Jet flow control system for inhibiting reverse pressure gradient curved surface flow separation

Abstract

The invention belongs to the technical field of flow control, and discloses a jet flow control system for inhibiting reverse pressure gradient curved surface flow separation, which is characterized in that through an embedded multi-cavity jet structure, additive manufacturing integral forming / modular replacement and pneumatic modulation and communication control modes, on the premise that a complex mechanical reciprocating mechanism is not adopted, the reverse pressure gradient curved surface flow separation is inhibited, and the reverse pressure gradient curved surface flow separation is inhibited. And uniform output of jet flow of a nozzle, quick change of a jet angle and convenient setting of jet flow intensity and pulse parameters are realized, so that the engineering realizability of the device, the working condition switching efficiency and the repeatability of control input are improved.

Description

Jet control system for suppressing flow separation on adverse pressure gradient surfaces Technical Field

[0001] This invention belongs to the field of flow control technology, and in particular relates to a jet control system for suppressing flow separation on a reverse pressure gradient surface. Background Technology

[0002] In existing technologies, an active flow control approach centered on jets has been developed to address flow separation and drag reduction issues at the tails of two-dimensional ramps and axisymmetric bodies of revolution. The basic idea is to supplement momentum and introduce controllable disturbances to the near-wall boundary layer and separation shear layer near sensitive areas where separation occurs naturally or a shear layer forms. This is achieved by using wall-mounted slit nozzles or discrete nozzle arrays to shorten the separation bubble, promote reattachment, and improve wall pressure recovery. In the control of separation and drag reduction at the tails of axisymmetric bodies of revolution, tangential blowing and the Coanda effect (jet flowing along a curved surface) are typical jet control methods. By setting an annular slit jet concentric with the shape of the axisymmetric blunt body for tangential blowing, the bottom pressure can be significantly increased, the wake structure altered, and significant drag reduction achieved.

[0003] Compared to steady jets, pulsed jet actuators offer greater diversity in structure and implementation. Mechanical approaches are a traditional method, such as using the reciprocating motion of a piston or diaphragm to compress air within a cavity, periodically generating jet pulses. These devices are typically driven by a motor or loudspeaker to achieve mechanical vibrations at a specific frequency. Piezoelectric-driven synthetic jets are a typical example: using a piezoelectric ceramic oscillator to drive diaphragm oscillation within a small cavity, a zero-net-mass jet with alternating intake and exhaust can be generated without additional air supply lines. Synthetic jet actuators offer advantages such as fast response, high jet velocity, and no external piping, making them ideal for applications with size and weight constraints. Another type is the pneumatically modulated actuator, which primarily relies on high-speed switching valves to modulate a steady-state air source. For example, using a high-response solenoid valve (switching frequency up to several hundred hertz) to periodically open and close the air source according to a preset square wave signal can generate a pulsed jet with the desired frequency and duty cycle at a fixed nozzle.

[0004] Although the existing active control scheme for jet separation of two-dimensional slope and axisymmetric rotating body tail has been proven effective, there are still some shortcomings that this invention can overcome in terms of exciter implementation and adjustment methods. These shortcomings are mainly reflected in the following two aspects: (1) Mechanical (piston / diaphragm / voice coil, etc.) pulsating jet exciter has a complex structure and is not flexible enough in engineering integration and parameter adjustment.

[0005] Existing mechanical oscillation / synthetic jet schemes often require a multi-component assembly structure within the model, consisting of a "pressure-stabilizing cavity—flexible diaphragm seal—transverse rigid piston—external drive module," and rely on multiple drive units operating synchronously to ensure the two-dimensionality of the slit and a sufficient exit velocity range. Taking the oscillation control of the NASA hump model as an example, its oscillating blowing is achieved through a rigid piston, flexible diaphragm, and multiple voice coil drive modules spanning the model, and it needs to operate within a certain frequency range to achieve the required slit velocity.

[0006] Because such solutions involve issues such as moving parts, sealing and assembly tolerances, drive synchronization, and fatigue reliability, the system design and maintenance costs are high. Furthermore, key parameters such as frequency and amplitude are constrained by the inherent characteristics of the mechanism and the capabilities of the drive system, often requiring adjustments through driver replacement, structural dimension changes, or recalibration, making it difficult to achieve "rapid, fine-grained, and repeatable" parameter scanning and operating condition switching. In addition, when these devices are expanded into multi-nozzle arrays, the limitations and coupling issues of the diaphragm / piston in uniformly supplying air to multiple nozzles still need to be addressed, resulting in insufficient engineering flexibility.

