A ring-wing layout early warning aircraft

Abstract

The application belongs to the field of aircraft design, and particularly relates to a ring-wing layout early warning aircraft. The ring-wing layout early warning aircraft comprises a fuselage (1), a ring-wing (2), an engine (3), a vertical stabilizer (4), a radar antenna cover (5) and a horizontal stabilizer (6). The vertical stabilizer (4) is arranged at the back of the fuselage (1), the radar antenna cover (5) is fixed above, the wing root (21) of the ring-wing (2) penetrates through the floor below the middle section (12) of the fuselage, is curved and extended outward and rearward to the wing middle section (22) located at the side of the middle section (12) of the fuselage, the wing middle section (22) is extended upward and rearward to the wing tip (23) located above the fuselage, and the wing tip is connected with the radar antenna cover above the fuselage. The application improves the aerodynamic characteristics and cruising efficiency of the early warning aircraft, optimizes the aircraft structure, reduces the structure weight, effectively shields the strong infrared signal radiated by the engine, and comprehensively enhances the combat effectiveness of the early warning aircraft.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of aircraft design, and particularly relates to a ring-wing layout early warning aircraft. BACKGROUND

[0002] The early warning aircraft, also known as an airborne early warning command aircraft, is an airborne support aircraft provided with an airborne electronic system such as a search radar, an identification of friend or foe, a communication navigation, a command control and an electronic countermeasure, and is used for searching, monitoring and tracking air and sea targets, and commanding and guiding own aircraft to perform various combat tasks. The existing early warning aircraft, such as the E-3 of the United States, the E-767 of Japan and the A-100 of Russia, is mainly modified from a civil or military large transport aircraft, and adopts the following aerodynamic layout form, i.e. a cylindrical fuselage, a backward swept trapezoidal wing, a wing-mounted engine, a rear horizontal and vertical stabilizer / control surface, a support rod above the fuselage and a radar antenna cover. The biggest feature of these aircrafts is that the technology is mature, and the development cycle is relatively short, but there are the following disadvantages and shortcomings in modern war. Figure 1

[0003] Firstly, the backward swept trapezoidal wing cannot have a too large aspect ratio due to the influence of structural weight, wing stiffness and other factors, so that the induced drag cannot be further reduced, the aerodynamic efficiency of the aircraft cannot be further improved, and the mission radius and loiter time of the early warning aircraft are directly limited.

[0004] Secondly, the wing-mounted engine is easy to suck in the debris and other sundries on the airport runway during the take-off and landing stage, and the infrared signal is obvious during the air mission stage, so that the aircraft is easy to be attacked by enemy ground and air fire.

[0005] Thirdly, the support rod of the radar antenna cover above the fuselage not only directly increases the structural weight and frictional resistance of the whole aircraft, but also needs to pay a weight cost to strengthen the structure frame at the connection position of the fuselage.

[0006] Fourthly, the airflow disturbance caused by the radar antenna cover on the support rod has an adverse effect on the rear vertical tail, so that the longitudinal stability and control surface efficiency are reduced, and the heading stability of the aircraft is deteriorated. SUMMARY

[0007] In order to solve at least one of the above technical problems, the present application designs an early warning aircraft with a ring-wing layout, so as to improve the cruising efficiency, reduce the structural weight, improve the flight quality, increase the mission safety, and further improve the comprehensive combat effectiveness of the early warning aircraft.

[0008] The early warning aircraft with a ring-wing layout provided by the present application mainly comprises a fuselage, and the fuselage comprises a front segment, a middle segment and a rear segment, wherein the early warning aircraft with a ring-wing layout further comprises a ring wing, an engine, a vertical stabilizer, a radar antenna cover and a horizontal stabilizer.

[0009] ​The vertical stabilizer is arranged at the back of the fuselage, the radar radome is fixed above the vertical stabilizer, the engines are arranged at the upper middle part of the rear section of the fuselage, and the horizontal stabilizer is arranged behind the engines.

[0010] The annular wing comprises a wing root, a wing middle section and a wing tip, the wing root penetrates through the floor of the middle section of the fuselage, extends outward and rearward to the wing middle section beside the middle section of the fuselage, the wing middle section extends upward and rearward to the wing tip above the fuselage, and the wing tips on both sides of the annular wing are connected with the radar radome above the fuselage.

[0011] Preferably, the vertical stabilizer has a through hole extending from the back of the fuselage to the inside of the radar radome, which is used for passing the cable of the radar antenna.

