Oblique detonation ramjet acceleration device with adjustable wave system structure and application method

Abstract

The present invention discloses an oblique detonation ramjet acceleration device with a controllable wave system structure and an application method. The oblique detonation ramjet acceleration device with a controllable wave system structure includes: an accelerator, a pressure relief pipe, and an acceleration pipe, which are arranged and connected in sequence from left to right. The accelerator includes an outlet. One end of the pressure relief pipe is communicated with the outlet, and the other end is communicated with the acceleration pipe. A spiral coil is sleeved outside the acceleration pipe. There is a gap between the spiral coil and the acceleration pipe, and a wire is provided. The wire is insulated from the spiral coil, and both the wire and the spiral coil are connected to a power supply. The projectile is shot into the acceleration pipe at a high speed through the accelerator. The high-intensity oblique shock wave generated in the head region of the projectile compresses the air, causing the air molecules to form a conductive plasma gas. The spiral coil and the wire are energized to generate a magnetic field, and the magnetic field exerts a Lorentz force on the plasma gas, causing the plasma gas to move, thereby changing the position of the wave surface and realizing the regulation of the wave system structure.

Description

Technical Field

[0001] The present invention relates to the technical field of detonation engines, and more specifically, to an oblique detonation ramjet acceleration device with adjustable wave system structure and an application method thereof. Background Art

[0002] Detonation propulsion has the characteristics of fast heat release rate, self-boost pressure, and self-ignition. Its combustion process can be approximated as isobaric combustion. The thermodynamic cycle based on detonation combustion can improve the efficiency by about 50% compared with the traditional Brayton thermodynamic cycle. The ram accelerator is the most mature detonation propulsion system at present. There are two typical working modes of the ram accelerator. When the speed of the projectile is lower than the ideal characteristic detonation velocity of the premixed gas, it is the subsonic combustion mode. When the speed of the projectile is greater than the ideal characteristic detonation velocity of the premixed gas, it is the oblique detonation mode. Theoretically, the ram accelerator can accelerate the projectile to 8 km / s in the oblique detonation mode.

[0003] However, the existing ram accelerators have the following disadvantages: 1. The internal flow field structure of the ram accelerator is very complex and has the characteristics of high transience, resulting in severe oscillation of the thrust of the ram accelerator; 2. The non-starting state of the ram accelerator refers to the phenomenon that a supersonic flow field cannot be established in front of the projectile throat, and the detonation wave system propagates forward, resulting in a sharp decline in the thrust performance of the projectile. Since the ram accelerator is filled with high-energy and high-pressure combustible premixed gas, a huge amount of heat will be generated during the operation of the ram accelerator. When the heat release is too high, the detonation wave system will move to the front end of the projectile, causing the ram accelerator to enter the non-starting state; 3. Both the gun barrel and the projectile in the ram accelerator are geometrically invariable, and the combustible gas is pre-filled into the pipeline in a certain proportion. Therefore, during the operation of the ram accelerator, the wave system structure is difficult to adjust in a timely manner, resulting in its thrust performance being difficult to reach the optimal state.

[0004] Therefore, there is an urgent need to provide an oblique detonation wave ramjet acceleration device that can adjust the wave system structure during operation. Summary of the Invention

[0005] In view of this, the present invention provides an oblique detonation ramjet acceleration device with adjustable wave system structure and an application method thereof.

[0006] On the one hand, the present invention provides an oblique detonation ramjet acceleration device with adjustable wave system structure, including an accelerator, a pressure relief pipe, and an acceleration pipe connected in sequence.

[0007] The accelerator, the pressure relief pipe, and the acceleration pipe are arranged and connected in sequence from left to right:

[0008] The accelerator includes an outlet;

[0009] One end of the pressure relief pipe is communicated with the outlet, and the other end is communicated with the acceleration pipe;

[0010] One end of the acceleration tube is communicated with the pressure relief tube;

[0011] A spiral coil is sleeved outside the acceleration tube and has the same length as the acceleration tube. There is a gap between the spiral coil and the acceleration tube, and a wire is provided. The wire is insulated from the spiral coil, and both the wire and the spiral coil are connected to a power source;

[0012] Fill the acceleration tube with a combustible premixed gas, and project a projectile from the outlet. After the projectile enters the acceleration tube, a reflected shock wave, a detonation wave, an expansion wave, and an oblique shock wave are sequentially formed on the surface of the projectile from the left. The oblique shock wave compresses and ionizes the combustible premixed gas into a plasma gas;

[0013] At the same time, in the energized state of the spiral coil and the wire, the spiral coil applies a first Lorentz force to the plasma gas in the energized state, and the wire applies a second Lorentz force to the plasma gas in the energized state. The resultant force of the first Lorentz force and the second Lorentz force adjusts the movement direction of the plasma gas to control the position of the detonation wave.

