CN218806534U

CN218806534U - Rotor wing front-back staggered tilt rotor wing machine and control system thereof

Info

Publication number: CN218806534U
Application number: CN202222953538.7U
Authority: CN
Inventors: 邵平; 施黎鸣; 季鹏宇
Original assignee: Brick Fly Shanghai Aviation Technology Co ltd
Current assignee: Brick Fly Shanghai Aviation Technology Co ltd
Priority date: 2022-11-07
Filing date: 2022-11-07
Publication date: 2023-04-07
Anticipated expiration: 2032-11-07

Abstract

The utility model provides a rotor front and back staggered tilt gyroplane and control system thereof, wherein, the rotor front and back staggered tilt gyroplane includes fuselage, wing, fin, undercarriage and the rotor that verts, wherein, the rotor that verts is a plurality of, and two rows around arranging by the way around being staggered on the wing, every rotor that verts includes the mechanism that verts that rotor and drive rotor vert, the mechanism drive rotor that verts of the rotor of the front-seat row upwards verts, the mechanism drive rotor that verts of the rotor that verts of back-seat row verts downwards. The utility model discloses compromise the efficiency of aircraft under the rotorcraft that verts hovers and the state of cruising, possessed comparatively succinct structure, be favorable to the attitude control of aircraft, the design of flight control software and aircraft overall structure's design, be convenient for arrange bigger more excellent rotor system.

Description

Rotor wing front-back staggered tilt rotor wing machine and control system thereof

Technical Field

The utility model belongs to the technical field of the aircraft, a gyroplane verts is related to, concretely relates to staggered gyroplane and control system verts around rotor.

Background

The types of conventional aircraft are divided into fixed-wing aircraft and rotorcraft. Fixed wing aircraft technology is mature, fast, far voyage, large capacity, but requires a longer runway during takeoff or descent. Gyroplanes may not require airstrips to provide vertical take-off and landing in narrow take-off and landing areas, but have slower flight speed and shorter range.

Tilt rotor aircraft not only possess the gyroplane can conveniently carry out the function of VTOL in a flexible way and also compromise the performance that fixed wing aircraft speed is high, the voyage is far away simultaneously. However, the mechanical structure of the tilt rotor aircraft with the conventional structure is extremely complex, the power output and the attitude of the aircraft need to be controlled by two sets of complex periodic pitch systems which are the same as the helicopter, a special transmission shaft is needed to keep the synchronous consistency of the output of the left and right sets of rotor systems, and the difficulty of operation and maintenance is far higher than that of a common aircraft, so that the tilt rotor aircraft is not yet civilized.

Unmanned aerial vehicle and electronic VTOL aircraft develop rapidly in recent years, also emerge at present a batch electronic rotor product that verts.

The following are electric tiltrotor aircraft which have been newly developed and yet to be put into production and applied worldwide:

1. the hexagonal rotor layout tilt rotorcraft developed by Joby Aviation corporation has the following features and deficiencies:

(1) The novel JobyS4 tilting mechanism has more tilting mechanisms, the overall structure is heavier, and the weight of the novel JobyS4 reaches 2.4 tons;

(2) The tilting structure is more complex, and two different tilting mechanisms, four wingtip tilting mechanisms and two forward extending rod tilting mechanisms are provided, so that the manufacturing cost is higher, and the use and maintenance are more complex;

(3) The design of the whole airplane is limited more, the positions of the rotor wings need to be considered more, and a symmetrical hexagonal structure is formed, so that the airplane body is designed to be thick and short, and is difficult to design into a more optimized fixed-wing airplane body;

(4) The four tilting motors on the outer sides of the main wing and the empennage have larger areas to be overlapped with the outer sides of the wings, so that the outer sides of the wings are negatively affected by downwash airflow.

