An engine power transmission device and aircraft

Abstract

The present disclosure relates to the technical field of aircraft, and particularly relates to an engine power transmission device and an aircraft. The engine power transmission device comprises a swing assembly and a fuel delivery assembly, the fuel delivery assembly is in communication with a fuel storage container of the aircraft and a thrust chamber of the engine respectively, the fuel delivery assembly is used for delivering fuel in the fuel storage container into the thrust chamber of the engine, the swing assembly is sleeved on the fuel delivery assembly, the swing assembly has a first end and a second end, the first end is fixedly connected with a body structure of the aircraft, and the second end is fixedly connected with the thrust chamber of the engine through the fuel delivery assembly. The engine power transmission device and the aircraft provided by the present disclosure 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.

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

[0002] The attitude control of an aircraft is mainly realized through the swing of an engine. When the engine swings, a power transmission assembly is often needed to connect the engine and the body structure of the aircraft. When the engine swings within a certain angle range, different directions of thrust generated by the engine can be transmitted to the body structure of the aircraft by the power transmission assembly to realize the attitude control of the aircraft such as pitch, yaw or roll.

[0003] However, the engine power transmission assembly used in the related art has the following problems. First, the installation is not convenient enough, which leads to a large amount of time and labor needed in the assembly and maintenance of the aircraft. Second, 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

[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 are more compact and improve the space utilization efficiency of the aircraft as a whole.

[0005] According to one aspect of the present disclosure, an engine power transmission device is provided, which comprises a swing assembly and a fuel delivery assembly. The fuel delivery assembly is in communication with a fuel storage container of an aircraft and a thrust chamber of an engine, respectively. The fuel delivery assembly is used to deliver fuel in the fuel storage container into the thrust chamber of the engine. The swing assembly is sleeved on the fuel delivery assembly. The swing assembly has a first end and a second end. The first end is fixedly connected with a body structure of the aircraft. The second end is fixedly connected with the thrust chamber of the engine through the fuel delivery assembly.

[0006] The swing assembly comprises a plurality of first swing portions at the first end, a plurality of second swing portions at the second end and a connecting piece sleeved on the fuel delivery assembly. Each first swing portion and each second swing portion are movably connected with the connecting piece.

[0007] According to another aspect of the present disclosure, an aircraft is provided, which comprises a body structure, an engine and an engine power transmission device according to an embodiment of the present disclosure. The engine power transmission device is fixedly connected with the body structure and the thrust chamber of the engine, respectively.

[0008] In one or more technical solutions provided in this disclosure, firstly, the fuel delivery assembly is connected to the aircraft's fuel storage container and the engine's thrust chamber, respectively, enabling the smooth delivery of fuel from the aircraft's fuel storage container to the engine's thrust chamber. This ensures stable fuel supply to the engine, contributing to its continuous and stable operation and preventing abnormal engine operation due to fuel supply issues, thereby ensuring stable power output during aircraft flight. Secondly, a swing assembly is sleeved on the fuel delivery assembly. The swing assembly has a first end and a second end. The first end is fixedly connected to the aircraft's fuselage structure, and the second end is fixedly connected to the engine's thrust chamber via the fuel delivery assembly. When the engine's thrust chamber changes direction, causing the swing assembly to move, it can cause multiple first swing parts located at the first end and multiple second swing parts located at the second end to swing under the support of the connecting member. Therefore, the engine can flexibly swing the aircraft fuselage to a certain extent, adapting to various attitude changes and vibrations during flight. This effectively buffers the forces generated between the fuselage and the engine due to changes in flight status, reducing the risk of structural damage that may result from rigid connections.

[0009] Based on this, by combining the swing assembly with the fuel delivery assembly, the entire engine power transmission device can not only deliver fuel, but also connect the engine and the fuselage and provide flexible buffering. This makes the overall structure relatively compact and does not occupy too much space inside the aircraft. It is conducive to the rational layout and integration of various systems inside the aircraft and improves the overall space utilization efficiency of the aircraft.

[0010] In addition, the swing assembly of this disclosure includes a plurality of first swing portions located at a first end, a plurality of second swing portions located at a second end, and a connector sleeved on the fuel delivery assembly, wherein each first swing portion and each second swing portion is movably connected to the connector. Attached Figure Description

[0011] The above and other objects, features, and advantages of this disclosure will become more apparent from the more detailed description of the embodiments thereof in conjunction with the accompanying drawings. The drawings are provided to further illustrate the embodiments of this disclosure and form part of the specification. They are used together with the embodiments of this disclosure to explain the disclosure and do not constitute a limitation thereof. In the drawings, the same reference numerals generally represent the same components or steps.

