Truss structure of aircraft and aircraft comprising truss structure

Abstract

The utility model relates to a truss structure of an aircraft and the aircraft comprising the truss structure. Specifically, the truss structure of the aircraft comprises a nose structure, a fuselage structure and a tail structure which are connected in sequence, the fuselage structure comprises a first supporting frame and a second supporting frame, the first supporting frame is connected with the nose structure, the second supporting frame is connected with the tail structure, and the first supporting frame is connected with the nose structure. The machine head structure, the machine body structure and the machine tail structure are all formed by splicing rod pieces and connecting pieces, the connecting pieces are provided with inserting barrels, and the rod pieces can be inserted into the inserting barrels so as to be spliced with the connecting pieces. The utility model further provides an aircraft.

Description

Technical Field

[0001] The present application belongs to the field of aircraft, and in particular to a truss structure of an aircraft. Background Art

[0002] The background description provided herein is intended to generally present the context of the disclosure.

[0003] The trusses of aircraft are mainly made of structural materials, which need to have high specific strength and specific stiffness to reduce the structural weight of the aircraft, improve flight performance or increase economic benefits. Early aircraft were mainly made of wood, cloth and steel. With the development of technology, steel pipes began to be used instead of wood as fuselage trusses, and aluminum was used as skin to manufacture all-metal aircraft.

[0004] With the progress and development of science and technology, composite materials, especially carbon fiber composite materials, are used more and more in aircraft. The biggest feature of carbon fiber material is its light texture, outstanding specific strength and specific stiffness in mechanics, corrosion resistance and good thermal stability, making aircraft develop towards lightweight manufacturing.

[0005] However, the production cost of carbon fiber is relatively high, which makes it expensive. The processing of carbon fiber is also difficult, requiring special processing equipment and processes. The process of making molds for producing parts of specific shapes with carbon fiber is cumbersome and expensive, which greatly limits the shape design of parts.

[0006] Therefore, it is desirable to provide a new aircraft truss. Utility Model Content

[0007] 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.

[0008] According to a first aspect of the present application, there is provided a truss structure of an aircraft, characterized in that the truss structure comprises a nose structure, a fuselage structure and a tail structure connected in sequence, wherein the fuselage structure comprises a first support frame and a second support frame, the first support frame is connected to the nose structure, and the second support frame is connected to the tail structure, and wherein the nose structure, the fuselage structure and the tail structure are all formed by splicing rods and connecting members, wherein the connecting member is provided with an insert sleeve, and the rod can be inserted into the insert sleeve to be spliced ​​with the connecting member.

[0009] Preferably, the first support frame includes a first connecting member and a second connecting member, the first connecting member includes a first top beam and a first bottom beam, the first top beam and the first bottom beam are connected through a first supporting member, and the second connecting member is respectively connected to the first top beam and the first bottom beam through a rod, thereby forming a triangular structure with the first supporting member as one side with the first connecting member.

[0010] Preferably, the second support frame includes a third connecting member and a fourth connecting member, the third connecting member includes a second top beam and a second bottom beam, the second top beam and the second bottom beam are connected through the second support member, and the fourth connecting member is respectively connected to the second top beam and the second bottom beam through a rod, thereby forming a triangular structure with the third connecting member with the second support member as one side.

[0011] Preferably, the first support member and the second support member are respectively provided with a first rib plate and a second rib plate, wherein the first rib plate and the second rib plate are provided with a hollow structure.

[0012] Preferably, the nose structure includes a fifth connecting member, and the fifth connecting member is respectively connected to the first connecting member and the second connecting member through a rod, so as to form a conical structure with the fifth connecting member as the vertex.

[0013] Preferably, the tail structure comprises a first tail structure connected to the second top beam, and a second tail structure connected to the second bottom beam, wherein both the first tail structure and the second tail structure are composed of rods arranged at an angle.

[0014] Preferably, the first bottom beam is provided with a front landing gear, and the second bottom beam is provided with a rear landing gear.

[0015] Preferably, the bottoms of the front landing gear and the rear landing gear are both provided with concave curved surfaces.

[0016] Preferably, the first bottom beam is provided with a third rib, wherein the third rib is hollowed out.

[0017] Preferably, the first connecting member, the second connecting member, the third connecting member, the fourth connecting member and the fifth connecting member are all provided with curved surfaces so as to fit with the aircraft shell.

