A bird strike test launching device based on multi-stage coil electromagnetic emission.

Abstract

This invention relates to the field of bird strike testing technology for aero-engines, and discloses a bird strike test launching device based on multi-stage coil electromagnetic launch. The device employs a cartridge case comprising a segmented inner cartridge case and a magnetically induction outer cartridge case. Under the electromagnetic force of the multi-stage coil, the magnetically induction outer cartridge case drives the segmented inner cartridge case and the bird body to accelerate within the barrel. A discarding mechanism then blocks the magnetically induction outer cartridge case within the barrel, achieving separation between the magnetically induction outer cartridge case and the segmented inner cartridge case. This improves the service life of the magnetically induction outer cartridge case and facilitates its reuse. Furthermore, the invention utilizes the cutting blade of the discarding mechanism to force the segmented inner cartridge case to disintegrate and separate from the bird body, achieving smooth and efficient separation between the segmented inner cartridge case and the bird body, ensuring the bird maintains a stable flight state after launch.

Description

Technical Field

[0001] This invention relates to the field of bird strike testing technology for aero-engines, and discloses a bird strike testing launching device based on multi-stage coil electromagnetic launching. Background Technology

[0002] During the development of aero-engines, a series of tests are required to verify their airworthiness. Among these tests, bird strike tests aim to verify the engine's tolerance to bird strikes. To improve development efficiency and systematically understand damage patterns, bird strike resistance tests on key components such as the fan are usually conducted before the overall aircraft bird strike test.

[0003] Component-level bird strike tests commonly use simulated bird projectiles instead of real birds. A simulated bird projectile is a projectile structure specifically designed for impact test components. It is installed inside a sabot and accelerated by a compressed air cannon. When the sabot carrying the bird projectile moves to the muzzle ejector, the ejector stops the sabot, while the simulated bird projectile continues to fly at high speed due to inertia, achieving separation and ultimately impacting the rotating components of the engine.

[0004] Multi-stage electromagnetic coil launching systems are a novel type of launching device that converts electromagnetic energy into kinetic energy. They offer significant advantages such as high launch speed, large launch kinetic energy, high energy conversion rate, strong load adjustability, and good controllability. However, existing schemes using multi-stage electromagnetic coil launching systems for launching birds suffer from drawbacks such as short cartridge case lifespan and the inability to smoothly and efficiently separate the cartridge case from the bird, resulting in unstable flight after launch. Summary of the Invention

[0005] The purpose of this invention is to provide a bird strike test launching device based on multi-stage coil electromagnetic launch, which can achieve smooth and efficient separation between the cartridge case and the bird body, and can improve the service life of the magnetic cartridge case and maintain the stable flight state of the bird body after launch.

[0006] To achieve the above-mentioned technical effects, the technical solution adopted by the present invention is as follows:

[0007] A bird strike test launching device based on multi-stage coil electromagnetic launch, comprising a barrel, and further comprising:

[0008] The projectile body includes a cartridge case and a bird body. The cartridge case includes a magnetic outer cartridge case and a split inner cartridge case inserted into the magnetic outer cartridge case. The magnetic outer cartridge case has a buffer structure at its exit end face. The split inner cartridge case has a magnetic induction plate. The bird body is placed inside the split inner cartridge case and is held in place by the split inner cartridge case.

[0009] A deceleration coil, located outside the barrel, is used to generate a force that forces the split inner cartridge case and the magnetic outer cartridge case to decelerate.

[0010] The ejection mechanism is located at the muzzle of the cannon barrel and is used to abut against the buffer structure and stop the magnetic outer cartridge case. The ejection mechanism is equipped with a cutting blade to force the split inner cartridge case to disintegrate and separate from the bird body.

[0011] Furthermore, the segmented inner cartridge case includes at least two arc-shaped segments, which are clamped by a clamping member and are cylindrical. The tail of each arc-shaped segment is provided with a separation slope, which forms an obtuse angle with the direction in which the bird is ejected. The separation slope is used to drive the arc-shaped segments to separate from the bird under the force of the cutting blade after the cutting blade cuts the clamping member.

