CN210391545U - Aircraft tire lateral water deflector and aircraft landing gear - Google Patents
Aircraft tire lateral water deflector and aircraft landing gear Download PDFInfo
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- CN210391545U CN210391545U CN201921091934.5U CN201921091934U CN210391545U CN 210391545 U CN210391545 U CN 210391545U CN 201921091934 U CN201921091934 U CN 201921091934U CN 210391545 U CN210391545 U CN 210391545U
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Abstract
The utility model provides an aircraft tire side water guide plate and aircraft undercarriage, can be through simple structure, with the rivers guide of aircraft tire side splash in order to avoid the engine, manger plate is effectual, maintains and the operation cost is low. The aircraft tire side water guide plate includes: a mounting portion mounted to a mounting object; a connection portion provided obliquely so as to be bent inward by a first predetermined angle with respect to the mounting portion; and a water guide portion formed in a wedge shape or a pointed cone shape so as to be bent inward at a second predetermined angle with respect to the connection portion on a side of the connection portion opposite to the mounting portion, the first predetermined angle and the second predetermined angle being formed so that the water guide portion forms a water guide angle obliquely upward with respect to a horizontal direction. The aircraft landing gear includes: a landing gear axle; and the lateral water guide plates are arranged on two sides of the landing gear wheel shaft.
Description
Technical Field
The utility model relates to an aircraft landing gear structural design, more specifically relate to an aircraft landing gear that aircraft tire side direction water deflector and be equipped with aircraft tire side direction water deflector, above-mentioned aircraft tire side direction water deflector is used for guiding the rivers that aircraft tire side splashes and avoids the engine to reduce the engine and intake.
Background
According to the requirements of relevant clauses of airworthiness standards of transport-type airplanes, the degree of foreign object suction of an engine is minimized in the stages of airplane taxiing, takeoff and landing. The foreign matter referred to here is mainly track water.
On the other hand, an aircraft having a tail boom layout (hereinafter simply referred to as a "tail boom layout aircraft") is more likely to have a problem that water enters the engine due to water splashing from tires because the engine is located close to the fuselage. In particular, when the aircraft is taxiing on a hydroplaning runway, the splash side stream of the front wheel may more easily enter the engine.
In the prior art, the problem that the water splashed by the tires enters the engine is solved or improved in several ways.
(1) Additionally arranging a water retaining flanging on the tire
The addition of a water-stop bead to a tire (e.g., a front tire) specifically forms a skirt on the sidewall of the tire, the skirt being made of the same rubber material as the tread of the tire.
Through add the manger plate turn-ups on the tire, can keep off the tire splash to a certain extent to simple structure can not lead to promoting by a wide margin of cost.
On the other hand, the water retaining effect of the water retaining flange additionally arranged on the tire is limited, and particularly for certain types of tires, the problem of water splashing cannot be solved through the water retaining flange.
(2) Water baffle is additionally arranged on undercarriage
The water baffle is additionally arranged on the landing gear, so that most of water flow can be effectively blocked. The existing aircraft mainly presses water flow by additionally arranging a water baffle around a tire so that the water flow does not enter an engine. The installation form of the water baffle mainly comprises: (i) the structure of adding water baffles on the side and the rear part of the tire as shown in figure 1; and (ii) the addition of water dams at the sides and front of the tire as shown in FIG. 2, in a similar manner to that of (i).
However, in both the water deflector installation form (i) and the water deflector installation form (ii), it is necessary to wrap the water deflector over almost half or more of the outer contour surface area of the tire in order to press most of the water flow as much as possible.
In addition, because the impact force of rivers is big, consequently, in order to guarantee the intensity of breakwater, need make the breakwater thick and heavy, need set up a lot of installation interfaces with undercarriage adaptation simultaneously.
In view of the structural complexity of these two forms of breakwater installation, and the cumbersome installation and high maintenance costs, the cost of airline operations is increased.
Therefore, how to design an aircraft tire lateral water guide plate with simple structure, good water retaining effect and low cost and an aircraft landing gear with the aircraft tire lateral water guide plate becomes a technical problem to be solved urgently.
