CN111491855A

CN111491855A - Motor vehicle spoiler comprising aerodynamic blades with a plurality of flaps

Info

Publication number: CN111491855A
Application number: CN201880082009.8A
Authority: CN
Inventors: 弗兰克·莱特里尔; 阿尔诺·埃斯科菲
Original assignee: Plastic Omnium SE
Current assignee: Plastic Omnium SE
Priority date: 2017-12-26
Filing date: 2018-12-26
Publication date: 2020-08-04
Also published as: EP3732090A1; FR3075749A1; FR3075749B1; WO2019129794A1

Abstract

The invention relates to a rear spoiler (4) for a motor vehicle (2), characterized in that it comprises a movable aerodynamic blade (8), the movable aerodynamic blade (8) comprising a plurality of flaps (10), each flap (10) being rotationally movable about its own axis of rotation (A).

Description

Motor vehicle spoiler comprising aerodynamic blades with a plurality of flaps

Technical Field

The present invention relates to the field of motor vehicles, and in particular to spoilers for motor vehicles.

Background

Spoilers (spollers) refer to body components that form an extension of the rear of the roof of a vehicle intended to improve the aerodynamic performance of the motor vehicle in which the component is disposed. Spoilers are also used for the aesthetic appearance of the vehicle. They are usually located and fixed in the upper and rear parts of the vehicle, between the roof and the upper edge of the windows, on the roof or tailgate.

Spoilers are known which comprise movable aerodynamic blades, that is to say elements which improve the aerodynamic performance by moving the air further backwards with respect to the separation point of the vehicle (i.e. the point where the air no longer follows the body), which can be deployed by translation between a retracted position and a deployed position inside the spoiler.

This is particularly the case when the movable aerodynamic blade is deployed in a linear manner towards the rear of the vehicle, as described in document DE 19902289.

However, the use of rails or slides has a number of disadvantages.

Firstly, the sliding device is a relatively bulky mechanism, in particular in the axial deployment direction of the movable aerodynamic blade. In fact, the minimum axial dimension of the device in the retracted position is greater than the deployment stroke, and is particularly greater when using cantilever deployment. In fact, it is necessary to make the length of the slides able to ensure the required unwinding stroke, while maintaining the length of engagement between the different branches of each slide, which is critical both to ensure precise guidance of the end of the stroke, and to ensure robust support and reliability of the movable aerodynamic blade and of the forces acting thereon (in particular the aerodynamic forces to which the cantilever is subjected in the unfolded position).

In general, changing the deployed/retracted position of the aerodynamic blades between the outside and the inside of the spoiler does not allow a perfect seal to be achieved to protect the device from intrusion from the external environment (rain, snow, frost, dust, dry leaves). In addition, the sliding device is particularly fragile, since its proper function depends mainly on the quality of the guidance provided by the branches of the slide. Therefore, it is necessary to provide a mechanism for protecting the slide device, which leads to an increase in the weight of the device, an increase in the design cost, and an increase in the size.

Finally, the sliding device is difficult to implement. It is indeed necessary to ensure excellent parallelism between the slides to ensure correct guidance of the device. Geometric dispersion inherent in mass production and distortion due to aging over life can hinder proper operation by losing parallelism.

Devices for unwinding aerodynamic blades implemented by blades rotating around a vertical axis by a plurality of foils, the different foils of which share the same axis of rotation, are also known, for example in document FR 2972994.

The disadvantage of this device is again that it is bulky, but this time in the vertical direction. In fact, the fact that different portions share the same axis of rotation results in a stacking of the portions in a vertical direction. It is then necessary to divide the aerodynamic blade into two separate side portions so that the overall dimensions in the central region, in the retracted position, do not interfere with the third brake (park) light, nor do they obscure it in the deployed position. Thus, the overall structure of several discrete parts becomes more complex.

Disclosure of Invention

The present invention aims to remedy these drawbacks by providing a spoiler for a motor vehicle comprising movable aerodynamic blades that can be deployed by means of less bulky and less expensive mechanisms than those described above.

To this end, the invention relates to a rear spoiler for a motor vehicle, comprising a movable aerodynamic blade comprising a plurality of flaps, each flap being rotationally movable about its own axis of rotation.

Thus, the individual flaps of the movable aerodynamic device are deployed by rotation, thereby obviating the need for bulky sliding mechanisms, which are heavy and difficult to implement.