[0014] Preferably, it further includes:

[0015] A sleeve is sleeved outside the acceleration tube. The inner wall of the sleeve is fixedly connected to the acceleration tube. The sleeve further includes a hollowed-out area. The extending direction of the hollowed-out area is parallel to the extending direction of the acceleration tube. The sleeve is made of an insulating material;

[0016] The wire is located in the hollowed-out area, and the spiral coil is sleeved outside the sleeve.

[0017] Preferably, a protrusion is provided on the outer wall of the sleeve, and a fixing groove is provided on the protrusion. One end of the spiral coil is engaged with the fixing groove.

[0018] Preferably, the number of the wires is at least two, and adjacent wires are insulated from each other.

[0019] Preferably, the projectile is spindle-shaped.

[0020] Preferably, the ejection speed of the projectile is greater than the ideal detonation velocity of the combustible premixed gas.

[0021] On the other hand, the present invention also provides an application method of an oblique detonation ramjet acceleration device with a controllable wave system structure, which is applied to the oblique detonation ramjet acceleration device with a controllable wave system structure described in any one of the above, including:

[0022] Fill the acceleration tube with a combustible premixed gas. The projectile is ejected from the outlet. After the projectile enters the acceleration tube, a reflected shock wave, a detonation wave, an expansion wave, and an oblique shock wave are sequentially formed on the surface of the projectile from the left.

[0023] Control the current direction and magnitude of the helical coil, and at the same time control the current direction and magnitude of the wire to adjust the position of the detonation wave.

[0024] Preferably, one side of the projectile away from the accelerator is a first wedge surface. The oblique shock wave corresponds to the position of the first wedge surface. The oblique shock wave compresses the combustible premixed gas in the acceleration tube and ionizes the combustible premixed gas into a plasma gas.

[0025] Preferably, controlling the current direction and magnitude of the helical coil and at the same time controlling the current direction and magnitude of the wire to adjust the position of the detonation wave includes:

[0026] The magnetic field generated by the helical coil in the energized state exerts a first Lorentz force on the plasma gas, and the magnetic field generated by the wire in the energized state exerts a second Lorentz force on the plasma gas. The resultant force of the first Lorentz force and the second Lorentz force adjusts the movement direction of the plasma gas to control the position of the detonation wave.

[0027] Compared with the prior art, the oblique detonation ramjet acceleration device with a controllable wave system structure provided by the present invention has at least achieved the following beneficial effects:

[0028] The oblique detonation ramjet acceleration device with adjustable wave structure provided by the present invention comprises an accelerator, a pressure relief tube and an acceleration tube, which are arranged and connected in sequence from the left: the accelerator comprises an outlet; one end of the pressure relief tube is connected to the outlet, and the other end is connected to the acceleration tube; one end of the acceleration tube is connected to the pressure relief tube; a spiral coil is sleeved outside the acceleration tube and is of the same length as the acceleration tube, a spacing is provided between the spiral coil and the acceleration tube, and a wire is provided, the wire and the spiral coil are insulated, and the wire and the spiral coil are both connected to a power supply; the acceleration tube is filled with combustible premixed gas, and a projectile is ejected from the outlet. After the projectile enters the acceleration tube, a reflected shock wave, a detonation wave, an expansion wave and an oblique shock wave are formed in sequence on the surface of the projectile from the left, and the oblique shock wave compresses and ionizes the combustible premixed gas into plasma gas; at the same time, when the spiral coil and the wire are energized, In the state, the spiral coil applies a first Lorentz force to the plasma gas when it is energized, and the wire applies a second Lorentz force to the plasma gas when it is energized. The combined force of the first Lorentz force and the second Lorentz force adjusts the movement direction of the plasma gas to control the position of the detonation wave. The projectile is accelerated to supersonic speed by an accelerator and then shot into an accelerating tube filled with combustible premixed gas. When the projectile moves at high speed, a high-intensity oblique shock wave is generated in the head area of ​​the projectile. The oblique shock wave compresses the air, causing the air molecules to dissociate and ionize to form a conductive plasma gas. The spiral coil and the wire are energized to generate a magnetic field. The plasma gas flows in the magnetic field to generate an induced current. The magnetic field has a Lorentz force on the induced current, that is, the Lorentz force is applied to the plasma gas. The plasma gas is moved by the Lorentz force, thereby changing the position of the wave surface, thereby realizing the regulation of the wave system structure.

