Tilt rotor aircraft

Abstract

The invention belongs to the technical field of aircraft design, and relates to a tilt-rotor aircraft. The tilt-rotor aircraft comprises a fuselage (1), wings (2), an empennage (3), an undercarriage and a power device, the power device comprises a front engine system (4) and a rear engine system (5), the front engine system (4) comprises a front engine (9) and a front engine propeller (10), the rear engine system (5) comprises a rear engine (11) and a rear engine propeller (12), the front engine system (4) is hinged to the head of the aircraft, and the rear engine system (5) is hinged to the tail of the aircraft; the tilt rotor aircraft has a vertical take-off and landing state and a high-speed flight state, in the vertical take-off and landing state, the rotating planes of the front propeller (10) and the rear propeller (12) are parallel to the horizontal plane of the aircraft body, and in the high-speed flight state, the rotating planes of the front propeller (10) and the rear propeller (12) are perpendicular to the horizontal plane of the aircraft body. According to the tilt-rotor aircraft, the aerodynamic force interference of the rotor wings of the tilt-rotor aircraft to the wings is reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft design, and in particular to a tilt-rotor aircraft. Background Art

[0002] As a high-speed, long-distance means of transportation, airplanes play an irreplaceable role in modern military and civilian fields. According to the flight mode of the aircraft, aircraft can usually be divided into fixed-wing aircraft and rotary-wing aircraft. Fixed-wing aircraft refers to aircraft whose wings are relatively fixed to the fuselage, such as the Boeing 737 and F-15. Rotary-wing aircraft refers to aircraft whose wing surfaces that generate lift rotate relative to the fuselage, such as the "Black Hawk" and "Apache".

[0003] Fixed-wing aircraft and rotary-wing aircraft have their own characteristics in terms of usage and mission capabilities. Fixed-wing aircraft require a longer runway for takeoff and landing, have a fast flying speed in the air, have a strong loading capacity, and have a long range. Rotary-wing aircraft only need a flat ground for takeoff and landing, have a relatively slow flying speed in the air, have a relatively weak loading capacity, and have a relatively short range.

[0004] Engineers have attempted to combine the advantages of fixed-wing aircraft and rotary-wing aircraft, but such aircraft have the following problems.

[0005] The first is the aerodynamic interference between the rotor and wing of this aircraft. During high-speed flight, the two huge propellers cover the front of the wing, and the aerodynamic forces on the rotor and the fixed wing interfere with each other, increasing the difficulty of aircraft aerodynamic design and flight mechanics processing, and reducing flight safety.

[0006] Secondly, the aircraft has too large a windward area during high-speed flight. In order to achieve vertical takeoff and landing, the aircraft uses two huge propeller discs. During high-speed flight, the two propeller discs are perpendicular to the flight direction, which greatly increases the aircraft's windward area and limits the aircraft's maximum speed. Summary of the invention

[0007] In order to solve the above problems, the present application provides a tilt-rotor aircraft to reduce the aerodynamic interference between the rotor and the wing of the aircraft.

[0008] The tilt-rotor aircraft provided in this application mainly includes:

[0009] A fuselage, wings, tail, landing gear and power unit, wherein the power unit includes a front engine system and a rear engine system, the front engine system includes a front engine and a front engine propeller driven by the front engine, the rear engine system includes a rear engine and a rear engine propeller driven by the rear engine, the front engine system is hinged to the head of the aircraft, and the rear engine system is hinged to the tail of the aircraft;

[0010] The tilt-rotor aircraft has a vertical take-off and landing state and a high-speed flight state. In the vertical take-off and landing state, the front launch system and the rear launch system are both tilted upward, so that the rotation planes of the front launch propeller and the rear launch propeller are parallel to the horizontal plane of the fuselage. In the high-speed flight state, the front launch system and the rear launch system are both tilted downward, so that the rotation planes of the front launch propeller and the rear launch propeller are perpendicular to the horizontal plane of the fuselage.

[0011] Preferably, the front propeller and the rear propeller overlap on the projection plane of the speed axis of the aircraft.

[0012] Preferably, in the vertical take-off and landing state, the rear propeller thrust is vertically upward; during high-speed flight, the rear propeller thrust is horizontally forward, and directional control is achieved by adjusting the pitch angle of the propeller blades.

[0013] Preferably, the output power of the front engine and the rear engine is the same or different.

[0014] Preferably, the pulling force of the front propeller and the rear propeller is the same or different.

[0015] The present application reduces the aerodynamic interference of the rotor of the tilt-rotor aircraft on the wing by adjusting the position of the engine, thereby increasing the safety of flight. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is an axial view of a preferred embodiment of the tilt-rotor aircraft of the present application in a vertical take-off and landing state.

[0017] Figure 2 It is an axial view of a preferred embodiment of the tilt-rotor aircraft of the present application in high-speed flight state.

[0018] Among them, 1-fuselage, 2-wing, 3-tail, 4-front engine system, 5-rear engine system, 9-front engine, 10-front engine propeller, 11-rear engine, 12-rear engine propeller. DETAILED DESCRIPTION

[0019] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the implementation of this application will be described in more detail in combination with the drawings in the implementation of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and cannot be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in combination with the drawings.

