Thrust Reverser Actuation With Electric Pumps and Hydraulic Circuits
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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, construction costs, and potential damage during actuator jams.
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 a main hydraulic circuit is used to power thrust reverser actuators, then the actuators can be powered, but significant power is wasted and components become heavier
Solution Approach 1:
The system divides the hydraulic power supply into separate independent pumps for each actuator group, rather than using a single high-pressure main hydraulic circuit. This segmentation allows each pump to operate at the specific pressure needed for its actuators, avoiding the power wastage of using high-pressure hydraulic fluid when lower pressure suffices.
Solution Approach 2:
The invention changes the pressure parameter from the high pressure of the main hydraulic circuit (3000-5000 psi) to a lower pressure suitable for thrust reverser actuation. By using electrically-driven pumps that generate only the required pressure, the system avoids the energy loss inherent in using high-pressure hydraulic fluid for low-power applications.
2Reliability
If a mechanical synchronization system is used to link actuators, then the actuators are synchronized, but weight increases and damaging loads can be transferred during jams
Solution Approach 1:
The invention replaces the mechanical synchronization system (worm wheels, threaded sections, flex shafts) with an electrical control system. Electric motors driving the pumps can be synchronized through electrical signals, eliminating the need for heavy mechanical linkages between actuators while maintaining synchronization reliability.
Solution Approach 2:
The system introduces an electrical control intermediary that coordinates the operation of multiple independent pumps. Rather than mechanically linking actuators, the control system uses electrical signals to synchronize pump operation, thereby achieving actuator synchronization without the weight and damage risks of mechanical linkages.
3Ease of operation
If electric motors with high inertia are used in electronic actuation systems, then actuators can be controlled, but the system must be built very strongly adding weight and costs to prevent damage during jams
Solution Approach 1:
The invention uses electrically-driven pumps with controllable speed and torque characteristics that can be dynamically adjusted. Unlike high-inertia electric motors that require strong mechanical structures to handle sudden loads, these pumps can be controlled to provide smooth acceleration and deceleration, reducing the need for over-engineered components and reducing overall system weight.
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 the risk of actuator damage, while maintaining efficient operation and synchronization of actuators, thereby improving overall efficiency and reducing construction costs.
Implementation Method 1
a bi-directional electrically-driven pump configured to pump hydraulic fluid through the hydraulic circuit
Implementation Method 2
Conventional hydraulic systems are powered by the aircraft's main hydraulic circuit. The main hydraulic circuit is at a very high pressure (e.g. 3000-5000 psi (21-35 MPa))
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.