Power nacelle structure for distributed electric propulsion aircraft and aircraft

Abstract

The utility model relates to the technical field of aviation, in particular to a power nacelle structure for a distributed electric propulsion aircraft and the aircraft. The power nacelle structure comprises a plurality of mutually independent nacelle units, the plurality of nacelle units are arranged at equal intervals, and flexible separators are arranged among the nacelle units. The power nacelle structure and the fuselage structure are independent, and the design and force transmission of a power device bearing structure are not affected; the short cabin units are flexibly connected, so that the influence of deformation of the bearing structure on the short cabin structure is reduced; the short cabin unit serves as a single structural unit, most parts can be replaced, and the functions of replacing different positions of the same aircraft and modularly assembling and matching different models of aircrafts can be achieved. And meanwhile, the structure is simple, and installation and maintenance are convenient.

Description

TECHNICAL FIELD

[0001] The utility model relates to aviation technology field, concretely relates to a power nacelle structure for distributed electric propulsion aircraft and aircraft. BACKGROUND

[0002] At present, the nacelle of aircraft is all integrated power system, that is, multiple engines are installed in a whole nacelle shell, and the nacelle area corresponding to a single engine cannot be independently disassembled or replaced. Generally, the inlet duct, fan case and other components of commercial aircraft engine should be designed as LRU, with quick disassembly and replaceability. The existing distributed propulsion system structure cannot meet the above requirements. At the same time, the distributed power system is generally installed on the upper surface of the wing, and the whole power nacelle needs special design to match the structural stiffness with the wing, so as to avoid the mutual influence of force transmission between the two structures. SUMMARY

[0003] The utility model discloses a power nacelle structure for distributed electric propulsion aircraft and aircraft to solve any one of the above and other potential problems of prior art.

[0004] In order to solve the above technical problems, the technical scheme of the utility model is: a power nacelle structure for distributed electric propulsion aircraft, the power nacelle structure comprises a plurality of independent nacelle units, the plurality of nacelle units are arranged equidistantly in a straight line, and flexible isolators are arranged between the nacelle units.

[0005] Further, the nacelle unit is a three-section structure, comprising in sequence:

[0006] A nacelle for providing support for the motor and fan;

[0007] An inlet duct and a tail nozzle for providing smooth aerodynamic surface for internal flow channel airflow;

[0008] A fan case for providing fairing for external airflow of nacelle;

[0009] Among them, the inlet duct is arranged at the front end of the nacelle, the tail nozzle is arranged at the rear end of the nacelle, and the fan case is arranged at the top of the nacelle.

[0010] Further, the nacelle comprises a nacelle body, a fan stator, a first positioning groove, a second positioning groove, a nacelle fixing hole and a mounting joint.

[0011] The casing body is a cylindrical structure with flanges at the front and rear ends, the power unit is arranged inside the casing body, the first positioning groove and the second positioning groove are symmetrically arranged on the flanges at the front end and the rear end of the casing body, the casing fixing hole is arranged on the flanges at the front end and the rear end of the casing body, and the mounting section is arranged at the bottom of the casing body.

[0012] Further, the center of the starting face of the cylindrical structure is taken as the origin, the axis is taken as the X axis, the vertical direction is taken as the positive direction of the Y axis, the XY plane is symmetrical, the casing fixing hole is located in the flange range of Y<0, and the first positioning groove and the second positioning groove are located in the flange range of Y>0.

[0013] Further, the cross section of the first positioning groove and the second positioning groove is a right trapezoidal groove, and the angle of the hypotenuse is 45-75°.

[0014] Further, the air inlet channel includes an air inlet channel lip assembly and an air inlet channel mounting partition frame.

[0015] The air inlet channel mounting partition frame is arranged at the rear end of the air inlet channel body, and the air inlet channel lip assembly and the air inlet channel mounting partition frame are connected by glue riveting.

[0016] The air inlet channel mounting partition frame is arranged at the rear end of the air inlet channel body, and the air inlet channel lip assembly and the air inlet channel mounting partition frame are connected by glue riveting.

[0017] Further, the tail nozzle includes a tail nozzle fairing tower tip assembly and a tail nozzle mounting partition frame.

[0018] The tail nozzle mounting partition frame is arranged at the front end of the tail nozzle fairing tower tip assembly, and the tail nozzle fairing tower tip assembly and the tail nozzle mounting partition frame are connected by glue riveting.

[0019] The tail nozzle mounting partition frame is arranged at the front end of the tail nozzle fairing tower tip assembly, and the tail nozzle fairing tower tip assembly and the tail nozzle mounting partition frame are connected by glue riveting.

[0020] Further, the cross section of the positioning groove is an angular cross section, and the angle of the hypotenuse of the angular cross section is 45-75°.

