Abstract: A configuration system (80) arranged to configure an aircraft in a single-pilot mode and a two-pilot mode, comprising: acquisition means (84) and authentication means (83) arranged to acquire and authenticate a configuration order that defines the selected mode and controls the configuration system (80) to configure the aircraft in the selected mode; first activation means (85) arranged to activate equipment dedicated to piloting by a single-pilot on board when the aircraft is configured in single-pilot mode, and to deactivate dedicated equipment when the aircraft is configured in two-pilot mode; verification means (87) arranged to, when the aircraft is configured in the single-pilot mode, verify that single-pilot flight conditions are met and inform the sole pilot on board and a ground station of the results of these checks.

Abstract: According to various embodiments, there is provided a grinding module including a base; a cylinder mounted to the base with a longitudinal axis of the cylinder arranged at least substantially perpendicular to a surface of the base, wherein the cylinder is rotatable about the longitudinal axis of the cylinder, and wherein a cylindrical surface of the cylinder is adapted to receive a grinding belt; a linear actuator mounted to the base with a centreline of linear motion of the linear actuator arranged to intersect the longitudinal axis of the cylinder; and a holder connected to the linear actuator, the holder adapted to hold a workpiece with a surface of the workpiece facing the cylindrical surface of the cylinder, wherein the linear actuator is adapted to move the holder relative to the cylinder along the centreline of linear motion of the linear actuator, and wherein the cylindrical surface of the cylinder is adapted to define a curved profile so that the grinding belt is adapted to grind and shape the surfac

Abstract: An aerial vehicle may include a first wing structure. The aerial vehicle may further include a first propeller and a second propeller disposed along the first wing structure. The aerial vehicle may further include a second wing structure disposed to intersect the first wing structure to form a cross configuration. The aerial vehicle may further include a third propeller and a fourth propeller disposed along the second wing structure. In a hovering orientation of the aerial vehicle, respective propeller rotational axes of the first and second propellers may be angled off-vertical in respective planes which may be perpendicular to a transverse axis of the first wing structure, and respective propeller rotational axes of the third and fourth propellers may be angled off-vertical in respective planes which may be perpendicular to a transverse axis of the second wing structure.

Abstract: An aerial vehicle including a first wing structure and a second wing structure which intersects the first wing structure perpendicularly at a position offset from a midpoint of a transverse axis of the first wing structure in a direction towards a first wingtip of the first wing structure. The aerial vehicle may further include a first set of at least two propellers with respective propeller rotational axes disposed side-by-side along a portion of the first wing structure extending between the midpoint of the transverse axis of the first wing structure and a second wingtip of the first wing structure. The aerial vehicle may further include a second set of at least two propellers with respective propeller rotational axes disposed side-by-side along a first portion of the second wing structure extending from a first surface of the first wing structure.

Abstract: A method and system for generating a set of values for respective ones of a set of parameters used in determining rotor blade profiles for a coaxial rotor system. The method includes establishing (302) a ratio of respective desired thrusts of an upper rotor (102, 602) and a lower rotor (104, 604) of the coaxial rotor system based on a desired performance of the coaxial rotor system, and determining (304) the set of values of the set of parameters from the desired thrusts ratio based on a torque balance condition between the upper rotor and the lower rotor of the coaxial rotor system.

Abstract: An apparatus for launch and recovery of an Unmanned Aerial Vehicle (UAV), a method for launching a UAV, a method for recovering a UAV and a kit of parts for launch and recovery of a UAV. The apparatus comprises a boom having a center member for receiving the UAV, and first and second arm members extending outwardly and upwardly from the center member, wherein the boom is configured to be lifted to a predetermined height into the air from a reference point; and wherein the boom is movable in the air to an operating position forward of the reference point.

Abstract: Various embodiments provide a portable electronic device holder (400, 500, 600, 700, 900, 1100, 1400) for a passenger seat (202), including a longitudinal clamping structure (420, 520) having a generally L-shaped cross-section. The clamping structure includes a supporting flap (422, 522) forming an L-base of the generally L-shaped clamping structure and configured to support a portable electronic device, and a clamping flap (424, 524) forming an L-leg of the generally L-shaped clamping structure and configured to clamp the portable electronic device against a surface (650) abutting the portable electronic device. The portable electronic device holder further includes a mounting element (410, 510) for slidably or titlably mounting the clamping structure to the passenger seat.

Abstract: An apparatus and method for aerial recovery of an unmanned aerial vehicle (UAV) are provided. The apparatus includes a rigid base having a first section and a second section, wherein the first section is securely mounted to a floor of an aircraft. The apparatus further includes a servicing platform moveably mounted to the base and configured to move along a direction parallel to a longitudinal axis of the aircraft such that in an extended position, the servicing platform at least partially protrudes from a rear cargo door of the aircraft, wherein the servicing platform comprises a capturing mechanism configured to capture the UAV in the extended position.

Abstract: Various embodiments provide a method for installing a seat suspension on a seat frame having a first side frame member and a second side frame member opposed to and spaced apart from each other. The method may include moving a retainer on a first side of the seat suspension in a direction substantially perpendicular to a plane defined by the first and second side frame members for fastening onto a support member on the first side frame member; and moving a retainer on a second side of the seat suspension in the direction substantially perpendicular to the plane defined by the first and second side frame members for fastening onto a support member on the second side frame member. The second side of the seat suspension is opposed to and spaced apart from the first side of the seat suspension.

Abstract: A seat structure for a passenger seat, and a passenger seat. In one embodiment, the seat structure comprises a seat pan for mounting on a frame structure of the passenger seat in a manner such that the seat pan is moveable in forward and backward directions relative to the frame independently from movement of a seat back of the passenger seat; and biasing means for biasing the seat pan in a default position.