CN114476050A - A tilting ducted fixed-wing aircraft - Google Patents

Abstract

The application provides a duct fixed wing aircraft verts includes: the fuselage, the main wing, the duck wing, duct fan engine and undercarriage, wherein, the fuselage is including the mission load cabin that is located the anterior cockpit of fuselage and is located the fuselage back, the undercarriage sets up the bottom at the fuselage, the main wing upper surface of every side is equipped with a plurality of duct fan engine, and the duck wing upper surface of every side also is equipped with a plurality of duct fan engine, main wing and duck wing can rotate for the fuselage along the wing axis, through the rotation of control main wing and duck wing, make duct fan engine on main wing and the duck wing rotatory to with ground vertical state and with ground parallel state, thereby take off and the vertical take off and land when landing and horizontal flight. The utility model provides a duct fixed wing aircraft verts can realize possessing the ability of VTOL, horizontal high-speed flight simultaneously, and compatible tradition helicopter and fixed wing aircraft advantage, VTOL and horizontal flight mode conversion are simple, and the security is high.

Description

A tilting ducted fixed-wing aircraft

technical field

The present application belongs to the technical field of aircraft overall design, and particularly relates to a tilting ducted fixed-wing aircraft.

Background technique

Tilt-rotor aircraft is an aircraft with a new configuration principle, which is an aircraft between helicopters and fixed-wing aircraft. When the tilt-rotor is in a vertical position, this type of aircraft is similar to a double-rotor tandem helicopter, which can hover, fly sideways, fly back, take off and land vertically, etc., eliminating the need for a special take-off and landing runway and not restricted by the site; when tilting When the rotor is in a horizontal position, this type of aircraft is similar to fixed-wing aircraft, suitable for high-speed long-distance flight, and has a larger flight envelope.

However, existing tilt-rotor aircraft of this type are usually large in size and are not suitable for use in future cities.

SUMMARY OF THE INVENTION

The purpose of the present application is to provide a tilting ducted fixed-wing aircraft to solve or alleviate at least one problem in the background art.

The technical solution of the present application is: a tilting ducted fixed-wing aircraft, the aircraft includes: a fuselage, a main wing, a canard, a ducted fan engine and a landing gear, wherein the fuselage includes a fuselage located in front of the fuselage. The cockpit and the task load bay at the rear of the fuselage, the landing gear is arranged at the bottom of the fuselage, the upper surface of each side of the main wing is provided with several ducted fan engines, and the upper surface of each side of the canard is also provided with Several ducted fan engines, the main wings and canards can rotate relative to the fuselage along the axis of the wing, and the ducted fan engines on the main wings and canards are rotated by controlling the rotation of the main wings and canards To the state of being perpendicular to the ground and parallel to the ground, so as to achieve vertical take-off and landing and horizontal flight during take-off and landing.

Further, the main wing and the canard are symmetrical about the fuselage axis.

Further, the area of the main wing is larger than that of the canard.

Further, the number of ducted fan engines arranged on the upper surface of the main wing is greater than the number of ducted fan engines arranged on the upper surface of the canard.

Further, an attitude control airfoil along the chord length direction is provided along the outer side of the main wing spanwise direction, and the attitude of the main wing airfoil can be precisely adjusted by controlling the deflection of the attitude control airfoil.

Further, the tip end of the main wing has a vertically arranged winglet, and the tail of the winglet has a rudder along the fuselage direction.

Further, ducted fan flaps along the chord length are provided on the outer side along the spanwise direction of the canard.

Further landing gears include wheeled and sled gears. .

The tilting ducted fixed-wing aircraft of the present application can realize point-to-point rapid transportation of people/goods in the city, and has the ability of vertical take-off and landing and horizontal high-speed flight, compatible with the advantages of traditional helicopters and fixed-wing aircraft, and the conversion of vertical take-off and landing and horizontal flight modes It is simple and safe, and can also realize hovering flight function. According to different target tasks, it can be dedicated to carrying passengers, or it can also be equipped with a modular task load compartment to realize functions such as medical rescue and cargo, and realize multi-function and multi-scenario. application to provide a green, safe and feasible aircraft for urban air traffic.

Description of drawings

In order to more clearly illustrate the technical solutions provided by the present application, the accompanying drawings will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application.

FIG. 1 is a schematic diagram of the overall structure of the tilting ducted fixed-wing aircraft of the present application.

FIG. 2 is a schematic diagram of the double-opening tail hatch of the aircraft of the present application.

