Steering enhancement and drag reduction method and device for high-speed aircraft rudder shock wave regulation and control

Abstract

The invention relates to a steerage enhancement and drag reduction method and device for high-speed aircraft rudder shock wave regulation and control. The method comprises the following steps: arranging a high-energy jet array on a control surface of the high-speed aircraft; the high-energy jet jetted by the high-energy jet array directly acts with the incoming flow to redistribute the pressure on the control surface so as to regulate and control the flow field shock wave of the control surface of the high-speed aircraft; the speed near a high-energy jet outlet is increased through high-energy jet sprayed by the high-energy jet array, and an area for reducing frictional resistance is generated at the downstream of the high-energy jet outlet, so that the resistance of the high-speed aircraft is reduced. The local frictional resistance of the control surface of the aircraft can be regulated while the control efficiency of the control surface of the high-speed aircraft is enhanced.

Description

Technical Field

[0001] The present invention relates to the technical field of high-speed aircraft control, and in particular to a method and device for enhancing rudder efficiency and reducing drag of a high-speed aircraft rudder body shock wave control. Background Art

[0002] Mechanical control surfaces are key components of high-speed aircraft. Their performance directly affects the range, maneuverability and survivability of high-speed aircraft, and are the focus of high-speed aircraft research and development. Mechanical control surfaces must maintain high maneuverability, rapid response and high sensitivity to changes in the deflection angle of the control surfaces when working at high speed and high altitude. High-speed aircraft are also required to have the ability to travel long distances, which requires reducing the resistance they encounter.

[0003] However, due to the complex flow phenomena such as three-dimensional shock wave interference, shock wave boundary layer interference, boundary layer transition, boundary layer separation and reattachment in the rudder area of ​​high-speed aircraft, when the high-speed aircraft is flying, the control efficiency of the rudder surface is reduced, and the sensitivity of the aircraft control torque to the change of the rudder surface deflection angle is weakened. In addition, among the great resistances encountered by high-speed aircraft during flight, friction resistance accounts for a large proportion, which will seriously affect the range of the aircraft. Summary of the invention

[0004] Based on this, it is necessary to provide a rudder efficiency enhancement and drag reduction method and device for high-speed aircraft rudder body shock wave regulation that can enhance the control efficiency of high-speed aircraft rudder surfaces and reduce the friction resistance of aircraft rudder surfaces in response to the above technical problems.

[0005] A method for enhancing the rudder efficiency and reducing drag of a high-speed aircraft rudder body shock wave control, wherein a high-energy jet array is arranged on the rudder surface of the high-speed aircraft; the method comprises: The high-energy jets ejected by the high-energy jet array directly interact with the incoming flow to redistribute the pressure on the rudder surface, so as to regulate the flow field shock wave of the rudder surface of the high-speed aircraft; The high-energy jets ejected by the high-energy jet array raise the velocity profile near the high-energy jet outlet and generate a region with reduced friction resistance downstream of the high-energy jet outlet, thereby reducing the resistance of the high-speed aircraft.

[0006] In one of the embodiments, a high-energy jet array is arranged on the windward side of the rudder of the high-speed aircraft, and the high-energy jets ejected by the high-energy jet array interact with the incoming flow to enhance the nose-down moment of the high-speed aircraft.

[0007] In one of the embodiments, on the windward side of the rudder of a high-speed aircraft, the high-energy jet array is arranged on the windward side close to the trailing edge.

[0008] In one of the embodiments, a high-energy jet array is arranged on the leeward side of the rudder surface of the high-speed aircraft, and the high-energy jets ejected by the high-energy jet array interact with the incoming flow to increase the nose-up moment of the high-speed aircraft.

[0009] In one of the embodiments, on the leeward side of the high-speed aircraft control surface, the high-energy jet array is arranged on the leeward side close to the trailing edge.

[0010] In one of the embodiments, the high-energy jet array is composed of more than two high-energy jet exciters; each of the high-energy jet exciters is distributed in a spanwise array along the flow direction of the rudder surface.

[0011] In one of the embodiments, in the span direction of the rudder surface, when the high-energy jet exciters are arranged, the influence areas of the high-energy jet three-dimensional bow shock waves upstream of each high-energy jet outlet are connected to each other.

[0012] In one of the embodiments, on the windward side of the high-speed aircraft rudder surface, the high-energy jet exciter is arranged at any chord length position of the trailing edge rudder surface of the windward side and / or the leeward side.