[0012] Furthermore, the formula for calculating the angle between the separating inclined plane and the direction in which the bird is launched is as follows:

[0013] ;

[0014] in, The angle between the separating inclined plane and the direction in which the bird is launched. It is the arctangent function; The axial length of the arc-shaped valve body; The radius of the inner wall of the arc-shaped valve body; The thickness of the arc-shaped valve body; The velocity of the arc-shaped petal along the firing direction when it comes into contact with the cutting blade.

[0015] Furthermore, the outer surface of the arc-shaped flap is provided with a clamping groove along the circumferential direction for accommodating the clamping member; the outer surface of the arc-shaped flap is also provided with a razor groove along the axial direction, and the groove depth of the razor groove is greater than the groove depth of the clamping groove.

[0016] Furthermore, the outer surface of the arc-shaped valve is provided with a slot, and the magnetic induction sheet is installed in the slot.

[0017] Furthermore, the inner surface of the magnetic outer shell is provided with a guide groove, and the outer surface of the arc-shaped flap is provided with a positioning protrusion that cooperates with the guide groove.

[0018] Furthermore, the buffer structure includes a rubber buffer element installed on the end face of the magnetic outer cartridge case outlet.

[0019] Furthermore, the shell-removing mechanism includes a connecting cylinder and a cutter disc for fixing the cutting blade. The connecting cylinder is fixed to the muzzle of the cannon barrel, and the cutter disc is fixed to the connecting cylinder. The minimum inner diameter of the cutter disc is greater than the maximum outer diameter of the split inner cartridge case, and the maximum outer diameter of the cutter disc is less than the maximum outer diameter of the rubber buffer.

[0020] Furthermore, the cutter head includes a fixed ring and a movable buffer ring, as well as a buffer spring connecting the fixed ring and the movable buffer ring; the fixed ring is fixed to the connecting cylinder, and the cutting blade is fixed to the fixed ring; the axis of the movable buffer ring is collinear with the axis of the fixed ring.

[0021] Compared with the prior art, the beneficial effects of this invention are:

[0022] This invention employs a cartridge case comprising a segmented inner cartridge case and a magnetically induction outer cartridge case. Under the electromagnetic force of a multi-stage coil, the magnetically induction outer cartridge case accelerates the segmented inner cartridge case and the bird within the gun barrel. A discarding mechanism then blocks the magnetically induction outer cartridge case within the barrel, achieving separation between the two. Furthermore, a deceleration coil decelerates the projectile, and a buffer structure cushions the impact between the magnetically induction outer cartridge case and the discarding mechanism, thereby increasing the service life of the magnetically induction outer cartridge case and facilitating its reuse. Simultaneously, the invention utilizes the cutting blade of the discarding mechanism to force the segmented inner cartridge case to disintegrate and separate from the bird, achieving a smooth and efficient separation between the segmented inner cartridge case and the bird, ensuring the bird maintains stable flight after launch. Attached Figure Description

[0023] Figure 1 This is an example of a bird strike test launching device based on multi-stage coil electromagnetic emission;

[0024] Figure 2 This is a schematic diagram of the structure of the magnetic outer shell and the segmented inner shell in the embodiment;

[0025] Figure 3 This is a cross-sectional view of the magnetic outer cartridge case and the segmented inner cartridge case in the embodiment;

[0026] Figure 4 This is a schematic diagram of the structure of the magnetic outer shell in the embodiment;

[0027] Figure 5 This is a schematic diagram of the structure of the first locking block in the front mounting groove of the magnetic outer shell in the embodiment;

[0028] Figure 6 This is a schematic diagram of the structure of the rubber buffer in the embodiment;

[0029] Figure 7 This is a schematic diagram of the segmented inner cartridge case in the embodiment;