[0018] Preferably, the second bottom beam is formed by a truss.

[0019] Preferably, the second top beam is provided with a plurality of lug plates, wherein the lug plates are provided with holes or hooks.

[0020] Preferably, at least one of the first connecting member, the second connecting member and the third connecting member is provided with an insertion hole and / or a slot so as to insert the reinforcing rod and / or the reinforcing plate therein.

[0021] Preferably, at least one of the first connecting member, the second connecting member, the third connecting member and the fourth connecting member is provided with a skin mounting hole so as to mount the aircraft skin to the truss structure.

[0022] Preferably, the second connecting member and the second top beam are provided with wing mounting holes so as to mount the wing to the truss structure.

[0023] Preferably, an adhesive is further provided between the rod and the insert tube, so as to bond the rod and the insert tube.

[0024] Preferably, the rod is a carbon fiber tube.

[0025] In another aspect of the present application, an aircraft is also provided, which includes a truss structure according to the principle of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] 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:

[0027] Figure 1 , Figure 2 and Figure 3 The truss structure of an aircraft according to the principles of the present application is schematically shown in different viewing angles;

[0028] Figure 4 A first connector according to the principles of the present application is schematically shown;

[0029] Figure 5 Schematically illustrates a second connector according to the principles of the present application;

[0030] Figure 6 Schematically illustrates a third connector according to the principles of the present application;

[0031] Figure 7 schematically illustrates a fourth connector according to the principles of the present application; and

[0032] Figure 8 A fifth connector according to the principles of the present application is schematically shown.

[0033] 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

[0034] 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.

[0035] 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 (multiple) aspects. In particular, any feature indicated as being preferred or advantageous may be combined with any other (multiple) features indicated as being preferred or advantageous.

[0036] In view of the problems in the prior art, the present application provides a new truss structure for an aircraft. Figure 1 , shows a truss structure 10 of an aircraft according to the principles of the present application. The truss structure 10 includes a nose structure 100, a fuselage structure 200 and a tail structure 300 connected in sequence. The nose structure 100, the fuselage structure 200 and the tail structure 300 are all spliced ​​by rods 11 and connecting members. The connecting members can be provided with inserts such as inserts 12 to receive the rods 11 inserted therein so as to achieve splicing of the rods 11 and the connecting members. The rods 11 can be carbon fiber rods or metal rods. In a preferred embodiment, the rods 11 are carbon fiber rods, so that the truss structure 10 has sufficient strength and light weight.

[0037] Refer to the attached Figure 1 and attached Figure 2 The fuselage structure 200 includes a first support frame 210 and a second support frame 220, wherein the first support frame 210 is connected to the nose structure 100, and the second support frame 220 is connected to the tail structure 300. Figure 1 , Attachment Figure 4 and attached Figure 5 The first supporting structure 210 includes a first connecting member 211 and a second connecting member 212, wherein the first connecting member 211 includes a first top beam 213, a first bottom beam 214 and a first supporting member 215, and the first top beam 213 and the first bottom beam 214 are connected by the first supporting member 215. It should be understood that the number of first supporting members 215 can be 1, or 2 or more. In one embodiment, the number of first supporting members is 1, which connects the middle parts of the first top beam 213 and the first bottom beam 214 respectively. In another embodiment, the number of first supporting members is 2, as shown in the attached figure. Figure 4 As shown, they are respectively connected to the two ends of the first top beam 213 and the first bottom beam 214. It should be understood that the number of the first support members 215 can be more than two according to the force requirements of the truss structure 10, and this application does not limit this.

[0038] Refer to the attached Figure 1 , Attachment Figure 2 and attached Figure 3The second connecting member 212 is connected to the first top beam 213 and the first bottom beam 214 respectively through the rod 11, thereby forming a triangular structure with the first connecting member 211 and the first supporting member 215 of the first connecting member 211 as one side, so as to enhance the force performance of the first supporting frame 210. Figure 1 , Attachment Figure 3 and attached Figure 5 , multiple inserts 12 may be provided at both ends of the second connecting member 212, so that the two ends thereof are respectively connected to the two ends of the first top beam 213 and the two ends of the first bottom beam 214 through the rod 11, thereby forming a quadrilateral structure with the second connecting member 212 and the first top beam 213 as two opposite sides, and a quadrilateral structure with the second connecting member 212 and the first bottom beam 214 as two opposite sides, such as a trapezoidal structure. On this basis, it should be understood that one or more inserts 12 may also be provided at the middle portion of the second connecting member 212, so that the middle portion thereof is respectively connected to the middle portion of the first top beam 213 and the middle portion of the first bottom beam 214 through one or more rods 11, so as to further enhance the mechanical properties of the first support frame 210.