[0013] In one of the embodiments, when each of the high-energy jet exciters performs jet injection, the jet ejection angle is perpendicular to the rudder surface.

[0014] A rudder effect enhancement and drag reduction device for shock wave control of a rudder body of a high-speed aircraft, the device comprising: a sensor and a processor arranged on the high-speed aircraft, a suction hole arranged near an air inlet of the high-speed aircraft, and a high-energy jet array arranged on a rudder surface of the high-speed aircraft; The sensor is electrically connected to the processor, the processor is electrically connected to a control switch of the high-energy jet array, and the suction hole is communicated with the high-energy jet array through a pipeline.

[0015] The above-mentioned rudder efficiency enhancement and drag reduction method and device for shock wave control of the rudder body of a high-speed aircraft are achieved by arranging a high-energy jet array on the rudder surface of the high-speed aircraft; the high-energy jets ejected from the high-energy jet array directly act on the incoming flow to redistribute the pressure on the rudder surface to control the flow field shock waves of the rudder surface of the high-speed aircraft; the high-energy jets ejected from the high-energy jet array raise the velocity profile near the high-energy jet outlet and generate an area with reduced friction resistance downstream of the high-energy jet outlet to reduce the resistance of the high-speed aircraft.

[0016] The present invention adjusts the shock wave structure, vortex structure and flow characteristics of the high-speed aircraft rudder surface by directly interacting with the incoming flow through the high-energy jets ejected by the high-energy jet array, thereby changing the pressure distribution on the rudder surface and enhancing the control efficiency of the high-speed aircraft rudder surface; at the same time, the high-energy jets ejected by the high-energy jet array change the velocity gradient of the aircraft rudder surface and the body and other areas to achieve the purpose of regulating the local friction resistance of the aircraft rudder surface. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0018] Figure 1 It is a flow chart of the method for enhancing the rudder efficiency and reducing drag by controlling the shock wave of the rudder body of a high-speed aircraft in Example 1; Figure 2 This is a schematic diagram of the distribution of the high-energy jet array on the control surface in Example 1; Figure 3 This is a schematic diagram of the shock wave structure of the lower control surface controlled by the high-energy jet array in Example 1; Figure 4 The pressure distribution cloud diagram of the control surface in Example 1; Figure 5 This is a schematic diagram of the effect of the high-energy jet array in Example 1 on enhancing the rudder effect; Figure 6 It is the velocity gradient contour map at Z=0.042m in Example 1, where: Figure 6 (a) is the velocity gradient contour map under uncontrolled state. Figure 6 (b) is a velocity gradient contour diagram of the control surface high-energy jet array under the control of the method of the present invention; Figure 7 It is the velocity gradient contour map at Y=0.016m in Example 1, where: Figure 7 (a) is the velocity gradient contour map under uncontrolled state. Figure 7 (b) is a velocity gradient contour diagram of the control surface high-energy jet array under the control of the method of the present invention; Figure 8 It is a structural block diagram of the rudder effect enhancement and drag reduction device for high-speed aircraft rudder body shock wave control in Example 2; Fig. 9 This is a schematic diagram of air introduction through the suction hole in Example 2.

[0019] Explanation of the reference numerals: suction hole 1, air collecting chamber 2, pipeline 3, line 31, high-energy jet exciter 4, processor 5, sensor 6, fuselage 7, control surface 8.

[0020] The purpose, features and advantages of the present invention will be further described with reference to the accompanying drawings in conjunction with the embodiments. DETAILED DESCRIPTION

[0021] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0022] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0023] In addition, in the present invention, descriptions such as "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" or "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0024] In the present invention, 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, an electrical connection, a physical connection, or a wireless communication connection; it can be a direct connection, or an indirect connection through an intermediate medium, or 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 the present invention can be understood according to specific circumstances.

[0025] It can be understood that the technical solutions between the various embodiments of the present invention can be combined with each other, but it must be based on the fact that ordinary technicians in the field can implement it. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0026] The following will describe the implementation of the present invention in detail with reference to the accompanying drawings in the embodiment diagram of the present invention.

