KR102219558B1 - A hybrid type rotorcraft having a horizontal stabilizer and two fins arranged on the horizontal stabilizer - Google Patents

Abstract

The present invention relates to a hybrid type rotorcraft 20, wherein the rotorcraft has one main rotor 1, each half-wings 3 and 3'disposed symmetrically on both sides of the front-rear midplane XOZ At least two propulsion elements (2, 2') each mounted on the top, horizontal stabilizer (8) disposed in the rear area of the rotorcraft 20 on both sides of the front-rear midplane (XOZ), and the front and rear With two pins (21, 21') disposed on both sides of the directional midplane (XOZ), each of the pins (21, 21') is each left/right bottom disposed under the horizontal stabilizer (8) It includes fin airfoils 22 and 22', and respective left/right upper fin airfoils 23 and 23' disposed on the horizontal stabilizing plate 8.

Description

A hybrid type rotorcraft having one horizontal safety plate and two pins arranged on the horizontal safety plate {A HYBRID TYPE ROTORCRAFT HAVING A HORIZONTAL STABILIZER AND TWO FINS ARRANGED ON THE HORIZONTAL STABILIZER}

The project that led the drafting of this patent application was CleanSky 2 grant agreement No. The European Union's Horizon 2020 Research and Innovation Program in the context of “GAM-FRC-2014-001 Issue E” and ITD Airframe Amendment No. Funding received from "Grant agreement CSJU-CS2-GAM-AIR-2014-15-01 Annex 1-Issue B04-Date: October 2nd, 2015".

The present invention relates to the field of hybrid rotorcraft. Such a rotorcraft has one main rotor serving to provide lift and possibly also propulsion for such rotorcraft, and to provide propulsion in addition to those generated by such a main rotor. It has at least two propellers.

The applicant has specifically described a hybrid rotorcraft of this type in patent document FR2916418. Specifically, this patent document FR2916418 describes a hybrid helicopter, in which propulsion is provided by two propellers driven by two turboshaft engines, one of which is each It is disposed at the outer end of the half wing and forms a thrusting element for providing all or part of the thrust of the rotorcraft.

In addition, such patent document FR2916418 describes the presence of stabilization and control surfaces near the rear end of the fuselage, and these stabilization and control surfaces are two pitch control surfaces which can be moved relative to the front part, especially for pitching. It includes a horizontal stabilizer with the beams, and also includes two pins disposed at one end of the horizontal stabilizer for steering. Specifically, these horizontal stabilizers and pins form a U-shaped upside down.

Further, according to patent document FR2916418, such pins can be arranged vertically and in a manner that is inclined to a vertical line.

Nevertheless, when the fins are placed in an inclined manner with respect to the vertical line, one free end of each fin runs away from the anteroposterior midplane of the rotorcraft, while the other end is against the horizontal stabilizer. It is stuck. Such an upside down U-shape emerges from the main rotor and can cause vibration problems in the fuselage, especially due to airflows interacting with the stabilizer and pins, and these interactions are called "couplings" below. Is referred to in.

In addition, and as described by the applicant in patent document EP2733066, it is also known to provide a horizontal stabilizer in which a left vertical pin and a right vertical pin are arranged on a hybrid rotorcraft, each of which is vertically below the horizontal stabilizer. Each bottom (bottom) fin airfoil located in a vertical position, and has a top (top) fin airfoil located vertically on the horizontal stabilizer.

Nevertheless, although the type of H-shaped stabilizer is largely disturbed by the wake from the fuselage, engine covers, and the head of the main rotor, from the front and rear midplane of the rotorcraft. Although effective in keeping the pins apart, it requires the horizontal stabilizer to exhibit a large span. In addition, such a span may be ineffective in providing stabilization, and may even cause behavior problems, and as a result of the airflow from the main rotor impinging on the stabilizer, the visibility limits for the pilot are crossed. It can cause slow interactions that tend to lift the nose of the Such a type of slow interaction may be referred to by the term "attitude hump".

Also known are rotorcraft having bottom fin airfoils that can be rotated relative to a horizontal stabilizer, or alternatively H-shaped stabilizers representing upper fin airfoils, as described in patent document US2940693.

In such a situation, the movable arrangement of the top fin airfoils is combined with the securing arrangement of the bottom fin airfoils. Such a fastening arrangement of the bottom fin airfoils is also parallel to the symmetrical front-rear midplane of the rotorcraft.

