Directional button pull-off mechanism of multi-tube launching device and pull-off method of directional button pull-off mechanism

Abstract

The invention relates to the technical field of multi-tube launching devices, and particularly discloses a directional button pull-off mechanism of a multi-tube launching device and a pull-off method.The launching device comprises an aircraft, the aircraft comprises a large-diameter section and a small-diameter section, the directional button pull-off mechanism comprises a launching cylinder and a locking hoop, the launching cylinder is arranged on the aircraft in a sleeving mode, and the locking hoop is arranged on the launching cylinder; a spiral guide groove and a straight guide groove are formed in the launch canister, the locking hoop is connected to the tail end of the aircraft and connected with a pull rod, the end, away from the locking hoop, of the pull rod is connected with the aircraft through a shear screw, the inner diameter of the launch canister is larger than the outer diameter of the locking hoop, and the outer diameter of the locking hoop is larger than the outer diameter of the tail end of the aircraft. A limiting table is arranged at the inner end of the locking hoop, a shearing table is arranged on the pull rod, the inner diameter of the launching cylinder is smaller than the outer diameter of the shearing table, and the outer diameter of the shearing table is smaller than the inner diameter of the straight guide groove. According to the invention, stable locking of the aircraft can be realized, and reliable pull-off of the aircraft during launching is realized.

Description

Technical Field

[0001] The invention relates to the technical field of multi-tube launching devices, and in particular provides a directional button pulling-off mechanism and a pulling-off method of a multi-tube launching device. Background Art

[0002] The directional button pull-off mechanism is a device that can realize automatic release of the directional button. It is a part of the locking device and is used for axial positioning and locking between aircraft. Similar pull-off mechanisms are also widely used in other mechanical systems that require automatic release, such as automatic lock trigger pop-up mechanism, detached plug passive pull-off mechanism, etc. The design of the directional button pull-off mechanism usually needs to meet the requirements of simple structure, high reliability, and easy operation to ensure that the release action can be completed quickly and safely under specific conditions.

[0003] For traditional aircraft, when the aircraft is launched, it rotates forward along the spiral guide groove of the aircraft so that the aircraft is in a rolling flight state when flying out of the aircraft. In the new technology iteration process, it is required to use the original aircraft with a spiral guide groove, and the aircraft is required to be fixed and locked before launching. It cannot roll during launching and can only fly out of the aircraft smoothly. Since multi-tube aircraft usually require stable bullet blocking locking and reliable locking pull-out, in order to better ensure the locking stability of the aircraft, achieve reliable pull-out when the aircraft is launched, reduce production costs, and lightweight structure, a new type of directional button pull-out mechanism for multi-tube launching device is needed. Summary of the invention

[0004] In order to solve the above problems, the present invention provides a directional button pulling-off mechanism and a pulling-off method for a multi-tube launching device.

[0005] The present invention provides a directional button pull-off mechanism of a multi-tube launcher, the launcher includes an aircraft, the aircraft includes a large diameter section and a small diameter section, the small diameter section is arranged on the tail side of the aircraft, the directional button pull-off mechanism includes a launch tube and a locking hoop; the launch tube is sleeved on the aircraft, a spiral guide groove and a straight guide groove are provided on the launch tube, and the straight guide groove is arranged on the tail side of the launch tube; The locking hoop is connected to the tail end of the aircraft, and a pull rod is connected to the locking hoop, and the pull rod is coplanar with the axial cross section of the straight guide groove; the end of the pull rod away from the locking hoop is connected to the aircraft through a shear screw; the end of the pull rod away from the locking hoop is provided with a shear table that can be accommodated in the straight guide groove and can slide in the straight guide groove, and the outer end of the shear screw away from the aircraft side includes a clamping section, and the clamping section is limited in the shear table; when the shear table slides from the straight guide groove to the spiral guide groove, the spiral groove wall of the spiral guide groove can limit the shear table and make the shear screw shear and unlock to form a second pull-off checkpoint so that the aircraft can be disengaged from the locking hoop and launched; The inner diameter of the launching tube is larger than the outer diameter of the locking hoop, the outer diameter of the locking hoop is larger than the outer diameter of the tail end of the aircraft, the locking hoop is sleeved on the tail end of the aircraft and is connected with the aircraft in a clearance fit; a limiting platform is provided at the inner end of the locking hoop, the outer diameter of the limiting platform is larger than the inner diameter of the launching tube; when the shearing platform slides in the straight guide groove to a position close to the spiral guide groove, the limiting platform is limited on the launching tube, thereby forming the first pulling-off checkpoint so that the aircraft can be pulled off the locking hoop and launched, and at this time the shearing screw is sheared under the force of the pull rod and the aircraft.