[0029] Of course, any product implementing the present invention does not necessarily need to achieve all of the above technical effects at the same time.

[0030] Further features and advantages of the present invention will become apparent from the following detailed description of exemplary embodiments of the present invention with reference to the attached drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] The accompanying drawings, which are incorporated in and constitute a part of the specification, illustrate embodiments of the invention and, together with the description, serve to explain the principles of the invention.

[0032] Figure 1 It is a structural schematic diagram of an oblique detonation ramjet acceleration device with an adjustable wave system structure provided by the present invention;

[0033] Figure 2 It is another structural schematic diagram of the oblique detonation ramjet accelerator with adjustable wave system structure provided by the present invention;

[0034] Figure 3 yes Figure 2 A-A' section view;

[0035] Figure 4 It is a schematic diagram of a wave system structure;

[0036] Figure 5 It is a schematic diagram of the structure of an acceleration tube, a wire, and a helical coil. Detailed implementation manners

[0037] Various exemplary embodiments of the present invention will now be described in detail with reference to the accompanying drawings. It should be noted that: unless otherwise specifically stated, the relative arrangements of components and steps, numerical expressions, and numerical values set forth in these embodiments do not limit the scope of the present invention.

[0038] The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way a limitation on the present invention or its application or use.

[0039] Technologies, methods, and devices known to those of ordinary skill in the relevant art may not be discussed in detail, but where appropriate, the technologies, methods, and devices should be regarded as part of the specification.

[0040] In all the examples shown and discussed herein, any specific values should be construed as merely exemplary and not as a limitation. Thus, other examples of the exemplary embodiments may have different values.

[0041] It should be noted that: like reference numerals and letters denote like items in the following drawings, and thus, once an item is defined in one drawing, further discussion thereof in subsequent drawings is not required.

[0042] Referring to Figure 1 , Figure 1 is a schematic diagram of a structure of an oblique detonation ramjet acceleration device with a controllable wave system structure provided by the present invention, to illustrate a specific embodiment of the oblique detonation ramjet acceleration device 100 with a controllable wave system structure provided in this embodiment, including an accelerator 1, a pressure relief pipe 7, and an acceleration tube 4.

[0043] The accelerator 1, the pressure relief pipe 7, and the acceleration tube 4 are arranged and connected in sequence from left to right:

[0044] The accelerator 1 includes an outlet 2;

[0045] One end of the pressure relief pipe is communicated with the outlet 2, and the other end is communicated with the acceleration tube 4;

[0046] One end of the acceleration tube 4 is communicated with the pressure relief pipe 7;

[0047] A helical coil 5 is sleeved outside the acceleration tube 4 and has the same length as the acceleration tube 4. There is a gap between the helical coil 5 and the acceleration tube 4, and a wire 6 is provided. The wire 6 is insulated from the helical coil 5, and both the wire 6 and the helical coil 5 are connected to a power supply (not shown in the figure).

[0048] The acceleration tube 4 is filled with a combustible premixed gas. A projectile 3 is emitted from the outlet 2. After the projectile 3 enters the acceleration tube 4, a reflected shock wave, a detonation wave, an expansion wave, and an oblique shock wave are sequentially formed on the surface of the projectile 3 from the left. The oblique shock wave compresses and ionizes the combustible premixed gas into a plasma gas.

[0049] At the same time, in the energized state of the helical coil 5 and the wire 6, the helical coil 5 exerts a first Lorentz force on the plasma gas in the energized state, and the wire 6 exerts a second Lorentz force on the plasma gas in the energized state. The resultant force of the first Lorentz force and the second Lorentz force adjusts the movement direction of the plasma gas to control the position of the detonation wave.