[0027] Example 1 The present embodiment discloses a method for enhancing the rudder efficiency and reducing drag by regulating the shock wave of the rudder body of a high-speed aircraft. The high-energy jets ejected by the high-energy jet array directly interact with the incoming flow to adjust the shock wave structure, vortex structure and flow characteristics of the rudder surface of the high-speed aircraft, thereby changing the pressure distribution on the rudder surface and enhancing the control efficiency of the rudder surface of the high-speed aircraft. At the same time, the high-energy jets ejected by the high-energy jet array change the velocity gradient of the aircraft rudder surface and the body, so as to achieve the purpose of regulating the local friction resistance of the aircraft rudder surface.

[0028] like Figure 1 As shown, the method for enhancing the rudder efficiency and reducing drag of the rudder body shock wave control of the high-speed aircraft provided in this embodiment includes the following steps: Step 201, arranging a high-energy jet array on the control surface of a high-speed aircraft.

[0029] Step 202, the high-energy jets ejected from the high-energy jet array directly interact with the incoming flow to redistribute the pressure on the control surface to control the flow field shock wave of the control surface of the high-speed aircraft.

[0030] Step 203, the high-energy jets ejected by the high-energy jet array raise the velocity profile near the high-energy jet outlet and generate a region of reduced frictional resistance downstream of the high-energy jet outlet to reduce the resistance of the high-speed aircraft.

[0031] It can be understood that by arranging high-energy jet arrays on the rudders on both sides of the high-speed aircraft, it is possible to adjust and control the shock wave structure of the rudder surface of the high-speed aircraft, the three-dimensional shock wave interference structure of the rudder body of the high-speed aircraft, and the vortex structure in the corner flow field, enhance the shock wave intensity of the front edge of the rudder, change the pressure distribution of the rudder surface on both sides of the high-speed aircraft, and provide additional pitching moment for the high-speed aircraft, so as to achieve the goal of enhancing the control efficiency of the rudder surface of the high-speed aircraft. At the same time, near the high-energy jet outlet, due to the presence of the jet, the velocity profile of the rudder surface can be changed, the local friction resistance can be reduced, and finally the goal of enhancing the control efficiency of the rudder surface of the high-speed aircraft and reducing the resistance can be achieved.

[0032] In one of the embodiments, a high-energy jet array is arranged on the windward side of the rudder of a high-speed aircraft, and the high-energy jets ejected from the high-energy jet array interact with the incoming flow to enhance the nose-down moment of the high-speed aircraft.

[0033] In one of the embodiments, on the windward surface of the high-speed aircraft control surface, the high-energy jet array is arranged on the windward side close to the trailing edge.

[0034] In one of the embodiments, a high-energy jet array is arranged on the leeward side of the rudder surface of the high-speed aircraft, and the high-energy jets ejected from the high-energy jet array interact with the incoming flow to increase the nose-up moment of the high-speed aircraft.

[0035] In one of the embodiments, on the leeward side of the control surface of the high-speed aircraft, the high-energy jet array is arranged on the leeward side close to the trailing edge.

[0036] In this embodiment, a high-energy jet array can be arranged on the windward side and / or leeward side of the high-speed aircraft as needed, and the high-energy jets ejected from the high-energy jet array directly interact with the incoming flow to form a shock wave structure and a vortex structure, thereby forming a separation shock wave and a three-dimensional bow shock wave behind the oblique shock wave of the rudder surface, thereby realizing the regulation of the shock wave of the rudder surface flow field, enhancing the pressure distribution in front of the high-energy jet outlet on the rudder surface, increasing the pressure on the rudder surface in front of the high-energy jet outlet, and improving the rudder surface control efficiency of the high-speed aircraft at the same rudder surface deflection angle.

[0037] Specifically, when it is necessary to enhance the head-down maneuverability of a high-speed aircraft or adjust the flight attitude to obtain a head-down trend, the aircraft's mechanical rudder control is coordinated with the high-energy jet array on the windward side to open and eject high-energy jets to enhance the head-down moment of the high-speed aircraft and achieve regulation of the head-down action in the aircraft's pitch attitude. For example, during the flight of a high-speed aircraft, if you want to quickly change the flight trajectory to dive downward or correct the attitude to enter a specific flight state, you need to generate a head-down moment. The windward high-energy jet array cooperates with the mechanical rudder to perform corresponding work, and the ejected jet interacts with the incoming flow to redistribute the rudder pressure, forming a stronger shock wave at the front edge of the rudder, causing the windward pressure to change, thereby generating a head-down moment, and at the same time regulating the shock wave of the rudder flow field to ensure airflow stability and improve control accuracy.