In addition, the movable arrangement of the upper fin airfoils allows the horizontal stabilizer to occupy a high position above the tail boom, and between the free ends of the upper fin airfoils and the blades of the main rotor. Avoid the risk of random collision.

Conversely, the device on which the bottom fin airfoils can move is combined with the device to which the top fin airfoils are fixed. The upper fin airfoils in such a fixed arrangement are likewise parallel to the symmetrical anteroposterior midplane of the rotorcraft.

In this other variant, placing the bottom fin airfoils movable allows the horizontal stabilizer to occupy a low position under the tail boom, and any collision between the free ends of the bottom fin airfoils and the ground. Avoid danger.

However, as for the H-shaped stabilizer above, such a device implies a large span for the horizontal stabilizer. Thus, such a span can cause behavioral problems and can create a low-speed interaction that tends to lift the nose of the rotorcraft above the visibility limits for the pilot. Therefore, the movable arrangement of the top (or bottom) airfoils does not provide a solution for avoiding the stabilizing plate disturbing the airflow generated by the main rotor.

It is therefore an object of the present invention to propose a rotorcraft in which the aforementioned limitations can be eliminated. In addition, the rotorcraft according to the invention avoids reducing or even avoiding the aforementioned vibration problems specific to the upside-down U-shaped stabilizers that could potentially cause airflow separation at the junction between the fins and the horizontal stabilizer. Make it possible.

Another object of the present invention is to limit the span of the horizontal stabilizer so as to optimally stabilize the rotorcraft without generating a low-speed interaction of the flight attitude hump type.

Accordingly, the present invention provides a hybrid type rotorcraft, which includes a main rotor that provides at least all or part of its lift force thereto;

At least two propulsion elements providing all or part of the propulsion force of the rotorcraft, each of which two propulsion elements are mounted on each half wing, and these half wings are symmetrical anteroposterior directions of all or part of the rotorcraft It is arranged to be symmetrical on both sides of the midplane (XOZ), and the front-rear midplane (XOZ) is between the front zone and the rear zone of the rotorcraft in the vertical direction X, and the height (elevation) the at least two propulsion elements extending between a bottom zone and a top zone of the rotorcraft in the Z direction;

A horizontal stabilizer disposed in the rear area of the rotorcraft at either side of the front-rear midplane (XOZ); And

Includes two fins disposed on each side of the front-rear midplane XOZ,

The two pins are composed of a left pin located in a left distal zone of the horizontal stabilizer, and a right pin located in a right distal zone of the horizontal stabilizer, and each of the left and right pins is the horizontal Including a left/right bottom fin airfoil disposed under the stabilizer plate and a left/right upper fin airfoil disposed on the horizontal stabilizer, and the left bottom/upper fin airfoils and the right bottom/upper fin airfoils are the horizontal stabilizer plate Is firmly attached to

According to the present invention, such a rotorcraft has the left bottom fin airfoil approaching the left upper fin airfoil from their respective junctions with the horizontal stabilizer, and the right bottom fin airfoil is their respective junction with the horizontal stabilizer. Accessing the right upper fin airfoil from the s, the left bottom/upper fin airfoils fully or partially extend away from the anteroposterior midplane (XOZ) at least at their free ends, and the right bottom/upper fin The airfoils extend in full or in part away from the anteroposterior midplane XOZ at least at their free ends.

In other words, for each left/right fin, the upper fin airfoil and the bottom fin airfoil do not extend parallel to the front-rear midplane XOZ. These upper fin airfoils and bottom fin airfoils extend away from the front-rear midplane XOZ, thereby enabling the span of the horizontal stabilizer to be limited.

In addition, such an arrangement also reduces or even avoids the problem of separating air flows at the junctions between the two fins and the horizontal stabilizer, reduces the aerodynamic drag of the rotorcraft, and reduces the surface area. It serves to optimize the tail stablizer assembly in terms of weight and weight.

Advantageously, in the horizontal plane (YOZ) perpendicular to the front-rear midplane (XOZ) and crossing the two pins, all four of the left/right and bottom/upper pin airfoils are each fixed to the horizontal stabilizer. May have first ends and respective free ends of the left bottom/top pin airfoils, wherein the free ends of the left bottom/top pin airfoils are made of the left bottom/top pin airfoils to form a back angle in the range of 90°-175° Cooperate with the first ends, and the free ends of the right bottom/upper fin airfoils cooperate with the first ends of the right bottom/upper fin airfoils to form a back angle in the range of 90° to 175°.

