CN107628244A - A Dual-Lift Duct VTOL Aircraft Based on Tilting Duct - Google Patents

Abstract

The invention discloses a dual-lift ducted VTOL aircraft based on a tilt duct, and relates to an aircraft. The vertical take-off and landing aircraft comprises an aircraft body, two wings, N tilting ducted fans, two lifting ducted fans and two ducted covers. The wings are correspondingly arranged on two sides of the middle rear part of the fuselage, and each wing is formed by extending the side part outwards. Every group verts the ducted fan and corresponds the both sides of installing at the fuselage, and every verts the ducted fan and rotates through the connecting piece that corresponds and be connected with the fuselage. Two lift ducted fans are mounted embedded in the two wings. The two ducted cowlings are mounted on top of the two lift ducted fans and can be opened or closed. The invention provides attitude control in a vertical take-off and landing stage and propulsion in a horizontal flight stage through the tilting ducted fans, and provides main lift force in the vertical take-off and landing stage through the two lift force ducted fans. The vertical take-off and landing are realized, and the lift force and the attitude control part are decoupled, so that the complexity of the dynamic characteristic of the invention is reduced, and the reliability is improved.

Description

A Dual-Lift Duct VTOL Aircraft Based on Tilting Duct

technical field

The invention relates to an aircraft, in particular to a dual-lift duct vertical take-off and landing aircraft based on a tilt duct.

Background technique

Vertical take-off and landing aircraft usually refers to a type of aircraft that can take off and land vertically like a helicopter, has the ability to hover, and can fly horizontally in the manner of a fixed-wing aircraft. Benefiting from the advantages of convenient take-off and landing and high flight efficiency, vertical take-off and landing aircraft have important application value in the military. There are three types of vertical take-off and landing aircraft: rotor-type vertical take-off and landing aircraft, tilting-type vertical take-off and landing aircraft, and tailseat type vertical take-off and landing aircraft. The following will be described with a tilting vertical take-off and landing aircraft.

Existing tilting vertical take-off and landing aircraft include tilting dual rotors, tilting quadrotors, tilting wings, tilting ducted fans, etc., all of which change the direction of thrust through a rotating mechanism to achieve vertical takeoff and landing.

However, due to the complex structure and transmission mechanism of the existing tilting vertical take-off and landing aircraft, the flight dynamic characteristics during the transition process are complicated and the reliability is low.

Contents of the invention

The present invention aims to solve at least one of the technical problems existing in the prior art. For this reason, the present invention proposes a kind of vertical take-off and landing aircraft based on the double-lift duct of the tilting duct.

The invention provides a dual-lift duct vertical take-off and landing aircraft based on a tilt duct, comprising:

body;

Two wings, used to generate lift, are arranged on both sides of the middle and rear part of the fuselage correspondingly, and each wing is formed by extending outward from the side, and the outer edge of each wing is streamlined;

N tilting ducted fans are used for attitude control in the vertical take-off and landing phase and propulsion in the horizontal flight phase, N is an even number and divided into N/2 groups, and each group of tilting ducted fans is correspondingly installed on the fuselage On both sides, each tilting ducted fan is rotatably connected to the fuselage through a corresponding connecting piece; and

Two lift ducted fans, used to provide the main lift during the vertical take-off and landing phase, are correspondingly embedded in the two wings; and

Two duct covers are installed on the upper parts of the two lift duct fans correspondingly, and can be opened or closed relative to the two lift duct fans. The two duct covers are opened during the vertical take-off and landing stage to allow the airflow Through, the two duct covers are closed during the horizontal flight stage, and no air flow passes through.

Further, in the vertical take-off and landing state, the thrust axes of the N tilting ducted fans are all downward, and by adjusting their deflection angles and thrust magnitudes, it provides pitching moment and rolling moment;

The two duct covers are opened to allow the airflow to enter the two lift duct fans smoothly to provide the main lift for the dual-lift duct vertical take-off and landing aircraft.

Further, in the transition state from vertical flight to horizontal flight, the N tilting ducted fans gradually change their angles, so that the dual-lift ducted VTOL aircraft has 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 wings, so that the dual-lift ducted vertical take-off and landing aircraft has a higher lift-drag Ratio, to obtain greater range and flight time.

