Aircraft power device with wing body fusion layout and control method of aircraft power device

Abstract

The invention belongs to the field of wing body fusion layout aircraft power devices and control methods thereof, and particularly relates to a wing body fusion layout aircraft power device and a control method thereof. A built-in engine is arranged on the inner side of the rear portion of an aircraft body, and an external engine is arranged on the outer side of the rear portion of an aircraft; the built-in engine and the external engine jointly provide thrust for takeoff of the aircraft, only the external engine provides thrust for cruising of the aircraft during cruising of the aircraft, takeoff performance of the aircraft can be improved on the premise that the weight of the aircraft is not remarkably increased, and cruising resistance of the aircraft is guaranteed through the design of an air inlet channel, an air outlet channel, an air inlet cover and an air outlet cover of the built-in engine. The increase of the cruise resistance of the aircraft is avoided, so that the condition that the cruise performance and take-off performance of the aircraft are not coordinated with each other in the wing body fusion layout can be well balanced.

Description

Technical Field

[0001] The present application belongs to the field of wing-body fusion layout aircraft power unit and control method thereof, and specifically relates to a wing-body fusion layout aircraft power unit and control method thereof. Background Art

[0002] The aircraft wing-body fusion layout refers to the full lift surface aerodynamic shape with highly integrated wings and fuselage. Under the same loading requirements, the wing-body fusion layout can reduce the aircraft's wetted area and reduce the friction resistance of the aircraft's flight. Compared with the conventional wing and fuselage layout, the cruise efficiency of the wing-body fusion layout can be increased by 15% to 20%.

[0003] The longitudinal dimension of the aircraft's wing-body blended layout is relatively short, and the longitudinal balancing capability is limited, which limits the use of the high lift system. In addition, the wing-body blended layout aircraft has a small cruising resistance and often adopts an overall parameter design with a small thrust-to-weight ratio, which often results in insufficient take-off performance.

[0004] Comprehensive analysis shows that the existing wing-body fusion layout aircraft scheme has inconsistent data. The wing-body fusion layout of the aircraft has a high cruise aerodynamic efficiency, and a relatively small thrust engine can meet the cruise flight requirements, but the take-off performance is insufficient, and a relatively large thrust engine is required to meet the take-off field length requirements. If the design increases the cruising altitude to reduce the wing load, or increases the longitudinal trim capability by lengthening the rear fuselage to enhance the aircraft's take-off performance, new problems will be introduced.

[0005] This application is proposed in view of the above-mentioned technical defects. Summary of the invention

[0006] The purpose of the present application is to provide a wing-body fusion layout aircraft power unit and a control method thereof, so as to overcome or alleviate at least one of the known technical defects.

[0007] The technical solution of this application is: On the one hand, a power plant of a wing-body fusion layout aircraft is provided, comprising: an internal engine and an external engine; The built-in engine is arranged on the inner side of the rear part of the machine body, and is provided with an air intake duct and an exhaust duct, wherein the air intake duct inlet is opened on the back of the rear part of the machine body, and the exhaust duct outlet is opened at the tail end of the machine body, and an air intake duct inlet cover is arranged at the air intake duct inlet, and an exhaust duct outlet cover is arranged at the exhaust duct outlet; When the air inlet cover and the exhaust cover are closed, they are integrated with the external curved surface of the fuselage; There are two outboard engines, set outside the rear of the aircraft; The power unit of the wing-body fusion layout aircraft has a take-off working state and a cruising working state; When the power unit of the wing-body fusion layout aircraft is in the take-off working state, the air inlet cover and the exhaust cover are opened, and the internal engine and the external engine are working; When the power unit of a wing-body fusion aircraft is in cruising mode, the air intake cover and exhaust cover are closed, the internal engine is shut down, and the external engine is working.

[0008] Optionally, in the above-mentioned wing-body fusion layout aircraft power unit, the air inlet cover and the exhaust cover are driven by an actuator to be opened or closed.

[0009] Optionally, in the above-mentioned wing-body fusion layout aircraft power unit, the built-in engine adopts a large-thrust, small-sized engine.

[0010] Optionally, in the above-mentioned wing-body fusion layout aircraft power unit, the external engine adopts a wing-mounted engine.

[0011] Optionally, in the above-mentioned wing-body fusion layout aircraft power unit, the external engine adopts a backpack engine.

[0012] On the other hand, a method for controlling a power plant of a wing-body fusion aircraft is provided, which is used to control the power plant of the wing-body fusion aircraft, comprising: When the aircraft takes off, the power unit of the aircraft with wing-body fusion layout is in the take-off working state; When the aircraft is cruising, the power unit of the aircraft with a wing-body blended layout is in cruising working state.