In addition, the fact that the different portions do not share the same axis of rotation makes it possible to overcome the need to stack the different portions constituting the movable aerodynamic blade. Thus, a vertical structure with a smaller volume can be obtained, wherein the number of stacking levels is smaller than the number of fins constituting the movable aerodynamic blade.

The spoiler according to the present invention may further comprise one or more of the following features:

-at least a part of said fins are symmetrically distributed with respect to a plane dividing the spoiler into a right side and a left side;

-at least one portion of said fins is distributed on a left portion and a right portion of said spoiler, said portions being separated by a transverse vertical plane of said spoiler passing through the center thereof when the spoiler is mounted on the motor vehicle, the rotation axis of each fin located on the left portion of said spoiler being symmetrical to the rotation axis of each fin located on the right portion of said spoiler with respect to the transverse vertical plane of said spoiler passing through the center thereof;

-the spoiler comprises a lower face and an upper face, the rotation of the flaps being able to be carried out between the planes of the lower face and the upper face of the spoiler;

-the axis of rotation is a substantially vertical axis when the spoiler is mounted on a motor vehicle;

-each tab overlaps with the tab with which it is in contact or at least one of the tabs with which it is in contact;

the different tabs extend in two planes parallel to each other, each tab extending in at least one different plane of the tab with which it is in contact or the tab with which it is in contact;

-the number of fins is odd;

the flaps are interconnected to each other by at least one connecting arm;

-all the flaps are rotated by means of a single actuator;

-an actuator is able to cooperate with only one of said flaps;

the actuator can cooperate with a gear wheel that can cooperate with a circular toothing of a tab connected to the gear wheel; and

the different airfoils of the movable aerodynamic blade are distributed at regular intervals.

The invention also relates to a motor vehicle comprising a spoiler according to the invention.

Drawings

We will now present embodiments of the invention by way of non-limiting example and with the support of the accompanying drawings, in which:

fig. 1 to 3 are perspective views of the rear part of a motor vehicle comprising a spoiler according to the invention, which spoiler comprises aerodynamic blades, which are in a retracted position, in the process of being deployed or retracted, and in a deployed position inside the spoiler respectively,

figure 4a is a schematic top view of the movable aerodynamic device according to the invention in a retracted position inside the spoiler,

fig. 4b is a schematic top view of the movable aerodynamic device according to the invention in a deployed position, deployed in extension of the rear end of a motor vehicle when the rear spoiler is mounted on the motor vehicle.

FIGS. 5a and 5b are rear views of two examples of possible overlaps of the vanes constituting the movable aerodynamic blade, an

Fig. 6 to 8 are schematic views of an airfoil constituting an aerodynamic blade in a retracted position, during deployment or retraction, and in a deployed position inside a spoiler, respectively.

Detailed Description

We now refer to fig. 1 to 3, which illustrate embodiments of the present invention. In the following, directional terms, such as "longitudinal axis X", "transverse axis Y", "vertical axis Z", "front", "rear", "above", "below" and the like, refer to the usual directions of a motor vehicle as shown in the coordinate system of fig. 1.

These figures show the rear of a motor vehicle 2 comprising a spoiler 4. In this example, the spoiler 4 is intended to be arranged in the rear edge region of the roof above the rear window 6 and comprises a movable aerodynamic blade 8 which is movable between a retracted position (visible in fig. 1) and a deployed position (visible in fig. 3) inside the spoiler 4. The movable aerodynamic blade 8 is composed of a plurality of airfoils 10. The combination of the different flaps 10 and their arrangement relative to each other makes it possible to form a movable aerodynamic blade 8, said movable aerodynamic blade 8 having, in this example, a continuous surface between its two most distal ends in a direction parallel to the transverse axis Y of the vehicle 2. This means that two adjacent fins 10 (which are continuous in a direction parallel to the transverse axis Y of the vehicle 2 when the spoiler 4 is mounted on the motor vehicle 2) can be superposed on at least 5% of the surface of the fin 10, preferably at least 25% of the surface of the fin 10. The trailing edge (bird de foil) line 13 of the movable air blade 8 does not include a corner point (points anguletux), but as shown, can form a curved line including a circle. Different fins 10 can be arranged at regular intervals. Fig. 1 to 3 show a movable aerodynamic blade 8 comprising five airfoils 10. Obviously, this number may vary.

The fins 10 are all rotationally movable. For example a rotation of an angle equal to 180 deg.. The angle of rotation of the fins 10 may differ from 180 deg., depending on the number of fins 10, the length of the outlet of the fins to be implemented, but also the aerodynamic shape of the trailing edge line. Each foil 10 is rotationally movable about a rotation axis a different from the other foils (which means that its rotation axis is specific), the rotation axes of the different foils being able to be parallel to each other, as seen in fig. 5a and 5 b.

