Aircraft pod and aircraft comprising same

Abstract

The invention relates to an aircraft pod (54) equipped with a thrust reverser (62) comprising:-at least one longitudinal actuator (86) to activate or deactivate the thrust reverser; -at least one deflection system (72) configured to deflect, in an activated state, an air flow conducted in the pod (54) towards a lateral opening (64) of the pod (54); -at least one orientation system (74) comprising: o at least one lateral deflector (76) configured to be able to orient the air flow deflected by the deflection system (72) towards the upstream end of the pod (54); o, for each longitudinal actuator (86), a hollow longitudinal deflector (90) configured to receive the longitudinal actuator (86) and comprising an aerodynamic profile having a leading edge edge oriented towards the deflection system (72).

Description

Technical Field

[0001] The present application relates to an aircraft pod equipped with at least one thrust reverser (thrust reverser) comprising at least one longitudinal deflector configured to accommodate a longitudinal actuator, and also to an aircraft comprising an aircraft propulsion assembly containing at least one such pod. Background Art

[0002] according to Figures 1 to 3 In the illustrated embodiment, the aircraft 10 includes a plurality of propulsion assemblies 12 positioned below each wing 14 of the aircraft 10 and connected to the wing by a pylon 16. Each propulsion assembly 12 includes a power plant (motorized device) 18 positioned inside a pod 20. The power plant 18 includes a fan having an axis of rotation (symmetry) A18.

[0003] In the following description, the longitudinal direction is parallel to the rotation axis A18. The longitudinal plane is a plane containing the rotation axis A18, and the transverse plane is a plane perpendicular to the rotation axis A18. The concepts of front / upstream and rear / downstream refer to positions with reference to the flow direction of the air flow in the nacelle 20, i.e., the air flow flows from the front (upstream) to the rear (downstream).

[0004] The nacelle 20 has a generally tubular shape and defines, together with the actuator 18 , an annular duct 22 in which the secondary air flow flows. The nacelle 20 comprises an upstream portion 24 and a downstream portion 26 which extends as far as a trailing edge 28 .

[0005] The pod 20 includes a thrust reverser 30, which is positioned at the downstream portion 26 and is configured to be able to be in an active state and an inactive state. In the active state, the thrust reverser deflects at least a portion of the secondary air flow flowing in the annular duct 22 toward the outside and upstream of the pod 20, while in the inactive state, it does not deflect the secondary air flow flowing in the annular duct 22.

[0006] The thrust reverser 30 includes at least one lateral opening 32 ( Figure 3 According to one configuration, the downstream portion 26 of the pod 20 is movable between a first position corresponding to an inactive state of the thrust reverser 30 and a second position corresponding to an active state of the thrust reverser 30, in which the downstream portion 26 is in contact with the upstream portion 24 (e.g. Figure 2 In the second position, the downstream portion 26 is away from the upstream portion 24 to create a lateral opening 32 (as shown in FIG. Figure 3 shown).

[0007] In order to displace the downstream part 26, the thrust reverser 30 includes a plurality of longitudinal actuators 34 connecting the upstream part 24 and the downstream part 26, which are distributed in the circumferential direction of the nacelle and are configured to enable the downstream part 26 to be displaced from front to rear or in the reverse direction (from rear to front) relative to the upstream part 24.

[0008] The thrust reverser 30 includes a deflection system 36 that is configured to be in a retracted position ( Figure 2 In the retracted position, the deflection system 36 does not interfere with the secondary air flow; and in the deployed position (as shown in FIG. 1 ) when the thrust reverser 30 is activated. Figure 3 As shown, in the deployed position, the deflection system 36 disrupts the secondary air flow and directs it towards the lateral opening 32 .

[0009] The thrust reverser 30 further comprises a directional system 38, which is configured to be able to directionalize the air flow deflected by the deflection system 36 toward the outside of the pod and upstream. In addition, the downstream portion 26 comprises a chamber 40 open in the direction toward the upstream portion 24, which is configured to be able to accommodate the directional system 38 and the longitudinal actuator 34. The chamber 40 is defined by an inner wall 26.1 and an outer wall 26.2, which are spaced apart in the direction toward the upstream portion 24 and connected to the trailing edge 28.