In other words, for each left/right fin, its bottom/upper fin airfoils approach each other to form an angle of 90° to 175° in the transverse plane YOZ.

In practice, the free end of the left/right bottom fin airfoil is parallel to the anteroposterior midplane (XOZ) to form an inclination angle in the range of 5° to 45°, and the first of the left/right bottom fin airfoils. It can extend away from the corresponding plane P/P' containing the end.

Such an angle of inclination of the left/right bottom fin airfoil specifically serves to limit the span of the horizontal safety plate by reducing or even eliminating coupling problems.

Similarly, to form an inclination angle in the range of 5° to 45°, the free end of the left/right upper fin airfoil is parallel to the anteroposterior midplane (XOZ), and the first end of the left/right upper fin airfoil. It can extend away from the corresponding plane (P/P') containing

It can also be seen that such an inclination angle for the left/right upper fin airfoil serves to limit the span of the horizontal stabilizer by reducing or even eliminating coupling problems.

In an advantageous embodiment of the invention, the left/right bottom fin airfoil may be different from the corresponding left/right upper fin airfoil.

In addition, the left/right bottom fin airfoil is in a corresponding plane (P/P') different from the angle of inclination, length, or twist relative to the corresponding plane (P/P') of the left/right upper fin airfoil. It can have an angle of inclination, length, or twist for. Further, the left/right bottom pin airfoil and the left/right top pin airfoil can also be made of two different parts without forming a single-piece unit.

Advantageously, each of the two pins is parallel to the anteroposterior midplane (XOZ) and onto a corresponding plane (P/P') containing one of the first ends of the left/right and bottom/top pin airfoils. Orthogonal projection can represent the shape of an arrow head with its tip facing towards the front section of the rotorcraft.

Specifically, the shape of an arrow head for orthogonal projection of the two pins onto the corresponding planes (P/P') serves to increase the lever arm with respect to the center of gravity of the rotorcraft, thereby rotating It serves to improve the stability of the yaw control of the wing.

In practice, the end of each orthogonal projection may cooperate with a corresponding left/right distal region of the horizontal stabilizer.

In other words, each end of the arrowhead of the orthogonal projections of the two pins onto the corresponding plane (P/P') can be positioned in the height direction Z at the same level as the horizontal stabilizer, and each left/right And the upper/bottom fin airfoil may extend in the longitudinal direction X toward the rear section of the rotorcraft.

In an advantageous embodiment of the present invention, the horizontal stabilizer may be disposed symmetrically with respect to the front-rear midplane (XOZ).

Such symmetry with respect to the horizontal stabilizer is evident for certain variants of hybrid rotorcraft, and especially for rotorcraft suitable to reach high cruising speeds, which can usually reach or even exceed 200 knots (kt). Can be adapted.

In another embodiment of the present invention, the horizontal stabilizer may be disposed asymmetrically with respect to the front-rear midplane XOZ.

Accordingly, the horizontal stabilizer may represent depth dimensions in the OY direction, thickness dimensions in the OZ direction, and width dimensions in the OX direction different from each other on both sides of the front-rear midplane XOZ.

Likewise, in the first modification of the present invention, two pins may be symmetrically arranged with respect to the front-rear midplane XOZ.

However, in the second modification of the present invention, two pins may be arranged asymmetrically with respect to the front-rear midplane XOZ.

In such a situation, and by way of example, the dimensions, shapes, and angular orientations of the left pin may each differ from those of the right pin.

The invention and its advantages appear in more detail through non-limiting examples and in the context of the following description of the embodiments given with reference to the accompanying drawings.
1 is a side view of a first modified example of a rotorcraft according to the present invention.
2 is a front view of a first modified example of a rotorcraft according to the present invention.
3 is a front view of a second modification of the rotorcraft according to the present invention.
4 is a front view of a third modified example of the rotorcraft according to the present invention.
5 is a front view of a fourth modified example of a rotorcraft according to the present invention.

Elements present in two or more drawings are given the same reference numerals to each of them, and of course the invention is not limited to the examples shown schematically for the purpose of representing the angular values shown in the drawings in a non-limiting manner. Specifically, for the orientation angle or inclination angle of the various pins, the angle values and ranges of angle values to be considered are also those specified in the description given below.

It should be observed that in FIGS. 1 to 5 three mutually orthogonal directions (X, Y, Z) are shown.

The direction X is said to be "longitudinal" in so far as it extends along longitudinal dimensions towards the rear zone of the fuselage of the rotorcraft according to the invention.

