Undercarriage and aircraft with same
By using the coordination between the limiting parts and the limiting parts in the landing gear of the aircraft, the rotation stroke of the aircraft wheel is limited, which solves the problem of excessive rotation of the aircraft wheel damage to the turning actuator and improves the working reliability of the aircraft.
Patent Information
- Application Number
- CN202420875502.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-04-24
- Publication Date
- 2025-02-11
- Estimated Expiration
- 2034-04-24
AI Technical Summary
During the turning process of the landing gear of the existing aircraft, excessive rotation of the wheels is likely to damage the turning actuator or direction control components.
A landing gear is designed to limit the rotation stroke of the wheel through the coordination of the limiting parts and the limiting parts, thereby avoiding excessive rotation of the wheel.
It effectively avoids damage to the turning actuator or direction control components by excessive rotation of the aircraft wheel, and improves the working reliability of the aircraft.
Smart Images
Figure CN222452523U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of aircraft, in particular to a landing gear and an aircraft having the same. Background Art
[0002] The landing gear is an important component of an aircraft. When the aircraft is driving on the ground, the wheels on the landing gear rotate to achieve the aircraft's turning. When the wheels rotate excessively, the turning actuator on the aircraft is easily damaged. Utility Model Content
[0003] The utility model aims to solve at least one of the technical problems existing in the prior art. To this end, the utility model proposes a landing gear, which can limit the turning travel of the wheels.
[0004] The utility model also provides an aircraft with the landing gear.
[0005] The landing gear according to the first aspect of the utility model includes: an outer tube, the upper end of which is suitable for being connected to the fuselage of the aircraft; a piston rod and a wheel, the upper end of the piston rod is movably arranged in the outer tube and the lower end extends out of the outer tube, and the wheel is connected to the lower end of the piston rod; a torque arm assembly, the upper end of the torque arm assembly is provided with a rotating cylinder, the rotating cylinder is rotatably mounted on the outer tube, and the lower end of the torque arm assembly is connected to the piston rod; a limiting member, one end of the limiting member is connected to one of the rotating cylinder and the outer tube, the other of the rotating cylinder and the outer tube is provided with a limiting portion, and the other end of the limiting member is configured to cooperate with the limiting portion to allow the rotating cylinder to rotate relative to the outer tube between a first position and a second position.
[0006] According to the landing gear of the first aspect of the utility model, the limiting member and the limiting portion cooperate to limit the rotational travel of the wheel during the turning process of the aircraft, thereby preventing the wheel from rotating excessively and damaging the turning actuator or the direction control component.
[0007] According to some embodiments of the utility model, the landing gear also includes: a limit support, which is arranged on the outer peripheral wall of one of the rotating drum and the outer drum, and the limit support forms a supporting surface. The limit member is provided with a mounting plate portion, and the mounting plate portion is arranged on the supporting surface and is detachably connected to the limit support.
[0008] According to some embodiments of the utility model, the limiting member includes a first section and a second section, the lower end of the first section is connected to the outer peripheral wall of the rotating drum, the upper end of the first section exceeds the upper end of the rotating drum, one end of the second section is connected to the upper end of the first section, and the other end extends toward the outer cylinder along the radial direction of the outer cylinder and cooperates with the limiting portion.
[0009] According to some embodiments of the present invention, a limiting boss extending along the circumference of the outer cylinder is formed at one end of the second section away from the first section, and the limiting boss cooperates with the limiting portion.
[0010] According to some embodiments of the present utility model, a surface of the limiting boss facing the outer cylinder is a cylindrical arc surface.
[0011] According to some embodiments of the present invention, a material reduction groove is formed on a side of the limiting member facing away from the rotating drum.
[0012] According to some embodiments of the utility model, the limiting portion includes: a first limiting protrusion and a second limiting protrusion, the first limiting protrusion and the second limiting protrusion are arranged at intervals in the circumferential direction of the outer cylinder, when the rotating cylinder is in the first position, the limiting member abuts against the first limiting protrusion, and when the rotating cylinder is in the second position, the limiting member abuts against the second limiting protrusion.
[0013] According to some embodiments of the utility model, a limiting fold surrounding the outer cylinder is also formed on the outer peripheral wall of the outer cylinder, and the limiting fold is arranged between the first limiting protrusion and the second limiting protrusion and the rotating cylinder, and the first limiting protrusion and the second limiting protrusion are connected to the limiting fold.
