Engine force transmission device and aircraft

Abstract

The invention relates to the technical field of aircrafts, in particular to an engine force transmission device and an aircraft. The engine force transmission device comprises a swing assembly and a fuel conveying assembly, the fuel conveying assembly communicates with a fuel storage container of the aircraft and a thrust chamber of an engine, the fuel conveying assembly is used for conveying fuel in the fuel storage container into the thrust chamber of the engine, and the fuel conveying assembly is sleeved with the swing assembly. The swing assembly is provided with a first end and a second end, the first end is fixedly connected with an aircraft body structure of the aircraft, and the second end is fixedly connected with a thrust chamber of the engine through the fuel conveying assembly. According to the engine force transmission device and the aircraft, the structure of the aircraft can be more compact, the use space of the aircraft is reduced, and the overall space utilization efficiency of the aircraft is improved.

Description

Technical Field

[0001] The present disclosure relates to the technical field of aircraft, and in particular to an engine power transmission device and an aircraft. Background Art

[0002] The attitude control of aircraft is mainly achieved through the swing of the engine. When the engine swings, a force transmission component is often required. The force transmission component connects the engine and the aircraft body structure. When the engine swings within a certain angle range, the force transmission component can be used to transmit the thrust generated by the engine in different directions to the aircraft body structure to achieve attitude control of the aircraft such as pitch, yaw or roll.

[0003] However, the engine power transmission components used in the related art are, firstly, not easy to install, which requires a lot of time and manpower in the assembly and maintenance of the aircraft. Secondly, the space utilization rate is not high, which not only increases the weight and volume of the aircraft, but also may reduce the performance and efficiency of the aircraft. Summary of the invention

[0004] The present disclosure is proposed in view of the above problems. The present disclosure provides an engine power transmission device and an aircraft, which have a more compact structure and improve the overall space utilization efficiency of the aircraft.

[0005] According to one aspect of the present disclosure, there is provided an engine force transmission device, comprising a swing assembly and a fuel delivery assembly, wherein the fuel delivery assembly is respectively connected to a fuel storage container of an aircraft and a thrust chamber of an engine, and the fuel delivery assembly is used to deliver fuel in the fuel storage container to the thrust chamber of the engine, the swing assembly is sleeved on the fuel delivery assembly, and the swing assembly has a first end and a second end, wherein the first end is fixedly connected to a body structure of the aircraft, and the second end is fixedly connected to the thrust chamber of the engine through the fuel delivery assembly;

[0006] The swing assembly includes a plurality of first swing parts located at the first end, a plurality of second swing parts located at the second end, and a connecting piece sleeved on the fuel delivery assembly, and each first swing part and each second swing part are movably connected to the connecting piece.

[0007] According to another aspect of the present disclosure, an aircraft is provided, including an airframe structure, an engine, and an engine force transmission device according to an embodiment of the present disclosure, wherein the engine force transmission device is fixedly connected to the airframe structure and a thrust chamber of the engine, respectively.

[0008] In one or more technical solutions provided in the embodiments of the present disclosure, firstly, the fuel delivery assembly is connected to the fuel storage container of the aircraft and the thrust chamber of the engine respectively, and the fuel in the fuel storage container of the aircraft can be smoothly delivered to the thrust chamber of the engine, which ensures that the engine can obtain fuel stably, helps the engine to work continuously and stably, avoids abnormal operation of the engine due to problems such as poor fuel supply, and thus ensures the stability of the power output of the aircraft during flight. Secondly, the swing assembly is sleeved on the fuel delivery assembly, and the swing assembly has a first end and a second end, the first end is fixedly connected to the body structure of the aircraft, and the second end is fixedly connected to the thrust chamber of the engine through the fuel delivery assembly. When the thrust chamber of the engine changes direction to drive the swing assembly to move, it can drive the multiple first swing parts located at the first end and the multiple second swing parts located at the second end to swing under the support of the connecting member, so that the engine can drive the aircraft body to swing flexibly to a certain extent, adapt to various attitude changes, vibrations, etc. of the aircraft during flight, and can effectively buffer the force generated between the body and the engine due to factors such as changes in flight status, and reduce the risk of structural damage that may be caused by rigid connection.

