Aircraft equipped with two windshields offering optimized visibility.
The aircraft's dual windshields with developable surfaces and single curvature address visibility, bird resistance, and anti-icing issues, offering improved visibility and resistance to impacts.
Patent Information
- Authority / Receiving Office
- FR · FR
- Patent Type
- Applications
- Current Assignee / Owner
- EUROCOPTER FRANCE SA
- Filing Date
- 2024-11-25
- Publication Date
- 2026-05-29
AI Technical Summary
Existing aircraft windshields face challenges in providing optimal visibility, resisting bird strikes, and incorporating anti-icing systems, particularly in designs with double-curvature polycarbonate windshields that limit the use of heating films.
The aircraft is equipped with two windshields supported by a frame, featuring a developable surface with single curvature, allowing integration of heating films and enhancing visibility by extending outer segments to provide unobstructed views of the surroundings.
The solution provides enhanced visibility, resistance to bird strikes, and effective anti-icing capabilities while minimizing visual obstructions and aerodynamic drag.
Smart Images
Figure 00000000_0000_ABST
Abstract
Description
Title of the invention: Aircraft equipped with two windshields for optimized visibility
[0001] The present invention relates to an aircraft equipped with two windshields with optimized visibility.
[0002] An aircraft usually includes a canopy, namely a part of the aircraft allowing a pilot or co-pilot to observe the outside world.
[0003] A canopy comprises at least one transparent element supported by a frame. A transparent element oriented along the direction of travel of the aircraft is usually called a "windshield." Each windshield constitutes the primary line of sight from the cockpit to the outside of the aircraft. Other transparent elements may include windows. A window is sometimes located on the side walls and possibly on the upper and / or lower walls of the aircraft. A window may also be located in the forward area of the aircraft, but outside the primary line of sight from the cockpit to the outside of the aircraft.
[0004] Each windshield or porthole may comprise a single layer of a transparent material or several layers of the same material or of different materials. Materials that may constitute a transparent panel include, for example, glass, a polymer, or a ceramic. In particular, a windshield may comprise a polycarbonate panel.
[0005] A helicopter windshield must allow a pilot or co-pilot to have a clear view of their surroundings. The canopy must be carefully designed to provide the pilot or co-pilot with minimal obstructions and to avoid distorting their vision.
[0006] An aircraft must also withstand the impact of a bird in flight. The rigidity and the means of attaching each windshield to a frame are therefore taken into account to withstand such an impact.
[0007] Furthermore, an aircraft is likely to fly in icing conditions. A windshield can then be equipped with a de-icing system. For example, a windshield may include a heating film.
[0008] Under these conditions, the windshield(s) of a helicopter are designed to address multiple issues.
[0009] Thus, light helicopters often include a double-curved polycarbonate windshield. Such a windshield is advantageous but limits the choice of technical solutions, particularly for combating icing. Indeed, the double curvature makes making it difficult, or even impossible, to use a modern multi-layer solution involving the use of a heating film.
[0010] Medium and heavy helicopters include several windshields, usually single-curved, and windows to manage visibility, bird strikes, and icing. While this design is advantageous, the visibility stereogram may present obscured areas that cause discomfort for the pilot.
[0011] For example, French patent FR 3039128 describes an aircraft comprising six transparent panels, including two windshields and four windows. Each transparent panel is attached on one side to a frame of the aircraft, at the periphery of the canopy, and on the other side to another transparent panel. Each windshield is fitted with a transparent element held in a frame. The frame has an inner elevation post and an outer elevation post that extend parallel, primarily in elevation, and are connected by a lower cross member and an upper cross member that extend primarily transversely. The two inner elevation posts of the two windshields are connected to each other. Furthermore, the outer elevation post of each windshield is longer than the inner elevation post of that windshield, the outer elevation post being offset from the inner elevation post only upwards.Finally, the lower crossbar is curved while the upper crossbar has a double change of direction.
[0012] The present invention then aims to provide an aircraft that offers good visibility to a pilot or co-pilot, is resistant to impact with a bird, while allowing the use of a de-icing film for example.
[0013] The present invention relates to an aircraft equipped with a canopy having at least a first windscreen and a second windscreen supported by a frame and arranged along a transverse axis next to each other, each windscreen extending along a vertical axis from a lower segment to an upper segment and along the transverse axis from an inner segment to an outer segment.