[0039] Refer to the attached Figure 1 , Attachment Figure 2 and attached Figure 6 The second support frame 220 includes a third connecting member 221 and a fourth connecting member 222, wherein the third connecting member 221 includes a second top beam 223, a second bottom beam 224, and a second supporting member 225, and the second top beam 223 and the second bottom beam 224 are connected by the second supporting member 225. It should be understood that the number of the second supporting members 225 can be 1 or more than 2. In one embodiment, the number of the second supporting members is 1, which is respectively connected to the middle parts of the second top beam 223 and the second bottom beam 224. In one embodiment, the number of the second supporting members is 2, as shown in the attached figure. Figure 6 As shown, they are respectively connected to the two ends of the second top beam 223 and the second bottom beam 224. It should be understood that the number of the second support members 225 can be more than two according to the force requirements of the truss structure 10, and this application does not limit this.

[0040] Refer to the attached Figure 1 , Attachment Figure 2 , Attachment Figure 3 and attached Figure 7 The fourth connecting member 222 is provided with a plurality of inserting tubes 12, the number of which may be two, which are respectively connected to the first top beam 213 and the second top beam 223 through the rod 11, and connected to the second bottom beam 224 through the rod 11, so as to form a triangular structure with the third connecting member 221 and the second supporting member 225 of the third connecting member 221 as one side, so as to enhance the force performance of the second supporting frame 220. In one embodiment, as shown in the attached Figure 3As shown, each fourth connecting member 222 is connected to the second top beam 223 through two or more rods 11, and each rod 11 connected to the second top beam 223 can be arranged at an angle, thereby further strengthening the connection strength between the fourth connecting member 222 and the second top beam 223. In one embodiment, each fourth connecting member 222 is connected to the second bottom beam 224 through two or more rods 11, and each rod 11 connected to the second bottom beam 224 can be arranged at an angle, thereby further strengthening the connection strength between the fourth connecting member 222 and the second bottom beam 224. It should be understood that according to the force requirements of the truss structure 10, the number of the fourth connecting members 222 can be more than two, and the fourth connecting members 222 can also be connected through the rods 11.

[0041] Refer to the attached Figure 1 , Attachment Figure 4 and attached Figure 6 , the first support member 215 may be provided with a first rib plate 216, and the second support member 225 may be provided with a second rib plate 226, so as to further strengthen the strength of the first support member 215 and the second support member 225. Advantageously, the first rib plate 216 and the second rib plate 226 may both be provided with hollowing, so as to reduce the overall weight of the truss structure 10. Advantageously, since the first bottom beam 214 bears a large load, the first bottom beam 214 may be provided with a third rib plate 218, and the third rib plate 218 is arranged at an angle with the main body of the first bottom beam 214, so as to strengthen the strength of the first bottom beam 214, so that it can bear a larger load. Advantageously, the third rib plate 218 may be connected to the first rib plate 216, so as to enhance the overall strength of the first connecting member 211. Advantageously, the third rib plate 218 may be provided with hollowing, so as to reduce the overall weight of the truss structure 10.

[0042] Refer to the attached Figure 1 and attached Figure 2 The tail structure 300 includes a first tail structure 310 and a second tail structure 320, wherein the first tail structure 310 is connected to the second top beam 223, and the second tail structure 320 is connected to the second bottom beam 224. The first tail structure 310 and the second tail structure 320 are both composed of rods 11 arranged at an angle. The rods constituting the first tail structure 310 may be connected to each other or not at their ends, and the rods constituting the second tail structure 320 may also be connected to each other or not at their respective ends. The first tail structure 310 and the second tail structure 320 may be close to each other at their ends so that the two are arranged at an angle so as to conform to the outer contour of the tail.