[0009] On this basis, by combining the swing assembly with the fuel delivery assembly, the entire engine force transmission device can not only realize fuel delivery, but also take into account the functions of connecting the engine and the fuselage and providing flexible buffering. This makes the overall structure relatively compact and does not occupy too much internal space of the aircraft. It is conducive to the rational layout and integration of various systems inside the aircraft, thereby improving the overall space utilization efficiency of the aircraft.

[0010] In addition, the swing assembly of the embodiment of the present disclosure includes multiple first swing parts located at the first end, multiple second swing parts located at the second end, and a connecting piece sleeved on the fuel delivery assembly, and each first swing part and each second swing part are movably connected to the connecting piece. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] The above and other purposes, features and advantages of the present disclosure will become more apparent by describing the embodiments of the present disclosure in more detail in conjunction with the accompanying drawings. The accompanying drawings are used to provide a further understanding of the embodiments of the present disclosure and constitute a part of the specification. Together with the embodiments of the present disclosure, they are used to explain the present disclosure and do not constitute a limitation of the present disclosure. In the accompanying drawings, the same reference numerals generally represent the same components or steps.

[0012] Figure 1 is a schematic structural diagram of an engine force transmission device according to an embodiment of the present disclosure;

[0013] Figure 2 is a schematic structural diagram of a swing assembly according to an embodiment of the present disclosure;

[0014] Figure 3is a schematic structural diagram of a fuel delivery assembly according to an embodiment of the present disclosure;

[0015] Figure 4 is a schematic structural diagram of a connecting member according to an embodiment of the present disclosure;

[0016] Figure 5 is a schematic structural diagram of a first swinging portion of an embodiment of the present disclosure;

[0017] Figure 6 It is a schematic structural diagram of the second swing part of an embodiment of the present disclosure.

[0018] Reference numerals:

[0019] 100-swinging assembly, 100a-first end, 100b-second end, 110-first swinging part, 111-first through hole, 120-second swinging part, 121-second through hole, 122-third through hole, 130-connecting piece, 131-annular part, 132-connecting shaft, 132a-first connecting shaft, 132b-second connecting shaft, 200-fuel delivery assembly, 210-fuel delivery pipe, 220-first fixing part, 230-second fixing part, 300-fixing piece. DETAILED DESCRIPTION

[0020] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present disclosure more clearly understood, the present disclosure is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present disclosure and are not used to limit the present disclosure.

[0021] It should be noted that when an element is referred to as being "fixed to" or "disposed on" another element, it can be directly on the other element or indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or indirectly connected to the other element.

[0022] 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 technical features indicated. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of the present disclosure, "multiple" means two or more, unless otherwise clearly and specifically defined. "Several" means one or more, unless otherwise clearly and specifically defined.

[0023] In the description of the present disclosure, it is necessary to understand that the directions or positional relationships indicated by the terms "upper", "lower", "front", "back", "left", "right", etc. are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present disclosure and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as a limitation on the present disclosure.

[0024] In the description of the present disclosure, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" 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 or an electrical connection; 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 disclosure can be understood according to specific circumstances.

[0025] The attitude control of an aircraft is a key technology to ensure that it can fly stably according to the predetermined trajectory during flight, and this process mainly relies on the swing of the engine. When the engine is swinging, the force transmission component plays an indispensable role. It is like a bridge, tightly connecting the engine and the aircraft body structure.

[0026] When the engine swings within a specific angle range, the direction of the thrust it generates will change accordingly. For example, when the aircraft needs to pitch, the engine swings in a specific direction. At this time, the force transmission component needs to transfer the thrust generated by the engine to the fuselage structure, causing the aircraft's head to rise or pitch down, thereby achieving pitch attitude control. Similarly, in terms of yaw control, the engine swings to generate lateral thrust, which is transmitted to the fuselage through the force transmission component, allowing the aircraft to change its course to the left or right. In roll control, the engine's swinging thrust is transmitted through the force transmission component, driving the aircraft to rotate around its own longitudinal axis to achieve roll attitude adjustment.

[0027] However, the engine power transmission components used in the related art are, firstly, not easy to install, which requires a lot of time and manpower in the assembly and maintenance of the aircraft. Secondly, the space utilization rate is not high, which not only increases the weight and volume of the aircraft, but also may reduce the performance and efficiency of the aircraft.