[0007] (2) Although the pneumatically modulated pulse jet can be switched on and off using a solenoid valve, the gas supply regulation links other than the solenoid valve mostly rely on manual adjustment, resulting in low regulation efficiency, insufficient repeatability and portability.

[0008] Existing pulse jet systems typically rely on compressed air sources, using solenoid valves to control pulse frequency and duty cycle. However, to achieve the target jet intensity, it often requires upstream chamber pressure (or differential pressure) setting, pre- / post-valve piping matching, and a calibration process for each operating condition. Public reports indicate that in related experiments, the "desired jet velocity" is usually obtained by setting the chamber pressure and the external static pressure difference, and the average chamber pressure and instantaneous jet velocity need to be measured for each type of operating condition during the calibration phase. For pulse jets, phase averaging is also required to obtain the velocity response within the cycle, thereby determining parameters such as nominal blowing intensity and duty cycle.

[0009] This means that while solenoid valves can provide "on / off" modulation, the jet intensity (e.g., determined by the supply pressure ratio and flow rate) often relies on manual rotary pressure regulators and throttle valves in engineering, as well as repeated adjustments and calibrations using flow meters / pressure gauges. This makes it difficult to achieve automatic parameter setting, rapid reproduction, and consistency across operating conditions. When frequent switching between steady-state and pulse modes or migration between different models / nozzle geometries is required, the supply settings and pipeline dynamic response still need to be readjusted, limiting experimental efficiency and system flexibility. Furthermore, to improve the pulse frequency range, existing systems even require complex drive strategies such as "dedicated high-speed solenoid valves + multi-valve staggered phase drive," further increasing the workload of system configuration and debugging.

[0010] Based on the aforementioned shortcomings, existing technologies generally suffer from problems such as "complex structural implementation, high dependence on manual adjustment, and inconvenience in parameter switching and reproduction" at the actuator level, making it difficult to simultaneously achieve: rapid variable nozzle geometry (such as injection angle), guaranteed uniformity of outlet flow velocity in array nozzles, and automated, digital adjustment and recording of pulse parameters and air supply intensity. To solve these problems, this invention proposes a jet control system for suppressing flow separation on adverse pressure gradient surfaces. Summary of the Invention

[0011] To address the common problems of existing steady / pulse jet exciters, such as complex structure, difficult installation and integration, high requirements for sealing and assembly, and insufficient flexibility in parameter (frequency / amplitude) adjustment due to reliance on drive mechanisms and calibration processes, this invention aims to provide a steady / pulse jet exciter and its gas supply modulation system for the separation control of two-dimensional ramps and axisymmetric rotating bodies. Through an embedded multi-cavity injection structure, additive manufacturing for integrated molding / modular replacement, and pneumatic modulation and communication control, this invention achieves uniform jet output, rapid variable injection angle, and convenient setting of jet intensity and pulse parameters without employing complex mechanical reciprocating mechanisms. This improves the engineering feasibility of the device, the efficiency of operating condition switching, and the repeatability of control inputs.

[0012] To achieve the above objectives, this invention provides a jet control system for suppressing flow separation on a reverse pressure gradient surface, comprising an axisymmetric rotating body model, an actuator group, a pulse jet gas path, and a parameter control module. The actuator group is installed inside the axisymmetric rotating body model and includes several blowing chambers evenly arranged along the circumference of the axisymmetric rotating body model. The inlet end of each blowing chamber is connected to the pulse jet gas path, and the angle between the outlet direction of each blowing chamber and the wall of the axisymmetric rotating body model is adjustable. The pulse jet gas path is communicatively connected to the parameter control module.

[0013] Optionally, each of the blowing chambers is a streamlined expansion structure, including an inlet section, an expansion and rectification section and an outlet section arranged in sequence, wherein the end of the inlet section away from the expansion and rectification section is connected to the pulse jet gas path.

[0014] Optionally, the pulse jet air path includes an air compressor, a filter, an electro-proportional valve, and a solenoid valve arranged in sequence, with the end of the solenoid valve away from the electro-proportional valve connected to the inlet section of each blowing chamber.