2. Tilting rotorcraft with 6 rotors in front and back rows developed by Wisk Aero and Archer Aviation respectively has the following characteristics and disadvantages:

(1) The number of rotor wing brackets is large, so that the structural weight and the wind resistance are increased, and the cruising pneumatic efficiency is influenced;

(2) The front rotor and the rear rotor are different (fixed after forward tilting), so that a flight control algorithm is more complex, the attitude control force on the airplane is lower in the attitude conversion process, and the airplane is easy to lose control when the conditions such as strong crosswind and the like occur;

(3) Too many rotors result in too dense a rotor arrangement, which in turn reduces the overall rotor disc area, resulting in higher rotor disc loads during the vertical takeoff and landing and hovering phases of the aircraft, reducing the flight efficiency at this phase.

In view of the above, those skilled in the art will be able to develop a tiltrotor aircraft with a novel rotor layout to optimize and overcome the above-mentioned deficiencies of the prior art tiltrotor aircraft.

SUMMERY OF THE UTILITY MODEL

The utility model relates to a solve above-mentioned problem and go on, aim at provides a rotor around staggered formula rotorcraft that verts and control system thereof.

The utility model provides a staggered tilt rotorcraft around rotor, including fuselage, wing, fin, undercarriage and the rotor that verts, have such characteristic: the rotor that verts is a plurality of to be arranged into two rows in the front and back to the place of leaving right before being on the wing, every verts the rotor and includes the rotor and drives the mechanism that verts that the rotor verts, and the mechanism that verts of the rotor that verts of the preceding row drives the rotor and upwards verts, and the mechanism that verts of the rotor that verts of the back row drives the rotor and verts downwards.

The utility model provides an in the rotor front and back staggered tilt rotor aircraft, can also have such characteristic: the front row of tilting rotors are arranged at the outer side of the front edge of the wing, and the rear row of tilting rotors are arranged at the inner side of the rear edge of the wing.

The utility model provides an in the rotor front and back staggered tilt rotor aircraft, can also have such characteristic: the front row of tilting rotors are arranged at the inner side of the front edge of the wing, and the rear row of tilting rotors are arranged at the outer side of the rear edge of the wing.

The utility model provides an in the rotor front and back staggered tilt rotor aircraft, can also have such characteristic: the front row tilting rotor and the rear row tilting rotor are respectively two.

The utility model provides an in the rotor front and back staggered tilt rotor aircraft, can also have such characteristic: every rotor that verts still includes the vaulting pole, and the mechanism that verts passes through the vaulting pole to be connected with the wing, and the vaulting pole of the rotor that verts of front-row sets up forward along the direction that is on a parallel with the fuselage, and the vaulting pole of the rotor that verts of back-row sets up backward along the direction that is on a parallel with the fuselage.

The utility model provides an in the rotor front and back staggered tilt rotor aircraft, can also have such characteristic: the wing includes a main wing and an aileron.

The utility model provides an in the rotor front and back staggered tilt rotor aircraft, can also have such characteristic: the rear wings include a horizontal rear wing having an elevator and a vertical rear wing having a rudder.

The utility model also provides a staggered tilt gyroplane's control system around the rotor has such characteristic, include: the flight control system is used for controlling ailerons of the wings, control surfaces of the empennage, rotors of the tilting rotors and the tilting mechanism.

The utility model provides an among the control system of formula tilt rotor aircraft staggers around the rotor, still have such characteristic: the flight control system is used for controlling the tilt rotor aircraft with the rotors staggered front and back in a fixed wing mode, a tilt transition mode, a hovering vertical take-off and landing mode, a left yaw mode and a right yaw mode; all tilt when the rotor is in fixed-wing mode

The rotor wing of the rotor wing is driven by the tilting mechanism to be in a vertical posture; when the tilt rotor aircraft with the rotors staggered front and back is in a tilt transition 5 mode, the tilt mechanisms of all tilt rotors synchronously drive the rotors to tilt at the same angular speed; staggered tilting type rotor wing

When the gyroplane is in a hovering vertical take-off and landing mode, the rotors of all the tilting rotors are in a horizontal posture under the driving of the tilting mechanisms; when the rotor wing front-back staggered tilt rotor aircraft is deflected leftwards, the tilt mechanism of the tilt rotor wing positioned on the front row of the left wing drives the rotor wing to tilt backwards slightly, the tilt mechanism of the tilt rotor wing positioned on the back row of the left wing drives the rotor wing to tilt forwards slightly, and meanwhile, the tilt mechanism is positioned on the back row of the left wing