[0014] According to some embodiments of the utility model, the torque arm assembly includes: a first torque arm and a second torque arm, the first torque arm is rotatably connected to the second torque arm, the rotating cylinder is formed on the first torque arm, and the second torque arm is connected to the piston rod.
[0015] The aircraft according to the second aspect of the utility model comprises: the landing gear according to the first aspect of the utility model; and a steering actuator, wherein the steering actuator is connected to the rotating drum.
[0016] According to the aircraft of the second aspect of the utility model, by providing the landing gear according to the first aspect of the utility model, the reliability of the aircraft during operation can be improved.
[0017] Additional aspects and advantages of the present invention will be given in part in the following description, and in part will become apparent from the following description, or will be learned through the practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS
[0018] Figure 1 is a schematic diagram of a landing gear according to an embodiment of the utility model;
[0019] Figure 2 yes Figure 1 A schematic diagram of the connection between the rotating drum and the outer drum shown in ;
[0020] Figure 3 yes Figure 2 A schematic diagram of another angle of the limiting member shown in FIG.
[0021] Reference numerals:
[0022] 100. Landing gear;
[0023] 10. outer cylinder; 11. limiting portion; 111. first limiting protrusion; 112. second limiting protrusion; 12. limiting folding edge;
[0024] 20. Piston rod;
[0025] 30. Wheels;
[0026] 40. Torque arm assembly; 41. First torque arm; 411. Rotating drum; 42. Second torque arm;
[0027] 50, limit member; 51, first section; 52, second section; 521, limit boss; 53, material reduction groove; 54, mounting plate;
[0028] 60. Limit support. DETAILED DESCRIPTION
[0029] The embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and should not be construed as limiting the present invention.
[0030] Reference below Figure 1-Figure 3 A landing gear 100 according to an embodiment of the first aspect of the present invention is described.
[0031] like Figure 1 and Figure 2 As shown, the landing gear 100 according to the embodiment of the first aspect of the utility model includes: an outer tube 10, a piston rod 20, a wheel 30, a torque arm assembly 40 and a limit member 50.
[0032] Specifically, the upper end of the outer cylinder 10 is suitable for being connected to the fuselage of the aircraft, the upper end of the piston rod 20 is movably disposed in the outer cylinder 10 and the lower end extends out of the outer cylinder 10, the wheel 30 is connected to the lower end of the piston rod 20, the upper end of the torque arm assembly 40 is provided with a rotating cylinder 411, the rotating cylinder 411 is rotatably sleeved on the outer cylinder 10, the lower end of the torque arm assembly 40 is connected to the piston rod 20, one end of the limit member 50 is connected to one of the rotating cylinder 411 and the outer cylinder 10, the other of the rotating cylinder 411 and the outer cylinder 10 is provided with a limiting portion 11, and the other end of the limit member 50 is configured to cooperate with the limiting portion 11 to enable the rotating cylinder 411 to rotate relative to the outer cylinder 10 between the first position and the second position.
[0033] That is to say, one end of the limiting portion 11 may be connected to the rotating cylinder 411 , and the outer cylinder 10 is provided with the limiting portion 11 ; or one end of the limiting portion 11 may be connected to the outer cylinder 10 , and the rotating cylinder 411 is provided with the limiting portion 11 .
[0034] For example, the limiting portion 11 may include a limiting protrusion, and the limiting member 50 has two matching portions with the limiting protrusion, and when the rotating drum 411 is in the first position and the second position, the two matching portions respectively match with the limiting protrusion in a limiting manner; the limiting portion 11 may also include two limiting protrusions, and a part of the limiting member 50 rotates between the two limiting protrusions; the limiting portion 11 may also include a limiting protrusion and a limiting groove, and the limiting member 50 has two matching portions, and when the rotating drum 411 is in the first position and the second position, the two matching portions respectively match with the limiting protrusion and the limiting groove in a limiting manner; the limiting portion 11 may also be a limiting groove, and a part of the limiting member 50 moves between the two side walls of the limiting groove.
[0035] When the aircraft is traveling on the ground, the aircraft travels on the ground via the wheels 30 of the landing gear 100. When the fuselage of the aircraft shakes, the piston rod 20 moves up and down relative to the outer tube 10, and a damping force can be generated between the piston rod 20 and the outer tube 10, thereby achieving vibration reduction of the aircraft.
