摘要:
A rotorcraft provided with an anti-torque tail rotor having a drive axis of constant orientation and having a rotor disk that is arranged mainly to one side of the tail boom of the rotorcraft. A control mechanism for controlling the blades of the tail rotor includes a rotary control plate engaged with the blades and movable by a control rod extending along the drive axis of the tail rotor. The control plate is arranged in a constant mounting plane (PM) and serves to provide permanent cyclic variation in the pitch of the blades. Turning the control rod changes the way in which the cyclical variation of the pitch of the blades is operated between providing a contribution to lift and providing a contribution to propulsion in translation of the rotorcraft, depending on the angular orientation of the control plate in its mounting plane (PM).
摘要:
A single engine rotary wing aircraft is provided including a fuselage having a longitudinal first axis. A main rotor assembly is mounted to the fuselage for rotation about a second axis, perpendicular to the first axis. A tailboom is connected to an empennage. The tailboom is mounted to an end of the fuselage such that the tailboom is laterally offset from the first axis in a first direction. The rotary wing aircraft also includes a propulsion system. The single engine of the propulsion system is laterally offset from the first axis in a second direction opposite the first direction.
摘要:
A method of piloting an aircraft (1) provided with at least one rotary wing (2) and a tail rotor (10) suitable for swiveling to pass reversibly from an anti-torque mode of operation to a propulsion mode of operation, said tail rotor (10) having a plurality of second blades (12) having a second variable pitch and rotating about an axis of rotation (AX), said axis of rotation presenting a first variable salient angle (θ) relative to a first plane (P1). Thus, in the anti-torque mode of operation, said second pitch is controlled using first control means (31). Furthermore, in the propulsion mode of operation, said first salient angle (θ) is controlled using first control means (31) and said second pitch is controlled using second control means (32) for controlling thrust.
摘要:
The present invention discloses a rotor that enables an aircraft to be passively stable in hover. The rotor, having a generally fixed geometry is tiltably connected to its rotor shaft. The outer part of the rotor blades have a pitch fixed relative to the rotational plane, whereas the inner part of the rotor blades have a pitch fixed relative to a reference plane perpendicular to the rotor shaft.
摘要:
A single engine rotary wing aircraft is provided including a fuselage having a longitudinal first axis. A main rotor assembly is mounted to the fuselage for rotation about a second axis, perpendicular to the first axis. A tailboom is connected to an empennage. The tailboom is mounted to an end of the fuselage such that the tailboom is laterally offset from the first axis in a first direction. The rotary wing aircraft also includes a propulsion system. The single engine of the propulsion system is laterally offset from the first axis in a second direction opposite the first direction.
摘要:
A tail assembly (10) for a rotorcraft (20), the tail assembly (10) comprising a first stabilizer (3) extending transversely on either side of an anteroposterior plane (P1), and a second stabilizer (4, 4″) extending in elevation. Two propellers (31, 41) positioned on either side of the anteroposterior plane (P1) provide the rotorcraft (20) with at least part of its yaw control and its propulsion. The axes of the two propellers (31, 41) are situated in a plane substantially parallel to the horizontal plane (P3) and they intersect at a position in the anteroposterior plane (P1) of the rotorcraft (20) that is located between the front end of the rotorcraft (20) and the propellers (31, 41). Using both propellers (31, 41) of the tail assembly (10) simultaneously makes it possible to provide the rotorcraft (20) with longitudinal thrust while conserving its transverse thrust for the anti-torque function, it being possible to control these two thrusts independently.
摘要:
The invention relates to compensation for the torque which is produced by the main rotor (110) of a helicopter (100). The apparatus according to the invention for torque compensation is intended for a helicopter whose main rotor rotates about a rotation axis (RH) during operation and thus produces a torque, which acts on the fuselage (120) of the helicopter and would cause it to rotate. The apparatus comprises a lateral flow fan (200) having a housing (210) and having a rotor (220) which is mounted in the housing, wherein the lateral flow fan is arranged on the tail boom (130) of the helicopter such that it produces a thrust effect (F) during operation which compensates for the torque of the main rotor.
摘要:
A propulsion system comprising independent rotor sub-systems producing a thrust force of a desired magnitude in any desired radial direction from the centre of the propulsion system, driven from a single driveshaft that may be fixed in its position in the vehicle. When the propulsion system is fitted, for example, to a single-main-rotor helicopter in place of the convention anti-torque tail rotor, the helicopter is thereby equipped with a propulsion system that can produce yaw, pitch, the anti-torque lateral thrust for stability in hover, aft thrust or drag as well as the direct forward thrust that will enable the helicopter to fly at higher speeds. The propulsion system may also be applied in other aeronautical systems as well as to marine and industrial systems to impart energy into a fluid and thereby induce movement in that fluid.
摘要:
A rotorcraft provided with an anti-torque tail rotor having a drive axis of constant orientation and having a rotor disk that is arranged mainly to one side of the tail boom of the rotorcraft. A control mechanism for controlling the blades of the tail rotor includes a rotary control plate engaged with the blades and movable by a control rod extending along the drive axis of the tail rotor. The control plate is arranged in a constant mounting plane (PM) and serves to provide permanent cyclic variation in the pitch of the blades. Turning the control rod changes the way in which the cyclical variation of the pitch of the blades is operated between providing a contribution to lift and providing a contribution to propulsion in translation of the rotorcraft, depending on the angular orientation of the control plate in its mounting plane (PM).