[0014] This aircraft is remarkable in that the inner segments of the first and second windshields are straight, the inner segments of the first and second windshields are connected to the same central frame post, the outer segments of the first and second windshields being connected respectively to two lateral frame posts, the outer segment of each windshield being longer than the inner segment of that windshield and projecting from the inner segment of that windshield at least upwards or downwards of the aircraft, each windshield having a transparent wall presenting a developable surface with a single curvature.
[0015] The aircraft can be of any type, and can in particular be an aircraft with a rotary wing, or even in particular a helicopter.
[0016] A "developable surface" is a surface in which every point lies on at least one straight line along which the surface is curved. Such a surface can then roll without slipping on a plane, with contact with the plane occurring along a straight line. For example, every windshield is a section of a cylinder of revolution or a truncated cone.
[0017] Such a geometry makes it possible to obtain an acceptable dispersion of the energy resulting from a frontal collision with a bird.
[0018] Moreover, such a developable surface makes it possible to implement existing windshield technologies, including the use of glass and / or multi-layered windshields.
[0019] Such a developable surface also allows the implementation of various anti-icing technologies, and in particular allows the integration of a heating film.
[0020] Furthermore, the first and second windshields each have an outer segment that is longer than their inner segment. The expression "projecting from the inner segment at least upwards or downwards" means that, for an individual looking through the canopy when the aircraft is resting on a level landing strip, the outer segment of a windshield reaches a higher volume located above the inner segment and / or a lower volume located below the inner segment, as required. The expression "downward" refers to a direction from the head of an individual seated in a cockpit to a plane passing through a cockpit floor, while the expression "upward" refers to the opposite direction from the pilot's head away from that floor.The lower volume allows the windshield to have a geometry that provides a satisfactory downward viewing angle for a pilot or co-pilot, for example, to locate a ground reference point or a casualty to rescue. The upper volume allows the windshield to have a geometry that provides a satisfactory upward viewing angle, for example, to see the tips of a helicopter's rotor blades, particularly during a tactical turn.
[0021] Consequently, an aircraft according to the invention is equipped with two windshields providing good visibility to a pilot or co-pilot, capable of withstanding a bird strike as defined in standard certification regulations, and equipped with an anti-icing system. The dimensions of the windshields also limit the use of multiple transparent surfaces supported by a frame, thereby reducing the visual obstruction caused by the frame.
[0022] The aircraft may also include one or more of the following features taken alone or in combination.
[0023] According to one possibility, the outer segments of the first windshield and the second windshield are straight.
[0024] This feature can facilitate the attachment of windshields to the frame.
[0025] Alternatively, the outer segments can, for example, be curved.
[0026] According to a possibility compatible with the preceding ones, the canopy may comprise only the first windscreen and the second windscreen.
[0027] According to this option, the canopy has no other transparent panels than the transparent panels of the first and second windshields. Thus, such a canopy limits the number of transparent panels and consequently the number of cross members and frame members that could obstruct the field of vision of a pilot or co-pilot.
[0028] According to a possibility compatible with the preceding ones, the developable surface may exhibit a constant curvature.
[0029] Such a curvature makes it possible to limit reflections or distortions of vision thanks to a single ray in any area of the windshield.
[0030] Alternatively, the developable surface may exhibit an evolving curvature.
[0031] Such a curvature optimizes the aircraft's aerodynamics. In particular, an evolving curvature allows for a better aerodynamic transition between the forward tip of the fuselage and the sides of the aircraft thanks to a radius that varies according to the needs of each area.
[0032] According to a possibility compatible with the preceding ones, the first windshield may have a curved section in each plane parallel to a generatrix of said developable surface of this first windshield, and the second windshield may have a curved section in each plane parallel to a generatrix of said developable surface of this second windshield.
[0033] Such a curvature makes it possible to obtain good resistance to a frontal impact with a bird, and to equip the windshield with an anti-icing system.
[0034] According to a possibility compatible with the preceding ones, the outer segment of each windshield can extend from a lower outer end connected to the lower segment of that windshield to an upper outer end connected to the upper segment of that windshield and the inner segment of each windshield can extend from a lower inner end connected to the lower segment of that windshield to an upper inner end connected to the upper segment of that windshield, the lower outer end of a windshield being able to be in a low plane located below a lower intermediate plane containing the lower inner end of that windshield when the aircraft is resting on a horizontal landing area, the low plane and the lower intermediate plane being parallel to a cockpit floor delimited by the first windshield and the second windshield.
