CN204250360U - Culvert type verts aircraft - Google Patents

Abstract

The utility model discloses a duct type tilting aircraft, which belongs to the field of aerospace. It includes a fuselage, a tail and a front wing, the front wings are symmetrically installed on both sides of the fuselage, and the tip of the front wing is equipped with a tiltable spiral wing that can rotate by 90°, and the fuselage A duct is arranged on the top, and ducted propellers are installed in the duct; ailerons are installed on the trailing edge of the front wing. During the tilting process of the wingtip propeller, the utility model increases the lift supply of the aircraft by increasing the rotational speed of the ducted propeller inside the fuselage, improves the safety, stability and reliability of the aircraft in the process of switching modes, and effectively reduces the rate of flight accidents . At the same time, by adjusting the rotation speed of the ducted propeller, it is also convenient to quickly adjust the flight attitude of the aircraft to adapt to different flight environments; the end cover is movably installed on the port of the duct, and the duct is closed in the cruise mode of the aircraft, which can reduce the Reduced flat flight resistance, improving flight speed and efficiency.

Description

ducted tilt aircraft

technical field

The utility model relates to a tilting aircraft, in particular to a duct type tilting aircraft, which belongs to the field of aerospace.

Background technique

At present, aircraft are mainly divided into two categories: helicopters and fixed-wing aircraft. Helicopters have superior low-speed and low-altitude performance, but low efficiency; fixed-wing aircraft have a large flight radius and high efficiency, but poor low-altitude and low-speed performance, and have higher requirements for airport conditions. Therefore, combining the advantages of these two types of aircraft to combine the vertical take-off and landing and hovering performance of helicopters and the high-speed cruise performance of fixed-wing aircraft has become the focus of current aircraft research.

In 2007, the U.S. Marine Corps began to equip the V-22 "Osprey" tilt-rotor aircraft jointly designed and manufactured by Bell and Boeing. Most of the V-22's body structure is made of new composite materials. Its two rotating propellers each have 3 blades, and the two rotors rotate in opposite directions and can be folded. The fixed wing of the V-22 is a cantilevered upper monoplane, constant profile, slightly forward-swept, and can be rotated by 90°. When the aircraft takes off and lands vertically, the rotor shaft is perpendicular to the ground, and it is in a horizontal helicopter flight state, and can hover in the air, fly back and forth and fly sideways; after the tilt rotor aircraft takes off and reaches a certain speed, the rotor shaft can move forward Tilting at an angle of 90°, it is in a horizontal state, and the rotor is used as a pulling propeller. At this time, the tilting rotor can fly at a higher speed for a long distance like a fixed-wing aircraft. The V-22 tiltrotor combines the advantages of helicopters and fixed-wing aircraft. It not only has the vertical take-off and landing and air hovering capabilities of ordinary helicopters, but also has the high-speed cruise flight capabilities of turboprop aircraft. However, accidents have occurred frequently since it was officially put into use, especially in the process of switching between helicopter mode and cruise mode, it is prone to insufficient lift, resulting in poor overall stability of the tiltrotor and causing flight accidents.

Utility model content

The technical problem to be solved by the utility model is to overcome the defects of the prior art, and provide a ducted tilting aircraft that can ensure the continuous supply of lift in the process of mutual conversion between the helicopter mode and the cruise mode, and ensure flight safety.

In order to solve the above-mentioned technical problems, the ducted tilting aircraft provided by the utility model includes a fuselage, a tail and a front wing, and the front wing is symmetrically installed on both sides of the fuselage, and the tip of the front wing A tiltable screw wing that can rotate by 90° is installed on the top, and it is characterized in that: a duct is arranged on the fuselage, and a ducted propeller is installed in the duct; an aileron is installed on the trailing edge of the front wing.

In the utility model, rear wings are installed symmetrically on both sides of the fuselage; tiltable helical wings that can rotate at 90° are installed on the wing tips of the rear wings, and ailerons are installed on the trailing edge of the rear wings. .

In the utility model, the duct is located between the front wing and the rear wing, and an end cover is movably installed on the port of the duct.

In the utility model, the tiltable screw wing includes a wingtip propeller, a nacelle, a drive motor, a connecting rod and a wing steering gear, the wingtip propeller is fixedly connected to the drive motor, and the drive motor is fixed in the nacelle. The cabin is connected to one end of the connecting rod, and the other end of the connecting rod is connected to the wing steering gear, and the wing steering gear controls the tilting of the nacelle through the connecting rod.

In the utility model, the ducted propellers are upper and lower pairs of coaxial counter-rotating propellers.

In the utility model, the tail includes a vertical tail and a flat tail, one end of the vertical tail is fixedly connected to the fuselage, and the other end is vertically connected to the flat tail; a rudder is installed on the vertical tail, and an elevator is installed on the flat tail.

