A co-flow thrust vectoring nozzle

Abstract

The present application provides a co-directional thrust vector nozzle, which relates to the technical field of engine vector nozzles. The co-directional thrust vector nozzle includes a nozzle body, a secondary flow introduction hole, a plurality of secondary flow holes, and a Coanda wall. The secondary flow holes are arranged on a first connecting surface and a second connecting surface, the first connecting surface is connected to the second connecting surface, the connection angle between the first connecting surface and the second connecting surface toward the main jet inlet is less than 180 degrees, and the secondary flow flowing out of the secondary flow holes is parallel to the main jet. By changing the arrangement of the secondary flow holes, the main jet is in an unstable flow state. When the secondary flow is introduced into either side of the co-directional thrust vector nozzle, the secondary flow can destroy the integrity of the main jet, thereby reducing the stability of the main jet, and can improve the deflection hysteresis and control nonlinearity problems.

Description

Technical Field

[0001] The present application relates to the technical field of engine vector nozzles, and in particular to a co-directional flow thrust vector nozzle. Background Art

[0002] Thrust vector control technology has great benefits for the maneuverability and combat effectiveness of aircraft. The vector nozzle, which is the core component of thrust vector technology, is now mainly divided into two categories, one is the mechanical thrust vector nozzle and the other is the fluid thrust vector nozzle. The mechanical thrust vector nozzle mainly changes the direction of the jet by mechanically deflecting the tail of the nozzle to achieve the effect of thrust vectoring, but due to its high energy consumption during thrust steering, heavy mechanical structure and poor stealth effect, the fluid thrust vector nozzle has become the main research direction today. The fluid thrust vector nozzle can use the secondary flow to induce the deflection of the main jet, thereby achieving thrust steering.

[0003] In the current co-directional thrust vectoring nozzle, the internal flow field structure of the main jet is constantly changing during the deflection process and is not periodic. The non-steady-state process of the evolution of the flow field structure can lead to deflection hysteresis and control nonlinear problems. Summary of the invention

[0004] In view of the shortcomings of the related technologies mentioned above, the present application provides a co-directional flow thrust vector nozzle to solve the above technical problems.

[0005] The present application provides a co-directional thrust vector nozzle, comprising:

[0006] A nozzle body, two secondary flow introduction holes, a plurality of secondary flow holes, and a Coanda wall;

[0007] The nozzle body is a shaped tube body, and the cross section perpendicular to the axis of the nozzle body is a rectangle. The nozzle body includes a nozzle inner wall and a nozzle outer wall, and the nozzle inner wall is arranged on two opposite sides of the nozzle body. One end of the nozzle body is a main jet inlet, and the nozzle inner wall and the nozzle outer wall are closed to form a cavity. The nozzle inner wall and the nozzle outer wall are connected at a side away from the main jet inlet through at least one secondary flow connection group, and the secondary flow connection group includes a first connection surface and a second connection surface, and the first connection surface intersects with the second connection surface, and the angle at the intersection is less than 180 degrees;

[0008] Two secondary flow introduction holes are arranged on the outer wall of the nozzle opposite to the main jet inlet, a plurality of secondary flow holes are arranged on the first connecting surface and the second connecting surface, the secondary flow introduction holes are connected with the cavity, the cavity is connected with each of the secondary flow holes, and the secondary flow flowing out of the secondary flow holes is parallel to the main jet;

[0009] The Coanda wall surface is connected to the outer wall of the nozzle provided with a secondary flow introduction hole.

[0010] In one embodiment of the present application, an angle between the first connection surface and the second connection surface at the intersection is 90 degrees.

[0011] In one embodiment of the present application, at least two grooves are provided on the tail of the Coanda wall away from the main jet inlet, and the Coanda wall with at least two grooves is symmetrical about the central axis of the nozzle body, and the grooves are used to introduce air for secondary flow airflow supplement.