[0006] Furthermore, a connecting platform is provided at the small diameter section of the aircraft near the large diameter section, and a connecting hole for connecting a shear screw is opened on the connecting platform; the shearing platform includes a shearing hole connected to the connecting hole, the shearing hole is a stepped hole structure including a locking step, and the shearing hole specifically includes an inner hole close to the connecting hole and an outer hole located outside the inner hole, and the inner diameter of the outer hole is larger than the inner diameter of the inner hole; the locking step is formed by the bottom wall of the outer hole, and the locking section of the shear screw is limited on the locking step.

[0007] Furthermore, the shear screw also includes a shear section 1 located in the inner hole and a shear section 2 located in the connecting hole; the outer walls of the shear section 1 and the shear section 2 are both conical wall structures, the connection between the shear section 1 and the shear section 2 is the connecting section, the outer diameter of the outer wall of the shear section 1 and the outer diameter of the outer wall of the shear section 2 both gradually decrease toward the connecting section; the outer diameter of the connecting section is the smallest outer diameter of the shear screw; when the shearing table slides from the straight guide groove to the spiral guide groove, the spiral groove wall of the spiral guide groove can limit the shearing table and allow the shear screw to be sheared at the connecting section.

[0008] Furthermore, a bearing section 1 is included between the shearing section 1 and the clamping section, and a bearing section 2 is included on the inner side of the shearing section 2; the bearing section 1 and the bearing section 2 are both cylindrical structures, the bearing section 1 is threadedly connected to the inner hole, and the bearing section 2 is threadedly connected to the connecting hole.

[0009] Furthermore, the inner diameter of the launching tube is smaller than the outer diameter of the shearing table, and the outer diameter of the shearing table is smaller than the inner diameter of the straight guide groove.

[0010] Furthermore, two limit platforms are symmetrically arranged on the locking hoop and two connecting platforms are symmetrically arranged on the aircraft. The pull rod includes two rods respectively connected between the two limit platforms and the two connecting platforms. The shear screw includes two rods respectively installed on the two pull rods. The pull rod is fastened to the locking hoop through the limit platforms. The two pull rods are respectively arranged corresponding to the two straight guide grooves, and the axial cross-sections of the two pull rods and the two straight guide grooves are coplanar.

[0011] A method for pulling off a directional button pulling off mechanism of a multi-tube launcher, wherein the outer diameter of the connecting section is calculated to achieve shearing of the shear screw at the connecting section, assuming that the outer diameter of the connecting section is d1, and the outer diameters of the first and second bearing sections are d2, then d2>d1; the pulling force that each pull rod can withstand is F1, the destructive force that the shearing platform on each pull rod can withstand is F2, and the thrust generated when the aircraft starts to fly is F3; Then F1 should satisfy: F1>F3 / 2. At this time, under the action of thrust F3, the tie rod is not broken and the shear screw is broken. The denominator 2 here is the number of tie rods, that is, two tie rods. Then d1 should satisfy: , ; Where τ is the allowable shear stress of the material used for the shear screw.

[0012] Furthermore, assuming that the maximum destructive force that the actual measured limit shearing table can withstand is F4, F2=F4*k; wherein k is the safety factor, and the value of k is 0.5 to 0.8.

