WO2019062257A1

WO2019062257A1 - Double lift force ducted vertical take-off and landing aircraft based on tilt duct

Info

Publication number: WO2019062257A1
Application number: PCT/CN2018/094442
Authority: WO
Inventors: 陈海昕; 周肖鹏; 张茂权
Original assignee: 清华大学
Priority date: 2017-09-29
Filing date: 2018-07-04
Publication date: 2019-04-04

Abstract

A double lift force ducted vertical take-off and landing aircraft based on a tilt duct, comprising an aircraft body (10), two wings (9), N tilt ducted fans (1, 2), two lift force ducted fans (5, 7), and two duct covers (6, 13), N being an even number. The wings (9) are oppositely arranged on either side of the rear middle portion of the aircraft body (10), and each wing (9) is formed by stretching outwards from the side portion. The N tilt ducted fans (1, 2) are divided into N/2 groups. Each group of tilt ducted fans (1, 2) are oppositely mounted on either side of the aircraft body (10), and each tilt ducted fan (1, 2) is rotatably connected to the aircraft body (10) by means of a corresponding connecting member. The two lift force ducted fans (5, 7) are embeddedly mounted in the two wings (9). The two duct covers (6, 13) are mounted on the upper portions of the two lift force ducted fans (5, 7) and can be opened or closed.

Description

Double-lifting ducted vertical take-off and landing aircraft based on tilting duct

Technical field

The present invention relates to an aircraft, and more particularly to a double-lift ducted vertical take-off and landing aircraft based on a tilting duct.

Background technique

Vertical take-off and landing aircraft usually refer to the ability to take off and land vertically like a helicopter, have a hovering capability, and can fly a class of aircraft horizontally in the form of a fixed-wing aircraft. Benefiting from the advantages of convenient take-off and landing and high flight efficiency, the vertical take-off and landing aircraft has important application value in military field. There are three types of vertical take-off and landing aircraft: rotor-type vertical take-off and landing aircraft, tilt-type vertical take-off and landing vehicles, and tailstock-type vertical take-off and landing aircraft. The following description will be made with a tilt-type vertical take-off and landing aircraft.

The existing tilting type vertical take-off and landing aircraft includes a tilting double rotor, a tilting four-rotor, a tilting wing, a tilting ducted fan, etc., all of which change the thrust direction by a rotating mechanism to achieve vertical take-off and landing.

However, the existing tilt-type vertical take-off and landing aircraft is complicated in structure and transmission mechanism, resulting in complex flight dynamic characteristics and low reliability in the transition process.

Summary of the invention

The present invention aims to solve at least one of the technical problems existing in the prior art. To this end, the present invention proposes a dual-lift ducted vertical take-off and landing aircraft based on tilting ducts.

The invention provides a double-lifting ducted vertical take-off and landing aircraft based on tilting ducts, comprising:

body;

Two wings for generating lift, correspondingly disposed on both sides of the middle rear portion of the fuselage and each wing is extended outward from the side, and the outer edge of each wing is streamlined;

N tilting ducted fans for attitude control in the vertical takeoff and landing phase and propulsion in the horizontal flight phase, N is even and divided into N/2 groups, each set of tilting ducted fans is mounted on the fuselage On both sides, each of the tilting ducted fans is rotatably connected to the fuselage through a corresponding connecting member; and

Two lift ducted fans for providing primary lift during the vertical takeoff and landing phase, correspondingly embedded in the two wings; and

Two ducted hoods correspondingly mounted on the upper portions of the two lift duct fans, and being openable or closable relative to the two lift duct fans, the two duct covers are opened during the vertical take-off and landing phases, so that the airflow By the horizontal flight phase, the two duct covers are closed and no airflow passes.

Further, in the vertical take-off and landing state, the thrust axes of the N tilting ducted fans are all downward, and the pitching moment is provided for the double-lifting ducted vertical take-off and landing aircraft by adjusting their deflection angles and thrust magnitudes. Rolling torque

The two duct shrouds are opened to allow airflow to smoothly enter the two lift duct fans, and provide the main lift for the double lift duct vertical takeoff and landing aircraft.