[0035] Each windscreen thus offers optimized visibility towards the bottom of the aircraft.
[0036] According to a possibility compatible with the preceding ones, the outer segment of each windshield can extend from a lower outer end connected to the lower segment of that windshield to an upper outer end connected to the upper segment of that windshield and the inner segment of each windshield can extend from a lower inner end connected to the lower segment of that windshield to an upper inner end connected to the upper segment of that windshield, the upper outer end of a windshield being able to be in a high plane located above an upper intermediate plane containing the upper inner end of that windshield when the aircraft is resting on a horizontal landing area, the high plane and upper intermediate plane being parallel to a cockpit floor delimited by the first windshield and the second windshield.
[0037] Each windscreen thus offers optimized visibility towards the top of the aircraft.
[0038] According to a possibility compatible with the preceding ones, the inner segment of each The windshield may have a first angle of curvature, with a first plane parallel to the floor of a cockpit delimited by the first windshield, equal to a second angle of curvature. The second angle of curvature separates a straight line passing through a lower outer edge and an upper outer edge of this windshield and a second plane parallel to the floor. Optionally, the first and second angles of curvature may be between 30 and 50 degrees.
[0039] Alternatively, the inner segment of each windshield may have a first angulation with a first plane parallel to a floor of a cockpit delimited by the first windshield different from a second angulation, the second angulation separating a straight line passing through a lower outer end and an upper outer end of this windshield and a second plane parallel to the floor.
[0040] The first angle of the inner segment of each windshield allows the pilot or co-pilot to have an acceptable view towards the ground and towards the sky over the equipment in the cockpit.
[0041] The second angle makes it possible to improve the aerodynamics of the aircraft.
[0042] Optionally, the first angulation may be between 30 and 40 degrees and / or the second angulation may be between 35 and 50 degrees to promote the effects described above.
[0043] Optionally, the first angle may be less than the second angle.
[0044] According to a possibility compatible with the preceding ones, each windshield may comprise at least one solar film and / or a heating film and / or a variable opacity film, i.e. at least one of the following films: solar film, heating film, variable opacity film.
[0045] The developable surface of windshields allows for the integration of various types of film, permanently fitted or peelable.
[0046] According to a possibility compatible with the preceding ones, the inner segments, outer segments, lower segments and upper segments may be devoid of a concave radius whose tangents would be located in the associated windshield, namely in the space delimited by the segments forming its contour, possibly at least when the developable surface is flattened.
[0047] The general outline of each windshield does not include such so-called concave radii. Such a windshield limits the risk of initiating fracture, namely the risk of jacking.
[0048] According to a possibility compatible with the previous ones, the first windshield and the second windshield can be tangent along the central pillar.
[0049] Such an arrangement offers the possibility of using a single wiper blade to sweep both windshields.
[0050] Alternatively, the first windshield and the second windshield may not be tangent along the central pillar.
[0051] Such an arrangement can make it possible to reduce aerodynamic drag and / or downward air deflection, also known as "downwash" in English.
[0052] According to a possibility compatible with the preceding ones, the lower segment and the upper segment of each windshield can be connected to said frame.
[0053] According to a possibility compatible with the preceding ones, at least one or even each of the lower and upper segments of the first windshield and of the lower and upper segments of the second windshield can describe a broken line.
[0054] Complementarily or alternatively, at least one or even each of the lower and upper segments of the first windshield and the lower and upper segments of the second windshield can describe a convex curve, namely a curve whose tangents would be located outside the associated windshield, possibly at least when the developable surface is flattened.
[0055] Such a shape makes it possible to maximize the field of vision of a pilot or co-pilot, and can make it possible not to generate a concave beam.
[0056] According to a possibility compatible with the preceding ones, at least one of the first windscreens and second windscreens may include a transparent wall and at least one reinforcement disposed against the transparent wall.
[0057] Such reinforcement can eliminate the need to connect an internal area of the windshields to the frame, thereby optimizing the visibility offered by the windshields. This reinforcement can be transparent, for example, by comprising a plate made of a rigid and transparent plastic material such as polycarbonate or polymethyl methacrylate, and for example, a material known under the brand name Plexiglas®.