[0030] Figure 8 This is a schematic diagram of the slot structure on the arc-shaped valve body in the embodiment;

[0031] Figure 9 This is a schematic diagram of the magnetic induction sheet mounted on the arc-shaped lobe in the embodiment;

[0032] Figure 10This is a schematic diagram of the assembly of the connecting cylinder and the cutter head in the embodiment;

[0033] Figure 11 This is a schematic diagram of the cutter head structure in the embodiment;

[0034] Figure 12 This is a schematic diagram of the connecting cylinder in the embodiment;

[0035] Figure 13 This is a schematic diagram showing the angle between the separation ramp and the direction in which the bird is launched, as illustrated in the embodiment.

[0036] Among them, 1-cannon barrel, 2-reduction coil, 3-magnetic outer cartridge case, 31-silicon steel part, 32-end cap, 33-rubber buffer, 331-second locking block, 332-pre-tightening buffer spring, 333-rubber buffer block, 34-guide slide, 35-mounting groove, 351-stop ring, 36-notch, 37-first locking block, 4-segmented inner cartridge case, 41-arc-shaped segment, 42-separation slope, 43-clamping groove, 44-razor groove, 45-slot, 46-magnetic induction sheet, 47-positioning protrusion, 5-clamping component, 6-connecting cylinder, 61-rubber ring, 62-pre-tightening groove, 7-cutter disc, 71-fixing ring, 72-movable buffer ring, 73-buffer spring, 74-cutting blade, 8-clamp, 9-bird body. Detailed Implementation

[0037] The present invention will now be described in further detail with reference to the embodiments and accompanying drawings. However, this should not be construed as limiting the scope of the above-described subject matter of the present invention to the following embodiments; all technologies implemented based on the content of the present invention fall within the scope of the present invention.

[0038] Example

[0039] See Figures 1 to 13 A bird strike test launching device based on multi-stage coil electromagnetic launch, comprising a barrel 1, and further comprising:

[0040] The projectile body includes a cartridge case and a bird body 9. The cartridge case includes a magnetic outer cartridge case 3 and a segmented inner cartridge case 4 inserted into the magnetic outer cartridge case 3. The magnetic outer cartridge case 3 is a hollow aluminum cylinder with a silicon steel part 31 embedded inside. The silicon steel part 31 is composed of multiple heat-treated annular silicon steel sheets stacked together to reduce hysteresis loss and eddy current loss of the magnetic outer cartridge case 3 and improve magnetic permeability. The segmented inner cartridge case 4 is provided with a magnetic induction sheet 46. The bird body 9 is placed inside the segmented inner cartridge case 4 and is clamped by the segmented inner cartridge case 4.

[0041] Deceleration coil 2, which is located outside the barrel 1, is used to generate a force that forces the split inner cartridge case 4 and the magnetic outer cartridge case 3 to decelerate.

[0042] The ejection mechanism is located at the muzzle of the cannon barrel 1 and is used to stop the magnetic outer cartridge case 3. The ejection mechanism is equipped with a cutting blade 74 to force the split inner cartridge case 4 to disintegrate and separate from the bird body 9.

[0043] This invention employs a cartridge case comprising a split inner cartridge case 4 and a magnetic outer cartridge case 3. Under the electromagnetic force of a multi-stage coil, the magnetic outer cartridge case 3 drives the split inner cartridge case 4 and the bird body 9 to accelerate within the barrel 1. A discarding mechanism is used to block the magnetic outer cartridge case 3 within the barrel 1, achieving separation between the magnetic outer cartridge case 3 and the split inner cartridge case 4. Furthermore, a deceleration coil 2 is used to decelerate the projectile, and a buffer structure is used to buffer the impact between the magnetic outer cartridge case and the discarding mechanism, thereby improving the service life of the magnetic outer cartridge case 3 and facilitating its reuse. Simultaneously, this invention also utilizes the cutting blade 74 of the discarding mechanism to force the split inner cartridge case 4 to disintegrate and separate from the bird body 9, achieving a smooth and efficient separation between the split inner cartridge case 4 and the bird body 9, ensuring that the bird body 9 maintains a stable flight state after launch.

