The present invention relates to A power margin indicator device constituting a first limitation indicator for a rotorcraft, for providing a pilot of said rotorcraft with information about a power margin available on at least one engine and a main power transmission gearbox of said rotorcraft as a function of flying conditions, said device comprising: input means for collecting input data corresponding various operating parameters of said at least one engine and of said MGB; calculation means connected to said input means, said calculation means serving to determine a collective pitch margin for the blades of a rotor of said rotorcraft; and display means presenting said collective pitch margin.

A method and control system that implements a particular aircraft harnessing for an aircraft is provided. The control system includes an effector Line-Replaceable Unit (LRU) including a first connection port, a second connection port, and a first interconnect wire internally connecting the first connection port and the second connection port, a first control LRU connected using a first harnessing to the effector LRU, and a second control LRU connected using a second harnessing to the effector LRU, wherein the first control LRU and the second control LRU are configured to communicate using the first interconnect wire in the effector LRU.

A method and control system that implements a particular aircraft harnessing for an aircraft is provided. The control system includes an effector Line-Replaceable Unit (LRU) including a first connection port, a second connection port, and a first interconnect wire internally connecting the first connection port and the second connection port, a first control LRU connected using a first harnessing to the effector LRU, and a second control LRU connected using a second harnessing to the effector LRU, wherein the first control LRU and the second control LRU are configured to communicate using the first interconnect wire in the effector LRU.

Disclosed is a method and apparatus for detecting and ranging cloud features. The method comprises: obtaining image data(e.g. using a camera (200); classifying, as a cloud feature, an image segment (502-508) of the image data; determining a plurality of moments of the image segment (502-508); using the determined plurality of moments, determining a geometric representation of that image segment (502-508); and, using the geometric representation, determining a distance between the cloud feature represented by that image segment (502-508) and an entity that obtained the image data.

Disclosed is a method and apparatus for detecting and ranging cloud features. The method comprises: obtaining image data(e.g. using a camera (200); classifying, as a cloud feature, an image segment (502-508) of the image data; determining a plurality of moments of the image segment (502-508); using the determined plurality of moments, determining a geometric representation of that image segment (502-508); and, using the geometric representation, determining a distance between the cloud feature represented by that image segment (502-508) and an entity that obtained the image data.

A system, a method and instructions embodied on a non-transitory computer-readable storage medium that solve a 3D point-in-polygon (PIP) problem is presented. This system projects polygons that comprise a set of polyhedra onto projected polygons in a reference plane. Next, the system projects a data point onto the reference plane, and performs a 2D PIP operation in the reference plane to determine which projected polygons the projected data point falls into. For each projected polygon the projected data point falls into, the system performs a 3D crossing number operation by counting intersections between a ray projected from the corresponding data point in a direction orthogonal to the reference plane and polyhedral faces corresponding to projected polygons, to identify polyhedra the data point falls into. The system then generates a visual representation of the set of polyhedra, wherein each polyhedron is affected by data points that fall into it.

A system, a method and instructions embodied on a non-transitory computer-readable storage medium that solve a 3D point-in-polygon (PIP) problem is presented. This system projects polygons that comprise a set of polyhedra onto projected polygons in a reference plane. Next, the system projects a data point onto the reference plane, and performs a 2D PIP operation in the reference plane to determine which projected polygons the projected data point falls into. For each projected polygon the projected data point falls into, the system performs a 3D crossing number operation by counting intersections between a ray projected from the corresponding data point in a direction orthogonal to the reference plane and polyhedral faces corresponding to projected polygons, to identify polyhedra the data point falls into. The system then generates a visual representation of the set of polyhedra, wherein each polyhedron is affected by data points that fall into it.

An aircraft cockpit module (10) that incorporates, on the one hand, a single pilot seat (12) and, on the other hand, at least a part of the piloting equipment and controls necessary for flying an aircraft, the module (10). The aircraft cockpit module forms an assembly which can be moved unitarily and to be incorporated in a single operation in an aircraft cockpit. The module is dedicated to a single pilot and makes it possible to simplify the integration of the cockpit.

An aircraft cockpit module (10) that incorporates, on the one hand, a single pilot seat (12) and, on the other hand, at least a part of the piloting equipment and controls necessary for flying an aircraft, the module (10). The aircraft cockpit module forms an assembly which can be moved unitarily and to be incorporated in a single operation in an aircraft cockpit. The module is dedicated to a single pilot and makes it possible to simplify the integration of the cockpit.

Internal interchangeable modular avionics platform assemblies and methods for removably mounting and interchanging modular avionics platforms within an aircraft. In some embodiments, modular avionics platform assemblies may include a modular avionics platform configured to support various avionics equipment, suitable for removable mounting within a forward fuselage, and interchangeable with a number of alternate platforms. A platform may include a frame structure, and mounting pins and a connector assembly disposed on the frame structure. The mounting pins may project outwardly from the frame structure to align with and detachably secure to corresponding airframe members of an aircraft when the frame structure is in a mounted position. The connector assembly may be disposed on the frame structure and have a plurality of connectors, including connectors for alternating current, direct current, and data. In some embodiments, the platform may also include an environmental cooling system disposed on the frame structure.