CN212951108U

CN212951108U - Variable-diameter unmanned tilt rotorcraft

Info

Publication number: CN212951108U
Application number: CN202021830506.2U
Authority: CN
Inventors: 吴伟伟; 马存旺; 孙凯军; 汪艳伟; 汪洋
Original assignee: Rainbow UAV Technology Co Ltd
Current assignee: Rainbow UAV Technology Co Ltd
Priority date: 2020-08-27
Filing date: 2020-08-27
Publication date: 2021-04-13
Anticipated expiration: 2030-08-27

Abstract

The utility model relates to a become unmanned gyroplane that verts of diameter belongs to aircraft design technical field. The unmanned tilt rotor aircraft comprises a front wing and a rear wing, wherein two ends of the front wing and two ends of the rear wing are respectively provided with a set of rotor wings, and the number of the rotor wings is four, the rotor wings are of variable-diameter structures, and when the tilt rotor aircraft works in a helicopter mode for flying, the rotor wings are in a vertical large-diameter state; when the tilt rotor aircraft works in a fixed wing mode and flies horizontally, the rotor is in a horizontal small-diameter state. The utility model provides a problem of ordinary vert gyroplane in that helicopter mode flight oar dish load is big, hover inefficiency, the inefficiency of cruising when fixed wing mode flight.

Description

Variable-diameter unmanned tilt rotorcraft

Technical Field

The utility model relates to an aircraft design technical field, it is concrete, relate to an unmanned gyroplane that verts of variable diameter.

Background

The tilt rotor aircraft is an aircraft which can take off and land vertically and fly forwards at high speed, combines the advantages of a helicopter and a fixed-wing aircraft, has the characteristics of capability of taking off and landing vertically, high flying speed and long endurance time, and has good military and civil application prospects, for example, a large number of arming forces of V-22 developed in the United states. However, because the design of the rotor system needs to give consideration to both helicopter mode flight and fixed-wing mode flight, but the two modes of flight are different or even contradictory to the design requirements of the rotor system, a larger rotor disc diameter is needed during helicopter mode flight, and a smaller rotor disc diameter is needed during fixed-wing mode flight, so that the tilt rotor aircraft rotor system needs to be balanced during design, resulting in performance inferior to that of a helicopter, such as hovering efficiency, lift limit and the like, during helicopter mode flight, and performance inferior to that of a common fixed-wing aircraft, such as maximum speed, voyage and the like, during fixed-wing mode flight. In addition, the tilting rotor aircraft has many rotating parts, including an engine, a speed reducer, a transmission shaft, a rotor wing and the like, vibration coupling is performed between each moving part and the aircraft body, and the vibration characteristic of the whole aircraft is complex.

SUMMERY OF THE UTILITY MODEL

The utility model provides a technical problem be: the defects of the prior art are overcome, the hybrid power variable-diameter unmanned tilting rotorcraft is provided, a rotor system of the hybrid power variable-diameter unmanned tilting rotorcraft is in an extended large-diameter state when hovering, and is in a contracted small-diameter state when cruising, and the problems that an ordinary tilting rotorcraft is large in load of a helicopter mode flight propeller disc, low in hovering efficiency and low in cruising efficiency in a fixed wing mode are solved.

The technical scheme of the utility model is that: the diameter-variable unmanned tilting rotorcraft comprises a front wing and a rear wing, wherein two sets of rotors are respectively arranged at two ends of the front wing and the rear wing, the number of the rotors is four, the rotors are of diameter-variable structures, and when the tilting rotorcraft works in a helicopter mode for flying, the rotors are in a vertical large-diameter state; when the tilt rotor aircraft works in a fixed wing mode and flies horizontally, the rotor is in a horizontal small-diameter state.

The rotor comprises a rotor shaft, a motor and N variable-diameter blade assemblies, wherein N is more than or equal to 3;

each variable-diameter blade assembly comprises a hub, a screw fixing piece, a pull pipe, a blade airfoil section and a blade inner section;

paddle inner segment one end fixed mounting is on the propeller hub, another pot head is in the paddle airfoil section, can remove for the paddle airfoil section, the propeller hub is installed on rotor shaft lateral wall, the motor is arranged at rotor shaft inside, the screw rod of driving N variable diameter paddle subassemblies simultaneously rotates, the screw rod is located the paddle inner segment, the one end and the paddle inner segment of screw rod pass through the screw rod mounting and are connected, the screw rod can be rotatory around screw rod mounting center pin, the other end of screw rod is located the trombone slide inside, pass through threaded connection with the trombone slide, the trombone slide links firmly with paddle airfoil section, screw rod forward or reverse rotation, the control trombone slide is outside or inside to be removed, and then the extension or the shrink of control airfoil section.

