Combined jet course control surface of aircraft

Abstract

The invention provides a combined jet course control surface of an aircraft, and belongs to the technical field of active flow control. The control surface comprises a jet exciter and a circular rector exciter which are mounted on a wing; the jet exciter is located in the middle section area of the upper surface of the wing and provided with a first jet outlet located in the upper surface, and the included angle between the outlet direction of the first jet outlet and the corresponding incoming flow direction of the wing is larger than 90 degrees. The circular rector exciter is located in the trailing edge area of the upper surface of the wing and provided with a second jet flow outlet located in the upper surface, and the included angle between the outlet direction of the second jet flow outlet and the corresponding incoming flow direction of the wing is smaller than 90 degrees. The jet flow exciter and the circular rector exciter are combined to achieve the control effect of stabilizing lift force and increasing resistance, longitudinal and transverse torque coupling is reduced, decoupling design of a control surface is achieved, the course control effect of a combined mechanical control surface is formed, the control effect is improved, meanwhile, coupling of the torque control characteristic and the attack angle is reduced, and the control characteristic is improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of active flow control, and particularly relates to a combined jet heading control rudder surface for an aircraft. Background Art

[0002] The heading attitude control of a flying wing layout aircraft is usually achieved by using drag-type control rudder surfaces, that is, by generating a yaw moment through the drag difference on both sides of the aircraft to achieve yaw attitude control. Common ones include differential inner and outer ailerons, split rudders, combined spoilers, full-moving wingtips, etc.

[0003] The mechanical control method of the rudder surface generates a yaw moment through the deflection of the mechanical rudder surface, which will bring a series of problems in stealth, aerodynamics, control, and structure. The jet-type heading attitude control method simplifies the aircraft structure and can solve the problems existing in the mechanical rudder surface, but the direct jet control method has problems of low control efficiency and insufficient control ability, and will also generate serious longitudinal and lateral moment coupling, and the control characteristics are coupled with the angle of attack, making the aerodynamic characteristics modeling and operation of heading control extremely complex.

[0004] Therefore, how to design a heading control rudder surface that takes into account the heading control efficiency, control ability, control characteristics, and the improvement of the comprehensive performance of stealth and aerodynamics is a difficult problem encountered by aircraft overall, aerodynamic, and control designers. Summary of the Invention

[0005] The purpose of the present application is to provide a combined jet heading control rudder surface for an aircraft to solve the above technical problems existing in the prior art.

[0006] The present application is implemented as follows: The present application provides a combined jet heading control rudder surface for an aircraft, including a jet actuator and a circulation actuator installed on the wing; the jet actuator is located in the middle section area of the upper surface of the wing, the jet actuator has a first jet outlet located on the upper surface, and the included angle between the outlet direction of the first jet outlet and the oncoming flow direction corresponding to the wing is greater than 90 degrees; the circulation actuator is located in the trailing edge area of the upper surface of the wing, the circulation actuator has a second jet outlet located on the upper surface, and the second jet outlet faces the trailing edge of the wing, and the included angle between the outlet direction of the second jet outlet and the oncoming flow direction corresponding to the wing is less than 90 degrees.

[0007] The technical solution adopted by the present invention can achieve the following beneficial effects: In this application, by setting the angle between the outlet direction of the first jet outlet of the jet actuator and the oncoming flow direction to be greater than 90 degrees, the jet actuator is used to force the flow separation on the upper surface of the wing, achieving the control effect of destroying lift and increasing drag; and by setting the angle between the outlet direction of the second jet outlet of the circulation actuator and the oncoming flow direction to be less than 90 degrees, the jet deflects towards the lower surface of the wing, generating the control effect of increasing lift and increasing drag; by using the jet actuator and the circulation actuator in cooperation to form the control effect of stable lift and increased drag, a drag difference can be generated between the left and right wings, forming a yaw control moment, improving the control efficiency. Moreover, the longitudinal and lateral moment coupling is reduced, the decoupling design of the control surface is realized, the heading control effect of the combined mechanical control surface is formed, the control ability is improved, and at the same time, the coupling between the moment control characteristics and the angle of attack is reduced, and the control characteristics are improved. In addition, in this application, the heading control force is formed by combining jets, the traditional mechanical control surface is cancelled, the overall stealth performance of the aircraft is improved, the structural weight is reduced, and the space utilization rate is increased. Brief Description of the Drawings