[0050] It should be noted that the accelerator 1 is a general term for devices that can provide an initial velocity to the projectile 3. The accelerator 1 in this embodiment can be any acceleration device that can make the ejection velocity of the projectile 3 reach supersonic speed, and this embodiment does not make specific limitations on this. When the projectile 3 enters the acceleration tube 4 filled with a combustible premixed gas at supersonic speed, an oblique shock wave is generated in the head region of the projectile 3, that is, an oblique shock wave is generated in the region of the projectile 3 away from the accelerator 1. The gas behind the projectile 3, that is, the gas on the side of the projectile 3 close to the accelerator 1, is heated and ignited by the oblique shock wave, generating a high pressure at the rear of the projectile 3 to provide thrust for the projectile 3, and continuously accelerating in the direction away from the accelerator 1. The longer the length of the acceleration tube 4, the longer the acceleration distance of the projectile 3, and the greater the velocity increment of the projectile 3. However, when the velocity of the projectile 3 is too high, the velocity increment of the projectile 3 will gradually decrease. Therefore, the length of the acceleration tube 4 can be reasonably selected according to actual needs, and this embodiment does not make limitations on this. There is a gap between the helical coil 5 and the acceleration tube 4, and a gap between the wire 6 and the acceleration tube 4, which can prevent the heat generated when the helical coil 5 and the wire 6 are energized from being transferred to the acceleration tube 4 and affecting the flow field in the acceleration tube 4. The wire 6 is insulated from the helical coil 5, which can prevent the wire 6 from overlapping with the helical coil 5 and causing a short circuit. The helical coil 5 has the same length as the acceleration tube 4, which can ensure that the magnetic field generated when the helical coil 5 is energized can fully act on any plasma gas in the acceleration tube 4. The velocity of the projectile 3 increases from 0 to supersonic speed in the accelerator 1 and then is ejected. When ejected, it carries the combustible gas in the accelerator 1. The function of the pressure relief pipe 7 is to discharge this part of the gas to prevent the projectile 3 from carrying the combustible gas into the acceleration tube 4 and affecting the ram acceleration effect of the projectile 3. The principle of the pressure relief pipe 7 is similar to that of an internal relief valve. The high-pressure combustible gas carried by the projectile 3 is discharged to the low-pressure environment outside the pressure relief pipe 7 through the pressure difference. The present invention does not improve the structure of the pressure relief pipe 7, and the existing pressure relief pipe 7 can be used.

[0051] It can be understood that when the projectile 3 moves in the acceleration tube 4, the strong compression effect of the oblique shock wave generated in the head region of the projectile 3 converts the macroscopic function into the internal energy of compressed air, and then stimulates the vibration energy of air molecules, causing the air molecules to dissociate and ionize to form a conductive plasma gas; when the oblique shock wave heats and ignites the gas behind the projectile 3, expansion waves, detonation waves, and reflected shock waves will be generated near the projectile 3. Among them, the detonation wave needs to be located at the rear of the projectile 3, and the detonation wave will generate continuous thrust when it expands at the rear of the projectile 3. When the spiral coil 5 and the wire 6 are energized to generate a magnetic field, the flowing plasma gas will generate an induced current in the magnetic field, and the magnetic field has a Lorentz force on the induced current, that is, a Lorentz force is applied to the plasma gas. The magnetic field generated by the energization of the spiral coil 5 applies a first Lorentz force to the plasma gas, and the magnetic field generated by the energization of the wire 6 applies a second Lorentz force to the plasma gas. The movement direction of the plasma gas depends on the resultant force direction of the Lorentz force it receives. The movement of the plasma gas will affect the position of the detonation wave near the projectile 3. Therefore, the current direction and magnitude applied to the spiral coil 5 and the wire 6 can be adjusted to adjust the magnetic field around the acceleration tube 4, thereby adjusting the force direction of the plasma gas, and then changing the position of the detonation wave to achieve the regulation of the wave system structure. By adjusting the force direction of the plasma gas through the resultant force direction, more flexible regulation can be achieved, enabling the oblique detonation ramjet acceleration device 100 with an adjustable wave system structure provided in this embodiment to reach a more ideal state. In this embodiment, the plasma gas is only affected by the first Lorentz force and the second Lorentz force. Of course, this is not limited thereto.

[0052] Compared with the prior art, the oblique detonation ramjet acceleration device 100 with an adjustable wave system structure provided by the present invention has at least the following advantages:

