CN212243814U - Four-blade rotary wing aircraft with integrated rotor wing and aircraft body - Google Patents

Abstract

The utility model proposes a four-blade rotary wing aircraft integrated with a rotor and fuselage, comprising a fuselage, a canard, a four-blade rotary wing and a tail, a propeller for providing forward flying power of the rotary wing aircraft, and an anti-torque device , power system and flight control system and landing gear; the upper surface of the fuselage has a depression at the position of the longitudinal symmetry plane of the fuselage, and the size of the depression matches the auxiliary blade, so that the auxiliary blade can be integrated into the fuselage; the four-blade rotating wing passes through the stairs The stepped propeller hub system is installed on the rotor main shaft of the rotary-wing aircraft; the stepped propeller hub system is divided into an upper propeller hub system and a lower propeller hub system. By designing the axially movable lower propeller hub, the invention enables the auxiliary blade to be integrated with the fuselage in the fixed-wing flight mode, greatly reduces the disturbance and resistance of the auxiliary blade in the fixed-wing flight mode, and reduces the The resistance during cruising flight maximizes the lift-drag ratio during cruising, thereby improving cruising efficiency and ensuring the high-speed flight capability of the rotary-wing aircraft.

Description

A four-blade rotary-wing aircraft with integrated rotor-fuselage

technical field

The utility model relates to the technical field of aircraft, in particular to an integrated design technology of a rotor and a fuselage of a rotary-wing aircraft, which is a four-blade rotary-wing aircraft integrated with a rotor and a fuselage.

Background technique

The rotary-wing aircraft is a new type of manned/unmanned aircraft that combines the vertical take-off and landing performance of a helicopter and the high-speed cruise performance of a fixed-wing aircraft. The patent number is ZL201110213680.1, and the Chinese patent titled "A Rotary Wing Aircraft with Variable Flight Mode" is a typical model. Rotary wing aircraft have a three-plane aerodynamic layout. Among them, the rotating wing, that is, the main wing, can be used as a rotor in the helicopter flight mode to provide the aircraft with the pulling force required for vertical take-off and landing through rotation. At the same time, when the aircraft has a certain flying speed, it can be locked as a fixed wing. Realize fixed-wing high-speed, high-efficiency flight. Therefore, in the take-off, landing and low-speed flight stages, the aircraft adopts the helicopter flight mode, and in the cruise and mission stages, the fixed-wing flight mode is adopted, and there is a switching flight mode between the fixed-wing flight mode and the helicopter flight mode.

In order to take into account both the helicopter flight mode and the fixed-wing flight mode, the rotary wing adopts a medium aspect ratio, the root is slightly larger than the trapezoidal wing plane design, and adopts a symmetrical elliptical airfoil at the leading and trailing edges. , there is always flow separation at the trailing edge, and the flow separation will bring additional power consumption. Therefore, in the helicopter flight mode stage, the power required by the rotating wing is larger than that of a traditional helicopter. At the same time, compared with the main rotor of the traditional helicopter, the single blade of the rotary wing has a large area and a large structural weight.

In order to effectively improve the load-carrying capacity and maximum take-off weight of rotary-wing aircraft, a four-blade rotary wing is proposed, such as "A Four-blade Rotary Wing and Rotary Wing Aircraft and Control Method" ZL201910189236.7 China patent. The four-blade rotating wing includes a pair of main blades and a pair of auxiliary blades; the blade section of the main blade adopts a symmetrical airfoil at the front and rear edges, and the plane shape of the blade adopts a front and rear symmetrical design, taking into account the fixed wing performance when locked ; And the blade profile of the auxiliary blade adopts the rotor airfoil that meets the performance requirements of the helicopter rotor; the main blade and the auxiliary blade are installed on the same propeller hub with a cross distribution.

SUMMARY OF THE INVENTION

technical problem to be solved

After further theoretical calculation, wind tunnel test and model flight verification, we found that in the fixed-wing flight stage of the four-blade rotary-wing aircraft, after the main rotor shaft is locked, the main blade is perpendicular to the fuselage symmetry plane, and the auxiliary blade is along the fuselage plane. The longitudinal symmetry plane of the fuselage is distributed. At this time, the auxiliary blades along the longitudinal symmetry plane of the fuselage produce airflow interference with the upper surface of the fuselage, which increases the resistance and affects the flow of the main blade that acts as a fixed wing. The auxiliary blade of the longitudinal symmetry plane is a slender structure, which will generate relatively strong vibration during the fixed-wing flight stage, which will further increase the flight resistance during the cruise stage.