[0008] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following will briefly introduce the drawings required for use in the embodiments of the present invention or the description of the prior art. Obviously, the following described drawings are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0009] Figure 1 It is a schematic diagram of the overall structure of the aircraft corresponding to the control surface provided by some embodiments of this application; Figure 2 It is a cross-section of the wing corresponding to the control surface provided by some embodiments of this application Figure 1 ; Figure 3 It is about the Figure 2 detail drawing at point A provided by some embodiments of this application; Figure 4 It is about the Figure 2 detail drawing at point B provided by some embodiments of this application; Figure 5 It is a cross-section of the wing corresponding to the control surface provided by some embodiments of this application Figure 2 ; Figure 6 It is about the Figure 5 detail at point C provided by some embodiments of this application Figure 1 ; Figure 7 It is about the Figure 5 detail at point C provided by some embodiments of this application Figure 2 ; Figure 8This is the detail at position D provided by some embodiments of the present application regarding Figure 5 the detail at position D Figure 1 ; Figure 9 This is the detail at position D provided by some embodiments of the present application regarding Figure 5 the detail at position D Figure 2 .

[0010] In the figure: 10 - aircraft, 100 - wing, 110 - upper surface, 120 - lower surface, 200 - jet actuator, 210 - first jet outlet, 220 - jet excitation cavity, 300 - circulation actuator, 310 - second jet outlet, 320 - circulation excitation cavity, 410 - first Coanda surface, 420 - second Coanda surface, 500 - separation surface, 610 - first step surface, 620 - second step surface. Detailed implementation manners

[0011] To make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions of the present invention will be described in detail below. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. All other implementation manners obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts fall within the scope protected by the present invention.

[0012] The terms "first", "second", etc. in the description and claims of the present application are used to distinguish similar objects, rather than to describe a specific order or sequence. It should be understood that such used data may be interchanged under appropriate circumstances so that the embodiments of the present application can be implemented in an order other than those illustrated or described herein, and the objects distinguished by "first", "second", etc. are generally of the same type, and do not limit the number of objects. For example, the first object may be one or multiple.

[0013] Some embodiments of the present application provide a combined jet heading control rudder surface for an aircraft. Referring to Figure 1 , Figure 2 and Figure 5 as shown, it includes a jet actuator 200 and a circulation actuator 300 installed on the wing 100. The jet actuator 200 is located in the middle section area of the upper surface 110 of the wing 100, and the circulation actuator 300 is located in the trailing edge area of the upper surface 110 of the wing 100.

[0014] The two ends of the wing 100 are the leading edge and the trailing edge respectively. When the aircraft 10 is flying, the part of the wing 100 that first contacts the airflow is the leading edge, and the part of the wing 100 that finally contacts the airflow is the trailing edge. The middle section area of the wing 100 refers to the area around the midpoint of the wing 100 along the oncoming flow direction, and the middle section area is located between the leading edge and the trailing edge.

[0015] The jet actuator 200 has a first jet outlet 210, and the first jet outlet 210 is disposed on the upper surface 110. The jet outputs from the jet actuator 200 through the first jet outlet 210 toward the outside of the upper surface 110. And the included angle between the outlet direction of the first jet outlet 210 and the oncoming flow direction corresponding to the wing 100 is greater than 90 degrees.

[0016] Reference Figure 6 And Figure 8 As shown, the oncoming flow direction corresponding to the wing 100 refers to the flow direction of the air flow on the surface of the wing 100 when the aircraft 10 is flying, and the oncoming flow direction is represented by a dotted arrow.

[0017] The jet output from the first jet outlet 210, without being interfered, will output outward along the outlet direction of the first jet outlet 210. At the same time, due to the disappearance of the circumferential constraint, the jet will spread around.

