Aircraft Thrust Reverser Electrical Switch for Nozzle Control
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing propulsion systems for aircraft face issues with untimely movement of the variable nozzle during thrust reversal, which can cause malfunctions in the electrical system and affect the thrust reverser, due to inadequate power management between the thrust reverser and variable nozzle actuation devices.
Innovation Solution
A propulsion assembly with an electrical switch that disconnects the variable nozzle from the aircraft's electrical network during reverse jet operation, ensuring the nozzle actuation device is deprived of power and preventing untimely movement, featuring a fixed and movable connector system that cooperates during direct jet operation but not during reverse jet operation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the variable nozzle actuation device remains connected to the electrical network during reverse jet operation, then the nozzle can respond to control signals, but untimely movement occurs causing electrical system malfunctions
Solution Approach 1:
The electrical switch is actuated in advance by the thrust reverser device before the variable nozzle actuation device could potentially receive control signals. This preliminary action disconnects power to the nozzle actuation device, preventing any untimely movement during reverse jet operation while maintaining the ability to control the nozzle during direct jet operation
Solution Approach 2:
An electrical switch acts as an intermediary component between the electrical network and the variable nozzle actuation device. This switch is controlled by the thrust reverser device and selectively connects or disconnects power supply, thereby mediating the potential conflict between thrust reverser operation and nozzle control requirements
2Reliability
If redundant locking systems are added to prevent untimely nozzle movement, then system reliability improves, but device complexity and weight increase
Solution Approach 1:
The control function for preventing untimely nozzle movement is merged into the existing thrust reverser device by using its actuation mechanism to control an electrical switch. This eliminates the need for separate redundant locking systems, reducing device complexity and weight while maintaining system reliability
Solution Approach 2:
The thrust reverser device itself provides the protective function by actuating the electrical switch that controls power to the nozzle actuation device. This self-service approach eliminates the need for additional independent safety systems, simplifying the overall device architecture
Data Source
Figure 1~3
Figure 4~5
AI summary
The invention relates to an aircraft propulsion assembly (1) including a turbojet pod (3) wherein said pod includes a stationary structure and a movable structure (7), including: a thrust reversal device (9) including at least one cover (15) translatable along a substantially longitudinal axis (17) of the pod between a retracted position, corresponding to a direct jet operation of the pod, and a deployed position, corresponding to a reverse jet position of the pod; and a secondary air flow exhaust nozzle (11) including a device (33) for electrically controlling and actuating said nozzle. The propulsion assembly according to the invention is characterized in that the device for controlling and actuating the nozzle includes at least one electrical switch (37) suitable for being closed during a direct jet operation of the pod and moreover suitable for being open during a reverse jet operation of the pod. Said switch includes at least one stationary connector (39) and at least one movable connector (41).