Further, in the horizontal flight state, the thrust axes of the N tilting ducted fans are all backward, and the thrust is provided by them. Each tilting ducted fan forms a canard with the corresponding connecting piece, and by adjusting its deflection angle The pitching moment and rolling moment can be provided for the dual-lift ducted vertical take-off and landing aircraft.

Further, the dual-lift ducted vertical take-off and landing aircraft also includes a vertical tail, which is used to provide heading safety, and is correspondingly arranged at the tips of the two wings, and the vertical tail is perpendicular to the corresponding wings .

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

Further described double-lift ducted vertical take-off and landing aircraft also includes:

The main landing gear is arranged on both sides of the lower part of the fuselage correspondingly and is located at the position of the two wings, and each main landing gear can be stowed or lowered relative to the fuselage; and

The front landing gear is arranged at the position where the lower part of the fuselage is located at the head of the fuselage, and the front landing gear can be stowed 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 dual-lift duct vertical take-off and landing aircraft and buffer landing impact;

In the state of level flight, the main landing gear and the front landing gear are in retracted state to reduce cruising resistance.

Further, each tilting ducted fan is driven by a motor, and each lift ducted fan 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 landing phase and propulsion in the horizontal flight phase through the tilting ducted fans, and provides the main lift in the vertical take-off and landing phase through two lift ducted fans. It not only realizes the vertical take-off and landing, but also decouples the lift force from the attitude control part, thereby reducing the complexity of the dynamic characteristics of the double-lift ducted vertical take-off and landing aircraft of the present invention, thereby improving the reliability.

Additional aspects and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention.

Description of drawings

The above and/or additional aspects and advantages of the present invention will become apparent and comprehensible from the description of the embodiments in conjunction with the following drawings, wherein:

Fig. 1 is a schematic axonometric view of a dual-lift ducted VTOL aircraft based on a tilting duct according to an embodiment of the present invention;

Fig. 2 is the schematic front view of the dual-lift duct VTOL aircraft based on the tilt duct shown in Fig. 1;

Fig. 3 is a schematic top view of the dual lift duct VTOL aircraft based on the tilt duct shown in Fig. 1;

Fig. 4 is the schematic side view of the dual-lift duct VTOL aircraft based on the tilt duct shown in Fig. 1;

Fig. 5 is a schematic perspective view of a vertical take-off and landing state of a dual-lift ducted vertical take-off and landing aircraft based on a tilting duct according to an embodiment of the present invention;

Fig. 6 is a schematic perspective view of a dual-lift duct VTOL aircraft in horizontal flight state according to an embodiment of the present invention.

The meanings of the symbols in the figure are 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 ducted cover; 7. Right lift ducted fan; 8 .vertical tail; 9. wing; 10. fuselage; 11. front landing gear; 12 canard; 13 right ducted cover.

detailed description

Embodiments of the present invention are described in detail below, examples of which are shown in the drawings, wherein the same or similar reference numerals designate the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the figures are exemplary only for explaining the present invention and should not be construed as limiting the present invention.

In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "upper", "lower", "front", "rear", "left", "right" etc. are based on those shown in the accompanying drawings. Orientation or positional relationship is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation of the present invention.

Fig. 1 is a schematic axonometric view of a dual lift duct VTOL aircraft based on a tilt duct according to an embodiment of the present invention. Fig. 2 is a schematic front view of the dual-lift duct-based VTOL aircraft shown in Fig. 1 . Fig. 3 is a schematic top view of the dual lift duct VTOL aircraft based on the tilt duct shown in Fig. 1 . Fig. 4 is a schematic side view of the dual-lift duct-based VTOL aircraft shown in Fig. 1 .