[0010] according to Figure 4 In the embodiment shown in FIG. 1 , the directional system 38 comprises a plurality of vane grids 42, called cascades, positioned at the lateral openings 32, each of which comprises a first wall positioned in a substantially longitudinal plane and a second wall positioned in a substantially transverse plane. The second wall is vane-shaped to deflect the air flow leaving the lateral openings 32 towards the upstream. Some of these vane grids 42 are spaced apart to accommodate the longitudinal actuators 34.

[0011] This embodiment is not satisfactory, since the mass (weight) of the vane cascade 42 is not negligible. Furthermore, the fact that the area occupied by the longitudinal actuator 34 is free from the orientation system 38 reduces the efficiency of the thrust reverser 30 . Summary of the invention

[0012] The object of the present invention is to remedy all or part of the disadvantages of the prior art.

[0013] To this end, the object of the present invention is an aircraft pod comprising an upstream end and a downstream end, the pod being configured to be able to direct a flow of air flowing in a longitudinal direction from the upstream end towards the downstream end, the pod comprising at least one thrust reverser comprising:

[0014] - at least one lateral opening, remote from the upstream and downstream ends, passing through the nacelle and defined by an upper edge and a lower edge;

[0015] at least one movable element configured to be able to assume a first position corresponding to an inactive state of the thrust reverser and a second position corresponding to an active state of the thrust reverser, wherein in the first position the movable element blocks (closes) the lateral opening and in the second position the movable element at least partially clears (opens) the lateral opening;

[0016] at least one longitudinal actuator passing through the lateral opening and configured to enable displacement of the movable part;

[0017] - at least one deflection system configured to assume a first position when the thrust reversers are in an inactive state and to assume a second position when the thrust reversers are in an active state, in which position the deflection system disrupts the air flow directed in the nacelle and directs it towards the lateral opening;

[0018] At least one direction system which is designed to be able to direct the air flow deflected by the deflection system.

[0019] According to the present invention, the orientation system comprises:

[0020] - at least one transverse deflector, positioned substantially in a plane perpendicular to the longitudinal direction and configured to be able to direct the air flow deflected by the deflection system towards the upstream end of the nacelle; each deflector comprises a first end and a second end connected to the support at the upper and lower edges of the lateral opening, respectively;

[0021] - for each longitudinal actuator, a hollow longitudinal deflector configured to house the longitudinal actuator and comprising an aerodynamic profile having a leading edge directed towards the deflection system.

[0022] This solution allows limiting the (adverse) impact of the longitudinal actuator on the efficiency of the thrust reverser.

[0023] According to another feature, each longitudinal deflector is connected to each transverse deflector.

[0024] According to another feature, each transverse deflector comprises, for each longitudinal actuator passing through each transverse deflector, a cutout following (along) the contour of the longitudinal deflector and housing the longitudinal actuator in this cutout.

[0025] According to another feature, each longitudinal deflector comprises a first wall and a second wall, each of the first wall and the second wall comprising an inner edge and an outer edge further away from the deflection system than the inner edge, the inner edges of the first wall and the second wall being adjacent to form a leading edge, and the outer edges being spaced apart.

[0026] According to another feature, the longitudinal deflector comprises a third wall connecting the outer edges of the first wall and the second wall.

[0027] According to another feature, the first wall has a first portion extending from the inner edge and having a first radius of curvature and a second portion extending from the outer edge to the first portion and having a second radius of curvature. In addition, the second wall includes a third portion extending from the inner edge and having a third radius of curvature and a fourth portion extending from the outer edge to the third portion and having a fourth radius of curvature.

[0028] According to other features, the third radius of curvature and the fourth radius of curvature are equal; and / or the second radius of curvature and the fourth radius of curvature are equal; and / or the first radius of curvature is significantly smaller (substantially or significantly smaller) than the third radius of curvature.

[0029] According to another feature, the orientation system includes a plurality of lateral deflectors, each of the lateral deflectors including an inner edge and an outer edge.

[0030] According to another feature, the inner edges of the first wall and the second wall of each longitudinal deflector are located at at least one of the inner edges of the transverse deflector.