[0058] The invention and its advantages will become apparent in more detail in the following description, with illustrative examples given by reference to the accompanying figures, which represent:
[0059] [Fig. 1], a view of an aircraft according to the invention,
[0060] [Fig.2], a view of the aircraft in [Fig.1] illustrating the presence of windshields having a developable surface with a single curvature,
[0061] [Fig. 3], a view of the aircraft from [Fig. 1] illustrating the improved field of vision,
[0062] [Fig. 4], a view of the aircraft in [Fig. 1] illustrating the presence of at least one film,
[0063] [Fig. 5], a view of the aircraft in [Fig. 1] illustrating the inclinations of the segments indoors and outdoors, and
[0064] the [Fig.6], a view of the aircraft of the [Fig.1] illustrating the absence of negative rays on the windshields.
[0065] Elements present in several separate figures are assigned one and the same reference.
[0066] Three directions X, Y and Z orthogonal to each other are represented in the figures.
[0067] The first direction X is said to be longitudinal and can be substantially parallel to a roll axis of the aircraft 1. The term "longitudinal" is relative to any direction parallel to the first direction X.
[0068] The second Y direction is said to be transverse and can be substantially parallel to a pitch axis of the aircraft 1. The term "transverse" is relative to any direction parallel to the second Y direction.
[0069] Finally, the third direction Z is said to be in elevation and can be substantially parallel to a yaw axis of the aircraft 1. The expression "in elevation" relates to any direction parallel to the third direction Z.
[0070] Figure 1 shows an aircraft 1 according to the invention. Such an aircraft 1 may comprise a fuselage 2 extending longitudinally and rearward from a nose 6 to a tail 7, transversely between two sides, and vertically from bottom to top from a hull at ground level to a summit. The aircraft 1 may be a rotorcraft comprising a rotor 3 equipped with at least one blade 4, and in particular may be a helicopter comprising a rotor 3 contributing, in particular, to its lift.
[0071] Aircraft 1 is equipped with a canopy 10, delimiting forward a cockpit comprising a floor 95 illustrated with dotted lines.
[0072] The canopy 10 has at least a first windscreen 30 and a second windscreen 40 supported by a frame 20 so as to be transversely side by side, or even joined together. The canopy 10 may include at least one porthole (not shown), or may be without a porthole.
[0073] The first windshield 30 and the second windshield 40 each comprise a transparent wall 35, 45, and optionally a frame framing the transparent wall 35, 45. Thus, the first windshield 30 has a first transparent wall 35 optionally framed by a first frame, and the second windshield 40 has a second transparent wall 45 optionally framed by a second frame. Each transparent wall 35, 45 may comprise one or more layers of material. Each transparent wall 35, 45 may comprise glass, a polymer, or a ceramic.
[0074] Each windscreen 30, 40 extending along the vertical axis Z, and from bottom to top, from a lower segment 33, 43 to an upper segment 34, 44. Each windscreen 30, 40 extends along the transverse axis Y from an inner segment 31, 41 to an outer segment 32, 42.
[0075] Thus, the first windshield 30 extends along the vertical axis Z, and from bottom to top, from a first lower segment 33 to a first upper segment 34, and along a first direction of the transverse axis Y, from a first inner segment 31 to a first outer segment 32. Similarly, the second windshield 40 extends along the vertical axis Z, and from bottom to top, from a second lower segment 43 to a second upper segment 44, and along a second direction of the transverse axis Y, from a second inner segment 41 to a second outer segment 42.
[0076] The different segments 31, 32, 33, 34, 41, 42, 43, 44 of a windscreen 30, 40 can be formed by the transparent wall 35, 45 and / or the frame of this windscreen 30, 40 as appropriate.
[0077] The inner segments 31, 41, or, depending on the variant, the respective outer segments 32, 42 of the first windshield 30 and second windshield 40, may be straight and may be parallel. According to an illustrated example, the respective inner segments 31, 41 of the first windshield 30 and second windshield 40 are parallel, or the respective outer segments 32, 42 of the first windshield 30 and second windshield 40 are parallel.