As shown in Figure 1, also referring to Figures 2-3, the present invention proposes a dual-lift ducted vertical take-off and landing aircraft based on a tilting duct, generally including a fuselage 10, two wings 9, and N Tilting ducted fans, two lift ducted fans and two ducted covers. The fuselage 10 of the double-lift ducted vertical take-off and landing aircraft of the present invention is usually equipped with essential aircraft systems such as an engine system, a fuel system, a payload compartment, and an avionics system. Two wings 9 are correspondingly arranged on both sides of the middle and rear portion of the fuselage 10 and each wing 9 is formed by extending outwards from the side. The outer edge of each wing 9 is streamlined, and the two wings 9 for generating lift. N tilting ducted fans are used for attitude control in the vertical take-off and landing phase and propulsion in the horizontal flight phase. Wherein, N is an even number and N tilting ducted fans are divided into N/2 groups, and each group of tilting ducted fans is correspondingly installed on both sides of the fuselage 10, and each tilting ducted fan is connected through a corresponding The parts are rotatably connected with the fuselage 10. In this example, there are two tilting ducted fans, namely a left tilting ducted fan 2 and a right tilting ducted fan 1 , and the two tilting ducted fans are arranged 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 the two groups of tilting ducted fans are respectively arranged at the head and the front of the fuselage 10 . Two lift duct fans are used to provide the main lift during the vertical take-off and landing phase, and the two lift duct fans are correspondingly embedded in the two wings 9 . In this example, the two lift duct fans are the left lift duct fan 5 and the right lift duct fan 7 respectively. Two duct covers, namely the left duct cover 6 and the right duct cover 13, are installed on the top of the two lift duct fans, namely the left lift duct fan 5 and the right lift duct fan 7, and can be opposite to the The two lift duct fans, the left lift duct fan 5 and the right lift duct fan 7, are turned on or off, and the vertical take-off and landing phase, that is, the left lift duct fan 5 and the right lift duct fan 7 are turned on to allow the airflow to pass through and to fly horizontally The stage is that the left lift duct fan 5 and the right lift duct fan 7 are closed, and no air flow passes through.

Wherein, the up, down, left, right, front, and back mentioned in this embodiment are all defined according to the direction of view.

In the present invention, the tilting ducted fan, that is, the left tilting ducted fan 2 and the right tilting ducted fan 1, and the lift ducted fan, that is, the left lifting ducted fan 5 and the right lifting ducted fan 7, all adopt the fan and The structure in which the engine is surrounded by ducts. Among them, the ducted fan, as the main propulsion system of the aircraft and the key component of the fuselage structure, has the following main advantages compared with the traditional propeller: 1) Under the same power consumption, the traction and power load of the ducted fan are greater than those of the propeller with the same diameter. Isolated propeller; 2) Because the rotating fan and engine are surrounded by ducts, the aerodynamic noise of the fan is reduced, which is very important for manned aircraft; 3) The structure is compact, and the high-speed rotating fan and airborne equipment, personnel isolated for protection.

Fig. 5 is a schematic perspective view of a vertical take-off and landing state of a dual lift duct VTOL aircraft based on a tilting duct according to an 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 roll control moment can be provided by using the thrust difference and the thrust angle difference between the left tilting ducted fan 2 and the right tilting ducted fan 1, Realize the control of roll attitude. The pitch control can be realized by using the thrust difference between the left-tilted ducted fan 2 and the right-tilted ducted fan 1 and the left lift ducted fan 5 and the right lift ducted fan 7 . The lift difference between the left lift ducted fan 5 and the right lift ducted fan 7 can be used to provide additional roll control torque. Utilizing the rotational speed difference between the left lift duct fan 5 and the right lift duct fan 7, the yaw control of the aircraft can be realized.

Fig. 6 is a schematic perspective view of a vertical take-off and landing aircraft based on a tilting duct in a horizontal flight state of a dual-lift ducted vertical take-off and landing aircraft according to an embodiment of the present invention. In the cruising state of the aircraft, that is, the horizontal flight state, the left-tilted ducted fan 2 and the right-tilted ducted fan 1 are tilted 90°, and the thrust axes of the left-tilted ducted fan 2 and the right-tilted ducted fan 1 are all parallel to the ground, providing vertical lift. The thrust required for the forward flight of the double-lift ducted vertical take-off and landing aircraft. The left tilting ducted fan 2 and the right tilting ducted fan 1 form the left canard 12 and the right canard 12 with the corresponding connectors. By adjusting the deflection angle of the canard 12, the pitch control moment can be provided during horizontal flight. . Referring to Fig. 2, by adjusting the deflection angles of the canard 12 on the left side and the canard 12 on the right side, at this moment, the canard 12 on the left side and the canard 12 on the right side have positive angles of attack. The above-mentioned dual-lift ducted vertical take-off and landing aircraft provides the nose-up moment. If the angle of attack of the canard 12 on the left side and the canard wing 12 on the right side is both negative, then the nose-down moment is provided to the vertical take-off and landing aircraft with double-lift ducts. If the canard 12 on the left side and the canard 12 on the right side are differentially operated, the rolling control moment can also be provided. If the angle of attack of the canard 12 on the left side relative to the incoming flow is greater than the angle of attack of the canard 12 on the right side, then the dual-lift ducted VTOL aircraft is provided with a moment of right roll. If the angle of attack of the canard 12 on the left side relative to the incoming flow is smaller than the angle of attack of the canard 12 on the right side, then the dual-lift ducted VTOL aircraft is provided with a moment of roll to the left. The left lift duct fan 5 and the right lift duct fan 7 use the left duct cover 6 and the right duct cover 13 to cover their corresponding ducts in the cruising state of the aircraft, maintain the shape of the wing 9, and improve the lift-to-drag ratio of the whole aircraft .

