Fuel oil power shell structure of hybrid power aircraft

Abstract

The utility model relates to the technical field of aircraft shells, and discloses a fuel oil power shell structure of a hybrid power aircraft, an upper air inlet cover is integrally formed at the middle end of the top of an upper shell, a lower air inlet cover is connected to the intersection position of the bottom of the inner side of a left lower shell and the bottom of the inner side of a right lower shell, and an upper air inlet is formed in the inner side of the upper air inlet cover; the lower left shell, the lower right shell and the upper shell are integrally assembled to form the integral power shell, and the upper air inlet cover and the lower air inlet cover are respectively arranged at the center positions of the bottom and the top of the power shell, so that resistance airflow can quickly enter the inner side of the power shell through the upper air inlet and the lower air inlet; in this way, the power system in the power shell can be rapidly cooled through the airflow entering the inner side of the power shell, performance reduction caused by overheating of the power system is avoided, and it is guaranteed that the power system can fly for a long time in the low-temperature running state.

Description

TECHNICAL FIELD

[0001] The utility model relates to aircraft shell technical field, concretely is a kind of hybrid power aircraft fuel power shell structure. BACKGROUND

[0002] Hybrid power aircraft is a kind of aircraft using two or more power sources combined to achieve optimal performance, which combines traditional fuel power system and electric drive system, while the power shell of hybrid power aircraft is mainly used to protect and fix engine, while reducing air resistance, and for the power shell of hybrid power aircraft, it generally refers to the external structural part that provides protection and support for the power system of aircraft, which can ensure the normal operation of power device such as engine, and protect passengers and aircraft from external environment to some extent;

[0003] The current power shell structure of aircraft is generally a whole structure, which lacks a structure for flow guiding and resistance reducing on the outside of the power shell, so that the air resistance received by the power shell during flight is large, which not only affects the flight speed of the aircraft, but also increases the energy consumption of the aircraft. SUMMARY

[0004] (I) Technical problem solved

[0005] In view of the shortcomings of the prior art, the utility model provides a kind of hybrid power aircraft fuel power shell structure, solve the current power shell structure of aircraft generally be whole structure, it lacks the structure for flow guiding and resistance reducing on the outside of the power shell, so that the air resistance received by the power shell during flight is large, which not only affects the flight speed of the aircraft, but also increases the energy consumption of the aircraft.

[0006] (II) Technical scheme

[0007] To achieve the above purpose, the utility model provides the following technical scheme: a kind of hybrid power aircraft fuel power shell structure, including fuselage and power shell, the side of the fuselage is connected with power shell, the power shell is composed of left lower shell, right lower shell and upper shell jointly;

[0008] Left lower shell and right lower shell are arranged in pairs in the edge of fuselage in a center-symmetrical manner, upper shell is arranged at the top position of left lower shell and right lower shell, and the end of upper shell is connected with the top position of fuselage;

[0009] An upper air inlet cover is integrally formed in the top of the upper shell, lower air inlet covers are connected to the inner bottom of the left and right lower shells, the inner side of the upper air inlet cover and the top of the upper shell form an upper air inlet, and two air guide interface seats are symmetrically connected to the inner side of the top of the upper shell at the position of the inner side of the upper air inlet cover.

[0010] The lower air inlet cover is internally provided with a lower air inlet, and the left and right lower shells are each provided with an air outlet.

[0011] As a preferred technical scheme of the fuel power shell structure of the hybrid power aircraft, the left and right lower shells and the upper shell are assembled into an integral structure by welding, and the connection between the left and right lower shells, the upper shell and the fuselage is a smooth arc structure.

[0012] As a preferred technical scheme of the fuel power shell structure of the hybrid power aircraft, the upper air inlet cover and the lower air inlet cover are in the shape of a conical horn, and the air inlet direction of the upper air inlet and the lower air inlet extends to the inner side of the power shell.

[0013] As a preferred technical scheme of the fuel power shell structure of the hybrid power aircraft, the air outlet is arranged at the tail end of the left and right lower shells, and the air outlet is arranged on the same horizontal plane as the head of the fuselage.

[0014] As a preferred technical scheme of the fuel power shell structure of the hybrid power aircraft, the left and right sides of the upper shell are each connected with a connecting wing plate, the left and right sides of the fuselage are each connected with a special-shaped air deflector at the position corresponding to the connecting wing plate, and the connecting wing plate and the special-shaped air deflector form an integral streamlined structure.

[0015] As a preferred technical scheme of the fuel power shell structure of the hybrid power aircraft, the inner side of the connecting wing plate and the special-shaped air deflector is provided with a recess, and the recess and the side of the fuselage form a drag-reducing groove.