[0053] The oblique detonation ramjet acceleration device 100 of the adjustable wave system structure provided by the present invention comprises an accelerator 1, a pressure relief pipe 7 and an accelerating tube 4, which are arranged and connected in sequence from the left: the accelerator 1 comprises an outlet 2; one end of the pressure relief pipe is connected to the outlet 2, and the other end is connected to the accelerating tube 4; one end of the accelerating tube 4 is connected to the pressure relief pipe 7; a spiral coil 5 is sleeved outside the accelerating tube 4 and is of the same length as the accelerating tube 4, there is a gap between the spiral coil 5 and the accelerating tube 4, and a wire 6 is provided, the wire 6 and the spiral coil 5 are insulated, and the wire 6 and the spiral coil 5 are both connected to a power supply; the accelerating tube 4 is filled with combustible premixed gas, the outlet 2 shoots out a projectile 3, and after the projectile 3 enters the accelerating tube 4, a reflected shock wave, a detonation wave, an expansion wave and an oblique shock wave are formed in sequence on the surface of the projectile 3 from the left, and the oblique shock wave compresses the combustible premixed gas into plasma gas; at the same time, in the spiral coil When the spiral coil 5 and the wire 6 are powered on, the spiral coil 5 applies a first Lorentz force to the plasma gas, and the wire 6 applies a second Lorentz force to the plasma gas. The combined force of the first Lorentz force and the second Lorentz force adjusts the movement direction of the plasma gas to control the position of the detonation wave. The projectile 3 is accelerated to supersonic speed by the accelerator 1 and then shot into the acceleration tube 4 filled with combustible premixed gas. When the projectile 3 moves at high speed, a high-intensity oblique shock wave is generated in the head area of ​​the projectile 3. The oblique shock wave compresses the air, causing the air molecules to dissociate and ionize to form a conductive plasma gas. When the spiral coil 5 and the wire 6 are powered on, a magnetic field is generated. When the plasma gas flows in the magnetic field, an induced current is generated. The magnetic field has a Lorentz force on the induced current, that is, a Lorentz force is applied to the plasma gas. The plasma gas is moved by the Lorentz force, thereby changing the position of the wave surface, thereby realizing the regulation of the wave system structure.

[0054] In some optional embodiments, referring to Figure 2 and Figure 3 , Figure 2 This is another structural schematic diagram of the oblique detonation ramjet accelerator with adjustable wave system structure provided by the present invention. Figure 3 yes Figure 2 In the cross-sectional view along the A-A' direction, the oblique detonation ramjet acceleration device 100 with an adjustable wave system structure provided in this embodiment further includes:

[0055] The sleeve 8 is sleeved outside the accelerating tube 4. The inner wall of the sleeve 8 is fixedly connected to the accelerating tube 4. The sleeve 8 also includes a hollow area 9. The extension direction of the hollow area 9 is parallel to the extension direction of the accelerating tube 4. The sleeve 8 is made of insulating material.

[0056] The conductive wire 6 is located in the hollow area 9 , and the spiral coil 5 is sleeved outside the sleeve 8 .

[0057] It can be understood that the wire 6 is located between the spiral coil 5 and the acceleration tube 4, and there is a gap between the wire 6 and the spiral coil 5, and there is also a gap between the wire 6 and the acceleration tube 4. A sleeve 8 is provided to fix the position of the wire 6, so as to ensure the relative position stability of the wire 6 and the acceleration tube 4, and avoid the deformation of the wire 6 due to the action of gravity, thereby avoiding the change of the position of the magnetic field formed after the wire 6 is energized.

[0058] In some alternative embodiments, with continued reference to Figure 2 and Figure 3 , a protrusion 10 is provided on the outer wall of the sleeve 8, and a fixing groove 11 is provided on the protrusion 10. One end of the spiral coil 5 is engaged with the fixing groove 11.

[0059] It can be understood that the spiral coil 5 is sleeved outside the sleeve 8, and one end is engaged with the fixing groove 11, which can fix the position of the spiral coil 5.

[0060] In some alternative embodiments, with continued reference to Figure 2 and Figure 3 , the number of the wires 6 is at least two, and the adjacent wires 6 are insulated from each other.

[0061] It can be understood that the plasma gas in the acceleration tube 4 is subjected to the first Lorentz force exerted by the magnetic field formed by the energization of the spiral coil 5, and is also subjected to the second Lorentz force exerted by the magnetic field formed by the energization of the wire 6. The number of the wires 6 is at least two, that is, the plasma gas is subjected to the action of at least two second Lorentz forces. The resultant force of the first Lorentz force and at least two Lorentz forces affects the movement direction of the plasma gas. The increase in the number of the second Lorentz forces helps to regulate the direction of the resultant force. Of course, the number of the wires 6 can be set according to the actual situation, and this embodiment does not make specific limitations on this.

[0062] In some alternative embodiments, with reference to Figure 1 and Figure 4 , Figure 4 is a schematic diagram of a wave system structure, and the projectile 3 is spindle-shaped.