[0018] The included angle between the outlet direction of the first jet outlet 210 and the oncoming flow direction is greater than 90 degrees, indicating that the jet output from the first jet outlet 210 has a component opposite to the oncoming flow direction. The jet is opposite to the oncoming flow direction, which can force the flow separation on the upper surface 110 of the wing 100, achieving the control effect of destroying lift and increasing drag. Reference Figure 6 As shown, the outlet direction of the first jet outlet 210 is represented by a solid arrow, and the oncoming flow direction is represented by a dotted arrow, and the included angle formed between the two is greater than 90 degrees. The outlet direction of the first jet outlet 210 refers to the direction along the axis of the first jet outlet 210 and toward the outside of the wing 100.

[0019] The circulation actuator 300 has a second jet outlet 310, and the second jet outlet 310 is disposed on the upper surface 110. The jet outputs from the circulation actuator 300 through the second jet outlet 310 toward the outside of the upper surface 110. The second jet outlet 310 faces the trailing edge of the wing 100, and the included angle between the outlet direction of the second jet outlet 310 and the oncoming flow direction corresponding to the wing 100 is less than 90 degrees.

[0020] The jet output from the second jet outlet 310, without being interfered, will output outward along the outlet direction of the second jet outlet 310. At the same time, due to the disappearance of the circumferential constraint, the jet will spread around. The included angle between the circumferential direction of the second jet outlet 310 and the oncoming flow direction is less than 90 degrees, indicating that the jet output from the second jet outlet 310 has a component in the same direction as the oncoming flow direction. The jet is in the same direction as the oncoming flow direction, which can flow together with the oncoming flow along the upper surface 110 of the wing 100 and deflect toward the lower surface 120 of the wing 100, generating the control effect of increasing lift and increasing drag. Figure 8In the figure, the outlet direction of the second jet outlet 310 is represented by a solid arrow, and the oncoming flow direction is represented by a dashed arrow. The included angle formed between the two is less than 90 degrees. The outlet direction of the second jet outlet 310 refers to the direction along the axis of the second jet outlet 310 and facing outward from the wing 100.

[0021] In the embodiment of the present application, the jet actuator 200 and the circulation actuator 300 are cooperated, and by restricting the installation positions and jet outlet directions of the two actuators, a control effect of forming stable lift and increasing drag is formed, so that a drag difference is generated between the left and right wings 100, a yaw control moment is formed, the control efficiency is improved, and moreover, the longitudinal and lateral moment coupling is reduced, the decoupling design of the control surface is realized, the heading control effect of the combined mechanical control surface is formed, and at the same time, the coupling between the moment control characteristic and the angle of attack is reduced, and the control characteristic is improved.

[0022] In addition, the jet of the jet actuator 200 and the jet of the circulation actuator 300 form a heading control ability, realizing the heading attitude control without a mechanical control surface, canceling the traditional mechanical control surface, eliminating the damage of the deflection of the traditional mechanical control surface to the whole-aircraft stealth characteristic, improving the omnidirectional stealth performance of the aircraft 10, reducing the structural weight, and improving the space utilization rate.

[0023] The jet actuator 200 includes a jet excitation chamber 220, and the first jet outlet 210 is communicated with the jet excitation chamber 220. The jet actuator 200 is connected with a gas pipeline, and the gas pipeline supplies gas to the jet excitation chamber 220. Refer to Figure 3 、 Figure 6 and Figure 7 As shown, the jet excitation chamber 220 is located inside the wing 100, and one jet actuator 200 only has one jet excitation chamber 220 and one first jet outlet 210.

[0024] In some preferred embodiments, refer to Figure 3 、 Figure 6 and Figure 7 As shown, the first jet outlet 210 is connected with a first Coandă surface 410. The first Coandă surface 410 is located on the side of the first jet outlet 210 away from the trailing edge of the wing 100. After the jet comes out from the first jet outlet 210, it can adhere to the first Coandă surface 410 and flow. And one end of the first Coandă surface 410 is connected to the first jet outlet 210, and the end far from the first jet outlet 210 is connected to the upper surface 110. And, the first Coandă surface 410 is tangent to the upper surface 110 at the connection between the two, and a smooth transition is formed between the first Coandă surface 410 and the upper surface 110.