SUMMERY OF THE UTILITY MODEL
The utility model discloses a solve above-mentioned technical problem and do, its aim at provides an aircraft tire side direction water deflector and is equipped with the aircraft undercarriage of aircraft tire side direction water deflector, can be through simple structure, with the rivers guide of aircraft tire side splash in order to avoid the engine, the manger plate is effectual, maintains and the operation cost is low.
In order to solve the technical problem, an aspect of the utility model provides an aircraft tire side guide plate, characterized by includes: a mounting portion mounted to a mounting object; a connection portion that is provided obliquely so as to be bent inward by a first predetermined angle with respect to the mounting portion; and a water guide portion formed in a wedge shape or a pointed cone shape so as to be bent inward at a second predetermined angle with respect to the connection portion on a side of the connection portion opposite to the mounting portion, the first predetermined angle and the second predetermined angle being formed so that the water guide portion forms a water guide angle obliquely upward with respect to a horizontal direction.
According to the above configuration, since the connecting portion is provided obliquely so as to be bent inward by the first predetermined angle with respect to the mounting portion, the water guide portion is formed in a wedge shape or a pointed cone shape so as to be bent inward by the second predetermined angle with respect to the connecting portion on the side opposite to the mounting portion of the connecting portion, and the first predetermined angle and the second predetermined angle are formed so as to make the water guide portion form a water guide angle obliquely upward with respect to the horizontal direction, water on the ground is splashed due to contact between the tire and the ground during, for example, a rainy day, the aircraft can receive the splashed water by the water guide portion by the aircraft tire side water guide plate configured as described above, and guide the splashed water to avoid the engine by the water guide portion provided obliquely upward by the water guide angle with respect to the horizontal direction, whereby the water flow splashed by the tire side of the aircraft can be guided to avoid the engine by a simple configuration, the water retaining effect is good.
Preferably, the first predetermined angle is an acute angle smaller than 30 °, and the second predetermined angle is a right angle or an obtuse angle close to a right angle, so that the water diversion angle is equal to or larger than the first predetermined angle.
Preferably, the aircraft tire side guide plate further comprises a diagonal portion.
Preferably, the slanted portion is a rib having a triangular plate shape.
Preferably, the water guide portion has an inner side surface on one side in a bending direction and an outer side surface on the side away from the bending direction, one side of the triangular plate-shaped rib is formed at a widthwise center of the inner side surface of the water guide portion, and the other side of the triangular plate-shaped rib is formed at a widthwise center of the inner side surface of the connecting portion.
Preferably, one side of the triangular plate-shaped rib extends on the inner side surface of the water guide part to a position not exceeding a sharp edge of the water guide part, and the other side of the triangular plate-shaped rib extends on the inner side surface of the connecting part to a position not exceeding a half height of the connecting part.
In traditional breakwater, need bear a large amount of splash load, so require structural strength height, heaviness, and the utility model discloses an aircraft tire side direction water deflector need not to push down rivers, only need follow the trend with rivers guide in order to avoid getting into the engine, consequently, only need set up diagonal brace piece and can guarantee sufficient intensity.
Preferably, the mounting portion has a mounting hole to which a shaft of the mounting object is mounted.
According to the structure, the single mounting hole is only arranged on the mounting part of the aircraft tire side guide plate so as to be connected with a mounting object (undercarriage wheel axle), so that the interface is single, the structure is greatly simplified, the maintenance cost can be saved, and the efficiency is improved.
Meanwhile, a large amount of labor cost and material cost are not needed to be spent for maintenance, and the maintenance and operation cost is low.
The utility model discloses an on the other hand provides an aircraft undercarriage, characterized by, include: a landing gear axle; the lateral water guide plates are arranged on the two sides of the landing gear wheel shaft.
Preferably, a stop is provided between the landing gear axle and the mounting hole of the mounting portion of the aircraft tire side water deflector; fasteners and locks to secure the aircraft sidewall to the landing gear axle and prevent removal.
The aircraft landing gear with the aircraft tire lateral water guide plate can guide water flow splashed by the side edge of the aircraft tire to avoid an engine through a simple structure, and is good in water retaining effect and low in maintenance and operation cost.