[0012] In one embodiment of the present application, a plurality of grooves are arranged on the coanda wall surface, and the area of ​​each groove is equal.

[0013] In one embodiment of the present application, the Coanda wall includes a first sub-wall and a second sub-wall, wherein the side of the first sub-wall away from the main jet inlet is parallel to the first connecting surface, and the side of the second sub-wall away from the main jet inlet is parallel to the second connecting surface.

[0014] In one embodiment of the present application, the areas of the secondary flow holes disposed on the inner walls of the nozzles on two opposite sides are equal.

[0015] In one embodiment of the present application, the co-current thrust vectoring nozzle further includes a heat sink having a plurality of heat dissipation holes, the heat sink being disposed on an outer wall of the nozzle, and the heat sink covering the Coanda wall.

[0016] In one embodiment of the present application, the co-current thrust vectoring nozzle further includes a nozzle fixing assembly, wherein the nozzle fixing assembly is disposed at one end of the nozzle body close to the main jet inlet, and the nozzle fixing assembly is used to fix the co-current thrust vectoring nozzle on the airflow supply device.

[0017] In one embodiment of the present application, the co-directional flow thrust vector nozzle further includes a secondary flow control valve, and the secondary flow control valve is connected to the secondary flow inlet hole and is used to adjust the air intake volume of the secondary flow inlet hole.

[0018] As described above, the co-directional flow thrust vector nozzle provided by the present application has the following beneficial effects:

[0019] A co-current thrust vectoring nozzle in the present application includes a nozzle body, a secondary flow introduction hole, a plurality of secondary flow holes, and a Coanda wall. The secondary flow holes are arranged on a first connection surface and a second connection surface, the first connection surface is connected to the second connection surface, the connection angle between the first connection surface and the second connection surface toward the main jet inlet is less than 180 degrees, and the secondary flow flowing out of the secondary flow holes is parallel to the main jet. By changing the arrangement of the secondary flow holes, the main jet is in an unstable flow state. When the secondary flow is introduced into either side of the co-current thrust vectoring nozzle, the secondary flow can destroy the integrity of the main jet, thereby reducing the stability of the main jet, and can improve the deflection hysteresis and control nonlinearity problems.

[0020] It should be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The drawings herein are incorporated into the specification and constitute a part of the specification, showing embodiments consistent with the present application, and together with the specification, are used to explain the principles of the present application. Obviously, the drawings described below are only some embodiments of the present application, and for those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative work. In the drawings:

[0022] Figure 1 is a structural schematic diagram of a co-current flow thrust vectoring nozzle shown in an exemplary embodiment of the present application;

[0023] Figure 2 yes Figure 1 A schematic structural diagram of the co-current thrust vector nozzle from another perspective is shown;

[0024] Figure 3 yes Figure 1 A structural schematic diagram of the co-current thrust vector nozzle from another perspective is shown;

[0025] Figure 4 is a structural schematic diagram of a co-current flow thrust vectoring nozzle shown in another exemplary embodiment of the present application;

[0026] Figure 5 It is a schematic diagram showing the arrangement of the secondary flow connection group according to an exemplary embodiment of the present application.

[0027] 111. Inner wall of nozzle; 112. Outer wall of nozzle; a. First connecting surface; b. Second connecting surface; 113. Secondary flow connecting group; 120. Secondary flow inlet hole; 130. Secondary flow hole; 140. Coanda wall; 141. Groove; 142. First sub-wall; 143. Second sub-wall; 150. Heat sink; 151. Heat dissipation hole; 160. Fixing assembly; c. Main jet inlet. DETAILED DESCRIPTION

[0028] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0029] It should be noted that all directional indications in the embodiments of the present application are only used to explain the relative position relationship, movement status, etc. between the components in a certain specific posture. If the specific posture changes, the directional indication will also change accordingly.