The variable diameter blade assembly is configured such that the blades extend when flying in helicopter mode and retract when flying in fixed wing mode, such that the extended rotor diameter is 1.71 times the retracted rotor diameter.

The front wing and the rear wing are both arranged above the fuselage and are in smooth transition with the fuselage.

The front wing is provided with a front aileron and a front flap wing which are opposite to two sides of the fuselage, and the rear wing is provided with a rear aileron and a rear flap wing which are opposite to two sides of the fuselage, and both of the front ailerons and the rear flap wings deflect downwards when the helicopter flies in a helicopter mode.

Each rotor is driven by an electric motor in a separate motor compartment.

The motor nacelle tilts with the rotor.

The variable-diameter unmanned tilt rotor aircraft further comprises an engine, a generator, energy storage equipment and a power cable;

the engine drives the generator to generate power and transmit the power to the energy storage equipment, the electric energy is transmitted to the motor cabin through the power cable, and the motor in the motor cabin drives the rotor wing to rotate to generate pulling force.

The engine is a turbine engine.

The diameter-variable unmanned tilt-rotor aircraft further comprises an empennage, and a heading is arranged on the empennage and used for controlling the fixed wing mode during flat flight.

Compared with the prior art, the utility model beneficial effect does:

(1) the utility model adopts the variable-diameter rotor wing, realizes the large rotor wing diameter in the hovering state and the small rotor wing diameter in the flat flying state by changing the diameter of the rotor wing, improves the flying efficiency in the helicopter mode and the fixed wing mode, reduces the required take-off power and improves the take-off weight and the flight range during voyage compared with the prior method for fixing the diameter of the rotor wing;

(2) the utility model adopts the hybrid power system, the engine drives the generator to generate electricity and supply power to each motor through the power cable, and the motor is directly supplied with power to drive the rotor wing through the oil-electricity hybrid power, thereby saving complex mechanical transmission parts, improving the flight performance and simultaneously reducing the vibration level of the whole aircraft;

(3) the utility model discloses a four sets of rotor systems, it is better to adopt two sets of rotor systems to take off and land stage stability with ordinary rotor aircraft that verts, and anti-wind ability reinforce does benefit to the application under the strong wind condition.

Drawings

Fig. 1 is an isometric test chart of a vertical flight state according to an embodiment of the present invention;

fig. 2 is an isometric test chart of a level flight state according to an embodiment of the present invention;

FIG. 3 is a layout diagram of the equipment in the embodiment of the present invention;

fig. 4 shows the components of the variable diameter rotor part according to the embodiment of the present invention.

Detailed Description

The present invention will be further explained with reference to the following examples.

The utility model provides a unmanned gyroplane that verts of hybrid variable diameter takes off weight 1400kg, including 4 rotor 1, motor-driven cabin 2, fuselage 4, front wing 3, rear wing 11, fin 14, nose landing gear 7, main landing gear 8 and built-in equipment. The front wing 3 and the rear wing 11 are respectively arranged at the front part and the rear part of the fuselage 4. Rotor 1 is mounted on motor nacelle 2. The rotor wing 1 and the motor cabin 2 are respectively arranged at the wingtips of the front wing 3 and the rear wing 11 and can rotate around a fixed shaft thereof, and the conversion between a helicopter mode and a fixed wing mode is realized by controlling the rotating angle. The rotor 1 provides lift in helicopter mode and tension in fixed wing mode. The front and rear wings 3, 11 provide lift in the fixed wing mode. The tail fin 14 is disposed at the rear of the body 4. The nose landing gear 7 and the main landing gear 8 are arranged on the lower part of the fuselage.

The two ends of the front wing 3 and the rear wing 11 are respectively provided with a set of rotor wings 1, four rotor wings in total, the rotor wings 1 are of variable-diameter structures, and when the tilt rotor aircraft works in a helicopter mode for flying, the rotor wings are in a vertical large-diameter state, as shown in figure 1; when the tiltrotor aircraft is operated in a fixed-wing mode and flies horizontally, the rotor is in a horizontal small-diameter state, as shown in fig. 2.