Technical solutions

In order to solve the above problems, and at the same time to improve the take-off weight of the rotary-wing aircraft, the utility model proposes a rotary-wing aircraft integrated with the rotor body, which still adopts the form of four blades, but takes into account the propeller hub structure and the fixed-wing cruise at the same time. Efficiency, through the design of the fuselage and rotor hub, the use of lift-type auxiliary propellers. When the aircraft is in helicopter mode, the auxiliary propeller is in the highest position, and the upper and lower propeller hubs are driven to rotate by the rotor shaft to complete the helicopter mode flight. During the process, the auxiliary propeller is equivalent to the lifting device for the main propeller, and bears more than half of the pulling force under heavy load conditions. Provides effective support for the helicopter mode of rotary-wing aircraft; when the aircraft is in fixed-wing mode, the auxiliary propeller is lowered to the specially set recessed position in the longitudinal direction of the fuselage, the main propeller is locked in the horizontal direction of the aircraft, the auxiliary propeller is locked in the vertical direction of the aircraft, and the auxiliary propeller is locked in the vertical direction of the aircraft. The body is fused, and the final aircraft forms a three-plane aircraft, which reduces the resistance during high-speed flight and realizes the integrated design of the rotor and fuselage.

The technical scheme of the present utility model is:

The four-blade rotary-wing aircraft integrated with the rotor and fuselage comprises a fuselage, a canard mounted on the longitudinal front of the fuselage, a four-bladed rotary wing mounted on the longitudinal middle of the fuselage, and a canard mounted on the longitudinal center of the fuselage. The tail wing at the longitudinal tail of the body, the propeller installed on the fuselage to provide the forward flight power of the rotary-wing aircraft, the anti-torque device installed on the fuselage, the power system and flight control system installed inside the fuselage, and the lower part of the fuselage. the landing gear;

Canards provide part of the lift during the fixed-wing and transition phases of rotary-wing aircraft, and in some way provide pitch and/or roll control and/or trim moments; the flat tail in the tail is used in rotary-wing aircraft The fixed-wing and transition phases of flight provide part of the lift and in some way provide pitch and/or roll control and/or trim moments;

The four-bladed rotary wing provides full pull during the helicopter-mode flight phase of the rotary-wing aircraft and is locked during the fixed-wing-mode flight phase of the rotary-wing aircraft; the four-bladed rotary wing includes a pair of main blades and A pair of auxiliary blades; the locked main blade is perpendicular to the longitudinal symmetry plane of the rotary-wing aircraft, and provides partial lift during the flight stage of the rotary-wing aircraft in the fixed-wing mode; the locked auxiliary blades are along the longitudinal symmetry plane of the fuselage;

It is characterized in that: the upper surface of the fuselage has a depression at the position of the longitudinal symmetry plane of the fuselage, and the size of the depression position matches the locked auxiliary blade, so that the auxiliary blade can be integrated into the fuselage;

The four-blade rotary airfoil is mounted on the main shaft of the rotor of the rotary-wing aircraft through a stepped propeller hub system;

The stepped propeller hub system is divided into an upper propeller hub system and a lower propeller hub system;

The main structure of the upper propeller hub system is fixedly installed on the upper part of the rotor main shaft of the rotary-wing aircraft, and is used to install two main blades in the rotary-wing aircraft, and realize the transmission and pitch changing functions of the main blades; the upper propeller The main structure of the hub system includes a propeller clip and an upper propeller hub; the upper propeller hub adopts a seesaw type propeller hub with elastic constraints; the propeller clip adopts a torsion bar type propeller clip;

The lower propeller hub system is installed on the main shaft of the rotor of the rotary-wing aircraft, and is located at the lower part of the main structure of the upper propeller hub system, and is used to install two auxiliary blades in the rotary-wing aircraft, and realize the transmission and change of the auxiliary blades. distance function;

The lower hub system can control the auxiliary blade to move along the main shaft axis after the rotor main shaft of the rotary-wing aircraft is locked, and define the axial position of the auxiliary blade; When moved into position, the sub-blades are integrated into the recesses in the fuselage of the rotary-wing aircraft.