The tilting mechanism of the tilting rotor wing in the front row of the right wing drives the rotor wing to tilt forward slightly, and the tilting mechanism of the tilting rotor wing 0 in the rear row of the right wing drives the rotor wing to tilt backward slightly; when the rotary wing is staggered back and forth and the rotary wing tilts the rotary wing aircraft to the right, the rotary wing is positioned on the left

The tilting mechanism driving rotor wing of the tilting rotor wing of the front wing row tilts forward slightly, the tilting mechanism driving rotor wing of the tilting rotor wing of the back wing row on the left side tilts backward slightly, the tilting mechanism driving rotor wing of the tilting rotor wing of the front wing row on the right side tilts backward slightly, and the tilting mechanism driving rotor wing of the tilting rotor wing of the back wing row on the right side tilts forward slightly.

The utility model provides an among the control system of the formula of staggering verting gyroplane around the rotor, still have such characteristic: when the 5-rotor forward-backward staggered tilt rotor aircraft is in a fixed wing mode, the attitude control of the aircraft is realized by the control surfaces of the ailerons and the empennage of the wings

The implementation is carried out; when the tilt rotor aircraft with the staggered rotors is in a tilt transition mode, the attitude control of the aircraft is realized through the difference of the rotating speeds of the ailerons of the wings, the control surface of the empennage and the rotors of the tilt rotors; when the rotor wing front and back staggered type tilting rotor aircraft is in a hovering vertical take-off and landing mode, the attitude control of the aircraft is realized through the difference of the rotating speed of the rotor wing of the tilting rotor wing.

Action and effect of the utility model

0 according to the utility model relates to a staggered formula rotorcraft that verts around rotor and control system thereof because with the slope on the wing

The rotor sets to two rows in the front and back to the front bank verts the rotor and is staggered arrangement around with the back row verts the rotor, so, the utility model has the advantages of it is following:

(1) Simultaneously, the efficiency of the tilt rotor aircraft under hovering and cruising states is considered, and all tilt rotors under any working state are ensured

The rotor wings work, so that the overall power system of the airplane can be kept in a state with higher efficiency all the time;

5 (2) the airplane is ensured to have a simpler structure, the structural weight and the overall aerodynamic performance of the airplane are favorably reduced, and meanwhile, the airplane is ensured to have more compact structure

The manufacturing, using and maintenance of the airplane are facilitated;

(3) The attitude control of the airplane is facilitated, the strong attitude control effect is ensured under the vertical take-off and landing hovering, attitude conversion and fixed wing cruising states, and the airplane has extremely high safe flight performance;

(4) The design of flight control software of the airplane is facilitated, the design difficulty of the flight control software is reduced, the control 0 effect of the flight control software is improved, and excellent robustness can be achieved;

(5) The overall structural design of the aircraft is facilitated, the overall structural design of the aircraft cannot be influenced due to the structural problems of arrangement of the tilt rotor and the power device, and the overall structure of the aircraft can be designed and optimized more conveniently;

(6) The rotor wing system is convenient to arrange, larger and better, the airplane is ensured to have larger propeller disk area and lower propeller disk load, and the airplane has abundant power output and excellent flight performance in the aspects of lifting hovering and vertical take-off and landing.

Drawings

Fig. 1 is a schematic perspective view of a tilt-rotor aircraft with front and rear staggered wings in a fixed-wing mode according to embodiment 1 of the present invention;

fig. 2 is a top view of a tiltrotor aircraft with front-rear staggered wings according to embodiment 1 of the present invention in a fixed-wing mode;

fig. 3 is a side view of a tiltrotor aircraft with front-rear staggered wings according to embodiment 1 of the present invention in a fixed-wing mode;

fig. 4 is a front view of a tilt-rotor aircraft with front-back staggered rotor wings in a fixed-wing mode according to embodiment 1 of the present invention;