[0044] In some embodiments, the segmented inner cartridge case 4 includes at least two arc-shaped segments 41, which are clamped together by clamping members 5 and are cylindrical in shape. The material of the clamping members 5 must ensure that it can withstand the force required to clamp the segmented inner cartridge case 4, and the material of the cutting blade 74 must ensure that it can cut through the clamping members 5. See also Figures 2 to 3 , Figures 5 to 9In this embodiment, the segmented inner cartridge case 4 is made of PVC material, the clamping member 5 can be an elastic rope or other structure capable of clamping the segmented inner cartridge case 4, and the cutting blade 74 is made of aluminum alloy. Furthermore, the segmented inner cartridge case 4 is composed of three arc-shaped segments 41 combined to form a cylindrical structure, which is then clamped together by an elastic rope. Each arc-shaped segment 41 is an arc-shaped structure with a central angle of 120°. The tail of each arc-shaped segment 41 is provided with a separation slope 42, the angle between the separation slope 42 and the direction of the bird's flight 9 is obtuse, and the separation slope 42 extends radially outward from the outer surface of the arc-shaped segment 41. When the bird 9 is launched, after the cutting blade 74 cuts the clamping member 5, as the segmented inner cartridge case 4 moves towards the barrel 1, the separation ramp 42 contacts the cutting blade 74. Simultaneously, as the cutting blade 74 slides along the separation ramp 42, it applies pressure to the ramp 42, forcing the individual arc-shaped segments 41 to separate, causing the segmented inner cartridge case 4 to open outwards, thus separating the segmented inner cartridge case 4 from the bird 9. This embodiment, by designing the separation ramp 42, not only ensures that the arc-shaped segments 41 can smoothly separate under the action of the cutting blade 74, but also effectively reduces the interference of the arc-shaped segments 41 on the flight attitude of the bird 9 during the separation process, allowing the bird 9 to maintain a stable flight attitude, thereby improving the accuracy and reliability of the bird strike test. Furthermore, the radially outward extension of the separation ramp 42 enhances the guidance of the arc-shaped segments 41 during the separation process, making the separation process of the arc-shaped segments 41 smoother and more efficient.

[0045] It should be noted that, as Figure 13 As shown, the angle between the separation ramp 42 and the direction of the bird's body 9 is determined by the following formula:

[0046] ;

[0047] in, The angle between the separating inclined plane 42 and the direction in which the bird body 9 is emitted is called the angle. The calculation results are in Between, when the angle The calculation result is less than At that time, the included angle Values When the included angle The calculation result is greater than At that time, the included angle Values ; It is the arctangent function; The axial length of the arc-shaped valve body 41; The radius of the inner wall of the arc-shaped valve body 41 is the radius corresponding to the inner diameter of the arc-shaped valve body 41. The thickness of the arc-shaped valve body 41; This refers to the velocity of the arc-shaped lobe 41 along the firing direction when it contacts the cutting blade. It should be noted that the velocity of the arc-shaped lobe 41 along the firing direction when it contacts the cutting blade... This can be equated to the theoretical velocity of the segmented inner cartridge case 4 before it reaches the muzzle and contacts the cutting blade. This theoretical velocity can be calculated using relevant parameters such as current and Lorentz force.

[0048] The angle between the separation ramp 42 and the direction of the bird's body 9 as emitted is determined using the above formula. This ensures that the impact force when the cutting blade 74 and the separation slope 42 are in complete contact is evenly distributed on the separation slope 42, ensuring that the arc-shaped petal 41 is stably separated from the bird body 9.