Further, the recessed position of the fuselage of the rotary-wing aircraft is provided with a shape-preserving retractable baffle, which is used to maintain the shape of the recessed opening of the fuselage and the fuselage as a whole.

Further, the blade section of the main blade adopts a symmetrical airfoil design at the front and rear edges, and the plane shape of the blade adopts a downstream symmetrical design; the blade section of the auxiliary blade adopts a rotor airfoil that meets the performance requirements of the helicopter rotor.

Further, the lower propeller hub system includes a sliding actuator, a lower propeller hub, an upper moving block, a lower moving block and a lower propeller hub pitch changer; With key fit, the rotor main shaft can drive the lower propeller hub to rotate through the splines; when the rotor main shaft is locked, the lower propeller hub can be driven by the sliding actuator to move along the spline axial direction, and is constrained by the upper and lower limit blocks. , to achieve the upper-in-position and lower-in-position limits; the lower propeller hub pitch changer realizes the pitch change of the auxiliary blades, and can cooperate with the sliding actuator to realize the lower propeller hub moving along the spline axial direction.

Further, the bottom of the lower propeller hub has a transition structure matched with the sliding actuator, so that the sliding actuator can drive the lower propeller hub to move along the spline axial direction, and the sliding actuator body does not rotate with the lower propeller hub.

Further, the transition structure at the bottom of the lower propeller hub is a circular chute structure, and the actuating end of the sliding actuator is located in the circular chute, which can drive the lower propeller hub to move along the spline axial direction, and can also move the lower propeller hub in the lower propeller hub. It slides relative to the lower propeller hub during rotation.

Further, the lower propeller hub adopts the form of a bearingless propeller hub with a flexible beam structure; both ends of the flexible beam are sheathed with a pitch change jacket, and the outer end of the pitch change jacket is connected with the auxiliary blade through the blade mounting seat; the lower propeller hub is variable The pitch device is connected to the pitch change jacket to realize pitch change of the auxiliary blades.

Further, the lower propeller hub pitch changer includes a pitch changing actuator, a fixed plate, a moving plate, a pitch changing connecting rod, and a lower propeller hub pitch changing rocker arm; when the lower propeller hub moves from bottom to top, through the sliding action The lower propeller hub and the fixed plate move up along the axial direction of the rotating main shaft together with the actuator and the variable pitch actuator; after the lower propeller hub slides to reach the constraint position of the upper moving block, the sliding actuator stops, and the variable pitch actuator It can manipulate and control the auxiliary blades to change the collective pitch, and the upper moving block transmits the lift generated by the auxiliary blades to the main shaft of the rotor.

Further, the lower hub pitch changer has at least three pitch change actuators, and the fixed plate and the moving plate are matched with the rotating main shaft through spherical joints, so that the pitch change actuators can manipulate and control the auxiliary blades to change the collective pitch. and periodic variable distance.

Further, the rotor main shaft adopts a hollow shaft; the upper propeller hub automatic tilter in the upper propeller hub system is located in the lower part of the lower propeller hub system and inside the fuselage; the upper propeller hub system adopts a long connection inside the rotor main shaft. The rod realizes the connection between the structure on the upper part of the rotor main shaft in the upper propeller hub system and the automatic tilter of the upper propeller hub inside the fuselage.

beneficial effect

In order to improve the load-carrying capacity and the maximum take-off weight of the rotary-wing aircraft, the utility model proposes a rotor-body integrated design concept on the basis of the concept of a four-blade rotary-wing aircraft, and based on this, a stepped propeller hub is proposed. The system, through the design of the axially movable lower hub, enables the auxiliary blades to be integrated with the fuselage in the fixed-wing flight mode, greatly reducing the disturbance and resistance of the auxiliary blades in the fixed-wing flight mode, reducing the The resistance during cruising flight maximizes the lift-drag ratio during cruising, thereby improving the cruising efficiency and ensuring the high-speed flight capability of the rotary-wing aircraft.