[0015] Optionally, both the electro-proportional valve and the solenoid valve are communicatively connected to the parameter control module.

[0016] On the other hand, to achieve the above objectives, the present invention provides a jet control system for suppressing flow separation on a reverse pressure gradient surface, comprising a two-dimensional ramp model, an actuator group, and a steady jet gas path. The two-dimensional ramp model has an internal receiving cavity, and the actuator group is arranged inside the receiving cavity. The actuator group includes a plurality of blowing chambers, each of which is arranged longitudinally at a preset interval. The inlet end of each blowing chamber is connected to the steady jet gas path, and the angle between the outlet direction of each blowing chamber and the wall of the two-dimensional ramp model is adjustable.

[0017] Optionally, the receiving cavity is flush with the outer surface of the two-dimensional ramp model.

[0018] Optionally, each of the blowing chambers is a streamlined expansion structure, including an inlet section, an expansion and rectification section and an outlet section arranged in sequence, wherein the end of the inlet section away from the expansion and rectification section is connected to the pulse jet gas path.

[0019] Optionally, the constant jet air path includes at least one constant jet air path, which includes an air compressor, a filter, a pressure regulating valve, a flow meter and a throttle valve arranged in sequence, with the end of the throttle valve away from the flow meter connected to the inlet section of the corresponding blowing chamber.

[0020] The technical effects of this invention are as follows: The jet control system for suppressing flow separation on a reverse pressure gradient surface provided by this invention achieves uniform jet output, rapid variable jet angle, and convenient setting of jet intensity and pulse parameters without using a complex mechanical reciprocating mechanism through an embedded multi-cavity jet structure, additive manufacturing integral molding / modular replacement, and pneumatic modulation and communication control. This improves the engineering feasibility of the device, the efficiency of operating condition switching, and the repeatability of control input. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] The accompanying drawings, which form part of this application, are used to provide a further understanding of this application. The illustrative embodiments of this application and their descriptions are used to explain this application and do not constitute an undue limitation of this application. In the drawings: Figure 1 is a schematic diagram of the two-dimensional ramp model and actuator assembly structure in Embodiment 1 of the present invention; Figure 2 is a schematic diagram of the internal structure of the actuator and its air path in Embodiment 1 of the present invention; Figure 3 is a schematic diagram of the rotating actuator model and its air path in Embodiment 2 of the present invention.

[0023] Labeling Explanation: 1. Air blowing chamber; 2. Exciter assembly; 3. Ramp model; 4. Receiving chamber; 5. Air compressor; 6. Filter; 7. Pressure regulating valve; 8. Flow meter; 9. Throttling valve; 10. Electro-proportional valve; 11. Solenoid valve; 12. Inlet of expansion and rectification section; 13. Expansion section; 14. Outlet of expansion and rectification section. Detailed Implementation

[0024] The technical solutions of the present invention will be clearly and completely described below with reference to the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0025] To facilitate understanding of the present invention, a more comprehensive description of the invention will be given below with reference to the accompanying drawings, and several embodiments of the invention will be provided. However, the invention can be implemented in many different forms and is not limited to the embodiments described herein. Rather, these embodiments are provided so that the disclosure of the invention will be more thorough and complete.

[0026] It should be noted that when an element is referred to as being "fixed to" another element, it can be directly on the other element or there may be an intervening element. When an element is considered to be "connected to" another element, it can be directly connected to the other element or there may be an intervening element. The terms "vertical," "horizontal," "left," "right," and similar expressions used in this document are for illustrative purposes only. The terms "include," "include," "have," "contain," etc., used in this document are all open-ended terms, meaning that they include but are not limited to.

[0027] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. The terminology used herein in the specification of this invention is for the purpose of describing particular embodiments only and is not intended to limit the invention. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0028] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. This application will now be described in detail with reference to the accompanying drawings and embodiments.

[0029] As shown in Figures 1 and 2, this embodiment provides a jet control system for suppressing flow separation on a reverse pressure gradient surface, including a two-dimensional ramp model 3, an exciter group 2, and a steady jet air path. The two-dimensional ramp model 3 has an internal receiving cavity 4, and the exciter group 2 is arranged inside the receiving cavity 4. The exciter group 2 includes several blowing chambers 1, which are arranged sequentially at preset intervals. The air inlet of each blowing chamber 1 is connected to the steady jet air path, and the angle between the air outlet direction of each blowing chamber 1 and the wall of the two-dimensional ramp model 3 is adjustable.

