Mean structure for controlling oblique shock wave angle and oblique detonation engine

Abstract

The invention discloses an element structure for controlling the oblique shock wave angle and an oblique detonation engine, the element structure for controlling the oblique shock wave angle comprises a plurality of plate bodies which are stacked up and down and a plurality of linear moving mechanisms, each plate body is provided with a first surface, a second surface, a third surface and a fourth surface, the first surface is parallel to the length direction of a combustion chamber, and the fourth surface is parallel to the length direction of the combustion chamber; the second face is arranged on the side, close to the inlet end of the combustion chamber, of the first face, the included angle theta is formed between the second face and the first face, the third face is arranged on the side, close to the outlet end of the combustion chamber, of the first face, the fourth face is parallel to the first face, and the two ends of the fourth face are connected with the second face and the third face respectively. A wedge surface is formed by connecting lines between inflection points in the plate bodies; the moving ends of the multiple linear moving mechanisms are connected with the third faces of the multiple plate bodies in a one-to-one correspondence mode. The traditional mode of changing the angle of the wedge surface through rotary motion is changed into the mode of changing the angle of the wedge surface through horizontal motion, so that the blockage ratio of the engine is prevented from being changed.

Description

Technical Field

[0001] This invention relates to the field of oblique detonation engine technology, specifically a metastructure for controlling the angle of oblique shock waves and an oblique detonation engine. Background Technology

[0002] like Figure 1 As shown, the oblique detonation engine uses the oblique shock wave induced by the wedge surface to initiate the oblique detonation shock wave. When it is necessary to change the initiation position or shape of the oblique detonation shock wave, it is necessary to change the intensity of the oblique shock wave. The traditional method is to rotate the wedge surface around the intersection point with the bottom surface to change the wedge surface angle, thereby changing the intensity and angle of the oblique shock wave, and thus achieving the purpose of controlling the initiation and shape of the oblique detonation shock wave.

[0003] While rotating the wedge surface around its intersection with the base can change the wedge angle, it has significant drawbacks. First, changing the wedge angle... β When the total height H changes, the engine's blockage ratio will change, causing engine congestion, resulting in decreased engine thrust and boundary layer separation. Secondly, when the wedge rotates around the intersection of the wedge and the bottom surface, it will affect the nozzle behind and cause changes in the nozzle's structure, which is not conducive to stable engine operation. Summary of the Invention

[0004] The purpose of this invention is to provide a metastructure for controlling the angle of oblique shock waves and an oblique detonation engine, so as to solve the technical problems existing in the traditional method of changing the angle of the oblique shock wave by rotating the wedge surface around the intersection point of the wedge surface and the bottom surface.

[0005] The technical solution of this invention is: A modular structure for controlling the angle of oblique shock waves, used as a wedge surface to induce the formation of oblique shock waves on one side of the combustion chamber outlet, includes multiple stacked plates and multiple linear movement mechanisms. Each plate has a first, second, third, and fourth surface. The first surface is parallel to the length direction of the combustion chamber, and the second surface is located on the side of the first surface near the combustion chamber inlet, forming an angle with the first surface. θ The included angle θThe angle is acute. The third surface is located on the side of the first surface near the combustion chamber outlet. The fourth surface is parallel to the first surface, and its two ends are connected to the second and third surfaces respectively. The connection between the second and fourth surfaces forms an inflection point. The line connecting the inflection points in each plate forms a wedge surface. The number of multiple linear moving mechanisms is the same as the number of the multiple plates. Each linear moving mechanism has a moving end that moves along the length of the combustion chamber. The moving ends of the multiple linear moving mechanisms are connected to the third surface of each of the multiple plates respectively. The angle of the wedge surface is adjusted by driving each plate to move in a staggered manner towards the combustion chamber outlet through the multiple linear moving mechanisms.

[0006] Preferably, as a further improvement of the present invention, when two adjacent plates are misaligned, the slope of the line connecting the inflection points of the two adjacent plates is less than or equal to the slope of the second surface.

