Aircraft Control Surface Actuation Independent Testing Interface
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Solution Overview
Problem
Current aircraft control surface actuation systems require inputs from multiple flight control systems, making it difficult and complex to rig and test control surfaces like spoilers early in the manufacturing process, and pose safety risks due to potential miscommunication between technicians.
Innovation Solution
A control surface actuation system comprising a test interface and a controller with an interface cable, allowing independent operation of control surface actuators without relying on other flight control systems, enabling earlier testing and reducing the need for hydraulic fluid filling and bleeding, while allowing technicians to operate safely and efficiently.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If control surface actuators are integrated with multiple flight control systems, then system reliability is improved, but device complexity and difficulty of testing increase
Solution Approach 1:
The system is divided into independent functional modules: the flight control system, the test system, and the actuator. The test interface cable assembly provides a separate testing pathway that does not require integration with the flight control system, allowing independent testing while maintaining system integrity.
Solution Approach 2:
The test interface cable assembly acts as an intermediary device that connects the controller to the actuator line independently of the flight control system. This intermediary testing mechanism allows technicians to test actuators without engaging the complex flight control system, reducing testing complexity while maintaining reliability.
2Reliability
If control surface actuators are integrated with multiple flight control systems, then system reliability is improved, but manufacturing and testing time increase
Solution Approach 1:
The actuator line is pre-installed and can be independently tested using the test interface cable assembly before full system integration. This preliminary testing allows manufacturing progress to continue without waiting for complete flight control system integration, reducing overall manufacturing time while ensuring reliability through proper testing.
Solution Approach 2:
The testing process is segmented into independent phases: initial actuator testing via the test interface cable assembly, followed by integrated flight control system testing. This segmentation allows parallel processing and reduces the total time required for manufacturing and testing.
3Reliability
If technicians use integrated flight control systems to operate control surfaces, then comprehensive system testing is achieved, but safety risks increase due to potential miscommunication
Solution Approach 1:
The test interface cable assembly serves as a safe intermediary for initial actuator operation during rigging. This dedicated testing interface eliminates the risk of inadvertent spoiler commands by providing a isolated testing pathway that does not trigger flight control system responses, while still allowing comprehensive actuator functionality verification.
Solution Approach 2:
The testing function is extracted from the integrated flight control system and placed into a separate, dedicated test interface. This extraction allows technicians to safely operate control surfaces during manufacturing without the complexity and safety risks of the full flight control system, while maintaining the ability to perform comprehensive testing.
Data Source
AI summary
Aircraft control surface actuation systems and methods are described herein. An example control surface actuation system includes an interface cable, a test interface, and a controller. The test interface is to be disposed in an electrical equipment (EE) bay of an aircraft and operatively coupled to an actuator associated with a control surface of the aircraft. The interface cable is to be connected between the test interface and the controller, and the controller is to transmit a signal via the interface cable to the test interface to control the actuator.