Damping airbag and rotor aircraft comprising same
By designing a shock absorbing airbag of multi-cavity unit, the problem of poor impact cushioning force when landing is solved, achieving higher shock absorption effect and structural safety.
Patent Information
- Application Number
- CN202420778320.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-04-15
- Publication Date
- 2025-03-21
- Estimated Expiration
- 2034-04-15
AI Technical Summary
Existing rotorcrafts are difficult to effectively buffer impact forces when landing, resulting in structural wear and damage, and the existing shock absorbing airbags are complex in structure and are not easy to maintain.
A shock absorbing airbag including multiple cavity units is designed, with a polygonal cross-section, the airbag made of flexible material and formed integrally by 3D printing, and the airbag can be installed on the bottom of the landing gear of the rotorcraft.
When the shock absorbing airbag is subjected to external force, the cavity unit and the gas will undergo elastic deformation, which can withstand greater force, and when some cavity units are damaged, the rest can still play a role, improving the landing safety and shock absorption effect of the rotorcraft.
Smart Images
Figure CN222646260U_ABST
Abstract
Description
Technical Field
[0001] The present application belongs to the field of shock absorbing devices, and in particular, relates to a shock absorber and a rotorcraft including the shock absorber. Background Art
[0002] The background description provided herein is intended to generally present the context of the disclosure.
[0003] Shock-absorbing devices are widely used in a variety of production and living tools such as aircraft, shoes, vehicles, digital products, and furniture. Among them, in the field of aircraft, how to safely perform landing and reduce the impact of landing is the key to ensuring the safety of aircraft structure and load. At present, in the field of rotorcraft, multi-rotor and composite wing vertical lift aircraft mostly use hard landing methods, including landing with landing gear or landing with fuselage. Among them, the landing gear is mostly made of carbon plate, fiberglass plate or aluminum plate, but the carbon plate, fiberglass plate and aluminum plate are affected by the stiffness of the material itself, and the buffering effect of the landing impact force is not obvious, and the belly landing method is easy to cause wear and damage to the fuselage structure. In other fields, shock-absorbing airbags and spring shock absorbers are mostly used for shock absorption. The existing shock-absorbing airbags have only one cavity inside, and they can no longer be used when the airbag is damaged and leaks, and the spring shock absorber has a complex structure and is not easy to maintain and repair.
[0004] Therefore, a new shock absorbing device is desired. Utility Model Content
[0005] This section introduces the concepts of the present application in a simplified form, which are further reflected in the detailed description below. This section is not intended to identify key features or essential features of the claimed subject matter, nor is it intended to be used as an aid in determining the scope of the claimed subject matter.
[0006] According to one aspect of the present application, a shock-absorbing airbag is provided, wherein the shock-absorbing airbag comprises a closed capsule body, wherein the closed capsule body has a plurality of cavity units inside.
[0007] In some preferred embodiments, the cavity unit has a polygonal cross-section, wherein the polygonal cross-section is any one of a hexagon, a pentagon, a quadrilateral or a triangle.
[0008] In some preferred embodiments, the shock-absorbing airbag further includes a columnar protrusion connected to the closed bag body.
[0009] In some preferred embodiments, the closed capsule is streamlined and has a first curved surface and a second curved surface, and the first curved surface and the second curved surface are arranged opposite to each other.
[0010] In some preferred embodiments, the surface area of the first curved surface is greater than the surface area of the second curved surface, and the columnar protrusion is connected to the first curved surface.
[0011] In some preferred embodiments, the columnar protrusions are cylindrical protrusions.
[0012] In some preferred embodiments, the columnar protrusion is perpendicular to the length direction of the cavity unit.
[0013] In some preferred embodiments, the shock-absorbing airbag is made of a flexible material.
[0014] In some preferred embodiments, the flexible material is rubber or TPU.
[0015] In some preferred embodiments, the shock-absorbing airbag is integrally formed by 3D printing.
[0016] According to another aspect of the present application, a rotorcraft is provided, comprising a fuselage and a landing gear connected to the fuselage, wherein the aforementioned shock-absorbing airbag is provided at the bottom of the landing gear. BRIEF DESCRIPTION OF THE DRAWINGS
[0017] Other or additional features, advantages and details are presented by way of example only in the following detailed description of the embodiments. In the drawings:
[0018] Figure 1 A shock-absorbing airbag according to the principles of the present application is schematically shown;
[0019] Figure 2 The shock-absorbing airbag according to the principle of the present application is schematically shown from another perspective;
[0020] Figure 3 The internal structure of the shock-absorbing airbag according to the principle of the present application is schematically shown;
[0021] Figure 4 Schematically shows the internal structure of the shock-absorbing airbag according to the principle of the present application from another perspective;
[0022] Figure 5 A rotorcraft according to the principles of the present application is schematically shown;
[0023] Figure 6 schematically illustrates a partial view of a rotorcraft according to the principles of the present application; and
[0024] Figure 7 A partial view of a rotorcraft according to the principles of the present application is schematically shown from another perspective.