[0016] (Three) beneficial effects

[0017] Compared with the prior art, the fuel power shell structure of the hybrid power aircraft has the following beneficial effects:

[0018] 1、By the left lower shell, the right lower shell and the upper shell in the form of the overall assembly to form the overall power shell, and in the bottom and top center position of the power shell are respectively provided with the upper air inlet cover and the lower air inlet cover, so that the resistance airflow can quickly enter the inside of the power shell through the upper air inlet and the lower air inlet during the flight of the aircraft, so that the airflow entering the inside of the power shell can quickly cool the power system inside the power shell, avoid the performance decline caused by overheating of the power system, and ensure that the power system can operate for a long time in the low temperature operation state.

[0019] And the two air outlets symmetrically arranged at the edge of the power shell facilitate the quick discharge of the cooled airflow entering the inside of the power shell, so as to reduce the air resistance of the power shell during flight by means of flow guiding and resistance reduction, and reduce the energy consumption of the aircraft during flight.

[0020] 2、By arranging the connecting wing plate and the special-shaped air deflector at the top edge position of the fuselage and the power shell, the resistance encountered by the aircraft during movement in the air can be further effectively reduced, the flight efficiency is improved, the fuel is saved, and the lift and wake shape of the aircraft are also optimized, which helps to improve the controllability of the aircraft, and the air inlet and outlet design of the upper air inlet, the lower air inlet and the air outlet further reduces the disturbance of the aircraft to the surrounding airflow, reduces the possibility of vortex and airflow separation, reduces environmental noise, and helps to improve the safety and controllability of the aircraft. BRIEF DESCRIPTION OF DRAWINGS

[0021] Figure 1 It is a structural schematic view of the utility model.

[0022] Figure 2 It is a structural schematic view of the lower air inlet cover of the utility model.

[0023] Figure 3 It is a structural schematic view of the air deflector interface seat of the utility model.

[0024] Figure 4 It is an explosion view of the power shell of the utility model.

[0025] In the drawing: 1, fuselage; 2, power shell; 201, left lower shell; 202, right lower shell; 203, upper shell;

[0026] 3, upper air inlet cover; 4, lower air inlet cover; 5, upper air inlet; 6, air deflector interface seat; 7, lower air inlet; 8, air outlet; 9, connecting wing plate; 10, special-shaped air deflector. DETAILED DESCRIPTION

[0027] Clearly, the described embodiments are merely a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments of the present application, all the other embodiments obtained by those skilled in the art without creative efforts under the premise that no creative efforts are made, belong to the scope of protection of the present application. Embodiments

[0028] Please refer to Figures 1-4 The present application provides the following technical scheme: a hybrid power aircraft fuel power shell structure, comprising a fuselage 1 and a power shell 2, one side of the fuselage 1 is connected with the power shell 2, the power shell 2 is composed of a lower left shell 201, a lower right shell 202 and an upper shell 203;

[0029] The lower left shell 201 and the lower right shell 202 are arranged in pairs in a center-symmetrical manner on the edge of the fuselage 1, the upper shell 203 is arranged at the top position of the lower left shell 201 and the lower right shell 202, and the end of the upper shell 203 is connected with the top position of the fuselage 1, the lower left shell 201, the lower right shell 202 and the upper shell 203 are assembled into an integral structure by welding, and the connection between the lower left shell 201, the lower right shell 202 and the upper shell 203 and the fuselage 1 is a smooth arc structure, facilitating the integral assembly of the lower left shell 201, the lower right shell 202 and the upper shell 203 to form the integral power shell 2;

[0030] The upper shell 203 is integrally formed with an upper air inlet cover 3 at the top middle end, the inner side bottom intersection position of the lower left shell 201 and the lower right shell 202 is connected with a lower air inlet cover 4, the inner side of the upper air inlet cover 3 and the top of the upper shell 203 form an upper air inlet 5, and the inner side of the top of the upper shell 203 is connected with two air guide interface seats 6 in a center-symmetrical manner at the inner side position of the upper air inlet cover 3.

[0031] The inside of the lower air inlet cover 4 is provided with a lower air inlet 7, the cross section of the upper air inlet cover 3 and the lower air inlet cover 4 is a conical horn structure, the air inlet direction of the upper air inlet 5 and the lower air inlet 7 extends to the inner side of the power shell 2, facilitating the rapid entry of the resistance airflow into the inner side of the power shell 2 through the upper air inlet 5 and the lower air inlet 7 during the flight of the aircraft, and the edge of the lower left shell 201 and the lower right shell 202 is provided with an air outlet 8, the air outlet 8 is arranged at the tail end of the lower left shell 201 and the lower right shell 202, and the air outlet direction of the air outlet 8 is at the same horizontal plane as the head of the fuselage 1, facilitating the rapid discharge of the airflow entering the power shell 2 and being cooled, so as to reduce the air resistance of the power shell 2 during flight by means of flow guiding and resistance reduction.