[0013] Furthermore, when the pulling-off is achieved at the first pulling-off checkpoint, the following steps are included: S1: The aircraft starts, and the shearing table slides along the straight guide groove. At this time, the pull rod and the locking hoop move in the direction of the aircraft. S2: When the shearing table approaches the spiral guide groove, the limit table blocks the end of the launch tube. At this time, the locking hoop and the pull rod no longer move, and the locking hoop is separated from the aircraft. S3: As the aircraft continues to work, the force of the aircraft's movement is applied to the shear segment 2 and the load-bearing segment 2 of the shear screw through the connecting platform. Since the locking hoop restricts the pull rod from moving forward, the pulling force of the pull rod is applied to the clamping segment, shear segment 1 and load-bearing segment 1 of the shear screw through the shear platform, and the shear screw is sheared at the connecting segment.

[0014] Furthermore, when the pulling-off is not achieved at the first pulling-off checkpoint, but is achieved at the second pulling-off checkpoint, the following steps are included: S1: The aircraft starts, and the shearing table slides along the straight guide groove. At this time, the pull rod and the locking hoop move in the direction of the aircraft; S2: When the limiter fails, when the shearing table enters the spiral guide groove, the spiral groove wall of the spiral guide groove prevents the shearing table and the aircraft from moving forward synchronously. At this time, the locking hoop and the pull rod no longer move forward, and the aircraft is separated from the locking hoop; S3: As the aircraft continues to work, the force of the aircraft's movement is applied to the shearing section 2 and the load-bearing section 2 of the shearing screw through the connecting platform, and the pulling force of the pull rod is applied to the clamping section, shearing section 1 and the load-bearing section 1 of the shearing screw through the shearing platform, and the shearing screw is sheared at the connecting section.

[0015] Compared with the prior art, the present invention can achieve the following beneficial effects: It is mainly suitable for locking the aircraft in the multi-tube launcher and can realize reliable unlocking when launching the aircraft. The aircraft is fixed in the aircraft of the multi-tube launcher by shear screws, pull rods and locking hoops. While meeting the requirements of bullet blocking and locking, it can effectively solve the problem of the aircraft being equipped with traditional aircraft with spiral guide grooves, and can stably realize the ability of locking (directional button) pulling out when the aircraft is launched.

[0016] 1. Since the directional button pull-off mechanism of the present invention is installed at the tail of the aircraft, the integrity of the aircraft is guaranteed; the aircraft of the multi-tube launcher is mostly wound with non-metallic materials, which avoids opening a hole in the middle of the aircraft, which can greatly improve the processability of the aircraft processing and effectively improve the strength of the aircraft.

[0017] 2. The present invention can accurately ensure the locking force of the aircraft by controlling the material of the shear screw or the diameter of the shearing part, can stably realize the ability of the locking (directional button) to be pulled off, and greatly reduces the production cost of the product.

[0018] 3. The present invention has a simple structure and reliable function. The locking hoop can also be designed to be lightweight according to actual conditions, thus providing a new structural mode for the design of the bullet blocking locking mechanism of the multi-tube launcher.

[0019] Since multi-tube aircraft usually require stable bullet-blocking locking and reliable locking and pulling out, in order to better ensure the locking stability of the aircraft, achieve reliable pulling out when the aircraft is launched, and reduce production costs, the structure is lightweight. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 Schematic diagram of the structure of the directional button pull-off mechanism provided according to an embodiment of the present invention Figure 1 ; Figure 2 Schematic diagram of the structure of the directional button pull-off mechanism provided according to an embodiment of the present invention Figure 2 (launch tube not shown); Figure 3 yes Figure 2 A partial enlarged view of point B in the middle; Figure 4 It is a schematic diagram of the partial structure of a pull rod in a directional button pulling mechanism provided according to an embodiment of the present invention; Figure 5 yes Figure 2 A front view of Figure 6 yes Figure 5 Sectional view in the AA direction; Figure 73 is a schematic diagram of the structure of the shear screw in the directional button pull-off mechanism provided according to an embodiment of the present invention, wherein d1 is the outer diameter of the connecting section, and d2 is the outer diameter of the bearing section 1 and the bearing section 2.