Further, in the transition state of the vertical flight to the horizontal flight transition, the N tilting ducted fans gradually change the angle, so that the double-lifting ducted vertical take-off and landing aircraft has a forward speed and acceleration;

As the flight speed increases, the two wings gradually generate lift, and the two duct covers are closed to maintain the shape of the wing, so that the double lift duct has a high lift resistance for the vertical takeoff and landing aircraft. Than to get a larger range and voyage.

Further, in the horizontal flight state, the thrust axes of the N tilting ducted fans are all rearward, and the thrust is provided by the tilting ducted fan, and each of the tilting ducted fans and the corresponding connecting member forms a duck wing by adjusting the deflection angle thereof. A pitching moment and a rolling moment may be provided for the double-lifting ducted vertical take-off and landing aircraft.

Further, the dual-lift ducted vertical take-off and landing aircraft further includes a vertical tail wing for providing heading safety, correspondingly disposed at the tip of the two wings, the vertical tail and the corresponding wing being perpendicular to each other .

Further, the rear end of each vertical tail forms a rudder for providing a yaw moment.

Further, the double lift ducted vertical takeoff and landing aircraft further includes:

a main landing gear corresponding to the lower sides of the fuselage and located at the positions of the two wings, each main landing gear being retractable or lowered relative to the fuselage; and

a front landing gear disposed at a position of the lower portion of the fuselage at a position of the fuselage head, the front landing gear being retractable or lowered relative to the fuselage;

In the vertical take-off and landing state, the main landing gear and the front landing gear are in a lowered state to support the double-lifting ducted vertical take-off and landing aircraft and the cushioning landing impact;

In the horizontal flight state, the main landing gear and the front landing gear are in a stowed state to reduce cruising resistance.

Further, each of the tilting ducted fans is driven by a motor, and each of the lift ducted fans is driven by a turboshaft engine, a piston engine or an electric motor.

The dual-lift ducted vertical take-off and landing aircraft of the present invention provides attitude control in the vertical take-off and phase stages and advancement in the horizontal flight phase through the tilting ducted fan, and provides the main lift in the vertical take-off and landing phase through the two lift ducted fans. Not only the vertical take-off and landing, but also the lifting force and the attitude control part are decoupled, thereby reducing the complexity of the dynamic characteristics of the double-lifting ducted vertical take-off and landing aircraft of the present invention, thereby improving the reliability.

The additional aspects and advantages of the invention will be set forth in part in the description which follows.

DRAWINGS

The above and/or additional aspects and advantages of the present invention will become apparent and readily understood from

1 is a schematic axial side view of a dual lift force ducted vertical takeoff and landing aircraft based on tilting ducts, in accordance with one embodiment of the present invention;

Figure 2 is a schematic front view of the double-lifting ducted vertical take-off and landing aircraft based on the tilting duct shown in Figure 1;

Figure 3 is a schematic plan view of the double-lifting ducted vertical take-off and landing aircraft based on the tilting duct shown in Figure 1;

Figure 4 is a schematic side view of the double-lifting ducted vertical take-off and landing aircraft based on the tilting duct shown in Figure 1;

5 is a schematic perspective view of a vertical take-off and landing state of a double-lifting ducted jib vertical take-off and landing aircraft based on tilting ducts according to an embodiment of the present invention;

6 is a schematic perspective view of a horizontal flight state of a two-lift force duct vertical take-off and landing aircraft based on a tilting duct according to an embodiment of the present invention.

The symbols in the figure indicate the meanings as follows:

1. Right tilting ducted fan; 2. Left tilting ducted fan; 3. Main landing gear; 4. Rudder; 5. Left lift ducted fan; 6. Left duct cover; 7. Right lift ducted fan; Vertical tail; 9. wing; 10. fuselage; 11. front landing gear; 12 canard; 13 right duct cover.