[0032] Two side edge ends of the upper shell 203 are connected with connecting wing plates 9, and the two side edge ends of the fuselage 1 are connected with special-shaped air deflectors 10 at positions corresponding to the connecting wing plates 9, the connecting wing plates 9 and the special-shaped air deflectors 10 form an overall streamlined structure, the inner sides of the connecting wing plates 9 and the special-shaped air deflectors 10 are provided with recesses, and the recesses and the side edges of the fuselage 1 form drag reduction grooves, so as to reduce the resistance encountered by the aircraft when moving in the air, improve the flight efficiency, save fuel, and also optimize the lift and wake shape of the aircraft.

[0033] The working principle and use process of the utility model are as follows: the left lower shell 201, the right lower shell 202 and the upper shell 203 form the overall power shell 2 in an overall assembly manner, and the power shell 2 is connected with the fuselage 1.

[0034] During the flight of the aircraft, the upper air inlet cover 3 and the lower air inlet cover 4 are arranged at the bottom and the top center positions of the power shell 2 respectively, so that the resistance airflow can quickly enter the inside of the power shell 2 through the upper air inlet 5 and the lower air inlet 7 when the aircraft is flying, and the airflow entering the inside of the power shell 2 can quickly cool the power system in the power shell 2, so as to avoid performance degradation of the power system due to overheating and ensure that the power system can fly for a long time in a low-temperature operation state.

[0035] At the same time, the two air outlets 8 arranged symmetrically at the edge of the power shell 2 are used to quickly discharge the airflow entering the inside of the power shell 2 and cooled, so as to reduce the air resistance of the power shell 2 during flight by means of flow guiding and resistance reduction, and also reduce the energy consumption of the aircraft during flight.

[0036] In addition, the connecting wing plates 9 and the special-shaped air deflectors 10 arranged at the top edge positions of the fuselage 1 and the power shell 2 can further effectively reduce the resistance encountered by the aircraft when moving in the air, improve the flight efficiency, save fuel, and also optimize the lift and wake shape of the aircraft, which is helpful to improve the controllability of the aircraft, and the air inlet and outlet design of the upper air inlet 5, the lower air inlet 7 and the air outlet 8 further reduces the disturbance of the aircraft to the surrounding airflow, reduces the possibility of vortex and airflow separation, reduces environmental noise, and also helps to improve the safety and controllability of the aircraft.

[0037] Finally, it should be noted that: the above only for the preferred embodiments of the present application, and is not intended to limit the present application, although the foregoing embodiments of the present application have been described in detail, for the skilled in the art, it still can be modified, or for the equivalent replacement of part of the technical features of the technical solutions recorded in the foregoing embodiments. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application, shall be included within the scope of the present application.

Claims

1. A hybrid power aircraft fuel power casing structure comprising a fuselage (1) and a power casing (2), characterized in that: The fuselage (1) is connected with a power shell (2), and the power shell (2) is composed of a left lower shell (201), a right lower shell (202) and an upper shell (203); The left lower shell (201) and the right lower shell (202) are symmetrically arranged on the side of the fuselage (1), and the upper shell (203) is arranged at the top of the left lower shell (201) and the right lower shell (202), and the end of the upper shell (203) is connected with the top of the fuselage (1); The top of the upper shell (203) is integrally formed with an upper air inlet cover (3), the inner bottom of the left lower shell (201) and the right lower shell (202) is connected with a lower air inlet cover (4), the inner side of the upper air inlet cover (3) and the top of the upper shell (203) form an upper air inlet (5), and the inner side of the top of the upper shell (203) is connected with two air guide interface seats (6) in a central symmetric manner. The inside of the lower air inlet cover (4) is provided with a lower air inlet (7), and the side of the left lower shell (201) and the right lower shell (202) is provided with an air outlet (8).

2. A hybrid power aircraft fuel power pod structure according to claim 1, wherein: The left lower shell (201), the right lower shell (202) and the upper shell (203) are assembled into an integral structure by welding, and the connection between the left lower shell (201), the right lower shell (202) and the upper shell (203) and the fuselage (1) is a smooth arc structure.

3. A hybrid power aircraft fuel power pod structure according to claim 1, wherein: The cross section of the upper air inlet cover (3) and the lower air inlet cover (4) is a conical horn structure, and the air inlet direction of the upper air inlet (5) and the lower air inlet (7) extends to the inside of the power shell (2).

4. A hybrid power aircraft fuel power pod structure according to claim 1, wherein: The air outlet (8) is arranged at the tail end of the left lower shell (201) and the right lower shell (202), and the air outlet direction of the air outlet (8) is on the same horizontal plane as the head of the fuselage (1).

5. A hybrid power aircraft fuel power pod structure according to claim 1, wherein: The upper shell (203) is connected with a connecting wing plate (9) on both sides, the fuselage (1) is connected with a special-shaped air deflector (10) corresponding to the connecting wing plate (9), and the connecting wing plate (9) and the special-shaped air deflector (10) form an integral streamlined structure.

6. A hybrid power aircraft fuel power pod structure according to claim 5, wherein: The inner side of the connecting wing plate (9) and the special-shaped air deflector (10) is provided with a recess, and the recess and the side of the fuselage (1) form a drag reduction groove.

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