[0036] When the aircraft needs to turn, the turning actuator drives the rotating drum 411 to rotate relative to the outer drum 10, and the rotating drum 411 drives the piston rod 20 to rotate through the torque arm assembly 40, thereby rotating the wheel 30 connected to the piston rod 20, thereby realizing the turning of the aircraft.
[0037] It is understandable that when the wheel 30 rotates excessively, the displacement of the turning actuator or the direction control component connected to the wheel 30 will also be large. At the same time, the force acting on the wheel 30 is large, which can easily cause damage to the turning actuator or the direction control component.
[0038] In this embodiment, a limit member 50 is provided on one of the outer cylinder 10 and the rotating cylinder 411, and a limit portion 11 is provided on the other of the outer cylinder 10 and the rotating cylinder 411. The limit member 50 cooperates with the limit portion 11 to allow the rotating cylinder 411 to rotate between the first position and the second position relative to the outer cylinder 10, thereby limiting the rotational travel of the wheel 30, thereby preventing the wheel 30 from rotating excessively and causing damage to the turning actuator or the direction control component.
[0039] Among them, by setting the limiter 50 independent of the rotating drum 411 and the outer drum 10, during the production process, the limiter 50 can be assembled to the rotating drum 411 or the outer drum 10 in a timely manner according to the assembly space requirements, thereby reducing the difficulty of assembly. During the product design process, the structure of the limiter 50 can be adjusted to make the limiter 50 and the limiter 11 match more turning strokes, so that the structural changes to the rotating drum 411 or the outer drum 10 are relatively small, which can reduce the difficulty of product design.
[0040] According to the landing gear 100 of the first aspect of the utility model, the limit member 50 cooperates with the limit portion 11 to limit the rotation travel of the wheel 30 during the turning process of the aircraft, thereby preventing the wheel 30 from rotating excessively and damaging the turning actuator or direction control components.
[0041] In some embodiments of the present invention, Figure 1 and Figure 2 As shown, the landing gear 100 also includes: a limit support 60, the limit support 60 is arranged on the outer peripheral wall of one of the rotating drum 411 and the outer drum 10, the limit support 60 forms a support surface, and the limit member 50 is provided with a mounting plate portion 54, the mounting plate portion 54 is arranged on the support surface and is detachably connected to the limit support 60. By providing the limit support 60, the mounting plate portion 54 is connected to the support surface on the limit support 60 to improve the connection strength, and in the product design process, the size parameters of the limit support 60 and the limit member 50 can be adjusted to meet more limit scenarios, thereby reducing the difficulty of product design. Among them, the mounting plate portion 54 is detachably connected to the limit support 60, and when the limit member 50 is damaged, the limit member 50 can be replaced on the limit support 60. Preferably, the mounting plate portion 54 is bolted to the limit support 60.
[0042] In some embodiments of the present invention, the wheel 30 includes: a wheel fork and a roller, the roller can be rotatably arranged on the wheel fork, and the wheel fork is connected to the piston rod 20. In the process of product design, the size of the wheel fork and the roller can be adjusted to meet more product design needs.
[0043] In some embodiments of the present invention, Figure 1 and Figure 2As shown, the limiting member 50 includes a first section 51 and a second section 52 , and the lower end of the first section 51 is connected to the outer peripheral wall of the rotating drum 411 , that is, one end of the limiting member 50 is connected to the rotating drum 411 , and the limiting portion 11 is provided on the outer drum 10 .
[0044] The upper end of the first section 51 exceeds the upper end of the rotating drum 411, one end of the second section 52 is connected to the upper end of the first section 51, and the other end extends toward the outer drum 10 along the radial direction of the outer drum 10 and cooperates with the limiting portion 11. Therefore, the limiting member 50 will not interfere with the rotation of the rotating drum 411 relative to the outer drum 10, and the structure of the limiting member 50 is relatively simple, which can reduce the difficulty and cost of production. In the process of product design, the size or relative angle of the first section 51 and the second section 52 can be adjusted to meet more product design needs.