[0025] The Coandă surface is a convex surface with continuously varying curvature. The jet output from the first jet outlet 210 adheres to the first Coandă surface 410 and flows gradually to the upper surface 110 connected to the first Coandă surface 410, in the opposite direction to the oncoming flow direction on the upper surface 110. Utilizing the Coandă effect, after the jet is output from the first jet outlet 210, it can adhere to the first Coandă surface 410 and flow to the upper surface 110 of the wing 100, thereby improving the flow separation effect generated by the jet output from the first jet outlet 210 on the upper surface 110 of the wing 100, and improving the control effect of destroying lift and increasing drag. In a preferred embodiment, the inner wall of the first jet outlet 210 is tangentially arranged with the first Coandă surface 410, which is more convenient for fluid flow.

[0026] In some preferred embodiments of the present application, the first jet outlet 210 is further connected to a separation surface 500, and the separation surface 500 is located on one side of the first jet outlet 210 close to the trailing edge of the wing 100. The first Coandă surface 410 and the separation surface 500 are respectively located on both sides of the first jet outlet 210. And along the jet output direction of the jet actuator 200, the distance between the separation surface 500 and the axis of the first jet outlet 210 increases. Refer to Figure 7 As shown, the farther the distance from the first jet outlet 210, the farther the distance between the separation surface 500 and the axis of the first jet outlet 210, and the less likely the jet output from the first jet outlet 210 is to adhere to the separation surface 500.

[0027] On both sides of the first jet outlet 210 are the first Coandă surface 410 and the separation surface 500 respectively, and the jet flows towards the first Coandă surface 410. The structure of the first Coandă surface 410 can improve the adhesion effect of the jet. After the jet is output from the first jet outlet 210, the distance between the separation surface 500 and the jet gradually increases, which is beneficial to reducing the possibility of the jet adhering to the separation surface 500, thereby improving the adhesion effect of the jet on the first Coandă surface 410 to a certain extent, improving the flow separation effect generated by the jet output from the first jet outlet 210 on the upper surface 110 of the wing 100, and improving the control effect and control efficiency of the jet actuator 200.

[0028] The distance between the separation surface 500 and the axis of the first jet outlet 210 can be the shortest distance between the separation surface 500 and the axis, and along the jet output direction, the shortest distance between the two gradually increases. The distance between the separation surface 500 and the axis of the first jet outlet 210 can also be the distance between the two in any direction, and along the jet output direction, the distance between the two in this direction gradually increases.

[0029] In some preferred embodiments, refer to Figure 7As shown, a first stepped surface 610 is also connected between the first jet outlet 210 and the first Coanda surface 410, and the first stepped surface 610 is perpendicular to the first Coanda surface 410.

[0030] The first stepped surface 610 can change the flow direction and velocity distribution of the jet output from the first jet outlet 210, making it easier for the jet to adhere along the first Coanda surface 410, thereby enhancing the Coanda effect. Moreover, the first stepped surface 610 can provide a local flow obstruction, making the flow of the jet on the first Coanda surface 410 more stable and reducing flow separation caused by excessive velocity changes or pressure gradients; the first stepped surface 610 can also change the pressure distribution of the jet on the first Coanda surface 410 to make it more uniform; and the first stepped surface 610 can also change the boundary layer characteristics of the fluid, reduce the occurrence of turbulence, and thus improve the stability of the flow.

[0031] In the case where the height of the first stepped surface 610 is zero, that is, the first jet outlet 210 is directly connected to the first Coanda surface 410, referring to Figure 3 and Figure 6 as shown, the edge of the first jet outlet 210 is smoothly connected to the first Coanda surface 410 to avoid the influence of uneven connection between the two on the flow of the jet.

[0032] The included angle corresponding to the first Coanda surface 410 is , , referring to Figure 7 as shown, along the output direction of the jet, the included angle formed by the connection line between the two ends of the first Coanda surface 410 and the center of the circle corresponding to the first Coanda surface 410 is . The first Coanda surface 410 is a convex surface with continuously changing curvature, and the size of the included angle determines the length and extension direction of the Coanda surface, restricting to be between 0 degrees and 90 degrees to ensure that the first Coanda surface 410 can cooperate with the jet smoothly and adjust the output direction of the jet.