[0049] In some embodiments, the outer surface of the arc-shaped flap 41 is provided with a clamping groove 43 along the circumferential direction for accommodating the clamping member 5; the outer surface of the arc-shaped flap 41 is also provided with a razor groove 44 along the axial direction, the groove depth of the razor groove 44 being greater than the groove depth of the clamping groove 43, so that the cutting blade 74 can smoothly cut the clamping member 5, and the separating inclined surface 42 extends radially outward along the arc-shaped flap 41, starting from the bottom of the razor groove 44. See also Figure 7 In this embodiment, each arc-shaped petal 41 has an axial razor groove 44 in the middle of its outer wall, and the split inner cartridge case 4 has three razor grooves 44, which are evenly distributed at 120° along the circumference of the outer wall of the split inner cartridge case 4. Correspondingly, the cutting blade 74 of the shell removal mechanism is also provided with three blades, one cutting blade 74 corresponding to one razor groove 44.

[0050] In some embodiments, see Figures 7 to 9 Each of the arc-shaped segments 41 is also provided with a slot 45 on its outer surface. A magnetic induction sheet 46 is installed in the slot 45. The magnetic induction sheet 46 is made of silicon steel, which gives the PVC segmented inner shell 4 a certain magnetic induction characteristic. When the projectile is in the acceleration stage inside the barrel 1, the silicon steel card of the segmented inner shell 4 and the magnetic outer shell 3 are subjected to the Lorentz force together, which drives the projectile to accelerate. When the projectile is in the deceleration stage at the end of the barrel 1, since the magnetic induction characteristic of the segmented inner shell 4 is weaker than that of the magnetic outer shell 3, under the action of the deceleration coil 2, the Lorentz force on the magnetic outer shell 3 is greater than that on the segmented inner shell 4, so that the deceleration acceleration of the magnetic outer shell 3 is greater than that of the segmented inner shell 4, forming a stepped deceleration of the magnetic outer shell 3 and the segmented inner shell 4.

[0051] In some embodiments, the inner surface of the magnetic outer shell 3 is provided with a guide groove 34, and the outer surface of the arc-shaped flap 41 is provided with a positioning protrusion 47 that cooperates with the guide groove 34. See [reference needed] Figure 4 and Figure 7In this embodiment, the inner surface of the magnetic outer shell 3 has three pairs of guide grooves 34, which are evenly distributed at a central angle of 120°. The outer surface of the arc-shaped petal 41 has three pairs of positioning protrusions 47, which are also evenly distributed at a central angle of 120°. When the split inner shell 4 is installed, the positioning protrusions 47 are inserted into the guide grooves 34 to limit the movement. Moreover, when the magnetic outer shell 3 and the split inner shell 4 are separated, the positioning protrusions 47 and the guide grooves 34 act as guides to ensure that the split inner shell 4 slides smoothly inside the magnetic outer shell 3, avoiding jamming or displacement during the separation process.

[0052] In some embodiments, the front end of the magnetic outer shell 3 is provided with a buffer structure that abuts against the release mechanism, see [reference]. Figure 1 and Figure 4 This avoids direct hard contact between the magnetic outer shell 3 and the ejection mechanism, extending the service life of the magnetic outer shell 3 and increasing the number of cycles. At the same time, the rear end of the magnetic outer shell 3 is also connected to an end cap 32 via a thread, which prevents the split inner shell 4 and the bird body 9 from being thrown backward due to inertia during the acceleration of the magnetic outer shell 3.