In addition, by designing the stepped propeller hub system, the main blade is on the top and the auxiliary blade is on the bottom, which also makes the auxiliary blade play an effect equivalent to the main blade lifting device. It bears more than half of the pulling force from the distance and provides effective support for the helicopter mode flight of the rotary-wing aircraft.

At the same time, the design of the stepped propeller hub system also enables redundant control of the take-off and landing, pitch control and roll control of the rotary-wing aircraft in the helicopter mode, which improves the safety margin of the system.

In addition, in the present invention, the automatic tilting devices for realizing the pitch change function of the upper propeller hub and the lower propeller hub are all located inside the fuselage, which also reduces the resistance of the rotary-wing aircraft during flight.

Additional aspects and advantages of the invention will be set forth, in part, from the following description, and in part will be apparent from the following description, or 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 readily understood from the following description of embodiments in conjunction with the accompanying drawings, wherein:

Fig. 1 is a schematic diagram of a stepped propeller hub;

Among them: 1. Upper propeller hub system, 2 Lower propeller hub system;

Figure 2 is an example plan shape of a main blade;

Figure 3 is an example plan shape of a sub-blade;

Fig. 4 is a schematic diagram of the structure of the upper propeller hub;

Among them: 3 propeller clamps, 4 variable pitch hinge shells, 5 pull torsion bars, 6 needle roller bearings, 7 upper propeller hubs, 8 long connecting rods, 9 steering plates, 10 pitch change rods, 11 elastic hinges, 12 propeller hub splints, 13 swing hinge, 14 upper propeller hub variable pitch rocker arm, 15 propeller hub support arm;

Fig. 5 is a schematic diagram of the structure of the lower propeller hub;

Among them: 16 blade mounts, 17 pitch change jackets, 18 upper moving blocks, 19 splines, 20 propeller hub flexible beams, 21 lower propeller hub pitch-changing rockers, 22 lower moving blocks, 23 pitch-changing connecting rods, 24 moving disc, 25 fixed disc, 26 sliding actuator, 27 variable pitch actuator;

6 is a schematic diagram of the aerodynamic layout of the entire aircraft with a stepped hub rotating wing aircraft, and the control rudder surface is not included in the figure;

In the picture: 28 fuselage, 29 canard, 30 horizontal tail, 31 vertical tail, 32 forward-pulling propeller, 33 four-blade rotary wing, 34 landing gear, 35 tail rotor;

Figure 7 is a schematic diagram of an inclusive fuselage; (a) side view, (b) top view;

In the picture: 36 fuselage auxiliary propeller containing groove;

Figure 8 is a schematic diagram of the arrangement of the main propeller and the auxiliary propeller of the four-blade rotor; (a) side view, (b) top view;

In the picture: 37 main blades, 38 auxiliary blades;

FIG. 9 is a schematic diagram of the change of the rotary-wing aircraft during the whole flight process.

Figure 10 is a comparison chart of the lift-drag ratio between the fusion and non-fusion methods in the fixed-wing flight stage. The solid line in the figure represents the result of the fusion design, and the dotted line represents the result of the non-fusion design. The figure shows the whole aircraft cruising at a speed of 550km/h The curve of lift-drag ratio K versus lift coefficient CL.

Detailed ways

The following describes the embodiments of the present invention in detail. The embodiments are exemplary and are intended to be used to explain the present invention, but should not be construed as limiting the present invention.

This embodiment provides a large-load, large take-off weight rotary-wing aircraft based on a four-blade rotary wing and an integrated design of the rotor body. It consists of a fuselage, a canard mounted on the longitudinal front of the fuselage, a four-blade rotary wing mounted on the longitudinal center of the fuselage, and a tail mounted on the longitudinal tail of the fuselage, which is mounted on the fuselage to provide a rotary-wing aircraft for forward flight. The powered propeller, the anti-torque device installed on the fuselage, the power system and flight control system installed inside the fuselage, and the landing gear installed in the lower part of the fuselage.