[0013] Optionally, in the above-mentioned method for controlling a power unit of an aircraft with a wing-body layout, an air inlet cover and an exhaust cover of an aircraft with a wing-body layout are driven by an actuator to be opened or closed.

[0014] Optionally, in the above-mentioned method for controlling a power unit of an aircraft with a wing-body blended layout, a large-thrust, small-sized engine is used as a built-in engine in the design of the power unit of an aircraft with a wing-body blended layout.

[0015] Optionally, in the above-mentioned method for controlling a power unit of an aircraft with a wing-body blended layout, in designing a power unit of an aircraft with a wing-body blended layout, a wing-mounted engine is used as an external engine.

[0016] Optionally, in the above-mentioned method for controlling a power unit of an aircraft with a wing-body blended layout, in designing a power unit of an aircraft with a wing-body blended layout, a backpack engine is used as an external engine.

[0017] This application has at least the following beneficial technical effects: Provided is a power unit for a wing-body fusion layout aircraft and a control method thereof, wherein an internal engine is arranged on the inner side of the rear portion of a fuselage, and an external engine is arranged on the outer side of the rear portion of the aircraft. When the aircraft takes off, the internal engine and the external engine jointly provide thrust for the aircraft to take off, and when the aircraft is cruising, only the external engine provides thrust for the aircraft to cruise. The take-off performance of the aircraft can be improved without significantly increasing the weight of the aircraft. Furthermore, by designing an air inlet duct, an exhaust duct, an air inlet cover, and an exhaust cover of the internal engine, the cruising resistance of the aircraft is ensured and an increase in the cruising resistance of the aircraft is avoided, thereby being able to well balance the uncoordinated cruising performance and take-off performance of the wing-body fusion layout aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 is a top view of a power plant of an aircraft with a wing-body fusion layout provided in an embodiment of the present application; Figure 2 is a side view of a power plant of an aircraft with a wing-body fusion layout provided in an embodiment of the present application; in: 1-Internal engine; 2-External engine; 3-Intake cover; 4-Exhaust cover.

[0019] In order to better illustrate the present embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be construed as limitations on the present application. DETAILED DESCRIPTION

[0020] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0021] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application indicates that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0022] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable 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. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0023] A power plant for an aircraft with a wing-body fusion layout, such as Figure 1 As shown, it includes an internal engine 1 and an external engine 2.

[0024] The built-in engine 1 is arranged on the inner side of the rear part of the machine body, and is equipped with an air intake duct and an exhaust duct, wherein the air intake duct inlet is opened on the back of the rear part of the machine body, and the exhaust duct outlet is opened at the tail end of the machine body, and an air intake cover 3 is arranged at the air intake duct inlet, and an exhaust cover 4 is arranged at the exhaust duct outlet. The air intake cover 3 and the exhaust cover 4 are driven by an actuator to open or close. When the air intake cover 3 and the exhaust cover 4 are closed, they are integrated with the external curved surface of the machine body.

[0025] The internal engine 1 can adopt a large thrust and small size engine to avoid a significant increase in the weight of the aircraft. The fuel consumption rate is not required, and the thrust of the take-off state is designed to meet the capacity requirements of the aircraft take-off field length.

[0026] There are multiple built-in engines 1 and their corresponding air inlet ducts, exhaust ducts, air inlet covers 3 and exhaust cover 4, which are symmetrically distributed on the inner side of the rear part of the machine body with the machine body axis as the symmetry axis.

[0027] There are two external engines 2, which are arranged on the outside of the rear of the aircraft. Wing-mounted engines or backpack engines can be used. They are designed to have a low fuel consumption rate in cruising state, and the thrust in cruising state meets the requirements of the aircraft's cruising flight.

[0028] There are multiple pairs of external engines 2, which are arranged at the rear of the aircraft with the fuselage axis as the axis of symmetry.

[0029] The power unit of the wing-body fusion layout aircraft has take-off working state and cruising working state.

[0030] When the power unit of the wing-body fusion layout aircraft is in the take-off working state, the air inlet cover 3 and the exhaust cover 4 are opened, and the internal engine 1 and the external engine 2 are working.

[0031] When the power unit of the wing-body fusion layout aircraft is in a cruising state, the air inlet cover 3 and the exhaust cover 4 are closed, the internal engine 1 is shut down, and the external engine 2 is working.