The engine 22 drives the generator 21 to generate electricity and transmit the electricity to the energy storage device 20, the electricity is transmitted to the motor cabin 2 through the power cable 19, and the motor in the motor cabin 2 drives the rotor 1 to rotate to generate pulling force. Each rotor is driven by an electric motor in a separate motor compartment 2.

The energy storage device 20 provides extra power when the unmanned aerial vehicle needs larger power (such as in a takeoff and climb phase), absorbs the extra power in a cruise phase of the unmanned aerial vehicle, and plays a role in power allocation, so that the engine 22 serving as a source power always works in an optimal state; the heat management device 23 is a cooling and heat dissipation management system for each part of the power system, and good cooling can reduce the operating temperature of the motor and improve efficiency.

As shown in fig. 3, the built-in devices include a task device 16, an avionic device 17, a fuel system 18, a power cable 19, an energy storage device 20, a generator 21, an engine 22, and a thermal management device 23; the mission equipment 16 is arranged at the front part of the fuselage 4, the avionic equipment 17 is arranged behind the mission equipment, the fuel system 18 is arranged in the middle of the fuselage 4, the energy storage equipment 20, the generator 21 and the engine 22 are sequentially arranged behind the fuel system, and the thermal management equipment 23 is arranged at the rear part of the fuselage 4.

As shown in fig. 4, the rotor includes a rotor shaft 28, a motor 24, and N variable diameter blade assemblies, N being equal to or greater than 3.

Each variable-diameter blade component adopts a rigid blade design and comprises a hub 25, a screw 26, a screw fixing piece 27, a pull pipe 29, a blade airfoil section 6 and a blade inner section 5;

one end of the blade inner section 5 is fixedly installed on a hub 25, the other end of the blade inner section is sleeved in the blade airfoil section 6 and can move relative to the blade airfoil section 6, the hub 25 is installed on the side wall of a rotor shaft 28, a motor 24 is arranged in the rotor shaft 28 and drives screws 26 of N variable-diameter blade assemblies to rotate simultaneously, the screws 26 are located in the blade inner section 5, one end of each screw 26 is connected with the blade inner section 5 through a screw fixing piece 27, each screw 26 can rotate around the central shaft of the screw fixing piece 27, the other end of each screw 26 is located in a pull pipe 29 and is in threaded connection with the pull pipe 29, the pull pipe 29 is fixedly connected with the blade airfoil section 6, the screws 26 rotate forwards or reversely to control the pull pipe 29 to move outwards or inwards and further control the extension or contraction of the airfoil section 6, so that the variable-diameter blades move in variable-pitch relative to the hub 25. The hub 25 is also capable of rotating the variable diameter blades relative to the rotor shaft 28.

Typically, each rotor set contains 3 variable diameter blades, which extend in helicopter mode flight with a rotor diameter of 3.6m and retract in fixed wing mode flight with a rotor diameter of 2.1m, the extended rotor diameter being 1.71 times the rotor diameter in the retracted state.

Preferably, both the front wing 3 and the rear wing 11 are arranged above the fuselage and are in smooth transition with the fuselage, the wingspan of the front wing 3 is 3.7m, the wingspan of the rear wing 11 is 4.2m, and meanwhile, the vertical position of the front wing 3 is lower than that of the rear wing 11.

Preferably, the front wing 3 is provided with a front aileron 9 and a front flap 10, and the rear wing 11 is provided with a rear aileron 12 and a rear flap 13, both of which are deflected downwards in helicopter mode flight.

Preferably, the motor nacelle 2 tilts with the rotor 1, the tilting angle ranging from 0 ° to 95 °.

Preferably, a rudder 15 is arranged on the rear wing 14 for controlling the heading when the fixed wing mode is flat, for example, when the aircraft head deviates to the right, the rudder 14 deflects to the left to generate a lateral force to the right, and when a yaw moment to the left is added around the center of gravity of the aircraft, the aircraft head deflects to the left to return the aircraft to the original heading.

Preferably, the engine 22 is a turboshaft engine.