[0028] In view of the above problems, the embodiments of the present disclosure provide an engine force transmission device and an aircraft, which can make the structure of the aircraft more compact, reduce the use space of the aircraft, and improve the overall space utilization efficiency of the aircraft. The aircraft includes an airplane, a rocket or other types of aircraft, which are not limited here.

[0029] Figure 1 The structure diagram of the engine power transmission device according to the embodiment of the present disclosure is shown. Figure 2 The structure diagram of the swing assembly of the embodiment of the present disclosure is shown. Figure 3 FIG. 2 shows a schematic diagram of the structure of the fuel delivery assembly according to an embodiment of the present disclosure. Figures 1 to 3 As shown, the engine force transmission device of the embodiment of the present disclosure includes: a swing assembly 100 and a fuel delivery assembly 200, wherein the fuel delivery assembly 200 is respectively connected to the fuel storage container of the aircraft and the thrust chamber of the engine, and the fuel delivery assembly is used to deliver the fuel in the fuel storage container to the thrust chamber of the engine. Therefore, the fuel delivery assembly can smoothly deliver the fuel in the fuel storage container of the aircraft to the thrust chamber of the engine in a timely manner, ensuring that the engine can obtain fuel stably, helping the engine to work continuously and stably, avoiding abnormal operation of the engine due to problems such as poor fuel supply, and thus ensuring stable power output during the flight of the aircraft.

[0030] In one example, if Figures 1 to 3 As shown, the swing assembly 100 is sleeved on the fuel delivery assembly 200, and the swing assembly 100 has a first end 100a and a second end 100b, the first end 100a is fixedly connected to the fuselage structure of the aircraft, and the second end 100b is fixedly connected to the thrust chamber of the engine through the fuel delivery assembly 200. The swing assembly 100 includes a plurality of first swing parts 110 located at the first end 100a, a plurality of second swing parts 120 located at the second end 100b, and a connecting member 130 sleeved on the fuel delivery assembly 200, and each first swing part 110 and each second swing part 120 are movably connected to the connecting member 130.

[0031] Since one end of the above-mentioned swing assembly 100 is connected to the fuselage, and the other end is connected to the engine thrust chamber through the fuel delivery assembly, when the engine thrust chamber changes direction to drive the swing assembly 100 to move, it can drive the multiple first swing parts 110 located at the first end 100a and the multiple second swing parts 120 located at the second end 100b to swing under the support of the connecting member 130, so that the engine pushes the aircraft fuselage to swing flexibly to a certain extent, adapt to various posture changes, vibrations, etc. of the aircraft during flight, and can effectively buffer the force generated between the fuselage and the engine due to factors such as changes in flight status, thereby reducing the risk of structural damage that may be caused by rigid connection.

[0032] On this basis, by combining the swing assembly 100 with the fuel delivery assembly 200, the entire engine force transmission device can achieve fuel delivery while taking into account the functions of connecting the engine and the body and providing flexible buffering, so that the overall structure is relatively compact and will not occupy too much internal space of the aircraft, which is conducive to the rational layout and integration of various systems inside the aircraft and improves the overall space utilization efficiency of the aircraft.

[0033] In one achievable manner, Figures 1 to 3 As shown, each first swing portion 110 of the embodiment of the present disclosure is also fixedly connected to the fuselage structure of the aircraft, and each second swing portion 120 is also fixedly connected to the thrust chamber of the engine through the fuel delivery assembly 200.

[0034] In specific implementation, when the engine thrust chamber changes direction, it can drive the swing assembly 100 to swing, so that the swing assembly 100 can drive the body structure of the aircraft to move, thereby completing various posture changes of the aircraft during flight.

[0035] In an alternative approach, Figure 4 FIG. 2 shows a schematic diagram of the structure of the connecting member of the embodiment of the present disclosure. Figures 1 to 4 As shown, the above-mentioned connecting member 130 has an annular portion 131 and a plurality of connecting shafts 132 fixed on the side of the annular portion 131, the plurality of connecting shafts 132 are evenly spaced along the circumference of the annular portion 131, the plurality of connecting shafts 132 include a plurality of first connecting shafts 132a and a plurality of second connecting shafts 132b, the first connecting shafts 132a and the second connecting shafts 132b are arranged at intervals, each first swinging portion 110 is movably connected to the corresponding first connecting shaft 132a, and each second swinging portion 120 is movably connected to the corresponding second connecting shaft 132b.

