An airborne lightweight dual-channel circulation control unit

Abstract

The invention discloses an airborne lightweight dual-channel circulation control unit, the circulation control unit comprises at least two independent jet channels, which share a middle wall surface; the jet channel comprises at least an air source inlet, a transition section, a rectifying section and a jet outlet, the air source inlets of the two jet channels adopt a cross-displacement design, the air source inlet axes are in the same plane and pass through the center line of the Coanda profile, and adopt a reverse external thread design, the transition section is a circular channel turning into a rectangular channel, and there is a boss on the side of the transition section outlet away from the other jet channel, and a pressure sensor and a temperature sensor are arranged on the boss, flow reinforcement ribs are arranged in the rectifying section, and adjacent reinforcement ribs adopt an intermittent dislocation structure, which is used for rectifying and reinforcing the structure of the jet channel, and the weight and volume of the structure are reduced as much as possible while meeting the structural safety, the outer profile of the tail end of the circulation control unit is seamlessly combined with the outer profile of the trailing edge of the wing, and is positioned and fixed on the aircraft by mesh brackets on both sides.

Description

Technical Field

[0001] The invention belongs to the field of circulation control and relates to a dual-channel circulation control unit, in particular to an airborne lightweight dual-channel circulation control unit. Background Art

[0002] Most existing aircraft use traditional mechanical control surfaces to change the aerodynamic force and torque of the aircraft for flight attitude control, but this control method has some inherent defects: the deflection of the control surface changes the volume and shape of the aircraft, destroys the stealth design of the aircraft's aerodynamic shape, and reduces low observability; the gaps, steps, and bulges generated between the active surface and the stabilizer and between the active surface destroy the seamless and smooth continuous design principles of the wing, and increase additional aerodynamic resistance; limited by the incoming flow velocity pressure, the control efficiency is low at low speed and the control ability is insufficient; the control link is complex, the structure is heavy, the space utilization rate is low, and the maintenance is complicated. Therefore, the traditional mechanical control surface control method can no longer meet the higher requirements of the integrated design of aerodynamics / stealth / control / structure of future combat aircraft, and it is urgent to develop a new aerodynamic control technology.

[0003] Active jet circulation control technology realizes flight control of aircraft without mechanical control surfaces by generating virtual control surfaces through jets. It is a very promising active flow control technology. As an active jet circulation control actuator, the circulation control unit is the key to the application of active jet circulation control technology. It is arranged at the trailing edge of the wing along the span direction, and the jet slot is arranged along the span direction. High-temperature and high-pressure gas is ejected from the slot at the trailing edge of the actuator through the internal flow channel. For the large aspect ratio circulation control unit, it is necessary to ensure the uniformity of the jet along the span direction and reduce the pressure loss, and also meet the requirements of the structural strength of the high-pressure ratio gas, while meeting the narrow installation space requirements of the pointed trailing edge wing. The weight of the actuator directly affects the engineering applicability of the active jet circulation control technology. Therefore, the design constraints of the airborne circulation control unit are very many and relatively complex.

[0004] From the above, it can be seen that the circulation control unit is a key aerodynamic component for realizing jet circulation control technology, and it is also a very important component for promoting engineering applications. Therefore, it is necessary to carry out the design of an airborne lightweight dual-channel circulation control unit. Summary of the invention

[0005] The purpose of the present invention is to provide an airborne lightweight dual-channel circulation control unit to overcome the defects of the prior art, wherein the circulation control unit can meet the requirements of high pressure ratio air source control and narrow wing trailing edge installation space.