[0031] According to another feature, the outer edges of the first wall and the second wall of each longitudinal deflector are located at the outer edge of at least one of the transverse deflectors.

[0032] According to another feature, the geometry of the first wall and the second wall is determined according to the desired orientation of the air flow exiting (flowing from) the lateral opening.

[0033] According to another feature, each longitudinal deflector extends between a first end and a second end, with its aerodynamic profile varying between the first end and the second end.

[0034] The invention also relates to an aircraft comprising at least one pod having one of the above-mentioned characteristics. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Other features and advantages will become apparent from the following description of the invention, given by way of example and with reference to the accompanying drawings, in which:

[0036] - Figure 1 This is a perspective view of the vehicle and propulsion assembly.

[0037] - Figure 2 is a cross-sectional schematic diagram showing a propulsion assembly equipped with a thrust reverser in an inactive state according to an embodiment of the prior art,

[0038] - Figure 3 yes Figure 2 A schematic cross-section of the propulsion unit, with the thrust reversers activated, is visible in the figure.

[0039] - Figure 4is a perspective view showing a portion of a thrust reverser according to an embodiment of the prior art,

[0040] - Figure 5 is a side view showing a portion of a propulsion assembly including a thrust reverser in an activated state according to an embodiment of the present invention,

[0041] - Figure 6 is a schematic cross-sectional view showing a propulsion assembly including a thrust reverser in an inactive state according to an embodiment of the present invention,

[0042] - Figure 7 yes Figure 6 A schematic cross-section of the propulsion unit, with the thrust reversers activated, is visible in the figure.

[0043] - Figure 8 is a perspective view showing a portion of a longitudinal deflector configured to accommodate a longitudinal actuator according to an embodiment of the present invention,

[0044] - Fig. 9 is a perspective view showing a part of a directional system of a thrust reverser according to an embodiment of the present invention, viewed from the outside of a nacelle,

[0045] - Fig.10 is a perspective view showing a portion of a directional system of a thrust reverser according to an embodiment of the present invention as viewed from the inside of a nacelle,

[0046] - Fig.11 is a longitudinal cross-sectional view showing a portion of a direction-directing system of a thrust reverser according to an embodiment of the present invention,

[0047] - Fig.12 yes Fig.11 A transverse cross-sectional view of a portion of the orientation system shown. DETAILED DESCRIPTION

[0048] according to Figure 5 , 6 In the embodiment shown in FIG. 7 , the propulsion assembly 50 includes a power plant 52 positioned inside a pod 54. The pod is generally tubular in shape and defines, together with the power plant 52, an annular duct 56 in which the secondary air flow flows. The pod 54 includes an upstream portion 54.1 and a downstream portion 54.2 having a trailing edge 58. The pod 54 has an outer surface F54.

[0049] According to one application, the aircraft comprises at least one such propulsion assembly. Regardless of the embodiment, the pod 54 is tubular and extends between an upstream end and a downstream end. The pod 54 is configured to guide the air flow 60 in a longitudinal direction from the upstream end toward the downstream end.

[0050] The pod 54 includes at least one thrust reverser 62, which is located at the downstream portion 54.2 and is configured to be capable of being in an activated state (e.g. Figure 5 and 7 as shown) and inactive state (as shown) Figure 6 As shown in the figure, in the activated state, the thrust reverser deflects at least a portion of the air flow 60 flowing in the annular duct 56 toward the outside and upstream end of the pod 54, and in the inactivated state, the thrust reverser does not deflect the air flow 60 flowing in the annular duct 56.

[0051] The thrust reverser 62 includes: at least one lateral opening 64, which passes through the pod 54 and is away from the upstream and downstream ends of the pod 54 and is configured to enable the annular duct 56 to communicate with the outside of the pod 54 (particularly its outer surface F54); and at least one movable part 66, which is configured to be in a state corresponding to the inactive state of the thrust reverser 62 (in the state of Figure 6 ) and corresponds to the activation state of the thrust reverser 62 (in Figure 5 and Figure 7 In the first position, the movable part 66 closes the lateral opening 64, and in the second position, the movable part 66 at least partially clears the lateral opening 64. The lateral opening 64 is defined by an upper edge and a lower edge.