[0043] Refer to the attached Figure 1 and attached Figure 8The nose structure 100 includes a fifth connecting member 110, which is connected to the first connecting member 211 and the second connecting member 212 through the rod 11, thereby forming a conical structure with the fifth connecting member 110 as the vertex, so as to enhance the strength of the nose structure 100 and conform to the outer contour of the nose. The fifth connecting member 110 can be connected to the two ends of the first bottom beam 214 of the first connecting member 211 and / or the middle part of the first bottom beam 214 through the rod 11; similarly, the fifth connecting member 110 can also be connected to the two ends of the second connecting member 212 and / or the middle part of the second connecting member 212 through the rod 11.

[0044] Refer to the attached Figure 4 and attached Figure 6 , the first bottom beam 214 may be provided with a front landing gear 217, and the second bottom beam 224 may be provided with a rear landing gear 227. In one embodiment, the number of the front landing gear 217 is one, and is provided in the middle of the first bottom beam 214, and the number of the rear landing gear 227 may be two, and are provided at both ends of the second bottom beam 224. In another embodiment, the number of the front landing gear 217 may be two, and are provided at both ends of the first bottom beam 214, and the number of the rear landing gear 227 may be one, and is provided in the middle of the second bottom beam 224. When the first bottom beam 214 is provided with a third rib 218, the main body of the first bottom beam 214 and the third rib 218 may be connected to the front landing gear 217, thereby enhancing the stability and force performance of the front landing gear 217. Advantageously, the bottoms of the front landing gear 217 and the rear landing gear 227 may be provided with concave surfaces for mounting shock-absorbing pads. Advantageously, the front landing gear 217 and / or the rear landing gear 227 may be provided with hollowing to reduce the overall weight of the truss structure 10 .

[0045] Refer to the attached Figure 4 , Attachment Figure 5 , Attachment Figure 6 and attached Figure 7 The first connector 211, the second connector 212, and the third connector 221 may be provided with a socket 13 so that a reinforcing rod may be inserted therein, thereby strengthening the strength of the connector. The reinforcing rod may be a carbon fiber rod or a metal rod. Additionally or alternatively, the connector may be provided with a slot (not shown) into which a reinforcing plate may be inserted to strengthen the strength of the connector. The reinforcing plate may be a metal plate or a carbon fiber plate. The first connector 211, the second connector 212, the third connector 221, and the fourth connector 222 may be provided with a shell mounting hole 14 so that the aircraft shell or skin may be mounted to the truss structure 10 by screwing or clamping. Refer to the attached Figure 5 and attached Figure 6 The second connecting member 212 and the second top beam 223 may be provided with wing mounting holes 15 so that the wing can be mounted on the truss structure 10 by screwing or clamping.

[0046] See attached Figure 8 The fifth connecting member 110 is provided with a curved surface 111 so as to fit with the outer shell of the aircraft. Similarly, the first connecting member 211, the second connecting member 212, the third connecting member 221, and the fourth connecting member 222 may also be provided with curved surfaces so as to fit with the outer shell of the aircraft.

[0047] See attached Figure 6 The second bottom beam 224 may be formed by a truss, so as to further enhance the strength of the second bottom beam 224 and reduce the overall weight of the truss structure 10. Advantageously, the second top beam 223, the first bottom beam 214, and the first top beam 213 may also be formed by a truss.

[0048] See attached Figure 3 and attached Figure 6 , a plurality of lugs 228 may be provided on the second top beam 223, and holes or hooks may be provided on the lugs 228 for hanging cargo, installing aircraft accessories, etc. In one embodiment, one lug 228 is provided at each end of the second top beam 223. In one embodiment, the lugs 228 may be provided with slots 229, into which reinforcing plates may be inserted, and the reinforcing plates may be metal plates or carbon fiber plates, so as to strengthen the strength of the lugs 228. The reinforcing plates may be provided with holes that can be aligned with the holes on the lugs 228, so as to hang cargo, install aircraft accessories, etc.

[0049] Advantageously, an adhesive, such as epoxy resin or 502 glue, may be provided between the rod 11 and the insert 12 to strengthen the connection strength between the rod 11 and the insert 12. Those skilled in the art will readily appreciate that the rod 11 according to the present application may be a rod of other materials, such as a metal rod, in addition to a carbon fiber tube.

[0050] Advantageously, the connectors according to the principles of the present application can be made by 3D printing, thereby simplifying the process and saving costs. In addition, the printing material is a plastic material mixed with carbon fiber and glass fiber to enhance the overall strength of the connector.