[0006] The object of the present invention is achieved through the following technical solutions:

[0007] An airborne lightweight dual-channel circulation control unit, the circulation control unit comprises a first jet channel and a second jet channel, the first jet channel and the second jet channel are respectively provided with an air source inlet, a transition section, a rectifying section and a jet outlet in sequence; the air source inlet comprises a first air source inlet and a second air source inlet corresponding to the first jet channel and the second jet channel respectively, the first air source inlet and the second air source inlet are staggered, and the axes of the two air source inlets are parallel and in the same plane, and the plane passes through the center line of a Coanda surface set at the end of the control unit; the first jet channel and the second jet channel are arranged in an overlapping manner, and the two jet channels share an intermediate wall surface in the rectifying section; the jet outlets of the first jet channel and the second jet channel are respectively provided with jet nozzles, and a Coanda surface is provided at the end of the intermediate wall surface, the Coanda surface is symmetrically arranged relative to the center line of the intermediate wall surface, and the Coanda surface is located downstream of the jet nozzle; and the first jet channel and the second jet channel share the Coanda surface.

[0008] According to a preferred embodiment, the transition section is located downstream of the gas source inlet and is a transition section from a circular channel to a rectangular channel.

[0009] According to a preferred embodiment, the side wall of the transition section is provided with a pressure sensor mounting boss and a temperature sensor mounting boss, and the pressure sensor mounting boss and the temperature sensor mounting boss are respectively provided with a pressure sensor and a temperature sensor to complete the pressure and temperature monitoring in the flow channel.

[0010] According to a preferred embodiment, the straightening section is located downstream of the transition section, and the jet channel of the straightening section gradually increases in the spanwise direction as the flow distance increases.

[0011] According to a preferred embodiment, the jet channel of the straightening section is divided into a plurality of uniform sub-jet channels at intervals.

[0012] According to a preferred embodiment, the jet channel of the straightening section is evenly provided with a plurality of flow direction reinforcing ribs along the span direction, so as to separate the jet channel into a plurality of sub-jet channels and structures and realize structural reinforcement of the jet channel.

[0013] According to a preferred embodiment, each reinforcing rib adopts a discontinuous staggered structure, and two adjacent sub-jet channels are not closed and can communicate with each other in the span direction. By adopting a discontinuous staggered structure, two adjacent sub-jet channels are not closed and can communicate with each other in the span direction, forming a complementary flow position, while ensuring the structural strength, promoting the span direction flow between the jet channels, ensuring the uniformity of the span direction pressure inside the jet channel, and thus promoting the uniformity of the jet outlet flow.

[0014] According to a preferred embodiment, a contraction section is provided at the end of the jet nozzle, and the contraction ratio of the contraction section is greater than 10, thereby achieving the purpose of reducing the jet velocity in the channel.

[0015] According to a preferred embodiment, the first gas source inlet and the second gas source inlet are circular pipes, and the outer walls are provided with reverse external threads.

[0016] According to a preferred embodiment, a step is provided on the side wall of the tail end of the circulation control unit, and the downstream outer surface of the step is consistent with the outer surface of the trailing edge of the wing. The rear part of the circulation control unit is seamlessly combined with the outer surface of the trailing edge of the wing at the step, and the front part of the circulation control unit is installed inside the wing at the step.

[0017] According to a preferred embodiment, a plurality of mesh brackets are provided on both sides of the circulation control unit to realize the positioning and installation and fixation of the circulation control unit.

[0018] The aforementioned main scheme of the present invention and its further options can be freely combined to form multiple schemes, all of which are schemes that can be adopted and claimed for protection by the present invention. After understanding the scheme of the present invention, those skilled in the art can understand that there are multiple combinations based on the prior art and common knowledge, all of which are technical schemes to be protected by the present invention, and they are not exhaustively listed here.

[0019] Beneficial effects of the present invention:

[0020] The airborne lightweight dual-channel circulation control unit provided by the present invention has two channels that are independent of each other and can be controlled separately. Through the cross-staggered air source inlet design, the air source inlet diameter is increased under the condition of limited internal space at the trailing edge of the wing, thereby reducing pipeline pressure loss.