[0038] When it is necessary to enhance the nose-up maneuverability of a high-speed aircraft or adjust the flight attitude to obtain a nose-up trend, the aircraft's mechanical rudder control is coordinated with the high-energy jet array on the leeward side to open and eject high-energy jets to enhance the nose-up moment of the high-speed aircraft, and to achieve regulation of the aircraft's pitch attitude and the shock wave of the rudder flow field in favor of the nose-up action. For example, a nose-up moment is required during the aircraft's ascent phase or when it needs to be adjusted to a level flight attitude. The leeward high-energy jet array cooperates with the mechanical rudder to perform corresponding work, and the ejected jet interacts with the incoming flow to change the pressure distribution of the rudder surface, generating an upward pressure difference, forming a nose-up moment, and at the same time changing the shock wave structure of the rudder flow field to ensure flight stability and controllability.

[0039] When it is necessary to achieve more complex flight attitude adjustments or optimize the overall aerodynamic performance of the aircraft, the high-energy jet arrays on the windward and leeward sides are opened and ejected at the same time through the mechanical control of the aircraft, so as to achieve coordinated control of the aircraft's pitch, yaw and other attitudes, as well as comprehensive optimization of the complex flow field in the rudder area. For example, when a high-speed aircraft performs high-maneuverability flight, such as rapid turns and evasive actions, a single windward or leeward jet cannot meet the needs. At this time, the jets on both sides are turned on at the same time, and the mechanical control surfaces are used to perform corresponding work. By precisely controlling the intensity, angle and other parameters of the jets on both sides, the attitude of the aircraft can be adjusted more flexibly, and the complex flow fields such as shock wave interference and vortex structure in the rudder area can be comprehensively optimized to reduce resistance and improve flight efficiency and maneuverability.

[0040] At the same time, the high-energy jets ejected from the high-energy jet array on the windward and / or leeward sides will lift the velocity profile near the high-energy jet outlets, reduce the velocity gradients in these areas, and reduce the frictional resistance in these areas; and also generate an area with reduced frictional resistance downstream of the high-energy jet outlets, thereby achieving the goal of enhancing the rudder effect while reducing the resistance experienced by high-speed aircraft.

[0041] In one of the embodiments, the high-energy jet array is composed of more than two high-energy jet exciters; each high-energy jet exciter is distributed in a spanwise array along the flow direction of the rudder surface.

[0042] The high-energy jet array method includes arranging two or more high-energy jet exciters in rows and columns with equal spacing, and / or unequal spacing; it can be arranged in a single row or in more than two rows. The number and spacing of the high-energy jet exciters are set according to the specific situation.

[0043] Specifically, see Figure 2 , is to arrange a high-energy jet array near the trailing edge on the windward side. It can be seen that on each rudder, the high-energy jet exciters are arranged in double rows and single columns with equal spacing. Each high-energy jet exciter is arranged as far downstream as possible in the flow direction, and the high-energy jet exciters on the rudders on both sides of the high-speed aircraft are symmetrical based on the fuselage centerline and are evenly arranged along the flow direction of the rudder surface. This is to improve the control efficiency of the rudder surface of the high-speed aircraft while minimizing the friction resistance of the rudder surface.

[0044] In addition, the ejection intensity of high-energy jets can be controlled to cope with more complex flight conditions. For example, the ejection intensity of high-energy jet actuators can be adjusted according to the flight state of the high-speed aircraft (such as flight Mach number, angle of attack change, etc.) and the required control effect of the rudder surface (such as enhancing the nose-down or nose-up moment, optimizing aerodynamic characteristics, etc.) to achieve more precise control of the shock wave of the rudder surface flow field, while further improving the control efficiency of the rudder surface, minimizing the adverse effects on the overall resistance of the aircraft, and ensuring that the high-speed aircraft can maintain good flight performance and stability under various complex flight conditions.

[0045] In one of the embodiments, in the span direction of the rudder surface, when the high-energy jet exciters are arranged, the influence areas of the high-energy jet three-dimensional bow shock waves upstream of the high-energy jet outlets are connected to each other.

[0046] It can be understood that when arranging the high-energy jet exciter, in the span direction of the rudder, the influence area of ​​the high-energy jet three-dimensional bow shock wave upstream of each high-energy jet outlet is interconnected, so as to achieve a point-to-surface control effect. In the flow direction of the rudder, it should be ensured that the influence of the reverse rotating vortex system downstream of each high-energy jet on the pressure distribution of the rudder, and the direct three-dimensional shock wave interference phenomenon between the rudder and the fuselage produces additional lateral force and lateral moment on the fuselage. And the influence range of the high-energy jet on the velocity gradient on the rudder is increased as much as possible, so as to achieve the purpose of maximizing the reduction of the resistance of the high-speed aircraft.