Detailed ways

The embodiments of the present invention are described in detail below, and the examples of the embodiments are illustrated in the drawings, wherein the same or similar reference numerals are used to refer to the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are intended to be illustrative of the invention and are not to be construed as limiting.

In the description of the present invention, it is to be understood that the orientation or positional relationship of the terms "upper", "lower", "front", "rear", "left", "right", etc. is based on the drawings. The orientation or positional relationship is merely for the purpose of describing the present invention and the simplification of the description, and is not intended to indicate or imply that the device or element referred to has a particular orientation, is constructed and operated in a particular orientation, and thus is not to be construed as limiting the invention.

1 is a schematic axial side view of a dual lift force ducted vertical takeoff and landing aircraft based on tilting ducts, in accordance with one embodiment of the present invention. 2 is a schematic front view of the double-lifting ducted vertical take-off and landing aircraft based on the tilting duct shown in FIG. 3 is a schematic plan view of the double-lifting ducted vertical take-off and landing aircraft based on the tilting duct shown in FIG. 4 is a schematic side view of the double-lifting ducted vertical take-off and landing aircraft of FIG. 1 based on the tilting duct.

As shown in FIG. 1 , referring also to FIG. 2-3 , the present invention provides a dual-lift ducted vertical take-off and landing aircraft based on tilting ducts. The aircraft may generally include a fuselage 10 , two wings 9 , and N Tilting ducted fan, two lift ducted fans and two ducted hoods. The fuselage 10 of the double-lift ducted vertical take-off and landing aircraft of the present invention is usually equipped with an aircraft system, a fuel system, a payload bay, an avionics system and the like. Two wings 9 are correspondingly disposed on both sides of the middle rear portion of the fuselage 10 and each wing 9 is extended outward from the side, and the outer edge of each wing 9 is streamlined, two wings 9 is used to generate lift. N tilting ducted fans are used for attitude control during the vertical takeoff and landing phases and advancement of the horizontal flight phase. Wherein, N is an even number and N tilting ducted fans are divided into N/2 groups, and each set of tilting ducted fans is correspondingly mounted on both sides of the fuselage 10, and each tilting ducted fan passes a corresponding connection The piece is rotatably coupled to the body 10. In this example, two tilting ducted fans, namely a left tilting ducted fan 2 and a right tilting ducted fan 1, are provided, and two tilting ducted fans are disposed on both sides of the head of the fuselage 10. Of course, in other embodiments, N may be four and divided into two groups, and two sets of tilting ducted fans are respectively disposed at the head and the front of the body 10. Two lift ducted fans are used to provide the main lift in the vertical takeoff and landing phase, and two lift ducted fans are correspondingly embedded in the two wings 9. In this example, the two lift duct fans are a left lift duct fan 5 and a right lift duct fan 7. Two ducted covers, namely a left duct cover 6 and a right duct cover 13, are mounted on the upper portions of the two lift duct fans, namely the left lift duct fan 5 and the right lift duct fan 7, and are The two lift duct fans, that is, the left lift duct fan 5 and the right lift duct fan 7 are opened or closed, and the left lift duct fan 5 and the right lift duct fan 7 are opened in the vertical take-off and landing phases, so that the airflow passes and the horizontal flight At the stage, the left lift duct fan 5 and the right lift duct fan 7 are closed, and no airflow passes.

The upper, lower, left, right, front, and back described in this embodiment are defined according to the direction of the view.

The tilting ducted fan of the present invention, that is, the left tilting ducted fan 2 and the right tilting ducted fan 1 and the lift ducted fan, that is, the left lift ducted fan 5 and the right lift ducted fan 7 are both used for the fan and The structure in which the engine is surrounded by ducts. Among them, the ducted fan is the main component of the aircraft and the key components of the fuselage structure. The main advantages of the conventional ducted propeller are as follows: 1) Under the same power consumption, the tensile force and power load of the ducted fan are greater than the same diameter. Isolated propeller; 2) Because the rotating fan and engine are enclosed by the duct, the aerodynamic noise of the fan is weakened, which is very important for the manned aircraft; 3) compact structure, high-speed rotating fan and airborne equipment, personnel Isolated to provide a certain protection.