[0078] Furthermore, the respective inner segments 31, 41 of the first windscreen 30 and the second windscreen 40 are fixed to the same central upright 21 of the frame 20. Optionally, the respective inner segments 31, 41 of the first windscreen 30 and second windscreen 40 are tangent, the first windscreen 30 and the second windscreen 40 then being side by side.
[0079] Furthermore, the respective outer segments 32, 42 of the first windscreen 30 and second windscreen 40 are fixed to the respective first and second lateral uprights 22, 23 of the frame 20.
[0080] Furthermore, the lower segment 33, 43 and the upper segment 34, 44 of each windscreen 30, 40 are optionally connected respectively to lower cross members 105, 106 and upper cross members 107, 108 of said frame 20.
[0081] Optionally, the first windscreen 30 and the second windscreen 40 are symmetrical with respect to a plane passing through the central pillar 21.
[0082] As illustrated in [Fig.2], the first transparent wall 35 and the second transparent wall 45 each have a developable surface.
[0083] Each point of each of the windscreens 30, 40 then forms part of a straight line 85 along which the transparent wall 35, 45 is curved.
[0084] Each transparent wall 35, 45 may have a constant or changing curvature.
[0085] As illustrated in [Fig. 3], the outer segment 32, 42 of each windshield 30, 40 has a length L1 greater than a length L2 of the inner segment 31, 41 of this windshield 30, 40. Thus, the first outer segment 32 is longer than the first inner segment 31, and the second outer segment 42 is longer than the second inner segment 41. The term "long" refers to the length of the segment in question along an axis running from one end of this segment to the other, that is, from the lower segment 33, 43 to the upper segment 34, 44.
[0086] In addition, the outer segment 32, 42 of each windscreen 30, 40 is projecting / extends from the inner segment 31, 41 of this windscreen at least upwards so that the transparent wall 35, 45 covers an upper area 81, 82, and / or downwards of the aircraft 1 so that the transparent wall 35, 45 covers a lower area 83, 84 in order to improve the stereogram of vision.
[0087] More specifically, the first outer segment 32 of the first windscreen 30 extends from a first lower outer end 61 connected to the first lower segment 33 of this first windscreen 30 to a first upper outer end 62 connected to the first upper segment 34 of this first windscreen 30, and the first inner segment 31 of the first windscreen 30 extends from a first lower inner end 63 connected to the first lower segment 33 of this first windscreen 30 to a first upper inner end 64 connected to the first upper segment 34 of this first windscreen 30.
[0088] Similarly, the second outer segment 42 of the second windshield 40 extends from a second lower outer end 71 connected to the second lower segment 43 of this second windshield 40 to a second upper outer end 72 connected to the second upper segment 44 of this second windshield 40 and the second inner segment 41 of the second windshield 40 extends from a second lower inner end 73 connected to the second lower segment 43 of this second windshield 40 to a second upper inner end 74 connected to the second upper segment 44 of this second windshield 40.
[0089] Therefore, to extend visibility downwards, the lower outer ends 61,71 of the windscreens 30, 40 can be located in a low plane PB situated under a lower intermediate plane PINTB containing the lower inner ends 63, 73 of the windscreens 30, 40, the low plane PB and the lower intermediate plane PINTB being parallel to the floor and the low plane PB being possibly arranged between the lower intermediate plane PINTB and the floor.
[0090] To extend upward visibility, the upper outer extremities 62, 72 of the windscreens 30, 40 may be located in a high plane PH situated above an upper intermediate plane PINTH containing the upper inner extremities 64, 74 when the aircraft 1 rests on a horizontal landing area 100, the high plane PH and the upper intermediate plane PINTH being parallel to the floor and the upper intermediate plane PINTH being arranged between the high plane PH and the floor.
[0091] With reference to [Fig. 4], each windshield 30, 40 may include at least one treatment film 50, such as a solar film 51, a heating film 52, or a variable opacity film 53. Each film may be integrated into the transparent surface of a windshield or may be peelable.
[0092] According to another aspect and with reference to [Fig. 5], the inner segment 31, 41 of each windscreen 30, 40 may have a first angulation ANG1 with a first plane parallel to the floor, different from a second angulation ANG2 separating the floor and a straight line passing through the lower outer end 61, 71 and the upper outer end 62, 72 of the outer segment 32, 42 of this windscreen 30, 40. The first angulation ANG1 may be less than the second angulation ANG2.