[0053] In some embodiments, see Figures 1 to 6 The magnetic outer shell 3 has an L-shaped mounting groove 35 at its outlet end face. The first branch groove of the L-shaped mounting groove 35 extends inward from the outlet end face of the magnetic outer shell 3 along the length direction of the magnetic outer shell 3. The second branch groove of the L-shaped mounting groove 35 is arranged circumferentially along the magnetic outer shell 3. The first branch groove has a notch 36 leading to the second branch groove. The inner wall of the second branch groove has a first locking block 37. The buffer structure includes a rubber buffer 33 installed in the mounting groove 35. The rubber buffer 33 has a second locking block 331. The second locking block 331 is used to insert into the mounting groove 35 along the notch 36 and abut against the first locking block 37 after the rubber buffer 33 rotates at a preset angle. In this embodiment, the mounting groove 35 is an annular mounting groove 35. The groove opening of the annular mounting groove 35 is provided with a retaining ring 351, so that the groove opening width of the annular mounting groove 35 is less than the groove width. Three notches 36 are provided at equal intervals on the retaining ring 351. Three first locking blocks 37 are also provided, all of which are provided on the inner wall of the retaining ring 351. One first locking block 37 corresponds to one notch 36, and each first locking block 37 is set close to the notch 36. The rubber buffer 33 is a ring made of rubber. The second locking block 331 is provided on the side wall of the rubber buffer 33. When the rubber buffer 33 is inserted into the mounting groove 35, it is rotated by a preset angle so that the second locking block 331 abuts against the first locking block 37, thereby realizing the connection between the rubber buffer 33 and the magnetic outer shell 3.

[0054] Further, see Figure 6The second locking block 331 is fixed with a pre-tightening buffer spring 332. When the rubber buffer component 33 is inserted into the mounting groove 35, the free end of the pre-tightening buffer spring 332, i.e., the bottom end of the pre-tightening buffer spring 332, abuts against the bottom of the annular mounting groove 35, thereby keeping the second locking block 331 pressed against the first locking block 37. It should be noted that when the rubber buffer ring is rotated, the rotation angle is small, and the bending and tilting angle of the pre-tightening buffer spring 332 is small, so there will be no excessive tilting. Therefore, the pre-tightening buffer spring 332 can play its intended role normally.

[0055] Further, see Figure 6 The rubber buffer 33 is also provided with multiple rubber buffer blocks 333, which further enhance the buffering effect when the rubber buffer 33 collides with the shell removal mechanism.

[0056] In some embodiments, see Figure 1 , Figures 10 to 12 The shell ejection mechanism includes a cutter disc 7 that fixes the cutting blade 74 and a connecting cylinder 6. The cutter disc 7 is fixed to the muzzle of the cannon barrel 1 via the connecting cylinder 6. The cutter disc 7 includes a fixed ring 71 and a movable buffer ring 72, as well as a buffer spring 73 connecting the fixed ring 71 and the movable buffer ring 72. The fixed ring 71 is fixed to the connecting cylinder 6, and the cutting blade 74 is fixed to the inner wall of the fixed ring 71. The axis of the movable buffer ring 72 is collinear with the axis of the fixed ring 71, and the movable buffer ring 72 can be a rubber ring 61. When the magnetic outer shell 3 impacts the movable buffer ring 72, the movable buffer ring 72 compresses the buffer spring 73 and moves towards the fixed ring 71. The impact energy of the magnetic outer shell 3 is absorbed by the rubber ring 61, the buffer spring 73, and the rubber buffer 33 at the front end of the magnetic outer shell 3, stopping the magnetic outer shell 3 inside the cannon barrel 1, improving the durability of the magnetic outer shell 3, increasing the number of reuses, and extending the service life of the magnetic outer shell 3. It should be noted that the inner diameter of the fixing ring 71 is larger than the maximum outer diameter of the split inner cartridge case 4, ensuring that the split inner cartridge case 4 can pass smoothly through the fixing ring 71. At the same time, the outer diameter of the movable buffer ring 72 is smaller than the maximum outer diameter of the rubber buffer 33, ensuring that the magnetic outer cartridge case 3 is stopped by the movable buffer ring 72.

