CN205186510U - No rudder face aircraft of independent air supply air feed - Google Patents

Abstract

The utility model provides a rudderless aircraft supplied by an independent air source. The basic configuration is a fixed-wing aircraft with a canard layout, including a fuselage, a main wing, a canard, a push-back power device, a propeller, and a small wingtip. Wings, main landing gear and nose landing gear rely on a set of circulation control device to replace the traditional rudder surface, which has a simple structure and is easy to maintain. And because the conventional rudder surface is canceled, the original sharp edges, openings and bosses on the wing surface will disappear, which will reduce the radar scattering area of the aircraft and improve the stealth of the aircraft.

Description

Rudderless aircraft with independent air supply

technical field

The utility model relates to the field of aviation machinery, in particular to an aircraft without a rudder surface supplied by an independent air source.

Background technique

The effective steering control produced by the control surfaces of the aircraft, so that it can carry out stable flight. However, the traditional rudder surface has many defects, such as complex structure, cumbersome maintenance, increased flight resistance and reduced stealth. Excellent aerodynamic performance, long range, long endurance and high stealth are important indicators in the design of next-generation aircraft. Traditional circulation control technology often provides air source for the device from engine bleed air, which will affect the power output of the engine.

Utility model content

In order to solve the problems of the prior art, the utility model provides an aircraft without a rudder surface supplied by an independent air source. The traditional rudder surface is replaced by a circulation control device, and the structure is simple and easy to maintain. And because the conventional rudder surface is canceled, the original sharp edges, openings and bosses on the wing surface will disappear, which will reduce the radar scattering area of the aircraft and improve the stealth of the aircraft.

The utility model comprises a canard layout fixed-wing aircraft composed of a fuselage, a main wing, a canard, a push-back power unit, a propeller, a winglet, a main landing gear and a front landing gear. Quantity control device; The circulation control device includes a multi-blade centrifugal fan and a Konda trailing edge connected by a nozzle, wherein the nozzle includes a closed cavity consisting of an upper closed surface, a lower closed surface, and closed curved surfaces on both sides, The upper and lower closed surfaces are converging at 15° from the interface of the multi-wing centrifugal fan to the rear edge of Coanda, and there are air outlet slots between the upper and lower closed surfaces and the rear edge of Coanda; The partition divides the nozzle vertically into two upper and lower inner cavities with equal volume, and each inner cavity is connected with an independent multi-blade centrifugal fan.

In order to prevent the pressure loss caused by the expansion of the section, resulting in insufficient jet energy, the closed curved surfaces on both sides of the nozzle gradually increase from the interface of the multi-wing centrifugal fan to the rear edge of the Coanda in the horizontal direction, and the inner cavity of the nozzle passes through the curved guide. The flow plate is divided into several small cavities, and the cross-sectional area of any section of the small cavity from the interface of the multi-wing centrifugal fan to the trailing edge of Coanda is equal, and the cross-sectional area of any small cavity at the trailing edge of Coanda is The cross-sectional area is equal to the internal cavity cross-sectional area at the interface of the nozzle multi-blade centrifugal fan. The circulation control aileron exciter is used to replace the aileron to realize the control of the roll attitude. Usually conventional rudder surfaces realize this control through differential deflection, and the aircraft without rudder surfaces of the utility model realizes the control of roll attitude by opening the circulation control aileron exciter on one side to cause left and right lift unbalanced. The basic structure of the circulation control aileron exciter is similar to that of the circulation control elevator exciter, but there is only one cavity and one air outlet slot, and the air is supplied by a centrifugal fan, which can deflect the airflow at the trailing edge of the wing downwards, increasing one Increase the circulation of the side wings to achieve the purpose of increasing the lift.

The fuselage is provided with a circulation control aileron exciter, and the circulation control aileron exciter includes an aileron centrifugal fan and an aileron Coanda trailing edge connected by an aileron nozzle, and the aileron nozzle It includes upper and lower closed surfaces, and aileron air outlet slots are respectively opened between the lower closed surface of the aileron nozzle and the trailing edge of the aileron Coanda.

The beneficial effects of the utility model are:

1. Increase lift and reduce drag: Circulation control technology can generate beneficial interference to the airflow, not only can control the flight attitude, but also improve the aerodynamic performance of the aircraft to achieve increase lift and reduce drag. The experimental results show that within the range of normal flight angle of attack, the maximum increase of the lift coefficient of the model can reach 23.1%, and the decrease of the drag coefficient can reach 31.7% after the circulation control device is turned on.

2. The structure of the rudderless surface is simple: the traditional control rudder surface is not used, and the circulation control method is used to provide force and moment for the attitude adjustment and maneuvering of the aircraft, so as to realize rudderless flight. The circulation control device is designed and optimized to make it miniaturized, light and easy to carry onboard, and has good control rudder effect. The wing structure of the rudderless UAV is simple, without complex transmission devices, and replaced by simple jet devices.