[0030] In this application, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "fixation" 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 an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0031] See also Figure 1 , Figure 1 is a schematic diagram of the structure of a co-current thrust vector nozzle shown in an exemplary embodiment of the present application. Figure 1 It can be seen that the co-current thrust vector nozzle may include:

[0032] The nozzle body, two secondary flow introduction holes 120 , a plurality of secondary flow holes 130 , and a Coanda wall 140 .

[0033] The nozzle body is a shaped tube body, and the cross section perpendicular to the axis of the nozzle body is a rectangle. The nozzle body includes a nozzle inner wall 111 and a nozzle outer wall 112. The nozzle inner wall 111 is arranged on two opposite sides of the nozzle body. The nozzle inner wall 111 and the nozzle outer wall 112 are closed to form a cavity ( Figure 1 The cavity is not shown), and one end of the nozzle body is the main jet inlet. In the embodiment of the present application, the main jet inlet can be rectangular, that is, the co-current thrust vector nozzle provided in the embodiment of the present application can be a binary vector nozzle.

[0034] It should be noted that the dual-vector nozzle is better integrated with the rear fuselage of the aircraft, which helps to reduce the radar cross-sectional area (RCS), and the exhaust gas is more easily mixed with the external cold air, thereby reducing the infrared signal characteristics and improving the stealth effect. In addition, the dual-vector nozzle is simpler in structure, lighter in weight, and more reliable.

[0035] In one embodiment of the present application, the side of the nozzle inner wall 111 and the nozzle outer wall 112 away from the main jet inlet is connected by at least one secondary flow connection group 113, and the secondary flow connection group 113 includes a first connection surface a and a second connection surface b, and the first connection surface a intersects with the second connection surface b and the angle at the intersection is less than 180 degrees. It should be noted that the length of the first connection surface is the same as the length of the second connection surface, and the first connection surface and the second connection surface are both connected to the nozzle inner wall and the nozzle outer wall. The angle at the intersection of the first connection surface a and the second connection surface b mentioned in the present application is the angle close to the main jet inlet, and the angle at the intersection is toward the main jet inlet.

[0036] Please refer to Figure 2 , which is Figure 1 The structural diagram of the co-current thrust vector nozzle from another perspective is shown. Figure 1 and Figure 2 It can be seen that two secondary flow introduction holes 120 are arranged on the opposite outer walls of the nozzle near the main jet inlet, and multiple secondary circulation holes 130 are arranged on the first connecting surface a and the second connecting surface b. The secondary flow introduction hole 120 is connected to the cavity, and the cavity is connected to each secondary circulation hole 130, and the secondary flow flowing out of the secondary circulation hole 130 is parallel to the main jet. After the secondary flow flows into the cavity from the secondary flow introduction hole 120, it can flow out from the secondary circulation hole 130. In the embodiment of the present application, the secondary flow introduction hole 120 and the secondary circulation hole 130 can be arranged on the same side of the nozzle body, and the nozzle inner wall 111 is arranged on both sides of the nozzle body provided with the secondary flow introduction hole 120 and the secondary circulation hole 130, that is, the cavity is located between the secondary flow introduction hole 120 and the secondary circulation hole 130 in the co-directional flow thrust vector nozzle.

[0037] In one embodiment of the present application, the secondary flow introduction hole 120 may be connected to a gas source providing device to provide the secondary flow through the gas source providing device.

[0038] Exemplarily, the air source providing device may be a jet engine, and the jet engine may be used as a source of the primary jet flow and as a source of the secondary flow flow. The jet engine may be a small turbojet engine or a turbofan engine.

[0039] It should be noted that the secondary flow hole 130 is facing the outlet of the co-directional flow thrust vector nozzle, that is, the direction of the secondary flow hole 130 is the same as the direction of the main jet inlet, the injection direction of the secondary flow is the same as the injection direction of the main jet, and the secondary flow flowing out of the secondary flow hole is parallel to the main jet.