[0036] It can be understood that the above-mentioned annular portion 131 is a hollow structure, so that the fuel delivery assembly can pass through the annular portion 131, and the connection method of the above-mentioned movable connection includes a rotational connection. The above-mentioned annular portion 131 and the above-mentioned multiple connecting shafts 132 can be a topic-forming structure or a fixed connecting shaft on the annular portion 131, which is not limited here.

[0037] In specific implementation, when the aircraft needs to change its attitude, the engine thrust chamber begins to change the thrust direction. At this time, the engine thrust chamber can drive the second swinging part 120 to swing. At this time, since the first connecting shaft 132a and the second connecting shaft 132b are arranged at intervals, and each first swinging part 110 is movably connected to the corresponding first connecting shaft 132a, and each second swinging part 120 is movably connected to the corresponding second connecting shaft 132b. Therefore, when the second swinging part 120 swings, the first swinging part 110 connected thereto can swing relatively independently with the second swinging part 120 on the basis of their respective connecting shafts, and cooperate with each other, which brings high flexibility to the whole system and can adapt to different working scenes and movement requirements to form a coordinated movement mode.

[0038] On this basis, since the multiple connecting shafts 132 are evenly spaced along the circumference of the annular portion 131, the positions of each first swinging portion 110 and the second swinging portion 120 can be evenly distributed in the annular space, which is very beneficial for application scenarios that require precise control of the position and angle of each swinging portion. In addition, the structures of the annular portion 131 and the connecting shaft 132 are relatively simple. During the installation process, it is only necessary to flexibly connect the first swinging portion 110 and the second swinging portion 120 to the corresponding first connecting shaft 132a and the second connecting shaft 132b, respectively, thereby reducing the difficulty and complexity of installation and improving installation efficiency.

[0039] In one achievable approach, Figure 5 FIG. 2 shows a schematic diagram of the structure of the first swinging part of an embodiment of the present disclosure. Figure 5 As shown, each first swinging portion 110 of the embodiment of the present disclosure has a first through hole 111 matched with the corresponding first connecting shaft 132 a , and each first connecting shaft 132 a passes through the corresponding first through hole 111 .

[0040] In actual applications, each of the above-mentioned first swing parts 110 has a first through hole 111, and the corresponding first connecting shaft 132a connected to one of the first swing parts 110 passes through the first through hole 111 of the first swing part 110, so that the first swing part 110 is rotatably connected to the corresponding first connecting shaft 132a, and the first swing part 110 can rotate around the corresponding first connecting shaft 132a.

[0041] In one achievable approach, Figure 6 FIG. 2 shows a schematic diagram of the structure of the second swinging part of an embodiment of the present disclosure. Figure 6 As shown, each second swinging portion 120 of the embodiment of the present disclosure has a second through hole 121 that cooperates with the corresponding second connecting shaft 132 b , and each second connecting shaft 132 b passes through the corresponding second through hole 121 .

[0042] In actual application, each of the above-mentioned second swing parts 120 has a second through hole 121, and the corresponding second connecting shaft 132b connected to one of the second swing parts 120 passes through the second through hole 121 of the first swing part 110, so that the second swing part 120 is rotatably connected to the corresponding second connecting shaft 132b, and the second swing part 120 can rotate around the corresponding second connecting shaft 132b.

[0043] Therefore, when the attitude of the aircraft needs to be adjusted during flight, the control system issues a command to drive the first swing part 110 and the second swing part 120 to rotate around the corresponding connecting shafts. For example, the second swing part 120 rotates around the second connecting shaft 132b connected thereto, so that the second swing part 120 can swing. When the second swing part 120 swings, it can drive the first swing part 110 to swing around the first connecting shaft 132a, so that the first swing part 110 can swing.

[0044] In one example, if Figures 1 to 3 As shown, the fuel delivery assembly 200 of the embodiment of the present disclosure includes a fuel delivery pipe 210, a first fixing portion 220 and a second fixing portion 230. The first fixing portion 220 is located at one end of the fuel delivery pipe 210 close to the fuel storage container, and the second fixing portion 230 is located at one end of the fuel delivery pipe 210 close to the thrust chamber. The first fixing portion 220 is communicated with the fuel delivery pipe 210 and the fuel storage container respectively, and the second fixing portion 230 is communicated with the fuel delivery pipe 210 and the thrust chamber of the engine respectively, and each second swinging portion 120 is fixedly connected to the second fixing portion 230.