fig. 5 is a schematic perspective view of a tilt-rotor aircraft with front and back staggered wings in tilt transition mode according to embodiment 1 of the present invention;

fig. 6 is a top view of a tiltrotor aircraft with front-back staggered wings in tilting transition mode according to embodiment 1 of the present invention;

fig. 7 is a side view of a tiltrotor aircraft with front-back staggered wings in tilt transition mode according to embodiment 1 of the present invention;

fig. 8 is a front view of a tiltrotor aircraft with front-back staggered wings in tilting transition mode according to embodiment 1 of the present invention;

fig. 9 is a schematic perspective view of a tilt-rotor aircraft with front-back staggered wings in a hovering vertical takeoff and landing mode according to embodiment 1 of the present invention;

fig. 10 is a top view of a tiltrotor aircraft with front-rear staggered rotor wings in a hovering vertical takeoff and landing mode according to embodiment 1 of the present invention;

fig. 11 is a side view of a tiltrotor aircraft with staggered front and back rotor wings in a hover vertical take-off and landing mode according to embodiment 1 of the present invention;

fig. 12 is a front view of a tiltrotor aircraft with front-rear staggered wings in a hovering vertical takeoff and landing mode according to embodiment 1 of the present invention;

fig. 13 is a plan view of a tilt-rotor aircraft with front-rear staggered rotor wings according to embodiment 1 of the present invention, when the aircraft is yawing leftward;

fig. 14 is a left side view of a tiltrotor aircraft with front-rear staggered wings according to embodiment 1 of the present invention, when the aircraft is yawing leftward;

fig. 15 is a plan view of a tilt-rotor aircraft with front-back staggered wings according to embodiment 1 of the present invention, when the aircraft is yawing rightward;

fig. 16 is a left side view of a tiltrotor aircraft with front and rear staggered wings according to embodiment 1 of the present invention, when the aircraft is yawing rightward;

fig. 17 is a top view of a tiltrotor aircraft with staggered front and rear wings according to embodiment 2 of the present invention.

Description of the reference numerals:

10 a fuselage; 20 wings; 21 a main wing; 22 ailerons; 30 tail wings; 31 horizontal rear wing; 311 elevators; 32 vertical tail fins;

a 321 rudder; 40 landing gear; 50 tilt rotors; 51 a rotor wing; 52 a tilt mechanism; 53 brace the pole.

Detailed Description

In order to make the technical means, creation features, achievement purposes and effects of the present invention easy to understand, the following embodiments are specifically illustrated in conjunction with the accompanying drawings.

Examples

Fig. 1 is a schematic perspective view of a tiltrotor aircraft with staggered rotors in fixed-wing mode.

As shown in fig. 1, the present embodiment provides a tiltrotor aircraft with staggered rotors, which includes a fuselage 10, wings 20, a tail 30, a landing gear 40, and a tiltrotor 50.

The wing 20 comprises two main wings 21 and two ailerons 22. Two main wings 21 are respectively connected to both sides of the middle of the body 10 for generating lift force and maintaining lateral balance when the aircraft is flying. Two ailerons 22 are respectively connected to the trailing edges of the two main wings 21 for deflecting to effect the longitudinal roll of the aircraft.

Tail 30 includes a horizontal tail 31 and two vertical tails 32. The horizontal rear wing 31 is connected to the rear end of the fuselage 10 and includes a horizontal stabilizer for maintaining the balance of pitch during flight of the aircraft and an elevator 311 connected to the rear edge of the horizontal stabilizer and the elevator 311 is used to provide pitch control. Two vertical stabilizers 32 are respectively attached to both sides of the horizontal stabilizer 31, and each vertical stabilizer 32 includes a vertical stabilizer for maintaining a balanced heading when the aircraft is flying and a rudder 321 attached to a rear edge of the vertical stabilizer, the rudder 321 being used to provide heading control.

Landing gear 40 is attached to the bottom of fuselage 10 for supporting the takeoff and landing of the aircraft. In this embodiment, the landing gears 40 are provided in two, evenly distributed at the bottom of the fuselage 10.