The four-blade rotary airfoil is composed of two sets of blades with different configurations, that is, a "main and auxiliary blade" system including a pair of main blades and a pair of auxiliary blades. Among them, the main blade is designed to take into account the two flight modes of fixed-wing mode and helicopter mode. The blade profile adopts a symmetrical airfoil design at the front and rear edges, such as an elliptical airfoil, and the plane shape of the blade adopts a downstream symmetrical design, such as trapezoid, rectangular Wait. The other pair of auxiliary blades is completely designed to meet the flight requirements of helicopter mode. It adopts high-performance rotor design and can use high aspect ratio. The blade profile adopts high-performance rotor airfoil. The auxiliary rotor has higher rotor aerodynamic efficiency and Lighter structural weight.

The four-blade rotary wing provides full pull during the helicopter-mode flight phase of the rotary-wing aircraft, and locks during the fixed-wing-mode flight phase of the rotary-wing aircraft, with the locked main blade perpendicular to the longitudinal symmetry plane of the rotary-wing aircraft , which provides part of the lift during the fixed-wing flight phase of a rotary-wing aircraft. The locked auxiliary blades are along the longitudinal symmetry plane of the fuselage.

The upper surface of the fuselage has a depression at the position of the longitudinal symmetry plane of the fuselage, and the size of the depression position matches the locked auxiliary blade, so that the auxiliary blade can be integrated into the fuselage; The retractable baffle is used to maintain the shape of the fuselage with the recessed opening of the fuselage as a whole. When the auxiliary blade descends into or rises out of the fuselage, the shape-preserving retractable baffle opens.

The four-blade rotary airfoil is mounted on the main shaft of the rotor of the rotary-wing aircraft through a stepped propeller hub system; the stepped propeller hub system is divided into an upper propeller hub system and a lower propeller hub system.

The main structure of the upper propeller hub system is fixedly installed at the top position of the rotor main shaft of the rotary-wing aircraft, and is used to install two main blades in the rotary-wing aircraft, and realize the transmission and pitch changing functions of the main blades. As shown in FIG. 4 , in this embodiment, the main structure of the upper propeller hub system installed on the top of the rotor main shaft includes a propeller clamp 3 , a pitch-variable hinge housing 4 , a torsion bar 5 , a needle roller bearing 6 , and an upper propeller hub 7 , Long connecting rod 8, steering plate 9, variable pitch rod 10, elastic hinge 11, propeller hub splint 12, swing hinge 13, upper propeller hub pitch-changing rocker arm 14, propeller hub support arm 15.

The upper propeller hub 7 adopts a seesaw-type propeller hub with elastic constraints; the propeller hub splint 12 connects the propeller hub arms 15 on both sides, and can swing up and down around the swinging hinge 13, and the elastic hinge 11 provides elasticity for the swinging motion Constraints to increase rotor steering torque. The propeller clip 3 adopts a torsion bar type propeller clip, the torsion bar 5 is installed in the propeller hub support arm 15, one end is connected with the pitch-variable hinge shell 4, and the other end is connected with the upper propeller hub 7, and is subjected to centrifugal force and pitch-changing torsion. The structure reduces the number of bearings used, the number of parts, maintenance complexity and lubrication problems; the variable pitch hinge housing 4 is mounted on the propeller hub support arm 15 through the needle roller bearing 6 to transmit the torque in the rotation plane of the upper propeller hub .

In order to reduce the resistance and cooperate with the installation space of the lower propeller hub, the control system of the upper propeller hub system adopts in-axis control, that is, the pitch change hinge shell is connected by the pitch change rocker arm and the pitch change rod, and the pitch change rod is connected by the steering plate and The long connecting rod connection in the hollow rotating main shaft is located at the lower part of the lower propeller hub system and is located in the upper propeller hub automatic tilter inside the fuselage, and the pitch change control of the main blade is realized through the upper propeller hub automatic tilter .

As shown in Figure 1, the lower propeller hub system is installed on the main shaft of the rotor of the rotary-wing aircraft, and is located at the lower part of the main structure of the upper propeller hub system, and is used to install two auxiliary blades in the rotary-wing aircraft, and realize the auxiliary blade of the rotary-wing aircraft. The transmission and pitch function of the propeller. The lower hub system can control the auxiliary blade to move in the axial direction of the main shaft after the rotor main shaft of the rotary-wing aircraft is locked, and define the axial position of the auxiliary blade; When , the auxiliary blade is integrated into the fuselage of the rotary-wing aircraft, so as to avoid the disturbance of the auxiliary blade in the fixed-wing flight mode and reduce the resistance.

