Construction and operation of electric or hybrid aircraft
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 components, such as a power source for powering an electric motor, of the electric or hybrid aircraft. The failures that pose a greater safety risk may be monitored and indicated by one or more subsystems without use of programmable components.
1. 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 and alerting of failures of device components of the electric or hybrid aircraft, 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 device component that is supported by the housing and facilitates operation of the electric motor, and
output a first alert to notify of a first condition associated with the device component, the first condition being within a category of conditions which may imminently cause a fatality or a destruction of the housing; 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 device component from communications on the communication bus, and
output a second alert to notify of a second condition associated with the device component.
2. The aircraft monitoring system of claim 1 , wherein the device component comprises a motor controller configured to operate the electric motor.
3. The aircraft monitoring system of claim 1 , wherein the non-programmable components consist of analog or combinational logic electronic components.
4. The aircraft monitoring system of claim 1 , wherein the non-programmable components consist of non-stateful components.
5. The aircraft monitoring system of claim 1 , wherein the non-programmable components are configured to:
activate an indicator supported by the housing to output the first alert, and
inactivate the indicator unless the indicator is outputting the first alert.
6. The aircraft monitoring system of claim 5 , wherein the indicator comprises a light.
7. The aircraft monitoring system of claim 5 , wherein the indicator comprises an audible alarm.
8. The aircraft monitoring system of claim 1 , wherein the first subsystem is not configured to communicate via the communication bus.
9. The aircraft monitoring system of claim 1 , wherein:
the non-programmable components are configured to monitor the device component using a first output from a first sensor; and
the programmable component is configured to monitor the device component using a second output from a second sensor different from the first sensor.
10. The aircraft monitoring system of claim 1 , wherein the non-programmable components are configured to output the first alert to the programmable component or another programmable component supported by the housing, and the programmable component or the another programmable component are configured to activate an electronic device supported by the housing to attempt to address the first condition.
11. The aircraft monitoring system of claim 1 , wherein the non-programmable components are configured to output the first alert to an electronic device remote from the housing.
12. The aircraft monitoring system of claim 1 , wherein the non-programmable components and the programmable component are configured to monitor the device component using a common output from a sensor.
13. The aircraft monitoring system of claim 1 , wherein the first condition is a failure or an overheating of the device component.
14. The aircraft monitoring system of claim 1 , wherein the first condition is the device component being on fire.
15. The aircraft monitoring system of claim 1 , wherein the first alert indicates that a crash of the housing is imminent.
16. The aircraft monitoring system of claim 1 , wherein the second condition is within a category of conditions which may not imminently cause the fatality or the destruction of the housing.
17. The aircraft monitoring system of claim 1 , wherein the programmable component comprises a processor.
18. The aircraft monitoring system of claim 1 , further comprising a display configured to present the second alert.
19. 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;
facilitating, by the device component, operation of the electric motor;
propelling, by the electric motor, the housing;
monitoring, by the non-programmable components, the device component;
outputting, by the non-programmable components, a first alert to notify of a first condition associated with the device component, the first condition being likely to imminently cause a fatality or a destruction of the housing;
monitoring, by the programmable component, the device component from communications on the communication bus; and
outputting, by the programmable component, a second alert to notify of a second condition associated with the device component.
20. The method of claim 19 , wherein the device component comprises a motor controller, and said facilitating comprises operating the electric motor.
21. The method of claim 19 , further comprising:
activating an indicator supported by the housing to output the first alert;
inactivating the indicator when the non-programmable components are not outputting the first alert; and
presenting the second alert on a display supported by the housing.
22. The method of claim 19 , further comprising, responsive to the first alert, activating an electronic device supported by the housing to attempt to address the first condition.