[0045] In some embodiments of the present invention, Figure 1-Figure 3 As shown, a limiting boss 521 extending along the circumferential direction of the outer tube 10 is formed at one end of the second section 52 away from the first section 51, and the limiting boss 521 cooperates with the limiting portion 11. It can be understood that the weight of the aircraft is relatively large, and when the limiting member 50 and the limiting portion 11 cooperate in limiting, the limiting member 50 is subjected to a relatively large force. By providing the limiting boss 521, the size of the limiting boss 521 in the circumferential direction of the outer tube 10 is relatively large, so that the strength of the limiting boss 521 is also relatively high, thereby improving the reliability of the limiting cooperation between the limiting member 50 and the limiting portion 11.
[0046] In some embodiments of the present invention, Figure 3 As shown, the surface of the limiting boss 521 facing the outer cylinder 10 is a cylindrical arc surface. As a result, the distance between the two ends of the limiting boss 521 and the outer cylinder 10 can be shortened, so as to facilitate the limiting cooperation between the limiting boss 521 and the limiting portion 11, wherein, preferably, the axis of the cylindrical arc surface coincides with the axis of the outer cylinder 10, so that the distance between the limiting boss 521 and the outer cylinder 10 can be evenly distributed, and during the rotation of the limiting boss 521 relative to the outer cylinder 10, the distance between the limiting boss 521 and the outer cylinder 10 will not change, thereby reducing the difficulty of product design.
[0047] In some embodiments of the present invention, Figure 2 and Figure 3 As shown, a material reduction groove 53 is formed on the side of the stopper 50 away from the rotating drum 411. By providing the material reduction groove 53, the weight of the stopper 50 can be reduced on the premise that the strength of the stopper 50 meets the use requirements. On the one hand, the torque of the stopper 50 on the rotating drum 411 can be reduced, thereby improving the reliability and stability of the rotating drum 411 during the rotation process on the outer drum 10, and on the other hand, the production cost can be reduced.
[0048] In some embodiments of the present invention, Figure 1 and Figure 2 As shown, the limiting part 11 includes: a first limiting protrusion 111 and a second limiting protrusion 112, the first limiting protrusion 111 and the second limiting protrusion 112 are arranged at intervals in the circumferential direction of the outer cylinder 10, the rotating cylinder 411 is in the first position, the limiting member 50 abuts against the first limiting protrusion 111, and the rotating cylinder 411 is in the second position, and the limiting member 50 abuts against the second limiting protrusion 112. Thus, the limiting member 50 can cooperate with the limiting part 11 to make the rotating cylinder 411 rotate between the first position and the second position relative to the outer cylinder 10, and the structure of the limiting part 11 is relatively simple, and the difficulty is relatively low in the production and product design process. In the process of product design, the size, position or spacing of the first limiting protrusion 111 and the second limiting protrusion 112 can be adjusted to meet more product design needs.
[0049] In some embodiments of the present invention, Figure 1 and Figure 2 As shown, a limiting fold 12 surrounding the outer cylinder 10 is also formed on the outer peripheral wall of the outer cylinder 10, and the limiting fold 12 is arranged between the first limiting protrusion 111 and the second limiting protrusion 112 and the rotating drum 411, and the first limiting protrusion 111 and the second limiting protrusion 112 are connected to the limiting fold 12. By providing the limiting fold 12, the limiting fold 12 can limit the rotating drum 411 in the axial direction of the outer cylinder 10, thereby improving the reliability of the rotation connection between the rotating drum 411 and the outer cylinder 10, and reducing the difficulty of assembling the rotating drum 411 on the outer cylinder 10, and by connecting the first limiting protrusion 111 and the second limiting protrusion 112 with the limiting fold 12, the structural strength of the first limiting protrusion 111 and the second limiting protrusion 112 can be improved, thereby further improving the reliability of the landing gear 100 during operation.
[0050] In some embodiments of the present invention, Figure 1 As shown, the torque arm assembly 40 includes: a first torque arm 41 and a second torque arm 42, the first torque arm 41 and the second torque arm 42 are rotatably connected, the rotating cylinder 411 is formed on the first torque arm 41, and the second torque arm 42 is connected to the piston rod 20. In this way, in the process of the piston rod 20 moving up and down relative to the outer cylinder 10, the first torque arm 41 and the second torque arm 42 rotate synchronously relative to each other, so that the piston rod 20 can cooperate with the outer cylinder 10 normally to achieve vibration reduction of the aircraft. In the process of product design, the parameters such as the size or initial relative angle of the first torque arm 41 and the second torque arm 42 can be adjusted to meet more product design needs.