[0021] Further, the flexible partition includes an air inlet channel section, a fairing cover section and a tail nozzle section, and is a hollow structure, and the outer contour is continuous with the shape of the outer surface of the nacelle unit.

[0022] An aircraft includes a fuselage and a wing, and uses a distributed power device, and the power device is arranged with the above-mentioned power nacelle structure.

[0023] The utility model discloses an advantageous effect is: due to adopting above -mentioned technical scheme, the utility model discloses power nacelle structure and fuselage structure are independent, do not influence the wing design and power transmission, the flexible connection between short cabin unit, reduce the influence of wing deformation to short cabin structure, short cabin unit as single structure unit, most parts can replace each other, can realize the replacement of different positions of same aircraft and modular assembly match the function of different model aircraft, and the structure has simple structure, convenient installation, convenient maintenance simultaneously. BRIEF DESCRIPTION OF DRAWINGS

[0024] Figure 1 It is a structural schematic view of the utility model for power nacelle structure of distributed electric propulsion aircraft.

[0025] Figure 2 It is a structural schematic view of adjacent short cabin unit of the utility model.

[0026] Figure 3 It is a structural schematic view of short cabin unit of the utility model.

[0027] Figure 4 It is a structural schematic view of the utility model's nacelle.

[0028] Figure 5 It is the cross section schematic view of the first positioning slot of the utility model.

[0029] Figure 6 It is a structural schematic view of the fan cover of the utility model.

[0030] Figure 7 It is a structural schematic view of the inlet duct of the utility model.

[0031] Figure 8 It is a structural schematic view of the tail nozzle of the utility model.

[0032] In the drawing:

[0033] 1. short cabin unit, 1-1. nacelle, 1-11. nacelle body, 1-12. power unit, 1-13. first positioning slot, 1-14. second positioning slot, 1-15. nacelle fixed hole, 1-16. mounting section, 1-2. inlet duct, 1-21. inlet duct body, 1-22. tail inlet duct mounting partition, 1-3. tail nozzle, 1-31. tail nozzle body, 1-32. tail nozzle mounting partition, 1-33. positioning flange edge, 1-34. mounting hole, 1-4. fan cover, 2. flexible isolator. DETAILED DESCRIPTION

[0034] The specific drawing and specific embodiment below further illustrate the technical scheme of the utility model.

[0035] As Figure 1As shown, the utility model discloses a kind of power nacelle structures for distributed electric propulsion aircraft, which includes several independent short nacelle units, several short nacelle units are equidistantly arranged in linear alignment, and flexible isolator is provided between the short nacelle unit.

[0036] Further, the short nacelle unit is three-section structure, sequentially includes:

[0037] Engine case for providing support for motor, fan;

[0038] Inlet duct and tail nozzle for providing smooth aerodynamic surface for internal flow channel airflow;

[0039] Fan cover for providing fairing for short nacelle external airflow;

[0040] Wherein, the inlet duct is arranged at the front end of the engine case, the tail nozzle is arranged at the rear end of the engine case, and the fan cover is arranged at the top of the engine case.

[0041] Further, the engine case includes engine case body, fan stator, first positioning slot, second positioning slot, engine case fixing hole and mounting section;

[0042] The engine case body is a cylindrical structure with flange edges at the front and rear ends, the power unit is arranged inside the engine case body, the first positioning slot and the second positioning slot are symmetrically arranged on the flange edges of the front end and the rear end of the engine case body;The engine case fixing hole is arranged on the flange edges of the front end and the rear end of the engine case body, and the mounting section is arranged at the bottom of the engine case body.

[0043] Further, the center of the starting face of the cylindrical structure is taken as the origin, the axis is taken as X axis, the vertical direction is taken as Y axis positive direction, based on XY plane symmetry, the engine case fixing hole is located in the flange edge range of Y <0;The first positioning slot and the second positioning slot are located in the flange edge range of Y >0.

[0044] Further, the cross section of the first positioning slot and the second positioning slot is a right trapezoidal slot, and the bevel angle is 45-75 °.

[0045] Further, the inlet duct includes inlet duct lip assembly and inlet duct mounting partition frame;

[0046] Wherein, the inlet duct mounting partition frame is arranged at the rear end of the inlet duct body, and the inlet duct lip assembly and the inlet duct mounting partition frame are connected by glue riveting;

[0047] The inlet duct mounting partition frame is provided with positioning flange and mounting hole matched with the first positioning slot and the engine case fixing hole.

[0048] Further, the tail nozzle comprises a tail nozzle fairing tower tip assembly and a tail nozzle mounting bulkhead;

[0049] The tail nozzle mounting bulkhead is arranged at the front end of the tail nozzle fairing tower tip assembly, and the tail nozzle fairing tower tip assembly and the tail nozzle mounting bulkhead are connected by glue riveting.

