A method of operating an under-actuated actuator system including a plurality of actuators (3), preferably for operating a multiactuator aerial vehicle (1), wherein the actuators (3) are individual propulsion units of the multiactuator aerial vehicle (1), each actuator having a maximum physical capacity u.sup.max, the method including: controlling the actuators (3) by with an actual control input u∈.sup.k computed from an allocation equation u=D.sup.−1u.sub.p, wherein D.sup.−1 is an inverse allocation matrix and u.sub.p∈.sup.m is a pseudo control input defined by a system dynamics equation m(x){umlaut over (x)}+c(x,{dot over (x)})+g(x)+G(x)u.sub.p=f.sub.ext, wherein x∈n is an n-dimensional configuration vector of the system, m(x)∈.sup.n×n is a state dependent generalized moment of inertia, c(x,{dot over (x)})∈.sup.n are state dependent Coriolis force, g(x)∈.sup.n are gravitational forces and f.sub.ext∈.sup.n are external forces and torques, and G(x)∈.sup.n×m is a control input matrix which contains the information of under-actuation. The system is under-actuated if Rank

An actuator assembly includes a primary load path for tightly coupling an actuated surface to a reference structure, and a secondary load path having a backlash portion for coupling the actuated surface to the reference structure with backlash, wherein the secondary load path is unloaded during an operative state of the primary load path and loaded during a failure state of the primary load path. A first sensor is configured to sense relative displacement between a portion of the primary load path and a portion of the secondary load path. A controller is operatively coupled to the first sensor, the controller configured to determine a load on the primary load path based on relative displacement sensed by the first sensor.

An actuator assembly includes a primary load path for tightly coupling an actuated surface to a reference structure, and a secondary load path having a backlash portion for coupling the actuated surface to the reference structure with backlash, wherein the secondary load path is unloaded during an operative state of the primary load path and loaded during a failure state of the primary load path. A first sensor is configured to sense relative displacement between a portion of the primary load path and a portion of the secondary load path. A controller is operatively coupled to the first sensor, the controller configured to determine a load on the primary load path based on relative displacement sensed by the first sensor.

An airborne vehicle having a body section; a main wing extending from the body section configured to generate aerodynamic lift, the main wing having one or more main wing control surfaces; and a tail assembly extending from the body section aft of the main wing. The tail assembly having a first tail member and a second tail member substantially parallel to each other. The first tail member having one or more control surfaces and the second tail member having one or more flap surfaces selectively deployable between a retracted position and an extended position. The flap surfaces being configured to increase a surface area and/or camber of the second tail member in the extended position.

Disclosed are methods, systems, and non-transitory computer-readable medium for controlling an automatic descent of a vehicle. For instance, the method may include: determining whether a descent trigger condition is present; and in response to determining the descent trigger condition is present, performing an automatic descent process. The automatic descent process may include: obtaining clearance data from an on-board system of the vehicle; generating a descent plan based on the clearance data, the descent plan including a supersonic-to-subsonic transition and/or a supersonic-descent to a target altitude; and generating actuator instructions to a control the vehicle to descend to the target altitude based on the descent plan.

Disclosed are methods, systems, and non-transitory computer-readable medium for controlling an automatic descent of a vehicle. For instance, the method may include: determining whether a descent trigger condition is present; and in response to determining the descent trigger condition is present, performing an automatic descent process. The automatic descent process may include: obtaining clearance data from an on-board system of the vehicle; generating a descent plan based on the clearance data, the descent plan including a supersonic-to-subsonic transition and/or a supersonic-descent to a target altitude; and generating actuator instructions to a control the vehicle to descend to the target altitude based on the descent plan.

A method for controlling a hybrid helicopter having at least one lifting rotor, at least one forward-movement propeller and an empennage provided with at least one moveable empennage surface. The method includes the following steps: using a main sensor to determine a current value of a rotor parameter conditioning a current power drawn by the lifting rotor, using an estimator to determine a current setpoint of the rotor parameter, adjusting a position of the moveable empennage surface using a deflection controller as a function of the current value and of current setpoint.

A method for controlling a hybrid helicopter having at least one lifting rotor, at least one forward-movement propeller and an empennage provided with at least one moveable empennage surface. The method includes the following steps: using a main sensor to determine a current value of a rotor parameter conditioning a current power drawn by the lifting rotor, using an estimator to determine a current setpoint of the rotor parameter, adjusting a position of the moveable empennage surface using a deflection controller as a function of the current value and of current setpoint.

A flight control system includes an active control inceptor, a flight control computer, and a force trim release. The active control inceptor includes a control member movable from a first position to a second position to command a vehicle-body rate and including a detent position that holds an attitude. The flight control computer generates a trim command from the second position, a reference position, and a vehicle-body state. With the force trim release selected when the control member is moved from the first position to the second position, the first position is designated as the reference position and the second position is designated as the detent position. Upon deselection of the force trim release with the control member at the second position, the second position is designated as the reference position and the trim command is designated as the detent position.

A system for the prioritization of flight controls in an electric aircraft is illustrated. The system includes a plurality of flight components, a sensor, and a computing device. The plurality of flight components are coupled to the electric aircraft. The sensor is coupled to each flight component of the plurality of flight components. Each sensor of the plurality of sensors is configured to detect a failure event of a flight component of the plurality of flight components and generate a failure datum associated to the flight component of the plurality of flight components. The computing device is communicatively connected to the sensor and is configured to receive the failure datum associated to the flight component of the plurality of flight component from the sensor, determine a prioritization element as a function of the failure datum, and restrict at least a flight element as a function of the prioritization element.