Another direction Y is said to be "transverse" and extends substantially perpendicular to the axis X along a transverse dimension towards the left side of the fuselage of the rotorcraft according to the invention.

Finally, the third axis Z is said to be "in elevation" and corresponds to the height dimensions of the fuselage of the rotorcraft according to the invention.

Therefore, as described above, the present invention relates to a hybrid type rotorcraft.

1-5, such a rotorcraft 10-50 is one for providing the rotorcraft 10-50 with all or part of its lift, and possibly a portion of its thrust. With two main rotors (1) and two propulsion elements (2, 2') mounted on two half wings (3, 3'), in this case such two propulsion elements (2, 2') Serves to provide additional thrust to the rotorcraft 10-50. Therefore, the two half wings (3, 3') can be advantageously arranged symmetrically on either side of the symmetrical front-rear midplane (XOZ) of the rotorcraft (10 to 50), and in the front view, the rotorcraft (10 to The variants of 50) are partially obscured in FIGS. 2 to 5 for easier visibility.

In addition, such an anteroposterior midplane (XOZ) is the rotorcraft 10 to 50 in the longitudinal direction (X) between the upper section (7) and the bottom section (6) of the rotorcraft 10 to 50 in the height direction (Z). ) Extends between the front section 4 and the rear section 5.

The rotorcraft 10-50 also has horizontal stabilizers 8, 28 arranged in the rear section 5 of the rotorcraft 10-50 on either side of the anteroposterior midplane XOZ. Advantageously, such a horizontal stabilizer 8 is then symmetric with respect to the anteroposterior midplane XOZ.

As shown, two pins 11 to 51 and 11' to 51' are likewise arranged on each side of the front-rear midplane XOZ, and advantageously such pins 11 to 41, 11' to 41 Is symmetric with respect to the anteroposterior midplane (XOZ).

Thus, the left pins 11 to 51 are located in the left distal region 9 of the horizontal safety plates 8, 28, and the right pins 11' to 51' are located in the right distal region 9 ′ of the horizontal safety plates 8, 28. ).

Each of the left/right pins 11 to 51, 11' to 51' is a left/right bottom pin airfoil (12 to 51, 12' to 51') disposed under the horizontal stabilizer (8, 28), and a horizontal stabilizer plate It has (8, 28) upper left/right fin airfoils (13 to 53, 13' to 53') disposed above.

In addition, as shown in Fig. 1, the orthogonal projection of the pin 11 on the plane P parallel to the front-rear midplane XOZ, the tip 18 is toward the front section of the rotorcraft. It is oriented and can represent the shape of an arrow-head cooperating with the distal region 9 of the horizontal stabilizer 8.

As shown in Figure 2, the first modification of the rotorcraft 20 has a left pin 21 and a right pin 21', each of these pins moving away from the front-rear midplane (XOZ), corresponding Each of the left/right upper fin airfoils 23 and 23' extending completely away from the plane P/P' is shown.

In addition, in the horizontal plane YOZ perpendicular to the front-rear midplane XOZ and intersecting the two pins 21, 21', each of the first ends of the left/right upper pin airfoils 23, 23' Fields 25, 25' are fixed to the left/right distal regions 9, 9'contained in the corresponding planes P/P'. The free end 27 of the upper left pin airfoil 23 extends away from the left side of the plane P, and the free end 27' of the upper right pin airfoil 23' is of the plane P'. Extend it farther to the right.

Also in the first modified example of the rotorcraft 20, the left/right bottom fin airfoils 22, 22' extend sufficiently away from the corresponding planes P/P', so that the front-rear midplane ( XOZ) away from it. Each of the first ends 24 and 24 ′ of the left/right bottom fin airfoils 22 and 22 ′ have left/right distal regions 9 and 9 contained in the corresponding planes P/P′. '). The free end 26 of the left bottom pin airfoil 22 extends away from the left side of the plane P, and the free end 266 of the right bottom pin airfoil 22' is the right side of the plane P'. Extend it away from the side.

Therefore, in order to form a back angle in the range of 90° to 175°, the free ends 26, 27 of the left bottom/upper fin airfoils 22, 23 are identical to the same left bottom/upper fin airfoils ( 22, 23) cooperates with the first ends 24, 25. Similarly, in order to form each backing angle in the range of 90° to 175°, the free ends 26', 27' of the right bottom/top fin airfoils 22', 23' are the same right bottom. Cooperates with the first ends 24', 25' of the upper fin airfoils 22', 23'.

