Conventional thrust reverser actuation systems for jet propulsion engines are inefficient due to high power requirements, complex synchronization systems, and excessive weight, leading to power wastage and increased construction costs.
Innovation Solution
A thrust reverser actuation system utilizing bi-directional electrically-driven pumps to power hydraulically-driven actuators, eliminating the need for high-pressure hydraulic circuits and complex synchronization systems, and simplifying control mechanisms.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If conventional hydraulic systems are used to power thrust reverser actuators, then sufficient actuation power is provided, but significant power wastage occurs due to high pressure requirements
Solution Approach 1:
The system divides the hydraulic power supply into separate segments: the aircraft's main hydraulic system and individual pump units for each actuator. Each actuator has its own pump that draws from a common low-pressure reservoir, eliminating the need to use the high-pressure main hydraulic system for thrust reverser actuation.
Solution Approach 2:
A common hydraulic reservoir serves as an intermediary between the aircraft's hydraulic system and the individual actuator pumps. This reservoir stores hydraulic fluid at low pressure, and the pumps draw from it to provide the necessary high pressure locally at each actuator, avoiding direct connection to the high-pressure main system.
2Power
If conventional hydraulic systems operate at high pressure, then sufficient power is available, but components must be constructed to handle higher pressures leading to weight gains
Solution Approach 1:
The hydraulic power delivery is segmented into distributed pump units, each serving an individual actuator. This allows each component to be sized for the specific power requirements of its actuator rather than being designed for the full system's maximum power demand, reducing overall component size and weight.
Solution Approach 2:
High pressure is generated locally at each actuator by its own pump unit, rather than distributing high pressure throughout the entire system. This allows components to be optimized for local requirements, using smaller, lighter components that only need to handle the pressure and flow needed for their specific actuator.
3Reliability
If mechanical synchronization systems are used to coordinate actuators, then actuator synchronization is achieved, but weight is added to the system
Solution Approach 1:
The system replaces mechanical synchronization linkages with an electronic control system. A control unit receives signals and independently controls each pump unit's operation, eliminating the need for mechanical connections between actuators while maintaining synchronization through electronic coordination.
Solution Approach 2:
An electronic control unit serves as an intermediary between the pilot's input and the individual actuator pumps. This control unit coordinates the operation of multiple pumps independently, achieving synchronization through electronic signaling rather than mechanical linkages.
4Reliability
If mechanical synchronization systems are used, then actuator coordination is ensured, but complex linkages are required between actuators
Solution Approach 1:
Complex mechanical linkages between actuators are replaced with an electronic control system. The control unit independently manages each pump unit through electronic signals, eliminating the need for physical synchronization mechanisms while maintaining coordinated actuator operation.
Solution Approach 2:
The synchronization function is segmented and distributed to individual electronic control units that manage each pump independently. This modular electronic approach replaces the monolithic mechanical synchronization system, reducing complexity while maintaining coordination through independent but synchronized control.
5Ease of manufacture
If electronic systems with electrical motors are used, then no hydraulic fluid is required, but complex controls are needed to prevent actuator damage
Solution Approach 1:
The system uses hydraulics at the actuator level through pump units that convert electrical energy to hydraulic pressure locally. This hybrid approach combines the simplicity of electrical control with the effectiveness of hydraulic actuation, avoiding the need for complex electronic controls while eliminating the need for the aircraft's main hydraulic system.
Solution Approach 2:
The control unit acts as an intermediary that simplifies the interface between electrical control signals and hydraulic actuation. It manages the operation of multiple independent pump units through straightforward electronic control, avoiding the need for complex control algorithms while maintaining precise actuator coordination.
6Power
If conventional hydraulic systems are used, then actuation power is sufficient, but construction costs increase due to heavy-duty components
Solution Approach 1:
Each actuator system is designed with local quality in mind, using components sized and rated for the specific power requirements of that actuator rather than the maximum system requirements. This allows for more economical component selection and reduces overall construction costs while maintaining sufficient actuation power.
Solution Approach 2:
The system is segmented into independent actuator-pump units, each with components sized for its specific requirements. This modular approach allows for more efficient use of materials and reduces the need for over-engineered heavy-duty components throughout the entire system, lowering construction costs.
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 system reduces weight, power consumption, and complexity, while preventing actuator damage from synchronization issues, and enhances operational efficiency by using bi-directional pumps to control the direction of actuation.
Implementation Method 1
a bi-directional electrically-driven pump configured to pump hydraulic fluid through the hydraulic circuit
Data Source
AI summary
A thrust reverser actuation system for a jet propulsion engine for a vehicle, the thrust reverser actuation system comprising: a plurality of hydraulically-driven thrust reverser actuators for actuating one or more thrust reverser components of the jet propulsion engine, each actuator comprising: a hydraulic circuit; and a bi-directional electrically-driven pump configured to pump hydraulic fluid through the hydraulic circuit, wherein the hydraulic circuit and the pump are configured such that the direction of the pump dictates the direction of the actuation of the actuator.