An integrated asymmetric brake system for an aircraft includes a housing and a control surface actuator arranged in the housing. The control surface actuator includes a torque limiter output member and is operable to selectively deploy and retract a control surface. An asymmetry brake system is arranged in the housing and is operably connected to the control surface actuator and the torque limiter output member. The asymmetry brake system is selectively operable to prevent deployment of the control surface by activating the torque limiter output member upon detecting an asymmetry event. An asymmetry brake test monitor switch is mounted in the housing and operably coupled to the asymmetry brake system. The asymmetry brake test monitor switch is monitored to confirm functionality of the asymmetry brake system prior to flight.
INTEGRATED ASSYMETRY BRAKE MECHANISM
2022-06-23
Patent
Electronic Resource
English
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