The dual-lift ducted vertical take-off and landing aircraft of the present invention provides attitude control in the vertical take-off and landing phase and propulsion in the horizontal flight phase through the tilting ducted fan, that is, the left-tilting ducted fan 2 and the right-tilting ducted fan 1. The ducted fans, that is, the left lift ducted fan 5 and the right lift ducted fan 7, provide the main lift in the vertical take-off and landing stage, which not only realizes the vertical take-off and landing, but also decouples the lift from the attitude control part, thereby reducing the double lift of the present invention. The complexity of the dynamic characteristics of the ducted vertical take-off and landing aircraft, thereby improving the reliability.

In addition, the dual-lift ducted vertical take-off and landing aircraft of the present invention also has the advantages of high-efficiency level flight, small outline size, simple flight control, and good engineering realization. It also has the advantages of long range and fast speed in terms of performance. It is used in conventional and special aircraft fields such as light aircraft, transport aircraft, reconnaissance aircraft, and electronic warfare aircraft.

As shown in Figure 1, in the present embodiment, the described double-lift ducted vertical take-off and landing aircraft also includes a vertical tail 8, which is used to provide heading safety, and is correspondingly arranged at the tips of the two wings 9, so The vertical tail 8 and the corresponding wings 9 are perpendicular to each other.

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

As shown in FIG. 1 , in this embodiment, the dual-lift ducted VTOL aircraft further includes a main landing gear 3 and a front landing gear 11 . The main landing gear 3 is correspondingly arranged on both sides of the lower part of the fuselage 10 and is located at the position of the two wings 9 , and each main landing gear 3 can be retracted or lowered relative to the fuselage 10 . The front landing gear 11 is arranged on the lower part of the fuselage 10 at the head position of the fuselage 10 , and the front landing gear 11 can be stowed or lowered relative to the fuselage 10 .

As shown in Figure 5, in the present 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 all downward, by adjusting them The deflection angle and the magnitude of the thrust provide pitching moment and rolling moment for the double-lift ducted vertical take-off and landing aircraft.

The left duct cover 6 and the right duct cover 13 are opened to allow airflow to enter the left lift duct fan 5 and the right lift duct fan 7 smoothly, and provide main lift for the dual-lift duct vertical take-off and landing aircraft. The thrust difference is realized by adjusting the rotational speeds of the left lift ducted fan 5 and the right lift ducted fan 7, which can provide rolling moment and yaw moment.

The main landing gear 3 and the front landing gear 11 are in a lowered state to support the dual-lift duct vertical take-off and landing aircraft and buffer landing impact.

Referring to Fig. 1, in the present embodiment, in the transitional state from vertical flight to horizontal flight, the N tilting ducted fans, that is, the left tilting ducted fan 2 and the right tilting ducted fan 1 gradually change angles, so that the Dual-lift ducted VTOL aircraft have forward speed and acceleration.

As the flight speed increases, the two wings 9 gradually generate lift, and the left duct cover 6 and the right duct are closed to maintain the shape of the wings 9, so that the double-lift duct can take off and land the aircraft vertically It has a higher lift-to-drag ratio to obtain greater range and flight time.

Referring to Fig. 6, in this embodiment, 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 backward, and thrust is provided by them, each A tilting ducted fan forms the canard 12 with the corresponding connecting piece, that is, the canard 12 on the left side and the canard 12 on the right side are formed correspondingly. By adjusting the deflection angle, the double-lift ducted vertical take-off and landing aircraft can provide pitching moment and rolling moment. Along with the raising of flight speed, the efficiency of aerodynamic control surface improves, and the vertical empennage 8 that is positioned at the tip of wing 9 provides heading stability, and rudder 4 provides yaw moment. Ailerons located on the trailing edge of wing 9 provide the roll moment.