[0052] According to one embodiment, the nacelle 54 comprises two lateral openings 64 which are substantially symmetrical with respect to a vertical longitudinal plane passing through the axis of the power plant.

[0053] According to one configuration, the downstream portion 54.2 is a removable O-shaped tubular cover which forms the removable member 66 and which, in the closed position ( Figure 6 ) and the open position ( Figure 5 and Figure 7 The closed position corresponds to the reverse thrust device 62 being in an inactive state, wherein the downstream portion 54.2 is in contact with the upstream portion 54.1 ( Figure 6 ), the open position corresponds to when the thrust reverser 62 is in an activated state, wherein the downstream portion 54.2 is spaced apart from the upstream portion 54.1 to create a lateral opening 64 between the upstream portion 54.1 and the downstream portion 54.2.

[0054] The downstream portion 54.2 comprises an inner wall 68.1 and an outer wall 68.2 which are connected at the trailing edge 58 and which form therebetween a chamber 70 which is open in the direction towards the upstream portion 54.1.

[0055] Of course, the present invention is not limited to this configuration of the moving part 66 .

[0056] The thrust reverser assembly 62 includes at least one deflection system 72 configured to be in a retracted position (eg, Figure 6 ), in which the deflection system 72 does not interfere with the air flow 60 directed by the pod 54; and in which the thrust reverser device 62 is in the deployed position (as shown) when the thrust reverser device 62 is in the activated state. Figure 7 ), in which deployed position the deflection system 72 is deployed in the annular duct 56 , disrupting (interfering with) the air flow 60 and directing it in a radial direction (perpendicular to the longitudinal direction) toward the lateral opening 64 .

[0057] According to an embodiment, the deflection system 72 comprises, for each lateral opening 64, at least one panel 72.1, and for each panel 72.1, at least one hinge 72.2 connecting the panel 72.1 to the nacelle 54 and at least one connecting rod (connecting rod) 72.3 connecting the panel 72.1 to the power unit 52. Of course, the present invention is not limited to this embodiment of the deflection system 72. Thus, each panel may be connected to the power unit 52 via a hinge.

[0058] The thrust reverser 62 further comprises at least one orientation system 74 configured to be able to orient at least a portion of the air flow 60 deflected by the deflection system 72 and exiting through the lateral opening 64. According to one arrangement, the orientation system 74 is positioned at the lateral opening 64.

[0059] According to one arrangement, the orientation system 74 and the chamber 70 are configured such that the orientation system 74 is positioned in the chamber 70 in an inactive state.

[0060] According to an embodiment, the orientation system 74 includes at least one transverse deflector 76, which is generally positioned in a transverse plane and extends between a first end 76.1 and a second end 76.2. Each transverse deflector 76 has a curved inner edge 76.3 and an outer edge 76.4, which are generally in the shape of a circular arc, connecting the first end 76.1 and the second end 76.2, wherein the inner edge 76.3 is closer to the deflection system 72 than the outer edge 76.4. According to one configuration, the inner edge 76.3 and the outer edge 76.4 have a curvature adapted to the curvature of the inner wall 68.1 and the outer wall 68.2 of the downstream portion 54.2 of the pod 54, so that the orientation system 74 can be accommodated in the chamber 70 when the thrust reverser 62 is in an inactive state.

[0061] Each lateral deflector 76 is configured to be able to direct the air flow deflected by the deflection system 72 and exiting the lateral opening 64 in a radial direction and towards the upstream end.

[0062] According to an embodiment, each transverse deflector 76 comprises a blade in the shape of a crown-like portion having a concave curvature in the longitudinal plane (the centre of the radius of curvature being offset towards upstream relative to the transverse deflector 76 ).

[0063] According to one configuration, each lateral deflector 76 has a constant width (the distance between the inner edge 76.3 and the outer edge 76.4) and curvature between its first end 76.1 and second end 76.2. Thus, the air flow leaving the pod 54 is substantially constant around the pod 54. Fig.11 As shown, according to one arrangement, the lateral deflectors 76 have different widths, the width decreasing from upstream towards downstream.