Tiltrotor rotors 50 are an important part of the present application. In this embodiment, the quantity of tiltrotor 50 is four, and two tiltrotor 50 set up in the front row, and the symmetry is installed in the leading edge outside department of two main wings 21 respectively, and two other tiltrotor 50 set up in the back row, and the symmetry is installed in the inboard department of the trailing edge of two main wings 21 respectively, and the overall arrangement makes the front row tilt rotor 50 stagger around with the back row tilt rotor 50. The structure, layout characteristics, and control method of the tilt rotor 50 will be specifically described below.

Each tilt rotor 50 includes a rotor 51 and a tilt mechanism 52 that drives tilt of rotor 51. Specifically, tilting mechanism 52 drives rotor 51 to tilt on a vertical plane parallel to fuselage 10, and rotor 51 is driven by tilting mechanism 52 to achieve a vertical posture, a tilted posture, and a horizontal posture.

Wherein, the rotor 51 of all tilt rotors 50 in the vertical posture is kept at the same height position, the rotor 51 of the front row tilt rotor 50 in the horizontal posture is located at a position higher than the main wing 21, and the rotor 51 of the rear row tilt rotor 50 in the horizontal posture is located at a position lower than the main wing 21, that is, the tilt mechanism 52 of the front row tilt rotor 50 drives the rotor 51 to tilt up when changing from the vertical posture to the tilt posture or the horizontal posture, and the tilt mechanism 52 of the rear row tilt rotor 50 drives the rotor 51 to tilt down when changing from the vertical posture to the tilt posture or the horizontal posture. When the aircraft hovers and lands vertically, the rotor 51 of the front row tilting rotor 50 in the horizontal posture can be ensured above the main wing 21, if the aircraft tilts left and right at the moment, the rotor 51 of the front row tilting rotor 50 cannot hit the ground, and the rear row tilting rotor 50 cannot hit the ground due to the fact that the rear edge of the main wing 21 is arranged on the inner side of the rear edge of the aircraft, and the deflection range is limited when the aircraft tilts left and right, so that the aircraft cannot hit the ground. Meanwhile, since no tilt rotor 50 is provided inside the leading edge of the main wing 21, such an arrangement is advantageous for safely getting on and off passengers and loading and unloading goods.

Each tiltrotor 50 further includes a strut 53 connected to main wing 21 for mounting tiltrotor 52, strut 53 being disposed parallel to fuselage 10. Wherein, the stay 53 of the front row tilt rotor 50 is disposed forward along the direction parallel to the fuselage 10, and the stay 53 of the rear row tilt rotor 50 is disposed rearward along the direction parallel to the fuselage 10.

Based on the above-mentioned overall arrangement of rotor 50 that verts, this rotor staggers open rotorcraft that verts around mainly has three mode, is the stationary vane mode respectively, verts transition mode and hover the VTOL mode.

Fig. 2 is a top view of a rotorcraft with staggered front and back rotors in fixed-wing mode, fig. 3 is a side view of a rotorcraft with staggered front and back rotors in fixed-wing mode, and fig. 4 is a front view of a rotorcraft with staggered front and back rotors in fixed-wing mode.

As shown in fig. 1 to 4, when the tiltrotor aircraft with staggered rotors is in the fixed-wing mode, rotors 51 of four tiltrotors 50 are in a vertical attitude by being driven by respective tilt mechanisms 52, at this time, the rotation of rotors 51 of front tiltrotors 50 generates a force pulling the aircraft forward, the rotation of rotors 51 of rear tiltrotors 50 generates a force pushing the aircraft forward, and attitude control of the aircraft is realized by ailerons 22, elevators 311 of horizontal tail 31, and rudder 321 of vertical tail 32.

Fig. 5 is a perspective view of a tilt-rotor aircraft with staggered rotors around the rotor in a tilt transition mode, fig. 6 is a top view of the tilt-rotor aircraft with staggered rotors around the rotor in the tilt transition mode, fig. 7 is a side view of the tilt-rotor aircraft with staggered rotors around the rotor in the tilt transition mode, and fig. 8 is a front view of the tilt-rotor aircraft with staggered rotors around the rotor in the tilt transition mode.