[0040] The Coanda wall 140 is connected to the outer wall of the nozzle provided with the secondary flow introduction hole 120, that is, in the embodiment of the present application, two Coanda walls may be provided. The provision of the Coanda wall 140 enables the airflow to flow close to the outer wall of the nozzle. The Coanda wall can be used to help guide the ejected high-speed airflow, thereby changing the direction of thrust, which enables the aircraft to change the flight direction without changing the fuselage attitude, thereby improving the maneuverability and flexibility of the aircraft. In addition, the Coanda effect enables the ejected airflow (including the main jet and the secondary flow) to better adhere to the nozzle wall, thereby reducing thrust loss, helping to improve the efficiency of the nozzle, and making fuel consumption lower under the same thrust.

[0041] In one embodiment of the present application, the angle between the first connecting surface a and the second connecting surface b at the intersection is 90 degrees.

[0042] The applicant found that when simulating through CFD (Computational Fluid Dynamics), if the arrangement of the secondary flow holes 130 on the inner wall of the nozzle on either side is a straight line, the vector deflection control effect is not ideal. Therefore, the applicant compared the vector deflection angle curves under different working conditions and different secondary flow control conditions, and found that changing the arrangement of the secondary flow holes 130 on the inner wall of the nozzle can change the control effect of the vector deflection. Among them, the effect is best when the first connecting surface and the second connecting surface form an angle. When the angle between the connecting surface (including the first connecting surface and the second connecting surface) and the axis of the co-current thrust vector nozzle is 15° (that is, the angle at the intersection of the first connecting surface and the second connecting surface is 30 degrees), a relatively obvious control hysteresis can still be found; when the angle between the connecting surface and the axis of the co-current thrust vector nozzle is 30° (that is, the angle at the intersection of the first connecting surface and the second connecting surface is 60 degrees), the hysteresis effect is significantly improved; and when the angle between the connecting surface and the axis of the co-current thrust vector nozzle is 45° (that is, the angle at the intersection of the first connecting surface and the second connecting surface is 90 degrees), the linearity of the jet deflection reaches the best. When controlling the co-current thrust vector nozzle, the aircraft is more likely to deflect.

[0043] Based on the above analysis, in the co-directional flow thrust vector nozzle provided in the embodiment of the present application, the secondary flow hole is arranged on the first connection surface a and the second connection surface b, the first connection surface a and the second connection surface b intersect and the angle at the intersection is less than 180 degrees, which can improve the deflection hysteresis and control nonlinear problems. When the angle at the intersection of the first connection surface a and the second connection surface b is 90 degrees, the effect of improving the deflection hysteresis and control nonlinear problems is more obvious.

[0044] In one embodiment of the present application, at least two grooves 141 are provided at the tail of the Coanda wall 140 away from the main jet inlet. The Coanda wall 140 provided with at least two grooves 141 is symmetrical about the central axis of the nozzle body, and the grooves 141 are used to introduce air for secondary flow airflow supplement.

[0045] The secondary flow mainly serves to reduce the Reynolds magnitude on the Coanda wall 140, so that the main jet cannot trigger the Coanda effect with the Coanda wall 140, and serves as an isolating air cushion. When the secondary flow rate is insufficient, it cannot be guaranteed to serve as an isolating air cushion. Since the total amount of secondary flow rate is determined according to the engine-induced amount, the secondary flow rate cannot be corrected. Based on this, the embodiment of the present application provides at least two grooves 141 at the tail of the Coanda wall 140 away from the main jet inlet, and supplements the secondary flow rate of the co-directional thrust vector nozzle by introducing free secondary flow. The supplemented free secondary flow mainly acts on the jet outlet, and is used to suppress the generation of the backflow vortex structure of the jet. Therefore, the inlet of the free secondary flow is set at the outlet of the co-current thrust vector nozzle (that is, the tail of the Coanda wall 140 away from the main jet inlet), the grooves 141 are distributed at the jet outlet, and the Coanda wall 140 with at least two grooves 141 is symmetrical about the central axis of the nozzle body, so that the introduced free secondary flow is symmetrically distributed and evenly acts on the main jet. A single Coanda wall is symmetrical about the central axis of the nozzle body, and the two Coanda walls are the same (the two Coanda walls can completely overlap).