[0057] See Figure 1 and Figure 12The connecting cylinder 6 of the shell-removing mechanism is fixed to the muzzle of the gun barrel 1. The connecting cylinder 6 is a hollow cylindrical structure, and it is divided into three sections along the axial direction according to its inner diameter. The inner diameter of the first section is the smallest, which matches the outer diameter of the fixing ring 71 in the cutter head 7, and is used to install the cutter head 7. The inner diameter of the second section is slightly larger, which matches the outer diameter of the gun barrel 1. Moreover, when the connecting cylinder 6 is fitted onto the gun barrel 1, the step formed by the inner walls of the first and second sections of the cylinder acts as a limit, restricting the insertion of the gun barrel 1. The depth of the connecting cylinder 6; the inner diameter of the inner wall of the third section of the cylinder is the largest, and at least two pre-tightening grooves 62 are evenly distributed circumferentially on the cylinder corresponding to the inner wall of the third section. Before installing the connecting cylinder 6, a rubber ring 61 is first installed on the outside of the barrel 1. When installing the connecting cylinder 6, the rubber ring 61 is placed on the inner wall of the third section, and then the third section of the cylinder is tightened with a clamp 8. Due to the presence of the pre-tightening grooves 62, the clamp 8 tightens so that the third section of the cylinder tightens the rubber ring 61 onto the barrel 1, thereby fixing the connecting cylinder 6 to the barrel 1. The rubber ring 61 plays a buffering and shock-absorbing role, which can reduce the vibration transmission between the barrel 1 and the connecting cylinder 6. At the same time, by utilizing the elasticity and sealing properties of rubber, it reduces the direct friction and wear between the two, and can also prevent dust, impurities, etc. from entering the connection part to a certain extent, thus protecting the connecting cylinder 6.

[0058] It should be noted that during the launch of the projectile, the deceleration coil 2 is energized, generating an electromagnetic force opposite to the direction of the projectile's motion. This force acts on the magnetic outer shell 3 and the split inner shell 4. Since the magnetic induction characteristics of the magnetic outer shell 3 are stronger than those of the split inner shell 4, the Lorentz force on the magnetic outer shell 3 is stronger than that on the split inner shell 4. Therefore, the deceleration acceleration of the magnetic outer shell 3 is greater than that of the split inner shell 4. Meanwhile, since the bird body 9 does not have magnetic induction characteristics, it will not decelerate due to the Lorentz force, but it will decelerate due to the friction between the split inner shell 4 and the bird body 9. Therefore, when the deceleration coil 2 is energized, the magnetic outer shell 3, the split inner shell 4, and the bird body 9 will experience a stepped deceleration.

[0059] Working principle: Under the electromagnetic force of the multi-stage coil, the projectile carrying the bird 9 accelerates towards the movable buffer ring 72. When the deceleration coil 2 is energized, the magnetic outer cartridge case 3, the split inner cartridge case 4, and the bird 9 will decelerate in a stepped manner. When the magnetic outer cartridge case 3 and the split inner cartridge case 4 carrying the bird 9 reach the release mechanism, the magnetic outer cartridge case 3, which has residual velocity, collides with the movable buffer ring 72 and stops moving. The split inner cartridge case 4 carrying the bird 9 continues to pass through the movable buffer ring 72 and the fixed ring 71. The cutting blade 74 on the fixed ring 71 cuts the high-strength elastic rope, thus untying the split inner cartridge case 4. As the split inner cartridge case 4 carrying the bird 9 continues to move forward, the cutting blade 74 contacts the separation inclined surface 42 and applies pressure to the separation inclined surface 42, forcing the split inner cartridge case 4 to disintegrate and separate. The bird 9 continues to move forward, thus separating the bird 9 from the cartridge case. When the magnetic outer shell 3 carrying residual velocity collides with the movable buffer ring 72, the movable buffer ring 72, the buffer spring 73 on the cutter head 7, and the rubber buffer 33 at the front end of the magnetic outer shell 3 can effectively absorb the residual energy, achieve buffering, and prevent collision damage.