As shown in fig. 5 to 8, when the rotorcraft with staggered front and back rotors needs to be converted from the fixed-wing mode to the hovering vertical-takeoff and landing mode, tilt mechanism 52 of front row tilt rotor 50 drives rotor 51 to tilt up, tilt mechanism 52 of rear row tilt rotor 50 drives rotor 51 to tilt down, tilt mechanisms 52 of four tilt rotors 50 tilt in synchronization, and the tilt angular velocities remain the same, and the rotorcraft with staggered front and back rotors is in the tilt transition mode. In the process, the rotor 51 of the front row tilt rotor 50 pulls the aircraft by generating a forward component force through rotation, the rotor 51 of the rear row tilt rotor 50 pushes the aircraft by generating a forward component force through rotation, one part of attitude control of the aircraft is consistent with that in a fixed wing mode and is realized by the ailerons 22, the elevators 311 of the horizontal tail 31 and the rudder 321 of the vertical tail 32, the other part of attitude control of the aircraft is realized by a rotation speed difference of the rotors 51 of the four tilt rotors 50, the ratio of the two parts of attitude control of the aircraft is automatically distributed by a control system of the aircraft according to the tilt angle of the whole aircraft and the tilt angles of the rotors 51 of the four tilt rotors 50, and the attitude control of the aircraft is in a mixed control mode at the moment.

When rotor staggered form tilt rotor aircraft need convert the stationary vane mode into from hovering the VTOL mode, the mechanism 52 that verts of the rotor 50 and the rotor 50 that verts of back row presses the above respectively the opposite direction drive rotor 51 verts, and the mechanism 52 that verts of four tilt rotors 50 verts in step to the angular velocity that verts keeps unanimous.

Fig. 9 is a schematic perspective view of a tilt-rotor front-back staggered-rotor aircraft in a hover vertical take-off and landing mode, fig. 10 is a top view of the tilt-rotor front-back staggered-rotor aircraft in the hover vertical take-off and landing mode, fig. 11 is a side view of the tilt-rotor front-back staggered-rotor aircraft in the hover vertical take-off and landing mode, and fig. 12 is a front view of the tilt-rotor front-back staggered-rotor aircraft in the hover vertical take-off and landing mode.

As shown in fig. 9 to fig. 12, when the tilt-rotor aircraft with staggered rotors is in the hovering vertical landing mode, the rotors 51 of the four tilt rotors 50 are driven by the respective tilt mechanisms 52 to be in a horizontal posture, at this time, the rotors 51 of the four tilt rotors 50 all rotate to generate an upward lift force, so that the aircraft can realize hovering and vertical landing in the air, the posture control of the aircraft is completely realized through the difference in the rotation speeds of the rotors 51 of the four tilt rotors 50, and meanwhile, the four rotors 51 generate small-amplitude symmetric differential tilting by controlling the tilt mechanisms 52 of the four tilt rotors 50, and the posture control of the yaw of the aircraft can be realized.

Fig. 13 is a top view of a rotorcraft with staggered front-to-back rotors in a leftward yaw, and fig. 14 is a left view of a rotorcraft with staggered front-to-back rotors in a leftward yaw.

As shown in fig. 13 and 14, when the tiltrotor aircraft with staggered rotors needs to yaw left, tilting mechanism 52 of tiltrotor rotor 50 in the front row of left wing 20 drives rotor 51 to tilt slightly backward, tilting mechanism 52 of tiltrotor rotor 50 in the rear row of left wing 20 drives rotor 51 to tilt slightly forward, so that two horizontal backward components are generated on the left side, tilting mechanism 52 of tiltrotor rotor 50 in the front row of right wing 20 drives rotor 51 to tilt slightly forward, tilting mechanism 52 of tiltrotor rotor 50 in the rear row of right wing 20 drives rotor 51 to tilt slightly backward, so that two horizontal forward components are generated on the right side, and tilting mechanisms 52 of four tiltrotor rotors 50 tilt four rotors 51 in a differential manner, so that the whole aircraft obtains a counterclockwise moment, thereby enabling yaw to be performed to the left side.

