Systems and vehicle are provided. A vehicle system for a vehicle includes: a trajectory selection module configured to select a potential vehicle path relative to a current vehicle movement condition; a trajectory movement condition module configured to estimate a modeled movement condition of the vehicle along the potential vehicle path; a limit comparison module configured to determine whether the modeled movement condition violates vehicle limits; and a violation indicator module configured to generate an indication of impending violation.

Methods, apparatus, and articles of manufacture for a distributed aircraft actuation system are disclosed. An example apparatus includes a non-responsive component detector to determine a position difference between a first position of a first control surface of an aircraft and a second position of a second control surface of the aircraft, the first position lagging the second position, and a command generator, in response to determining that the position difference satisfies a threshold, the command generator is to cease movement of the second control surface at the second position, attempt to move the first control surface to the second position, and cease movement of the first control surface when moved to the second position.

Methods, apparatus, and articles of manufacture for a distributed aircraft actuation system are disclosed. An example apparatus includes a non-responsive component detector to determine a position difference between a first position of a first control surface of an aircraft and a second position of a second control surface of the aircraft, the first position lagging the second position, and a command generator, in response to determining that the position difference satisfies a threshold, the command generator is to cease movement of the second control surface at the second position, attempt to move the first control surface to the second position, and cease movement of the first control surface when moved to the second position.

An aircraft control system 100 including a control assembly 110 having control units, including a first control unit 130 for controlling actuation of the aircraft component during a first time period, using electrical resource 512 from a first electrical resource device 510, and a second control unit 140 for controlling actuation of the aircraft component during a second time period, and a switch mechanism 120 for switching control of the actuation of the aircraft component between the first and second control units, wherein the switch mechanism has a first electrical resource device status input 513 for indicating the status of the first electrical resource device 510 and wherein, the switch mechanism is configured to switch control between the first 130 and second 140 control units based on the first electrical resource device status input 513.

An aircraft control system 100 including a control assembly 110 having control units, including a first control unit 130 for controlling actuation of the aircraft component during a first time period, using electrical resource 512 from a first electrical resource device 510, and a second control unit 140 for controlling actuation of the aircraft component during a second time period, and a switch mechanism 120 for switching control of the actuation of the aircraft component between the first and second control units, wherein the switch mechanism has a first electrical resource device status input 513 for indicating the status of the first electrical resource device 510 and wherein, the switch mechanism is configured to switch control between the first 130 and second 140 control units based on the first electrical resource device status input 513.

Systems and methods for deploying adjacent trailing edge flaps that are part of different flap assemblies of different stiffnesses are disclosed. An exemplary method comprises: deploying a first flap of a first flap assembly having a first stiffness by a first deployment amount and deploying a second flap adjacent the first flap by a second deployment amount where the deployment amount of the first flap part of the flap assembly of lower stiffness is greater than the second deployment amount of the second flap part of the flap assembly of higher stiffness. The difference in deployment amounts may be adapted to improve continuity between the first flap and the second flap when the first and second flaps are deployed and subjected to an aerodynamic load.

Systems and methods for deploying adjacent trailing edge flaps that are part of different flap assemblies of different stiffnesses are disclosed. An exemplary method comprises: deploying a first flap of a first flap assembly having a first stiffness by a first deployment amount and deploying a second flap adjacent the first flap by a second deployment amount where the deployment amount of the first flap part of the flap assembly of lower stiffness is greater than the second deployment amount of the second flap part of the flap assembly of higher stiffness. The difference in deployment amounts may be adapted to improve continuity between the first flap and the second flap when the first and second flaps are deployed and subjected to an aerodynamic load.

A system and a method for a battery power management system for an electric aircraft is disclosed. The system includes at least a flight component of an electric aircraft, at least a battery, wherein the at least a battery is configured power the at least a flight component of the electric aircraft, at least a sensor communicatively connected to the at least a battery and a controller communicatively connected to the at least a sensor. The controller is configured to receive sensor data from the at least a sensor, identify a battery status as a function of the sensor data and a battery threshold, and control the power from the at least a battery to the at least a flight component of the electric aircraft as a function of the battery status, further comprising reducing a torque to the at least a flight component.

A system and a method for a battery power management system for an electric aircraft is disclosed. The system includes at least a flight component of an electric aircraft, at least a battery, wherein the at least a battery is configured power the at least a flight component of the electric aircraft, at least a sensor communicatively connected to the at least a battery and a controller communicatively connected to the at least a sensor. The controller is configured to receive sensor data from the at least a sensor, identify a battery status as a function of the sensor data and a battery threshold, and control the power from the at least a battery to the at least a flight component of the electric aircraft as a function of the battery status, further comprising reducing a torque to the at least a flight component.

An aircraft wing having a main wing and a trailing edge flight control surface movable between a retracted position, a first extended position in which the control surface is positioned rearwardly in the chord wise direction relative to its retracted position, and a second extended position in which the control surface is rotated relative to its retracted position. A closure panel, mounted to the main wing, extends from the main wing to the control surface, to provide an air flow surface between the main wing and control surface, both when the control surface is in its retracted position and its first extended position. The closure panel is movable, relative to the control surface, to an open configuration in which it opens an airflow passage provided between the control surface and an opposed surface of the aircraft wing when the control surface is in its second extended position.