[0021] Through the reverse thread design of the gas source inlet, the circulation control unit and the gas supply pipeline in a narrow space can be quickly connected and sealed through the external sleeve;

[0022] Through the design of flow direction reinforcement rib rectification, the adverse stress of the simply supported beam is reduced, and the rectangular frame with a large aspect ratio is changed into multiple rectangular frames with a small aspect ratio. Under the condition of meeting the structural strength, the uniformity of the spanwise jet is improved, the thickness of the jet channel wall is reduced, and the structural weight and space volume of the circulation control unit are reduced;

[0023] Moreover, the intermittent staggered structure is adopted for each reinforcing rib, so that two adjacent sub-jet channels are not closed and can communicate with each other in the span direction, forming a complementary flow position, which promotes the span direction flow between the jet channels while ensuring the structural strength, and ensures the uniformity of the span direction pressure inside the jet channel, thereby promoting the uniformity of the jet outlet flow;

[0024] The design of two flow channels sharing the middle wall further reduces the structural weight and space volume of the circulation control unit;

[0025] By arranging pressure sensors and temperature sensors in the jet channel, closed-loop control of the jet control is achieved as terminal feedback;

[0026] The circulation control unit is seamlessly integrated inside the wing by designing a seamless combination of the rear outer surface of the circulation control unit and the outer surface of the trailing edge of the wing. The circulation control unit can be quickly installed and fixed by arranging mesh brackets on both sides of the circulation control unit. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a schematic diagram of the structure of the airborne lightweight dual-channel circulation control unit of the present invention;

[0028] Figure 2 This is a cross-sectional view of the installation of the airborne lightweight dual-channel circulation control unit of the present invention inside the wing;

[0029] Figure 3 It is a trailing edge cross-sectional view of the airborne lightweight dual-channel circulation control unit of the present invention;

[0030] Figure 4 It is a cross-sectional view of the internal flow channel of the airborne lightweight dual-channel circulation control unit of the present invention;

[0031] Among them, 0-circulation control unit, 1-first jet channel, 2-second jet channel, 3-first air source inlet, 4-second air source inlet, 5-first air source inlet reverse external thread, 6-second air source inlet reverse external thread, 7-first air source inlet axis, 8-second air source inlet axis, 9-middle wall, 10-transition section, 11-pressure sensor mounting boss, 12-temperature sensor mounting boss, 13-step, 14-Coanda surface, 15-mesh bracket, 16-jet nozzle, 17-contraction section, 18-circulation control unit outer surface, 19-wing trailing edge outer surface, 21-straightening section, 22-flow reinforcement rib. DETAILED DESCRIPTION

[0032] The following describes the embodiments of the present invention through specific examples, and those skilled in the art can easily understand other advantages and effects of the present invention from the contents disclosed in this specification. The present invention can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present invention. It should be noted that the following embodiments and the features in the embodiments can be combined with each other without conflict. It should be noted that in order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention are clearly and completely described below. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments.

[0033] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inside", "outside", etc. indicate the orientation or position relationship that the product of the invention is usually placed in when in use. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", "third", etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0034] In addition, the terms "horizontal", "vertical", "overhanging" and the like do not mean that the components are required to be absolutely horizontal or overhanging, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0035] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0036] Embodiment 1:

[0037] refer to Figures 1 to 4 As shown, the present invention discloses an airborne lightweight dual-channel circulation control unit 0, which includes a first jet channel 1 and a second jet channel 2, and the first jet channel 1 and the second jet channel 2 are respectively provided with an air source inlet, a transition section 10, a rectifying section 21 and a jet outlet.

[0038] Preferably, the air source inlet includes a first air source inlet 3 and a second air source inlet 4 corresponding to the first jet channel 1 and the second jet channel 2, respectively, and the first air source inlet 3 and the second air source inlet 4 are staggered. The two channels are independent of each other and can be controlled separately. Through the design of the cross-staggered air source inlet, the purpose of increasing the air source inlet diameter and reducing the pipeline pressure loss is achieved in the case of limited internal space at the trailing edge of the wing.