[0045] It is understandable that the above-mentioned fuel delivery pipe 210, the first fixing portion 220 and the second fixing portion 230 can be an integrally formed structure, or a structure in which the fuel delivery pipe 210 is fixedly connected to the first fixing portion 220 and the second fixing portion 230 respectively, which is not limited here. The first fixing portion 220 is arranged at one end of the fuel delivery pipe 210 close to the fuel storage container, and its main function is to connect the fuel delivery pipe 210 with the fuel storage container and establish a connection channel for the fuel to enter the delivery pipe from the storage container. The second fixing portion 230 is located at one end of the fuel delivery pipe 210 close to the thrust chamber, connecting the fuel delivery pipe 210 and the thrust chamber of the engine to ensure that the fuel can smoothly enter the thrust chamber from the delivery pipe.

[0046] In actual applications, when the attitude of the aircraft needs to be adjusted during flight, since the second swinging part 120 is fixedly connected to the second fixed part 230, and the second fixed part 230 is fixedly connected to the thrust chamber of the engine, the thrust chamber of the engine will push the second swinging part 120 to swing around the second connecting axis 132b. As the second swinging part 120 swings, the connecting member 130 connected thereto begins to play a role in transmitting power, thereby driving the first swinging part 110 to swing around the first connecting axis 132a. At this time, since the first swinging part 110 is fixedly connected to the body structure of the aircraft, the swing of the first swinging part 110 will directly act on the aircraft body, so that the aircraft can adjust its attitude in an expected manner.

[0047] On this basis, when the engine thrust chamber changes position due to attitude adjustment, since the first swing part 110 is fixedly connected to the body structure of the aircraft, and the first fixed part 220 is also connected to the fuel storage container, even if the engine thrust chamber pushes the first swing part 110, the second swing part 120 and the connecting member 130 to change direction, the fuel delivery assembly 200 can always maintain a stable connection with the fuel storage container and the thrust chamber, ensuring that the fuel can be continuously, stably and efficiently delivered to the engine thrust chamber, thereby ensuring the normal operation of the engine and improving the reliability of the aircraft power system.

[0048] In one example, the fuel delivery pipe includes a flexible pipe or a bellows.

[0049] In actual applications, when the position of the engine thrust chamber changes due to attitude adjustment, the fuel delivery pipe 210 needs to change shape accordingly. The flexible pipe or bellows can effectively adapt to this dynamic change and can bend and stretch as the position of the engine thrust chamber changes, ensuring that the fuel delivery path always remains unobstructed. Whether in the pitch, yaw or roll process of the aircraft, the fuel can be stably delivered from the storage container to the thrust chamber without interruption of delivery due to twisting or excessive stretching of the pipe. Not only does it ensure the continuity of fuel delivery, but it also provides greater flexibility for the attitude adjustment of the aircraft.

[0050] In one achievable manner, Figure 1 As shown, the engine power transmission device of the embodiment of the present disclosure further includes a fixing member 300, which is respectively fixedly connected to the body structure of the aircraft and the plurality of first swinging parts 110. It should be understood that the fixing member 300 may be in the shape of a ring, and the fixing member 300 is a hollow structure, and the diameter of the first fixing part 220 included in the fuel delivery assembly 200 may be smaller than the diameter of the fixing member 300.

[0051] In practical applications, one end of the fixing member 300 is closely connected to the aircraft body structure, and the other end is fixedly connected to the plurality of first swinging parts 110. When the engine is working, the thrust generated is transmitted to the connecting member 130 through the second swinging part 120, and then transmitted to the first swinging part 110 by the connecting member 130. At this time, the fixing member 300 plays a role, effectively transmitting the force borne by the first swinging part 110 to the aircraft body structure, thereby realizing the pitch, yaw and roll of the aircraft.

[0052] In an optional manner, the second swinging part is provided with a plurality of third through holes 122. The third through holes 122 can reduce the weight of the structure, reduce the overall weight of the aircraft, and improve the thrust-to-weight ratio of the aircraft, thereby selecting an engine with relatively small power or reducing the amount of fuel carried, which helps to reduce the manufacturing and operating costs of the aircraft.

[0053] Illustratively, the fixed connection in the embodiments of the present disclosure may include welding, bolt connection or other fixed connection methods, which are not limited here.

