A bypass turbojet engine nacelle that forms a fan casing includes a first, upstream, streamlining element and a second streamlining element that forms a jet pipe. The second element can move translationally between a position ensuring aerodynamic continuity of the nacelle and a downstream position u
A bypass turbojet engine nacelle that forms a fan casing includes a first, upstream, streamlining element and a second streamlining element that forms a jet pipe. The second element can move translationally between a position ensuring aerodynamic continuity of the nacelle and a downstream position uncovering flow reversal openings. A thrust reverser device is housed in the nacelle and includes flow reverser flaps and cascades of vanes providing radial guidance for the flow. The cascades of vanes providing radial guidance for the flow can move in translation along the axis of the nacelle between a retracted position into the first steamlining element and an active flow-guidance position, the second streamlining element being secured to the cascades of vanes, the reverser flaps being mounted to rotate about axes that are transverse with respect to the axis of the nacelle and secured to the cascades of vanes.
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1. A nacelle for a bypass turbojet engine, forming an envelope of a fan, comprising: a first streamlining element, upstream, and a second streamlining element forming a pipe, the second streamlining element being movable in translation between a position in which it ensures aerodynamic continuity of
1. A nacelle for a bypass turbojet engine, forming an envelope of a fan, comprising: a first streamlining element, upstream, and a second streamlining element forming a pipe, the second streamlining element being movable in translation between a position in which it ensures aerodynamic continuity of the nacelle and a downstream position uncovering flow reversal openings;a thrust reverser device accommodated in the nacelle and comprising bypass flow reverser flaps and cascades for radial guidance of flow,wherein the cascades for radial guidance of flow are movable in translation along a length of the axis of the nacelle between a position in which they are retracted into the first streamlining element and an active flow guidance position, the second streamlining element being integral with the cascades, andwherein the bypass flow reverser flaps are fitted to be movable in rotation around transverse axes that are transverse relative to the axis of the nacelle and that are fixed relative to the cascades, the reverser flaps being controlled in rotation by connecting rods having a first extremity articulated on the reverser flaps and a second extremity sliding in a housing of the first streamlining element. 2. A nacelle according to claim 1, wherein the first streamlining element comprises guide rails and the cascades bear against the guide rails to guide the cascades, extending in a downstream direction from an upstream edge of the first streamlining element. 3. A nacelle according to claim 1, wherein the cascades are integral with a synchronizing ring perpendicular to the axis of the engine. 4. A nacelle according to claim 1, wherein the cascades are set in movement in translation by a motor unit accommodated in the first streamlining element. 5. A nacelle according to claim 1, wherein the first streamlining element comprises guide rails for guiding the cascades, extending in a downstream direction from an upstream edge of the first streamlining element, and wherein the connecting rods are guided along a length of guide rails with an arrangement driving pivoting of the connecting rods around an axis perpendicular to the guide rails, and tilting of the bypass flow reverser flaps when the second streamlining element is at a given distance from the first streamlining element, in the downstream position uncovering the flow reversal openings. 6. A turbojet engine comprising a nacelle according to claim 1, wherein the second streamlining element, forming a pipe, creates with a primary flow fairing a flow section that is variable, as a function of an axial position of the second streamlining element. 7. A turbojet engine comprising a nacelle according to claim 1, the second streamlining element forming a pipe creating with a primary flow fairing a flow section that is variable, as a function of axial position of the second streamlining element, and a flow section of which increases when the second streamlining element forming a pipe is driven from its upstream position over a part of its movement in a downstream direction, the thrust reverser device being put in place when the second streamlining element forming a pipe continues its movement in a downstream direction. 8. A nacelle according to claim 1, wherein the cascades include radial fittings, the bypass flow reverser flaps include yokes, and the yokes are traversed by shafts that also pass through the fittings to pivotally attach the bypass flow reverser flaps directly to the cascades. 9. A nacelle according to claim 1, wherein the connecting rods include a shaft with a notch to control rotation of the bypass flow reverser flaps, the first streamlining element comprises guide rails to guide the cascades, and the guide rails include a wheel that rolls between the notch and the shaft of the connecting rods. 10. A nacelle according to claim 9, wherein the notch of the connecting rods does not extend along an entire length of the shaft such that, as the second streamlining element being moves towards the downstream position, the wheel exits the notch and the connecting rods tilt to pivot the bypass flow reverser flaps to the active flow guidance position. 11. A nacelle according to claim 9, wherein the connecting rods extend parallel to the guide rails. 12. A nacelle according to claim 2, wherein the connecting rods extend parallel to the guide rails. 13. A nacelle according to claim 1, wherein the second extremity of the connecting rods extends into the housing that forms an upstream edge of the flow reversal openings, each of the connecting rods including a stop pin to prevent the second extremity from traveling downstream of the housing. 14. A nacelle according to claim 1, wherein the bypass flow reverser flaps are directly attached to the cascades such that the bypass flow reverser flaps pivot around the cascades. 15. A nacelle according to claim 1, wherein the transverse axes are constituted by shafts the pass through fittings that are integral with the cascades. 16. A nacelle according to claim 1, wherein the second extremity of the connecting rods is at an upstream part of the connecting rods that comprises a slide adapted to slide relative to a stop pin, said stop pin being integral with a flow diversion edge of the first streamlining element.
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