[0025] It should be understood that throughout the drawings, corresponding reference numerals identify similar or corresponding components or features. It should also be understood that the drawings are not necessarily drawn to scale and are merely schematic illustrations of exemplary embodiments of the present application and are not intended to limit the present application. DETAILED DESCRIPTION
[0026] The exemplary embodiments of the present application are described below in conjunction with the accompanying drawings. It should be understood that the following description is only exemplary in nature and is not intended to limit the present application, application or use.
[0027] The present application will now be further described. In the following paragraphs, different aspects of the present application are defined in more detail. Unless clearly indicated to the contrary, each aspect so defined may be combined with any other aspect(s). In particular, any feature indicated as being preferred or advantageous may be combined with any other feature(s) indicated as being preferred or advantageous.
[0028] See attached Figure 1 and attached Figure 2 , shows a shock-absorbing airbag 100 according to the principle of the present application, which includes a closed capsule 110 and a columnar protrusion 120. The closed capsule 110 contains gas, such as air, so that the closed capsule 110 can be restored to its original state after being compressed to achieve a shock-absorbing effect. The closed capsule 110 is connected to the columnar protrusion 120, so that the shock-absorbing airbag 100 can be installed on a corresponding device that needs shock absorption through the columnar protrusion 120. Alternatively, the shock-absorbing airbag 100 may not be provided with the columnar protrusion 120, so that the shock-absorbing airbag 100 can be installed on the corresponding device by bonding.
[0029] See attached Figure 3 and attached Figure 4 The closed capsule 110 has a plurality of cavity units 111 inside, and the cavity units 111 are adjacent to each other and are all closed cavities, and each cavity unit has gas inside. This structure enables the closed capsule 110 to produce elastic deformation when subjected to external force, so that it can withstand greater force. At the same time, when some of the cavity units 111 are damaged, the remaining cavity units 111 can still function, so that the shock-absorbing airbag 100 will not fail completely.
[0030] The cavity unit 111 preferably has a hexagonal cross-section, that is, each cavity unit is in the shape of a hexagonal prism or a substantially hexagonal prism, so that the interior of the shock-absorbing airbag 100 is honeycomb-shaped. This structure fully utilizes the internal space of the shock-absorbing airbag 100 while having sufficient stability and strength, thereby ensuring that the shock-absorbing airbag 100 has sufficient elasticity. Alternatively, the cavity unit 111 may also have a cross-section in any of the shapes of a pentagon, rectangle, triangle, circle or other polygons. It is easy for those skilled in the art to understand that, due to the limitation of the shape of the closed capsule 110, an edge cavity unit 112 will be formed at the junction of the cavity unit 111 and the closed capsule 110. The edge cavity unit 112 is an incomplete cavity unit 111, which also has a shock-absorbing effect.
[0031] See attached Figure 1 and attached Figure 2 The closed capsule 110 is streamlined, and has a first curved surface 113 and a second curved surface 114 arranged opposite to the first curved surface. This allows the streamlined closed capsule 110 to reduce air resistance when the shock-absorbing airbag 100 is installed on the landing gear of the rotorcraft, thereby improving flight efficiency. Alternatively, the closed capsule 110 can also be a rectangular parallelepiped or other shapes. Advantageously, the columnar protrusion 120 can be a cylindrical protrusion or a prismatic protrusion so that it can be inserted into a corresponding device that needs shock absorption, such as a mounting hole of a rotorcraft, and then the shock-absorbing airbag 100 is installed on the corresponding device. The columnar protrusion 120 is connected to the first curved surface 113, and the surface area of the first curved surface 113 is larger than the surface area of the second curved surface 114. This allows the first curved surface 113 to contact the mounting surface of the device that needs shock absorption when the shock-absorbing airbag 100 is installed, thereby increasing the contact area and improving the installation stability. Alternatively, in an embodiment where the columnar protrusion 120 is not provided, the first curved surface 113 can be used as a bonding surface to be bonded to a device requiring shock absorption, thereby increasing the bonding area.
