Abstract: This is a packing case (40), a set of cutouts and a method of obtaining a case comprising a bottom that forms a half-case (41) obtained from a first cutout and a lid formed from a second cutout, the underside of the bottom being equipped with recesses (19, 85, 108, 109, 110, 111) and the lid comprising at least two tabs (33, 43, 54, 55, 56, 57, 73, 74, 75, 88) bonded onto its top face, in vertical alignment with the recesses of complementary shape. The lid comprises a central panel (20, 37) equipped on its sides with four lateral panels (21, 22, 23, 24, 77, 79, 81) of which two (21, 23) are equipped with end flaps (27, 28, 29, 30) said tabs each being connected to one of said end flaps.

Abstract: The invention relates to a set (22) of blanks for forming a packaging box, a method and a corresponding box. The set includes two corrugated board blanks, namely: a first blank (2?) including flaps connected to one another by first fold lines (9?), one side of said blank having no folds; and a second blank (12?) including panels (13?, 14?, 15?, 16?) connected to one another by third fold lines (19?), the panels of the second blank being stacked respectively on the part of the first blank having no folds. Two non-adjacent flaps (3?, 5?) of the first blank are glued to two respective facing panels (13?, 15?) of the second blank, thereby preventing the relative movement thereof during folding or during the formation of the box when the blanks are wound around a volume having pre-determined dimensions.

Abstract: According to the invention, the elevators (8) and/or the adjustable horizontal stabilizer (6) are operated in such a way that a negative lift (DP2) is generated and a nose-up moment (CDP) is thus created to counter the nose-down moment (CB) resulting from braking. The value of the negative lift (DP2) matches the vertical force exerted by the ground on the front landing gear (12), which force is subject to a reference value (Fav3).

Abstract: The present invention relates to a one-piece blank (14) made of corrugated cardboard for the production of a display case (1), the case, the method and the machine for producing said case. The blank comprises a band (2) of panels (15, 16, 17, 18) connected together in pairs by parallel fold lines (24, 25, 26, 27). The band (2) comprises a precut transverse line (20) making it possible to divide the blank into two half-blanks (21, 22), said transverse line determining on either side and for each parallel fold line (24, 25, 26, 27) two separate portions of fold line (24?, 24?; 25?, 25?; 26?, 26?; 27?, 27?) offset relative to one another in order to make it possible to at least partly compensate for the thicknesses of cardboard when the second half-blank is wrapped over the first half-blank around a mandrel.

Abstract: According to the invention, the elevators (8) and/or the adjustable horizontal stabiliser (6) are operated in such a way that a negative lift (DP2) is generated and a nose-up moment (CDP) is thus created to counter the nose-down moment (CB) resulting from braking. The value of the negative lift (DP2) matches the vertical force exerted by the ground on the front landing gear (12), which force is subject to a reference value (Fav3).

Abstract: The device (1) comprises a means (3) for determining the current weight of the aircraft, a means (4) for calculating a reduced thrust value which is proportional to the said current weight, a means (5) for determining at least one engine command, so that the engines deliver a thrust equal to the said reduced thrust value, and a means (7) for applying this command to those engines of the aircraft which have not failed.

Abstract: The invention concerns a generally parallelepiped corrugated box for packaging and transporting objects, the box comprising a lid formed by a lateral can-band carton including a front wall, a rear wall, and side walls and a top, and a tray forming a base including a central panel comprising four main sides each respectively provided with a first flap. The front and rear flaps are U-shaped and define each with the top a central recess enabling an object in the box to be gripped manually by a user from the side and/or from above. One or several partly precut portions and/or one or several bonding points enable the walls of the lid to be detached from the first flaps of the tray by manual separation resulting from a force applied perpendicularly to the walls.

Abstract: A reference value VRef is arbitrarily selected from the range of possible rotation speeds, the position of the trimmable horizontal stabiliser is angled at least in accordance with the centring, for said value VRef, the deviation between said reference value and the accelerating aircraft speed value VC is determined, and the elevators and/or the trimmable horizontal stabiliser of the aircraft are controlled, prior to rotation, in such a way that said deviation is taken into account.

Abstract: Detection of the overstepping of design loads of an aircraft tailplane may include determining current bending and twisting moments applied to the aircraft. The determined bending and twisting moments are compared with a safety envelope to determine the risk of developing permanent deformations on the tailplane. A determination is made as to whether a structural inspection of the tailplane should be performed based on the comparison result.

Abstract: Detection of the overstepping of design loads of an aircraft tailplane may include determining current bending and twisting moments applied to the aircraft. The determined bending and twisting moments are compared with a safety envelope to determine the risk of developing permanent deformations on the tailplane. A determination is made as to whether a structural inspection of the tailplane should be performed based on the comparison result.