The beneficial effects of the utility model are: (1), the utility model increases the lift supply of the aircraft by increasing the speed of the ducted propeller inside the fuselage during the tilting process of the wingtip propeller, thereby improving the safety of the aircraft in the transition mode process , stability and reliability, effectively reducing the rate of flight accidents; at the same time, by adjusting the speed of the ducted propeller, it is also convenient to quickly adjust the flight attitude of the aircraft to adapt to different flight environments; (2), by manipulating the front wing The steering gear inside the wingtip nacelle and the propeller can turn the aircraft from the helicopter/hover mode to the aircraft/cruising mode, which expands the application range of the aircraft; by tilting the rear wing wingtip nacelle, the aircraft can be further accelerated Flight mode conversion time and stability to ensure the flight safety of the aircraft; (3), the ducted propeller adopts two upper and lower coaxial reverse propellers, and different power supplies can be realized by adjusting the different speeds of the two common propellers, further improving The safety and stability of the aircraft in the flight mode conversion process; (4) install the end cover on the port of the duct, and close the duct under the cruise mode of the aircraft, which can reduce the level flight resistance and improve the flight speed and efficiency; (5), the aircraft of the utility model can take off and land vertically and can cruise at high speed, has low requirements for take-off and landing sites, and has a longer flight range than ordinary multi-rotor aircraft, and can be widely used in fields such as border reconnaissance and monitoring.

Description of drawings

Fig. 1 is the structure schematic diagram of the ducted tilting aircraft of the present invention;

Fig. 2 is a schematic diagram of the tilting process of the ducted tilting aircraft of the present invention;

Fig. 3 is a schematic diagram of the forward flight of the ducted tilting aircraft of the present invention;

Fig. 4 is the left side view of the ducted tilting aircraft of the present invention;

Fig. 5 is the front view of the ducted tilting aircraft of the present invention;

Fig. 6 is the left side view of the ducted tilting aircraft of the present invention when flying forward;

Fig. 7 is the structural diagram of the coaxial reverse ducted propeller of the utility model;

Fig. 8 is a structure diagram of the utility model wingtip tilting propeller;

Fig. 9 is a perspective view of the vertical state of the wingtip propeller of the present invention;

Figure 10 is a perspective view of the horizontal state of the utility model wingtip propeller;

Fig. 11 is the frame diagram of the utility model control system;

In the figure: 1-fuselage, 2-front wing, 3-bracket, 4-ducted propeller, 5-nacelle, 6-wing propeller, 7-fairing, 8-vertical tail, 9-horizontal tail, 10 -elevator, 11-rudder, 12-rear wing, 13-aileron, 14-landing gear, 15-duct end cover, 16-connecting rod, 17-connecting piece, 18-wing servo, 19-drive motor , 20-connecting rod.

Detailed ways

Below in conjunction with accompanying drawing, the utility model is described in further detail.

As shown in Figures 1, 4, 5 and 6, the ducted tilting aircraft of the present invention comprises a fuselage 1, the front left and right sides of the front of the fuselage 1 are respectively equipped with front wings 2, and the left and right sides of the rear of the fuselage 1 Rear wing 12 is installed respectively on both sides, and aileron 13 is all installed on the trailing edge of front wing 2, rear wing 12; Drive motor 19 is fixedly installed inside, and drive motor 19 is fixedly connected with wingtip propeller 6, and fairing 7 is installed on wingtip propeller 6 tops, and wingtip propeller 6 is 3 blades. Fuselage 1 top is provided with duct, and duct is positioned between front wing 2, rear wing 12, and duct propeller 4 is fixedly installed in duct by frame 3; Aircraft control system; the drive nacelle 5 is controlled by the wing steering gear 18 (not shown) in the wing, and can rotate between the horizontal position and the vertical position (that is, turn 90° to the forward direction of the aircraft), thereby driving the wing Pointed propeller 6 tilts. In this embodiment, all drive motors are brushless motors.

The tail includes a vertical tail 8 and a flat tail 9. One end of the vertical tail 8 is fixedly connected to the fuselage 1, and the other end is connected to the horizontal tail 9. The vertical tail 8 is perpendicular to the fuselage 1 and the flat tail 9. The rear portion of the vertical tail 8 is provided with a rudder 11. 11 connects the steering gear, and the steering gear is connected to the control system; the elevator 10 is installed at the rear of the flat tail 9, and the elevator 10 is connected and controlled by the steering gear, and the steering gear is electrically connected to the control system.

Landing gear 14 is installed on the fuselage 1 bottom.

As shown in Fig. 2, when the aircraft is converted from the helicopter mode to the cruising mode, the steering gear drives the nacelle 5 to tilt forward by 90°.

As shown in Figure 3, the end cap 15 is movably installed on the port of the duct, and the end cap 15 can close the duct when the aircraft is in cruise mode, reducing the resistance of the aircraft when it is in level flight, and improving the flight speed and efficiency.

