System and method for controlling differential thrust of a blown lift aircraft

A method of controlling an aircraft, comprising:

• receiving, at a computing device, a selected mode setting of a mode control panel, wherein the mode control panel has at least two selectable mode settings and is communicatively coupled to the computing device, and wherein the computing device contains at least one processor configured to control an attitude of the aircraft;
• evaluating a plurality of conditions from a plurality of sensors on the aircraft, the aircraft having a first wing and a second wing, and at least two thrust-producing devices operatively coupled to each of the first wing and the second wing and configured to blow over the first wing and the second wing;
• transmitting a power signal to the at least two thrust-producing devices operatively coupled to each of the first wing and the second wing based at least in part on the evaluation of the plurality of conditions from the plurality of sensors and the selected mode setting of the mode control panel;
• and
• controlling the attitude of the aircraft by selectively operating the at least two thrust-producing devices on each of the first wing and the second wing based on the transmitted power signal.

A non-transitory computer readable medium having instructions stored thereon, wherein the instructions, when executed by at least one processor, cause a computing device to perform operations comprising:

• receiving, at the computing device, a selected mode setting of a mode control panel, wherein the mode control panel has at least two selectable mode settings and is communicatively coupled to the computing device, and wherein the computing device is configured to control an attitude of an aircraft;
• evaluating a plurality of conditions from a plurality of sensors on the aircraft having a first wing and a second wing, and at least two thrust-producing devices operatively coupled to each of the first wing and the second wing and configured to blow over each of the first wing and the second wing;
• transmitting a power signal to the at least two thrust-producing devices operatively coupled to each of the first wing and the second wing based at least in part on the evaluation of the plurality of conditions from the plurality of sensors and the selected mode setting of the mode control panel;
• and
• controlling the attitude of the aircraft by selectively operating the at least two thrust-producing devices on each of the first wing and the second wing based on the transmitted power signal.