Patent ID: 11939041
Assignee: VOLOCOPTER GMBH
Field: Transport (Mechanical engineering)
Classification: CPC B  G | IPC B  G

Claim 10:
11. A controller (4) for an aircraft (1), the controller comprising:
a first computer (COM) with a first channel, the first computer (COM) is configured for supplying flight influencing units (2.1, . . . , 2.N) of the aircraft (1) via the first channel with control commands (SB) from the first computer (COM), the control commands (SB) originate from or are derived from a pilot input (PE), and
a second channel and a second computer (MON), the second computer (MON) is configured to monitor the first computer (COM), wherein the second computer (MON) is configured to check whether the control commands (SB) are suitable for a given physical state of the aircraft (1) and the pilot input (PE),
the second computer (MON) is configured to determine whether a current navigation state of the aircraft (1) coincides with the pilot input (PE), wherein the pilot input (PE) has been transformed into a desired navigation state of the aircraft (1) within a prescribed deviation, and the second computer (MON) is also configured to generate and output a control signal for controlling the aircraft (1) in dependence on a determination result of the determination;
wherein the second computer (MON) is also configured to check by a reverse control assignment whether the control commands (SB) during an activation of the flight influencing units (2.1, . . . , 2.N) of the aircraft (1) lead to a first force/moment vector which is suitable for the given physical state of the aircraft (1), in that the second computer (MON) is configured to at least one of:
i) compare the first force/moment vector, derived from the control commands (SB), with a second force/moment vector, said second force/moment vector is determined independently of the first force/moment vector,
ii) check for the first force/moment vector whether an axis and/or an amount of a torque contained in the first force/moment vector lies within a prescribed tolerance interval, or
iii) check for the first force/moment vector whether the first force/moment vector coincides with the pilot input (PE) within the prescribed deviation; and

the second computer (MON) is configured to generate and output an adapted control signal for controlling the aircraft (1) in dependence on a checking result according to i) to iii).