阅读说明：本技术 一种改善飞机滚转稳定性的导流片及方法 (flow deflector for improving rolling stability of airplane and method thereof ) 是由 高亦非 陈春鹏 黄领才 于 2019-10-10 设计创作，主要内容包括：本发明属于飞机气动设计领域,具体涉及一种改善飞机滚转稳定性的导流片。由于螺旋桨上单翼飞机可能存在的在一定侧滑下出现的翼根提前分离而导致的滚转稳定性下降,本发明在机翼前缘下方的机身上对称安装导流片,通过导流片所产生的涡流,改变机翼前缘下方上洗流区域内流场,减小当地迎角,改善滚转稳定性,提高飞行安全。(The invention belongs to the field of airplane aerodynamic design, and particularly relates to flow deflectors for improving the rolling stability of an airplane, wherein the rolling stability is reduced due to the fact that wing roots possibly existing under fixed sideslip of a single-wing airplane on a propeller are separated in advance.)

A flow deflector for improving the rolling stability of an airplane is characterized in that the flow deflector is of a sheet structure, is symmetrically arranged on a fuselage below a wing leading edge, and is positioned in an upper wash-flow area below the wing leading edge.

2. The guide vane for improving the rolling stability of an airplane as claimed in claim 1, wherein the guide vane is fixed to the airplane body by riveting or screwing.

3. The guide vane for improving roll stability of an aircraft as claimed in claim 1, wherein the angle of intersection between the mounting surface and the water surface reference plane of the aircraft body when installed is in the range of 0 ° to 30 °.

4. The guide vane for improving aircraft roll stability as claimed in claim 1, wherein the guide vane is a rectangular plate structure with chamfers on the outer edges.

5. The guide vane for improving aircraft roll stability of claim 1, wherein the guide vane for improving aircraft roll stability has an area of 0.1-0.25 m²。

6. The guide vane for improving the rolling stability of an aircraft according to claim 1, wherein the aspect ratio is 1:3 to 1: 2.

7, A method for improving the stability of rolling of airplane, which is characterized in that the airframe below the front edge of the wing is symmetrically provided with flow deflectors, and the eddy current generated by the flow deflectors changes the flow field in the upper wash flow area below the front edge of the wing, reduces the local attack angle and improves the stability of rolling.

8. The method of improving aircraft roll stability of claim 7, wherein the process is as follows:

step 1: analyzing test data, checking stability, observing a wing leading edge flow field and determining an upper wash-out area through a wind tunnel test;

step 2: continuously adjusting the installation position and angle of the flow deflector in the upstream washing area, performing an air duct test, analyzing data and selecting an optimal position and angle;

and step 3: after the position and the angle are determined, the area of the flow deflector is reduced, resistance reduction treatment is carried out, and the minimum area meeting the rolling stability requirement is obtained;

and 4, step 4: the flow deflector is verified through a large-size wind tunnel test and numerical simulation.

The technical field is as follows:

the invention belongs to the field of aircraft aerodynamic design, and particularly relates to flow deflectors and a method for improving the rolling stability of an aircraft.

Background art:

in the flying process of the airplane, if the critical attack angle is exceeded, stall is easily generated, so that the left wing and the right wing are asymmetrically separated, unstable rolling torque is generated, and the flying safety is damaged.

For example, when a single-wing aircraft on a propeller is under fixed sideslip angles, the flow at the wing root of the upper single-wing aircraft is interfered by the propeller sliding flow, the aircraft body, the landing gear cabin and the sideslip flow, so that when the wing is under fixed sideslip, the local attack angle at the wing root is increased, separation is easy to generate, the rolling stability is suddenly reduced, and the flight safety risk is generated.

The invention content is as follows:

the invention aims to provide flow deflectors which have simple structures and low cost and can effectively eliminate the unstable rolling phenomenon of an airplane.

The technical scheme includes that flow deflectors for improving the rolling stability of the airplane are sheet-shaped structures and are symmetrically arranged on a fuselage below the front edge of the wing.

The flow deflector for improving the rolling stability of the airplane is positioned in the upper wash flow area below the front edge of the wing.

The flow deflector for improving the rolling stability of the airplane is fixed with the airplane body in a riveting or screwing mode.

When the flow deflector for improving the rolling stability of the airplane is installed, the incidence angle between the installation surface of the flow deflector and the water surface reference surface of the airplane body ranges from 0 degree to 30 degrees, so that a vortex with sufficient strength is formed, and the flow diversion effect is realized.

The flow deflector for improving the rolling stability of the airplane is of a rectangular flat plate structure, and chamfers are arranged on the outer edge of the flow deflector, so that the flow deflector has better pneumatic efficiency.

The area of the flow deflector for improving the rolling stability of the airplane is 0.1-0.25 m²To optimize the flow field and improve stability.

The flow deflector for improving the rolling stability of the airplane has the aspect ratio of 1: 3-1: 2 so as to form a vortex with sufficient strength and eliminate separation.

A method for improving the rolling stability of airplane features that the guide vanes are symmetrically installed to the fuselage below the front edge of wing to generate vortex, so changing the flow field in the upper wash flow region below the front edge of wing, decreasing local angle of attack and improving the rolling stability.

The method for improving the rolling stability of the airplane comprises the following steps:

step 1: analyzing test data, checking stability, observing a wing leading edge flow field and determining an upper wash-out area through a wind tunnel test;

step 2: continuously adjusting the installation position and angle of the flow deflector in the upstream washing area, performing an air duct test, analyzing data and selecting an optimal position and angle;

and step 3: after the position and the angle are determined, the area of the flow deflector is reduced, resistance reduction treatment is carried out, and the minimum area meeting the rolling stability requirement is obtained;

and 4, step 4: the flow deflector is verified through a large-size wind tunnel test and numerical simulation.