[0007] Preferably, as a further improvement of the present invention, the included angle θ The degree range is 10° to 45°.

[0008] Preferably, as a further improvement of the present invention, the included angle θ The degree is 30°.

[0009] Preferably, as a further improvement of the present invention, the linear motion mechanism is any one of a lead screw linear motion module and a hydraulic cylinder.

[0010] Preferably, as a further improvement of the present invention, the plate is made of a high-temperature resistant alloy or a ceramic matrix composite material.

[0011] Preferably, as a further improvement of the present invention, the height of the third surface is 2mm to 5mm.

[0012] The present invention also discloses a detonation engine, including a combustion chamber and the aforementioned substructure for controlling the angle of the detonation shock wave. The lower wall of the outlet end of the combustion chamber is provided with an installation port, and multiple plates stacked vertically are disposed in the installation port. Each of the linear movement mechanisms is mounted on the body of the detonation engine.

[0013] Compared with the prior art, the beneficial effects of the present invention are: 1. This invention induces the formation of oblique shock waves by replacing the original wedge surface with a wedge surface formed by the lines connecting the inflection points of multiple stacked plates. When it is necessary to change the intensity of the oblique shock wave, multiple linear movement mechanisms drive each plate to move in a staggered manner toward the combustion chamber outlet end, so that the angle of the wedge surface formed by the lines connecting the inflection points of each plate changes, thereby controlling the angle of the oblique shock wave to change the intensity of the oblique shock wave.

[0014] 2. Since the change of the wedge angle is achieved by the horizontal staggered movement of multiple stacked plates, and the height of the multiple plates remains constant, the traditional method of changing the wedge angle through rotational motion is transformed into a method of changing the wedge angle through horizontal motion. This avoids problems caused by changing the engine's blockage ratio and does not affect the stable operation of the engine by changing the structure of the nozzle. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of an existing oblique detonation engine.

[0016] Figure 2 This is a three-dimensional structural diagram of a metastructure for controlling the angle of oblique shock waves according to the present invention.

[0017] Figure 3 This is a schematic diagram of the plate structure in the metastructure for controlling the angle of oblique shock waves according to the present invention.

[0018] Figure 4 This is a schematic diagram of the structure when the second surfaces of each plate are aligned in the metastructure for controlling the angle of the oblique shock wave according to the present invention.

[0019] Figure 5 This is a schematic diagram of the structure of the metastructure for controlling the angle of the oblique shock wave in this invention, when the second surfaces of each plate are misaligned.

[0020] Figure 6 This is an enlarged schematic diagram of the second surface of each plate in the metastructure for controlling the angle of the oblique shock wave of the present invention when they are misaligned.

[0021] Figure 7 This is a three-dimensional structural diagram of a component structure for controlling the angle of oblique shock waves, as described in this invention, installed in the combustion chamber of an oblique detonation engine.

[0022] Figure 8 This is a temperature diagram showing the alignment of the inclined surfaces of each plate unit in the elemental structure for controlling the angle of the oblique shock wave according to the present invention.

[0023] Figure 9 This is a temperature cloud map showing the misalignment of the inclined surfaces of each plate unit in the elemental structure for controlling the angle of the oblique shock wave according to the present invention. Detailed Implementation

[0024] The following is combined with Figures 2-9The specific embodiments of the present invention will be described in detail below. In the description of the invention, it should be understood that the terms "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention.

[0025] The terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature; in the description of the invention, unless otherwise stated, "a plurality of" means two or more.