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

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

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

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

[0016] Figure 5 is a structural schematic view of a first swing part according to an embodiment of the present disclosure;

[0017] Figure 6 is a structural schematic view of a second swing part according to an embodiment of the present disclosure.

[0018] Reference Signs:

[0019] 100 - swing assembly, 100a - first end, 100b - second end, 110 - first swing part, 111 - first through hole, 120 - second swing 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 solved by the present disclosure, the technical solutions and the beneficial effects clearer, the present disclosure will be further described in detail below with reference to the drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present disclosure and should not be used to limit the present disclosure.

[0021] It should be noted that when an element is referred to as being "fixed to" or "set 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", "second" are only used for descriptive purposes and should not be construed as indicating or implying relative importance or implicitly indicating the number of indicated technical features. Therefore, the features defined with "first", "second" can explicitly or implicitly include one or more of the features. In the description of the present disclosure, the meaning of "a plurality of" is two or more, unless otherwise explicitly and specifically limited. The meaning of "several" is one or more, unless otherwise explicitly and specifically limited.

[0023] In the description of the present disclosure, it needs to be understood that the terms "upper", "lower", "front", "back", "left", "right" and the like indicate the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present disclosure and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present disclosure.

[0024] In the description of the present disclosure, it needs to be noted that unless otherwise explicitly specified and limited, the terms "mounting", "connecting", "connection" should be understood broadly, for example, it can be fixed connection, or detachable connection, or integrally connected; it can be mechanical connection, or electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, it can be the internal communication of two elements or the interaction relationship between two elements. For those skilled in the art, the specific meaning of the above terms in the present disclosure can be understood according to the specific circumstances.

[0025] The attitude control of the aircraft is a key technology to ensure that it flies stably along the predetermined trajectory during flight, and this process mainly relies on the swing of the engine. When the engine swings, the power transmission assembly plays an indispensable role, which is like a bridge that closely connects the engine and the aircraft body structure.

[0026] When the engine swings within a certain angle range, the direction of the thrust generated by the engine will change accordingly. For example, when the aircraft needs to perform a pitch action, the engine swings in a certain direction, at this time the power transmission assembly needs to transmit the thrust generated by the engine to the aircraft body structure, so as to make the aircraft head up or down, thereby achieving the control of the pitch attitude. Similarly, in the aspect of yaw control, the engine swing generates lateral thrust, which is transmitted to the aircraft body through the power transmission assembly, so that the aircraft can change the heading to the left or right. In the aspect of roll control, the swing thrust of the engine is transmitted through the power transmission assembly, which drives the aircraft to rotate around its longitudinal axis, achieving the adjustment of the roll attitude.

[0027] However, the engine power transmission assembly used in the related art has the following problems. First, the installation is not convenient enough, which leads to a large amount of time and labor being consumed in the assembly and maintenance of the aircraft. Second, 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 present embodiment provides an engine power 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 FIG. 1 shows a structural schematic diagram of an engine force transmission device according to an embodiment of the present disclosure, Figure 2 FIG. 2 shows a structural schematic diagram of a swing assembly according to an embodiment of the present disclosure, Figure 3 FIG. 3 shows a structural schematic diagram of a fuel delivery assembly according to an embodiment of the present disclosure. As Figures 1 to 3 shown, the engine force transmission device according to an embodiment of the present disclosure comprises a swing assembly 100 and a fuel delivery assembly 200, wherein the fuel delivery assembly 200 is in communication with a fuel storage container of an aircraft and a thrust chamber of an engine respectively, and the fuel delivery assembly is used to deliver fuel in the fuel storage container to the thrust chamber of the engine. Therefore, the fuel delivery assembly can timely and smoothly deliver fuel in the fuel storage container of the aircraft to the thrust chamber of the engine, ensuring that the engine can stably obtain fuel, which helps the engine to continuously and stably work, avoids abnormal working of the engine due to poor fuel supply, and further ensures stable power output of the aircraft during flight.

[0030] In an example, as Figures 1 to 3 shown, the swing assembly 100 is sleeved on the fuel delivery assembly 200, the swing assembly 100 has a first end 100a and a second end 100b, the first end 100a is fixedly connected with a body structure of an aircraft, and the second end 100b is fixedly connected with a thrust chamber of an engine through the fuel delivery assembly 200. The swing assembly 100 comprises a plurality of first swing portions 110 at the first end 100a, a plurality of second swing portions 120 at the second end 100b, and a connecting piece 130 sleeved on the fuel delivery assembly 200, each first swing portion 110 and each second swing portion 120 are movably connected with the connecting piece 130.

