Bird impact test launching device based on multistage coil electromagnetic launching

Abstract

The invention relates to the technical field of aircraft engine bird strike tests, and discloses a bird strike test launching device based on multistage coil electromagnetic launching, a cartridge case comprising a split type inner cartridge case and a magnetic induction outer cartridge case is adopted, under the electromagnetic force effect of a multistage coil, the magnetic induction outer cartridge case drives the split type inner cartridge case and a bird body to accelerate in a gun barrel, and the bird strike test is completed. The shell removing mechanism is used for blocking the magnetic induction outer cartridge case in the gun barrel, separation of the magnetic induction outer cartridge case and the split type inner cartridge case is achieved, the service life of the magnetic induction outer cartridge case is prolonged, the magnetic induction outer cartridge case can be recycled conveniently, meanwhile, a cutting knife of the shell removing mechanism is used for forcing the split type inner cartridge case to be disintegrated and separated from a bird body, and the shell removing efficiency is improved. And stable and efficient separation between the split type inner cartridge case and the bird body is realized, and the bird body is ensured to maintain a stable flight state after being launched.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of bird impact test of aero-engine, and discloses a bird impact test launching device based on multi-stage coil electromagnetic launching. BACKGROUND

[0002] In the development process of an aero-engine, in order to verify its airworthiness, a series of examination tests need to be carried out. Among them, the bird impact test aims to verify the tolerance of the engine to the bird swallowing event. In order to improve the research and development efficiency and systematically master the damage law, usually before the whole machine bird swallowing test, the bird impact resistance verification test of the fan and other key components is carried out.

[0003] The component-level bird impact test generally uses a simulated bird bomb to replace a real bird body. The simulated bird bomb is a bomb body structure specially designed for impact test pieces, which is launched by compressed air gun acceleration when installed in the bomb holder. When the bomb holder with the bird bomb moves to the muzzle release device, the release device blocks the bomb holder to make it stop suddenly, while the simulated bird bomb continues to fly at high speed relying on inertia to realize separation, and finally hits the rotating components of the engine.

[0004] The multi-stage electromagnetic coil launching system is a new type of launching device that converts electromagnetic energy into kinetic energy, which has the advantages of high launching speed, large launching kinetic energy, high energy conversion rate, strong load adjustability and good controllability. However, the existing bird body launching scheme using a multi-stage electromagnetic coil launching system has the defects of short service life of the shell, and the problem of unstable separation between the shell and the bird body, which leads to unstable flight state of the bird body after launching. SUMMARY

[0005] The purpose of the present application is to provide a bird impact test launching device based on multi-stage coil electromagnetic launching, which can realize stable and efficient separation between the shell and the bird body, and can improve the service life of the magnetic shell and maintain the stable flight state of the bird body after launching.

[0006] In order to achieve the above technical effects, the technical scheme adopted by the present application is as follows: A bird impact test launching device based on multi-stage coil electromagnetic launching, comprising a barrel, further comprising: a bomb body, the bomb body comprising a shell and a bird body, the shell comprising a magnetic outer shell and a split inner shell inserted into the magnetic outer shell, an end face of an outlet of the magnetic outer shell being provided with a buffer structure, the split inner shell being provided with a magnetic induction sheet, and the bird body being placed in the split inner shell and being clamped by the split inner shell; a deceleration coil, the deceleration coil being arranged outside the barrel and being used to generate an acting force for decelerating the split inner shell and the magnetic outer shell; A shell-off mechanism is arranged at the muzzle of the barrel and is used to abut and stop the magnetic outer shell. The shell-off mechanism is provided with a cutting knife for forcing the split inner shell to disintegrate and separate from the bird body.

[0007] Further, the split inner shell comprises at least two arc-shaped petals which are clamped and cylindrical by a clamping member. The tail of the arc-shaped petal is provided with a separation slope which is an obtuse angle with the direction of the bird body shooting. The separation slope is used to drive the arc-shaped petal to disperse and separate from the bird body under the force of the cutting knife after the cutting knife cuts the clamping member.

[0008] Further, the separation slope and the direction of the bird body shooting are calculated by the following formula: ; Wherein, is the angle between the separation slope and the direction of the bird body shooting, is the arctangent function; is the axial length of the arc-shaped petal; is the radius of the inner wall of the arc-shaped petal; is the thickness of the arc-shaped petal; is the speed of the arc-shaped petal along the shooting direction when it contacts the cutting knife.

[0009] Further, the outer surface of the arc-shaped petal is provided with a clamping groove along the circumference for accommodating the clamping member. The outer surface of the arc-shaped petal is also provided with a razor groove along the axis, and the groove depth of the razor groove is greater than that of the clamping groove.

[0010] Further, the outer surface of the arc-shaped petal is also provided with a clamping groove, and the magnetic induction sheet is installed in the clamping groove.