[0064] The number of transverse deflectors 76 and their shape are determined to achieve the same aerodynamic function as the cascades of the prior art, namely to achieve sufficient flow to avoid operational problems of the fan of the power plant 52 and efficiency problems in terms of thrust reversal.

[0065] According to an embodiment, the orientation system 74 comprises at least one support 78 integral with the nacelle 54 , to which each lateral deflector 76 is connected.

[0066] according to Figure 5 In the embodiment shown in FIG. 1 , the support member 78 includes a first column 80.1 and a second column 80.2, which are parallel to each other and to the longitudinal direction, positioned above and below the lateral opening 64, and the first end 76.1 of each lateral deflector 76 is connected to the first column 80.1, and the second end 76.2 of each lateral deflector 76 is connected to the second column 80.2. Regardless of the embodiment, the first end 76.1 and the second end 76.2 of each lateral deflector 76 are connected to the support member 78 at the upper edge and the lower edge of the lateral opening 64, respectively.

[0067] According to one configuration, the support 78 comprises an upstream cross-piece 82, oriented in a direction parallel to the transverse plane and positioned upstream of the lateral opening 64, to which the first upright 80.1 and the second upright 80.2 are connected. The curvature of the upstream cross-piece 82 is substantially the same as the curvature of the nacelle 54. The upstream cross-piece 82 is integral with or integrated into the upstream portion 54.1 of the nacelle 54.

[0068] The support 78 comprises a downstream cross-piece 84 oriented in a direction parallel to the transverse plane and located downstream of the lateral opening 64 . The curvature of the downstream cross-piece 84 is substantially the same as that of the nacelle 54 .

[0069] According to one configuration, the upstream crosspiece 82 and the downstream crosspiece 84 are parallel to each other and connected by the first and second uprights 80.1, 80.2. Thus, the upstream crosspiece 82 and the downstream crosspiece 84 and the first and second uprights 80.1, 80.2 form a frame defining the lateral opening 64.

[0070] The thrust reverser 62 comprises at least one longitudinal actuator 86, which passes through the lateral opening 64 and is configured to displace a movable part 66 and to place it in a retracted state corresponding to the inactive state of the thrust reverser 62, in which the movable part 66 closes the lateral opening 64, and in a deployed state corresponding to the active state of the thrust reverser 62, in which the movable part 66 at least partially clears the lateral opening 64. Each longitudinal actuator 86 is oriented in a direction substantially parallel to the longitudinal direction.

[0071] According to one configuration, each longitudinal actuator 86 is a fluid pressure cylinder (cylinder or jack) and connects the upstream portion 54.1 and the downstream portion 54.2.

[0072] According to one configuration, the thrust reverser 62 comprises a plurality of longitudinal actuators 86 , for example four longitudinal actuators 86 , which are distributed in the circumference of the nacelle 54 and are positioned symmetrically with respect to a vertical longitudinal plane.

[0073] Each longitudinal actuator 86 interferes with a lateral deflector 76 of the orientation system 74. Each lateral deflector 76 includes a cutout 88 ( Fig.12 (see ).

[0074] In order to limit the effect of the longitudinal actuators 86 on thrust reversal (reverse thrust), the orientation system 74 includes, for each longitudinal actuator 86, a hollow longitudinal deflector 90 configured to accommodate the longitudinal actuator 86, which includes an aerodynamic profile having a leading edge 92 oriented toward the deflection system 72. The longitudinal deflector 90 widens in a direction away from the deflection system 72.

[0075] According to one arrangement, each longitudinal deflector 90 passes through the entire lateral opening 64 and has a first end 90 . 1 connected to the upstream cross-piece 82 and a second end 90 . 2 connected to the downstream cross-piece 84 .

[0076] According to an embodiment, each longitudinal deflector 90 includes a first wall 94 and a second wall 96 that form a V-shape in a transverse plane. Each of the first wall 94 and the second wall 96 includes an inner edge 94.1, 96.1 and an outer edge 94.2, 96.2, the outer edge 94.2, 96.2 being opposite the inner edge 94.1, 96.1 and further away from the deflection system 72 than the inner edge 94.1, 96.1. The inner edges 94.1, 96.1 of the first wall 94 and the second wall 96 are adjacent to form a leading edge 92, and the outer edges 94.2, 96.2 are spaced apart so that the first wall 94 and the second wall 96 form a receiving portion 98 for receiving the longitudinal actuator 86.