[0051] The present application also provides an aircraft, which includes a truss structure 10 based on the principles of the present application, wherein the aircraft can be a manned aircraft, or an unmanned aircraft or a drone.

[0052] The truss according to the principle of the present application can be made into a truss of corresponding shape according to the shape of the aircraft by splicing the connecting pieces and the rods, which simplifies the processing technology and ensures the structural strength of the truss. In addition, the present application uses carbon fiber rods to make the truss, and there is no need to further process the carbon fiber material, so that the characteristics of carbon fiber, such as light texture, excellent mechanical properties and good corrosion resistance, can be brought into play.

[0053] 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 truss structure of an aircraft, characterized in that: The truss structure includes a nose structure, a fuselage structure and a tail structure connected in sequence, wherein the fuselage structure includes a first support frame and a second support frame, the first support frame is connected to the nose structure, and the second support frame is connected to the tail structure, and wherein the nose structure, the fuselage structure and the tail structure are all spliced ​​by rods and connecting members, wherein the connecting member is provided with an insert, and the rod can be inserted into the insert to be spliced ​​with the connecting member, wherein the first support frame includes a first connecting member and a second connecting member, the first connecting member includes a first top beam and a first bottom beam, the first top beam is connected to the first bottom beam through a first support member, and the second connecting member is respectively connected to the first top beam and the first bottom beam through rods to form a triangular structure with the first support member as one side with the first connecting member.

2. The truss structure according to claim 1, characterized in that: The second support frame includes a third connecting member and a fourth connecting member, the third connecting member includes a second top beam and a second bottom beam, the second top beam and the second bottom beam are connected through a second support member, and the fourth connecting member is respectively connected to the second top beam and the second bottom beam through a rod, thereby forming a triangular structure with the third connecting member with the second support member as one side.

3. The truss structure according to claim 2, characterized in that: The first support member and the second support member are respectively provided with a first rib plate and a second rib plate, wherein the first rib plate and the second rib plate are provided with a hollow structure.

4. The truss structure according to claim 3, characterized in that: The nose structure includes a fifth connecting member, and the fifth connecting member is respectively connected to the first connecting member and the second connecting member through a rod, so as to form a conical structure with the fifth connecting member as the vertex.

5. The truss structure according to claim 4, characterized in that: The tail structure comprises a first tail structure connected to the second top beam, and a second tail structure connected to the second bottom beam, wherein both the first tail structure and the second tail structure are composed of rods arranged at an angle.

6. The truss structure according to claim 5, characterized in that: The first bottom beam is provided with a front landing gear, and the second bottom beam is provided with a rear landing gear.

7. The truss structure according to claim 6, characterized in that: The bottoms of the front landing gear and the rear landing gear are both provided with concave surfaces.

8. The truss structure according to claim 7, characterized in that: The first bottom beam is provided with a third rib plate, wherein the third rib plate is hollowed out.

9. The truss structure according to claim 8, characterized in that: The first connecting member, the second connecting member, the third connecting member, the fourth connecting member and the fifth connecting member are all provided with curved surfaces so as to fit with the aircraft shell.

10. The truss structure according to claim 9, characterized in that: The second bottom beam is composed of a truss.

11. The truss structure according to claim 10, characterized in that: The second top beam is provided with a plurality of lug plates, wherein the lug plates are provided with holes or hooks.

12. The truss structure according to claim 11, characterized in that: At least one of the first connecting member, the second connecting member and the third connecting member is provided with an insertion hole and / or a slot so as to insert the reinforcing rod and / or the reinforcing plate therein.

13. The truss structure according to claim 12, characterized in that: At least one of the first connecting member, the second connecting member, the third connecting member and the fourth connecting member is provided with a shell mounting hole so as to mount the aircraft shell to the truss structure.

14. The truss structure according to claim 13, characterized in that: The second connecting member and the second top beam are provided with wing mounting holes so as to mount the wing to the truss structure.

15. The truss structure according to claim 14, characterized in that: An adhesive is also provided between the rod and the insert tube, so as to bond the rod to the insert tube.

16. The truss structure according to any one of claims 1 to 15, characterized in that: The rod is a carbon fiber tube.

17. An aircraft, characterized in that: The aircraft comprises a truss structure according to any one of claims 1-16.

Images