[0011] Further, the inner surface of the magnetic outer shell is provided with a guide sliding groove, and the outer surface of the arc-shaped petal is provided with a positioning convex strip matched with the guide sliding groove.

[0012] Further, the buffer structure comprises a rubber buffer member installed at the end face of the outlet of the magnetic outer shell.

[0013] Further, the shell-off mechanism comprises a connecting barrel and a cutter disc for fixing the cutting knife. The connecting barrel is fixed to the muzzle of the barrel, and the cutter disc is fixed on the connecting barrel. The minimum inner diameter of the cutter disc is greater than the maximum outer diameter of the split inner shell, and the maximum outer diameter of the cutter disc is smaller than the maximum outer diameter of the rubber buffer member.

[0014] Further, the cutter head comprises a fixed ring and a movable buffer ring, and a buffer spring connecting the fixed ring and the movable buffer ring; the fixed ring is fixed on the connecting cylinder, and the cutting knife is fixed with the fixed ring; the axis of the movable buffer ring is collinear with the axis of the fixed ring.

[0015] Compared with the prior art, the application has the beneficial effects that: The application adopts the shell comprising the split inner shell and the magnetic induction outer shell, under the electromagnetic force of the multi-stage coil, the magnetic induction outer shell drives the split inner shell and the bird body to accelerate in the barrel, the magnetic induction outer shell is blocked in the barrel by the shell separation mechanism, the separation of the magnetic induction outer shell and the split inner shell is realized, the speed of the shell body is reduced by the speed reduction coil, the impact between the magnetic induction outer shell and the shell separation mechanism is buffered by the buffer structure, the service life of the magnetic induction outer shell is improved, and the magnetic induction outer shell is recycled. Meanwhile, the cutting knife of the shell separation mechanism forces the split inner shell to disintegrate and separate from the bird body, the stable and efficient separation between the split inner shell and the bird body is realized, and the bird body maintains a stable flight state after being launched. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 It is the bird impact test launching device based on the multi-stage coil electromagnetic launching in the embodiment; Figure 2 It is a structural schematic view of the magnetic induction outer shell and the split inner shell in the embodiment; Figure 3 It is a sectional view of the magnetic induction outer shell and the split inner shell in the embodiment; Figure 4 It is a structural schematic view of the magnetic induction outer shell in the embodiment; Figure 5 It is a structural schematic view of the first clamping block in the mounting slot at the front end of the magnetic induction outer shell in the embodiment; Figure 6 It is a structural schematic view of the rubber buffer in the embodiment; Figure 7 It is a structural schematic view of the split inner shell in the embodiment; Figure 8 It is a structural schematic view of the clamping slot on the arc-shaped lobe in the embodiment; Figure 9 It is a structural schematic view of the magnetic induction sheet mounted on the arc-shaped lobe in the embodiment; Figure 10 It is an assembly schematic view of the connecting cylinder and the cutter head in the embodiment; Figure 11 It is a structural schematic view of the cutter head in the embodiment; Figure 12 It is a structural schematic view of the connecting cylinder in the embodiment; Figure 13Figure 2 is a schematic diagram showing the angle between the separation slope and the bird body ejection direction in the embodiment.

[0017] 1 - barrel, 2 - deceleration coil, 3 - magnetic induction outer shell, 31 - silicon steel part, 32 - end cover, 33 - rubber buffer, 331 - second clamping block, 332 - pre-tightening buffer spring, 333 - rubber buffer block, 34 - guide sliding slot, 35 - mounting groove, 351 - blocking ring, 36 - notch, 37 - first clamping block, 4 - split inner shell, 41 - arc-shaped lobe, 42 - separation slope, 43 - clamping groove, 44 - razor slot, 45 - clamping slot, 46 - magnetic induction sheet, 47 - positioning convex strip, 5 - clamping member, 6 - connecting barrel, 61 - rubber ring, 62 - pre-tightening groove, 7 - cutter head, 71 - fixed ring, 72 - movable buffer ring, 73 - buffer spring, 74 - cutting knife, 8 - clamp, 9 - bird body. DETAILED DESCRIPTION

[0018] The application will be further described in conjunction with the embodiments and the accompanying drawings. However, it should not be understood that the above-mentioned subject matter of the application is limited to the following embodiments, and any technology realized based on the content of the application falls within the scope of the application.

[0019] EMBODIMENT REFERENCE Figures 1 to 13 A bird impact test launching device based on multi-stage coil electromagnetic launching, comprising a barrel 1, further comprising: a projectile, comprising a shell and a bird body 9, the shell comprising a magnetic induction outer shell 3 and a split inner shell 4 inserted into the magnetic induction outer shell 3; the magnetic induction outer shell 3 is an aluminum hollow cylindrical barrel, and a silicon steel part 31 is embedded in the magnetic induction outer shell 3, which is composed of a plurality of ring-shaped silicon steel sheets after heat treatment, so as to reduce the magnetic hysteresis loss and eddy current loss of the magnetic induction outer shell 3 and improve the magnetic permeability; the split inner shell 4 is provided with a magnetic induction sheet 46, and the bird body 9 is placed in the split inner shell 4 and clamped by the split inner shell 4; a deceleration coil 2, which is arranged outside the barrel 1 and is used to generate a force to force the split inner shell 4 and the magnetic induction outer shell 3 to decelerate; a shell separation mechanism, which is arranged at the barrel mouth of the barrel 1 and is used to stop the magnetic induction outer shell 3, and the shell separation mechanism is provided with a cutting knife 74, which is used to force the split inner shell 4 to disintegrate and separate from the bird body 9.