[0026] Example 1 like Figures 2-9 As shown, this embodiment of the invention provides a substructure for controlling the angle of oblique shock waves, which is set on one side of the combustion chamber outlet end 2 to act as a wedge surface to induce the formation of oblique shock waves. It includes multiple plates 3 stacked vertically and multiple linear movement mechanisms 4. Each plate 3 has a first surface 31, a second surface 32, a third surface 33, and a fourth surface 34. The first surface 31 is parallel to the length direction of the combustion chamber, and the second surface 32 is located on the side of the first surface 31 near the combustion chamber inlet end 1, forming an angle between the second surface 32 and the first surface 31. θ included angle θ The angle is acute. The third surface 33 is located on the side of the first surface 31 near the combustion chamber outlet end 2. The fourth surface 34 is parallel to the first surface 31, and the two ends of the fourth surface 34 are connected to the second surface 32 and the third surface 33 respectively. The connection between the second surface 32 and the fourth surface 34 forms an inflection point 35. The line connecting the inflection points 35 in each plate 3 forms a wedge surface. The number of multiple linear moving mechanisms 4 is the same as the number of multiple plates 3. The linear moving mechanism 4 has a moving end that moves along the length of the combustion chamber. The moving ends of the multiple linear moving mechanisms 4 are connected to the third surface 33 in each of the multiple plates 3 respectively. The angle of the wedge surface is adjusted by driving each plate 3 to move in a staggered manner towards the combustion chamber outlet end 2 through the multiple linear moving mechanisms 4.

[0027] In this embodiment, multiple sets of stacked control unit components are used to replace the original wedge surface, as shown in the reference. Figure 5As shown, when the second surfaces 32 of each plate 3 are aligned, a complete wedge surface is formed, at which point the maximum wedge angle is obtained. During operation, the supersonic airflow enters the combustion chamber from the inlet end 1, impacting the wedge surface to form an oblique shock wave. When it is necessary to adjust the intensity of the oblique shock wave, the linear movement mechanism 4 is controlled to move each plate 3 towards the direction closer to the outlet end 2 of the combustion chamber, causing the upper and lower adjacent plates 3 to be misaligned. (Refer to...) Figure 6 As shown, the lines connecting the inflection points 35 of each plate 3 form a new wedge surface. The angle of the new wedge surface is determined by the forward and backward misalignment distance, thus enabling the intensity and angle of the oblique shock wave to be adjusted accordingly as needed. Because the metastructure controlling the oblique shock wave angle in this invention transforms the traditional method of changing the wedge surface angle through rotational motion into a method of changing the wedge surface angle through horizontal motion, it avoids problems caused by changes in the engine's blockage ratio and does not affect the stable operation of the engine by altering the nozzle's structure.

[0028] Furthermore, the slope of the line connecting the inflection points 35 of two adjacent plates 3 after misalignment is less than or equal to the slope of the second surface 32. This arrangement ensures that after misalignment, the position of the sharp corner of the upper plate 3 (the connection between the first surface 31 and the second surface 32) will not exceed the position of the inflection point 35 of the lower plate 3. If it does, the first surface 31 of the upper plate 3 will obstruct the airflow, easily forming a detached shock wave. At the same time, due to the aerodynamic heating of the supersonic airflow, the sharp corner is easily ablated.

[0029] Preferably, the included angle θ The degree measure is 10°~45°, when the included angle θ Shock waves are prone to detaching from the engine body when the angle exceeds 45°, and such a large angle is not used inside the engine. θ The degree can be determined based on the maximum wedge angle required in actual flight. In specific implementation, the included angle... θ The angle was chosen to be 30°.

[0030] The height of the third surface 33 is 2mm to 5mm, which is determined according to the size of the combustion chamber.

[0031] The following parameters are: incoming flow velocity 2861 m / s, static temperature 300 K, and included angle. θ Taking an angle of 30°, a thickness of 2mm for plate 3, and a horizontal spacing of 4mm between two adjacent plates 3 as an example, the implementation of the present invention is verified.

[0032] When the second surfaces 32 of each plate 3 are aligned, the overall wedge angle is 30°, which is the angle between the two surfaces. θ To maintain consistency, the corresponding temperature contour map is as follows: Figure 8 As shown in the figure, a straight oblique shock wave can be observed, with a shock wave angle of 39° when aligned. When the second surfaces 32 of each plate 3 are misaligned, the corresponding temperature contour maps are as follows. Figure 9 As shown, the oblique shock wave is no longer a straight oblique shock wave. Its angle is larger at the bottommost metastructure unit, then attenuates, with a maximum attenuation angle of 27°. The comparison shows that the current metastructure can effectively control the angle of the oblique shock wave.