[0030] Two-dimensional ramp model 3 exciter and steady air supply regulation: This embodiment is for a two-dimensional ramp model 3 with natural separation flow. A receiving cavity 4 is set inside the model. The opening of the receiving cavity 4 is flush with the outer surface of the model and forms a mounting base for the detachable installation of the exciter assembly 2. The exciter assembly 2 consists of several blowing chambers 1 arranged along the longitudinal direction. Each blowing chamber 1 is provided with a streamlined expansion structure for flow rectification to improve the uniformity of the nozzle outflow.

[0031] The actuator group 2 is manufactured by photopolymer 3D printing, which can form multiple actuator groups 2 with different nozzle ejection angles α, and the ejection angle α can be quickly and variably configured by replacing the actuator group 2.

[0032] Each blowing chamber 1 is connected to a set of constant jet air path, which includes, in order of flow direction: air compressor 5, filter 6, pressure regulator 7, flow meter 8, and throttle valve 9. The jet volume flow rate Q is adjusted by the throttle valve 9. When multiple chambers work at the same time, a distribution manifold can be set up to achieve one-to-many air supply.

[0033] Design of a two-dimensional slope separation control exciter: Coordinate system definition: The origin O is located at the exact center of the slope starting point; x, y, and z are the flow direction, span direction, and normal direction, respectively.

[0034] Separation point location determination: The time-averaged velocity field is obtained through PIV, and the flow velocity is extracted in the near-wall region. When near-wall backflow occurs (flow velocity is negative) or the shear layer is significantly lifted and a separation bubble is formed, its starting position is defined as the separation point, and the flow distance from this position to point O is defined as d.

[0035] Actuator group 2 structure: Actuator group 2 consists of several blowing chambers 1 arranged along the spanwise direction. Each blowing chamber 1 includes an inlet section, an expansion and rectification section, and an outlet section: the inlet section is a circular cross-section with a diameter D1, used for reliable sealing connection with the air supply pipeline; the outlet section is a slit nozzle with a width of about 1 mm, and multiple slits are arranged at equal intervals along the spanwise direction to form a slit array; the slit nozzle is set with a spray angle α relative to the wall surface, and different separation conditions can be adapted by replacing actuator groups 2 with different α.

[0036] Outlet uniformity structure: The expansion rectifying section adopts a streamlined expansion configuration composed of two tangent circles, and its characteristic dimensions are characterized by R1 and R2. By designing and preparing multiple R1 / R2 combinations, the velocity distribution was measured along the spanwise direction at a distance of approximately 1 mm downstream of the slit outlet using a hot-wire anemometer. The root mean square error of the velocity distribution was used as the uniformity evaluation index, and the R1 / R2 combination with the optimal uniformity was selected for batch processing.

[0037] Installation method: The actuator assembly 2 is processed by photopolymer 3D printing and is detachably connected to the ramp model 3; after assembly, the outer surface of the actuator is flush with the surface of the ramp to reduce geometric interference to the reference flow field.

[0038] Manually adjustable steady jet air path: The air path is used to provide stable and adjustable compressed air to the exciter assembly 2. It includes, in order of flow direction: air compressor 5, filter 6, pressure regulator 7, flow meter 8, and throttle valve 9, with its end connected to the blowing chamber 1 or a distribution manifold. Different control intensities can be achieved by adjusting the volumetric flow rate Q through the throttle valve 9. In multi-chamber cases, a one-to-many air supply can be used via the distribution manifold, or an independent throttle valve 9 can be configured for each chamber to achieve zone / chamber-by-chamber adjustment.

[0039] This embodiment uses "compressed air source + embedded blowing chamber 1 + valve-controlled modulation" as its core, which can achieve pulse excitation without relying on mechanical oscillation structures such as pistons, diaphragms, and voice coils. This reduces the uncertainty caused by moving parts, sealing and assembly tolerances, reduces structural complexity and maintenance costs, and improves the long-term operational stability and repeatability of the system.