As shown in FIG. 5 , in this embodiment, the lower propeller hub system includes a sliding actuator, a lower propeller hub, an upper moving block, a lower moving block and a lower propeller hub pitch changer.

The lower propeller hub and the rotor main shaft are matched by splines along the axial direction of the rotor main shaft, and the rotor main shaft can drive the lower propeller hub to rotate through the splines; when the rotor main shaft is locked, the lower propeller hub can be driven by the sliding actuator. The key moves axially, and under the constraints of the upper and lower limit blocks, the upper and lower positions are limited; the lower hub pitch changer realizes the pitch change of the auxiliary blades, and can cooperate with the sliding actuator to realize the lower hub edge The spline moves axially.

In this embodiment, the lower propeller hub adopts the form of a bearingless propeller hub with a flexible beam structure; both ends of the flexible beam are sheathed with a pitch change jacket, and the outer end of the pitch change jacket is connected with the auxiliary blade through the blade mounting seat; the lower propeller The hub pitch changer is connected to the pitch change jacket to realize pitch change of the auxiliary blades.

The lower propeller hub pitch changer includes a pitch changing actuator, a fixed plate, a moving plate, a pitch changing connecting rod and a lower propeller hub pitch changing rocker arm.

When the lower propeller hub moves from bottom to up, the lower propeller hub and the fixed plate move up along the axis of the rotating main shaft through the cooperation of the sliding actuator and the variable pitch actuator; after the lower propeller hub slides to the upper limit moving block constraint position , the sliding actuator stops, the variable pitch actuator can drive the fixed plate and the moving plate to move, and then control the auxiliary blade to change the collective pitch, and the upper moving block transmits the lift generated by the auxiliary blade to the rotor main shaft. That is, as shown in Figure 5, in this case, the lower hub pitch changer has only two pitch change actuators, which can realize the change of the collective pitch of the auxiliary blades, but cannot realize the periodic pitch change, and the structure is relatively simple. The wing controls the main blades through the automatic tilter on the upper hub to achieve periodic pitch control.

Of course, the pitch changer of the lower hub may also have at least three pitch-change actuators, and the fixed plate and the moving plate are matched with the rotating main shaft through the spherical joint, so that the pitch-change actuator can manipulate and control the collective pitch of the auxiliary blades. and periodic variable distance.

When the lower propeller hub moves from top to bottom, the lower propeller hub and the fixed plate move down along the axial direction of the rotating main shaft through the cooperation of the sliding actuator and the variable pitch actuator; the lower propeller hub slides to reach the constraint position of the lower limit block After that, the sliding actuator and the variable pitch actuator stop, and the auxiliary blades are integrated into the fuselage of the rotary-wing aircraft.

In addition, in order to isolate the rotary motion of the lower propeller hub from the sliding actuator body, a transition structure that cooperates with the sliding actuator is provided at the bottom of the lower propeller hub. The actuating end of the propeller is located in the circular chute, which can drive the lower propeller hub to move along the spline axial direction, and can also slide relative to the lower propeller hub when the lower propeller hub rotates. In addition, a structure similar to the fixed plate and moving plate in the automatic tilter can also be used to realize the isolation of the rotary motion of the lower propeller hub from the body of the sliding actuator.

Canards provide partial lift during the fixed-wing and transition phases of rotary-wing aircraft, and provide pitch and/or roll control and/or trim moment by some means, such as full-motion canards, canard rudders Surfaces, etc.; the flat tail in the tail provides part of the lift during the fixed-wing flight phase of the rotary-wing aircraft and the transition flight phase, and provides pitch and/or roll control and/or trim moment by some means, such as full-motion flat tail, flat tail Rudder, etc. And in order to ensure the course control ability of the aircraft, there should be at least one vertical tail in the tail. The form of the tail can take many forms, such as T-shaped tail, H-shaped tail and so on.