[0093] For example, the first angulation ANG1 is between 30 and 40 degrees and / or the second angulation ANG2 is between 35 and 50 degrees.
[0094] Alternatively, the first angulation ANG1 and the second angulation ANG2 may be equal.
[0095] Furthermore, as illustrated in [Fig. 6], the inner segments 31, 41, outer segments 32, 42, lower segments 33, 43, and upper segments 34, 44 may be devoid of a concave radius whose tangents would be located within the contour of the relevant windshield 30, 40. Such concave radii are shown in dashed lines in [Fig. 6] to distinguish them from the invention.
[0096] For example, at least one of the lower segment 33, 43 and upper segment 34, 44 of each windshield 30, 40 can for this purpose describe a broken line 98, and for example a line having two sections. According to the illustrated example, the lower segment 33, 43 comprises a first lower section 101 which approaches the ground from the outer segment 32, 42 and then a second lower section 102 which starts from one end of the first lower section 101 and moves away from the ground to join the inner segment 31, 41. Conversely, the upper segment 34, 44 comprises a first upper section 103 which moves away from the ground from the outer segment 32, 42 then a second upper section 104 which starts from one end of the first upper section 103 moving closer to the ground to join the inner segment 31, 41.
[0097] According to another example, at least one of the lower segment 33, 43 and upper segment 34, 44 of each windscreen 30, 40 can for this purpose describe a convex curve 99 illustrated with discontinuous lines.
[0098] According to another aspect, the first windshield 30 and / or the second windshield 40 may include at least one reinforcement 350, 450 disposed against the transparent wall 35, 45 to stiffen it locally. The reinforcements 350, 450 are separate from any windshield frames. For example, at least one reinforcement is located against one face of a windshield 30, 40 facing the cockpit, and not facing the outside.
[0099] Naturally, the present invention is subject to numerous variations in its implementation. Although several embodiments have been described, it is understood that it is not conceivable to exhaustively identify all possible embodiments. It is, of course, conceivable to replace a described means with an equivalent means without departing from the scope of the present invention as defined by the claims.
Claims
Demands
1. Aircraft (1) equipped with a canopy (10) having at least a first windshield (30) and a second windshield (40) supported by a frame (20) and arranged side by side along a transverse axis (Y), each windshield (30, 40) extending along a vertical axis (Z) from a lower segment (33, 43) to an upper segment (34, 44) and along the transverse axis (Y) from an inner segment (31, 41) to an outer segment (32, 42), characterized in that the inner segments (31, 41) of the first windshield (30) and the second windshield (40) are straight, and the inner segments (31, 41) of the first windshield (30) and the second windshield (40) are connected to the same central post (21) of the frame (20), the outer segments (32, 42) of the first windscreen (30) and the second windscreen (40) being connected respectively to two lateral uprights (22, 23) of the frame (20), the outer segment (32, 42) of each windscreen (30,40) being longer than the inner segment (31, 41) of this windscreen (30, 40) and projecting from the inner segment (31, 41) of this windscreen (30, 40) at least upwards or downwards of the aircraft (1), each windscreen (30, 40) having a transparent wall (35, 45) presenting a developable surface.
2. Aircraft according to claim 1, characterized in that the developable surface has a constant curvature.
3. Aircraft according to claim 1, characterized in that the developable surface has an evolving curvature.
4. Aircraft according to any one of claims 1 to 3, characterized in that the first windscreen (30) has a curved section in each plane parallel to a generatrix of said developable surface of this first windscreen (30), and the second windscreen (40) has a curved section in each plane parallel to a generatrix of said developable surface of this second windscreen (40).
5. Aircraft according to any one of claims 1 to 4, characterized in that the outer segment (32, 42) of each windscreen (30, 40) extends from a lower outer extremity (61, 71) connected to the lower segment (33, 43) of this windshield (30, 40) to an upper outer end (62, 72) connected to the upper segment (34, 44) of this windshield (30, 40) and the inner segment (31, 41) of each windshield (30, 40) extends from a lower inner end (63, 73) connected to the lower segment (33, 43) of this windshield (30, 40) to an upper inner end (64, 74) connected to the upper segment (34, 44) of this windshield (30, 40), the lower outer end (61, 71) of a windshield (30, 40) being in a low plane (PB) located below a lower intermediate plane (PINTB) containing the lower inner end (63, 73) of this windshield (30, 40), the low plane (PB) and the lower intermediate plane (PINTB) being parallel to a cockpit floor delimited by the first windshield (30) and the second windshield (40).