Fig. 15 is a top view of a rotorcraft with staggered front and back rotors in a right yaw orientation, and fig. 6 is a left side view of a rotorcraft with staggered front and back rotors in a right yaw orientation.

As shown in fig. 15 and 16, when the tiltrotor aircraft with staggered rotors needs to yaw to the right, tilting mechanism 52 of tiltrotor rotor 50 in the front row of left wing 20 drives rotor 51 to tilt forward slightly, tilting mechanism 52 of tiltrotor rotor 50 in the back row of left wing 20 drives rotor 51 to tilt backward slightly, so that two horizontal forward force components are generated on the left side, tilting mechanism 52 of tiltrotor rotor 50 in the front row of right wing 20 drives rotor 51 to tilt backward slightly, tilting mechanism 52 of tiltrotor rotor 50 in the back row of right wing 20 drives rotor 51 to tilt forward slightly, so that two horizontal backward force components are generated on the right side, and tilting mechanisms 52 of four tiltrotor rotors 50 tilt four rotors 51 in a differential manner synchronously, so that the whole aircraft obtains a clockwise moment, thereby realizing yaw to the right side.

Note that, among them, the flight control system for controlling the aileron 22, the elevator 311, the rudder 321, and the tilt rotor 50 may be a control system of the tilt rotor aircraft with offset rotors, or may be a remote control system for realizing remote control.

Example 2

Fig. 17 is a top view of a tiltrotor aircraft with offset rotors forward and aft.

As shown in fig. 17, the present embodiment provides a tiltrotor aircraft with staggered rotors, including a fuselage 10, wings 20, a tail 30, landing gears 40, and tiltrotors 50. The difference from embodiment 1 is that the number of tilt rotors 50 is four, two tilt rotors 50 are disposed in the front row and symmetrically mounted at the inner sides of the leading edges of two main wings 21, respectively, and the other two tilt rotors 50 are disposed in the rear row and symmetrically mounted at the outer sides of the trailing edges of two main wings 21, respectively.

It should be noted that, when the aircraft is hovering for vertical take-off and landing, in order to avoid the rear row tilt rotor 50 rotor 51 hitting the ground due to the aircraft tilting, the aircraft lateral balance needs to be ensured.

Effects and effects of the embodiments

According to the rotor stagger type tilt rotor aircraft of the embodiment, because the tilt rotor on the wing is set into two rows in the front and the back, and the tilt rotor in the front row and the tilt rotor in the back row are arranged in the front and the back in a staggered manner, so the tilt rotor aircraft with the rotors staggered in the front and the back has the following advantages:

(1) Meanwhile, the efficiency of the tilt rotor aircraft in hovering and cruising states is considered, all tilt rotors in any working state are ensured to work, and the integral power system of the aircraft can be kept in a state with higher efficiency all the time;

(2) The aircraft is ensured to have a simpler structure, the structural weight and the overall aerodynamic performance of the aircraft are favorably reduced, and the manufacturing, the use and the maintenance of the aircraft are also favorably realized;

(4) The method is beneficial to the design of flight control software of the airplane, reduces the design difficulty of the flight control software, improves the control effect of the flight control software and can achieve excellent robustness;

(5) The design of the overall structure of the airplane is facilitated, the design of the overall structure of the airplane cannot be influenced due to the structural problems of the arrangement of the tilt rotor and the power device, and the design optimization of the overall structure of the airplane can be more conveniently carried out;

The above embodiments are preferred examples of the present invention, and are not intended to limit the scope of the present invention.

Claims

1. The utility model provides a staggered rotor verts gyroplane around, includes fuselage, wing, fin, undercarriage and verts the rotor, its characterized in that:

wherein, the rotor that verts is a plurality of, and arrange into two rows around the wrong place, every around being on the wing the rotor that verts includes rotor and drive the mechanism that verts of rotor, the antedisplacement the mechanism that verts of rotor drives the rotor and upwards verts, the back row the mechanism that verts of rotor drives the rotor and verts downwards.

