Low-overload thrust-adjustable launching test device

Abstract

The utility model relates to a low-overload thrust-adjustable launch test device, which comprises a launch canister assembly, a thrust-adjustable thrust-adjustable launch canister assembly and a thrust-adjustable thrust-adjustable thrust-adjustable launch canister assembly, and is characterized in that the launch canister assembly comprises a cylindrical and hollow launch canister body; the inner cylinder is coaxially arranged in the launching cylinder body, the outer diameter of the front end of the inner cylinder and the outer diameter of the main body are smaller than the inner diameter of the launching cylinder body, a boss protruding outwards in the radial direction is arranged at the rear end of the front end of the inner cylinder, and the boss is slidably connected into the launching cylinder body; the rear seat assembly is installed at the rear end of the launch canister body, the rear seat assembly is provided with a first cavity used for containing gunpowder, a second cavity is formed between the front end of the rear seat assembly and the inner canister, and after the gunpowder is ignited, due to the action of gas pressure, the first cavity and the second cavity are communicated, so that the gunpowder is ignited; the volume of the second cavity is larger than that of the first cavity, the gas pressure is reduced along with increase of the volume, and therefore low-overload launching can be achieved when the inner cylinder pushes the to-be-launched projectile or the unmanned aerial vehicle.

Description

Technical Field

[0001] The utility model relates to the technical fields of military industry and mechanical manufacturing, and in particular to a launch test device with adjustable low-overload thrust for launch tests of unmanned aerial vehicles and precision-guided artillery shells. Background Art

[0002] The launch tube has the advantages of great power, high accuracy, good maneuverability, and easy carrying and use, and is very popular among the troops.

[0003] At the same time, various drones and precision-guided artillery shells have appeared in modern warfare. A large number of launch tests will be carried out during the development of drones and precision-guided artillery shells. In particular, the precision electrical components on drones and precision-guided artillery shells have high requirements for launch overload. At the same time, the initial launch velocity also needs to be continuously iterated and verified, and the thrust needs to be continuously adjusted for verification.

[0004] Therefore, there is an urgent need for an experimental device solution that can realize low-overload launch tests and continuously adjust the thrust during the test. Summary of the invention

[0005] The technical problem to be solved by the utility model is how to help a launch test to achieve low overload and adjustable thrust.

[0006] In order to solve the above technical problems, the utility model provides a launch test device with adjustable low overload thrust, which comprises: a launch tube assembly, the launch tube assembly has a cylindrical and hollow launch tube body, the launch tube body has a front end along the launch direction and a rear end corresponding to the front end; an inner tube, the inner tube is an axisymmetric structure, and the axial section is in the shape of a "J", the inner tube is coaxially arranged in the launch tube body, the outer diameters of the front end of the inner tube and the main body are smaller than the inner diameter of the launch tube body, and a boss protruding radially outward is arranged at the front and rear ends of the inner tube, and the boss can be slidably connected in the launch tube body; a recoil assembly, the recoil assembly is installed at the rear end of the launch tube body, and the recoil assembly has a first chamber for placing gunpowder A second chamber is formed between the front end of the recoil assembly and the inner tube. After the gunpowder placed in the first chamber is ignited, the first chamber and the second chamber are connected due to the effect of gas pressure, so that the inner tube slides along the front end of the launch tube body under the effect of gas pressure. A first constraint step is radially inwardly arranged at the front end of the launch tube body. After the inner tube moves toward the front end, the first constraint step and the boss of the inner tube are stuck, so that the inner tube remains in the launch tube body. The volume of the second chamber is greater than that of the first chamber, and the gas pressure decreases with the increase of volume. Therefore, when the inner tube pushes the projectile or drone to be launched, low-overload launch can be achieved.

[0007] According to an embodiment of the utility model, the launch test device with low overload thrust and adjustable thrust may also include: a buffer ring, which is clamped between the outer wall of the inner tube and the inner wall of the launch tube, and is used to buffer the pressure between the boss of the inner tube and the first constraint step when launching projectiles or drones, so as to avoid damage to the inner tube.

[0008] According to an embodiment of the utility model, the launch test device with adjustable low overload thrust may further include: a push plate, which is arranged at one end of the inner tube close to the front end and is used to separate the projectile or drone to be launched from the inner tube.