[0031] Since one end of the swing assembly 100 is connected with the body, and the other end is connected with 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 100 to act, the plurality of first swing portions 110 at the first end 100a and the plurality of second swing portions 120 at the second end 100b can be driven to swing under the support of the connecting piece 130, so that the aircraft body driven by the engine can swing flexibly to a certain extent, adapt to various attitude changes and vibrations of the aircraft during flight, and effectively buffer the force between the body and the engine due to changes in flight state and other factors, and reduce the risk of structural damage caused by rigid connection.

[0032] On this basis, by combining the swing assembly 100 with the fuel delivery assembly 200, the entire engine power transmission device can realize fuel delivery, connect the engine and the airframe, and provide flexible buffering, so that the overall structure is relatively compact and does not occupy too much internal space of the aircraft, which is beneficial to the reasonable layout and integration of various systems in the aircraft and improves the overall space utilization efficiency of the aircraft.

[0033] In an implementable manner, as shown in Figures 1 to 3 each first swing part 110 is further fixedly connected with the airframe structure of the aircraft, and each second swing part 120 is further fixedly connected with the thrust chamber of the engine through the fuel delivery assembly 200.

[0034] In specific implementation, when the engine thrust chamber changes direction, the swing assembly 100 can be swung, so as to drive the airframe structure of the aircraft to move and complete various attitude changes of the aircraft during flight.

[0035] In an optional manner, Figure 4 a structural schematic diagram of the connecting piece of the embodiment of the present disclosure is shown. As shown in Figures 1 to 4 the connecting piece 130 has a ring-shaped part 131 and a plurality of connecting shafts 132 fixed on the side surface of the ring-shaped part 131, the plurality of connecting shafts 132 are equidistantly distributed along the circumference of the ring-shaped part 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 swing part 110 is movably connected with a corresponding first connecting shaft 132a, and each second swing part 120 is movably connected with a corresponding second connecting shaft 132b.

[0036] It can be understood that the ring-shaped part 131 is a hollow structure, so that the fuel delivery assembly can pass through the ring-shaped part 131, the movable connection includes rotary connection, and the ring-shaped part 131 and the plurality of connecting shafts 132 can be integrally formed, or the connecting shafts can be fixed on the ring-shaped part 131, which is not limited here.

[0037] In actual implementation, when the aircraft needs to change the attitude, the engine thrust chamber starts to change the thrust direction, at this time, the second swing part 120 can be swung by the engine thrust chamber, at this time, since the first connecting shaft 132a and the second connecting shaft 132b are arranged at intervals, and each first swing part 110 is movably connected with the corresponding first connecting shaft 132a, and each second swing part 120 is movably connected with the corresponding second connecting shaft 132b. Therefore, when the second swing part 120 swings, the first swing part 110 connected with the second swing part 120 can swing relatively independently on the basis of the respective connecting shafts, and cooperate with each other to bring higher flexibility to the whole system, so as to adapt to different working scenes and motion requirements and form a coordinated motion mode.

[0038] On this basis, since the plurality of connecting shafts 132 are equidistantly distributed along the circumference of the annular part 131, the positions of each first swing part 110 and second swing part 120 in the annular space are uniformly distributed, which is very advantageous for application scenarios that need to accurately control the positions and angles of the swing parts. Moreover, the structure of the annular part 131 and the connecting shaft 132 is relatively simple, and in the installation process, only the first swing part 110 and the second swing part 120 need to be movably connected with the corresponding first connecting shaft 132a and second connecting shaft 132b respectively, so as to reduce the difficulty and complexity of installation and improve the installation efficiency.

[0039] In an implementable manner, Figure 5 A structural schematic diagram of the first swing part of the embodiment of the present disclosure is shown. As shown in Figure 5 Each first swing part 110 of the embodiment of the present disclosure has a first through hole 111 matched with the corresponding first connecting shaft 132a, and each first connecting shaft 132a passes through the corresponding first through hole 111.

[0040] In actual application, each first swing part 110 has a first through hole 111, and the corresponding first connecting shaft 132a connected with 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 with the corresponding first connecting shaft 132a, and the first swing part 110 can rotate around the corresponding first connecting shaft 132a.