In addition, in order to form an inclination angle in the range of 5° to 45°, the free ends 27, 27' of the left/right upper fin airfoils 23, 23' are parallel to the anteroposterior midplane (XOZ). And extends away from the corresponding plane P/P' containing the first ends 25, 25' of the left/right upper fin airfoils 23, 23'. As shown by the example of FIG. 2, this angle is close to 20° and oriented away from the anteroposterior midplane (XOZ).

Similarly, to form an inclination angle in the range of 5° to 45°, the free ends 26, 26' of the left/right bottom fin airfoils 22, 22' are parallel to the anteroposterior midplane (XOZ). And extends away from the corresponding plane P/P' containing the first ends 24, 24' of the left/right bottom fin airfoils 22, 22'. As shown by the example of FIG. 2, this angle is likewise close to 20°.

As shown in Fig. 3, a second variant of the rotorcraft 30 is that such a rotorcraft 30 has a left fin 31 and a right fin 31 ′, each of which is partially a corresponding plane It is noteworthy that it represents each of the left/right upper fin airfoils 33, 33' extending away from (P/P') and goes away from the front and rear midplane (XOZ).

Therefore, in the horizontal plane YOZ that is perpendicular to the front-rear midplane XOZ and crosses the two fins 31 and 31', each of the left/right upper fin airfoils 33, 33' One ends 35, 35' are secured to the left/right distal regions 9, 9'contained in the corresponding plane P/P'. The free end 37 of the upper left pin airfoil 33 extends away from the left side of the plane P, and the free end 37' of the upper right pin airfoil 33' is of the plane P'. Extend it farther to the right.

In the second modified example of the rotorcraft 30, each of the fins 31 and 31 ′ partially extends away from the corresponding plane P/P ′ and moves away from the front-rear midplane XOZ. Also has a right bottom fin airfoil (32, 32'). Each first end 34, 34' of the left/right bottom pin airfoil 32, 32' is in the left/right distal regions 9, 9'contained in the corresponding plane P/P'. Sticking. The free end 36 of the left bottom pin airfoil 32 extends away from the left side of the plane P, and the free end 36' of the right bottom pin airfoil 32' is of the plane P'. Extend it farther to the right.

Moreover, in order to form respective back angles in the range of 90° to 175°, the free ends 36, 37 of the left bottom/top fin airfoils 32, 33 are the same left bottom/top fin air. It cooperates with the first ends 34, 35 of the foils 32, 33. Similarly, in order to form respective back angles in the range of 90° to 175°, the free ends 36', 37' of the right bottom/top fin airfoils 32', 33' are the same right bottom Cooperates with the first ends 34', 35' of the upper fin airfoils 32', 33'.

In addition, in order to form an inclination angle in the range of 5° to 45°, the free ends 37, 37' of the left/right upper fin airfoils 33, 33' are parallel to the anteroposterior midplane (XOZ). It extends away from the corresponding plane P/P' containing the first ends 35, 35' of the left/right upper fin airfoils 33, 33'. As shown by the example in FIG. 3, this angle is close to 20° and oriented away from the anteroposterior midplane (XOZ).

Similarly, to form an inclination angle in the range of 5° to 45°, the free ends 36, 36' of the left/right bottom fin airfoils 32, 32' are parallel to the anteroposterior midplane (XOZ) and It extends away from a corresponding plane P/P' containing the first ends 34, 34' of the left/right bottom fin airfoils 32, 32'. As shown by the example in FIG. 3, this angle is close to 20° and oriented away from the anteroposterior midplane (XOZ).

As shown in Fig. 4, a third variant of the rotorcraft 40 is that such a rotorcraft 40 has a left pin 41 and a right pin 41', each of which has a corresponding plane (P/ It is noteworthy that it represents each of the left/right upper fin airfoils 43, 43' extending completely away from P') and goes away from the front-rear midplane (XOZ).

In addition, in the horizontal plane YOZ perpendicular to the front-rear midplane XOZ and intersecting the two pins 41, 41', each of the first ends of the left/right upper pin airfoils 43, 43' Fields 45, 45' are fixed to the left/right distal regions 9, 9'contained in the corresponding planes P/P'. The free end 47 of the upper left pin airfoil 43 extends away from the left side of the plane P, and the free end 47' of the upper right pin airfoil 43' is of the plane P'. Extend it farther to the right.