[0021] The figure marks include: aircraft 1, large diameter section 2, small diameter section 3, launching tube 4, locking hoop 5, spiral guide groove 6, straight guide groove 7, pull rod 8, shear screw 9, shear platform 10, shear hole 11, clamping section 12, limit platform 13, connecting platform 14, connecting hole 15, clamping step 16, outer hole 17, inner hole 18, shearing section one 19, shearing section two 20, connecting section 21, load-bearing section one 22, load-bearing section two 23. DETAILED DESCRIPTION

[0022] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the following Figure 1-7 It should be understood that the specific embodiments described herein are only used to explain the present invention and do not constitute a limitation of the present invention.

[0023] A directional button pull-off mechanism for a multi-tube launcher, such as Figure 1 , Figure 2 As shown, the launching device includes an aircraft 1, and the aircraft 1 includes a large diameter section 2 and a small diameter section 3. The small diameter section 3 is arranged on the tail side of the aircraft 1. The directional button pulling mechanism includes a launching tube 4 and a locking hoop 5. The launching tube 4 is sleeved on the aircraft 1, and the locking hoop 5 is sleeved on the tail end of the aircraft 1 and is connected with the aircraft 1 with a clearance fit. A spiral guide groove 6 and a straight guide groove 7 are opened on the launching tube 4, and the straight guide groove 7 is arranged on the tail side of the launching tube 4. The locking hoop 5 is connected to the tail end of the aircraft 1.

[0024] The locking hoop 5 is connected with a pull rod 8, and the end of the pull rod 8 away from the locking hoop 5 is connected to the aircraft 1 through a shear screw 9. The shear screw 9 is made of high-strength steel. The end of the pull rod 8 away from the locking hoop 5 is provided with a shearing table 10 that can be accommodated in the straight guide groove 7 and can slide in the straight guide groove 7. The small diameter section 3 of the aircraft 1 is close to the large diameter section 2. A connecting table 14 is provided on the connecting table 14. A connecting hole 15 for connecting the shear screw 9 is opened. The shearing table 10 includes a shearing hole 11 connected to the connecting hole 15, and the shearing hole 11 includes Figure 4 The stepped hole structure of the locking step 16 is shown in the figure, the shear hole 11 specifically includes an inner hole 18 close to the connecting hole 15 and an outer hole 17 located outside the inner hole 18, the inner diameter of the outer hole 17 is larger than the inner diameter of the inner hole 18, the locking step 16 is formed by the bottom wall of the outer hole 17, the outer end of the shear screw 9 away from the side of the aircraft 1 includes a locking section 12, the locking section 12 is limited in the shear platform 10, and specifically the locking section 12 of the shear screw 9 is limited on the locking step 16.

[0025] The shear screw 9 also includes a shearing section 19 located in the inner hole 18 and a shearing section 20 located in the connecting hole 15. The outer walls of the shearing section 19 and the shearing section 20 are both conical wall structures. The connection between the shearing section 19 and the shearing section 20 is a connecting section 21. The outer diameters of the outer walls of the shearing section 19 and the outer diameters of the outer walls of the shearing section 20 gradually decrease toward the connecting section 21. The outer diameter of the connecting section 21 is the smallest point of the outer diameter of the shear screw 9. A bearing section 22 is included between the shearing section 19 and the clamping section 12. The inner side of the shearing section 20, that is, the side of the shearing section 20 away from the shearing section 12, includes a bearing section 23. The bearing section 122 and the bearing section 23 are both columnar structures. The bearing section 122 is threadedly connected to the inner hole 18, and the bearing section 23 is threadedly connected to the connecting hole 15. The structural design of the shear screw 9 can ensure the stability of the connection and realize that the shear screw 9 can be sheared smoothly when needed. The specific structure of the shear screw 9 is as follows Figure 7 As shown, the connection position of the shear screw 9 is as follows Figure 6 shown.