[0077] According to one configuration, the inner edges 94.1, 96.1 and the leading edge 92 of the first wall 94 and the second wall 96 of each longitudinal deflector 90 are located at at least one of the inner edges of the lateral deflectors 76. The outer edges 94.2, 96.2 of the first wall 94 and the second wall 96 of each longitudinal deflector 90 are located at the outer edge 76.4 of at least one of the lateral deflectors 76.

[0078] according to Figure 8 As can be seen in the construction, the longitudinal deflector 90 includes a third wall 100 which connects the outer edges 94 . 2 , 96 . 2 of the first and second walls to form the longitudinal deflector 90 in a tubular shape.

[0079] According to an embodiment, each longitudinal deflector 90 is connected to each lateral deflector 76. The fact that the longitudinal deflector 90 is connected to the lateral deflector 76 helps to increase the rigidity of the lateral deflectors. According to one configuration, the cutout 88 of each lateral deflector 76 follows (according to) the contour of the longitudinal deflector 90.

[0080] According to one embodiment, the longitudinal deflector 90 has a constant (unchanged) cross section between its first end 90.1 and the second end 90.2. According to another embodiment, the longitudinal deflector 90 has a non-constant (variable) cross section that varies between its first end 90.1 and the second end 90.2, the cross section varying depending on the desired orientation of the air flow leaving the lateral opening 64.

[0081] According to one embodiment, the longitudinal deflector 90 has a cross section that is symmetrical with respect to the longitudinal plane, such as Figure 8 According to another embodiment, the cross-section of the longitudinal deflector is asymmetrical. For example, one of the first wall 94 and the second wall 96 has a convex profile and the other has a profile including a convex portion and a concave portion.

[0082] According to an embodiment, the first wall 94 and the second wall 96 are flat (planar). According to another embodiment, at least one of the first wall 94 and the second wall 96 has a curvilinear (curved) profile.

[0083] According to one configuration, the geometry of the first wall 94 and the second wall 96 may be determined based on a desired orientation (a desired airflow orientation) of the airflow exiting the lateral opening 64. Thus, the longitudinal deflector 90 has an aerodynamic profile that varies between the first end 90.1 and the second end 90.2 based on the desired orientation of the airflow exiting the lateral opening 64.

[0084] according to Fig.12 In the embodiment shown in FIG. 1 , the first wall 94 has a first portion P1 extending from the inner edge 94.1 and having a first radius of curvature and a second portion P2 extending from the outer edge 94.2 to the first portion P1 and having a second radius of curvature. The second wall 96 includes a third portion P3 extending from the inner edge 96.1 and having a third radius of curvature and a fourth portion P4 extending from the outer edge 96.2 to the third portion P3 and having a fourth radius of curvature. According to one configuration, the third radius of curvature and the fourth radius of curvature may be equal. The second radius of curvature and the fourth radius of curvature may be equal. The first radius of curvature is significantly smaller than the third radius of curvature.

[0085] Of course, the present invention is not limited to this geometry of the longitudinal deflector 90 .