Abstract: An aircraft takeoff process may include applying a pitch command deflecting an adjustable horizontal tailplane of the aircraft by a predetermined angle. Thereafter, the pitch command is corrected in accordance with the deviation between a takeoff rotation speed and a stall reference speed VRref of the aircraft.

Abstract: A method and device for detecting an overstepping of design loads of the fin of an aircraft. The device includes a set of information sources and a section for determining, with the aid of information emanating from the set of information sources, a current bending moment. The device further includes a section for determining, with the aid of information emanating from the set of information sources, a current twisting moment, and a section for carrying out a comparison by comparing the pair formed by the current bending moment and the current twisting moment with a safety envelope representing a chart formed in a plane on the basis of pairs of values of bending and twisting moments and defined so that, for any pair which lies outside the safety envelope, there exists a risk of appearance of permanent deformation on the fin.

Abstract: Method and device for controlling and braking an aircraft running on the ground According to the invention, the aircraft (1) comprises two close undercarriage wheel assemblies (2D, 2G) and two distant undercarriage wheel assemblies (3D, 3G), the biggest of the braking commands (FD, FG) can, under certain conditions, be applied not only to the corresponding two undercarriage wheel assemblies, but also to the close undercarriage wheel assembly corresponding to the smallest braking command.

Abstract: The device (1) comprises a set (2) of information sources, means (3) for determining, with the aid of information emanating from said set (2), a current bending moment, means (5) for determining, with the aid of information emanating from said set (2), a current twisting moment, means (7) for carrying out a comparison by comparing the pair formed by the current bending moment and the current twisting moment with a safety envelope representing a chart formed in a plane on the basis of pairs of values of bending and twisting moments and defined so that, for any pair which lies outside the safety envelope, there exists a risk of appearance of permanent deformations on the fin, and means (10) for determining whether a structural inspection of the fin has to be performed, at least on the basis of the result of said comparison.

Abstract: A process and device for detecting on an aircraft an overshoot of design loads at the level of a structural part of the aircraft. The detection device includes a speed measuring device for measuring an effective speed of the aircraft. A first comparator compares the measured effective speed with a maximum speed relating to the current flight configuration of the aircraft. A vertical load measuring device measures a vertical load factor of the aircraft, and a second comparator compares the measured vertical load factor with a limit value of the vertical load factor. An inspection determining device determines whether a structural inspection needs to be performed at the level of the structural part, based of the results of the first and second comparisons.

Abstract: Process for aiding the takeoff of an aircraft. According to the invention, a reference speed VRref is chosen arbitrarily and the deviation existing between this reference value and the rotation speed value is determined and the elevators and/or the adjustable horizontal tailplane of the aircraft (1) is/are acted upon to take account of said deviation.

Abstract: According to the invention, the aircraft (1) comprises two close undercarriage wheel assemblies (2D, 2G) and two distant undercarriage wheel assemblies (3D, 3G), the biggest of the braking commands (FD, FG) can, under certain conditions, be applied not only to the corresponding two undercarriage wheel assemblies, but also to the close undercarriage wheel assembly corresponding to the smallest braking command.

Abstract: Process and device for detecting on an aircraft an overshoot of design loads at the level of a structural part of said aircraft. The detection device (1) comprises means (2) for measuring an effective speed of the aircraft, means (3) for carrying out a first comparison, by comparing this measured effective speed with at least one maximum speed relating at least to the current flight configuration of the aircraft, means (7) for measuring a vertical load factor of the aircraft, means (8) for carrying out a second comparison, by comparing said measured vertical load factor with at least one limit value of vertical load factor, and means (5) for determining whether a structural inspection needs to be performed at the level of said structural part, at least on the basis of the results of said first and second comparisons.

Abstract: A system for automatically controlling lift augmentation devices of an aircraft, during a phase of take-off by the aircraft, includes a controllable actuator that shifts the lift-augmentation devices, and a control unit for generating control demands to control the actuator to bring the lift-augmentation devices into a defined position. The control unit further includes a detector that detects actual take-off by the air craft and, if appropriate, signals such detection to the control unit. At start of the take-off phase, the lift-augmentation device are brought into a first position, in which they are deployed. The control unit generates, at least when the detector signals the actual take-off, a control demand making it possible to bring the lift-augmentation devices into a second position, in which the lift-augmentation devices are retracted by comparison with the first position.

Abstract: System for automatically controlling lift-augmentation devices of an aircraft during take-off.