2. The rotorcraft staggered fore and aft tilt rotor according to claim 1, wherein:

wherein, the front row tilt rotor wing is installed the leading edge outside department of wing, the back row tilt rotor wing is installed the trailing edge inboard department of wing.

3. The rotorcraft staggered fore and aft tilt rotor according to claim 1, wherein:

wherein, the front row tilt rotor wing is installed the inboard department of the leading edge of wing, the back row tilt rotor wing is installed the trailing edge outside department of wing.

4. The tiltrotor aircraft with staggered rotors according to claim 2 or 3, wherein:

wherein, the front row tilt rotor wing and back row tilt rotor wing respectively two.

5. The rotorcraft staggered fore and aft tilt rotor according to claim 1, wherein:

wherein each tilt rotor further comprises a strut,

the tilting mechanism is connected with the wing through the stay bar,

the front row the vaulting pole of rotor verts is along being on a parallel with the direction of fuselage sets up forward, the back row the vaulting pole of rotor verts is along being on a parallel with the direction of fuselage sets up backward.

6. The rotorcraft staggered fore and aft tilt rotor according to claim 1, wherein:

wherein the wing comprises a main wing and an aileron.

7. The rotorcraft staggered fore and aft tilt rotor according to claim 1, wherein:

wherein the rear wing includes a horizontal rear wing having an elevator and a vertical rear wing having a rudder.

8. A control system of a rotorcraft with staggered rotors, comprising:

a flight control system for controlling the ailerons of the wings of a tiltrotor aircraft with staggered rotors according to any one of claims 1 to 7, the control surfaces of the empennages, and the rotors and the tilting mechanisms of the tiltrotors.

9. The control system of claim 8, wherein:

wherein the flight control system is configured to control the tiltrotor aircraft with the rotors staggered fore and aft in a fixed-wing mode, a tilt transition mode, a hover VTOL mode, a yaw left, and a yaw right;

when the tilt rotor aircraft with the rotors staggered front and back is in a fixed wing mode, the rotors of all tilt rotors are in a vertical posture under the driving of the tilt mechanism;

when the tilt rotor aircraft with the rotors staggered front and back is in a tilt transition mode, the tilt mechanisms of all tilt rotors synchronously drive the rotors to tilt at the same angular speed;

when the tilt rotor aircraft with the rotors staggered front and back is in a hovering vertical take-off and landing mode, the rotors of all tilt rotors are in a horizontal posture under the driving of the tilt mechanisms;

when the tilting rotor aircraft with the rotors staggered front and back deflects left, the tilting mechanism of the tilting rotor positioned in the front row of the left side wing drives the rotor to tilt backwards slightly, the tilting mechanism of the tilting rotor positioned in the back row of the left side wing drives the rotor to tilt forwards slightly, meanwhile, the tilting mechanism of the tilting rotor positioned in the front row of the right side wing drives the rotor to tilt forwards slightly, and the tilting mechanism of the tilting rotor positioned in the back row of the right side wing drives the rotor to tilt backwards slightly;

work as stagger formula tilt rotor machine around the rotor when yawing to the right, the mechanism of verting drive rotor that is located the tilt rotor of left side wing front-row verts a little forward, and the mechanism of verting drive rotor that is located the tilt rotor of left side wing back row verts a little backward, and the mechanism of verting drive rotor that is located the tilt rotor of right side wing front-row simultaneously verts a little backward, and the mechanism of verting drive rotor that is located the tilt rotor of right side wing back row verts a little forward.

10. The control system of claim 9, wherein:

when the tilt rotor aircraft with the rotors staggered front and back is in a fixed wing mode, the attitude control of the aircraft is realized through control surfaces of ailerons and empennages of wings;

when the tilt rotor aircraft with the rotors staggered front and back is in a tilt transition mode, the attitude control of the aircraft is realized by the difference of the rotating speeds of the ailerons of the wings, the control surface of the empennage and the rotors of the tilt rotors;

when the tilt rotor aircraft with staggered rotors around is in a hovering vertical take-off and landing mode, the attitude control of the aircraft is realized through the rotating speed difference of the rotors of the tilt rotors.