FIG. 3 is a schematic diagram of a ducted fan flap and an attitude control airfoil of an aircraft of the present application.

Reference number:

11 - Body

12-Main wing

13 - duck wing

14- Ducted fan engine

15 - Landing Gear

16 - Rudder

17-wing slightly winglets

18-Side sliding door

19-Double tail hatch

141 - Ducted Fan Flaps

142 - Attitude Control Airfoil

Detailed ways

In order to make the implementation purpose, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.

In order to combine the advantages of a vertical take-off and landing tilt-rotor aircraft with the characteristics of a fixed-wing aircraft suitable for high-speed cruise flight, and at the same time, the ducted design makes it suitable for a wider range of scenarios and safer to fly, so as to effectively solve the increasingly serious problem of ground traffic congestion. The application proposes an aircraft that can be applied to future urban air transportation.

As shown in FIGS. 1 to 3 , the present application provides a tilting ducted fixed-wing aircraft, which adopts a high-efficiency electric canard aerodynamic layout, and the aircraft mainly includes a fuselage 11 , a main wing 12 , and a canard 13 , a number of ducted fan engines 14 and landing gear 15 and so on.

The fuselage 11 includes a cockpit at the front of the aircraft fuselage and a mission payload bay at the rear of the aircraft fuselage. The cockpit is similar in function and structure to the traditional manned small fixed-wing aircraft, and the cockpit can be driven by one or two people as needed. After the flight mission is determined, the configuration of the mission load compartment is firstly converted, and the appropriate configuration of the load compartment is selected. The mission load bay adopts a standard interface design, which can be quickly converted into seats, pallets, stretchers, small medical containers, etc. It can be dedicated to carrying passengers according to different target tasks, or can be equipped with modular load bays, including manned cabins, medical ambulance cabins, cargo cabins and special cabins, etc., to achieve multi-functional and multi-scenario applications.

A cabin door is provided on the fuselage 11. The cabin door includes a side sliding cabin door 18 located at the side of the fuselage and a double-opening tail cabin door 19 located at the rear of the fuselage. The side sliding cabin door 18 can facilitate the entry and exit of pilots and passengers. The tailgate 19 is used for cargo loading and unloading, wherein the double-opening tailgate 19 is in the form of a large opening and is characterized by easy loading and unloading. During manned flight, pilots and passengers can enter the aircraft through the side sliding hatch 18; during cargo flight, the cargo can be loaded on the special pallet of the aircraft by opening the double-opening tail hatch 19, and lifted by forklifts, lift trucks, etc. on the ground. The lift platform loads or unloads the pallet from the aircraft, locks the pallet through the onboard floor locking mechanism, and the bulk cargo can be anchored and fixed through the mooring device.

The main wing 12 and the canard 13 are symmetrical about the fuselage axis. In a preferred embodiment of the present application, the area of the main wing 12 is larger than that of the canard wing 13 . Further, the number of ducted fan engines arranged on the upper surface of the main wing is greater than the number of ducted fan engines arranged on the upper surface of the canard.

The main wing 12 is a double vertical tail structure to provide stability for low-speed cruising. The main wing 12 is arranged on the upper part of the rear side of the fuselage 11, and a propulsion system composed of several ducted fan engines 14 is installed on the upper surface of each side of the main wing 12, and several ducted fan engines 14 are used to provide the aircraft. main thrust. Several ducted fan engines 14 are integrally designed with the main wing 12. When the main wing 12 is controlled to rotate, the ducted fan engines 14 on the main wing 12 can provide power for vertical take-off and landing.

The outer side of the main wing 12 is provided with an attitude control airfoil 142 along the chord length direction. By controlling the deflection of the attitude control airfoil 142 , the attitude of the main wing airfoil can be precisely adjusted. The tip end of the main wing 12 has a winglet 17, and the tail of the winglet 17 has a rudder 16. By setting the winglet 17, the lift can be increased, the reverse pressure gradient can be reduced, and the stall resistance of the aircraft can also be improved. horn.

The canards 13 are arranged on the front side of the fuselage 11 , a plurality of ducted fan engines 14 are installed on the upper surface of the canards 13 on each side, and ducted fan flaps 141 are arranged on the outside of the canards 13 along the chord length direction. , through the integrated design of several ducted fan engines and the canard 13, when the canard 13 is controlled to rotate, the ducted fan engine on the canard 13 can provide the power for vertical take-off and landing.