In the example shown in the figures, the axis of rotation a is an axis parallel to the vertical axis Z of the vehicle 2 when the spoiler 4 is mounted on a motor vehicle. This may vary depending on the arc of the vehicle 2. In fact, the rotation axis a of the vane 10 is generally perpendicular to the different planes (strictly speaking, it may be a plane comprising, for example, one face of the vane 10, the vane 10 being a solid element) in which the different vanes 10 of the movable air blade 8 extend, whether or not these planes are perpendicular to the vertical axis Z. In other words, if the movable aerodynamic blade 8 consists of an airfoil 10 moving in a non-horizontal plane, the axis of rotation a will not be parallel to the vertical axis Z of the vehicle 2. In any case, at least a portion of the fins 10 is symmetrically distributed with respect to a plane separating the right and left sides of the spoiler. The plane may be, for example, a transverse vertical plane of the spoiler 4 passing through the center thereof when the spoiler 4 is mounted on the vehicle 2. Thus, the plane may be a plane passing through the center of the vehicle coincident with a longitudinal vertical plane of the vehicle 2, commonly referred to as the "Y0 plane" of the vehicle 2. It is also conceivable that the axes of rotation of the vanes 10 are not parallel to each other or that the vanes 10 are not planar, so that the movable aerodynamic blade 8 has a shape that is adapted to the curvature (curve) of the vehicle 2.

The axes of rotation a may also be parallel to each other, but not parallel to the vertical axis Z of the vehicle 2, when the spoiler is mounted on the motor vehicle. When the spoiler 4 is mounted on the motor vehicle, the rotation axis a may be aligned along an axis parallel to the transverse axis Y of the vehicle 2, or may be aligned along a curve 17 having the same shape as the trailing edge line 13.

The fins 10 may be distributed in a number of levels which is smaller than the number of fins 10 constituting the movable aerodynamic blade 8. As described above, this reduces the volume in the direction parallel to the vertical axis Z. For example (fig. 5b) it is possible that different fins 10 extend in two planes parallel to each other, each fin 10 extending in at least one different plane of the other fin 10 in contact therewith or of the fin 10 in contact therewith. Preferably, the fins 10 are arranged alternately in each of the two layers. In this case, the space requirement is greatly reduced, since the fins 10 lie in only two planes. This is therefore the best compromise between the reduction in size and the ease of movement of the different vanes 10. In fact, the distribution in the two planes makes it possible to prevent the different vanes 10 from interfering with each other in motion, while ensuring a satisfactory shape of the movable aerodynamic blade 8 due to the overlap between the different vanes 10. Alternatively, as shown in fig. 5a, the fins 10 may be distributed in three levels.

The choice of shape of the airfoil 10 will be guided by the search for a compromise between reducing size, ease of deployment and improving the aerodynamic performance of the vehicle 2.

With regard to the mechanism of deployment and retraction of the aerodynamic blades 8, this may be provided: a single blade 10 is actuated to move and rotation of the blade can actuate the other vanes 10 (each vane 10 can also be actuated individually). In this case, the different fins 10 can be connected to each other by means of connecting arms 14 (for example, rods, visible in fig. 6 to 8) or any other means that enable the movement of all the parts 10 as long as the movement of one of these fins is able to move. The flaps 10 may be deployed and retracted simultaneously but also sequentially.

For example, an actuator 15, for example an electric motor with direct torque and angular output, is able to move a gear 16, which gear 16 is for example at one end of the spoiler 4 and can in any case be in contact with one of the flaps 10 forming the movable aerodynamic blade 8. The setting of the actuator 15 to move the gear wheel 16 can be performed by means of one or more other gear wheels or by means of a belt (not shown) transmission connecting the actuator 15 to the gear wheel 16. The gear 16 may mesh with a circular tooth portion (not shown) formed on the vane 10 in contact with the gear 16. The fins 10 in contact with the gear 16 are connected directly or indirectly to all the other fins 10 constituting the movable aerodynamic blade 8 by means of moving all the other elements 10, for example by means of the connecting arms 14 visible in fig. 6 to 8. Wherein the movement arrangement of the lowermost wing 10 enables the other wings 10 to move in a synchronized manner by means of the connecting arms 14. It should be noted that the connecting arms are fixed to the flaps 10 by means of a connection that can rotate with respect to each other, for example a pivoting connection.