Similarly, the rotorcraft 40 has a left pin 41 and a right pin 41', respectively, representing the respective left/right bottom pin airfoils 42 and 42' extending away from the front-rear midplane XOZ. ). The first end 44, 44' of each of the left/right bottom fin airfoils 42, 42' is secured to the right/left distal region 9, 9'contained in the corresponding plane P/P'. . The free end 46 of the left bottom pin airfoil 42 extends away from the left side of the plane P, and the free end 46' of the right bottom pin airfoil 42' is of the plane P'. Extend it farther to the right.

Thus, in order to form the respective rear angles in the range of 90° to 175°, the free ends 46 and 47 of the left bottom/upper fin airfoils 42, 43 are identical to the left bottom/upper fin air. It cooperates with the first ends 44, 45 of the foils 42, 43. Similarly, the free ends 46', 47' of the right bottom/top fin airfoils 42', 43' are the same right bottom, in order to form each backing angle in the range of 90° to 175°. Cooperates with the first ends 44', 45' of the upper fin airfoils 42', 43'.

In addition, in order to form the respective inclination angles in the range of 5° to 45°, the free ends 47, 47' of each of the left/right upper fin airfoils 43, 43' are front and rear midplanes (XOZ ) And cooperate with a corresponding plane P/P' which contains the first ends 45, 45' of the left/right upper fin airfoils 43, 43' which are identical to each other. As shown by the example in FIG. 4, this angle is close to 25° and oriented away from the anteroposterior midplane (XOZ).

Similarly, the free ends 46, 46' of each of the left/right bottom fin airfoils 42, 42' are the anteroposterior midplanes (XOZ) to form respective tilt angles in the range of 5° to 45°. ) And cooperate with a corresponding plane P/P' containing the first ends 44, 44' of the left/right bottom fin airfoils 42, 42' which are identical to each other. As shown by the example in FIG. 4, this angle is close to 15° and oriented away from the anteroposterior midplane (XOZ).

As shown in Fig. 5, a fourth variant of the rotorcraft 50 has a left pin 51 and a right pin 51' representing different respective shapes, dimensions, and angular orientations. The upper left fin airfoil 53, the lower left fin airfoil 52, the upper right fin airfoil 53', and the lower right fin afoil 52' are away from the corresponding plane (P/P'). Extend completely and move away from the anteroposterior midplane (XOZ).

In addition, in the horizontal plane YOZ perpendicular to the front-rear midplane XOZ and intersecting the two pins 51 and 51', the first end 55 and the right bottom pin of the left upper pin airfoil 53 The first end 54' of the airfoil 52' is fixed to the left/right distal regions 9, 9', respectively, contained in the corresponding planes P/P'. Similarly, the first end 54 of the left bottom fin airfoil 52 and the first end 55' of the right upper fin airfoil 53' are contained in the corresponding planes P/P'. It is fixed to the right distal regions 9, 9'.

In addition, the free end 57 of the left upper fin airfoil 53 and the free end 56 of the left bottom fin airfoil 52 extend to the left of the plane P. Similarly, the free end 56' of the right bottom fin airfoil 52' and the free end 57' of the right upper fin airfoil 53' extend toward the right side of the plane P'.

Therefore, in order to form the respective backing angles in the range of 90° to 175°, the free ends 56, 57 of the left bottom/upper fin airfoils 52, 53 are the same left bottom/upper fin airfoils. It cooperates with the first ends 54, 55 of the s 52, 53. Similarly, in order to form each backing angle in the range of 90° to 175°, the free ends 56', 57' of the right bottom/top fin airfoils 52', 53' are the same right bottom. Cooperates with the first ends 54', 55' of the upper fin airfoils 52', 53'.

In addition, in order to form respective inclination angles in the range of 5° to 45°, the free end 57 of the left upper fin airfoil 53 and the free end 56' of the right bottom fin airfoil 52' Is parallel to the anteroposterior midplane (XOZ) and containing the first end 55 of the left upper fin airfoil 53 and the first end 54 ′ of the right bottom fin airfoil 52 ′, respectively. It extends away from the planes P/P'. As shown by the example in FIG. 5, this angle is close to 10° for the left upper fin airfoil 53 and the left lower fin airfoil 52, and the right lower fin airfoil 52' and the right upper fin It is close to 25° for the airfoil 53', and they are oriented opposite to the anteroposterior midplane XOZ.

Also in the fourth modified example of the rotorcraft 40, the horizontal stabilizer 28 may be asymmetric with respect to the front-rear midplane XOZ. As shown, the stabilizer 28 may have a left length dimension along a direction OY shorter than a right length dimension.