[0046] It should be noted that, by setting the Coanda wall 140 and the groove 141, the embodiment of the present application can introduce a free secondary flow to supplement the secondary flow rate when controlling the co-directional thrust vector nozzle, thereby increasing the vector deflection angle and playing a significant role in high-maneuverability flight.

[0047] In one embodiment of the present application, a plurality of grooves 141 are provided on the Coanda wall 140, and the area of ​​each groove 141 is equal. Since the area of ​​each groove 141 is equal, when the co-current flow thrust vector nozzle provided in the embodiment of the present application is used, each groove 141 can introduce a free secondary flow with an equal flow rate to supplement the secondary flow flow rate, thereby improving the nonlinear problem of the co-current flow thrust vector nozzle control.

[0048] Exemplarily, six grooves 141 may be provided on each Coanda wall 140 , and the area of ​​each groove 141 may be 213 square millimeters.

[0049] In one embodiment of the present application, the Coanda wall 140 may include a first sub-wall 142 and a second sub-wall 143, wherein the side of the first sub-wall 142 away from the main jet inlet is parallel to the first connecting surface, the side of the second sub-wall 143 away from the main jet inlet is parallel to the second connecting surface, and the position sequence of the first sub-wall and the second sub-wall is consistent with the position sequence of the first connecting surface and the second connecting surface. Each Coanda wall may be composed of two sub-walls (i.e., the first sub-wall and the second sub-wall), and the Coanda wall may be symmetrical about the axis of the co-current thrust vector nozzle.

[0050] In one embodiment of the present application, the arrangement of the secondary flow holes 130 on the inner wall of the nozzle may be symmetrical about the common edge connecting the two sub-walls.

[0051] In one embodiment of the present application, the areas of the secondary circulation holes 130 provided on the inner walls of the nozzles on opposite sides are equal. That is, the areas of the outlet surfaces of the secondary circulation holes 130 provided on the inner walls of the nozzles on opposite sides are equal. Such an arrangement can ensure that the co-current thrust vectoring nozzle can provide equal thrust vectors in both directions.

[0052] Please refer to Figure 3 , which is Figure 1 The structural diagram of the co-current thrust vector nozzle from another perspective is shown. Figure 1 and Figure 3 It can be seen that the co-current thrust vectoring nozzle further includes a heat sink 150, on which a plurality of heat dissipation holes 151 are arranged, and the heat sink 150 is arranged on the nozzle outer wall 112, and the heat sink 150 covers the coanda wall surface 140. The heat dissipation holes 151 can prevent the co-current thrust vectoring nozzle from being damaged by backfire, thereby extending the service life of the co-current thrust vectoring nozzle.

[0053] Please refer to Figure 4 , which is a structural schematic diagram of a co-current thrust vector nozzle shown in another exemplary embodiment of the present application. Figure 4 It can be seen that the co-current thrust vectoring nozzle also includes a nozzle fixing assembly 160, which is arranged at one end of the nozzle body close to the main jet inlet c, and the nozzle fixing assembly 160 is used to fix the co-current thrust vectoring nozzle on the airflow supply device.

[0054] It should be noted that the Coanda wall surface may be a plane surface or a curved surface. The two sub-wall surfaces of the Coanda wall surface may protrude toward the main jet inlet of the co-current thrust vector nozzle, and the two sub-wall surfaces of the Coanda wall surface may also be parallel.

[0055] Combination Figures 1 to 4 It can be seen that the nozzle fixing assembly 160 may include a nozzle fixing end and a connecting hole provided on the nozzle fixing end. The nozzle fixing end may be a plate, the nozzle fixing end may be connected to the nozzle body, and a main jet inlet may be provided on the nozzle fixing end. The connecting hole may be used to connect to the tail transition section of the gas source providing device.