Drawings
FIG. 1 is a view showing a structure for attaching water guards to the side and rear portions of a tire according to the prior art.
FIG. 2 is a view showing a structure of attaching water dams to the side and front of a tire according to the prior art.
Fig. 3 is a side view of the air guide plate for an aircraft tire according to the present invention.
Fig. 4 is a front view of the air guide plate for an aircraft tire side according to the present invention.
Fig. 5 is a view showing an installation form of the air guide plate to the tire side of the aircraft according to the present invention.
Fig. 6 is a schematic view showing the effect of guiding the water flow to the water guide plate at the tire side of the aircraft according to the present invention.
Detailed Description
Hereinafter, the aircraft tire side guide plate 100 of the present invention will be described in detail with reference to fig. 3 to 6. Fig. 3 is a view showing a side surface of the aircraft tire side guide plate 100 of the present invention, fig. 4 is a view showing a front surface of the aircraft tire side guide plate 100 of the present invention, fig. 5 is a view showing an installation form of the aircraft tire side guide plate 100 of the present invention, and fig. 6 is a schematic view showing a water flow guide effect of the aircraft tire side guide plate 100 of the present invention.
The utility model discloses an aircraft tire side water deflector 100 is the water deflector who installs additional at the undercarriage, and more specifically, as shown in FIG. 5, above-mentioned aircraft tire side water deflector 100 installs the both sides at undercarriage shaft 200.
As shown in the side view of fig. 3 and the front view of fig. 4, the aircraft tire side guide panel 100 includes a mounting portion 110, a connecting portion 120, a water guide portion 130, and a sprag portion 140.
More specifically, a mounting hole 111 is formed at the center of the mounting portion 110, and the aircraft tire side water deflectors 100 are mounted to portions on both sides of the landing gear axle 200 through the mounting hole 111.
The connecting portion 120 is provided obliquely so as to be bent inward at a first predetermined angle a1 with respect to the mounting portion 110 at the middle of the aircraft sidewall guide plate 100.
The water guide 130 is formed in a wedge shape or a pointed cone shape so as to be bent inward by a second predetermined angle a2 with respect to the connection portion 120 on the side of the connection portion 120 opposite to the mounting portion 110, and has an inner side surface 131 and an outer side surface 132 on the side in the bending direction.
The phrase "one member is bent to the inner side with respect to the other member" herein means that "a plane on which one member is located is bent to the counterclockwise direction with respect to a plane on which the other member is located".
The inclined support portion 140 is, for example, a triangular plate-shaped rib, one side 141 of which is formed at the center in the width direction of the inner surface 131 of the water guide portion 130 and extends on the inner surface 131 of the water guide portion 130 so as not to exceed the tip edge of the water guide portion 130, and the other side 142 of which is formed at the center in the width direction of the connection portion 120 and extends on the inner surface 121 of the connection portion 120 so as not to exceed half the height of the connection portion 120.
The first predetermined angle a1 and the second predetermined angle a2 are formed such that the water guide 130 forms a water guide angle A3 obliquely upward with respect to the horizontal direction.
Preferably, the water guide angle A3 is equal to or greater than the first predetermined angle a1, that is, the outer surface 132 of the water guide 130 is bent perpendicularly or at an obtuse angle close to a right angle with respect to the connection portion 120.
The "acute angle close to a right angle" herein means a range in which, although not a right angle (90 °), substantially the same effect as that of a perpendicular angle (90 °) in a strict sense can be achieved in an obtuse angle range larger than 90 °.
As an exemplary structure of the aircraft tire side guide plate 100 of the present invention, as shown in fig. 3, in the case where the mounting portion 110 is provided along the plumb direction, the connecting portion 120 is bent inward (counterclockwise or right side of fig. 3) with respect to the plumb direction (or the mounting portion 110), for example, by 16 °. That is, the first predetermined angle a1 is, for example, 16 °. Thus, the angle between the connection portion 120 and the mounting portion 110 is, for example, (180 ° -16 °) 164 °.