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

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

In the description of this specification, references to the terms "one embodiment," "some embodiments," "exemplary embodiments," "example," "specific examples," or "some examples" are intended to mean that the implementation A specific feature, structure, material, or characteristic described by an embodiment or example is included in at least one embodiment or example of the present invention. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

Although the embodiments of the present invention have been shown and described, those skilled in the art can understand that various changes, modifications, substitutions and modifications can be made to these embodiments without departing from the principle and spirit of the present invention. The scope of the invention is defined by the claims and their equivalents.

Claims (8)

1. A kind of 1. double lift culvert vertical take-off and landing aircrafts based on tilting duct, it is characterised in that including：

   Fuselage；

   Two wings, for producing lift, be correspondingly arranged at the postmedian of the fuselage both sides and each wing from sidepiece to Outer stretching, extension forms, and the lateral border of each wing is streamlined；

   N number of tilting duct fan, for the gesture stability in VTOL stage and the propulsion of level flight stage, N be even number and It is divided into N/2 groups, every group of tilting duct fan is correspondingly arranged on the both sides of the fuselage, and each tilting duct fan passes through corresponding Connector is rotatablely connected with the fuselage；With

   Two lift ducted fans, for providing the prevailing lift in VTOL stage, it is correspondingly embedded in installed in described two machines In the wing；With

   Two duct covers, it is corresponding installed in the top of described two lift ducted fans, and can relatively described two lift ducts Fan is opened or closed, and the VTOL stage, described two duct covers were opened, and were caused air flow through, level flight stage is described two Duct cover is closed, and airless passes through.
2. 2. double lift culvert vertical take-off and landing aircrafts according to claim 1, it is characterised in that in VTOL state, institute State that the thrust axis of N number of tilting duct fan is downward, be double lift by adjusting their deflection angle and thrust size Culvert vertical take-off and landing aircraft provides pitching moment and rolling moment；

   Described two duct covers are opened, and airflow smooth is entered described two lift ducted fans, are hung down for double lift ducts Straight landing aircraft provides prevailing lift.
3. 3. double lift culvert vertical take-off and landing aircrafts according to claim 1, it is characterised in that fly in vertical flight to level The transition state of row conversion, N number of tilting duct fan gradually change angle, make double lift culvert vertical take-off and landing aircrafts With speed forward and acceleration；

   With the raising of flying speed, described two wings gradually produce lift, and described two duct covers are closed, and maintain the machine Contour of flange, make double lift culvert vertical take-off and landing aircrafts that there is higher lift-drag ratio, to obtain larger voyage and endurance.
4. 4. double lift culvert vertical take-off and landing aircrafts according to claim 1, it is characterised in that in level flight condition, institute The thrust axis for stating N number of tilting duct fan backward, is provided by it thrust, each tilting duct fan and corresponding connector shape Into canard, pitching moment and rolling power can be provided for double lift culvert vertical take-off and landing aircrafts by adjusting its deflection angle Square.
5. 5. double lift culvert vertical take-off and landing aircrafts according to claim 1, it is characterised in that also including vertical tail, use In providing course security, the taper of described two wings is correspondingly arranged at, the vertical tail mutually hangs down with corresponding wing Directly.
6. 6. double lift culvert vertical take-off and landing aircrafts according to claim 5, it is characterised in that the rear end of each vertical tail Rudder is formed, for providing yawing.
7. 7. double lift culvert vertical take-off and landing aircrafts according to claim 1, it is characterised in that also include：

   Main landing gear, it is correspondingly arranged the bottom both sides of the fuselage and is risen and fallen positioned at the opening position of described two wings, each master Frame can relatively described fuselage pack up or put down；With

   Nose-gear, the bottom for being arranged on the fuselage are located at the opening position of the fuselage head, and the nose-gear can be relative The fuselage is packed up or put down；

   In VTOL state, the main landing gear is in down state with the nose-gear, to support double lift to contain Road VTOL aircraft is gentle to rush landing shock；

   In level flight condition, the main landing gear is in collapsed state with the nose-gear, to reduce cruise drag.
8. 8. double lift culvert vertical take-off and landing aircrafts according to any one of claim 1-7, it is characterised in that each to vert Ducted fan is driven by motor, and each lift ducted fan is driven by turboshaft engine, piston engine or motor.