[0040] Meanwhile, in this embodiment, the two-dimensional ramp scheme employs a detachable actuator group 2, and the injection angle can be quickly switched by changing different α versions; the axisymmetric rotating body scheme can provide integrated structural versions with different α values. Compared with existing methods that rely heavily on fixed nozzle directions and require reprocessing or significant modifications to change the injection direction, this embodiment significantly improves the configuration efficiency of nozzle direction parameters, facilitating rapid matching for different inflow conditions, different separation point locations, and different control objectives. Embodiment

[0041] As shown in Figures 2 and 3, this embodiment provides a jet control system for suppressing flow separation on a reverse pressure gradient surface. The system includes an axisymmetric rotating body model, an actuator group 2, a pulsed jet gas path, and a parameter control module. The actuator group 2 is installed inside the axisymmetric rotating body model and includes several blowing chambers 1 evenly arranged along the circumference of the axisymmetric rotating body model. The inlet end of each blowing chamber 1 is connected to the pulsed jet gas path, and the angle between the outlet direction of each blowing chamber 1 and the wall of the axisymmetric rotating body model is adjustable. The pulsed jet gas path is communicatively connected to the parameter control module.

[0042] Axisymmetric Rotating Body Model Exciter and Automatic Pulse Air Supply Adjustment: Addressing the issue of the complex structure of the axisymmetric rotating body model and the inconvenience of creating a large-sized receiving cavity 4, this embodiment adopts an integrated design of the rotating body model and exciter flow channel: the internal flow channel of the blowing chamber 1 is directly integrated into the interior of the rotating body and integrally formed using photopolymerization 3D printing. The interior of the blowing chamber 1 also adopts a streamlined expansion structure, with nozzles evenly arranged along the circumference of the rotating body to form a circumferential nozzle array; the nozzle direction forms a spray angle α with the wall surface, and different integrated structure versions with different α values ​​can be provided as needed.

[0043] The axisymmetric rotating body achieves selectable angle configuration through an integrated structure version with different α values, thus facilitating adaptation to different separation conditions and control objectives.

[0044] The pulse jet air path, in order of flow direction, includes: air compressor 5, filter 6, electro-proportional valve 10, and solenoid valve 11, with the end connected to the exciter's air supply inlet. Electro-proportional valve 10 is used to regulate and stabilize the air supply state to control the air supply pressure ratio PR, while solenoid valve 11 is used to achieve pulse modulation to control the pulse frequency fe and duty cycle dc. The control parameters of electro-proportional valve 10 and solenoid valve 11 are set and adjusted via RS485 communication, thereby achieving automatic control of jet intensity and pulse parameters.

[0045] When the pulse modulation function is not enabled, the solenoid valve 11 remains open or bypassed, and the electro-proportional valve 10 can still be used for steady jet regulation. Therefore, this automatic pneumatic circuit is compatible with both steady and pulse working modes.

[0046] Design of axisymmetric rotating body separation control actuator: 1. Integrated structure: The air blowing chamber 1 flow channel is integrated into the interior of the rotating body and 3D printed as a whole, avoiding the structural complexity and strength problems caused by opening a large-size accommodating cavity 4.

[0047] 2. Internal flow channel: The internal profile of the blowing chamber 1 is consistent with that of Example 1, and a streamlined expansion structure is adopted to improve the uniformity of the nozzle outflow.

[0048] 3. Nozzle array: Nozzles are evenly arranged around the circumference of the rotating body to form a circumferential array, and the nozzle direction forms a spray angle α with the wall surface; different integrated structure versions with different α can be provided according to requirements.

[0049] Automatic Adjustment of Pulse Jet Air Path: Considering that the high-speed opening and closing of solenoid valve 11 will introduce significant pressure and flow oscillations, the pulse air path uses electro-proportional valve 10 for upstream air supply regulation and stabilization, replacing the traditional pressure regulating valve 7 and throttle valve 9. The air path, in order of flow direction, includes: air compressor 5, filter 6, electro-proportional valve 10, solenoid valve 11, and connects to the exciter's air supply inlet at the end. Electro-proportional valve 10 is used to control the air supply pressure ratio PR, and solenoid valve 11 is used to realize pulse modulation and control fe and dc. The above control parameters are automatically set, adjusted online, and repeatedly recalled through communication methods such as RS485, thereby significantly reducing the reliance on manual debugging and improving reproducibility. When solenoid valve 11 is normally open / bypassed, the system degenerates into a steady jet regulation mode, thus being compatible with both steady and pulse operating conditions.