Claims

1. An aircraft pod (54) comprising an upstream end and a downstream end, the aircraft pod being configured to direct an air flow (60) flowing in a longitudinal direction from the upstream end toward the downstream end, the pod comprising at least one thrust reverser (62), the thrust reverser (62) comprising: - at least one lateral opening (64) extending through the nacelle (54) remote from the upstream end and the downstream end and defined by an upper edge and a lower edge; - at least one movable component (66), the at least one movable component (66) being configured to be able to assume a first position and a second position, wherein the first position corresponds to an inactive state of the thrust reverser, in which the movable component (66) closes the lateral opening (64); and the second position corresponds to an active state of the thrust reverser (62), in which the movable component (66) at least partially clears the lateral opening (64); - at least one longitudinal actuator (86) passing through the lateral opening (64) and configured to be able to displace the movable part (66); at least one deflection system (72) configured to be in a first position when the thrust reverser (62) is in the inactive state and in a second position when the thrust reverser (62) is in the active state, wherein the deflection system (72) disrupts the air flow (60) directed through the nacelle (54) and directs the air flow (60) toward the lateral opening (64); at least one orientation system (74) configured to orient the air flow (60) deflected by the deflection system (72); Characterized in that the orientation system (74) comprises: at least one transverse deflector (76) situated substantially in a plane perpendicular to the longitudinal direction and configured to be able to direct the air flow deflected by the at least one deflection system (72) towards the upstream end of the nacelle, each deflector (76) comprising a first end (76.1) and a second end (76.2), the first end (76.1) and the second end (76.2) being connected to a support (78) at the upper edge and the lower edge of the lateral opening (64), respectively; The orientation system (74) comprises, for each longitudinal actuator (86): A hollow longitudinal deflector (90) configured to accommodate the longitudinal actuator (86) and comprising an aerodynamic profile having a leading edge (92) oriented towards the deflection system (72).

2. The aircraft pod according to claim 1, characterized in that: Each longitudinal deflector (90) is connected to each transverse deflector (76).

3. The aircraft pod according to claim 2, characterized in that: Each lateral deflector (76) includes a cutout (88) for each longitudinal actuator (86) therethrough, the cutout (88) following the contour of the longitudinal deflector (90) and receiving the longitudinal actuator (86) therein.

4. An aircraft pod according to any one of the preceding claims, characterized in that Each longitudinal deflector (90) includes a first wall (94) and a second wall (96), each of the first wall (94) and the second wall (96) having an inner edge (94.1, 96.1) and an outer edge (94.2, 96.2), the outer edge (94.2, 96.2) being further away from the deflection system (72) than the inner edge (94.1, 96.1), the inner edges (94.1, 96.1) of the first wall (94) and the second wall (96) being adjacent to form the leading edge (92), and the outer edges (94.2, 96.2) being spaced apart.

5. The aircraft pod according to claim 4, characterized in that: The longitudinal deflector (90) comprises a third wall (100) connecting the outer edges (94.2, 96.2) of the first wall (94) and the second wall (96).

6. The aircraft pod according to claim 4 or 5, characterized in that: The first wall (94) has a first portion (P1) extending from the inner edge (94.1) and having a first radius of curvature, and a second portion (P2) extending from the outer edge (94.2) to the first portion (P1) and having a second radius of curvature, and the second wall (96) includes a third portion (P3) extending from the inner edge (96.1) and having a third radius of curvature, and a fourth portion (P4) extending from the outer edge (96.2) to the third portion (P3) and having a fourth radius of curvature.

7. The aircraft pod according to claim 6, characterized in that: The third radius of curvature and the fourth radius of curvature are equal and / or the second radius of curvature and the fourth radius of curvature are equal and / or the first radius of curvature is significantly smaller than the third radius of curvature.

8. The aircraft pod according to any one of claims 4 to 7, characterized in that: The steering system (74) includes a plurality of lateral deflectors (76), each of the lateral deflectors (76) including an inner edge (76.3) and an outer edge (76.4), and the inner edges (94.1, 96.1) of the first wall (94) and the second wall (96) of each longitudinal deflector (90) are located at at least one of the inner edges (76.3) of the lateral deflector (76).

9. The aircraft pod according to any one of claims 4 to 8, characterized in that: The steering system (74) includes a plurality of lateral deflectors (76), each of the lateral deflectors (76) including an inner edge (76.3) and an outer edge (76.4), and the outer edges (94.2, 96.2) of the first wall (94) and the second wall (96) of each longitudinal deflector (90) are located at the outer edge (76.4) of at least one of the lateral deflectors (76).

10. The aircraft pod according to any one of claims 4 to 9, characterized in that: The first wall (94) and the second wall (96) have geometries determined by a desired orientation of air flow exiting the lateral opening (64).

11. An aircraft pod according to any one of the preceding claims, characterized in that Each deflector extends between a first end (90.1) and a second end (90.2), the aerodynamic profile of the deflector varying between the first end (90.1) and the second end (90.2).

12. An aircraft comprising at least one aircraft pod according to any one of the preceding claims.

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