[0033] The farther the separation surface 500 deviates from the axis of the first jet outlet 210, the weaker the influence of the separation surface 500 on the jet. In some embodiments of the present application, the included angle between the separation surface 500 and the axis of the first jet outlet 210 is defined as , , , and the specific position of Figure 7 is shown in The larger is, the more the separation surface 500 deviates from the first jet outlet 210. To avoid affecting the normal flow of the oncoming flow, is the maximum value of

[0034] Referring toFigure 4 , Figure 8 and Figure 9 As shown in Figure 4 , Figure 8 and Figure 9 , the circulation actuator 300 includes a circulation excitation cavity 320, which is located within the wing 100 and communicates with the second jet outlet 310. The circulation excitation cavity 320 is connected to a gas pipeline for supplying gas to the circulation excitation cavity 320.

[0035] Refer to Figure 4 , Figure 8 and Figure 9 As shown in Figure 4 , Figure 8 and Figure 9 , the second jet outlet 310 is connected to a second Coandă surface 420. The end of the second Coandă surface 420 away from the second jet outlet 310 abuts against the lower surface 120 of the wing 100, and the second Coandă surface 420 is tangent to the lower surface 120 at their abutting position.

[0036] The second Coandă surface 420 is located on the side of the second jet outlet 310 close to the trailing edge end of the wing 100 and abuts against the lower surface 120 of the wing 100. The jet output from the second jet outlet 310 flows along the second Coandă surface 420 and deflects downward under the Coandă effect, producing a control effect of increasing lift and increasing drag. In a preferred embodiment, the inner wall of the second jet outlet 310 is tangent to the second Coandă surface 420, which is more convenient for fluid flow.

[0037] The circulation actuator 300 is only provided on the upper surface 110 of the wing 100. After the jet is output from the second jet outlet 310, it flows along the second Coandă surface 420 to the lower surface 120 of the wing 100 to produce a control effect of increasing lift and increasing drag. The setting of the second Coandă surface 420 is relatively flexible and has a wide range of settings. In some embodiments of the present application, the angle corresponding to the second Coandă surface 420 is defined as , , For the specific position of Figure 9 refer to the illustration in Figure 9 . It needs to be greater than 90 degrees to ensure that the jet attached to the second Coandă surface 420 can deflect to the lower surface 120. Along the output direction of the jet, the angle formed by the connection lines at both ends of the second Coandă surface 420 and the center of the circle corresponding to the second Coandă surface 420 is .

[0038] In some embodiments of the present application, a second stepped surface 620 is further connected between the second jet outlet 310 and the second Coandă surface 420. As shown in Figure 9 , the second stepped surface 620 is perpendicular to the second Coandă surface 420. The effect of the second stepped surface 620 is similar to that of the first stepped surface 610, generally playing a role in enhancing the Coandă effect and improving the control effect and control efficiency of the circulation actuator 300.​​

[0039] When the height of the second stepped surface 620 is zero, the second Coanda surface 420 is directly connected to the edge of the second jet outlet 310, and the connection between the two is smoothly transitioned to avoid affecting the flow of the jet, thereby affecting the control effect of the circulation actuator 300.

[0040] Reference Figure 1 As shown, in some embodiments of the present application, along the length direction of the wing 100, the length of the jet actuator 200 is the same as the length of the circulation actuator 300. The length direction of the wing 100 refers to the direction from the fuselage of the aircraft 10 to the tip of the wing 100. The same length of the jet actuator 200 and the circulation actuator 300 is more convenient for their mutual cooperation to improve the heading control efficiency and control ability of the aircraft 10. Preferably, the first jet outlet 210 and the second jet outlet 310 are arranged in parallel.

[0041] In some embodiments, temperature sensors and pressure sensors are arranged inside both the jet actuator 200 and the circulation actuator 300 to measure the temperature and total pressure of the jet respectively, which is more convenient for controlling the aircraft 10.

[0042] In actual implementation, the longitudinal and lateral control moments generated by the combined rudder surface control can be regulated by adjusting the chordwise position of the first jet outlet 210 of the jet actuator 200 on the upper surface 110 of the wing 100, so that the longitudinal and lateral coupling moments are minimized. Moreover, the aerodynamic gain of the combined control between the pressure ratio of the jet actuator 200 and the pressure ratio of the circulation actuator 300 can be established through calculation or experiment to further improve the heading control efficiency of the aircraft 10. The pressure ratio refers to the ratio between the internal pressure of the actuator and the atmospheric pressure.