[0054] In one example, the material of the first fixing part and the second fixing part included in the swing assembly and the fuel delivery assembly of the embodiment of the present disclosure can both be made of a material with relatively high strength.

[0055] The disclosed embodiment also provides an aircraft, which includes a body structure, an engine, and an engine force transmission device of the disclosed embodiment, wherein the engine force transmission device is fixedly connected to the body structure and the thrust chamber of the engine, respectively. It should be understood that the aircraft includes an airplane, a rocket, or other types of aircraft, which are not limited here.

[0056] In summary, the engine power transmission device and the aircraft of the embodiment of the present disclosure, firstly, the fuel delivery assembly is connected with the fuel storage container of the aircraft and the thrust chamber of the engine respectively, and the fuel in the fuel storage container of the aircraft can be smoothly delivered to the thrust chamber of the engine, which ensures that the engine obtains fuel stably, helps the engine to work continuously and stably, avoids the abnormal operation of the engine due to problems such as poor fuel supply, and thus ensures the stability of the power output of the aircraft during flight. Secondly, the swing assembly is sleeved on the fuel delivery assembly, and the swing assembly has a first end and a second end, the first end is fixedly connected to the body structure of the aircraft, and the second end is fixedly connected to the thrust chamber of the engine through the fuel delivery assembly. When the thrust chamber of the engine changes direction to drive the swing assembly to move, it can drive the multiple first swing parts located at the first end and the multiple second swing parts located at the second end to swing under the support of the connecting member, so that the engine can drive the aircraft body to swing flexibly to a certain extent, adapt to various attitude changes, vibrations, etc. of the aircraft during flight, and can effectively buffer the force generated by factors such as flight state changes between the body and the engine, and reduce the risk of structural damage that may be caused by rigid connection.

[0057] On this basis, by combining the swing assembly with the fuel delivery assembly, the entire engine force transmission device can not only realize fuel delivery, but also take into account the functions of connecting the engine and the fuselage and providing flexible buffering. This makes the overall structure relatively compact and does not occupy too much internal space of the aircraft. It is conducive to the rational layout and integration of various systems inside the aircraft, thereby improving the overall space utilization efficiency of the aircraft.

[0058] In addition, the swing assembly of the embodiment of the present disclosure includes multiple first swing parts located at the first end, multiple second swing parts located at the second end, and a connecting piece sleeved on the fuel delivery assembly, and each first swing part and each second swing part are movably connected to the connecting piece.

[0059] The basic principles of the present disclosure are described above in conjunction with specific embodiments. However, it should be noted that the advantages, strengths, effects, etc. mentioned in the present disclosure are only examples and not limitations, and it cannot be considered that these advantages, strengths, effects, etc. are required by each embodiment of the present disclosure. In addition, the specific details disclosed above are only for the purpose of illustration and ease of understanding, and are not limitations. The above details do not limit the present disclosure to the necessity of adopting the above specific details to be implemented.

[0060] The block diagrams of the devices, apparatuses, equipment, and systems involved in the present disclosure are only illustrative examples and are not intended to require or imply that they must be connected, arranged, and configured in the manner shown in the block diagrams. As will be appreciated by those skilled in the art, these devices, apparatuses, equipment, and systems can be connected, arranged, and configured in any manner. Words such as "including", "comprising", "having", etc. are open words, referring to "including but not limited to", and can be used interchangeably with them. The words "or" and "and" used here refer to the words "and / or" and can be used interchangeably with them, unless the context clearly indicates otherwise. The word "such as" used here refers to the phrase "such as but not limited to", and can be used interchangeably with it.

[0061] Additionally, as used herein, "or" used in a list of items beginning with "at least one" indicates a separate list, so that, for example, a list of "at least one of A, B, or C" means A or B or C, or AB or AC or BC, or ABC (i.e., A and B and C). Furthermore, the word "exemplary" does not mean that the example described is preferred or better than other examples.

[0062] It should also be noted that in the system and method of the present disclosure, each component or each step can be decomposed and / or recombined. Such decomposition and / or recombination should be regarded as equivalent solutions of the present disclosure.