[0041] In an implementable manner, Figure 6 A structural schematic diagram of the second swing part of the embodiment of the present disclosure is shown. As shown in Figure 6 Each second swing part 120 of the embodiment of the present disclosure has a second through hole 121 matched with the corresponding second connecting shaft 132b, and each second connecting shaft 132b passes through the corresponding second through hole 121.

[0042] In practical applications, each of the second swing parts 120 has a second through hole 121. 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, during flight, when attitude adjustment is required, the control system issues commands to drive the first swing part 110 and the second swing part 120 to rotate around their respective connecting shafts. For example, the second swing part 120 rotates around the second connecting shaft 132b connected to it, thereby realizing the swing of the second swing part 120. When the second swing part 120 swings, it can drive the first swing part 110 to swing around the first connecting shaft 132a, thereby realizing the swing of the first swing part 110.

[0044] In one example, such as Figures 1 to 3 As shown, the fuel delivery assembly 200 of this embodiment includes a fuel delivery pipe 210, a first fixing part 220 and a second fixing part 230. The first fixing part 220 is located at one end of the fuel delivery pipe 210 near the fuel storage container, and the second fixing part 230 is located at one end of the fuel delivery pipe 210 near the thrust chamber. The first fixing part 220 is connected to the fuel delivery pipe 210 and the fuel storage container, and the second fixing part 230 is connected to the fuel delivery pipe 210 and the thrust chamber of the engine, respectively. Each second swing part 120 is fixedly connected to the second fixing part 230.

[0045] It is understood that the aforementioned fuel delivery pipe 210, the first fixing part 220, and the second fixing part 230 can be integrally formed, or they can be separately fixedly connected to the fuel delivery pipe 210 and the first fixing part 220 and the second fixing part 230; this is not limited here. The first fixing part 220 is located at the end of the fuel delivery pipe 210 near the fuel storage container, and its main function is to connect the fuel delivery pipe 210 to the fuel storage container, establishing a connection channel for fuel to enter the delivery pipe from the storage container. The second fixing part 230 is located at the end of the fuel delivery pipe 210 near the thrust chamber, connecting the fuel delivery pipe 210 to the engine's thrust chamber, ensuring that fuel can smoothly enter the thrust chamber from the delivery pipe.

[0046] In actual application, when the attitude needs to be adjusted during the flight of the aircraft, since the second swing part 120 is fixedly connected with the second fixed part 230, and the second fixed part 230 is fixedly connected with the thrust chamber of the engine, the thrust chamber of the engine will push the second swing part 120 to swing around the second connecting shaft 132b, and with the swinging of the second swing part 120, the connecting piece 130 connected therewith starts to play a role of transmitting power, so as to drive the first swing part 110 to swing around the first connecting shaft 132a. At this time, since the first swing part 110 is fixedly connected with the body structure of the aircraft, the swinging of the first swing part 110 will directly act on the aircraft body, so that the aircraft can be adjusted in attitude in the expected manner.

[0047] On this basis, when the position of the engine thrust chamber is changed due to attitude adjustment, since the first swing part 110 is fixedly connected with the body structure of the aircraft, and the first fixed part 220 is also in communication with the fuel storage container, even if the engine thrust chamber pushes the first swing part 110, the second swing part 120 and the connecting piece 130 to change the direction, the fuel delivery assembly 200 can always maintain 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, guaranteeing the normal operation of the engine and improving the reliability of the power system of the aircraft.

[0048] In an example, the fuel delivery pipe described above comprises a flexible pipe or a bellows pipe.

[0049] In actual application, when the position of the engine thrust chamber is changed due to attitude adjustment, the fuel delivery pipe 210 needs to change shape accordingly. The flexible pipe or the bellows pipe can effectively adapt to such dynamic changes and can bend and stretch with the change of the position of the engine thrust chamber, ensuring that the fuel delivery path is always unblocked. Whether in the process of pitching, yawing or rolling of the aircraft, the fuel can be stably delivered from the storage container to the thrust chamber, and the delivery will not be interrupted due to excessive twisting or stretching of the pipe. Not only the continuity of fuel delivery is ensured, but also greater flexibility is provided for the attitude adjustment of the aircraft.

[0050] In an implementable manner, as shown in Figure 1 The engine force transmission device of the embodiment of the present disclosure further comprises a fixing piece 300 fixedly connected with the body structure of the aircraft and the plurality of first swing parts 110. It should be understood that the shape of the fixing piece 300 can be annular, the fixing piece 300 is a hollow structure, and the diameter of the first fixed part 220 included in the fuel delivery assembly 200 can be smaller than the diameter of the fixing piece 300.