[0009] According to an embodiment of the utility model, the rear seat assembly may include: a pressure control ring, which is axially arranged in the rear seat assembly, and has a side wall and an end face facing the strong front end, and is in a cup cover shape, and a through hole is arranged on the end face of the pressure control ring.

[0010] According to an embodiment of the utility model, the rear seat assembly may further include: a rear seat bottom, the rear seat bottom cover is arranged at the rear end of the pressure control ring, thereby forming a first chamber for placing gunpowder with the pressure control ring.

[0011] According to an embodiment of the utility model, a wire hole may be provided at the bottom of the rear seat for leading the electric ignition head out of the first chamber to facilitate ignition.

[0012] According to the embodiment of the utility model, after the electric ignition head is led out of the wire hole, silicone rubber can be applied to seal the first chamber.

[0013] According to an embodiment of the utility model, the rear seat assembly may further include: a diaphragm rupture piece, which is bonded to the end surface of the pressure control ring facing the interior of the first chamber by applying epoxy glue.

[0014] According to an embodiment of the utility model, the rupture membrane can be used to seal the first chamber. After the gunpowder is ignited, the rupture membrane is broken due to the gas pressure or pressure, so that the gas in the first chamber collides with the second chamber.

[0015] According to an embodiment of the utility model, the launch tube assembly may further include: a support rod having two ends, one end of which is rotatably connected to the front end of the launch tube body; and a base, which is rotatably connected to the rear end of the launch tube body, wherein the launch angle of the launch tube body can be adjusted by adjusting the angle between the support rod and the launch tube body and adjusting the angle between the base and the launch tube body.

[0016] Compared with the prior art, the technical solution provided by the embodiment of the utility model can at least achieve the following beneficial effects:

[0017] The utility model has the advantages of simple structure, convenient installation and accurate positioning. During the firing test, a carrier such as a shell to be fired is loaded into the inner cavity of the inner tube, and the support rod and the base are adjusted so that the firing tube assembly reaches the firing angle required for the test; a certain amount of black powder is poured into a pressure-controlling ring with holes on the cup-shaped end face to which a diaphragm-breaking piece is bonded, and an electric ignition head is loaded, and a wire of the electric ignition head is led out from the bottom of the rear seat, and a certain amount of silicone rubber is applied to the wire hole to make it sealed, and the electric ignition head is ignited by an ignition device, thereby realizing a low-overload firing test, and adjusting the thrust is realized by adjusting the amount of black powder.

[0018] The low-overload thrust adjustable launching test device provided by the utility model only needs to be loaded into the launching device of the utility model when conducting a launching test of ammunition or UAV, and the amount of gunpowder can be adjusted through the launching test device to achieve different verification speeds, while low-overload launching can be achieved. In actual use, the launching overload can be lower than 100g. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the drawings of the embodiments will be briefly introduced below. Obviously, the drawings in the following description only relate to some embodiments of the present utility model, rather than limiting the present utility model.

[0020] Figure 1 Schematic diagram of a launch test device with adjustable low-overload thrust according to an embodiment of the utility model;

[0021] Figure 2 yes Figure 1 sectional view of

[0022] Figure 3 and Figure 4 The utility model is a schematic diagram showing the use status of the launch test device with low overload thrust adjustment according to the embodiment of the utility model. DETAILED DESCRIPTION

[0023] In order to make the purpose, technical solution and advantages of the embodiment of the utility model clearer, the technical solution of the embodiment of the utility model will be clearly and completely described below in conjunction with the drawings of the embodiment of the utility model. Obviously, the described embodiment is a part of the embodiment of the utility model, not all of the embodiments. Based on the described embodiment of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0024] Unless otherwise defined, the technical or scientific terms used herein shall have the common meanings understood by persons with ordinary skills in the field to which the utility model belongs. The words "first", "second" and similar words used in the patent application specification and claims of the utility model do not indicate any order, quantity or importance, but are only used to distinguish different components. Similarly, words such as "one" or "a" do not indicate a quantity limitation, but indicate the existence of at least one.

[0025] Figure 1 1 is a front view showing a launch test device with adjustable low-overload thrust according to an embodiment of the utility model; Figure 2 yes Figure 1 Cross-sectional view of .

