CN105314096B - Individual gas sources supply without rudder face aircraft - Google Patents

Abstract

The invention 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 unit, a propeller, and a winglet 1. The main landing gear and the front 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 invention relates to the field of aviation machinery, in particular to a rudderless aircraft supplied with air from 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.

Contents of the invention

In order to solve the problems of the prior art, the present invention provides an aircraft without rudder surfaces supplied by an independent air source, which replaces the traditional rudder surfaces with a circulation control device, 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.

The invention 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. Control device; the circulation control device includes a multi-blade centrifugal fan and a Coanda 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 by differential deflection, and the non-rudder surface aircraft of the present invention 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 The pipe includes upper and lower two closed surfaces, and aileron air outlet slots are arranged between the lower closed surface of the aileron nozzle and the trailing edge of the aileron Coanda.

The beneficial effects of the present invention 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 invention 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 a schematic diagram of the structure of the present invention.

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 invention provides a rudderless aircraft supplied by an independent air source, its structure as shown in Figure 1, Figure 2 and Figure 3, comprising a fuselage 5, a main wing 3, a canard 6, a push-back power unit 7. The canard layout fixed-wing aircraft composed of propeller 8, winglet 11, main landing gear 12 and nose landing gear 13 has a circulation control device installed inside the main wing, which can realize rolling without relying on conventional ailerons and elevators. Rotation and pitch attitude control to achieve 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 present invention designs the nozzle from the air inlet into two separate upper and lower parts, separated by a flat plate in the middle, and the upper and lower parts have the same cavity volume, see 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 circular Coanda trailing edge 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 ejected 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 by differential deflection, and the non-rudder surface aircraft of the present invention 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 present invention 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 the air flow is controlled by the Coanda The effect creates a favorable 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 invention is a canard layout, and the traditional rudder surface is canceled, and the circulation control device embedded in the wing is replaced. The rest of the structure is similar to that of ordinary aircraft, simple in structure 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 present invention has completed a real aircraft without a rudder surface, and has carried out systematic wind tunnel experiments and flight test research on 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 invention 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 finished physical basic parameters of the present invention:

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 approaches of the present invention, and the above description is only a preferred embodiment of the present invention. It should be pointed out that for those of ordinary skill in the art, some improvements can also be made without departing from the principles of the present invention. Improvements should also be regarded as the protection scope of the present invention.

Claims (2)

1. a kind of individual gas sources supply without rudder face aircraft, including by fuselage（5）, host wing（3）, canard（6）, back-pushed move Power apparatus（7）, propeller（8）, winglet（11）, main landing gear（12）And nose-gear（13）The canard configuration of composition is fixed Rotor aircraft, it is characterised in that：Host wing（3）Inside is provided with some circulation control devices；Described circulation control device bag Include by jet pipe（1）The multi-wing centrifugal fan of connection（2）With coanda trailing edge（10）, wherein jet pipe（1）Including by upper sealing surface （15）, lower sealing surface（16）, both sides occluding surface composition closing inner chamber, up and down two sealing surfaces in 15 ° from multi-wing centrifugal wind Machine interface shrinks to coanda trailing edge to merge, and has out air cleft between two sealing surfaces and coanda trailing edge up and down（14）； Jet pipe（1）In be provided with dividing plate（17）, dividing plate（17）By jet pipe（1）In the vertical direction be divided into volume it is equal up and down in two Chamber, each inner chamber with an independent multi-wing centrifugal fan（2）It is connected；Described jet pipe（1）Both sides occluding surface level side Upwards from multi-wing centrifugal fan（2）Interface is to coanda trailing edge（10）Place gradually increases, jet pipe（1）Led by shaped form inner chamber Flow plate（18）Be divided into some areolas, described areola from multi-wing centrifugal fan interface to coanda trailing edge at arbitrarily cut The sectional area in face is equal, coanda trailing edge（10）Locate the sectional area and jet pipe in any one areola section（1）Multi-wing centrifugal wind Machine（2）The intracavity section product of interface is equal.

2. individual gas sources according to claim 1 supply without rudder face aircraft, it is characterised in that：Described host wing （3）It is provided with circulation control aileron driver（4）, described circulation control aileron driver（4）Including being connected by aileron jet pipe The aileron centrifugal blower and aileron coanda trailing edge connect, aileron jet pipe includes sealing surface under two sealing surfaces up and down, aileron jet pipe Aileron, which is had, between aileron coanda trailing edge goes out air cleft.