[0039] Furthermore, the axes of the two gas source inlets are parallel and in the same plane, and the plane passes through the center line of the Coanda profile 14 set at the end of the control unit.

[0040] Preferably, the first gas source inlet 3 and the second gas source inlet 4 are circular pipes, and the outer wall is provided with reverse external threads. Through the reverse thread design of the gas source inlet, the circulation control unit and the gas supply pipeline in a narrow space can be quickly connected and sealed through an external sleeve.

[0041] Preferably, the transition section 10 is located downstream of the gas source inlet and is a transition section from a circular channel to a rectangular channel.

[0042] Preferably, the side wall of the transition section 10 is provided with a pressure sensor mounting boss 11 and a temperature sensor mounting boss 12, and the pressure sensor mounting boss 11 and the temperature sensor mounting boss 12 are respectively provided with a pressure sensor and a temperature sensor to complete the pressure and temperature monitoring in the flow channel. By arranging the pressure sensor and the temperature sensor in the jet channel, the closed-loop control of the jet control is realized as the terminal feedback.

[0043] Preferably, the straightening section 21 is located downstream of the transition section 10, and the jet channel of the straightening section 21 gradually increases in the spanwise direction as the flow distance increases.

[0044] Furthermore, the jet channel of the rectifying section 21 is divided into a plurality of uniform small jet channels by gradually dividing the large jet channel into a plurality of uniform small jet channels by using a two-part method.

[0045] Furthermore, the jet channel of the straightening section 21 is evenly provided with a plurality of flow reinforcement ribs 22 along the span direction, so as to separate the jet channel and strengthen the structure.

[0046] Through the rectification design of the flow reinforcement rib 22, the adverse stress of the simply supported beam is reduced, and the rectangular frame with a large aspect ratio is changed into multiple rectangular frames with a small aspect ratio. Under the condition of meeting the structural strength, the uniformity of the spanwise jet is improved, the thickness of the jet channel wall is reduced, and the structural weight and spatial volume of the circulation control unit are reduced.

[0047] Furthermore, each reinforcing rib 22 is provided with an intermittent staggered structure, and two adjacent sub-jet channels are not closed, and can communicate with each other in the span direction. By adopting an intermittent staggered structure for each reinforcing rib, two adjacent sub-jet channels are not closed, and can communicate with each other in the span direction, forming a complementary flow position, while ensuring the structural strength, promoting the span direction flow between the jet channels, ensuring the span direction pressure uniformity inside the jet channel, and thus promoting the uniformity of the jet outlet flow.

[0048] Furthermore, the first jet channel 1 and the second jet channel 2 are arranged to overlap, and the two jet channels share a middle wall surface 9 in the rectifying section 21. The design of two flow channels sharing a middle wall surface further reduces the structural weight and space volume of the circulation control unit.

[0049] Preferably, the jet outlets of the first jet channel 1 and the second jet channel 2 are respectively provided with jet nozzles 16, and the end of the middle wall surface 9 is provided with a Coanda profile, the Coanda profile surface is symmetrically arranged relative to the midline of the middle wall surface 9, and the Coanda profile surface is located downstream of the jet nozzle 16. The first jet channel 1 and the second jet channel 2 share the Coanda profile surface.

[0050] Preferably, the end of the jet nozzle 16 is provided with a contraction section 17. The contraction ratio of the contraction section 17 is greater than 10, so as to achieve the purpose of reducing the jet velocity in the channel.

[0051] Preferably, a step 13 is provided on the side wall of the rear end of the circulation control unit 0, and the outer profile of the downstream of the step 13 is consistent with the outer profile of the trailing edge of the wing. The rear of the circulation control unit 0 is seamlessly combined with the outer profile 19 of the trailing edge of the wing at the step 13, and the front of the circulation control unit 0 is installed inside the wing at the step 13. The seamless combination design of the outer profile of the rear of the circulation control unit and the outer profile of the trailing edge of the wing realizes the seamless integration of the circulation control unit 0 inside the wing.