[0032] The columnar protrusion 120, the closed capsule 110 and the cavity unit are all made of flexible materials, such as rubber or TPU (thermoplastic polyurethane rubber). Alternatively, the columnar protrusion 120 can also be made of a rigid material. The number of columnar protrusions 120 can be one, or two or more. When the number of columnar protrusions 120 is one, it is preferably a prismatic protrusion, which makes it difficult to rotate in the corresponding mounting hole, thereby enhancing the installation stability.
[0033] See attached Figure 3 and attached Figure 4Since the shock-absorbing airbag 100 is usually subjected to external force along the direction of the columnar protrusion 120, the columnar protrusion 120 is arranged substantially perpendicular to the length direction of the cavity unit 111, which enables the external force to act in the direction along the cross-section of the cavity unit 111, giving full play to the stability of the hexagon or other shapes.
[0034] See attached Figure 5 , Attachment Figure 6 and attached Figure 7 , showing a rotorcraft 200 provided with a shock-absorbing airbag of the present application. The rotorcraft 200 includes a fuselage 210 and a landing gear 220 connected to the fuselage 210, wherein the bottom of the landing gear 220 is provided with a shock-absorbing airbag 100 according to the principle of the present application. The bottom of the landing gear 220 is provided with a mounting surface (not shown) that can match the shape of the shock-absorbing airbag 100, and the mounting surface is provided with a mounting hole (not shown) so that the columnar protrusion 120 of the shock-absorbing airbag 100 can be inserted. Advantageously, an adhesive such as glue can be applied between the first curved surface 113 and the mounting surface to make the connection between the shock-absorbing airbag 100 and the landing gear 220 more stable. The rotorcraft 200 can be a manned or unmanned aircraft.
[0035] Those skilled in the art will readily appreciate that, depending on the scenario in which the shock-absorbing airbag is used, the number and density of cavities in the airbag, and the wall thickness of the cavities can be designed according to the load amount to provide appropriate cushioning capacity. The shock-absorbing airbag of the present application can be formed in one piece, and in particular, can be formed in one piece by 3D printing.
[0036] The shock-absorbing airbag according to the principle of the present application has a plurality of cavity units inside, so it has good shock-absorbing ability, has a simple structure and is easy to install, and can be applied to multiple scenarios such as rotorcraft, shoes, vehicles, digital products, furniture, etc.
[0037] Although at least one exemplary embodiment is described in the foregoing detailed description, it should be understood that there are a large number of variations. It should also be understood that an exemplary embodiment or multiple exemplary embodiments described herein are merely examples and are not intended to limit the scope, applicability or configuration of the present application in any way. On the contrary, the foregoing detailed description will provide convenient guidance for those skilled in the art to implement an exemplary embodiment or multiple exemplary embodiments. It should be understood that various changes, modifications or changes, etc. can be made to the functions and arrangements of elements without departing from the scope of the present application as set forth in the attached claims and their equivalents.
Claims
1. A shock-absorbing airbag, characterized in that: The shock-absorbing airbag comprises a closed bladder body, wherein the closed bladder body has a plurality of cavity units inside, wherein the cavity units are adjacent to each other and are all closed cavities, and each cavity unit has gas inside.
2. The shock-absorbing airbag according to claim 1, characterized in that: The cavity unit has a polygonal cross section, wherein the polygonal cross section is any one of a hexagon, a pentagon, a quadrilateral or a triangle.
3. The shock-absorbing airbag according to claim 2, characterized in that: The shock-absorbing airbag also includes a columnar protrusion connected to the closed bag body.
4. The shock-absorbing airbag according to claim 3, characterized in that: The closed capsule is streamlined and has a first curved surface and a second curved surface, wherein the first curved surface and the second curved surface are arranged opposite to each other.
5. The shock-absorbing airbag according to claim 4, characterized in that: The surface area of the first curved surface is greater than that of the second curved surface, and the columnar protrusion is connected to the first curved surface.
6. The shock-absorbing airbag according to claim 5, characterized in that: The columnar protrusion is a cylindrical protrusion.
7. The shock-absorbing airbag according to claim 6, characterized in that: The columnar protrusion is perpendicular to the length direction of the cavity unit.
8. The shock-absorbing airbag according to claim 7, characterized in that: The shock-absorbing airbag is made of flexible material.
9. The shock-absorbing airbag according to claim 8, characterized in that: The flexible material is rubber or TPU.
10. The shock-absorbing airbag according to any one of claims 1 to 9, characterized in that: The shock-absorbing airbag is integrally formed by 3D printing.
11. A rotary-wing aircraft, comprising a fuselage and a landing gear connected to the fuselage, characterized in that: A shock-absorbing airbag as claimed in any one of claims 1 to 10 is arranged at the bottom of the landing gear.