[0026] like Figure 1 and Figure 2 As shown, the low overload thrust adjustable launch test device includes: a launch tube assembly 1, an inner tube 2 and a recoil assembly 5.

[0027] The launch tube assembly 1 has a cylindrical and hollow launch tube body 11, and the launch tube body 11 has a front end along the launch direction and a rear end corresponding to the front end.

[0028] The inner tube 2 is an axisymmetric structure, and its axial section is in the shape of a Chinese character "J". The inner tube 2 is coaxially arranged in the launch tube body 11. The outer diameters of the front end and the main body of the inner tube 2 are smaller than the inner diameter of the launch tube body 11. The front and rear ends of the inner tube 2 are provided with bosses 21 protruding radially outward, and the bosses 21 are slidably connected in the launch tube body 11.

[0029] The recoil assembly 5 is installed at the rear end of the launch tube body 11, and the recoil assembly 5 has a first chamber 6 for placing gunpowder.

[0030] A second chamber 7 is formed between the front end of the recoil assembly 5 and the inner tube 2. After the gunpowder placed in the first chamber 6 is ignited, the first chamber 6 and the second chamber 7 are connected due to the effect of gas pressure, so that the inner tube 2 slides along the front end of the launch tube body 11 under the action of gas pressure.

[0031] A first restraining step 13 is radially inwardly arranged at the front end of the launch tube body 11. After the inner tube 2 moves to the front end, the first restraining step 13 and the boss 21 of the inner tube 2 are stuck together, so that the inner tube 2 remains in the launch tube body 11.

[0032] The volume of the second chamber 7 is greater than that of the first chamber 6, and the gas pressure decreases as the volume increases, so that when the inner tube 2 pushes the projectile or drone to be launched, low-overload launch can be achieved.

[0033] According to one or some embodiments of the utility model, the launch test device with adjustable low overload thrust further includes: a buffer ring 4. The buffer ring 4 is sandwiched between the outer wall of the inner tube 2 and the inner wall of the launch tube body 11, and is used to buffer the pressure between the boss 21 of the inner tube 2 and the first constraint step 13 when launching projectiles or drones, so as to avoid damage to the inner tube 2.

[0034] According to one or some embodiments of the present invention, the launch test device with adjustable low overload thrust further includes a push plate 3. The push plate 3 is arranged at one end of the inner tube 2 close to the front end, and is used to separate the projectile or drone to be launched from the inner tube 2.

[0035] According to one or some embodiments of the present invention, the rear seat assembly 5 includes: a pressure control ring 52. The pressure control ring 52 is axially arranged in the rear seat assembly 5, and the pressure control ring 52 has a side wall and an end face facing the strong front end, and is in a cup-lid shape. A through hole is arranged on the end face of the pressure control ring 52.

[0036] According to one or some embodiments of the present invention, the rear seat assembly 5 further comprises: a rear seat bottom 54. The rear seat bottom 54 covers the rear end of the pressure control ring 52, thereby forming a first chamber 6 for placing gunpowder with the pressure control ring 52.

[0037] According to one or some embodiments of the present invention, a wire hole is provided at the rear seat bottom 54 for leading the electric ignition head out of the first chamber 6 to facilitate ignition.

[0038] According to one or some embodiments of the present invention, after the electric ignition head is led out of the wire hole, silicone rubber is applied to seal the first chamber 6 .

[0039] According to one or some embodiments of the present invention, the rear seat assembly 5 further includes a diaphragm rupture piece 53. The diaphragm rupture piece 53 is bonded to the end surface of the pressure control ring 52 facing the interior of the first chamber 6 by applying epoxy adhesive.

[0040] According to one or some embodiments of the present invention, the rupture membrane 53 is used to seal the first chamber 6 . After the gunpowder is ignited, the rupture membrane 53 is broken due to the gas pressure, so that the gas in the first chamber 6 collides with the second chamber 7 .

[0041] According to one or some embodiments of the present invention, the launching tube assembly 1 further includes: a support rod 16 and a base 19 .

[0042] The support rod 16 has two ends, one end of which is rotatably connected to the front end of the launch tube body 11 and the base 19 is rotatably connected to the rear end of the launch tube body 11.

[0043] The firing angle of the launch tube body 11 can be adjusted by adjusting the angle between the support rod 16 and the launch tube body 11 and the angle between the base 19 and the launch tube body 11.