Of course, the present invention may undergo a number of variations in its implementation. Although several embodiments are described, it will be immediately understood that it is conceivable to exhaustively identify all possible embodiments. It is of course possible to envision replacing any of the described means with equivalent means without departing from the scope of the invention.

Claims (13)

As a hybrid rotorcraft (10, 20, 30, 40, 50),
A main rotor (1) providing lift of the rotorcraft (10, 20, 30, 40, 50);
At least two propulsion elements (2, 2') each mounted on each half wing (3, 3') and providing the propulsion of the rotorcraft (10, 20, 30, 40, 50) ), the half wings (3, 3') are symmetrical on either side of the front-rear midplane (XOZ), which is the symmetry of the rotorcraft (10, 20, 30, 40, 50). And the front-rear midplane (XOZ) is between the front section (4) and the rear section (5) of the rotorcraft 10, 20, 30, 40, 50 in the longitudinal direction X, and the elevation ) Said at least two propulsion elements (2, 2') extending between the bottom section (6) and the upper section (7) of the rotorcraft (10, 20, 30, 40, 50) in the Z direction;
Horizontal stabilizers (8, 28) disposed in the rear section (5) of the rotorcraft (10, 20, 30, 40, 50) on both sides of the front-rear midplane (XOZ); And
Two fins (11, 21, 31, 41, 51, 11', 21', 31', 41', 51') disposed on each side of the front-rear midplane XOZ Including,
The two pins (11, 21, 31, 41, 51, 11', 21', 31', 41', 51') are left distal zone (9) of the horizontal stabilizer (8, 28) Left pins (11, 21, 31, 41, 51) located on the horizontal stabilizer (8, 28) and right pins (11', 21', 31', 41) located on the right distal region (9') of the horizontal stabilizer (8, 28) ', 51'), the left pins (11, 21, 31, 41, 51) and the right pins (11', 21', 31', 41', 51') each of the horizontal stabilizer (8) , 28) On the lower left/right bottom fin airfoil (12, 22, 32, 42, 52, 12', 22', 32', 42', 52') and the horizontal stabilizer (8, 28) Each of the arranged left/right upper fin airfoils 13, 23, 33, 43, 53, 13', 23', 33', 43', 53', and left bottom/upper fin airfoils 12 , 22, 32, 42, 52, 13, 23, 33, 43, 53) and right bottom/upper fin airfoils (12', 22', 32', 42', 52', 13', 23', 33', 43', 53') are firmly fixed to the horizontal stabilizers 8, 28,
The left bottom fin airfoil (12, 22, 32, 42, 52) is the respective junction points of the horizontal stabilizer (8, 28) and the left bottom fin airfoil (12, 22, 32, 42, 52) ( respective junctions) from the upper left pin airfoil (13, 23, 33, 43, 53), and the right bottom pin airfoil (12', 22', 32', 42', 52') From the junctions of the horizontal stabilizers 8 and 28 and the right bottom fin airfoils 12', 22', 32', 42', 52', the upper right fin airfoils 13', 23', 33 ', 43', 53'), and the free ends 16 of the left bottom/top fin airfoils 12, 22, 32, 42, 52, 13, 23, 33, 43, 53 , 26, 36, 46, 56, 17, 27, 37, 47, 57) extend away from the front-rear midplane XOZ, and the right bottom/upper pin airfoils 12', 22', 32 ', 42', 52', 13', 23', 33', 43', 53') of free ends (16', 26', 36', 46', 56', 17', 27', 37 ', 47', 57') extend away from the front-rear midplane XOZ,
The two pins (51, 51') are arranged asymmetrically with respect to the front-rear midplane (XOZ), a hybrid type rotorcraft. The method of claim 1,