[0012] Preferably, the wing tips of the annular wing are rigidly connected with the bottom end surface of the radar radome.

[0013] Preferably, the engines are supported by supports at the upper middle part of the rear section of the fuselage, the left and right engines are symmetrical relative to the fuselage, the engines are partially blocked by the wing middle section of the annular wing on both sides of the fuselage, and the engines are partially blocked by the wing tips of the annular wing above the fuselage.

[0014] Preferably, the horizontal stabilizer is located below and behind the jet port of the engine.

[0015] Preferably, the annular wing has a wing leading edge and a wing trailing edge, the sweepback angle of the wing leading edge is set to be between 10° and 35°, the sweepback angle of the wing trailing edge is set to be between 5° and 20°, the chord length of the wing root is large, the chord length of the wing tip is small, and the tip-to-root ratio is between 0.2 and 0.5.

[0016] Preferably, the aspect ratio of the annular wing on either side of the fuselage is not less than 15, and the aspect ratio is defined as the square of the spread length of the trapezoidal wing after being spread in the horizontal plane divided by the area of the trapezoidal wing.

[0017] Preferably, the main landing gear of the aircraft is connected to the annular wing through a main landing gear support column, the wing root of the annular wing of the aircraft adopts an airfoil with a relative thickness greater than 0.18, and a space for accommodating the main landing gear is arranged inside.

[0018] The advantages of the present application include:

[0019] (1) The proposed ring-wing layout early warning aircraft of the present application can greatly improve the wing aspect ratio, reduce the induced drag during cruising, and will not cause problems such as dramatic increase in structural weight and deterioration of wing stiffness, thereby improving the cruising efficiency and structural efficiency of the early warning aircraft. At the same time, the ring-wing layout reduces the spanwise size of the early warning aircraft, and reduces the requirement for the geometric space of the parking apron and hangar when the aircraft is parked.

[0020] (2) The proposed ring-wing layout early warning aircraft of the present application has the engine supported and installed on the rear section of the fuselage through the nacelle, which is shielded and protected by the ring-wing above, below and on both sides. During the take-off and landing stage of the aircraft, the engine can avoid inhaling foreign matter on the runway, and during the execution of the task in the air, the engine can shield the strong infrared signal emitted by the engine, greatly reducing the probability of being discovered, identified, tracked and attacked by the enemy, and improving the survivability of the aircraft. At the same time, the jet flow of the engine can increase the lift of the horizontal stabilizer / control surface below, improving its control efficiency.

[0021] (3) The proposed ring-wing layout early warning aircraft of the present application has the radar antenna cover supported on the upper back of the fuselage through the vertical stabilizer / control surface and the wing tips of the ring-wing. Compared with the typical early warning aircrafts (such as E-3, E-767, A-100), on the one hand, the radar antenna cover support structure is omitted, effectively reducing the overall structural weight, and on the other hand, the adverse effects of the airflow disturbance caused by the radar antenna cover on the rear vertical tail are completely avoided. BRIEF DESCRIPTION OF DRAWINGS

[0022] Figure 1 is a schematic diagram of the aerodynamic layout of the existing early warning aircraft.

[0023] Figure 2 is a three-dimensional view of the aerodynamic layout of the early warning aircraft with ring-wing layout according to a preferred embodiment of the present application.

[0024] Figure 3 is a top view of the aerodynamic layout of the early warning aircraft with ring-wing layout according to the embodiment shown in the present application. Figure 1

[0025] Figure 4 is a side view of the aerodynamic layout of the early warning aircraft with ring-wing layout according to the embodiment shown in the present application. Figure 1

[0026] Figure 5 is a front view of the aerodynamic layout of the early warning aircraft with ring-wing layout according to the embodiment shown in the present application. Figure 1

[0027] ​​​Wherein, 1 - fuselage, 11 - fuselage front section, 12 - fuselage middle section, 13 - fuselage rear section, 2 - annular wing, 21 - wing root, 22 - wing middle section, 23 - wing tip, 24 - wing leading edge, 25 - wing trailing edge, 3 - engine, 31 - support, 4 - vertical stabilizer, 5 - radar radome, 51 - side wall, 6 - horizontal stabilizer. DETAILED DESCRIPTION

[0028] For the purpose, technical solutions and advantages of the embodiments of the present application, the technical solutions in the embodiments of the present application will be described in more detail below. In the drawings, the same or similar reference signs represent the same or similar elements or elements with the same or similar functions throughout. The described embodiments are part of the embodiments of the present application, not all of the embodiments. The embodiments described below by reference to the drawings are exemplary and are intended to explain the present application, and cannot be understood as limiting the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application. The embodiments of the present application will be described in detail below with reference to the drawings.