Compare with conventional rotor unmanned aerial vehicle that verts, the utility model discloses a variable diameter rotor, the demand power that hovers descends about 30%, and efficiency of hovering improves about 10%, and the efficiency of cruising when preceding flying can improve more than 10%, and the power of cruising is showing and is descending. The motor of hybrid power is adopted to drive the rotor wing, mechanical moving parts are greatly reduced, the reliability of the whole machine is improved, vibration sources mainly come from an engine and the rotor wing and are mutually independent and not coupled, and therefore the vibration level of the whole machine is greatly reduced.

The present invention is described in an example of the specific application of the field, but any person skilled in the art should understand that the present invention includes but is not limited to the example, and any modification made on the basis of the above description is within the scope of the present invention.

Claims

1. The utility model provides a become unmanned rotorcraft that verts of diameter which characterized in that: the aircraft comprises a front wing (3) and a rear wing (11), wherein two ends of the front wing (3) and two ends of the rear wing (11) are respectively provided with a set of rotors, the number of the rotors is four, the rotors (1) are of variable-diameter structures, and when the tilt rotor aircraft works in a helicopter mode for flight, the rotors are in a vertical large-diameter state; when the tilt rotor aircraft works in a fixed wing mode and flies horizontally, the rotor is in a horizontal small-diameter state.

2. The variable diameter unmanned tiltrotor aircraft of claim 1, wherein: the rotor comprises a rotor shaft (28), a motor (24) and N variable diameter blade assemblies, N being greater than or equal to 3;

each variable diameter blade assembly comprises a hub (25), a screw (26), a screw fixing piece (27), a pull pipe (29), a blade airfoil section (6) and a blade inner section (5);

one end of the blade inner section (5) is fixedly arranged on a propeller hub (25), the other end of the blade inner section is sleeved in the blade airfoil section (6) and can move relative to the blade airfoil section (6), the propeller hub (25) is arranged on the side wall of a rotor shaft (28), a motor (24) is arranged in the rotor shaft (28), simultaneously drives the screws (26) of the N variable-diameter paddle components to rotate, the screws (26) are positioned in the inner paddle sections (5), one end of each screw (26) is connected with the inner paddle sections (5) through a screw fixing piece (27), the screws (26) can rotate around the central shaft of the screw fixing pieces (27), the other ends of the screws (26) are positioned in the pull tubes (29), and the pull pipe (29) is connected with the pull pipe (29) through threads, the pull pipe (29) is fixedly connected with the blade airfoil section (6), the screw (26) rotates forwards or reversely, the pull pipe (29) is controlled to move outwards or inwards, and then the extension or contraction of the blade airfoil section (6) is controlled.

3. A variable diameter unmanned tiltrotor aircraft according to claim 2, wherein the variable diameter blade assembly is extended when the blades are in helicopter mode flight and shortened when the blades are in flat flight in fixed wing mode, such that the extended rotor diameter is 1.71 times the shortened rotor diameter.

4. The variable diameter unmanned tiltrotor aircraft of claim 1, wherein: the front wing (3) and the rear wing (11) are both arranged above the fuselage and are in smooth transition with the fuselage.

5. The variable diameter unmanned tiltrotor aircraft of claim 1, wherein: the front wing (3) is provided with a front aileron (9) and a front flap (10) which are respectively opposite to two sides of the fuselage (4), the rear wing (11) is provided with a rear aileron (12) and a rear flap (13) which are respectively opposite to two sides of the fuselage (4), and the front aileron and the rear flap both deflect downwards when flying in a helicopter mode.

6. The variable diameter unmanned tiltrotor aircraft of claim 1, wherein: each rotor is driven by an electric motor in a separate motor nacelle (2).

7. The variable diameter unmanned tiltrotor aircraft of claim 6, wherein: the motor cabin (2) tilts along with the rotor wing (1).

8. The variable diameter unmanned tiltrotor aircraft according to any one of claims 1 to 7, wherein: the power generation system also comprises an engine (22), a generator (21), energy storage equipment (20) and a power cable (19);

the engine (22) drives the generator (21) to generate electricity and transmit the electricity to the energy storage device (20), the electricity is transmitted to the motor cabin (2) through the power cable (19), and the motor in the motor cabin (2) drives the rotor (1) to rotate to generate pulling force.

9. The variable diameter unmanned tiltrotor aircraft of claim 8, wherein: the engine (22) is a turbine engine.

10. A variable diameter unmanned tilt rotor aircraft according to claim 8, further comprising a tail wing (14), said tail wing (14) having a rudder (15) disposed thereon for controlling the heading when flying in a fixed wing mode.