3. Improve stealth: There are a large number of movable rudder surfaces on the conventional wings, which is very unfavorable for stealth. The utility model replaces the traditional rudder surface with a circulation control device, the original sharp edges, openings and protrusions on the wing are eliminated, the surface of the wing is very smooth without any opening, the radar scattering area is reduced, and the stealth performance is improved.

Description of drawings

Fig. 1 is the structural representation of the utility model.

Fig. 2 is a sectional view of A-A in Fig. 1 .

FIG. 3 is a partially enlarged schematic diagram of the circulation control device in FIG. 2 .

Figure 4 is a chord section view of Coanda's trailing edge.

Figure 5 is a cross-section of the nozzle of the circulation control lift actuator.

Figure 6 is a schematic diagram of closed curved surfaces on both sides of the nozzle.

Fig. 7 is a schematic diagram of the structure of the deflector inside the nozzle.

Figure 8 is a schematic diagram of the upper and lower cavities of the nozzle.

Fig. 9 is a schematic diagram of the overall structure of the circulation control device.

Fig. 10 is a schematic diagram of the overall structure of the aileron exciter for circulation control.

detailed description

The utility model provides a rudderless aircraft supplied by an independent air source. Its structure is shown in Fig. Device 7, propeller 8, winglet 11, main landing gear 12 and nose landing gear 13 constitute a fixed-wing aircraft with a canard layout, and a circulation control device is installed inside the main wing, which can be realized without relying on conventional ailerons and elevators. The control of roll and pitch attitude realizes rudderless flight.

The circulation control lifting actuator is composed of a multi-blade centrifugal fan 2 and a nozzle 1, wherein the multi-blade centrifugal fan 2 is used as an independent air source, and the multi-blade centrifugal fan motor 9 draws air from the wing tip to provide high-pressure and high-speed airflow , the nozzle is used to form the Coanda effect to deflect the airflow. One side of the nozzle 1 is connected to the multi-wing centrifugal fan 2, and the other side is the slender Coanda trailing edge, the trailing edge radius is 4.5mm, and there is a 300mm long air outlet slot at the trailing edge, the trailing edge radius and the air outlet slot The height ratio is 15, and the seam height is 0.3 mm as shown in Figure 4. Due to the limited internal space of the aircraft wing, in order to embed the nozzle inside the wing, the upper sealing surface 15 and the lower sealing surface 16 of the nozzle are at an angle of 15° from the interface of the centrifugal fan to the Coanda trailing edge shrinkage meeting, and the The thickness is 1 mm as shown in Figure 5. In order to prevent the pressure loss caused by the expansion of the section, resulting in insufficient jet energy, the shape design of the nozzle is carried out according to the following steps: 1. Select 5 sections equidistantly from the interface of the centrifugal fan to the trailing edge of Coanda; 2. Determine the area of the 5 sections. In order to be consistent with the area of the air inlet, i.e. 15.5mm×70mm, determine the required transverse width of each section. 3. According to the transverse width of the section determined in the second step, smoothly connect the boundary points in turn to obtain the shape shown in Figure 6. The surface thickness is 1mm. In order to make the air outlet uniform, a deflector 18 is arranged inside the nozzle. The deflector is curved and divides the inner cavity into 5 regions. The thickness of the deflector is 1mm, and rounded corners are provided near the air inlet. As shown in Figure 7. In order to complete the same function as the rudder surface and deflect the airflow up and down, the utility model designs the nozzle from the air inlet into two independent parts up and down, separated by a flat plate in the middle, and the volume of the upper and lower parts is equal. As shown in Figure 8, when the rotor of the centrifugal fan that provides the air source for the lower half of the pipeline rotates, the external airflow is sucked into the lower half of the pipeline, and the airflow will be deflected upward along the rear edge of the circular Coanda when it is shot out from the air outlet slot, and the same The principle is that when the rotor of the centrifugal fan that provides the air source for the upper part of the pipeline rotates, the external airflow is sucked into the upper part of the pipeline, and the airflow will be deflected downward along the rear edge of the circular Coanda when it is shot out from the air outlet slot. The final combination of the centrifugal fan and the nozzle is shown in Figure 9.

The circulation control aileron exciter is used to replace the aileron to realize the control of the roll attitude. Usually conventional rudder surfaces realize this control through differential deflection, and the aircraft without rudder surfaces of the utility model realizes the control of roll attitude by opening the circulation control aileron exciter on one side to cause left and right lift unbalanced. The basic structure of the circulation control aileron exciter is similar to that of the circulation control elevator exciter, but there is only one cavity and one air outlet slot, and the air is supplied by a centrifugal fan, which can deflect the airflow at the trailing edge of the wing downwards, increasing one Increase the circulation of the side wings to achieve the purpose of increasing the lift. The circulation control aileron exciter 4 designed in this work has a width of 240mm, a trailing edge radius of 4.5mm, and an air outlet slit height of 0.3mm, as shown in Figure 10.