[0029] The present application provides a ring wing layout early warning aircraft, as shown in the drawings, comprising a fuselage 1, the fuselage comprises a fuselage front section 11, a fuselage middle section 12 and a fuselage rear section 13, characterized in that the ring wing layout early warning aircraft further comprises an annular wing 2, an engine 3, a vertical stabilizer 4, a radar radome 5 and a horizontal stabilizer 6. Figures 2-5

[0030] Wherein, the vertical stabilizer 4 is arranged at the back of the fuselage 1, the radar radome 5 is fixed above the vertical stabilizer 4, the engine 3 is arranged at the upper part of the fuselage rear section 13 on both sides, and the horizontal stabilizer 6 is arranged behind the engine.

[0031] The annular wing 2 comprises a wing root 21, a wing middle section 22 and a wing tip 23, the wing root 21 penetrates from the floor of the fuselage middle section 12, extends outwardly and rearwardly to the wing middle section 22 beside the fuselage middle section 12, the wing middle section 22 extends upwardly and rearwardly to the wing tip 23 above the fuselage, and the wing tips 23 on both sides of the aircraft are connected with the radar radome 5 above the fuselage.

[0032] The vertical stabilizer 4 and the horizontal stabilizer 6 of the present application are both control surfaces, and the control of the attitude of the aircraft can be realized by controlling the angle thereof. The radar radome of the present application is supported above the back of the fuselage by the vertical stabilizer 4 and the wing tips at both ends of the annular wing 5. Compared with the typical early warning aircraft, on the one hand, the support structure of the radar radome is saved, which effectively reduces the overall structure weight, and on the other hand, the adverse effects of the airflow disturbance caused by the radar radome on the rear vertical tail are completely avoided.​

[0033] In some optional embodiments, the vertical stabilizer 4 has a through hole extending from the back of the fuselage to the inside of the radar dome 5, through which the cable of the radar antenna can pass. In this embodiment, the vertical stabilizer 4 bears the main weight of the radar dome and the radar antenna inside it.

[0034] In some optional embodiments, the wing tips 23 of the ring wing 2 are rigidly connected to the two sides of the bottom end face of the radar dome 5, serving as load bearing and bending resistance, and improving the load distribution at the wing tip. On the other hand, the wing tips 23 of the ring wing 2 are connected to the radar dome 5 at the bottom end of the radar dome 5, and the side walls 51 of the radar dome 5 do not block the radar dome 5 in the horizontal plane 360 degrees, improving the detection capability of the radar dome 5.

[0035] In some optional embodiments, the engines 3 are supported by the brackets 31 on the middle and upper part of the rear section 13 of the fuselage, and the left and right engines 3 are symmetrical relative to the fuselage. The engines 3 are partially blocked by the middle section 22 of the ring wing 2 on both sides of the fuselage, and the engines 3 are partially blocked by the wing tips 23 of the ring wing 2 above the fuselage. In addition, during the high-altitude flight of the aircraft, the wing roots 21 of the ring wing 2 can also block part of the engines 3 when the radar detects from the front and upward.

[0036] In this embodiment, the engines are supported and installed on the rear section of the fuselage through the nacelle, which is protected by the ring wing above, below and on both sides. During the take-off and landing stage of the aircraft, it can avoid the engine sucking foreign objects on the runway, and during the task in the air, it can block the strong infrared signal emitted by the engine, greatly reducing the probability of being discovered, identified, tracked and attacked by the enemy, and improving the survivability of the aircraft. At the same time, the jet flow of the engine can increase the lift of the horizontal stabilizer / control surface below, improving its control efficiency.

[0037] In some optional embodiments, the horizontal stabilizer 6 is located below and behind the jet port of the engine 3. The hot jet flow emitted by the engine can act on the horizontal stabilizer / control surface, producing boundary layer and circulation control effects, improving the aerodynamic efficiency of the horizontal stabilizer 6.