[0051] In practical application, one end of the fixing member 300 is fixedly connected with the body structure of the aircraft, and the other end is fixedly connected with the plurality of first swing parts 110. When the engine is working, the generated thrust is transmitted to the connecting member 130 through the second swing part 120, and then transmitted to the first swing part 110 through the connecting member 130. At this time, the fixing member 300 plays a role to effectively transmit the force borne by the first swing part 110 to the body structure of the aircraft, so as to realize the processes of pitching, yawing and rolling of the aircraft.

[0052] In an optional mode, a plurality of third through holes 122 are formed in the second swing part. The third through holes 122 can realize structural weight reduction, reduce the overall weight of the aircraft, improve the thrust-to-weight ratio of the aircraft, and then the power of the engine can be relatively small, or the carrying amount of fuel can be reduced, which helps to reduce the manufacturing and operating costs of the aircraft.

[0053] For example, the fixed connection in the embodiment of the present disclosure can include welding, bolt connection or other fixed connection mode, which is not limited here.

[0054] In an example, the swing assembly and the fuel delivery assembly of the embodiment of the present disclosure can use materials with high strength for the first fixed part and the second fixed part.

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

[0056] In summary, the engine power transmission device and the aircraft of the embodiments of the present disclosure have the following advantages. Firstly, the fuel delivery assembly is in communication with the fuel storage container of the aircraft and the thrust chamber of the engine respectively, and can smoothly deliver the fuel in the fuel storage container of the aircraft to the thrust chamber of the engine, thereby ensuring that the engine can stably obtain fuel, helping the engine to continuously and stably work, avoiding abnormal working of the engine due to poor fuel supply and the like, and further ensuring stable power output of the aircraft during flight. Secondly, the swing assembly is sleeved on the fuel delivery assembly, the swing assembly has a first end and a second end, the first end is fixedly connected with the body structure of the aircraft, and the second end is fixedly connected with 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 act, the plurality of first swing parts at the first end and the plurality of second swing parts at the second end can swing under the support of the connecting piece, so that the aircraft body driven by the engine can swing flexibly to a certain extent, adapt to various attitude changes and vibrations of the aircraft during flight, and effectively buffer the force between the aircraft body and the engine due to changes in flight state and the like, thereby reducing the risk of structural damage caused by rigid connection.

[0057] On this basis, by combining the swing assembly with the fuel delivery assembly, the entire engine power transmission device can not only realize fuel delivery, but also connect the engine and the body and provide flexible buffering function, so that the overall structure is relatively compact and does not occupy too much internal space of the aircraft, which is conducive to reasonable layout and integration of various systems in the aircraft and improves the overall space utilization efficiency of the aircraft.

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

[0059] The above describes the basic principles of the present disclosure in combination with specific embodiments, but it should be pointed out that the advantages, advantages, effects and the like mentioned in the present disclosure are only examples and not limitations, and these advantages, advantages, effects and the like cannot be considered as the must-have of each embodiment of the present disclosure. In addition, the above specific details are only for the purpose of example and understanding, and are not limited to the above specific details for the implementation of the present disclosure.

[0060] The block diagrams of devices, apparatuses, equipment, systems referred to in the present disclosure are shown by way of example only and are not intended to require or imply that the devices, apparatuses, equipment, systems must be connected, arranged, configured in the manner as illustrated. These devices, apparatuses, equipment, systems can be connected, arranged, configured in any manner as will be readily appreciated by those skilled in the art. Words such as "include," "contain," "have," etc., are used synonymously with each other and mean "including but not limited to," and will be understood to encompass the items listed as well as other like or similar items. The words "or" and "and" as used herein, unless otherwise indicated, shall carry a meaning to the effect that "and / or" and can be used interchangeably with each other. The word "such as" as used herein, unless otherwise indicated, shall carry a meaning to the effect that "such as but not limited to."

[0061] Also, as used in the description herein, the term "or" as used in the listing of items prefaced by "at least one of" indicates a disjunctive list such 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). In addition, the phrase "example of" as used herein means "example, but not the only example of."