The ducted fan engines 14 are distributed multi-electric ducted fan engines, which are evenly installed on the trailing edge flaps of the main wing 12 and above the trailing edge of the canard 13 . The ducted fan engine 14 adopts a modular design and can be quickly installed and replaced. The ducted fan engine 14 tilts along with the main wing 12 and the canard 13 to realize power steering vertical take-off and landing.

The landing gear 15 is arranged at the bottom of the fuselage 11 , which can be a skid-type landing gear or a wheel-type landing gear, and is mainly used to support the aircraft.

When taking off and landing, the canard 13 and the main wing 12 are driven by the tilting mechanism device to drive the ducted fan engine to rotate to a state perpendicular to the ground, and the vertical take-off and landing function of the aircraft is realized through the flight control system and the power control system.

When flying horizontally, the canard 13 and the main wing 12 are driven by the tilting mechanism to drive the ducted fan engine to rotate to a state parallel to the ground, and the level flight and attitude control of the aircraft can be achieved through the attitude control airfoil and rudder on the main wing.

After simulation calculation, the aerodynamic shape of the aircraft of this application can meet the requirements of the following usage scenarios: the wingspan is about 7m, the empty weight is about 700kg, the commercial load is about 200kg, the cruising speed is about 220km/h, and the maximum level flight speed is about 260km/h. All-electric ducted fan power energy, the maximum range is about 200km, and the cruising altitude can reach 2km.

The tilting ducted fixed-wing aircraft of the present application can realize point-to-point rapid transportation of people/goods in the city, and has the ability of vertical take-off and landing and horizontal high-speed flight, compatible with the advantages of traditional helicopters and fixed-wing aircraft, and the conversion of vertical take-off and landing and horizontal flight modes It is simple and safe, and can also realize hovering flight function. According to different target tasks, it can be dedicated to carrying passengers, or it can also be equipped with a modular task load compartment to realize functions such as medical rescue and cargo, and realize multi-function and multi-scenario. application to provide a green, safe and feasible aircraft for urban air traffic.

The above are only specific embodiments 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 substitutions within the technical scope disclosed in the present application, All should be covered within the scope of protection of this application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims (8)

1. A tilting ducted fixed-wing aircraft, characterized in that the aircraft comprises: a fuselage (11), a main wing (12), a canard (13), a ducted fan engine (14) and a landing gear ( 15), wherein the fuselage (11) includes a cockpit at the front of the fuselage and a task load bay at the rear of the fuselage, the landing gear (15) is arranged at the bottom of the fuselage (11), and the main engine on each side is The upper surface of the wing (12) is provided with a number of ducted fan engines (14), and the upper surface of the canard (13) on each side is also provided with a number of ducted fan engines (14). The main wing (12) and The canard (13) can rotate relative to the fuselage along the axis of the wing. By controlling the rotation of the main wing (12) and the canard (13), the ducts on the main wing (12) and the canard (13) are controlled. The fan engine (14) rotates to a state perpendicular to the ground and a state parallel to the ground, thereby realizing vertical take-off and landing and horizontal flight during take-off and landing. 2 . The tilting ducted fixed-wing aircraft according to claim 1 , wherein the main wing ( 12 ) and the canard ( 13 ) are symmetrical about the fuselage axis. 3 . 3. The tilting ducted fixed-wing aircraft according to claim 2, wherein the area of the main wing (12) is larger than the area of the canard (13). 4. The described tilting ducted fixed-wing aircraft as claimed in claim 3, wherein the number of ducted fan engines (14) provided on the upper surface of the main wing (12) is more than the canard wing (13) The number of ducted fan motors (14) provided on the upper surface. 5. The tilting ducted fixed-wing aircraft according to any one of claims 1 to 4, wherein an attitude control along the chord length direction is provided along the outer side of the main wing (12) spanwise direction The airfoil (142), by controlling the deflection of the attitude control airfoil (142), realizes the precise fine adjustment of the attitude of the airfoil of the main wing. 6. The tilting ducted fixed-wing aircraft according to claim 5, wherein the tip end of the main wing (12) has a vertically arranged winglet (17), The tail of the winglet (17) has a rudder (16) along the fuselage direction. 7. The described tilting ducted fixed-wing aircraft as claimed in claim 1, characterized in that, along the outside of the canard (13) spanwise direction is provided with ducted fan flaps ( 141). 8. The tilting ducted fixed-wing aircraft according to claim 1, wherein the landing gear (15) comprises a wheeled landing gear and a sled-type landing gear.

Images