[0020] The present application provides a tilt-rotor aircraft, such as Figure 1 and Figure 2 As shown, it mainly includes a fuselage 1, wings 2, tail 3, landing gear and a power device, wherein the power device includes a front engine system 4 and a rear engine system 5, the front engine system 4 includes a front engine 9 and a front engine propeller 10 driven by the front engine 9, the rear engine system 5 includes a rear engine 11 and a rear engine propeller 12 driven by the rear engine 11, the front engine system 4 is hinged at the head of the aircraft, and the rear engine system 5 is hinged at the tail of the aircraft;

[0021] The tilt-rotor aircraft has a vertical take-off and landing state and a high-speed flight state. In the vertical take-off and landing state, the front launch system 4 and the rear launch system 5 are both tilted upward, so that the rotation planes of the front launch propeller 10 and the rear launch propeller 12 are parallel to the horizontal plane of the fuselage. In the high-speed flight state, the front launch system 4 and the rear launch system 5 are both tilted downward, so that the rotation planes of the front launch propeller 10 and the rear launch propeller 12 are perpendicular to the horizontal plane of the fuselage.

[0022] refer to Figure 1 In the vertical take-off and landing state, the propeller disks of the two propellers are parallel to the ground, and the gravity of the aircraft is balanced by the pulling force of the two propellers to achieve vertical take-off and landing operations. Figure 2 In high-speed flight, the propeller disks of the two propellers are perpendicular to the horizontal plane of the fuselage. The drag of the aircraft is balanced by the pull of the propellers, thus achieving high-speed flight operation of the aircraft.

[0023] In some optional embodiments, the front propeller 10 and the rear propeller 12 overlap on the plane of the aircraft's speed axis projection. In this embodiment, the front propeller 10 and the rear propeller 12 basically overlap on the plane of the aircraft's speed axis projection, reducing the windward area of ​​the entire aircraft, laying a foundation for improving high-speed flight capabilities.

[0024] In some optional embodiments, in the vertical take-off and landing state, the pulling force of the rear propeller 12 is vertically upward; in the high-speed flight process, the pulling force of the rear propeller 12 is horizontally forward, and the direction control is achieved by adjusting the pitch angle of the propeller blades.

[0025] In some optional embodiments, the output power of the front engine 9 and the rear engine 11 are the same or different.

[0026] In some optional embodiments, the pulling force of the front propeller 10 and the rear propeller 12 are the same or different.

[0027] In the above two embodiments, during take-off and landing, the engine power of the front engine 9 and the rear engine 11 are not required to be the same, nor are the thrusts of the two propellers required to be the same; during high-speed flight, the engine power of the front engine 9 and the rear engine 11 are not required to be the same, nor are the thrusts of the two propellers required to be the same. This embodiment reduces the design and processing requirements for aircraft parts and improves design efficiency.

[0028] During high-speed flight, the airflow through the front propeller 10 affects the aerodynamic force of the fuselage 1 and a portion of the wing 2, while the airflow through the rear propeller 12 does not affect the aerodynamic force of the aircraft. Comprehensive analysis shows that the aerodynamic interference of the front propeller 10 and the rear propeller 12 on the wing 2 is significantly reduced compared to the design of the V-22.

[0029] In summary, the present application first relaxes the design constraints of the power device during high-speed flight of the tilt-rotor aircraft, and can control the engine speed, power and other parameters as needed. Secondly, the aerodynamic interference of the aircraft rotor on the wing is greatly reduced compared with the existing design, increasing the safety of flight. In addition, the front-end system 4 and the rear-end system 5 overlap on the OX axis projection plane of the aircraft, reducing the windward area of ​​the entire aircraft, laying a foundation for improving the high-speed flight capability.

[0030] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A tilt-rotor aircraft, characterized in that: The invention comprises a fuselage (1), wings (2), a tail wing (3), a landing gear and a power device, wherein the power device comprises a front engine system (4) and a rear engine system (5), the front engine system (4) comprises a front engine (9) and a front engine propeller (10) driven by the front engine (9), the rear engine system (5) comprises a rear engine (11) and a rear engine propeller (12) driven by the rear engine (11), the front engine system (4) is hinged to the head of the aircraft, and the rear engine system (5) is hinged to the tail of the aircraft; The tiltrotor aircraft has a vertical take-off and landing state and a high-speed flight state. In the vertical take-off and landing state, the front propeller system (4) and the rear propeller system (5) are both tilted upward, so that the rotation planes of the front propeller (10) and the rear propeller (12) are parallel to the horizontal plane of the fuselage. In the high-speed flight state, the front propeller system (4) and the rear propeller system (5) are both tilted downward, so that the rotation planes of the front propeller (10) and the rear propeller (12) are perpendicular to the horizontal plane of the fuselage.

2. The tilt-rotor aircraft according to claim 1, characterized in that: The front propeller (10) and the rear propeller (12) overlap on the projection plane of the speed axis of the aircraft.

3. The tilt-rotor aircraft according to claim 1, characterized in that: In the vertical take-off and landing state, the pulling force of the rear propeller (12) is vertically upward; in the high-speed flight process, the pulling force of the rear propeller (12) is horizontally forward, and the direction control is achieved by adjusting the pitch angle of the propeller blades.

4. The tilt-rotor aircraft according to claim 1, characterized in that: The output power of the front engine (9) and the rear engine (11) is the same or different.

5. The tilt-rotor aircraft according to claim 1, characterized in that: The pulling force of the front propeller (10) and the rear propeller (12) is the same or different.

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