As shown in fig. 3, when the mounting portion 110 is disposed along the plumb bob direction, the water guide portion 130 is bent inward, for example, 94 ° with respect to the connection portion 120. That is, the second predetermined angle a2 is, for example, 94 °. At this time, the outer surface 132 of the water guide 130 forms an angle of 86 °, for example, (16 ° + (180 ° -90 ° -20 °), with the connection portion 120, and the outer surface 132 of the water guide 130 forms an angle of 20 ° with respect to the horizontal direction, for example. That is, the diversion angle A3 is, for example, 20.
It should be noted that the first predetermined angle a1 ("16 °"), the second predetermined angle a2 ("94 °"), and the water diversion angle A3 ("20 °") listed above are merely examples, and the angle formed by the water diversion part 130, the connection part 120, and the mounting part 110 may be appropriately adjusted as long as the water diversion part 130 of the water diversion panel 100 can block the water flow splashed by the tire side of the aircraft and guide the water flow to avoid the engine.
Will the utility model discloses a step as follows of undercarriage is installed to aircraft tire side guide plate 100:
first, the aircraft tire side guide plate 100 is placed on both sides of the landing gear axle 200, and the landing gear axle 200 is inserted through the mounting hole 111 of the mounting portion 110;
next, a stop 300 is provided between the landing gear axle 200 and the mounting hole 111 to prevent the aircraft tire side water deflector 100 from rotating relative to the landing gear axle 200;
finally, the aircraft tire side water deflector 100 is fastened to the landing gear axle 200 by fasteners such as bolts and nuts and locking members such as safety pins, and is prevented from falling off.
The technical effect of the aircraft tire side guide plate 100 according to the present invention will be described with reference to fig. 6.
The utility model discloses a structure of aircraft tire side water guide plate 100, especially water guide 130, connecting portion 120, the mutual angle that becomes of installation department 110 three are confirmed after the characteristic of splashing through studying the tire, can be applicable to various tail and hang the aircraft particularly ideally to hang the aircraft with the tail outside the water guide to the lip of engine that aircraft nose landing gear splashes, very efficient guiding device.
As shown in fig. 6, in the process of the aircraft sliding in rainy days, for example, the tire T contacts with the ground G, so that the water W on the ground G splashes, and the water guide plate 100 for the aircraft tire side of the present invention can guide the splashed water W to avoid the engine by using the outer side surface 132 of the water guide portion 130, which is inclined obliquely upward with respect to the horizontal direction so as to form a water guide angle a3 (20 ° in the exemplary structure shown in fig. 3), and guide the splashed water to avoid the engine.
On the other hand, since only the single mounting hole 111 is provided in the mounting portion 110 of the aircraft tire side guide plate 100 to connect with the landing gear axle 200, the interface is single, the structure is greatly simplified, the maintenance cost can be saved, and the efficiency is improved.
Meanwhile, a large amount of labor cost and material cost are not needed to be spent for maintenance, and the maintenance and operation cost is low.
In addition, in traditional breakwater, need bear a large amount of splash water loads, so require structural strength height, heaviness, and the utility model discloses an aircraft wheel side need not to push down the rivers to breakwater 100, only need follow the same trend with rivers guide in order to avoid getting into the engine, consequently, only need set up diagonal bracing piece and can guarantee sufficient intensity.
Additional advantages and modifications will readily occur to those skilled in the art. Therefore, the invention in its broader aspects is not limited to the specific details and representative embodiments shown and described herein. Accordingly, modifications may be made without departing from the spirit or scope of the general inventive concept as defined by the appended claims and their equivalents.
In the foregoing description of the present invention, as an exemplary embodiment, the first prescribed angle a1 is, for example, 16 °, the second prescribed angle a2 is, for example, 94 °, and the water diversion angle A3 is, for example, 20 °, the present invention is not limited to this, and the first prescribed angle a1 may be set to be less than 30 °, the second prescribed angle a2 may be set to 90 ° ± 10 °, and the water diversion angle A3 may be set to 15 ° ± 45 ° from the viewpoint of effectively retaining splashed water and preventing splashed water from entering the engine.