[0033] The linear motion mechanism can be either a lead screw linear motion module or a hydraulic cylinder. In specific installation, the lead screw linear motion module or the hydraulic cylinder is installed on the engine block.

[0034] Among them, the material of plate 3 is a high-temperature resistant alloy or ceramic matrix composite material, which can adapt to high-temperature environment and avoid being burned by heated airflow.

[0035] Example 2 Based on Embodiment 1, this embodiment also provides a detonation engine, including a combustion chamber and the aforementioned substructure for controlling the angle of the detonation shock wave. The lower wall of the outlet end 2 of the combustion chamber is provided with an installation port 5. Multiple plates 3 stacked vertically are disposed in the installation port 5, and each linear movement mechanism 4 is mounted on the body of the detonation engine.

[0036] The above-disclosed embodiments are merely preferred embodiments of the present invention. However, the embodiments of the present invention are not limited thereto, and any variations that can be conceived by those skilled in the art should fall within the protection scope of the present invention.

Claims

1. A modular structure for controlling the angle of an oblique shock wave, used as a wedge surface to induce the formation of an oblique shock wave on one side of the combustion chamber outlet end (2), characterized in that, include: Multiple plates (3) are stacked vertically. Each plate (3) has a first surface (31), a second surface (32), a third surface (33), and a fourth surface (34). The first surface (31) is parallel to the length of the combustion chamber. The second surface (32) is located on the side of the first surface (31) near the inlet end (1) of the combustion chamber. An angle is formed between the second surface (32) and the first surface (31). θ The included angle θ The angle is acute. The third surface (33) is located on the side of the first surface (31) near the combustion chamber outlet end (2). The fourth surface (34) is parallel to the first surface (31), and the two ends of the fourth surface (34) are connected to the second surface (32) and the third surface (33) respectively. The connection between the second surface (32) and the fourth surface (34) forms an inflection point (35). The line connecting the inflection points (35) in each plate (3) forms a wedge surface. There are multiple linear moving mechanisms (4), and the number is the same as the number of the multiple plates (3). The linear moving mechanism (4) has a moving end that moves along the length of the combustion chamber. The moving ends of the multiple linear moving mechanisms (4) are connected to the third surface (33) of the multiple plates (3) respectively. The angle of the wedge surface is adjusted by driving each plate (3) to move in a staggered direction closer to the combustion chamber outlet end (2) through the multiple linear moving mechanisms (4).

2. The metastructure for controlling the angle of the oblique shock wave according to claim 1, characterized in that, The slope of the line connecting the inflection points (35) of two adjacent plates (3) after misalignment is less than or equal to the slope of the second surface (32).

3. The metastructure for controlling the angle of the oblique shock wave according to claim 1, characterized in that, The included angle θ The degree range is 10° to 45°.

4. The metastructure for controlling the angle of the oblique shock wave according to claim 3, characterized in that, The included angle θ The degree is 30°.

5. The metastructure for controlling the angle of the oblique shock wave according to claim 1, characterized in that, The linear motion mechanism can be either a lead screw linear motion module or a hydraulic cylinder.

6. The metastructure for controlling the angle of the oblique shock wave according to claim 1, characterized in that, The plate (3) is made of high-temperature resistant alloy or ceramic matrix composite material.

7. The metastructure for controlling the angle of the oblique shock wave according to claim 1, characterized in that, The height of the third surface (33) is 2mm~5mm.

8. A detonation engine, comprising a combustion chamber, and further comprising a substructure for controlling the angle of the detonation shock wave as described in any one of claims 1 to 7, characterized in that, The lower wall of the outlet end (2) of the combustion chamber is provided with an installation port (5), and multiple plates (3) stacked on top of each other are arranged in the installation port (5). Each linear movement mechanism (4) is installed on the body of the inclined detonation engine.

Images