Aircraft monitoring system and method for electric or hybrid aircrafts
AssigneeH55 SA
InventorsSébastien Demont, Bastian Dani
Life of this patent
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Abstract
This disclosure describes at least embodiments of an aircraft monitoring system for an electric or hybrid airplane. The aircraft monitoring system can be constructed to enable the electric or hybrid aircraft to pass certification requirements relating to a safety risk analysis. The aircraft monitoring system can have different subsystems for monitoring and alerting of failures of a component, such as a battery pack, a motor controller, and/or a motors. The failures that pose a greater safety risk may be monitored and indicated by one or more subsystems without use of programmable components.
Claims20
An aircraft monitoring system for an electric or hybrid aircraft, the aircraft monitoring system being constructed to enable the electric or hybrid aircraft to pass certification requirements relating to a safety risk analysis, the aircraft monitoring system having different subsystems for monitoring a plurality of parameters measured during operation of the electric or hybrid aircraft and for alerting of an out-of-limit parameter, failures that pose a greater safety risk being monitored and indicated by one or more subsystems without use of programmable components, the aircraft monitoring system comprising:
- a first subsystem configured to be supported by a housing and consisting of non-programmable components, the housing being configured to fly and be propelled by an electric motor,
- wherein the non-programmable components are configured to:
- monitor a plurality of parameters associated with operation of the electric motor,
- detect a first condition from one of the plurality of parameters failing to satisfy a first threshold, the first condition being within a category of conditions which may imminently cause a fatality or a destruction of the housing, and
- output a first alert to notify of the first condition;
- and
- a second subsystem configured to be supported by the housing and comprising a programmable component and a communication bus,
- wherein the programmable component is configured to:
- monitor the plurality of parameters from communications on the communication bus,
- detect a second condition from the one of the plurality of parameters failing to satisfy a second threshold, and
- output a second alert to notify of the second condition.
A method of operating an aircraft monitoring system of an electric or hybrid aircraft, the aircraft monitoring system being constructed to enable the electric or hybrid aircraft to pass certification requirements relating to a safety risk analysis, the method comprising:
- supporting a first subsystem, a second subsystem, a device component, and an electric motor with a housing that is configured to fly,
- wherein the first subsystem consists of non-programmable components, and the second subsystem comprises a programmable component and a communication bus;
- propelling, by the electric motor, the housing;
- monitoring, by the non-programmable components, a plurality of parameters associated with operation of the electric motor;
- detecting, by the non-programmable components, a first condition from one of the plurality of parameters failing to satisfy a first threshold, the first condition being likely to imminently cause a fatality or a destruction of the housing;
- outputting, by the non-programmable components, a first alert to notify of the first condition;
- monitoring, by the programmable component, the plurality of parameters from communications on the communication bus;
- detecting, by the programmable component, a second condition from one of the plurality of parameters failing to satisfy a second threshold;
- and
- outputting, by the programmable component, a second alert to notify of the second condition.
Dependencies are inferred from the claim text.