[0047] In one of the embodiments, on the windward side of the high-speed aircraft control surface, the high-energy jet exciter is arranged at any chord length position of the trailing edge control surface of the windward side and / or the leeward side.

[0048] It can be understood that as the flight Mach number of the high-speed aircraft gradually increases, in order to reduce the lateral force generated by the three-dimensional shock wave interference phenomenon between the rudder and the fuselage, the outlet position of the high-energy jet array should be moved as far downstream as possible to the rudder flow, so as to maximize the control efficiency of the rudder; but the moving distance cannot be too large, otherwise the area of ​​the local drag reduction of the rudder will be reduced, and the friction resistance of the high-speed aircraft cannot be effectively reduced. Therefore, the layout position of the high-energy jet exciter can be determined according to the required control effect and flight conditions.

[0049] For example, when enhancing the nose-down moment of a high-speed aircraft with Ma=3, a high-energy jet exciter is arranged on the windward side at a position 1 / 3 of the chord length of the rudder surface from the trailing edge. This can not only reduce the intensity of the periodic changes in the pressure distribution of the rudder surface caused by the reverse vortex downstream of the high-energy jet, thereby stably enhancing the rudder control efficiency of the high-speed aircraft, but also increase the influence area of ​​the high-energy jet array on the local friction resistance of the rudder surface as much as possible, thereby reducing the resistance experienced by the high-speed aircraft.

[0050] In one of the embodiments, when each high-energy jet exciter performs jet ejection, the jet ejection angle is perpendicular to the rudder surface.

[0051] In one embodiment, if Figure 3 The figure shows the shock wave structure of the rudder under the control of the high-energy jet array. The red curve in the figure is the oblique shock wave of the rudder surface, and the yellow curve is the three-dimensional bow shock wave generated by the high-energy jet. The other more detailed flow field structures are not marked in the figure. The three-dimensional shock wave surface in the figure is colored according to the pressure gradient. It can be seen that after the high-energy jet bow shock wave, the pressure increases, and the high-pressure area on the windward side of the rudder increases.

[0052] In one embodiment, if Figure 4 As shown in Figure 1, the pressure distribution cloud diagram of the rudder surface before and after the high-energy jet array on the rudder surface works when the rudder surface deflects 10°. It can be seen that when the high-energy jet array is activated, the pressure in front of the high-energy jet outlet on the rudder surface increases significantly, which enhances the control efficiency of the rudder surface of the high-speed aircraft.

[0053] In one embodiment, if Figure 5 As shown in FIG. 1 , it is a schematic diagram of the effect of the high-energy jet array on the rudder surface of a high-speed aircraft to enhance the rudder effect after the high-energy jet array is turned on. It can be found from the figure that after the control method provided by the present invention is used, in the process of deflecting the rudder surface from 0° to 18°, the pitch moment coefficient of the aircraft increases by 13.78%. The control efficiency of the rudder surface is significantly improved.

[0054] In one embodiment, if Figure 6 As shown in the figure, the velocity gradient contour diagram of the rudder flow field at Z=0.042m before and after the high-energy jet array of the rudder is started in the present invention is compared. Figure 6 (a) with Figure 6 (b) It can be seen that under the action of the high-energy jet array, the velocity gradient in a large area upstream of the jet outlet is reduced, the velocity profile is lifted, the velocity gradient on the windward side of the aircraft's rudder is reduced, and the frictional resistance is also reduced. The resistance on the aircraft's rudder is reduced by about 1.56%.

[0055] In one embodiment, if Figure 7 As shown in FIG. 7 (a), the velocity gradient contour diagram of the flow field near the fuselage of the high-speed aircraft at Y=0.016m before and after the high-energy jet array of the control surface in the present invention is activated is shown in FIG. Figure 7 (b) Under the action of the high-energy jet array, the velocity gradient near the rudder gap on the side of the high-speed aircraft fuselage is reduced, thereby reducing the friction resistance at this position. The resistance generated by the high-speed aircraft fuselage part is reduced by about 1.31% under the action of the high-energy jet array on the rudder surface in the embodiment of the present invention.