5 is a schematic perspective view of a vertical take-off and landing state of a double-lifting ducted jib vertical take-off and landing aircraft based on tilting ducts, in accordance with one embodiment of the present invention. In the present invention, in the vertical take-off and landing state, the thrust axis of each tilting ducted fan is perpendicular to the ground, and the thrust difference between the left tilting ducted fan 2 and the right tilting ducted fan 1 and the thrust angle difference can provide the rolling control torque. Achieve control of the roll attitude. The pitch control can be realized by the difference in thrust between the left tilting ducted fan 2 and the right tilting ducted fan 1 and the left lift ducted fan 5 and the right lift ducted fan 7. By using the lift difference between the left lift duct fan 5 and the right lift duct fan 7, an additional roll control torque can be provided. By using the difference in rotational speed between the left lift duct fan 5 and the right lift duct fan 7, the yaw control of the aircraft can be achieved.

6 is a schematic perspective view of a horizontal flight state of a vertical takeoff and landing aircraft of a vertical takeoff and landing aircraft based on a tilting ducted vertical takeoff and landing aircraft according to an embodiment of the present invention. In the state of aircraft cruising, that is, horizontal flight, the left tilting ducted fan 2 and the right tilting ducted fan 1 are tilted by 90°, and the left tilting ducted fan 2 and the right tilting ducted fan 1 are all parallel to the ground, providing vertical The two-lift force of the aircraft is the thrust required for the vertical take-off and landing of the aircraft. The left tilting ducted fan 2 and the right tilting ducted fan 1 and the corresponding connecting members form a left side duck wing 12 and a right side duck wing 12, and the pitching control torque during horizontal flight can be provided by adjusting the deflection angle of the duck wing 12. . Referring to FIG. 2, by adjusting the deflection angle of the canard 12 on the left side and the canard 12 on the right side, at this time, the angle of attack of the left side of the canard 12 and the right side of the canard 12 is positive, then The double-lifting ducted vertical take-off and landing aircraft provides head-up torque. If the angle of attack on the left side of the canard 12 and the right side of the canard 12 are both negative, the aircraft is provided with a heading moment for the double-lifting ducted vertical take-off and landing aircraft. If the left wing 12 is differential from the right wing 12, a roll control torque can also be provided. If the angle of attack of the left wing 12 relative to the incoming flow is greater than the angle of attack of the right wing 12, then the double-lifting ducted vertical take-off and landing aircraft provides a torque to the right. If the angle of attack of the left wing 12 relative to the incoming flow is less than the angle of attack of the right wing 12, then the double-lifting ducted vertical take-off and landing aircraft provides a torque to roll to the left. The left lift duct fan 5 and the right lift duct fan 7 utilize the left duct cover 6 and the right duct cover 13 to cover their corresponding ducts in the cruising state of the aircraft, maintaining the shape of the wing 9 and improving the lift-to-drag ratio of the whole machine. .

The double-lifting ducted vertical take-off and landing aircraft of the present invention provides attitude control in the vertical take-off and phase stages and propulsion through the horizontal flight stage through the tilting ducted fan, that is, the left tilting ducted fan 2 and the right tilting ducted fan 1, through two lifts The ducted fan, that is, the left lift duct fan 5 and the right lift duct fan 7 provide the main lift in the vertical takeoff and landing phase, not only realizes vertical takeoff and landing, but also decouples the lift from the attitude control portion, thereby reducing the double lift of the present invention. The complexity of the dynamic characteristics of the aircraft's vertical take-off and landing aircraft improves reliability.

In addition, the double-lifting ducted vertical take-off and landing aircraft of the invention has the advantages of high-efficiency leveling, small outer dimensions, simple flight control, good engineering realization, and the like, and has the advantages of long range and fast speed in performance, and can be applied. In the field of conventional and special aircraft such as light aircraft, transport aircraft, reconnaissance aircraft, electronic warfare aircraft.

