Shared-Redundancy Actuator Control for Lighter Aircraft Systems
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Solution Overview
Problem
Conventional actuator systems for aircraft require redundant control mechanisms for each actuator, leading to increased weight and complexity.
Innovation Solution
An actuator system with shared redundancy, utilizing a single transfer valve and four electrohydraulic servo valves (EHSVs) to control dual actuators, allowing for backup redundancy and reduced component count.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If each actuator has two redundant control mechanism pairs, then reliability is improved, but weight increases
Solution Approach 1:
The patent merges the redundant control resources of multiple actuators into a shared pool. Instead of each actuator having dedicated redundant control mechanisms, the control mechanisms are shared across multiple actuators, allowing one failed actuator to be controlled by another actuator's control system. This reduces total weight while maintaining reliability through shared redundancy.
Solution Approach 2:
The control mechanisms are designed to serve multiple functions and multiple actuators simultaneously. A single control mechanism can control its native actuator or take over control of another actuator when needed, making the control system universal rather than dedicated to a single actuator.
2Reliability
If each actuator has two redundant control mechanism pairs, then reliability is improved, but device complexity increases
Solution Approach 1:
The patent combines multiple control mechanisms into a shared resource pool that serves multiple actuators. This merging reduces the total number of control mechanisms needed while maintaining reliability through the ability to reallocate control resources between actuators based on operational needs.
Solution Approach 2:
The control system is designed to be dynamic, allowing control mechanisms to be reallocated between actuators based on operational conditions. When an actuator fails, the system dynamically reconfigures to allow another actuator to control the failed one, reducing complexity while maintaining reliability.
3Reliability
If redundant backup control is required for each actuator, then reliability is improved, but volume increases
Solution Approach 1:
The patent merges backup control capabilities across multiple actuators into a shared resource. Instead of each actuator having its own dedicated backup control volume, the backup control resources are shared, reducing total system volume while maintaining the ability to provide backup control when needed.
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 achieves lighter, less complex actuator systems with improved thermal efficiency and reduced weight, volume, and cost by sharing redundant control components.
Implementation Method 1
four electrohydraulic servo valves (EHSVs) to control dual actuators
Implementation Method 2
at least one transfer device (105) configured to be operated to select between a first control mode where the first actuator control device (103a) is operatively connected to the first actuator (101a)
Data Source
Figure 1
Figure 2
AI summary
An actuator system can include a first actuator (101a), a second actuator (101b), a first actuator control device (103a) configured to control the first actuator, a second actuator control device (103b) configured to control the second actuator, a shared redundant actuator control device (103c), and at least one transfer device (105) operatively connected to the first, second, and shared redundant actuator control devices. The at least one transfer device can be configured to be operated to select between a first control mode where the first actuator control device is operatively connected to the first actuator to control the first actuator and the second actuator control device is operatively connected to the second actuator to control the second actuator, a second control mode where the shared redundant actuator control device is operatively connected to the first actuator to control the first actuator and the second actuator control device is operatively connected to the second actuator to control the second actuator, and a third control mode where the first actuator control device is operatively connected to the first actuator to control the first actuator and the shared redundant actuator control device is operatively connected to the second actuator to control the second actuator.