[0056] It should be noted that Figures 1 to 4 In the illustrated co-current thrust vectoring nozzle, the nozzle fixed end is rectangular (in other embodiments, the fixed end may also be circular or other shapes, which is not limited in the embodiments of the present application). A plurality of connection holes may be provided on the nozzle fixed end to fix the co-current thrust vectoring nozzle to the tail transition section of the gas source providing device through connecting members such as screws.

[0057] See also Figure 5 , Figure 5 It is a schematic diagram showing the arrangement of the secondary flow connection group according to an exemplary embodiment of the present application. Figure 5 Three secondary flow connection groups 113 are shown, and the first connection surface a of one secondary flow connection group intersects with the second connection surface b of another secondary flow connection group. Figure 5 The three secondary flow connection groups shown, that is, the nozzle inner wall and the nozzle outer wall can be connected through three secondary flow connection groups, and multiple secondary flow holes can be arranged on the first connection surface and the second connection surface of the three secondary flow connection groups.

[0058] In one embodiment of the present application, the co-directional thrust vectoring nozzle further includes a secondary flow control valve, which is connected to the secondary flow introduction hole 120 and is used to adjust the air intake of the secondary flow introduction hole 120. The nozzle secondary flow channel pipeline is fastened to the secondary flow introduction hole 120 by bolts, and a sealing ring is installed at the connection to avoid secondary flow loss. The nozzle secondary flow channel pipeline connects the co-directional thrust vectoring nozzle and the air source providing device.

[0059] It should be noted that when thrust vector adjustment is not required during flight, both secondary flow control valves are in a closed state; when thrust vector adjustment is required during flight, it is only necessary to control the opening of the secondary flow control valve on one side according to demand, and the thrust vector is achieved by interfering the main jet with the secondary flow, and the vector angle of the thrust vector can be controlled by the opening of the secondary flow control valve. For example, when using the co-current thrust vector nozzle provided in the embodiment of the present application, the secondary flow control valve on the left side can be controlled to open so that all the secondary flow holes on the left side flow out the secondary flow, or the secondary flow control valve on the right side can be controlled to open so that all the secondary flow holes on the right side flow out the secondary flow.

[0060] In an embodiment of the present application, when the secondary flow control valves on both sides are in a closed state, the main jet is in an unstable flow state and may deflect to the left or to the right; when the secondary flow control valves on both sides are opened and the opening degrees are the same, the main jet is in a neutral state; when the secondary flow control valves on both sides are opened synchronously, but the secondary flow rates on both sides are different, the pressures on both sides of the main jet are different, and the main jet deflects under the action of the pressure difference on both sides. The greater the pressure difference, the greater the angle of deflection of the main jet.

[0061] Between the main jet inlet and the outlet of the co-current thrust vectoring nozzle, the main jet is not blocked by any components, and the ejection direction of the main jet is parallel to the ejection direction of the secondary jet.

[0062] In summary, the co-current thrust vectoring nozzle provided in the embodiment of the present application includes a nozzle body, a secondary flow introduction hole, a plurality of secondary flow holes, and a Coanda wall. The secondary flow holes are arranged on a first connecting surface and a second connecting surface, the first connecting surface is connected to the second connecting surface, the connection angle between the first connecting surface and the second connecting surface toward the main jet inlet is less than 180 degrees, and the secondary flow flowing out of the secondary flow holes is parallel to the main jet. By changing the arrangement of the secondary flow holes, the main jet is placed in an unstable flow state. When the secondary flow is introduced into either side of the co-current thrust vectoring nozzle, the secondary flow can destroy the integrity of the main jet, thereby reducing the stability of the main jet, and can improve the deflection hysteresis and control nonlinearity problems.

[0063] In the embodiments of the present application, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance. "Including" and "comprising" mentioned throughout the specification and claims are open-ended terms and should be interpreted as "including but not limited to".