6. Aircraft according to any one of claims 1 to 5, characterized in that the outer segment (32, 42) of each windscreen (30, 40) extends from a lower outer end (61, 71) connected to the lower segment (33, 43) of this windscreen (30, 40) to an upper outer end (62, 72) connected to the upper segment (34, 44) of this windscreen (30, 40) and the inner segment (31, 41) of each windscreen (30, 40) extends from a lower inner end (63, 73) connected to the lower segment (33, 43) of this windscreen (30, 40) to an upper inner end (64, 74) connected to the upper segment (34, 44) of this windscreen (30, 40), the upper outer end (62, 72) of a windshield (30, 40) being in a high plane (PH) located above an upper intermediate plane (PINTH) containing the upper inner end (64, 74) of this windshield (30, 40),the upper plane (PH) and the upper intermediate plane (PINTH) being parallel to a cockpit floor delimited by the first windshield (30) and the second windshield (40).
7. Aircraft according to any one of claims 1 to 6, characterized in that the inner segment (31, 41) of each windscreen (30, 40) has a first angulation (ANG1) with a first plane parallel to a cockpit floor delimited by the first windscreen (30) equal to a second angulation (ANG2), the second angulation (ANG2) separating a straight line passing through a lower outer end (61, 71) and an end upper outer (62, 72) of the outer segment (32, 42) of this windshield (30, 40) and a second plane parallel to the floor.
8. Aircraft according to any one of claims 1 to 6, characterized in that the inner segment (31, 41) of each windscreen (30, 40) has a first angulation (ANG1) with a first plane parallel to a floor of a cockpit delimited by the first windscreen (30) different from a second angulation (ANG2), the second angulation (ANG2) separating a straight line passing through a lower outer end (61, 71) and an upper outer end (62, 72) of the outer segment (32, 42) of this windscreen (30, 40) and a second plane parallel to the floor.
9. Aircraft according to claim 8, characterized in that the first angulation (ANG1) is between 30 and 40 degrees, the second angulation (ANG2) being between 35 and 50 degrees.
10. Aircraft according to any one of claims 8 to 9, characterized in that the first angulation (ANG1) is less than the second angulation (ANG2).
11. Aircraft according to any one of claims 1 to 10, characterized in that the canopy (10) comprises only the first windscreen (30) and the second windscreen (40).
12. Aircraft according to any one of claims 1 to 11, characterized in that each windscreen (30, 40) comprises at least one solar film (51) or a heating film (52) or a variable opacity film (53).
13. Aircraft according to any one of claims 1 to 12, characterized in that the inner segments (31, 41), outer segments (32, 42), lower segments (33, 43) and upper segments (34, 44) of each windscreen are devoid of a concave radius whose tangents would be located in the associated windscreen.
14. Aircraft according to any one of claims 1 to 13, characterized in that the first windscreen (30) and the second windscreen (40) are tangent or not tangent along the central pillar (21).
15. Aircraft according to any one of claims 1 to 14, characterized in that the lower segment (33, 43) and the upper segment (34, 44) of each windscreen (30, 40) are connected to said frame (20).
16. Aircraft according to any one of claims 1 to 15, characterized in that at least one of the lower segment (33) and upper segment (34) of the first windscreen (30) and of the lower segment (43) and upper segment (44) of the second windscreen (40) describes a broken line (98).
17. Aircraft according to any one of claims 1 to 16, characterized in that at least one of the lower segment (33) and upper segment (34) of the first windscreen (30) as well as the lower segment (43) and upper segment (44) of the second windscreen (40) describes a convex curve (99).
18. Aircraft according to any one of claims 1 to 17, characterized in that the outer segments (32, 42) of the first windscreen (30) and the second windscreen (40) are straight.
19. Aircraft according to any one of claims 1 to 18, characterized in that at least one of the first windscreen (30) and second windscreen (40) comprises a transparent wall (35, 45) and at least one reinforcement (350, 450) disposed against the transparent wall.