The propeller that provides the forward flying power of the rotary-wing aircraft can be a forward-pulling variable-pitch propeller installed on the head of the fuselage, but considering that the forward-pulling propeller is in the helicopter mode flight stage, the tail rotor does not work in the fixed-wing mode flight stage. Therefore, the two can be combined into a tail rotor with variable thrust direction. The thrust tail rotor moves through a specific rule to realize the change of the thrust direction, which can provide the anti-torque in helicopter mode and the thrust required for flight in fixed-wing mode.

Figure 9 is a schematic diagram of the change of the rotary-wing aircraft during the whole flight process. During the take-off and landing stage of the helicopter mode, the auxiliary propellers rise to the highest level, and form a four-bladed propeller with the main propeller to provide lift for the whole aircraft; the main propeller and auxiliary propeller are gradually unloaded during the transition process. , the main propeller is locked perpendicular to the longitudinal symmetry plane of the fuselage, and the auxiliary propeller descends to the lowest point to merge with the fuselage; the fixed-wing mode is a triplane aircraft.

Figure 10 is a comparison chart of the lift-drag ratio between the fusion and non-fusion methods in the fixed-wing flight stage. The solid line in the figure represents the result of the fusion design, and the dotted line represents the result of the non-fusion design. It can be seen from the figure that after fusion, the The lift-to-drag ratio is greater than that of the non-fusion method.

Although the embodiments of the present invention have been shown and described above, it should be understood that the above embodiments are exemplary and should not be construed as limitations of the present invention. Variations, modifications, substitutions, and alterations to the above-described embodiments are possible within the scope of the present invention without departing from the principles and principles.

Claims (10)