[0064] The above embodiments are merely illustrative of the principles and effects of the present application, and are not intended to limit the present application. Anyone familiar with the technology may modify or change the above embodiments without violating the spirit and scope of the present application. Therefore, all equivalent modifications or changes made by a person of ordinary skill in the art without departing from the spirit and technical ideas disclosed in the present application shall still be covered by the claims of the present application.

Claims

1. A co-current thrust vectoring nozzle, characterized in that: include: A nozzle body, two secondary flow introduction holes, a plurality of secondary flow holes, and a Coanda wall; The nozzle body is a shaped tube body, and the cross section perpendicular to the axis of the nozzle body is a rectangle. The nozzle body includes a nozzle inner wall and a nozzle outer wall, and the nozzle inner wall is arranged on two opposite sides of the nozzle body. One end of the nozzle body is a main jet inlet, and the nozzle inner wall and the nozzle outer wall are closed to form a cavity. The nozzle inner wall and the nozzle outer wall are connected at a side away from the main jet inlet through at least one secondary flow connection group, and the secondary flow connection group includes a first connection surface and a second connection surface, and the first connection surface intersects with the second connection surface, and the angle at the intersection is less than 180 degrees; Two secondary flow introduction holes are arranged on the outer wall of the nozzle opposite to the main jet inlet, a plurality of secondary flow holes are arranged on the first connecting surface and the second connecting surface, the secondary flow introduction holes are connected with the cavity, the cavity is connected with each of the secondary flow holes, and the secondary flow flowing out of the secondary flow holes is parallel to the main jet; The Coanda wall surface is connected to the outer wall of the nozzle provided with a secondary flow introduction hole; The Coanda wall is provided with at least two grooves at the tail away from the main jet inlet, and the Coanda wall provided with at least two grooves is symmetrical about the central axis of the nozzle body, and the grooves are used to introduce air for secondary flow airflow supplement, and the secondary flow airflow supplement acts on the jet outlet to suppress the generation of the backflow vortex structure of the jet, so that the main jet cannot trigger the Coanda effect with the Coanda wall, thereby achieving the effect of isolating the air cushion.

2. The co-current thrust vectoring nozzle according to claim 1, characterized in that: The included angle at the intersection of the first connecting surface and the second connecting surface is 90 degrees.

3. The co-current thrust vectoring nozzle according to claim 1, characterized in that: The wall surface of the Conda is provided with a plurality of grooves, and the area of ​​each groove is equal.

4. The co-current thrust vectoring nozzle according to claim 1, characterized in that: The Coanda wall includes a first sub-wall and a second sub-wall. The first sub-wall is parallel to the first connecting surface at one side away from the main jet inlet, and the second sub-wall is parallel to the second connecting surface at one side away from the main jet inlet.

5. The co-current thrust vectoring nozzle according to claim 1, characterized in that: The areas of the secondary flow holes arranged on the inner walls of the nozzles on opposite sides are equal.

6. The co-current thrust vectoring nozzle according to claim 1, characterized in that: The co-current thrust vectoring nozzle also includes a heat sink, which is provided with a plurality of heat dissipation holes. The heat sink is arranged on the outer wall of the nozzle, and the heat sink covers the Coanda wall.

7. The co-current thrust vectoring nozzle according to claim 1, characterized in that: The co-current thrust vectoring nozzle further comprises a nozzle fixing assembly, wherein the nozzle fixing assembly is arranged at one end of the nozzle body close to the main jet inlet, and the nozzle fixing assembly is used to fix the co-current thrust vectoring nozzle on an airflow supply device.

8. The co-current thrust vectoring nozzle according to claim 1, characterized in that: The co-flow thrust vector nozzle also includes a secondary flow control valve, which is connected to the secondary flow introduction hole and is used to adjust the air intake volume of the secondary flow introduction hole.

Images