A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector.

A system for in-flight stabilization including a plurality of flight components mechanically coupled to an aircraft, wherein the plurality of flight components includes a first flight component and a second flight component opposing the first flight component. The system further comprises a sensor mechanically coupled to the aircraft, wherein the sensor is configured to detect a failure event of a first flight component. The system comprises a vehicle controller communicatively connected to the sensor and is configured to receive the failure datum of the first flight component from the sensor, generate a failure notification configured to indicate that the vehicle controller received the failure datum from the sensor, and initiate an automatic response as a function of the failure datum. Initiating the automatic response further includes determining an autorotation inducement action for the second flight component to perform and commanding the second flight component to perform the autorotation inducement action.

A system for in-flight stabilization including a plurality of flight components mechanically coupled to an aircraft, wherein the plurality of flight components includes a first flight component and a second flight component opposing the first flight component. The system further comprises a sensor mechanically coupled to the aircraft, wherein the sensor is configured to detect a failure event of a first flight component. The system comprises a vehicle controller communicatively connected to the sensor and is configured to receive the failure datum of the first flight component from the sensor, generate a failure notification configured to indicate that the vehicle controller received the failure datum from the sensor, and initiate an automatic response as a function of the failure datum. Initiating the automatic response further includes determining an autorotation inducement action for the second flight component to perform and commanding the second flight component to perform the autorotation inducement action.

A monolithic attitude control motor frame includes a monolithic structure including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending from the outer surface of revolution. Adjacent cavities of the plurality of cavities share a side wall or side wall portion therebetween. Each of the cavities is configured to receive an attitude control motor. A monolithic attitude control motor system includes a monolithic frame including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending radially from the outer surface of revolution. The system further includes a plurality of attitude control motors corresponding to the plurality of cavities, such that an attitude control motor of the plurality of attitude motors is disposed in each cavity of the plurality of cavities.

A monolithic attitude control motor frame includes a monolithic structure including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending from the outer surface of revolution. Adjacent cavities of the plurality of cavities share a side wall or side wall portion therebetween. Each of the cavities is configured to receive an attitude control motor. A monolithic attitude control motor system includes a monolithic frame including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending radially from the outer surface of revolution. The system further includes a plurality of attitude control motors corresponding to the plurality of cavities, such that an attitude control motor of the plurality of attitude motors is disposed in each cavity of the plurality of cavities.

An aircraft for neutralizing flight comprising a fuselage, at least a power source, a plurality of laterally extending elements attached to the fuselage, a plurality of downward directed propulsors attached to the plurality of laterally extending elements and electrically connected to at least a power source, wherein the plurality of downward directed propulsors have a rotational axis offset from a vertical axis by a yaw-torque-cancellation angle, and a flight controller configured to include a notification unit.

An aerial paint spraying vehicle includes a body and a paint reservoir removably coupled to the body and configured to store paint. The aerial paint spraying vehicle includes a pressure vessel removably coupled to the body and configured to pressurize the paint from the paint reservoir. The aerial paint spraying vehicle includes a paint applicator assembly configured to receive the pressurized paint and expel the pressurized paint through a spray nozzle towards a target surface.

Exhaust redirecting devices are described that are suitable for use in tilt rotor aircraft. Such devices are constructed of light weight material and permit redirection of exhaust gases from turbojet engines of tilt rotor aircraft as nacelles of the aircraft transition between vertical and horizontal flight. Use of a controller permits coordination between exhaust redirection and nacelle position.

An aerial paint spraying vehicle includes a body and a paint reservoir removably coupled to the body and configured to store paint. The aerial paint spraying vehicle includes a pressure vessel removably coupled to the body and configured to pressurize the paint from the paint reservoir. The aerial paint spraying vehicle includes a paint applicator assembly configured to receive the pressurized paint and expel the pressurized paint through a spray nozzle towards a target surface.

A method for controlling an aircraft includes receiving, via a processor of the aircraft, one or more signals indicative of a target attitude and a current attitude of the aircraft, determining, via the processor, an error in attitude based on comparing the target attitude and the current attitude, and generating, via the processor, a command signal for at least one propulsion unit of the aircraft based at least in part on the error in attitude and a feedback loop with angular acceleration feedback.