Claims (9)
1. An aircraft tire sidewall guide deflector (100), comprising:
a mounting portion (110), the mounting portion (110) being mounted to a mounting object;
a connection part (120), wherein the connection part (120) is obliquely arranged in a manner of bending inwards relative to the mounting part (110) by a first predetermined angle (A1);
a water guide part (130), wherein the water guide part (130) is formed in a wedge shape or a pointed cone shape so as to be bent inward by a second predetermined angle (A2) with respect to the connection part (120) on the opposite side of the connection part (120) from the mounting part (110),
the first predetermined angle (A1) and the second predetermined angle (A2) are formed such that the water guide section (130) forms a water guide angle (A3) obliquely upward with respect to the horizontal direction.
2. The aircraft tire side guide plate (100) of claim 1,
the first prescribed angle (A1) is an acute angle of less than 30 DEG, and the second prescribed angle (A2) is a right angle or an obtuse angle close to a right angle, whereby the water diversion angle (A3) is equal to or greater than the first prescribed angle (A1).
3. The aircraft tire side guide plate (100) of claim 1,
the aircraft tire sidewall guide vane (100) further comprises a diagonal support portion (140).
4. The aircraft tire side guide plate (100) of claim 3,
the diagonal support portion (140) is a triangular plate-shaped rib.
5. The aircraft tire side guide plate (100) of claim 4,
the water guide part (130) has an inner side surface (131) on one side in the bending direction and an outer side surface (132) on one side far away from the bending direction,
one side (141) of the triangular plate-shaped rib is formed at the center of the width direction of the inner side surface (131) of the water guide part (130),
the other side (142) of the triangular plate-shaped rib is formed at the center in the width direction of the inner side surface (121) of the connecting portion (120).
6. The aircraft tire side guide plate (100) of claim 5,
one side (141) of the triangular plate-shaped rib extends on the inner side surface (131) of the water guide part (130) to a sharp edge which does not exceed the water guide part (130),
the other side (142) of the triangular plate-shaped rib extends on the inner side surface (121) of the connecting part (120) for no more than half of the height of the connecting part (120).
7. The aircraft tire side guide plate (100) of claim 1,
the mounting part (110) has a mounting hole (111) to which a shaft of the mounting object is mounted.
8. An aircraft landing gear, comprising:
a landing gear axle (200); and
the aircraft tire sidewall guide vane (100) of any one of claims 1 to 7 disposed on either side of the landing gear axle (200).
9. An aircraft landing gear according to claim 8, further comprising:
a stopper provided between the landing gear axle (200) and a mounting hole (111) of a mounting portion (110) of the aircraft tire side guide plate (100);
a fastener and a lock for fastening the aircraft sidewall guide plate (100) to the landing gear axle (200) and preventing the aircraft sidewall guide plate from falling off.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921091934.5U CN210391545U (en) | 2019-07-12 | 2019-07-12 | Aircraft tire lateral water deflector and aircraft landing gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921091934.5U CN210391545U (en) | 2019-07-12 | 2019-07-12 | Aircraft tire lateral water deflector and aircraft landing gear |
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| Publication Number | Publication Date |
|---|---|
| CN210391545U true CN210391545U (en) | 2020-04-24 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921091934.5U Active CN210391545U (en) | 2019-07-12 | 2019-07-12 | Aircraft tire lateral water deflector and aircraft landing gear |
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| CN (1) | CN210391545U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112644740A (en) * | 2020-12-31 | 2021-04-13 | 中国科学院长春光学精密机械与物理研究所 | Locking mechanism of aerospace device |
| CN115743651A (en) * | 2022-11-30 | 2023-03-07 | 中航(成都)无人机系统股份有限公司 | Ponding structure and unmanned aerial vehicle are prevented to unmanned aerial vehicle steering wheel actuator |
-
2019
- 2019-07-12 CN CN201921091934.5U patent/CN210391545U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112644740A (en) * | 2020-12-31 | 2021-04-13 | 中国科学院长春光学精密机械与物理研究所 | Locking mechanism of aerospace device |
| CN115743651A (en) * | 2022-11-30 | 2023-03-07 | 中航(成都)无人机系统股份有限公司 | Ponding structure and unmanned aerial vehicle are prevented to unmanned aerial vehicle steering wheel actuator |
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