[0026] The inner diameter of the launching tube 4 is larger than the outer diameter of the locking hoop 5, the outer diameter of the locking hoop 5 is larger than the outer diameter of the tail end of the aircraft 1, a limiting platform 13 is provided at the inner end of the locking hoop 5, the outer diameter of the limiting platform 13 is larger than the inner diameter of the launching tube 4, the inner diameter of the launching tube 4 is smaller than the outer diameter of the shearing platform 10, the outer diameter of the shearing platform 10 is smaller than the inner diameter of the straight guide groove 7, and the shearing platform 10 can limit the shaking of the aircraft 1 during transportation and storage.

[0027] Two limit platforms 13 are symmetrically arranged on the locking hoop 5, and two connecting platforms 14 are symmetrically arranged on the aircraft 1. The pull rod 8 includes two rods connected between the two limit platforms 13 and the two connecting platforms 14 respectively. The shear screw 9 includes two rods installed at the two pull rods 8 respectively. The pull rod 8 is fastened to the locking hoop 5 through the limit platforms 13. The two pull rods 8 are respectively arranged corresponding to the two straight guide grooves 7. The axial cross-sections of the pull rod 8 and the straight guide groove 7 are coplanar. The axial direction is as follows Figure 5 In the direction shown in M, the axial cross-sections of the two tie rods 8 and the two straight guide grooves 7 are coplanar, which can ensure the stability of the connection of the tie rod 8, so that the shearing table 10 can slide stably in the straight guide groove 7, providing protection for the subsequent twisting and pulling of the aircraft. When the shearing table 10 slides in the straight guide groove 7 to the spiral guide groove 6, the spiral groove wall of the spiral guide groove 6 can limit the shearing table 10 and allow the shear screw 9 to be sheared at the connecting section 21.

[0028] During storage and transportation of the aircraft 1, the aircraft 1 is confined in the straight guide groove 7 by the shear table 10 and the shear screw 9 on the pull rod 8. The internal force generated between the aircraft 1 and the launching tube 4 is smaller than the bullet-blocking locking force of the shear screw 9, thereby ensuring that the shear screw 9 is not damaged. Therefore, no axial relative movement will occur between the aircraft 1 and the launching tube 4, and the locking requirements when the aircraft 1 is separated from the locking hoop 5 can be met.

[0029] During launch, the first pulling-off checkpoint: the aircraft 1 moves forward, driving the locking hoop 5 forward. When the shearing platform 10 slides in the straight guide groove 7 to a position close to the spiral guide groove 6, the limiting platform 13 is limited on the end of the launching tube 4. The locking hoop 5 hits the end of the launching tube and stops moving forward. The thrust generated by the nozzle acts on the locking hoop 5, pulling the pull rod 8 to apply force to the shear screw 9, which can stably realize the locking pulling-off, causing the aircraft 1 to lose the locking force. The aircraft 1 loses the axial constraint and flies forward, thereby forming the first pulling-off checkpoint, allowing the aircraft 1 to escape from the locking hoop 5 and be launched. At this time, the shear screw 9 is sheared under the force of the pull rod 8 and the aircraft 1.

[0030] The second pull-out checkpoint: when the shearing platform 10 slides from the straight guide groove 7 to the spiral guide groove 6, the spiral groove wall of the spiral guide groove 6 can limit the shearing platform 10 and enable the shearing screw 9 to be sheared and unlocked to form a second pull-out checkpoint, so that the aircraft 1 can be disengaged from the locking hoop 5 and launched, that is, when the limiting platform 13 is successfully limited on the launching tube 4 so that the aircraft 1 is successfully pulled out, the shearing platform 10 does not need to cooperate with the spiral guide groove 6 to shear the shearing screw 9. At this time, the shearing screw 9 is sheared by the force of the pull rod 8 and the aircraft. Only when the first pull-out checkpoint fails, the shearing platform 10 cooperates with the spiral guide groove 6 to shear the shearing screw 9. The second pull-out checkpoint can further ensure that the aircraft 1 can be reliably pulled out.