[0044] The utility model has the advantages of simple structure, convenient installation and accurate positioning. During the firing test, the carriers to be fired, such as shells, are loaded into the inner cavity of the inner tube 2, and the support rod 16 and the base 19 are adjusted so that the launching tube assembly 1 reaches the firing angle required for the test; a certain amount of black powder is poured into the control pressure ring 52 with holes on the cup-shaped end surface to which the diaphragm 53 is bonded, and an electric ignition head is loaded, and the wire of the electric ignition head is led out from the rear seat bottom 54, and a certain amount of silicone rubber is applied to the wire hole to make it sealed, and the electric ignition head is ignited by the ignition device, thereby realizing a low-overload firing test, and the thrust is adjustable by adjusting the amount of black powder.

[0045] According to one or some embodiments of the utility model, an inner tube 2 is sleeved in the inner cavity of the launching tube assembly 1, the push plate 3 is placed on the vertical left of the "Changgong"-shaped inner tube 2, the annular buffer ring 4 is sleeved on the rear step of the inner tube 2 for positioning, and the rear seat is screwed into the tail of the launching tube assembly 1 in the form of a thread.

[0046] The launch tube assembly 1 includes three cylindrical launch tube bodies connected into one body by threads, two semi-annular clamps 12 are clamped to the launch tube body by clamp 12 screws, and the support rod 16 is connected to the clamp 12 by a support rod 16 seat and a support rod 16 screw; the base 19 is connected to the threaded hole on the side of the tail of the launch tube body by the base 19 screws.

[0047] The rear seat assembly 5 includes a rear seat body 51, which has a second constraint step 55. A cup-shaped pressure control ring 52 with a hole in the end face is inserted into the second constraint step 55 from the inner hole of the rear seat bottom 54 for positioning. The circular membrane-breaking piece 53 is coated with epoxy glue and bonded to the inner circular surface of the pressure control ring 52. The rear seat bottom 54 is screwed into the bottom of the rear seat body 51 through threads.

[0048] Figure 3 and Figure 4 The utility model is a schematic diagram showing the use status of the launch test device with low overload thrust adjustment according to the embodiment of the utility model.

[0049] like Figure 3 and Figure 4As shown, when in use, black powder can be used as gunpowder. After the black powder is ignited, the gas quickly expands in the pressure control ring 52 with holes on the cup-shaped end face, with a volume of V1, forming a pressure P1. After the gas expands, it breaks through the pressure constraint of the diaphragm 53 and enters the cavity of the second chamber 7 of the inner tube 2, with a volume of V2. Since the amount of gas generated is constant, the pressure P2 formed by the gas in the cavity in the tube, P2 is much smaller than P1, wherein P1 / P2=V2 / V1, and the driving force generated by the P2 pressure pushes the inner tube 2 to move the projectile or UAV forward together. When the inner tube 2 moves to the position of the first constraint step 13 at the mouth of the launch tube body, the annular buffer ring 4 and the first constraint step 13 at the mouth of the launch tube body are buffered and compressed, so that the inner tube 2 remains in the launch tube body, and the projectile or UAV flies out of the launch tube body, thereby realizing low overload launch.

[0050] When the experiment requires, the thrust can be adjusted by adjusting the value of V2 / V1, the aperture of the end hole of the cup-shaped end-face perforated pressure-control ring 52, and the thickness of the diaphragm-breaking sheet 53.

[0051] The utility model has a simple structure, convenient installation and accurate positioning. During the launch test, the carrier to be launched, such as a shell, is loaded into the inner cavity of the second chamber 7 of the inner tube 2, and the support rod 16 and the base 19 are adjusted so that the launch tube assembly 1 reaches the launch angle required for the test; a certain amount of black powder is poured into the control pressure ring 52 with a hole on the cup-shaped end face to which the diaphragm 53 is bonded, and an electric ignition head is loaded, and the electric ignition head wire is led out from the rear seat bottom 54, and a certain amount of silicone rubber is applied to the wire hole to make it sealed, and the electric ignition head is ignited by the ignition device, thereby realizing a low-overload launch test, and the thrust can also be adjusted by adjusting the amount of black powder.

