摘要:
A rear tail assembly for an aircraft, including a fuselage, a wing and at least one propulsion engine attached in the rear portion of the fuselage located behind the wing along the X longitudinal axis of the aircraft, wherein the aforementioned assembly includes aerodynamic surfaces connected in the rear portion of the fuselage. The tail assembly essentially includes horizontal aerodynamic surfaces and essentially vertical aerodynamic surface arranged so as to form an annular structure including at least one ring attached to the fuselage. At lease one engine is held in the ring formed by the tail assembly. In one embodiment, a central fin is used for defining two rings in the annular structure. In particular embodiments of an aircraft including such a tail assembly, one or two engines can be fitted in the ring area.
摘要:
A method for the determining, on board an aircraft, of an identifier of a communications center with which an aircraft crew wishes to enter into contact, includes the following operations: a) the writing, by the crew, of a radio-communications frequency to a display unit of the cockpit of the aircraft, b) the determining of surroundings of the aircraft, c) the determining of the communications centers situated in these surroundings, d) the comparing of the frequencies of these communications centers with the frequency displayed on the display unit of the cockpit, and f) when the frequency of a communications center is identical to the displayed frequency, the display on the aircraft display unit of the identifier of said communications center having a frequency identical to the displayed frequency.
摘要:
A pitch-oscillation limitation system, applied to an aircraft having main landing gear located toward the center of the aircraft and forward landing gear located under the nose of the aircraft, wherein the system includes means for automatically applying, in the event of sudden braking, time-deferred braking between the wheels of the landing gear under the wings and the wheels of the landing gear under the fuselage, so as to reduce the amplitude of the aircraft's pitching motion.
摘要:
A device and a method for assembling oriented objects, such as parts of a pipeline. The device includes means for rotational displacement about a rotational axis of a first and second base. The first base has a first main axis which is perpendicular to the rotational axis and includes first means for supporting objects that can be displaced in translation along the first main axis. The second base has a second main axis which is perpendicular to the rotational axis and includes second means for supporting objects and a revolving plate device for supporting and orienting one of the objects in an angular manner. The revolving plate device can be displaced in translation in relation to the second supporting means along the second main axis. Visualization means enable at least the rotational angle of the plate and the position of the second base to be visualised.
摘要:
An aircraft includes a fuselage and at least one engine provided with at least one propeller and mounted at a rear part of the fuselage, on the back thereof, with the at least one engine having an axis substantially parallel to the longitudinal axis of the fuselage, where the at least one engine is mounted on the rear part of the fuselage so that the propeller lies forward of the tails, and provided at the rear part of the fuselage, symmetrically with respect to the fuselage, are removable noise masking surfaces configured to occupy either a deployed position in which the removable noise masking surfaces project laterally with respect to the rear part of the fuselage and are positioned plumb with the propeller, or a retracted position in which the removable noise masking surfaces are incorporated into the rear part of the fuselage.
摘要:
An aircraft terrain avoidance system include a device having a first unit knowing a profile of the terrain that is located at the front of the aircraft, a second unit for determining an avoidance trajectory, a third unit which is connected to the first and second units and used to verify if there is a terrain collision risk for the aircraft, a fourth unit for emitting an alarm signal in the event of detection of a collision risk by the third unit, at least one aircraft performance database relating to an avoidance maneuvering gradient which can be flown by the aircraft according to particular flight parameters, and a fifth unit for determining the effective values of the particular parameters during the flight of the aircraft. The third unit is formed such that it is possible to determine the avoidance trajectory according to information received from the database and the fifth unit.
摘要:
A lightning protection system for a composite structure has an outer surface designed to be subject to an air flow. This system has an electrically conductive strip and fasteners from the strip to the structure.Since the structure has holes designed for the fasteners, at least some of these fasteners have an attachment element from the lightning to this structure. This attachment element is inserted into the hole with its top part approximately even with the outer surface of this structure, and the attachment element is in electrical contact with the electrically conductive strip. At least part of the electrically conductive strip is placed within the thickness of the structure and to be connected to the ground.
摘要:
The device for flying an aircraft includes a first unit for determining a control value corresponding to an instruction value representing the actuation of a control member by a pilot, a second unit for determining an effective control value corresponding to the instruction value which is actually applied to the aircraft, a third unit for automatically controlling the aircraft, a fourth unit for computing an auxiliary control value, which is closer to the effective controlled value, and a fifth unit for monitoring the control value and for detecting a pilot induced oscillation, where the automatic control is carried out with the aid of the controlled effective value and the auxiliary control value in the case of the detection of the pilot induced oscillation.
摘要:
An aircraft device includes a rudder, a control unit that applies a deflection instruction to the rudder, a measuring section that measures a recovery characteristic of aircraft movement in response to the rudder deflection instruction, a recorder that records an applied deflection instruction and a corresponding recovery characteristic, and a servo-control that maintains the recovery characteristic. The control unit receives a recovery instruction for a recovery characteristic, which is identifiable for an aerodynamic effect, and generates the rudder deflection instruction induced by the recovery instruction.