When the vehicle 2 is travelling, and a threshold speed is reached, the movable aerodynamic blade 8 is deployed. In view of the above-described example of an actuating mechanism, an actuator 15 connected to the electronic control unit of the vehicle moves the gear 16, for example by means of a belt or at least one other gear. The gear 16 then, due to its cooperation with the circular toothing, rotates the vane 10 in contact therewith about its rotation axis a. The foils 10 cooperate with the gear 16 to drive the other foils 10 about their respective rotational axes a in order to deploy the aerodynamic blade 8. As mentioned before, the wings may be rotated through 180 °, or at least a determined angle, depending on the various parameters mentioned. The above. For this purpose, it can be provided that the actuator 15 moves the gear wheel 16 at a defined speed and for a defined duration. Depending on the actuation system, an end stop may also be provided (e.g., at the flap 10 that is initially actuated) to ensure that the component 10 is in the optimal deployed position.

When the speed decreases and falls below the threshold speed, the actuator 15 moves the gear 16 in a direction opposite to the direction in which deployment is allowed. This has the consequence of causing all the flaps 10 (by the flaps in contact with the gear 16) to rotate in the opposite direction to that which allows them to unfold. This causes the movable aerodynamic blade 8 to retract.

The present invention is not limited to the embodiments presented and other embodiments will be apparent to those skilled in the art.

In particular, the number of fins 10, the number of levels on which the fins are distributed, the spacing between different fins 10, and even the deployment/retraction mechanism of the movable aerodynamic blade 8 may be varied.

Glossary

2: motor vehicle

4: spoiler

6: rear window

8: movable aerodynamic blade

10: wing panel

12: rear end of spoiler

13: trailing edge line

14: connecting arm

15: actuator

16: gear wheel

17: curve line

A: axis of rotation

Claims

1. A rear spoiler (4) for a motor vehicle (2), characterized in that it comprises a movable aerodynamic blade (8), which movable aerodynamic blade (8) comprises a plurality of flaps (10), each flap (10) being rotationally movable about its own axis of rotation (a).

2. Spoiler (4) according to claim 1, wherein at least a part of the fins (10) are symmetrically distributed with respect to a plane dividing the spoiler (4) into a right side and a left side.

3. Spoiler (4) according to claim 2, wherein at least a part of the fins (10) is distributed over a left and a right part of the spoiler (4), said parts being separated by a transverse vertical plane of the spoiler (4) passing through the centre of the spoiler (4) when the spoiler (4) is mounted on a motor vehicle (2), the axis of rotation (a) of each fin (10) located at the left part of the spoiler being symmetrical to the axis of rotation (a) of the fin (10) located at the right part of the spoiler (4) with respect to the transverse vertical plane of the spoiler (4) passing through the centre of the spoiler (4).

4. Spoiler (4) according to one of the preceding claims, comprising a lower face and an upper face, the rotation of the flaps (10) being able to be carried out between the planes in which the lower face and the upper face of the spoiler (4) lie.

5. Spoiler (4) according to any one of the preceding claims, wherein the rotation axis (a) is a substantially vertical axis when the spoiler (4) is mounted on a motor vehicle (2).

6. Spoiler (4) according to any one of the preceding claims, wherein each foil (10) overlaps at least one of the foil (10) with which it is in contact or the foil (10) with which it is in contact.

7. Spoiler (4) according to any one of the preceding claims, wherein different flaps (10) extend in two planes parallel to each other, each flap (10) extending in at least one different plane of the flap (10) in contact therewith or of the flap (10) in contact therewith.

8. Spoiler (4) according to one of the preceding claims, wherein the number of fins (10) is odd.

9. Spoiler (4) according to one of the preceding claims, wherein the wings (10) are connected to each other by means of at least one connecting arm (14).

10. Spoiler (4) according to one of the preceding claims, wherein all wings (10) are rotated by means of a single actuator (15).

11. Spoiler (4) according to claim 10, wherein the actuator (15) is able to cooperate with only one of the flaps (10).

12. Spoiler (4) according to any one of claims 10 and 11, wherein the actuator (15) is adapted to cooperate with a gear wheel (16), which gear wheel (16) is adapted to cooperate with a circular toothing of the flap (10) connected to this gear wheel (16).

13. Spoiler (4) according to any of the previous claims, wherein the different flaps (10) of the movable aerodynamic blade (8) are distributed at regular intervals.

14. A motor vehicle (2) comprising a spoiler (4) according to any one of the preceding claims.