Redundant Hydraulic Actuator Control with Shared Test Pressure
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Solution Overview
Problem
Conventional redundant vehicle control systems require multiple auxiliary pressure sources for pre-flight testing, which are not used during flight and increase weight and cost, while also posing safety risks due to dormant failures.
Innovation Solution
A redundant control system with primary and auxiliary hydraulic stages, where a single auxiliary pressure source can facilitate testing of multiple stages, reducing the number of auxiliary pressure sources needed, and ensuring independent operation of primary stages during flight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple auxiliary pressure sources are provided for each redundant hydraulic stage, then pre-flight testing capability is enabled, but weight and cost increase significantly
Solution Approach 1:
The patent combines multiple auxiliary pressure sources into a single shared auxiliary pressure source that serves all redundant hydraulic stages. This is achieved by providing a single auxiliary pressure source coupled to a common cavity, with selective fluid communication to each stage through control valves, eliminating the need for separate auxiliary sources for each stage while maintaining testing capability.
Solution Approach 2:
The single auxiliary pressure source is designed to serve multiple functions: it can test any individual redundant hydraulic stage independently, and can also test multiple stages simultaneously. The system provides universal testing capability across all stages through a unified auxiliary pressure source rather than dedicated sources for each stage.
2Reliability
If multiple auxiliary pressure sources are provided for each redundant hydraulic stage, then pre-flight testing capability is enabled, but device complexity increases
Solution Approach 1:
The patent merges multiple separate auxiliary pressure source systems into a single integrated auxiliary pressure source system. This consolidation reduces the overall number of components, simplifies the system architecture, and reduces complexity while maintaining the ability to test each redundant stage independently through selective fluid communication pathways.
3Weight of moving object
If a single auxiliary pressure source is used for multiple stages, then weight and cost are reduced, but the ability to test stages independently may be compromised
Solution Approach 1:
The system segments the fluid communication pathways between the single auxiliary pressure source and each redundant hydraulic stage using individual control valves. Each stage can be selectively isolated or connected to the auxiliary pressure source, enabling independent testing of any stage while maintaining a unified auxiliary pressure source architecture.
Solution Approach 2:
Control valves act as intermediaries between the single auxiliary pressure source and each redundant hydraulic stage. These valves enable selective fluid communication, allowing the auxiliary pressure source to independently test any stage by opening the appropriate valve pathways while keeping other stages isolated.
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 reduces the number of auxiliary pressure sources required, decreasing weight and cost while ensuring safe and efficient pre-flight testing and flight operations by utilizing a single auxiliary pressure source for testing multiple stages.
Implementation Method 1
an auxiliary stage operatively coupled to a first actuator piston of the plurality of actuator pistons to move the first actuator piston relative to at least one of the one or more actuator housings when the control system is operating in a ground-operation mode
Implementation Method 2
a plurality of primary stages coupled to the one or more actuator housings, each of the primary stages operatively coupled to move a respective actuator piston relative to at least one of the one or more actuator housings
Data Source
AI summary
Embodiments of the disclosure include a redundant control system for a vehicle. The redundant control system includes first and second actuator pistons mechanically coupled to one another and disposed in respective first and second fluid chambers. The first and second actuator pistons are movable by first and second primary stages. One of the primary stages includes a bypass valve with a pilot valve actuatable in response to movement of the first actuator piston.