[0031] A method for pulling off a directional button pulling off mechanism of a multi-tube launcher, wherein the outer diameter of the connecting section 21 is calculated to achieve shearing of the shear screw 9 at the connecting section 21, assuming that the outer diameter of the connecting section 21 is d1, and the outer diameters of the first bearing section 22 and the second bearing section 23 are d2, then d2>d1; the pulling force that each pull rod 8 can withstand is F1, the destructive force that the shearing platform 10 on each pull rod 8 can withstand is F2, and the thrust generated when the aircraft starts to fly is F3; Then F1 should satisfy: F1>F3 / 2. At this time, under the action of thrust F3, the tie rod 8 is not broken and the shear screw 9 is broken. The denominator 2 here is the number of tie rods, that is, two tie rods. Then d1 should satisfy: , ; Here, τ is the allowable shear stress of the material used for the shear screw 9, which ensures that the connecting section 21 is not easily damaged and is sheared off under the action of the corresponding force.

[0032] Here, F2 is proposed for the shearing table 9 on the tie rod 8, and is related to the materials of the tie rod 8 and the shearing table 9. F3 is proposed for the thrust of the aircraft. The values ​​of F2 and F3 are related to the material strength and the thrust size. The value of F2 may be greater than F3, or it may be less than F3.

[0033] Assume that the maximum destructive force that the limit shearing table 10 can withstand is actually measured to be F4, and F2=F4*k; wherein, k is a safety factor, and the value of k is 0.5 to 0.8, to ensure that the limit shearing table 10 does not reach the maximum destructive force F4 and will not be damaged, while leaving space for the value of d1 of the shearing screw 9.

[0034] When the pull-off is achieved at the first pull-off checkpoint, the following steps are included: S1: The aircraft 1 starts, and the shearing table 10 slides along the straight guide groove 7. At this time, the pull rod 8 and the locking hoop 5 move in the direction of the aircraft 1. The direction of the aircraft 1 is as follows: Figure 2 As shown in the F direction.

[0035] S2: When the shearing platform 10 approaches the spiral guide groove 6, the limiting platform 13 blocks the end of the launching tube 4. At this time, the locking hoop 5 and the pull rod 8 no longer move, and the locking hoop 5 is separated from the aircraft 1.

[0036] S3: As the aircraft 1 continues to work, the force of the aircraft 1 moving is applied to the shearing section 20 and the load-bearing section 2 23 of the shearing screw 9 through the connecting platform 14. Since the locking hoop 5 restricts the pull rod 8 from moving forward, the pulling force of the pull rod 8 is applied to the clamping section 12, the shearing section 19 and the load-bearing section 1 22 of the shearing screw 9 through the shearing platform 10, and the shearing screw 9 is sheared at the connecting section 21.

[0037] When the pulling-off is not achieved at the first pulling-off checkpoint, and the pulling-off is achieved at the second checkpoint, the method includes the following steps: S1: the aircraft 1 is started, and the shearing table 10 slides along the straight guide groove 7. At this time, the pull rod 8 and the locking hoop 5 move along the moving direction of the aircraft 1.

[0038] S2: When the limit plate 13 fails to limit, when the shearing plate 10 enters the spiral guide groove 6, the spiral groove wall of the spiral guide groove 6 prevents the shearing plate 10 and the aircraft 1 from moving forward synchronously. At this time, the locking hoop 5 and the pull rod 8 no longer move forward, and the aircraft 1 is separated from the locking hoop 5.

[0039] S3: As the aircraft 1 continues to work, the force of the aircraft 1 moving is applied to the shearing section 20 and the load-bearing section 2 23 of the shearing screw 9 through the connecting platform 14, and the pulling force of the pull rod 8 is applied to the clamping section 12, the shearing section 19 and the load-bearing section 1 22 of the shearing screw 9 through the shearing platform 10, and the shearing screw 9 is sheared at the connecting section 21.