As shown in FIG. 1 , in the embodiment, the double-lifting ducted vertical take-off and landing aircraft further includes a vertical tail 8 for providing heading safety, correspondingly disposed at the tip of the two wings 9 . The vertical tail 8 is perpendicular to the corresponding wing 9.

As shown in Fig. 1, in the present embodiment, the rear end of each vertical tail 8 forms a rudder 4 for providing a yaw moment.

As shown in FIG. 1 , in the embodiment, the double-lift ducted vertical take-off and landing aircraft further includes a main landing gear 3 and a nose landing gear 11 . The main landing gear 3 is correspondingly disposed at both sides of the lower portion of the fuselage 10 and at the positions of the two wings 9, and each of the main landing gears 3 can be retracted or lowered relative to the body 10. The nose landing gear 11 is disposed at a position where the lower portion of the body 10 is located at the head of the body 10, and the nose gear 11 can be stowed or lowered relative to the body 10.

As shown in FIG. 5, in the embodiment, in the vertical take-off and landing state, the thrust axes of the N tilting ducted fans, that is, the left tilting ducted fan 2 and the right tilting ducted fan 1 are both downward, by adjusting them The deflection angle and the magnitude of the thrust provide the pitching moment and the rolling moment for the double-lifting ducted vertical take-off and landing aircraft.

The left duct cover 6 and the right duct cover 13 are opened to smoothly flow the air into the left lift duct fan 5 and the right lift duct fan 7, and provide main lift for the double lift duct vertical takeoff and landing aircraft. The thrust difference is realized by adjusting the rotational speeds of the left lift duct fan 5 and the right lift duct fan 7, and the rolling moment and the yaw moment can be provided.

The main landing gear 3 and the front landing gear 11 are in a lowered state to support the double lift duct vertical takeoff and landing aircraft and cushioning landing impact.

Referring to FIG. 1, in the embodiment, in a transition state of vertical flight to horizontal flight conversion, the N tilting ducted fans, that is, the left tilting ducted fan 2 and the right tilting ducted fan 1 gradually change the angle, so that the The double lift ducted vertical takeoff and landing aircraft has forward speed and acceleration.

As the flight speed increases, the two wings 9 gradually generate lift, the left duct cover 6 and the right duct are closed, maintaining the outer shape of the wing 9 to make the double lift duct vertical takeoff and landing aircraft Has a higher lift-to-drag ratio for larger voyages and voyages.

Referring to FIG. 6, in the horizontal flight state, the thrust axes of the N tilting ducted fans, that is, the left tilting ducted fan 2 and the right tilting ducted fan 1 are all rearward, and thrust is provided by each of them. A tilting ducted fan and corresponding connector form a canard 12, i.e., correspondingly forming a canard 12 on the left side and a canard 12 on the right side. The pitching moment and the rolling moment can be provided for the double-lifting ducted vertical take-off and landing aircraft by adjusting its deflection angle. As the flight speed increases, the efficiency of the aerodynamic rudder surface increases, the vertical empennage 8 at the tip of the wing 9 provides heading stability, and the rudder 4 provides yaw moment. The ailerons located at the trailing edge of the wing 9 provide rolling torque.

The main landing gear 3 and the front landing gear 11 are in a stowed state to reduce cruising resistance.

In this embodiment, each of the tilting ducted fans, that is, the left tilting ducted fan 2 and the right tilting ducted fan 1 are driven by a motor, and sensitive speed regulation characteristics can be obtained to facilitate control. Each of the lift duct fans, that is, the left lift duct fan 5 and the right lift duct fan 7 are driven by a turboshaft engine, a piston engine or an electric motor, and a turbojet engine or a piston engine can be used to obtain a larger voyage time. Sensitive speed regulation is achieved with motor drive.