[0052] Preferably, a plurality of mesh brackets 15 are provided on both sides of the circulation control unit 0 to realize the positioning and installation of the circulation control unit 0. By arranging the mesh brackets for fixing on both sides of the circulation control unit, the circulation control unit can be quickly installed and fixed.

[0053] Through the structural design of the circulation control unit of the present invention, the circulation control unit can meet the requirements of large pressure ratio air source control and narrow wing trailing edge installation space.

[0054] The present invention increases the diameter of the air source inlet while satisfying the smaller installation space at the trailing edge of the wing through the staggered design of the air source inlet, reduces the flow pressure loss in the pipeline, reduces the structural weight and increases the flow uniformity through the strengthening ribs, and arranges pressure and temperature sensors to realize the pressure and temperature feedback of the terminal. The structure is simple, the weight is light, and the volume is small.

[0055] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. An airborne lightweight dual-channel circulation control unit, characterized in that: The circulation control unit (0) comprises a first jet channel (1) and a second jet channel (2), wherein the first jet channel (1) and the second jet channel (2) are respectively provided with an air source inlet, a transition section (10), a rectifying section (21) and a jet outlet in sequence; The gas source inlet comprises a first gas source inlet (3) and a second gas source inlet (4) corresponding to the first jet channel (1) and the second jet channel (2) respectively, the first gas source inlet (3) and the second gas source inlet (4) are staggered, and the axes of the two gas source inlets are parallel and in the same plane, and the plane passes through the center line of the Coanda profile (14) set at the end of the circulation control unit (0); The first jet channel (1) and the second jet channel (2) are arranged to overlap, and the two jet channels share a middle wall surface (9) in the rectifying section; The jet outlets of the first jet channel (1) and the second jet channel (2) are respectively provided with jet nozzles (16); the end of the intermediate wall surface (9) is provided with a Coanda profile (14); the Coanda profile (14) is symmetrically arranged relative to the midline of the intermediate wall surface (9); the Coanda profile (14) is located downstream of the jet nozzle (16); and the first jet channel (1) and the second jet channel (2) share the Coanda profile (14); The transition section (10) is located downstream of the gas source inlet and is a transition from a circular channel to a rectangular channel; The straightening section (21) is located downstream of the transition section (10), and the jet channel of the straightening section (21) gradually increases in the span direction as the flow distance increases; The jet channel of the rectifying section (21) is divided into a plurality of uniform sub-jet channels at intervals; The jet channel of the straightening section (21) is provided with a plurality of flow direction reinforcing ribs (22) along the span direction; Each reinforcing rib (22) is arranged in an intermittent staggered structure, and two adjacent sub-jet channels are not closed and communicate with each other in an upward direction.

2. The circulation control unit according to claim 1, characterized in that: The side wall of the transition section (10) is provided with a pressure sensor mounting boss (11) and a temperature sensor mounting boss (12), and the pressure sensor mounting boss (11) and the temperature sensor mounting boss (12) are respectively provided with a pressure sensor and a temperature sensor to complete the pressure and temperature monitoring in the flow channel.

3. The circulation control unit according to claim 1, characterized in that: The end of the jet nozzle (16) is provided with a contraction section (17), and the contraction ratio of the contraction section (17) is greater than 10.

4. The circulation control unit according to claim 1, characterized in that: The first gas source inlet (3) and the second gas source inlet (4) are circular pipes, and the outer walls are provided with reverse external threads.

5. The circulation control unit according to claim 1, characterized in that: A step (13) is provided on the side wall of the rear end of the circulation control unit (0); the downstream outer profile of the step (13) is consistent with the outer profile of the wing trailing edge (19); the rear of the circulation control unit (0) is seamlessly combined with the outer profile of the wing trailing edge (19) at the step (13); and the front of the circulation control unit (0) is installed inside the wing at the step (13); A plurality of mesh brackets (15) are provided on both sides of the circulation control unit (0) to realize the positioning, installation and fixation of the circulation control unit (0).

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