[0056] Although this embodiment Figure 1The steps in the process are shown in sequence as indicated by the arrows, but the steps are not necessarily executed in the order indicated by the arrows. Unless otherwise specified in this document, there is no strict order restriction for the execution of the steps, and the steps can be executed in other orders. Figure 1 At least part of the steps may include multiple sub-steps or multiple stages. These sub-steps or stages are not necessarily executed at the same time, but can be executed at different times. The execution order of these sub-steps or stages is not necessarily sequential, but can be executed in turn or alternately with other steps or at least part of the sub-steps or stages of other steps.

[0057] Example 2 Based on the method for enhancing the rudder effect and reducing drag by controlling the rudder body shock wave of a high-speed aircraft in Example 1, this embodiment discloses a device for enhancing the rudder effect and reducing drag by controlling the rudder body shock wave of a high-speed aircraft, such as Figure 8 and Fig. 9 As shown, the rudder efficiency enhancement and drag reduction device for shock wave control of the rudder body of a high-speed aircraft includes: a sensor 6 and a processor 5 arranged on the upper fuselage 7 of the high-speed aircraft, a suction hole 1 arranged near the air inlet of the high-speed aircraft, and a high-energy jet array arranged on the rudder surface 8 of the high-speed aircraft; the sensor 6 is electrically connected to the processor 5, the processor 5 is electrically connected to the control switches of the high-energy jet array and the suction hole 1 respectively, and the suction hole 1 is connected to the high-energy jet array through a pipeline 3.

[0058] Specifically, the suction hole 1 is arranged in a high-pressure distribution area on the surface of the high-speed aircraft, and the pressure distribution in this area is higher than the windward side pressure of the control surface. Fig. 9 As shown, a suction hole 1 is arranged at the head of a high-speed aircraft. Since the head of a high-speed aircraft has a very high dynamic pressure, by arranging a suction hole 1 capable of high-pressure gas suction at this position, the high-pressure gas at the head of the high-speed aircraft can be collected and used to generate high-energy jets through a high-energy jet array. In addition, the suction hole 1 can also be arranged at the air inlet position.

[0059] The high-energy jet array includes more than two high-energy jet exciters 4, which are arranged downstream of the flow direction of the rudder surface 8 and arranged along the span direction. Each high-energy jet exciter 4 is connected to the suction hole 1 through a pipeline 3. The suction hole 1 and the high-energy jet exciter 4 are respectively controlled to be turned on and off by a control switch, and each high-energy jet exciter 4 has an independent control switch, so that the processor 5 can independently turn on or off high-energy jet exciters 4 at different positions and in different numbers. Each control switch is electrically connected to the processor 5 through a line 31. The high-energy jet exciter 4 adopts a steady high-energy jet mode.

[0060] In addition, a gas collecting chamber 2 is provided between the suction hole 1 and the high-energy jet exciter 4 , through which gas is stored.

[0061] When working, the sensor 6 monitors the flight environment parameters in real time, including the pressure distribution on the rudder surface and the resistance of the aircraft; the sensor 6 feeds back the flight environment parameters to the processor 5, and the processor 5 judges the working state of the high-energy jet array on the rudder surface 8 according to the working state of the high-speed aircraft and external conditions, that is, turns on or off the high-energy jet generating devices at different positions and in different quantities. When the control efficiency of the aircraft rudder surface is low and the sensitivity of the rudder surface deflection angle is low, the maneuverability of the high-speed aircraft will be greatly reduced. At this time, the high-energy jet array on the rudder surface of the high-speed aircraft is turned on, and the pressure of the aircraft rudder surface can be redistributed, while improving the control efficiency and sensitivity of the aircraft rudder surface, and the velocity type in the boundary layer of the rudder surface is lifted, the friction resistance of the local area of ​​the rudder surface is reduced, and the resistance of the high-speed aircraft is reduced.

[0062] The high-pressure airflow in the head area of ​​the aircraft passes through the air inlet entrance, enters the air collecting chamber 2 inside the high-speed aircraft through the suction hole 1, and is connected to the high-energy jet exciter 4 through the pipeline 3. When the high-energy jet exciter 4 is working, a high-speed jet is generated at the high-energy jet outlet, which can form a new shock wave structure on the aircraft rudder 8 and change the original rudder flow field structure.