[0063] It can be understood that in the direction from the accelerator 1 to the acceleration tube 4, the spindle-shaped projectile 3 includes a first wedge surface 12 and a second wedge surface 13 which are oppositely arranged. The first wedge surface 12 is located on the side of the second wedge surface 13 away from the accelerator 1. The pointed first wedge surface 12 is used to induce an oblique shock wave to compress and ignite the combustible premixed gas, and the pointed second wedge surface 13 forms an expansion section between the rear part of the projectile 3 and the tube wall of the acceleration tube 4, so that the combusted combustible premixed gas can fully expand to generate thrust to push the projectile 3 to accelerate.

[0064] In some alternative embodiments, the exit velocity of the projectile 3 is greater than the ideal characteristic detonation velocity of the combustible premixed gas.

[0065] It is understandable that the combustion process of the combustible premixed gas is the propagation process of the detonation wave along the combustible premixed gas. After the detonation wave is excited, its propagation speed will quickly tend to a specific value of the combustible premixed gas, that is, reach the ideal characteristic detonation speed (CJ speed). Under normal circumstances, the detonation wave will propagate stably at the ideal characteristic detonation speed. Only the projectile 3 with an exit speed greater than the ideal characteristic detonation speed of the combustible premixed gas can induce an oblique shock wave. The high-intensity oblique shock wave is a necessary condition for inducing the combustion of the combustible premixed gas. In this embodiment, the exit speed of the projectile 3 is greater than 1200 m / s, and the Mach number is greater than 3.5. The moving speed range of the projectile 3 in the acceleration tube 4 is 1200 m / s - 8000 m / s, and the Mach number range is 3.5 - 23.5. Of course, it is not limited to this.

[0066] In some alternative embodiments, with continued reference to Figure 1 and Figure 4 , a specific embodiment of the application method of the oblique detonation ramjet acceleration device with a controllable wave system structure provided by the present invention is described, including:

[0067] Fill the acceleration tube 4 with the combustible premixed gas, and the projectile 3 exits from the outlet 2. After the projectile 3 enters the acceleration tube 4, a reflected shock wave 17, a detonation wave 16, an expansion wave 15, and an oblique shock wave 14 are sequentially formed on the surface of the projectile 3 from the left.

[0068] Control the current direction and magnitude of the spiral coil 5, and at the same time control the current direction and magnitude of the wire 6 to adjust the position of the detonation wave 16.

[0069] It is understandable that, with reference to Figure 4 , a recirculation zone 18 is formed between the reflected shock wave 17 and the detonation wave 16. The oblique shock wave 14 is located at the corresponding position of the first wedge surface 12 to compress the air. The position of the detonation wave 16 needs to be located behind the projectile 3, that is, at the corresponding position of the second wedge surface 13, so that the detonation wave 16 can expand behind the projectile 3 to generate continuous thrust. By adjusting the current direction and magnitude applied to the spiral coil 5 and the wire 6, the magnetic field around the acceleration tube 4 is adjusted. The force direction of the plasma gas in the acceleration tube 4 is affected by the magnetic field, so that the movement direction of the plasma gas changes, and then the position of the detonation wave 16 is adjusted to realize the regulation of the wave system structure.

[0070] In some alternative embodiments, with continued reference to Figure 1 and Figure 4 , one side of the projectile 3 away from the accelerator 1 is the first wedge surface 12. The oblique shock wave 14 corresponds to the position of the first wedge surface 12. The oblique shock wave 14 compresses the combustible premixed gas in the acceleration tube 4 and ionizes the combustible premixed gas into plasma gas.

[0071] It can be understood that when the projectile 3 moves in the acceleration tube 4, the first wedge surface 12 will generate an oblique shock wave 14. The strong compression effect of the oblique shock wave 14 converts the macroscopic function into the internal energy of compressed air, and then stimulates the vibration energy of air molecules, causing the air molecules to dissociate and ionize to form a conductive plasma gas. The plasma gas will be affected by the Lorentz force in the magnetic field. Therefore, by controlling the current direction and magnitude of the current applied to the spiral coil 5 and the wire 6, the magnetic field generated by the energization of the spiral coil 5 and the wire 6 can be controlled, thereby controlling the movement direction of the plasma gas, and thus adjusting the wave system structure in the acceleration tube 4.

[0072] In some alternative embodiments, referring to Figure 4 and Figure 5 , Figure 5 is a schematic structural diagram of an acceleration tube, a wire, and a spiral coil. By controlling the current direction and magnitude of the spiral coil 5 and simultaneously controlling the current direction and magnitude of the wire 6, the position of the detonation wave 16 is adjusted, including:

[0073] The magnetic field generated by the spiral coil 5 in the energized state exerts a first Lorentz force on the plasma gas, and the magnetic field generated by the wire 6 in the energized state exerts a second Lorentz force on the plasma gas. The resultant force of the first Lorentz force and the second Lorentz force adjusts the movement direction of the plasma gas to control the position of the detonation wave 16.