[0050] The tail nozzle mounting bulkhead is provided with a positioning flange edge and a mounting hole matched with the second positioning groove and the nacelle fixing hole.

[0051] Further, the positioning groove is in an angular cross section, and the oblique edge of the angular cross section has an inclination angle of 45-75°.

[0052] Further, the flexible partition comprises an air inlet channel section, a fairing section and a tail nozzle section, and is in a hollow structure with a continuous outer profile with the outer curved surface shape of the nacelle unit.

[0053] When the power nacelle structure is mounted on the wing, the following steps should be followed

[0054] 1. The innermost nacelle is positioned and connected to the corresponding bearing structure of the wing through the mounting joint.

[0055] 2. The multiple nacelles are sequentially positioned and connected to the corresponding bearing structure of the wing.

[0056] 3. The air inlet channel assembly is inserted into the first positioning groove from top to bottom, and the corresponding fixing hole at the top is connected by using the fastener.

[0057] 4. The installation of all air inlet channel assemblies is sequentially completed.

[0058] 5. The tail nozzle assembly is inserted into the second positioning groove from top to bottom, and the corresponding fixing hole at the top is connected by using the fastener.

[0059] 6. The installation of all tail nozzle assemblies is sequentially completed.

[0060] 7. The fairing is installed on the air inlet channel mounting bulkhead and the tail nozzle mounting bulkhead according to the corresponding position.

[0061] The two nacelle units are separated by the flexible partition, and can be installed in sequence on the wing to realize parallel installation of any number of units. For the innermost unit connected to the fuselage and the outermost unit, the outer surface can be replaced by a separate side wall plate to meet the special boundary requirements of different positions due to aerodynamic requirements.

[0062] In the above structure and connection mode:

[0063] 1. All positions using glue riveting connection can remove the glue layer or rivets according to the actual load and fatigue requirements.

[0064] 2. The mounting section part can be adjusted according to the actual wing (or corresponding load-bearing structure) structure in addition to the above-mentioned connection mode. Another possible connection mode of arranging fasteners in the axial direction is shown in the drawings.

[0065] 3. The casing should be a cylindrical structure with a flange at both ends. Generally, a hollow cylinder with a flange should be used, with the inner and outer surfaces relatively parallel and the thickness substantially uniform, and can be reinforced with stiffeners according to strength and stiffness requirements.

[0066] 4. With the short body axis end point as the origin, the axis to the rear as the X axis, and the vertical direction upward as the Y axis, the casing 1 structure should be symmetrical about the XY plane, and the necessary fixing holes for bolt and nut connection should all be located in the Y>0 flange range; the first positioning groove and the second positioning groove should all be located in the Y<0 flange range.

[0067] 5. For the inlet duct mounting partition, the angular bevel structure corresponding to the first positioning groove 1-13 in the Y>0 range of the flange and the mounting through hole corresponding to the casing in the Y<0 range of the flange are necessary.

[0068] 6. For the tail nozzle mounting partition, the angular bevel structure corresponding to the second positioning groove 1-14 in the Y>0 range of the flange and the mounting through hole corresponding to the casing in the Y<0 range of the flange are necessary.

[0069] 7. For the flange structure of the casing, the inlet duct mounting partition, and the tail nozzle mounting partition, a symmetrical structure along the XY plane should be used, and a circular shape should be used as the main shape to ensure the consistency of the mounting hole edge distance. Cutting can be allowed at positions such as the side surface to ensure that the overall width of the short body meets the design requirements.

[0070] 8. Flexible connection materials between adjacent short bodies are necessary, and should be divided into inlet duct sections, fairing sections, and tail nozzle sections according to the short body curved surface shape and part separation surface.

[0071] 9. The flexible connection materials used to isolate the short bodies should generally have a hollow structure to reduce the overall weight. At the same time, the connection material passing through the top of the short body should have a certain concave structure to avoid deformation outward after being squeezed, which can damage the overall aerodynamic shape.

[0072] 10. The short body structure should avoid mechanical connection with the wing, and only the fasteners can be added under the lower edge of the inlet duct 3 lip to avoid the lip being lifted up by the negative pressure generated by the airflow.

[0073] The above describes in detail the power nacelle structure for a distributed electric propulsion aircraft and the aircraft provided by the embodiments of the present application. The above description of the embodiments is only used to help understand the method of the present application and its core idea; meanwhile, for those skilled in the art, according to the idea of the present application, the specific implementation and application range can be changed, and the above description should not be understood as a limitation on the present application.