In the transverse plane YOZ perpendicular to the anteroposterior midplane XOZ and intersecting the two pins 11, 21, 31, 41, 51, 11', 21', 31', 41', 51', Left/right and bottom/top fin airfoils (12, 22, 32, 42, 52, 13, 23, 33, 43, 53, 12', 22', 32', 42', 52', 13', 23', 33', 43', 53') all of the first ends (14, 24, 34, 44, 54, 14', 24') fixed to the horizontal stabilizer (8, 28) , 34', 44', 54', 15, 25, 35, 45, 55, 15', 25', 35', 45', 55') and their respective free ends (16, 26, 36, 46, 56, 16', 26', 36', 46', 56', 17, 27, 37, 47, 57, 17', 27', 37', 47', 57') and 90° to 175° The free ends (16, 26, 36) of the left bottom/top fin airfoils (12, 22, 32, 42, 52, 13, 23, 33, 43, 53) to form a dihedral angle in the range of 46, 56, 17, 27, 37, 47, 57) are the first ends of the left bottom/upper fin airfoils 12, 22, 32, 42, 52, 13, 23, 33, 43, 53 ( 14, 24, 34, 44, 54, 15, 25, 35, 45, 55), and the right bottom/top fin airfoils to form a back angle in the range of 90° to 175° (12', 22', 32', 42', 52', 13', 23', 33', 43', 53') of the free ends (16', 26', 36', 46', 56' , 17', 27', 37', 47', 57') are the right bottom/upper fin airfoils 12', 22', 32', 42', 52', 13', 23', 33', 43', 53') leading to the first ends (14', 24', 34', 44', 54', 15', 25', 35', 45', 55') , Hybrid rotorcraft. The method of claim 2,
The free end (16, 26, 36, 46, 56, 16') of the left/right bottom fin airfoil (12, 22, 32, 42, 52, 12', 22', 32', 42', 52'), 26', 36', 46', 56') are parallel to the front and rear midplane (XOZ) and left/right bottom pin airfoils (12, 22, 32, 42, 52, 12', 22', 32' , 42', 52') and the corresponding plane (P/P') comprising the first end (14, 24, 34, 44, 54, 14', 24', 34', 44', 54') and 5 Hybrid type rotorcraft that extends away to form an angle of inclination ranging from ° to 45 °. The method of claim 2,
Free end (17, 27, 37, 47, 57, 17') of left/right upper fin airfoil (13, 23, 33, 43, 53, 13', 23', 33', 43', 53'), 27', 37', 47', 57') are parallel to the front and rear midplane (XOZ) and left/right upper fin airfoils (13, 23, 33, 43, 53, 13', 23', 33' , 43', 53') and a corresponding plane (P/P') comprising the first end (15, 25, 35, 45, 55, 15', 25', 35', 45', 55') and 5 Hybrid type rotorcraft that extends away to form an angle of inclination ranging from ° to 45 °. The method of claim 1,
The inclination angle of the left/right bottom pin airfoil (12, 22, 32, 42, 52, 12', 22', 32', 42', 52') with respect to the corresponding plane (P/P') is left/ Hybrid type, different from the inclination angle of the upper right fin airfoil (13, 23, 33, 43, 53, 13', 23', 33', 43', 53') to the corresponding plane (P/P') Rotorcraft. The method of claim 1,
Among the first ends 14, 14', 15, 15' of the left/right and bottom/upper fin airfoils 12, 13, 12', 13' parallel to the front-rear midplane XOZ The orthogonal projection of each of the two fins 11 and 11' onto the corresponding plane (P/P') containing one, the tip 18 of the rotorcraft 10 Hybrid type rotorcraft, showing the shape of an arrow-head towards the front section (4). The method of claim 6,
The end portion (18) of each of the orthogonal projections is connected to a corresponding left/right distal region (9, 9') of the horizontal stabilizer (8). The method of claim 1,
The horizontal stabilizing plate 8 is disposed symmetrically with respect to the front-rear midplane XOZ, a hybrid rotorcraft. The method of claim 1,
The horizontal stabilizer 28 is disposed asymmetrically with respect to the front-rear midplane (XOZ), a hybrid rotorcraft. delete The method of claim 1,
The length of the left/right bottom fin airfoil (12, 22, 32, 42, 52, 12', 22', 32', 42', 52') is the length of the left/right upper fin airfoil (13, 23, 33). , 43, 53, 13', 23', 33', 43', 53'). The method of claim 1,
The twist of the left/right bottom pin airfoil (12, 22, 32, 42, 52, 12', 22', 32', 42', 52') is the left/right upper pin airfoil (13, 23, 33, 43, 53, 13', 23', 33', 43', 53'), different from the twist of the hybrid type rotorcraft. The method of claim 1,
Corresponding plane (P/P') of left/right bottom fin airfoil (12, 22, 32, 42, 52, 12', 22', 32', 42', 52') and left/right upper fin air Foils (13, 23, 33, 43, 53, 13', 23', 33', 43', 53') do not form a single-piece unit, and are made of two different parts. ), a hybrid rotorcraft.

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