[0052] The low-overload thrust adjustable launching test device provided by the utility model only needs to be loaded into the launching device of the utility model when conducting a launching test of ammunition or UAV, and the amount of gunpowder can be adjusted through the launching test device to achieve different verification speeds, while low-overload launching can be achieved. In actual use, the launching overload can be lower than 100g.

[0053] The above description is merely an exemplary embodiment of the present invention and is not intended to limit the protection scope of the present invention. The protection scope of the present invention is determined by the appended claims.

Claims

1. A launch test device with low overload thrust and adjustable thrust, characterized in that: include: A launching barrel assembly, wherein the launching barrel assembly has a cylindrical and hollow launching barrel body, wherein the launching barrel body has a front end along a launching direction and a rear end corresponding to the front end; The inner tube is an axisymmetric structure, and is in the shape of a Chinese character "J" along the axial section. The inner tube is coaxially arranged in the launch tube body. The outer diameters of the front end and the main body of the inner tube are smaller than the inner diameter of the launch tube body. The front and rear ends of the inner tube are provided with bosses protruding radially outward, and the bosses are slidably connected to the launch tube body. A recoil assembly, the recoil assembly being mounted at the rear end of the launch tube body, the recoil assembly having a first chamber for placing gunpowder, Wherein, a second chamber is formed between the front end of the recoil assembly and the inner tube. After the gunpowder placed in the first chamber is ignited, the first chamber and the second chamber are connected due to the effect of gas pressure, so that the inner tube slides along the front end of the launch tube body under the effect of gas pressure. Among them, a first restraining step is radially inwardly arranged at the front end of the launch tube body. After the inner tube moves to the front end, the first restraining step and the boss of the inner tube are stuck, so that the inner tube remains in the launch tube body. Among them, the volume of the second chamber is greater than that of the first chamber, and the gas pressure decreases as the volume increases, so that when the inner tube pushes the projectile or drone to be launched, low-overload launch can be achieved.

2. The launch test device with adjustable low-overload thrust as claimed in claim 1, characterized in that: Also includes: A buffer ring is clamped between the outer wall of the inner tube and the inner wall of the launch tube, and is used to buffer the pressure between the boss of the inner tube and the first constraint step when launching projectiles or drones, so as to avoid damage to the inner tube.

3. The launch test device with adjustable low-overload thrust as claimed in claim 1, characterized in that: Also includes: A push plate is arranged at one end of the inner barrel near the front end, and is used to separate the projectile or drone to be launched from the inner barrel.

4. The launch test device with adjustable low-overload thrust as claimed in claim 1, characterized in that: The rear seat assembly comprises: a pressure control ring, which is axially arranged in the rear seat assembly, and the pressure control ring has a side wall and an end face facing the strong front end, and is in a cup cover shape, and a through hole is arranged on the end face of the pressure control ring.

5. The launch test device with adjustable low-overload thrust as claimed in claim 4, characterized in that: The rear seat assembly also includes a rear seat bottom, and the rear seat bottom cover is arranged at the rear end of the pressure control ring, so as to form a first chamber for placing gunpowder with the pressure control ring.

6. The launch test device with adjustable low-overload thrust as claimed in claim 5, characterized in that: The rear seat bottom is provided with a wire hole for leading the electric ignition head out of the first chamber to facilitate ignition.

7. The launch test device with adjustable low-overload thrust as claimed in claim 6, characterized in that: After the electric ignition head is led out of the wire hole, silicone rubber is applied to seal the first chamber.

8. The launch test device with adjustable low-overload thrust as claimed in claim 4, characterized in that: The rear seat assembly further comprises: a diaphragm rupture piece, which is bonded to the end surface of the pressure control ring facing the interior of the first chamber by applying epoxy adhesive.

9. The launch test device with adjustable low-overload thrust as claimed in claim 8, characterized in that: The rupture film is used to seal the first chamber. After the gunpowder is ignited, the rupture film is broken due to the gas pressure, so that the gas in the first chamber collides with the second chamber.

10. The launch test device with adjustable low-overload thrust as claimed in claim 1, characterized in that: The launch tube assembly also includes: A support rod, the support rod having two ends, one end of which is rotatably connected to the front end of the launch tube body; A base, the base being rotatably connected to the rear end of the launch tube body, The firing angle of the launch tube body is adjusted by adjusting the angle between the support rod and the launch tube body and adjusting the angle between the base and the launch tube body.

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