[0040] Although the embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and cannot be understood as limiting the present invention. Those skilled in the art may change, modify, replace and modify the above embodiments within the scope of the present invention.

Claims

1. A directional button pulling mechanism for a multi-tube launching device, the launching device comprising an aircraft, the aircraft comprising a large diameter section and a small diameter section, the small diameter section being arranged at the tail side of the aircraft, characterized in that: The directional button pulling mechanism comprises a launching tube and a locking hoop; the launching tube is sleeved on the aircraft, and a spiral guide groove and a straight guide groove are provided on the launching tube, and the straight guide groove is provided on the tail side of the launching tube; The locking hoop is connected to the tail end of the aircraft, and a pull rod is connected to the locking hoop, and the pull rod is coplanar with the axial cross section of the straight guide groove; the end of the pull rod away from the locking hoop is connected to the aircraft through a shear screw; the end of the pull rod away from the locking hoop is provided with a shear table that can be accommodated in the straight guide groove and can slide in the straight guide groove, and the outer end of the shear screw away from the aircraft side includes a clamping section, and the clamping section is limited in the shear table; when the shear table slides from the straight guide groove to the spiral guide groove, the spiral groove wall of the spiral guide groove can limit the shear table and make the shear screw shear and unlock to form a second pull-off checkpoint so that the aircraft can be disengaged from the locking hoop and launched; The inner diameter of the launching tube is larger than the outer diameter of the locking hoop, the outer diameter of the locking hoop is larger than the outer diameter of the tail end of the aircraft, the locking hoop is sleeved on the tail end of the aircraft and is connected with the aircraft in a clearance fit; a limiting platform is provided at the inner end of the locking hoop, the outer diameter of the limiting platform is larger than the inner diameter of the launching tube; when the shearing platform slides in the straight guide groove to a position close to the spiral guide groove, the limiting platform is limited on the launching tube, thereby forming the first pulling-off checkpoint so that the aircraft can be pulled off the locking hoop and launched, and at this time the shearing screw is sheared under the force of the pull rod and the aircraft.

2. The directional button pulling mechanism of the multi-tube launching device according to claim 1, characterized in that: A connecting platform is provided at the small diameter section of the aircraft near the large diameter section, and a connecting hole for connecting a shear screw is opened on the connecting platform; the shearing platform includes a shearing hole connected to the connecting hole, the shearing hole is a stepped hole structure including a locking step, and the shearing hole specifically includes an inner hole close to the connecting hole and an outer hole located outside the inner hole, and the inner diameter of the outer hole is larger than the inner diameter of the inner hole; the locking step is formed by the bottom wall of the outer hole, and the locking section of the shear screw is limited on the locking step.

3. The directional button pulling mechanism of the multi-tube launching device according to claim 2, characterized in that: The shear screw also includes a shear section 1 located in the inner hole and a shear section 2 located in the connecting hole; the outer walls of the shear section 1 and the shear section 2 are both conical wall structures, the connection between the shear section 1 and the shear section 2 is the connecting section, the outer diameter of the outer wall of the shear section 1 and the outer diameter of the outer wall of the shear section 2 both gradually decrease toward the connecting section; the outer diameter of the connecting section is the smallest outer diameter of the shear screw; when the shearing platform slides from the straight guide groove to the spiral guide groove, the spiral groove wall of the spiral guide groove can limit the shearing platform and allow the shear screw to be sheared at the connecting section.

4. The directional button pulling mechanism of the multi-tube launching device according to claim 3, characterized in that: The shearing section 1 includes a bearing section 1 between the shearing section 1 and the clamping section, and the inner side of the shearing section 2 includes a bearing section 2; the bearing section 1 and the bearing section 2 are both cylindrical structures, the bearing section 1 is threadedly connected to the inner hole, and the bearing section 2 is threadedly connected to the connecting hole.