[0020] The application adopts the shell including split inner shell 4 and magnetic induction outer shell 3, under the electromagnetic force of multi-stage coil, the magnetic induction outer shell 3 drives the split inner shell 4 to accelerate in the cannon barrel 1 with the bird body 9, the magnetic induction outer shell 3 is blocked in the cannon barrel 1 by using the shell separation mechanism, the separation of the magnetic induction outer shell 3 and the split inner shell 4 is realized, the speed of the shell body is reduced by using the speed reduction coil 2, the impact between the magnetic induction outer shell and the shell separation mechanism is buffered by using the buffer structure, the service life of the magnetic induction outer shell 3 is improved, the magnetic induction outer shell 3 is recycled, and simultaneously, the cutting knife 74 of the shell separation mechanism forces the split inner shell 4 to disintegrate and separate from the bird body 9, the stable and efficient separation between the split inner shell 4 and the bird body 9 is realized, and the stable flight state of the bird body 9 after launching is ensured.

[0021] In some embodiments, the split inner shell 4 includes at least two arc-shaped petals 41, the arc-shaped petals 41 are clamped by the clamping member 5 and are in a cylindrical shape, the material of the clamping member 5 needs to ensure that it can withstand the force required for clamping the split inner shell 4, and the material of the cutting knife 74 needs to ensure that it can cut the clamping member 5. Referring to Figures 2 to 3 、 Figures 5 to 9 In this embodiment, the split inner shell 4 is made of PVC material, the clamping member 5 can be made of elastic rope or other structures capable of clamping the split inner shell 4, and the cutting knife 74 is made of an aluminum alloy cutter; and the split inner shell 4 is formed into a cylindrical structure by combining three arc-shaped petals 41 together, and then the three arc-shaped petals 41 are clamped by elastic ropes, and each arc-shaped petal 41 is an arc-shaped structure with a central angle of 120°. The tail of the arc-shaped petal 41 is provided with a separation slope 42, the included angle between the separation slope 42 and the direction of the bird body 9 is obtuse, and the separation slope 42 extends outward along the radial direction of the arc-shaped petal 41 from the outer surface of the arc-shaped petal 41. When the bird body 9 is launched, after the cutting knife 74 cuts the clamping member 5, the separation slope 42 contacts the cutting knife 74 as the split inner shell 4 moves towards the cannon barrel 1, and the cutting knife 74 slides along the separation slope 42 while applying pressure to the separation slope 42, forcing each arc-shaped petal 41 to disperse, causing the split inner shell 4 to open outward, and achieving the separation of the split inner shell 4 and the bird body 9. By designing the separation slope 42, this embodiment not only ensures that the arc-shaped petals 41 can smoothly disperse under the action of the cutting knife 74, but also effectively reduces the interference of the arc-shaped petals 41 with the flight posture of the bird body 9 during the separation process, so that the bird body 9 maintains a stable flight posture, thereby improving the accuracy and reliability of the bird impact test. In addition, the characteristic that the separation slope 42 extends outward along the radial direction enhances the guidance of the arc-shaped petals 41 during the separation process, making the separation process of the arc-shaped petals 41 more stable and efficient.

[0022] It should be noted that, as shown in Figure 13 the included angle between the separation slope 42 and the direction of the bird body 9 is determined by the following formula: ; 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.

[0023] 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.

[0024] 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.

[0025] In some embodiments, see Figures 7 to 9Each 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.

[0026] 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 7 In 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.

[0027] 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.

[0028] In some embodiments, see Figures 1 to 6The 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.

[0029] Further, see Figure 6 The 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.

[0030] 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.

[0031] In some embodiments, see Figure 1 , Figures 10 to 12The 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.

[0032] See Figure 1 and Figure 12 The 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.

[0033] 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.

[0034] 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.

[0035] 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 equipped with a cutting blade (74) to force the split inner shell (4) to disintegrate and separate from the bird body (9).

2. The bird strike test launching device according to claim 1, characterized in that, 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).

3. The bird strike test launching device according to claim 2, 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.

4. The bird strike test launching device according to claim 3, 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).

5. The bird strike test launching device according to claim 4, 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).

6. The bird strike test launching device according to claim 5, 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).

7. 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.

8. The bird strike test launching device according to claim 7, 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).

9. The bird strike test launching device according to claim 8, 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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