As shown in Figure 7, the ducted propeller 4 is two pairs of coaxial counter-rotating propellers up and down, both of which are driven by independent motors. The frame 3 includes connecting rods 16 and connectors 17; The connecting rods 16 and the connecting pieces 17 are connected to each other and fixed in the duct of the fuselage 1 .

As shown in Figures 8 and 9, the nacelle 5 is connected to the wing steering gear 18 through the connecting rod 20, the connecting rod 20 is supported on the wing, and the wing steering gear 18 is arranged in the wing to control the tilting of the nacelle 5, Rotate between the horizontal position and the vertical position (that is, rotate 90° toward the forward direction of the aircraft), thereby driving the wingtip propeller 6 to tilt.

As shown in FIG. 11 , an aircraft power plant is installed inside the fuselage 1 , and the control system includes a flight control board, a power supply module, an electronic governor and various control modules. Wherein, the flight control board is respectively connected to control two driving motors of the ducted propeller and the driving motors of four wingtip propellers 6 through the electronic governor; The vertical tail steering gear, the horizontal tail steering gear of the horizontal tail 9 and the wing steering gear used to respectively control the tilting of the 4 wing tip propellers 6,

When this duct type tilting aircraft takes off, the nacelle 5 on the wingtips on both sides of the front wing 2 and the rear wing 12 is perpendicular to the ground, and the end cover 14 of the duct on the fuselage 1 is opened, and the front wing 2, the rear wing The aileron 12 on the wing 12 is put down, and driven by the motor, the electronic transmission controls the speed to make the ducted propeller 4 and the 4 wingtip propellers 6 run. When reaching a certain speed, the lift generated is greater than the weight of the aircraft itself, and the aircraft takes off vertically. At this time, the steering gear end of the connecting rod 20 is located at the No. 1 position of the steering gear, as shown in FIG. 9 . When the aircraft reaches the predetermined height and turns from the helicopter mode to the cruise mode, the four nacelles 5 are driven to tilt forward at the same time through the wing steering gear 18, and the speed of the propeller 4 inside the fuselage is increased through the electronic transmission during the tilting process. Increase the lift to make up for the loss of lift during the tilting process and ensure the stability and safety of the aircraft during the tilting process. When the nacelle 5 is tilted forward to 90° (that is, the steering gear end of the connecting rod 20 is rotated to the No. 2 position, and the nacelle 5 is parallel to the ground), the aircraft starts to fly forward, and the aileron 12 starts to be lifted. After the speed, the front wing 2 and the rear wing 12 produce enough lift to balance the aircraft's own weight, and the internal road propeller 4 of the fuselage stops working, and the end cover 14 is closed to reduce resistance. At the same time, by manipulating the rudder 11 and the elevator 10 to adjust the flight attitude of the aircraft, better maneuverability of the aircraft can be achieved.

The above is only a preferred embodiment of the utility model, it should be pointed out that for those of ordinary skill in the art, some improvements can be made without departing from the principle of the utility model, and these improvements should also be regarded as Protection scope of the present utility model.

Claims (6)

1. a culvert type verts aircraft, comprise fuselage (1), tail and front wing (2), described front wing (2) symmetry is arranged on fuselage (1) both sides, on the wing tip of described front wing (2) all install can 90 ° rotate verted screw wings, it is characterized in that: described fuselage (1) is provided with duct, in duct, shrouded propeller (4) is installed; Described front wing (2) trailing edge installs aileron (13).

2. culvert type according to claim 1 verts aircraft, it is characterized in that: described fuselage (1) bilateral symmetry install after wing (12); The wing tip of described rear wing (12) is all installed can the verted screw wing that rotates of 90 ° of degree, and described rear wing (12) trailing edge installs aileron (13).

3. culvert type according to claim 2 verts aircraft, it is characterized in that: described duct is positioned between front wing (2) and rear wing (12), movablely on the port of described duct installs end cap (15).

4. the culvert type according to any one of claims 1 to 3 verts aircraft, it is characterized in that: the described screw wing that verts comprises wing tip screw propeller (2), nacelle (5), drive motor (19), connecting rod (20) and wing steering wheel (18), described wing tip screw propeller (2) is fixedly connected with drive motor (19), drive motor (19) is fixed in nacelle (5), nacelle (5) connects one end of connecting rod (20), the other end of connecting rod (20) is connected with wing steering wheel (18), described wing steering wheel (18) controls nacelle (5) by connecting rod (20) and verts.

5. culvert type according to claim 4 verts aircraft, it is characterized in that: described shrouded propeller (4) is upper and lower two secondary contrarotating propellers.

6. culvert type according to claim 5 verts aircraft, it is characterized in that: described tail comprises vertical fin (8) and horizontal tail (9), described vertical fin (8) one end is fixedly connected with fuselage (1), and the other end is connected with horizontal tail (9) is vertical; The upper installation direction rudder (11) of described vertical fin (8), horizontal tail (9) is installed elevating rudder (10).