The invention has the technical effects that aiming at the reduction of the rolling stability caused by the separation of the wing root, the invention creatively provides the design of the flow deflector, the flow deflector is positioned at a specific position by , and the flow deflector with a specific structure and a specific shape is installed, so that the vortex with sufficient strength is formed on the flow deflector and acts on the wing flow field, the distribution of the flow field of the upper washing area of the wing leading edge is improved, the effective attack angle is reduced, the suction peak of the wing leading edge is reduced, the air flow separation when no flow deflector is arranged is avoided, the sideslip area with unstable rolling is reduced, and the rolling stability is improved.

Description of the drawings:

FIG. 1 is a view of the mounting location of the present invention for a vane to improve aircraft roll stability;

FIG. 2 is a schematic view of the configuration of a vane of the present invention for improving roll stability of an aircraft;

FIG. 3 is a comparative graph of lift coefficient versus yaw angle without and without a vane;

FIG. 4 is a schematic diagram comparing the roll torque coefficient with the change of the side slip angle without the power and with the guide vane;

FIG. 5 is a comparative graphical illustration of lift coefficient versus yaw angle with and without the use of a vane under power;

FIG. 6 is a graph comparing roll torque coefficient with yaw angle for a dynamic diaphragm and a dynamic diaphragm.

The specific implementation mode is as follows:

the invention is further illustrated in with reference to the following figures and examples:

referring to fig. 1 and 2, the flow deflector for improving the rolling stability of the aircraft has a rectangular sheet structure with an aspect ratio of 1: 3-1: 2, and the structural shape of the flow deflector is different from that of a conventional flow deflector (the conventional flow deflector is curved and used for guiding airflow and changing the direction of fluid and does not relate to the rolling stability problem), the sheet structure influences the airflow to form a vortex with sufficient strength, the separation is eliminated, and better stability is obtained.

Particularly, the installation position of the guide vane needs to be located in an upper washing flow area below the front edge of the wing, so that the direction of the upper washing flow area below the front edge of the wing is changed through the vortex generated by the guide vane, the local attack angle is reduced, the stall is delayed, the sideslip area with stable rolling is enlarged, and the rolling stability is improved.

The invention relates to a method for improving the rolling stability of an airplane, which is characterized in that flow deflectors are symmetrically arranged on a fuselage below a front edge of an airplane wing, and a flow field in an upper washing area below the front edge of the airplane wing is changed through a vortex generated by the flow deflectors, so that the local attack angle is reduced, and the rolling stability is improved.

The method for improving the rolling stability of the airplane comprises the following steps:

step 1: analyzing full-aircraft aerodynamic force test data through a small-size wind tunnel test, checking the longitudinal and transverse aerodynamic stability of an airplane, observing a wing leading edge flow field, and determining an upper washing flow area;

step 2, initially selecting positions in the upper washing flow area to install the guide vanes, then carrying out wind tunnel tests, analyzing full-aircraft aerodynamic force test data, continuously adjusting the installation positions and angles of the guide vanes according to test results, repeatedly carrying out wind tunnel tests, analyzing the data and selecting the optimal positions and angles for installing the guide vanes, wherein the initial installation positions of the guide vanes are -like selected at the center position of the upper washing flow area.

Step 3, after the position and the angle are determined, drag reduction treatment is carried out, the area of the guide vane is continuously reduced, times of small-area guide vanes are changed to carry out wind tunnel test, and whether smaller-area guide vanes are selected or not is judged according to the test result until the guide vanes with the minimum area meeting the rolling stability requirement are obtained;

and 4, performing large-size wind tunnel tests and/or numerical simulation under the condition that the small-size wind tunnel tests meet the requirements, verifying the guide vane, and performing -step optimization on the position, the angle and the like of the guide vane by referring to the small-size wind tunnel test method if the large-size wind tunnel tests do not meet the requirements.

The propeller-type airplane is taken as a platform below, flow deflectors (symmetrically arranged on two sides) are designed in front of a landing gear nacelle, the aspect ratio of the flow deflectors is 0.42, and the area of the flow deflectors is 0.183m²The plane is 16 degrees from the horizontal reference plane of the machine body, the two sides of the outer edge are rounded at 45 degrees, the central position of the flow deflector is 250mm away from the horizontal reference plane of the machine body, and the flow field distribution and the stability can be effectively improved through the optimal design of the appearance shape, the size and the position of the flow deflector.

The two unpowered implementation conditions are divided below, and the guide vanes are verified to change the local flow field of the wing, eliminate the close coupling between the landing gear bay and the wing, reduce the local incidence angle of the wing leading edge and improve the roll stability.

Referring to fig. 3 and 4 (unpowered and non-ground effect flap 45 ° state), in fig. 3, when there is no guide vane, the position where the wing starts to stall sideslips at-11 °, and after the guide vane is taken, the position where the wing starts to stall is pushed back, so that the rolling stability at-11 ° is recovered, as shown in fig. 4.

Referring to fig. 5 and 6, the wind tunnel test results of the states of flap 20 ° and attack angle 7 ° under the condition of power, i.e. propeller rotation, and the tension coefficient Tc equal to 0.31. The position of the wing with the guide vane, which starts to stall, is delayed from minus 6 degrees to minus 11 degrees, so that the sideslip stable area is effectively expanded, and the rolling stability is improved.

The above description is only an embodiment of the present invention, but the scope of the present invention is not limited thereto, and can be applied to other surface vehicles, such as seaplanes, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention should be covered by the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.