[0063] The device provided in this embodiment can adjust the shock wave structure, vortex structure and flow characteristics of the high-speed aircraft control surface through the high-energy jet array generated by the self-sustaining effect, and regulate the local friction resistance of the aircraft control surface while enhancing the control efficiency of the high-speed aircraft control surface. The energy required for the high-energy jet exciter 4 to work is completely from the high-speed incoming flow itself, and no additional supply is required, which has a wide range of engineering application prospects.

[0064] The technical features of the above embodiments may be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0065] The above-mentioned embodiments only express several implementation modes of the present invention, and the description thereof is relatively specific and detailed, but it cannot be understood as limiting the scope of the invention. It should be pointed out that, for a person of ordinary skill in the art, several modifications and improvements can be made without departing from the concept of the present invention, and these all belong to the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the attached claims.

Claims

1. A method for enhancing rudder efficiency and reducing drag by controlling shock waves of a rudder body of a high-speed aircraft, characterized in that: Arranging a high-energy jet array on the control surface of a high-speed aircraft; the method comprises: The high-energy jets ejected by the high-energy jet array directly interact with the incoming flow to redistribute the pressure on the rudder surface, so as to regulate the flow field shock wave of the rudder surface of the high-speed aircraft; The high-energy jets ejected by the high-energy jet array raise the velocity profile near the high-energy jet outlet and generate a region with reduced friction resistance downstream of the high-energy jet outlet, thereby reducing the resistance of the high-speed aircraft.

2. The method for enhancing rudder efficiency and reducing drag by shock wave control of a rudder body of a high-speed aircraft according to claim 1, characterized in that: A high-energy jet array is arranged on the windward side of the rudder surface of the high-speed aircraft, and the high-energy jets ejected by the high-energy jet array interact with the incoming flow to enhance the nose-down moment of the high-speed aircraft.

3. The method for enhancing rudder efficiency and reducing drag by shock wave control of a rudder body of a high-speed aircraft according to claim 2, characterized in that: On the windward side of the high-speed aircraft rudder surface, the high-energy jet array is arranged on the windward side close to the trailing edge.

4. The method for enhancing rudder efficiency and reducing drag by shock wave control of a rudder body of a high-speed aircraft according to claim 1, characterized in that: A high-energy jet array is arranged on the leeward side of the rudder surface of the high-speed aircraft, and the high-energy jets ejected by the high-energy jet array interact with the incoming flow to increase the nose-up moment of the high-speed aircraft.

5. The method for enhancing rudder efficiency and reducing drag by shock wave control of a rudder body of a high-speed aircraft according to claim 4, characterized in that: On the leeward side of the high-speed aircraft rudder surface, the high-energy jet array is arranged on the leeward side close to the trailing edge.

6. The method for enhancing rudder efficiency and reducing drag by shock wave control of a rudder body of a high-speed aircraft according to claim 3 or 5, characterized in that: The high-energy jet array is composed of more than two high-energy jet exciters; each of the high-energy jet exciters is distributed in a spanwise array along the flow direction of the rudder surface.

7. The method for enhancing rudder efficiency and reducing drag by shock wave control of a rudder body of a high-speed aircraft according to claim 6, characterized in that: In the span direction of the rudder surface, when the high-energy jet exciters are arranged, the influence areas of the high-energy jet three-dimensional bow shock waves upstream of the high-energy jet outlets are connected to each other.

8. The method for enhancing rudder efficiency and reducing drag by shock wave control of a rudder body of a high-speed aircraft according to claim 7, characterized in that: On the windward side of the high-speed aircraft rudder surface, the high-energy jet exciter is arranged at any chord length position of the windward side and / or the leeward side trailing edge rudder surface.

9. The method for enhancing rudder efficiency and reducing drag by shock wave control of a rudder body of a high-speed aircraft according to claim 8, characterized in that: When each of the high-energy jet exciters performs jet injection, the jet ejection angle is perpendicular to the rudder surface.

10. A rudder effect enhancement and drag reduction device for shock wave control of a rudder body of a high-speed aircraft, characterized in that: A method for enhancing rudder efficiency and reducing drag by shock wave control of a high-speed aircraft rudder body according to any one of claims 1 to 9, wherein the device comprises: a sensor and a processor arranged on the high-speed aircraft, a suction hole arranged near the air inlet of the high-speed aircraft, and a high-energy jet array arranged on the rudder surface of the high-speed aircraft; The sensor is electrically connected to the processor, and the processor is electrically connected to the high-energy jet array and the control switch of the suction hole respectively, and the suction hole is connected to the high-energy jet array through a pipeline.

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