1. A four-blade rotary wing aircraft integrated with a rotor and fuselage, comprising a fuselage, a canard installed in the longitudinal front of the fuselage, a four-blade rotary wing installed in the longitudinal middle of the fuselage, and a canard installed in the aircraft. The tail wing at the longitudinal tail of the body, the propeller installed on the fuselage to provide the forward flight power of the rotary-wing aircraft, the anti-torque device installed on the fuselage, the power system and flight control system installed inside the fuselage, and the lower part of the fuselage. the landing gear; Canards provide part of the lift during the fixed-wing and transition phases of rotary-wing aircraft, and in some way provide pitch and/or roll control and/or trim moments; the flat tail in the tail is used in rotary-wing aircraft The fixed-wing and transition phases of flight provide part of the lift and in some way provide pitch and/or roll control and/or trim moments; The four-bladed rotary wing provides full pull during the helicopter-mode flight phase of the rotary-wing aircraft and is locked during the fixed-wing-mode flight phase of the rotary-wing aircraft; the four-bladed rotary wing includes a pair of main blades and A pair of auxiliary blades; the locked main blade is perpendicular to the longitudinal symmetry plane of the rotary-wing aircraft, and provides partial lift during the flight stage of the rotary-wing aircraft in the fixed-wing mode; the locked auxiliary blades are along the longitudinal symmetry plane of the fuselage; It is characterized in that: the upper surface of the fuselage has a depression at the position of the longitudinal symmetry plane of the fuselage, and the size of the depression position matches the locked auxiliary blade, so that the auxiliary blade can be integrated into the fuselage; The four-blade rotary airfoil is mounted on the main shaft of the rotor of the rotary-wing aircraft through a stepped propeller hub system; The stepped propeller hub system is divided into an upper propeller hub system and a lower propeller hub system; The main structure of the upper propeller hub system is fixedly installed on the upper part of the rotor main shaft of the rotary-wing aircraft, and is used to install two main blades in the rotary-wing aircraft, and realize the transmission and pitch changing functions of the main blades; the upper propeller The main structure of the hub system includes a propeller clip and an upper propeller hub; the upper propeller hub adopts a seesaw type propeller hub with elastic constraints; the propeller clip adopts a torsion bar type propeller clip; The lower propeller hub system is installed on the main shaft of the rotor of the rotary-wing aircraft, and is located at the lower part of the main structure of the upper propeller hub system, and is used to install two auxiliary blades in the rotary-wing aircraft, and realize the transmission and change of the auxiliary blades. distance function; The lower hub system can control the auxiliary blade to move along the main shaft axis after the rotor main shaft of the rotary-wing aircraft is locked, and define the axial position of the auxiliary blade; When moved into position, the sub-blades are integrated into the recesses in the fuselage of the rotary-wing aircraft. 2. The four-blade rotary-wing aircraft integrated with the rotor-fuselage according to claim 1 is characterized in that: the recessed position of the rotary-wing aircraft fuselage is provided with a shape-preserving retractable baffle plate, which is used for the fuselage The position of the recessed opening and the overall shape of the fuselage can be maintained. 3. a kind of four-blade rotary airfoil aircraft with integrated rotor-fuselage according to claim 1 and 2, is characterized in that: the blade section of described main blade adopts front and rear edge symmetrical airfoil design, and the blade plane The shape adopts a downstream symmetrical design; the blade section of the auxiliary blade adopts a rotor airfoil that meets the performance requirements of the helicopter rotor. 4. The four-bladed rotary-wing aircraft with integrated rotor-fuselage according to claim 1, wherein the lower propeller hub system comprises a sliding actuator, a lower propeller hub, an upper moving block, and a lower moving limiter The lower propeller hub and the rotor main shaft are matched by splines along the axial direction of the rotor main shaft, and the rotor main shaft can drive the lower propeller hub to rotate through the splines; when the rotor main shaft is locked, the lower propeller hub can Driven by the sliding actuator, it moves axially along the spline, and under the constraints of the upper and lower limit blocks, the upper and lower positions are limited; the lower hub pitch converter realizes the pitch change of the auxiliary blades and can cooperate with The sliding actuator realizes the axial movement of the lower propeller hub along the spline. 5. The four-blade rotary wing aircraft with integrated rotor-fuselage according to claim 2, characterized in that: the bottom of the lower propeller hub has a transition structure that cooperates with the sliding actuator to realize the sliding actuator The lower propeller hub can be driven to move along the spline axial direction, and the sliding actuator body does not rotate with the lower propeller hub. 6. The four-blade rotary wing aircraft with integrated rotor-fuselage according to claim 5, characterized in that: the transition structure at the bottom of the lower propeller hub is a circular chute structure, and the sliding actuator is actuated The end is located in the circular chute, which can drive the lower propeller hub to move along the spline axial direction, and can also slide relative to the lower propeller hub when the lower propeller hub rotates. 7. The four-blade rotary wing aircraft with integrated rotor-fuselage according to claim 4, characterized in that: the lower propeller hub adopts the form of a bearingless propeller hub of a flexible beam structure; There is a pitch change jacket, and the outer end of the pitch change jacket is connected with the auxiliary blade through the blade mounting seat; the lower propeller hub pitch changer is connected on the pitch change jacket to realize the pitch change of the auxiliary blade. 8 . The four-blade rotary wing aircraft with integrated rotor-fuselage according to claim 4 , wherein the lower propeller hub pitch changer comprises a pitch-changing actuator, a fixed plate, a moving plate, a variable Pitch link and lower hub pitch-changing rocker arm; when the lower propeller hub moves from bottom to top, the lower propeller hub and the fixed plate move up along the axial direction of the rotating main shaft through the cooperation of the sliding actuator and the variable pitch actuator. ; After the lower propeller hub slides to the upper limit block constraint position, the sliding actuator stops, and the variable pitch actuator can control the auxiliary blade to change the collective pitch, and the upper limit block transmits the lift generated by the auxiliary blade to the rotor shaft. . 9 . The four-blade rotary wing aircraft with integrated rotor-fuselage according to claim 8 , wherein the lower propeller hub pitch changer has at least three pitch-changing actuators, a fixed plate and The moving plate is matched with the rotating main shaft through the spherical joint, so that the pitch-variable actuator can control the collective pitch and periodic pitch of the auxiliary blades. 10. The four-blade rotary wing aircraft with integrated rotor-fuselage according to claim 1, characterized in that: the rotor main shaft adopts a hollow shaft; the upper blade hub automatic tilter in the upper blade hub system It is located in the lower part of the lower propeller hub system and inside the fuselage; the upper propeller hub system adopts a long connecting rod inside the rotor main shaft to realize the structure on the upper part of the rotor main shaft in the upper propeller hub system and the upper propeller hub automatic tilter inside the fuselage Connection.

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