[0074] As used in the specification and claims, certain terminology is used to describe certain components. Those of ordinary skill in the art will understand that different manufacturers of hardware can refer to the same component using different names. The specification and claims should not be controlled based on differences in naming alone, but rather on the difference in functionality of the components. As used throughout the specification and claims, "comprise" or "comprising" is an open term that should be interpreted as "including but not limited to." "Approximately" means within an acceptable error range for the corresponding function, within which those skilled in the art would understand the technology to function essentially the same. The subsequent description in the specification is a preferred embodiment of implementing the present application, and the description is for the purpose of illustrating the general principles of the present application, and is not intended to limit the scope of the present application. The scope of protection of the present application is defined by the appended claims.

[0075] It should also be noted that the terms "comprise", "comprising", or any other variant thereof are intended to cover a non-exclusive inclusion, such that a product or system that comprises a list of elements does not only include those elements, but can also include other elements not expressly listed, or inherent to such product or system. Without more limitations, the element defined by the phrase "comprising a" does not exclude the presence of additional identical elements in the product or system that includes the element.

[0076] It should be understood that the term "and / or" used herein is only a description of the association relationship of the associated objects, which means that there can be three relationships, for example, A and / or B, which means that there are three cases of A alone, A and B together, and B alone. In addition, the character " / " in this paper generally represents that the front and rear associated objects are a "or" relationship.

[0077] The above description shows and describes several preferred embodiments of the present application, but as mentioned above, it should be understood that the present application is not limited to the form disclosed herein, and should not be regarded as excluding other embodiments, but can be used in various other combinations, modifications and environments, and can be modified by the above teaching or related art or knowledge within the scope of the application conceived. The changes and modifications made by those skilled in the art without departing from the spirit and scope of the present application shall be within the scope of protection of the appended claims of the present application.

Claims

1. A power nacelle structure for a distributed electric propulsion aircraft, characterized in that, The power nacelle structure comprises a plurality of independent nacelle units, the nacelle units are equidistantly arranged in a straight line, and flexible isolation members are arranged between the nacelle units.

2. The power nacelle structure of claim 1, wherein, The nacelle unit is a three-section structure, comprising, in sequence, a casing for supporting the motor and fan, an inlet duct and a tail nozzle for providing a smooth aerodynamic surface for the airflow in the internal flow channel, and a fan cover for providing flow regulation for the airflow outside the nacelle, wherein the inlet duct is arranged at the front end of the casing, the tail nozzle is arranged at the rear end of the casing, and the fan cover is arranged at the top of the casing.

3. The power nacelle structure of claim 2, wherein, The casing comprises a casing body, a fan stator, a first positioning groove, a second positioning groove, a casing fixing hole and a mounting joint; the casing body is a cylindrical structure with flanges at the front and rear ends, the power unit is arranged inside the casing body, the first and second positioning grooves are symmetrically arranged on the flanges at the front and rear ends of the casing body, the casing fixing hole is arranged on the flanges at the front and rear ends of the casing body, and the mounting joint is arranged at the bottom of the casing body.

4. The power nacelle structure of claim 3, wherein, Taking the center of the starting surface of the cylindrical structure as the origin, the axis to the rear as the X axis, and the vertical direction pointing to the wing as the positive direction of the Y axis, based on the symmetry of the XY plane, the casing fixing hole is located within the flange range of Y<0, and the first and second positioning grooves are located within the flange range of Y>0.

5. The power nacelle structure of claim 3, wherein, The cross section of the first and second positioning grooves is a right trapezoidal groove, and the angle of the hypotenuse is 45-75°.

6. The power nacelle structure of claim 3, wherein, The inlet duct comprises an inlet duct lip assembly and an inlet duct mounting partition; wherein the inlet duct mounting partition is arranged at the rear end of the inlet duct body, and the inlet duct lip assembly and the inlet duct mounting partition are connected by glue riveting; the inlet duct mounting partition is provided with a positioning flange and a mounting hole matched with the first positioning groove and the casing fixing hole.

7. The power nacelle structure of claim 3, wherein The tail nozzle comprises a tail nozzle fairing tower tip assembly and a tail nozzle mounting partition; wherein the tail nozzle mounting partition is arranged at the front end of the tail nozzle fairing tower tip assembly, and the tail nozzle fairing tower tip assembly and the tail nozzle mounting partition are connected by glue riveting; the tail nozzle mounting partition is provided with a positioning flange and a mounting hole matched with the second positioning groove and the casing fixing hole.

8. The power nacelle structure according to claim 6 or 7, characterized in that, The cross section of the positioning groove is an angular cross section; the angle of the hypotenuse of the angular cross section is 45-75°.

9. The power nacelle structure of claim 1, wherein, The flexible isolation member comprises an inlet duct section, a fairing cover section and a tail nozzle section, and is a hollow structure inside, and the external contour is continuous with the external curved surface shape of the nacelle unit.

10. An aircraft, comprising a fuselage and a wing, and using distributed power plants, characterized in that, The power device is arranged with the power nacelle structure according to any one of claims 1-9.

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