5. The directional button pulling mechanism of the multi-tube launching device according to claim 4, characterized in that: The inner diameter of the launching tube is smaller than the outer diameter of the shearing table, and the outer diameter of the shearing table is smaller than the inner diameter of the straight guide groove.

6. The directional button pulling mechanism of the multi-tube launching device according to claim 5, characterized in that: Two limit platforms are symmetrically arranged on the locking hoop, and two connecting platforms are symmetrically arranged on the aircraft. The pull rod includes two rods respectively connected between the two limit platforms and the two connecting platforms. The shear screw includes two rods respectively installed on the two pull rods. The pull rod is fastened to the locking hoop through the limit platforms. The two pull rods are respectively arranged corresponding to the two straight guide grooves, and the axial cross-sections of the two pull rods and the two straight guide grooves are coplanar.

7. A method for pulling off a directional button pulling off mechanism of a multi-tube launcher, wherein the outer diameter of the connecting section in claim 6 is calculated to achieve shearing of the shear screw at the connecting section, characterized in that: Assuming the outer diameter of the connecting section is d1, and the outer diameters of the load-bearing section 1 and the load-bearing section 2 are d2, then d2>d1; the pulling force that each tie rod can withstand is F1, the destructive force that the shearing table on each tie rod can withstand is F2, and the thrust generated when the aircraft starts to fly is F3; Then F1 should satisfy: F1>F3 / 2. At this time, under the action of thrust F3, the tie rod is not broken and the shear screw is broken. The denominator 2 here is the number of tie rods, that is, two tie rods. Then d1 should satisfy: 、 ； Where τ is the allowable shear stress of the material used for the shear screw.

8. The method for pulling off the directional button pulling off mechanism of the multi-tube launching device according to claim 7, characterized in that: Assume that the maximum destructive force that the actual measured limit shear table can withstand is F4, F2=F4*k; where k is the safety factor, and the value of k is 0.5 to 0.

8.

9. The method for pulling off the directional button pulling off mechanism of the multi-tube launching device according to claim 8, characterized in that: When the pull-off is achieved at the first pull-off checkpoint, the following steps are included: S1: The aircraft starts, and the shearing table slides along the straight guide groove. At this time, the pull rod and the locking hoop move in the direction of the aircraft. S2: When the shearing table approaches the spiral guide groove, the limit table blocks the end of the launch tube. At this time, the locking hoop and the pull rod no longer move, and the locking hoop is separated from the aircraft. S3: As the aircraft continues to work, the force of the aircraft's movement is applied to the shear segment 2 and the load-bearing segment 2 of the shear screw through the connecting platform. Since the locking hoop restricts the pull rod from moving forward, the pulling force of the pull rod is applied to the clamping segment, shear segment 1 and load-bearing segment 1 of the shear screw through the shear platform, and the shear screw is sheared at the connecting segment.

10. The method for pulling off the directional button pulling off mechanism of the multi-tube launching device according to claim 9, characterized in that: When the pulling-off is not achieved at the first pulling-off checkpoint, and the pulling-off is achieved at the second checkpoint, the method includes the following steps: S1: The aircraft starts, and the shearing table slides along the straight guide groove. At this time, the pull rod and the locking hoop move in the direction of the aircraft; S2: When the limiter fails, when the shearing table enters the spiral guide groove, the spiral groove wall of the spiral guide groove prevents the shearing table and the aircraft from moving forward synchronously. At this time, the locking hoop and the pull rod no longer move forward, and the aircraft is separated from the locking hoop; S3: As the aircraft continues to work, the force of the aircraft's movement is applied to the shearing section 2 and the load-bearing section 2 of the shearing screw through the connecting platform, and the pulling force of the pull rod is applied to the clamping section, shearing section 1 and the load-bearing section 1 of the shearing screw through the shearing platform, and the shearing screw is sheared at the connecting section.

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