[0043] By establishing the optimal combined control parameters of the pressure ratio of the jet actuator 200 and the pressure ratio of the circulation actuator 300, and obtaining the heading control rudder efficiency, the coupled longitudinal and lateral control moments and their variation relationships with the angle of attack under the combined control parameters, an aerodynamic database is established to form a combined jet heading control rudder efficiency scheme, which fully improves the control efficiency of the heading.

[0044] It should be noted that in this article, the term "including", "comprising" or any other variant thereof is intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements not only includes those elements, but also includes other elements not expressly listed, or elements inherent to such process, method, article or device. Without further limitation, an element defined by the statement "including a..." does not exclude the existence of additional identical elements in the process, method, article or device including that element.

[0045] The above are only specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention can easily think of changes or substitutions, which should all be covered within the protection scope of the present invention.

Claims

1. A combined jet heading control rudder surface of an aircraft, characterized in that It includes a jet actuator (200) and a circulation actuator (300) installed on the wing (100); The jet actuator (200) is located in the middle section area of the upper surface (110) of the wing (100). The jet actuator (200) has a first jet outlet (210) located on the upper surface (110). The included angle between the outlet direction of the first jet outlet (210) and the oncoming flow direction corresponding to the wing (100) is greater than 90 degrees; The circulation actuator (300) is located in the trailing edge area of the upper surface (110) of the wing (100). The circulation actuator (300) has a second jet outlet (310) located on the upper surface (110), and the second jet outlet (310) faces the trailing edge of the wing (100). The included angle between the outlet direction of the second jet outlet (310) and the oncoming flow direction corresponding to the wing (100) is less than 90 degrees.

2. The combined jet heading control rudder surface of an aircraft according to claim 1, characterized in that The first jet outlet (210) is connected to a first Coandă surface (410). The first Coandă surface (410) is located on the side of the first jet outlet (210) away from the trailing edge of the wing (100). The end of the first Coandă surface (410) away from the first jet outlet (210) is connected to the upper surface (110), and the first Coandă surface (410) is tangent to the upper surface (110) at the connection between the two.

3. The combined jet heading control rudder surface of an aircraft according to claim 2, characterized in that, The first jet outlet (210) is also connected to a separation surface (500). The separation surface (500) is located on the side of the first jet outlet (210) close to the trailing edge of the wing (100). Along the jet output direction of the jet actuator (200), the distance between the separation surface (500) and the axis of the first jet outlet (210) gradually increases.

4. The combined jet heading control rudder surface of an aircraft according to claim 2, characterized in that, A first stepped surface (610) is also connected between the first jet outlet (210) and the first Coandă surface (410). The first stepped surface (610) is perpendicular to the first Coandă surface (410).

5. A combined jet heading control rudder surface for an aircraft according to claim 3, characterized in that, The included angle corresponding to the first Coanda surface (410) is , .

6. The combined jet heading control rudder surface of an aircraft according to claim 5, characterized in that, The included angle between the separation surface (500) and the axis of the first jet outlet (210) is , .

7. A combined jet heading control rudder surface of an aircraft according to claim 1, characterized in that The circulation actuator (300) includes a circulation excitation cavity (320). The circulation excitation cavity (320) is located inside the wing (100) and is communicated with the second jet outlet (310). The second jet outlet (310) is connected to a second Coandă surface (420). The end of the second Coandă surface (420) away from the second jet outlet (310) is connected to the lower surface (120) of the wing (100), and the second Coandă surface (420) is tangent to the lower surface (120) at the connection between the two.

8. The combined jet heading control rudder surface of an aircraft according to claim 7, characterized in that, The included angle corresponding to the second Coanda surface (420) is , .

9. The combined jet heading control rudder surface of an aircraft according to claim 7, characterized in that A second stepped surface (620) is also connected between the second jet outlet (310) and the second Coandă surface (420). The second stepped surface (620) is perpendicular to the second Coandă surface (420).

10. A combined jet heading control rudder surface for an aircraft according to claim 1, characterized in that, Along the length direction of the wing (100), the length of the jet actuator (200) is the same as the length of the circulation actuator (300).

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