[0060] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A bird strike test launching device based on multi-stage coil electromagnetic launch, comprising a barrel (1), characterized in that, Also includes: The projectile body includes a cartridge case and a bird body (9). The cartridge case includes a magnetic outer cartridge case (3) and a split inner cartridge case (4) inserted into the magnetic outer cartridge case (3). The magnetic outer cartridge case (3) has a buffer structure at its exit end face. The split inner cartridge case (4) has a magnetic induction plate (46). The bird body (9) is placed inside the split inner cartridge case (4) and is clamped by the split inner cartridge case (4). Deceleration coil (2), which is located outside the barrel (1), is used to generate a force that forces the split inner shell (4) and the magnetic outer shell (3) to decelerate. The ejection mechanism is located at the muzzle of the cannon barrel (1) and is used to abut against the buffer structure and stop the magnetic outer shell (3). The ejection mechanism is provided with a cutting blade (74) to force the split inner shell (4) to disintegrate and separate from the bird body (9). The split-type inner cartridge case (4) includes at least two arc-shaped lobes (41). The arc-shaped lobes (41) are clamped by clamping members (5) and are cylindrical. The tail of the arc-shaped lobes (41) is provided with a separation slope (42). The angle between the separation slope (42) and the direction of the bird body (9) is an obtuse angle. The separation slope (42) is used to drive the arc-shaped lobes (41) to separate from the bird body (9) under the force of the cutting blade (74) after the clamping member (5) is cut by the cutting blade (74).

2. The bird strike test launching device according to claim 1, characterized in that, The formula for calculating the angle between the separating inclined plane (42) and the direction of the bird's body (9) is as follows: ； in, The angle between the separating inclined plane (42) and the direction in which the bird body (9) is emitted. It is the arctangent function; The axial length of the arc-shaped valve body (41); The radius of the inner wall of the arc-shaped valve body (41); The thickness of the arc-shaped valve body (41); The velocity of the arc-shaped lobe (41) along the firing direction when it comes into contact with the cutting blade.

3. The bird strike test launching device according to claim 2, characterized in that, The outer surface of the arc-shaped petal (41) is provided with a clamping groove (43) for accommodating the clamping member (5) along the circumferential direction; the outer surface of the arc-shaped petal (41) is also provided with a razor groove (44) along the axial direction, and the groove depth of the razor groove (44) is greater than the groove depth of the clamping groove (43).

4. The bird strike test launching device according to claim 3, characterized in that, The outer surface of the arc-shaped valve (41) is also provided with a slot (45), and the magnetic induction sheet (46) is installed in the slot (45).

5. The bird strike test launching device according to claim 4, characterized in that, The inner surface of the magnetic outer shell (3) is provided with a guide groove (34), and the outer surface of the arc-shaped petal (41) is provided with a positioning protrusion (47) that cooperates with the guide groove (34).

6. The bird strike test launching device according to claim 1, characterized in that, The buffer structure includes a rubber buffer (33) installed on the end face of the magnetic outer shell (3) at the exit.

7. The bird strike test launching device according to claim 6, characterized in that, The shell removal mechanism includes a connecting cylinder (6) and a cutter disc (7) for fixing the cutting blade (74). The connecting cylinder (6) is fixed to the muzzle of the cannon barrel (1), and the cutter disc (7) is fixed on the connecting cylinder (6). The minimum inner diameter of the cutter disc (7) is greater than the maximum outer diameter of the split inner cartridge (4), and the maximum outer diameter of the cutter disc (7) is less than the maximum outer diameter of the rubber buffer (33).

8. The bird strike test launching device according to claim 7, characterized in that, The cutter head (7) includes a fixed ring (71) and a movable buffer ring (72), and a buffer spring (73) connecting the fixed ring (71) and the movable buffer ring (72); the fixed ring (71) is fixed on the connecting cylinder (6), and the cutting blade (74) is fixed to the fixed ring (71); the axis of the movable buffer ring (72) is collinear with the axis of the fixed ring (71).

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