Hybrid electric aircraft with gyroscopic stabilization control

A non-transitory computer readable medium comprising computer-executable instructions, which, when executed by one or more processors of a computing system of an aircraft, cause the one or more processors to:

• cause, based at least in part on an orientation of a rotation axis of a turbo-generator of the aircraft relative to an orientation of a prime stability axis of the aircraft, at least one of:
• i) adjustment of the rotation axis relative to the prime stability axis of the aircraft;
• and
• ii) adjustment of a rotational speed of the turbo-generator.

A method of gyroscopic stabilization of an aircraft, the method comprising:

• determining a degree of misalignment between a rotation axis of a turbo-generator of the aircraft and a prime stability axis of the aircraft;
• compare the degree of misalignment to an alignment threshold, wherein the alignment threshold includes a first alignment threshold associated with a first control scheme that controls adjustment of the rotation axis relative to the prime stability axis of the aircraft, and wherein the alignment threshold includes a second alignment threshold associated with a second control scheme that controls adjustment of the rotational speed of the turbo-generator;
• causing, based at least in part on
• between the degree of misalignment to the alignment threshold, one of:
• i) initiating the second control scheme when the degree of misalignment exceeds the second alignment threshold;
• and
• ii) initiating the second control scheme and the first control scheme when the degree of misalignment exceeds the second alignment threshold and the first alignment threshold.