[0074] It can be understood that in Figure 5 multiple wires 6 are schematically shown. In this embodiment, only two wires 6 are energized as an example to illustrate another specific embodiment of the application method of the oblique detonation ramjet acceleration device 100 with a controllable wave system structure provided by the present invention. In Figure 5It is shown in the figure that the current direction of the energized spiral coil 5 is I1, and the generated magnetic field direction is H1; the current direction of the energized first wire 6.1 is I2.1, and the generated magnetic field direction is H2.1; the current direction of the energized first wire 6.2 is I2.2, and the generated magnetic field direction is H2.2. For any point P in space, when the oblique detonation ramjet acceleration device 100 with an adjustable wave system structure enters the oblique detonation mode, the gas molecules at point P will dissociate into charged plasma gas due to high temperature and high pressure and generate motion. The magnetic induction intensity at point P due to the energized spiral coil 5 is B1, the magnetic induction intensity at point P due to the energized first wire 6.1 is B2.1, and the magnetic induction intensity at point P due to the energized second wire 6.2 is B2.2. These three magnetic induction intensities are linearly independent. The plasma gas at point P will be subjected to the first Lorentz force exerted by the magnetic field generated by the energized spiral coil 5, and the plasma gas at point P will also be subjected to the second Lorentz force exerted by the magnetic field generated by the energized wire 6. The plasma gas at point P is subjected to the action of three linearly independent Lorentz forces, and the magnitude and direction of their resultant force can be controlled by the intensity and direction of the current in the spiral coil 5 and the wire 6. The backward movement of the plasma gas can move the position of the detonation wave 16 backward, so that the detonation wave 16 is located at the second wedge surface 13 of the projectile 3, realizing stable expansion. By applying the method of the oblique detonation ramjet acceleration device 100 with an adjustable wave system structure provided by the present invention, the oscillation range of the thrust of the oblique detonation ramjet acceleration device 100 with an adjustable wave system structure provided by the present invention can be effectively reduced, the situation that the oblique detonation ramjet acceleration device 100 with an adjustable wave system structure provided by the present invention enters a non-starting state can be avoided, and the overall performance is improved.

[0075] As can be seen from the above embodiments, the oblique detonation ramjet acceleration device with an adjustable wave system structure provided by the present invention has at least achieved the following beneficial effects:

[0076] The oblique detonation ramjet acceleration device with adjustable wave structure provided by the present invention comprises an accelerator, a pressure relief tube and an acceleration tube, which are arranged and connected in sequence from the left: the accelerator comprises an outlet; one end of the pressure relief tube is connected to the outlet, and the other end is connected to the acceleration tube; one end of the acceleration tube is connected to the pressure relief tube; a spiral coil is sleeved outside the acceleration tube and is of the same length as the acceleration tube, a spacing is provided between the spiral coil and the acceleration tube, and a wire is provided, the wire and the spiral coil are insulated, and the wire and the spiral coil are both connected to a power supply; the acceleration tube is filled with combustible premixed gas, and a projectile is ejected from the outlet. After the projectile enters the acceleration tube, a reflected shock wave, a detonation wave, an expansion wave and an oblique shock wave are formed in sequence on the surface of the projectile from the left, and the oblique shock wave compresses and ionizes the combustible premixed gas into plasma gas; at the same time, when the spiral coil and the wire are energized, In the state, the spiral coil applies a first Lorentz force to the plasma gas when it is energized, and the wire applies a second Lorentz force to the plasma gas when it is energized. The combined force of the first Lorentz force and the second Lorentz force adjusts the movement direction of the plasma gas to control the position of the detonation wave. The projectile is accelerated to supersonic speed by an accelerator and then shot into an accelerating tube filled with combustible premixed gas. When the projectile moves at high speed, a high-intensity oblique shock wave is generated in the head area of ​​the projectile. The oblique shock wave compresses the air, causing the air molecules to dissociate and ionize to form a conductive plasma gas. The spiral coil and the wire are energized to generate a magnetic field. The plasma gas flows in the magnetic field to generate an induced current. The magnetic field has a Lorentz force on the induced current, that is, the Lorentz force is applied to the plasma gas. The plasma gas is moved by the Lorentz force, thereby changing the position of the wave surface, thereby realizing the regulation of the wave system structure.

