In some embodiments, provide systems, apparatuses and methods to deliver products using unmanned delivery aircraft. In some embodiments, product delivery system is provided, comprising: an unmanned delivery aircraft configured to deliver a package to a package drop point corresponding to a location of a vehicle at a predefined drive-through station, wherein the delivery aircraft comprises: one or more cameras; an image processor configured to process images captured by the one or more cameras and based on the processing of the images confirm a precise location of the package drop point as defined according to a determined current location and an orientation of the vehicle; and a crane system that supports the first package and lowers the first package to the package drop point relative to the current location and orientation of the vehicle while the delivery aircraft hovers above the vehicle by a threshold distance.

An unmanned aerial vehicle (UAV) for transporting a payload is provided. The UAV comprises a body and one or more propellers rotatably connected to the body. The UAV further comprises a battery mounted to the body. The battery is releasable from the bottom of the UAV. The UAV further comprises a payload container mounted to the body. The payload container is releasable from the bottom of the UAV to a landing platform associated with a UAV station.

A method for assisting the braking of an aircraft on a runway comprises the steps implemented automatically, including: before the landing of the aircraft on the runway, receiving the input, by a crew member of the aircraft, of a target braking distance by a man-machine interface associated with a processing unit, the target braking distance corresponding to a distance between a threshold of the runway and a selected exit of the runway; engaging an automatic optimized braking mode of the aircraft making it possible for the aircraft to attain the target speed when it reaches the selected runway exit; andcontrolling a braking system of the aircraft, while the aircraft is running on the runway, according to this automatic optimized braking mode.

A method and device for generating an optimum vertical path intended to be followed by an aircraft. The device comprises at least one database relating to fixed and moving obstacles, a data entering unit, a data processing unit implementing iterative processing to generate an optimum vertical path between an initial state and a final state as a function of flight strategies, that optimum vertical path being generated in such a manner as to be free of any collision with surrounding obstacles and to conform to energy constraints, and a data transmission link for transmitting that optimum vertical path to at least one user system.

The device includes a reception unit for receiving a target energy including a target altitude and a target speed, a computation unit for computing a target energy state relative to the target energy, a computation unit for computing an energy difference between a final energy state at a final position, a computation unit for computing a dissipation distance making it possible for the aircraft to dissipate this energy difference, a computation unit for computing a limit position situated upstream of the final position, along a future flight trajectory of the aircraft, by the dissipation distance, the limit position being the most downstream position where the aircraft can dissipate the energy difference of the aircraft up to the final position, and an information transmission unit for transmitting at least the limit position to at least one user system.

A method of controlling the flight of an aircraft by automatically controlling the descent phase of an aircraft using a Flight Management System and Flight Guidance System (FMS & FGS) to control the air speed of the air craft and respond to an over speed condition.

Systems and methods for improving sink rate alerting for rotary wing aircraft. In one example, the system includes a radio altimeter that produces an altitude value, a processor that is in signal communication with the user interface device and the radio altimeter. The processor receives an altitude value, a position value for the aircraft and landing zone (LZ) information. The processor determines if the aircraft is on an approach to land at an LZ that is raised above surrounding terrain based on the received position value and LZ information. The processor receives sink rate information for the aircraft and generates a sink rate alert based on the received sink rate information and the aircraft altitude value if the sink rate information is greater than a sink rate value adjusted according to the LZ information. An output device outputs the generated sink rate alert. The LZ information includes an altitude value.

Cockpit display systems and methods for generating navigation displays including landing diversion symbology are provided. In one embodiment, the cockpit display system includes a cockpit monitor and a controller coupled to the cockpit monitor. The controller is configured to assess the current feasibility of landing at one or more diversion airports in a range of an aircraft on which the cockpit display system is deployed. The controller is further configured to assign each diversion airport to one of a plurality of predetermined landing feasibility categories, and generate a horizontal navigation display on the cockpit monitor including symbology representative of the feasibility category assigned to one or more of the diversion airports.

Methods, systems, and apparatus, including computer programs encoded on a computer storage medium, for landing aircrafts with optimal landing spot selection. In one aspect, a method includes initiating an autorotation of an aircraft in response to detecting all engine failure, determining a plurality of flight characteristics and conditions of the aircraft at a time of initiating the autorotation, the plurality of flight characteristics and conditions comprising an aircraft altitude, an aircraft velocity, and wind direction, determining total air-time for glideslope and flare control, and a geographic area within which to land the aircraft by autorotation based on the plurality of flight characteristics and conditions, and controlling the aircraft to land the aircraft by autorotation within the geographic area.

Flight deck systems are provided for integrating braking action information with flight deck runway functions. In one embodiment, the flight deck system includes a cockpit display device on which an airport display, such as a two dimensional or three dimensional Airport Moving Map, is generated. A controller is coupled to the cockpit display device and configured to produce a braking action graphic on the airport display indicative of the current braking action of a first runway approached for usage by the aircraft. The controller may determine the current braking action of the runway from braking action information received over a datalink. Further, in certain embodiments, the controller can assign the current braking action of the runway to a predetermined braking action category and produce the braking action graphic to visually identify the assigned braking action category.