[0032] A method for controlling a power plant of a wing-body fusion aircraft, for controlling the power plant of the wing-body fusion aircraft disclosed in the above embodiment, comprises: When the aircraft takes off, the power unit of the wing-body fusion layout aircraft is set to be in the take-off working state. In addition, the internal engine 1 and the external engine 2 work at the same time to jointly provide thrust for the aircraft to take off. The internal engine 1 and the external engine 2 can operate at the maximum state to generate a large thrust to make up for the problem of insufficient take-off performance of the wing-body fusion layout aircraft; When the aircraft is cruising, the power unit of the wing-body fusion layout aircraft is in the cruising working state. At this time, the internal engine 1 is shut down and only the external engine 2 works to provide thrust for the aircraft cruising. The air inlet cover 3 and the exhaust cover 4 are closed and integrated with the external curved surface of the fuselage, which will not increase the cruising resistance of the aircraft.

[0033] In the power unit and control method of the wing-body fusion layout aircraft disclosed in the above-mentioned embodiment, an internal engine 1 is arranged on the inner side of the rear part of the fuselage, and an external engine 2 is arranged on the outer side of the rear part of the aircraft. When the aircraft takes off, the internal engine 1 and the external engine 2 jointly provide thrust for the aircraft to take off. When the aircraft is cruising, only the external engine 2 provides thrust for the aircraft to cruise. The take-off performance of the aircraft can be improved without significantly increasing the weight of the aircraft. The design of the air intake duct, exhaust duct, air intake cover 3 and exhaust cover 4 of the internal engine 1 can ensure the cruising resistance of the aircraft and avoid an increase in the cruising resistance of the aircraft. This can well balance the incoordination between the cruising performance and the take-off performance of the wing-body fusion layout aircraft.

[0034] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. A wing-body fusion layout aircraft power plant, characterized in that: include: Internal engine (1), external engine (2); The built-in engine (1) is arranged on the inner side of the rear part of the machine body and is provided with an air intake duct and an exhaust duct, wherein the air intake duct inlet is opened on the back of the rear part of the machine body, the exhaust duct outlet is opened at the tail end of the machine body, and the air intake duct inlet is provided with an air intake duct cover (3), and the exhaust duct outlet is provided with an exhaust duct cover (4); When the air inlet cover (3) and the air outlet cover (4) are closed, they are integrated with the outer curved surface of the machine body; There are two outboard engines (2), which are arranged outside the rear of the aircraft; The power unit of the wing-body fusion layout aircraft has a take-off working state and a cruising working state; When the power unit of the wing-body fusion aircraft is in a take-off working state, the air inlet cover (3) and the exhaust cover (4) are opened, and the internal engine (1) and the external engine (2) are in operation; When the power unit of the wing-body fusion aircraft is in a cruising state, the air inlet cover (3) and the exhaust cover (4) are closed, the internal engine (1) is shut down, and the external engine (2) is in operation.

2. The wing-body fusion layout aircraft power plant according to claim 1, characterized in that: The air inlet cover (3) and the air outlet cover (4) are driven by an actuator to be opened or closed.

3. The wing-body fusion layout aircraft power plant according to claim 1, characterized in that: The built-in engine (1) is a high-thrust, small-sized engine.

4. The wing-body fusion layout aircraft power plant according to claim 1, characterized in that: The external engine (2) is a wing-mounted engine.

5. The wing-body fusion layout aircraft power plant according to claim 1, characterized in that: The external engine (2) is a backpack engine.

6. A method for controlling a power plant of a wing-body fusion aircraft, for controlling the power plant of a wing-body fusion aircraft according to claim 1, characterized in that: include: When the aircraft takes off, the power unit of the aircraft with wing-body fusion layout is in the take-off working state; When the aircraft is cruising, the power unit of the aircraft with a wing-body blended layout is in cruising working state.

7. The method for controlling a power plant of a wing-body fusion aircraft according to claim 6, characterized in that: In a power unit of an aircraft with a wing-body fusion layout, an air inlet cover (3) and an exhaust cover (4) are driven by an actuator to be opened or closed.

8. The method for controlling a power plant of a wing-body fusion aircraft according to claim 6, characterized in that: In designing a power unit for an aircraft with a wing-body fusion layout, the built-in engine (1) is a large-thrust, small-sized engine.

9. The method for controlling a power plant of a wing-body fusion aircraft according to claim 6, characterized in that: In designing a power plant for an aircraft with a wing-body blended layout, the external engine (2) is a wing-mounted engine.

10. The method for controlling a power plant of a wing-body fusion aircraft according to claim 6, characterized in that: In designing a power plant for an aircraft with a wing-body blended layout, the external engine (2) is a backpack engine.

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