[0063] Various changes, substitutions, and modifications of the techniques described herein may be made without departing from the teachings defined by the appended claims. Furthermore, the scope of the claims of the present disclosure is not limited to the specific aspects of the processes, machines, manufactures, compositions of events, means, methods, and actions described above. Currently existing or later to be developed processes, machines, manufactures, compositions of events, means, methods, or actions that perform substantially the same functions or achieve substantially the same results as the corresponding aspects described herein may be utilized. Thus, the appended claims include such processes, machines, manufactures, compositions of events, means, methods, or actions within their scope.

[0064] The above description of the disclosed aspects is provided to enable any person skilled in the art to make or use the present disclosure. Various modifications to these aspects will be readily apparent to those skilled in the art, and the general principles defined herein may be applied to other aspects without departing from the scope of the present disclosure. Therefore, the present disclosure is not intended to be limited to the aspects shown herein, but rather to the widest scope consistent with the principles and novel features disclosed herein.

[0065] The above description has been given for the purpose of illustration and description. In addition, this description is not intended to limit the embodiments of the present disclosure to the forms disclosed herein. Although multiple example aspects and embodiments have been discussed above, those skilled in the art will recognize certain variations, modifications, changes, additions and sub-combinations thereof.

Claims

1. An engine power transmission device, characterized in that: The invention comprises a swing assembly and a fuel delivery assembly, wherein the fuel delivery assembly is respectively connected to a fuel storage container of an aircraft and a thrust chamber of an engine, and the fuel delivery assembly is used to deliver fuel in the fuel storage container to the thrust chamber of the engine, the swing assembly is sleeved on the fuel delivery assembly, and the swing assembly has a first end and a second end, the first end is fixedly connected to the fuselage structure of the aircraft, and the second end is fixedly connected to the thrust chamber of the engine through the fuel delivery assembly; The swing assembly includes a plurality of first swing parts located at the first end, a plurality of second swing parts located at the second end, and a connecting piece sleeved on the fuel delivery assembly, and each first swing part and each second swing part are movably connected to the connecting piece.

2. The engine power transmission device according to claim 1, characterized in that: Each of the first swing parts is also fixedly connected to the fuselage structure of the aircraft, and each of the second swing parts is also fixedly connected to the thrust chamber of the engine through the fuel delivery assembly.

3. The engine power transmission device according to claim 1, characterized in that: The connecting member has an annular portion and a plurality of connecting shafts fixed on the side of the annular portion, the plurality of connecting shafts are evenly spaced along the circumference of the annular portion, the plurality of connecting shafts include a plurality of first connecting shafts and a plurality of second connecting shafts, the first connecting shafts and the second connecting shafts are arranged at intervals, each of the first swinging portions is movably connected to the corresponding first connecting shaft, and each of the second swinging portions is movably connected to the corresponding second connecting shaft.

4. The engine power transmission device according to claim 3, characterized in that: Each of the first swinging parts has a first through hole matched with the corresponding first connecting shaft, and each of the first connecting shaft passes through the corresponding first through hole.

5. The engine power transmission device according to claim 3, characterized in that: Each of the second swinging parts has a second through hole matched with the corresponding second connecting shaft, and each of the second connecting shaft passes through the corresponding second through hole.

6. The engine power transmission device according to claim 1, characterized in that: The fuel delivery assembly includes a fuel delivery pipe, a first fixing portion and a second fixing portion, wherein the first fixing portion is located at one end of the fuel delivery pipe close to the fuel storage container, and the second fixing portion is located at one end of the fuel delivery pipe close to the thrust chamber, the first fixing portion is communicated with the fuel delivery pipe and the fuel storage container respectively, the second fixing portion is communicated with the fuel delivery pipe and the thrust chamber of the engine respectively, and each of the second swinging portions is fixedly connected to the second fixing portion.

7. The engine power transmission device according to claim 6, characterized in that: The fuel delivery pipe includes a flexible pipe or a corrugated pipe.

8. The engine power transmission device according to claim 1, characterized in that: The engine force transmission device also includes a fixing member, which is respectively fixedly connected to the body structure of the aircraft and the plurality of first swinging parts.

9. The engine power transmission device according to any one of claims 1 to 8, characterized in that: Each of the second swing parts is provided with a plurality of third through holes.

10. An aircraft, characterized in that: It comprises a body structure, an engine and the engine force transmission device according to any one of claims 1 to 9, wherein the engine force transmission device is fixedly connected to the body structure and the thrust chamber of the engine respectively.

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