[0051] The aircraft according to the second embodiment of the utility model comprises: the landing gear 100 according to the first embodiment of the utility model and a steering actuator, wherein the steering actuator is connected to the rotating drum 411 .
[0052] Among them, the steering actuator can drive the rotating cylinder 411 to rotate relative to the outer cylinder 10 according to the instructions of the direction control component on the aircraft. The rotating cylinder 411 drives the piston rod 20 to rotate through the torque arm assembly 40, thereby rotating the wheel 30 connected to the piston rod 20, thereby realizing the turning of the aircraft.
[0053] According to the aircraft of the second embodiment of the utility model, by providing the landing gear 100 according to the first aspect of the utility model, the reliability of the aircraft during operation can be improved.
[0054] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.
[0055] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present utility model, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.
[0056] In the present invention, unless otherwise clearly specified and limited, the terms "install", "connect", "connect", "fix" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, or a communication; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.
[0057] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the utility model. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.
[0058] Although the embodiments of the present invention have been shown and described, those skilled in the art will appreciate that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the claims and their equivalents.
Claims
1. A landing gear, characterized in that: include: An outer cylinder, the upper end of which is suitable for being connected to the fuselage of the aircraft; A piston rod and a wheel, wherein the upper end of the piston rod is movably disposed in the outer tube and the lower end thereof extends out of the outer tube, and the wheel is connected to the lower end of the piston rod; A torque arm assembly, wherein the upper end of the torque arm assembly is provided with a rotating cylinder, the rotating cylinder is rotatably sleeved on the outer cylinder, and the lower end of the torque arm assembly is connected to the piston rod; A limiting member, one end of which is connected to one of the rotating cylinder and the outer cylinder, the other of the rotating cylinder and the outer cylinder is provided with a limiting portion, and the other end of the limiting member is configured to cooperate with the limiting portion to enable the rotating cylinder to rotate relative to the outer cylinder between a first position and a second position.
2. The landing gear according to claim 1, characterized in that: Also includes: A limit support, wherein the limit support is arranged on the outer peripheral wall of one of the rotating drum and the outer drum, the limit support forms a support surface, and the limit member is provided with a mounting plate portion, the mounting plate portion is arranged on the support surface and is detachably connected to the limit support.
3. The landing gear according to claim 1, characterized in that: The limiting member includes a first section and a second section, the lower end of the first section is connected to the outer peripheral wall of the rotating drum, the upper end of the first section exceeds the upper end of the rotating drum, one end of the second section is connected to the upper end of the first section, and the other end extends toward the outer cylinder along the radial direction of the outer cylinder and cooperates with the limiting portion.
4. The landing gear according to claim 3, characterized in that: A limiting boss extending along the circumferential direction of the outer cylinder is formed at one end of the second section away from the first section, and the limiting boss cooperates with the limiting portion.
5. The landing gear according to claim 4, characterized in that: A surface of the limiting boss facing the outer cylinder is a cylindrical arc surface.
6. The landing gear according to claim 4, characterized in that: A material reduction groove is formed on a side of the limiting member away from the rotating drum.
7. The landing gear according to any one of claims 3 to 6, characterized in that: The limiting portion includes: a first limiting protrusion and a second limiting protrusion, wherein the first limiting protrusion and the second limiting protrusion are arranged at intervals in the circumferential direction of the outer cylinder, and when the rotating cylinder is in the first position, the limiting member abuts against the first limiting protrusion, and when the rotating cylinder is in the second position, the limiting member abuts against the second limiting protrusion.
8. The landing gear according to claim 7, characterized in that: A limiting fold surrounding the outer cylinder is also formed on the outer peripheral wall of the outer cylinder, and the limiting fold is arranged between the first limiting protrusion, the second limiting protrusion and the rotating cylinder, and the first limiting protrusion and the second limiting protrusion are connected to the limiting fold.
9. The landing gear according to claim 1, characterized in that: The torque arm assembly includes: a first torque arm and a second torque arm, the first torque arm is rotatably connected to the second torque arm, the rotating cylinder is formed on the first torque arm, and the second torque arm is connected to the piston rod.
10. An aircraft, characterized in that: include: The landing gear according to any one of claims 1 to 9; A steering actuator is connected to the rotating drum.