The flight attitude control principle of the rudderless aircraft of the utility model is as follows: after the control signal is input, the multi-blade centrifugal fan starts to work, and under the action of the centrifugal impeller, the airflow inside the wing is accelerated, ejected through the nozzle, and is used to The reach effect forms a beneficial disturbance to the mainstream airflow, which can change the aerodynamic force acting on the wing. Based on the above principle, turn on the circulation control aileron exciter on one side to generate unequal lift force on the left and right wings to control the roll attitude, and control the circulation control lift exciter on both sides of the fuselage to deflect the airflow downward to generate bowing moment , the lifting actuator deflects the airflow upwards through the circulation control to generate the head-up moment. When the circulation control lifting actuator on one side of the fuselage turns on the up and down simultaneous blowing mode, a yaw moment can be formed to make the aircraft yaw to the side where the blowing is not turned on.

The configuration of the utility model is a canard layout, which cancels the traditional rudder surface and replaces it with a circulation control device embedded in the wing. The rest of the structure is similar to that of an ordinary aircraft, and the structure is simple and easy to maintain. Due to the cancellation of conventional rudder surfaces, the original sharp edges, openings and bosses on the wing surface will disappear, which will reduce the radar scattering area of the aircraft and improve the stealth of the aircraft. The utility model has completed a real aircraft without rudder surfaces, and carried out systematic wind tunnel experiment and flight test research to it. The results of wind tunnel experiments show that the rudderless aircraft can produce 50° rudder deflection effect of the same width aileron and 20° elevator rudder deflection effect under the condition of 10m/s wind speed. According to the flight test results, the circulation control device designed by the utility model can control the attitude proportionally, the aircraft is very stable during the flight, and the rudderless test flight is very smooth.

The following are the basic parameters of the finished object of the utility model:

Name: A rudderless aircraft with independent air supply

Wingspan: 1.73m; aspect ratio: 5; captain: 1.25m; maximum take-off weight: 6.00kg; cruise speed: 15m/s; circulation control air source: multi-wing centrifugal fan; main wing leading edge sweep angle : 30°; canard wing sweep angle: 15°.

There are many specific application ways of the utility model, and the above descriptions are only the preferred implementation modes of the utility model. Improvements, these improvements should also be regarded as the protection scope of the present utility model.

Claims (3)

1. A rudderless aircraft supplied by an independent air source, comprising a fuselage (5), a main wing (3), a canard (6), a push-back power unit (7), a propeller (8), a wing A canard layout fixed-wing aircraft composed of tiplets (11), main landing gear (12) and front landing gear (13), is characterized in that: several circulation control devices are installed inside the main wing (3); The circulation control device includes a multi-blade centrifugal fan (2) and a Coanda trailing edge (10) connected by a nozzle (1), wherein the nozzle (1) consists of an upper sealing surface (15), a lower sealing surface (16) 1. A closed inner cavity composed of closed curved surfaces on both sides. The upper and lower closed surfaces are at 15° from the interface of the multi-blade centrifugal fan to the Coanda trailing edge. The air outlet slot (14); the nozzle pipe (1) is provided with a partition (17), and the partition (17) divides the nozzle pipe (1) into two upper and lower inner cavities with equal volume in the vertical direction, and each inner cavity The cavities are connected with an independent multi-blade centrifugal fan (2). 2. The rudderless aircraft supplied by an independent air source according to claim 1, characterized in that: the closed curved surface on both sides of the nozzle (1) is horizontally from the interface of the multi-blade centrifugal fan (2) to the The trailing edge (10) of Coanda gradually increases, and the inner cavity of the nozzle (1) is divided into several small cavities by the curved deflector (18). The small cavities are from the interface of the multi-blade centrifugal fan to the The cross-sectional area of any section at the trailing edge of Coanda is equal, and the cross-sectional area of any small cavity section at the trailing edge (10) of Coanda is the same as the inner cavity at the interface of the nozzle (1) multi-blade centrifugal fan (2) The cross-sectional area is equal. 3. The rudderless aircraft supplied by an independent air source according to claim 1, characterized in that: said main wing (3) is provided with a circulation control aileron exciter (4), and said ring The volume control aileron exciter (4) includes the aileron centrifugal fan and the aileron Coanda trailing edge connected by the aileron nozzle. The aileron nozzle includes two closed surfaces up and down. Aileron air outlet slots are respectively opened between the Coanda trailing edges.