[0050] In this embodiment, the pulsed gas circuit employs a combination of an electro-proportional valve 10 and a solenoid valve 11: the electro-proportional valve 10 is used to regulate and stabilize the gas supply state (gas supply pressure ratio PR), and the solenoid valve 11 is used to modulate the pulse frequency fe and duty cycle dc. Parameters are automatically set and repeatedly recalled via RS485 communication. Compared to the prior art, which still heavily relies on manual pressure regulating valves 7 and throttle valves 9 for repeated adjustments (except for the solenoid valve 11), this embodiment significantly reduces the workload of manual parameter adjustment and improves the speed of operating condition switching and the reproducibility of control input.

[0051] When solenoid valve 11 remains open or bypassed, the electro-proportional valve 10 of this embodiment can directly achieve steady jet regulation; after activating solenoid valve 11, it can switch to pulse jet modulation. Therefore, compared with the existing practice that usually requires two independent gas circuits or extensive modifications to switch between steady / pulse, this embodiment can use the same automatic gas circuit to be compatible with both steady and pulse working modes, making the system more versatile, covering a wider range of working modes with less hardware, and reducing the complexity of system integration.

[0052] The above description is merely a preferred embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A jet control system for suppressing flow separation on a surface with an adverse pressure gradient, characterized in that, The device includes an axisymmetric rotating body model, an actuator group (2), a pulse jet air path, and a parameter control module. The actuator group (2) is installed inside the axisymmetric rotating body model. The actuator group (2) includes several blowing chambers (1) evenly arranged along the circumference of the axisymmetric rotating body model. The air inlet of each blowing chamber (1) is connected to the pulse jet air path. The angle between the air outlet direction of each blowing chamber (1) and the wall of the axisymmetric rotating body model is adjustable. The pulse jet air path is communicatively connected to the parameter control module.

2. The jet control system for suppressing flow separation on a reverse pressure gradient surface according to claim 1, characterized in that, Each of the blowing chambers (1) is a streamlined expansion structure, including an inlet section, an expansion and rectification section and an outlet section arranged in sequence. The end of the inlet section away from the expansion and rectification section is connected to the pulse jet gas path.

3. A jet control system for suppressing flow separation on a reverse pressure gradient surface according to claim 2, characterized in that, The pulse jet air path includes an air compressor (5), a filter (6), an electro-proportional valve (10) and a solenoid valve (11) arranged in sequence. The end of the solenoid valve (11) away from the electro-proportional valve (10) is connected to the inlet section of each blowing chamber (1).

4. A jet control system for suppressing flow separation on a reverse pressure gradient surface according to claim 3, characterized in that, Both the electro-proportional valve (10) and the solenoid valve (11) are communicatively connected to the parameter control module.

5. A jet control system for suppressing flow separation on a surface with an adverse pressure gradient, characterized in that, The system includes a two-dimensional ramp model (3), an actuator group (2), and a steady jet gas path. The two-dimensional ramp model (3) has an internal cavity (4), and the actuator group (2) is arranged inside the cavity (4). The actuator group (2) includes several blowing chambers (1), each blowing chamber (1) is arranged sequentially at a preset interval, and the air inlet of each blowing chamber (1) is connected to the steady jet gas path. The angle between the air outlet direction of each blowing chamber (1) and the wall of the two-dimensional ramp model (3) is adjustable.

6. A jet control system for suppressing flow separation on a reverse pressure gradient surface according to claim 5, characterized in that, The receiving cavity (4) is flush with the outer surface of the two-dimensional ramp model (3).

7. A jet control system for suppressing flow separation on a reverse pressure gradient surface according to claim 5, characterized in that, Each of the blowing chambers (1) is a streamlined expansion structure, including an inlet section, an expansion and rectification section and an outlet section arranged in sequence. The end of the inlet section away from the expansion and rectification section is connected to the pulse jet gas path.

8. A jet control system for suppressing flow separation on a reverse pressure gradient surface according to claim 7, characterized in that, The constant jet air path includes at least one constant jet air path, which includes an air compressor (5), a filter (6), a pressure regulating valve (7), a flow meter (8), and a throttle valve (9) arranged in sequence. The end of the throttle valve (9) away from the flow meter (8) is connected to the inlet section of the corresponding blowing chamber (1).

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