In the description of the present specification, the description with reference to the terms "one embodiment", "some embodiments", "illustrative embodiment", "example", "specific example", or "some examples", etc. Particular features, structures, materials or features described in the examples or examples are included in at least one embodiment or example of the invention. In the present specification, the schematic representation of the above terms does not necessarily mean the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in a suitable manner in any one or more embodiments or examples.

While the embodiments of the present invention have been shown and described, the embodiments of the invention may The scope of the invention is defined by the claims and their equivalents.

Claims

A double-lift ducted vertical take-off and landing aircraft based on tilting ducted, characterized in that it comprises:

body;

Two wings for generating lift, correspondingly disposed on both sides of the middle rear portion of the fuselage and each wing is extended outward from the side, and the outer edge of each wing is streamlined;

N tilting ducted fans for attitude control in the vertical takeoff and landing phase and propulsion in the horizontal flight phase, N is even and divided into N/2 groups, each set of tilting ducted fans is mounted on the fuselage On both sides, each of the tilting ducted fans is rotatably connected to the fuselage through a corresponding connecting member; and

Two lift ducted fans for providing primary lift during the vertical takeoff and landing phase, correspondingly embedded in the two wings; and

Two ducted hoods correspondingly mounted on the upper portions of the two lift duct fans, and being openable or closable relative to the two lift duct fans, the two duct covers are opened during the vertical take-off and landing phases, so that the airflow By the horizontal flight phase, the two duct covers are closed and no airflow passes.
The double-lift ducted hoisting and landing aircraft according to claim 1, wherein in the vertical take-off and landing state, the thrust axes of the N tilting ducted fans are all downward, by adjusting their deflection angles and thrusts. The size provides the pitching moment and the rolling moment for the double-lifting ducted vertical take-off and landing aircraft;

The two duct shrouds are opened to allow airflow to smoothly enter the two lift duct fans, and provide the main lift for the double lift duct vertical takeoff and landing aircraft.
The double-lift ducted hoisting and landing aircraft according to claim 1 or 2, wherein in the transition state of the vertical flight to the horizontal flight transition, the N tilting ducted fans gradually change the angle to make the double Lifting ducted vertical take-off and landing aircraft have forward speed and acceleration;

As the flight speed increases, the two wings gradually generate lift, and the two duct covers are closed to maintain the shape of the wing, so that the double lift duct has a high lift resistance for the vertical takeoff and landing aircraft. Than to get a larger range and voyage.
The double-lift ducted hoisting and landing aircraft according to any one of claims 1 to 3, characterized in that, in the horizontal flight state, the thrust axes of the N tilting ducted fans are all rearward, provided by The thrust, each tilting ducted fan and the corresponding connecting member form a canard, and the pitching torque and the rolling moment can be provided for the double-lifting ducted vertical take-off and landing aircraft by adjusting the deflection angle thereof.
The dual lift ducted hoisting and landing aircraft according to any one of claims 1 to 4, further comprising a vertical tail for providing heading safety, correspondingly disposed at the tip of the two wings The vertical tail is perpendicular to the corresponding wing.
The double lift bypass hoisting and landing aircraft according to claim 5, wherein the rear end of each vertical empennage forms a rudder for providing a yaw moment.
The double-lifting ducted vertical take-off and landing aircraft according to any one of claims 1 to 6, further comprising:

a main landing gear corresponding to the lower sides of the fuselage and located at the positions of the two wings, each main landing gear being retractable or lowered relative to the fuselage; and

a front landing gear disposed at a position of the lower portion of the fuselage at a position of the fuselage head, the front landing gear being retractable or lowered relative to the fuselage;

In the vertical take-off and landing state, the main landing gear and the front landing gear are in a lowered state to support the double-lifting ducted vertical take-off and landing aircraft and the cushioning landing impact;

In the horizontal flight state, the main landing gear and the front landing gear are in a stowed state to reduce cruising resistance.
The dual-lift ducted vertical take-off and landing aircraft according to any one of claims 1 to 7, wherein each of the tilting ducted fans is driven by a motor, and each of the lift ducted fans passes through a turboshaft engine and a piston engine. Or motor driven.