[0062] It is also important to note that the systems and methods of the present disclosure can be embodied in a variety of forms without departing from the spirit or essential characteristics thereof. Likewise, the disclosure is to be understood to include any alterations, modifications, and improvements to the examples of the disclosure that are suited to the same ends as those achieved by the examples disclosed herein, without departing from the scope of the disclosure. Therefore, the foregoing description is not intended to be taken in a limiting sense, but is made solely for purposes of illustrating aspects of the disclosure.

[0063] Various changes, modifications and alterations to the teachings of the present disclosure herein described will readily occur to those skilled in the art and it is intended that the scope of the disclosure encompass such alterations, modifications and changes within the scope of the appended claims. Moreover, although the foregoing has been described in some detail for purposes of clarity, it will be apparent that certain changes and modifications can be made without departing from the principles thereof. Accordingly, the various aspects of the disclosure are intended to embrace all such alterations, modifications and variations as are within the scope and ambit of the appended claims. In addition, while a number of aspects of the disclosure have been described herein, it is understood that the skilled artisan will be able to devise many other aspects that, although perhaps not explicitly stated or shown herein, embody the principles of the disclosure and are included within its spirit and scope.

[0064] The preceding 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 generic principles defined herein can be applied to other aspects without departing from the scope of the disclosure. Thus, the present disclosure is not intended to be limited to the aspects shown herein but is to be accorded the widest scope consistent with the claims and the principles and novel features disclosed herein.

[0065] The foregoing description has been presented for the purposes of illustration and description. Furthermore, the description is not intended to limit the embodiments of the disclosure to the forms disclosed herein. Although the various example aspects and embodiments have been described herein with regard to particular aspects and embodiments, those skilled in the art will recognize that certain modifications, changes, substitutions, additions and sub-combinations can be made without departing from the spirit of the disclosure.

Claims

1. An engine power transmission device characterized by comprising: The engine force transmission device comprises a swing assembly and a fuel delivery assembly, the fuel delivery assembly is in communication with a fuel storage container of an aircraft and a thrust chamber of an engine respectively, the fuel delivery assembly is used for delivering fuel in the fuel storage container into the thrust chamber of the engine, the swing assembly is sleeved on the fuel delivery assembly, the swing assembly has a first end and a second end, the first end is fixedly connected with a body structure of the aircraft, and the second end is fixedly connected with the thrust chamber of the engine through the fuel delivery assembly. The swing assembly comprises a plurality of first swing parts at the first end, a plurality of second swing parts at the second end and a connecting piece sleeved on the fuel delivery assembly, each first swing part and each second swing part are movably connected with the connecting piece. The connecting piece has a ring part and a plurality of connecting shafts fixed on the side surface of the ring part, the plurality of connecting shafts are equidistantly distributed along the circumference of the ring part, the plurality of connecting shafts comprise 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 first swing part is movably connected with a corresponding first connecting shaft, and each second swing part is movably connected with a corresponding second connecting shaft. The fuel delivery assembly comprises a fuel delivery pipe, a first fixed part and a second fixed part, the first fixed part is located at one end of the fuel delivery pipe close to the fuel storage container, the second fixed part is located at one end of the fuel delivery pipe close to the thrust chamber, the first fixed part is in communication with the fuel delivery pipe and the fuel storage container respectively, the second fixed part is in communication with the fuel delivery pipe and the thrust chamber of the engine respectively, and each second swing part is fixedly connected with the second fixed part.

2. The engine power transmission device according to claim 1, characterized by, Each first swing part is also fixedly connected with the body structure of the aircraft, and each second swing part is also fixedly connected with the thrust chamber of the engine through the fuel delivery assembly.

3. The engine power transmitting arrangement of claim 2, wherein, Each first swing part has a first through hole matched with a corresponding first connecting shaft, and each first connecting shaft passes through a corresponding first through hole.

4. The engine power transmission device of claim 2, wherein Each second swing part has a second through hole matched with a corresponding second connecting shaft, and each second connecting shaft passes through a corresponding second through hole.

5. The engine power transfer device of claim 4, wherein, The fuel delivery pipe comprises a flexible pipe.

6. The engine power transfer device of claim 1, wherein The engine force transmission device further comprises a fixing piece, the fixing piece is fixedly connected with the body structure of the aircraft and the plurality of first swing parts respectively.

7. The engine power transmission device according to any one of claims 1 to 6, characterized by A plurality of third through holes are formed in each second swing part.

8. An aircraft, characterized in that The engine force transmission device comprises a body structure, an engine and the engine force transmission device according to any one of claims 1-6, the engine force transmission device is fixedly connected with the body structure and the thrust chamber of the engine respectively.

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