A hoist is disclosed. In various embodiments, the hoist includes a torque tube defining a longitudinal axis and having a radially outer surface; a cable drum having a radially inner surface; and a bar spline disposed radially outward of the torque tube and radially inward of the cable drum and configured to transfer a torque from the torque tube to the cable drum.

A flight control system includes a flight control computer operable in a flight state and a ground state. A high demand trim relief logic is operable by the flight control computer in the ground state. The high demand trim relief logic is configured to automatically modify the neutral position of a rotor when a command input to the flight control computer to control the rotor is near an allowable limit.

An impact mitigation system for an aircraft and method of deploying the impact mitigation system is disclosed. A state parameter of the aircraft is obtained. The state parameter is used with an aircraft performance model to determine an acceleration capability of the aircraft. A trajectory of the aircraft is predicted using the state parameter of the aircraft and the acceleration capability of the aircraft. A location of an object with respect to the aircraft is determined and the impact mitigation system is deployed when the predicted trajectory indicates a contact with the object at a predicted contact velocity higher than a threshold velocity at a future time.

A rotary wing aircraft control system includes an airframe, a main rotor assembly supported by the airframe, and a control system arranged in the airframe and operatively connected to the main rotor assembly. The control system includes a flight control computer (FCC), at least one control inceptor device and a touchdown orientation control system. The touchdown orientation control system includes a computer readable program code an FCC to: sense, by a sensor operatively connected to the flight control computer (FCC), an altitude of the rotary wing aircraft relative to a landing surface, determine one of a landing state rearward velocity reference limit value and a landing state lateral velocity reference limit value associated with the altitude, and selectively limit a landing state flight envelope of the rotary wing aircraft to the one of the landing state rearward velocity reference limit value and the landing state lateral velocity reference limit value.

A rotary wing aircraft control system includes an airframe, a main rotor assembly supported by the airframe, and a control system arranged in the airframe and operatively connected to the main rotor assembly. The control system includes a flight control computer (FCC), at least one control inceptor device and a touchdown orientation control system. The touchdown orientation control system includes a computer readable program code an FCC to: sense, by a sensor operatively connected to the flight control computer (FCC), an altitude of the rotary wing aircraft relative to a landing surface, determine one of a landing state rearward velocity reference limit value and a landing state lateral velocity reference limit value associated with the altitude, and selectively limit a landing state flight envelope of the rotary wing aircraft to the one of the landing state rearward velocity reference limit value and the landing state lateral velocity reference limit value.

The present disclosure is directed toward systems and methods for inserting and removing a battery assembly from an unmanned aerial vehicle (UAV) and/or a UAV ground station (UAVGS). For example, systems and methods described herein enable convenient installation of a battery assembly within a UAV. The battery assembly and UAV further include features that facilitate secure connection of the battery assembly within the UAV and which prevents wear due to frequent installation and removal of the battery assembly within a receiving slot of the UAV. In one or more embodiments, the battery assembly includes a housing and one or more connectors having one or more features that cause the battery assembly to self-align when the battery assembly is inserted within the receiving slot of the UAV.

The present disclosure is directed toward systems and methods for inserting and removing a battery assembly from an unmanned aerial vehicle (UAV) and/or a UAV ground station (UAVGS). For example, systems and methods described herein enable convenient installation of a battery assembly within a UAV. The battery assembly and UAV further include features that facilitate secure connection of the battery assembly within the UAV and which prevents wear due to frequent installation and removal of the battery assembly within a receiving slot of the UAV. In one or more embodiments, the battery assembly includes a housing and one or more connectors having one or more features that cause the battery assembly to self-align when the battery assembly is inserted within the receiving slot of the UAV.

A method of determining cable angle includes acquiring image data of a cable and a load coupled to a rotorcraft using three-dimensional (3D) spatial perception system, constructing an image of the cable and load using the image data, and determining the angle of the cable relative to the external load at an interface of the cable and external load based on the image.

A method of determining cable angle includes acquiring image data of a cable and a load coupled to a rotorcraft using three-dimensional (3D) spatial perception system, constructing an image of the cable and load using the image data, and determining the angle of the cable relative to the external load at an interface of the cable and external load based on the image.

The present invention provides a foldable wing which comprises a wing supporting skeleton, a sliding rail, a skin supporting rib, a skin and a wing movement unit. The wing supporting skeleton comprises a horizontal beam, a longitudinal beam, a wing front edge beam, a wing trailing edge beam, a fixture connector and a sliding block, The wing supporting skeleton is a triangular girder for maintaining planar and sectional shapes of the foldable wing, supporting the skin supporting rib and the skin, and sustaining an aerodynamic load from the skin and a load of a fuselage. After the triangular girder is subjected to a force of the wing movement unit, a shape and an area of the triangular girder are changed so as to achieve folding and unfolding of the foldable wing. A rotocraft and a glider using the foldable wing are also provided.