[0038] In some optional embodiments, the ring wing 2 has a wing leading edge 24 and a wing trailing edge 25, the sweep angle of the wing leading edge 24 is set between 10° and 35°, and the sweep angle of the wing trailing edge is set between 5° and 20°. The chord length of the wing root 21 is large, the chord length of the wing tip 23 is small, and the tip-to-root ratio is between 0.2 and 0.5.

[0039] In some alternative embodiments, the aspect ratio of the annular wing 2 on either side of the fuselage is not less than 15, which is defined as the ratio of the square of the span of the trapezoidal wing after being spread in the horizontal plane to the area of the trapezoidal wing.

[0040] In this embodiment, the aspect ratio of the annular wing can be greatly improved by using the annular wing, the induced drag during cruising is reduced, and the problems such as dramatic increase in structural weight and poor wing stiffness are not caused, thereby improving the cruising efficiency and structural efficiency of the early warning aircraft; at the same time, the spanwise size of the early warning aircraft is reduced by using the annular wing, and the requirement for the geometric space of the parking apron and hangar when the aircraft is parked in the airport is reduced

[0041] In some alternative embodiments, the main landing gear of the aircraft is connected to the annular wing 2 through a main landing gear strut, the wing root 21 of the annular wing 2 of the aircraft adopts an airfoil with a relative thickness exceeding 0.18, and the intersection of the wing root 21 and the fuselage is fairing, and a space for accommodating the main landing gear is provided inside.

[0042] The above is only a specific embodiment of the present application, but the protection scope of the present application is not limited to this, any person skilled in the art can easily think of changes or replacements within the technical range disclosed in the present application, which should be covered in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A ring-wing layout early warning aircraft, comprising a fuselage (1) including a front fuselage section (11), a middle fuselage section (12) and a rear fuselage section (13), characterized in that, The early warning aircraft of the annular wing layout further comprises an annular wing (2), an engine (3), a vertical stabilizer (4), a radar antenna cover (5) and a horizontal stabilizer (6); The vertical stabilizer (4) is arranged at the back of the fuselage (1), the radar antenna cover (5) is fixed above the vertical stabilizer (4), the engine (3) is arranged at the upper middle part of the rear section (13) of the fuselage, and the horizontal stabilizer (6) is arranged behind the engine. The annular wing (2) comprises a wing root (21), a wing middle section (22) and a wing tip (23), the wing root (21) penetrates through the floor of the middle section (12) of the fuselage, extends outward and backward to the wing middle section (22) beside the middle section (12) of the fuselage, the wing middle section (22) extends upward and backward to the wing tip (23) above the fuselage, and the wing tips (23) on both sides of the aircraft are connected with the radar antenna cover (5) above the fuselage. The engine (3) is supported on the middle upper part of the rear section (13) of the fuselage by a support (31), the left and right engines (3) are symmetrical relative to the fuselage, the engine (3) is partially blocked by the wing middle section (22) of the annular wing (2) on both sides of the fuselage, and the engine (3) is partially blocked by the wing tip (23) of the annular wing (2) above the fuselage.

2. The ring-wing layout early warning aircraft of claim 1, wherein, The vertical stabilizer (4) has a through hole extending from the back of the fuselage to the inside of the radar antenna cover (5) to pass the cable of the radar antenna.

3. The ring-wing layout early warning aircraft of claim 1, wherein, The wing tip (23) of the annular wing (2) is rigidly connected with the bottom end face of the radar antenna cover (5) on both sides.

4. The ring-wing layout early warning aircraft of claim 1, wherein, The horizontal stabilizer (6) is located below and behind the jet port of the engine (3).

5. The ring-wing layout early warning aircraft of claim 1, wherein, The annular wing (2) has a wing leading edge (24) and a wing trailing edge (25), the sweepback angle of the wing leading edge (24) is arranged to be between 10° and 35°, the sweepback angle of the wing trailing edge is arranged to be between 5° and 20°, the chord length of the wing root (21) is large, the chord length of the wing tip (23) is small, and the tip-to-root ratio is between 0.2 and 0.

5.

6. The ring-wing layout early warning aircraft of claim 5, wherein, The aspect ratio of the annular wing (2) on either side of the fuselage is not less than 15, and the aspect ratio is defined as the square of the spread length of the trapezoidal wing after being spread in the horizontal plane to the area of the trapezoidal wing.

7. The ring-wing layout early warning aircraft of claim 5, wherein, The wing root (21) of the annular wing (2) of the aircraft adopts an airfoil with a relative thickness of more than 0.18, and a space for accommodating the main landing gear is arranged inside.

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