[0077] Although some specific embodiments of the present invention have been described in detail by way of example, it will be appreciated by those skilled in the art that the above examples are for illustration only and are not intended to limit the scope of the present invention. It will be appreciated by those skilled in the art that the above embodiments may be modified without departing from the scope and spirit of the present invention. The scope of the present invention is defined by the appended claims.

Claims

1. An oblique detonation ramjet acceleration device with an adjustable wave system structure, characterized in that, it includes: an accelerator, a pressure relief pipe, and an acceleration pipe, the accelerator, the pressure relief pipe, and the acceleration pipe are arranged and connected in sequence from the left: the accelerator includes an outlet; one end of the pressure relief pipe is communicated with the outlet, and the other end is communicated with the acceleration pipe; one end of the acceleration pipe is communicated with the pressure relief pipe; a spiral coil is sleeved outside the acceleration pipe and is of the same length as the acceleration pipe. There is a gap between the spiral coil and the acceleration pipe, and a wire is provided. The wire is insulated from the spiral coil, and both the wire and the spiral coil are connected to a power supply; fill the acceleration pipe with a combustible premixed gas, and the outlet ejects a projectile. After the projectile enters the acceleration pipe, a reflected shock wave, a detonation wave, an expansion wave, and an oblique shock wave are sequentially formed on the surface of the projectile from the left. The oblique shock wave compresses and ionizes the combustible premixed gas into a plasma gas; meanwhile, in the energized state of the spiral coil and the wire, the spiral coil exerts a first Lorentz force on the plasma gas in the energized state, and the wire exerts a second Lorentz force on the plasma gas in the energized state. The resultant force of the first Lorentz force and the second Lorentz force adjusts the movement direction of the plasma gas to control the position of the detonation wave.

2. The oblique detonation ramjet acceleration device with an adjustable wave system structure according to claim 1, characterized in that, it further includes: a sleeve body sleeved outside the acceleration pipe. The inner wall of the sleeve body is fixedly connected to the acceleration pipe. The sleeve body further includes a hollowed-out area. The extending direction of the hollowed-out area is parallel to the extending direction of the acceleration pipe. The sleeve body is made of an insulating material; the wire is located in the hollowed-out area, and the spiral coil is sleeved outside the sleeve body.

3. The oblique detonation ramjet acceleration device with an adjustable wave system structure according to claim 2, characterized in that, a protrusion is provided on the outer wall of the sleeve body, and a fixing groove is provided on the protrusion. One end of the spiral coil is engaged with the fixing groove.

4. The oblique detonation ramjet acceleration device with an adjustable wave system structure according to claim 1, characterized in that, the number of the wires is at least two, and adjacent wires are insulated from each other.

5. The oblique detonation ramjet acceleration device with an adjustable wave system structure according to claim 1, characterized in that, the projectile is spindle-shaped.

6. The oblique detonation ramjet acceleration device with an adjustable wave system structure according to claim 1, characterized in that, the ejection speed of the projectile is greater than the ideal characteristic detonation speed of the combustible premixed gas.

7. An application method of an oblique detonation ramjet acceleration device with an adjustable wave system structure, characterized in that, it is applied to the oblique detonation ramjet acceleration device with an adjustable wave system structure according to any one of claims 1-6, and includes: fill the acceleration pipe with a combustible premixed gas, and the outlet ejects the projectile. After the projectile enters the acceleration pipe, a reflected shock wave, a detonation wave, an expansion wave, and an oblique shock wave are sequentially formed on the surface of the projectile from the left; Control the current direction and magnitude of the spiral coil, and at the same time control the current direction and magnitude of the wire to adjust the position of the detonation wave.

8. The application method of the oblique detonation ramjet acceleration device with an adjustable wave system structure according to claim 7, characterized in that, One side of the projectile away from the accelerator is a first wedge surface, the oblique shock wave corresponds to the position of the first wedge surface, and the oblique shock wave compresses the combustible premixed gas in the acceleration tube to ionize the combustible premixed gas into plasma gas.

9. The application method of the oblique detonation ramjet acceleration device with an adjustable wave system structure according to claim 8, characterized in that, The control of the current direction and magnitude of the spiral coil, and at the same time the control of the current direction and magnitude of the wire to adjust the position of the detonation wave includes: The magnetic field generated by the spiral coil in the energized state exerts a first Lorentz force on the plasma gas, the magnetic field generated by the wire in the energized state exerts a second Lorentz force on the plasma gas, and the resultant force of the first Lorentz force and the second Lorentz force adjusts the movement direction of the plasma gas to control the position of the detonation wave.

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