Orientation button pulling-off mechanism and pulling-off method for multi-tube launching device

Abstract

The present invention relates to the technical field of multi-tube launching devices, and specifically discloses an orientation button pulling-off mechanism and a pulling-off method for a multi-tube launching device. The launching device includes an aircraft, which includes a large-diameter section and a small-diameter section. The orientation button pulling-off mechanism includes a launching tube and a locking hoop. The launching tube is sleeved on the aircraft. A spiral guide groove and a straight guide groove are provided on the launching tube. The locking hoop is connected to the tail end of the aircraft. A pull rod is connected to the locking hoop. One end of the pull rod away from the locking hoop is connected to the aircraft through a shear screw. The inner diameter of the launching tube 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 platform is provided at the inner end of the locking hoop, and a shear platform is provided on the pull rod. The inner diameter of the launching tube is smaller than the outer diameter of the shear platform, and the outer diameter of the shear platform is smaller than the inner diameter of the straight guide groove. The present invention can achieve stable locking of the aircraft and reliable pulling-off during the launch of the aircraft.

Description

Technical Field

[0001] The present invention relates to the technical field of multi-tube launching devices, and specifically provides an orientation button pulling-off mechanism and a pulling-off method for a multi-tube launching device. Background Art

[0002] The orientation button pulling-off mechanism is a device that can realize the automatic release of the orientation button. It belongs to a part of the locking device and is used for axial positioning and locking between aircraft. Similar pulling-off mechanisms are also widely used in other mechanical systems that require automatic release, such as automatic lock trigger ejection mechanisms, passive pulling-off mechanisms for shedding plugs, etc. The design of the orientation button pulling-off mechanism usually needs to meet requirements such as simple structure, high reliability, and convenient 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 process of new technology iteration, it is required to use the original aircraft with a spiral guide groove, and at the same time, the aircraft needs to be fixed and locked before launch, and it cannot roll during launch, but can only fly out of the aircraft smoothly. Since multi-tube aircraft usually require stable bullet-blocking locking and reliable locking pulling-off, in order to better ensure the locking stability of the aircraft, achieve reliable pulling-off during aircraft launch, reduce production costs, and make the structure lightweight, a new type of orientation button pulling-off mechanism for a multi-tube launching device is needed. Summary of the Invention

[0004] The present invention provides an orientation button pulling-off mechanism and a pulling-off method for a multi-tube launching device to solve the above problems.

[0005] An orientation button pulling-off mechanism for a multi-tube launching device provided by the present invention, the launching device 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, and the orientation button pulling-off mechanism includes 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 opened on the launching tube, and the straight guide groove is arranged on the tail side of the launching tube;

[0006] The locking hoop is connected to the tail end of the aircraft, a pull rod is connected to the locking hoop, and the axial cross-section of the pull rod is coplanar with the straight guide groove; one end of the pull rod away from the locking hoop is connected to the aircraft through a shear screw; a shear table that can be accommodated in the straight guide groove and can slide in the straight guide groove is provided at one end of the pull rod away from the locking hoop, and the outer end of the shear screw on the side away from the aircraft includes a clamping section, and the clamping section is limited in the shear table; when the shear table slides in the straight guide groove into the spiral guide groove, the spiral groove wall of the spiral guide groove can limit the shear table and cause the shear screw to shear and unlock to form a second pulling-off checkpoint, so that the aircraft is disengaged from the locking hoop and launched;

[0007] The inner diameter of the launcher tube 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. The locking hoop is sleeved on the tail end of the aircraft and is connected with the aircraft in a clearance fit manner. A limiting platform is arranged at the inner end of the locking hoop, and the outer diameter of the limiting platform is larger than the inner diameter of the launcher tube. When the shearing platform slides in the straight guide groove to be close to the spiral guide groove, the limiting platform is limited on the launcher tube, thereby forming the first pull-off checkpoint to enable the aircraft to be disengaged from the locking hoop and launched. At this time, the shearing screw is sheared under the force applied by the pull rod and the aircraft.

[0008] Further, a connecting platform is provided at the small-diameter section of the aircraft near the large-diameter section, and a connecting hole for connecting the shearing screw is opened on the connecting platform. The shearing platform includes a shearing hole communicated with the connecting hole. The shearing hole is a stepped hole structure including a clamping step. Specifically, the shearing hole includes an inner hole close to the connecting hole and an outer hole located outside the inner hole. The inner diameter of the outer hole is larger than the inner diameter of the inner hole. The clamping step is formed by the bottom wall of the outer hole, and the clamping section of the shearing screw is limited on the clamping step.

[0009] Further, the shearing screw further includes a first shearing section located in the inner hole and a second shearing section located in the connecting hole. The outer walls of the first shearing section and the second shearing section are both conical wall structures. The connection part between the first shearing section and the second shearing section is a connecting section. The outer diameter of the outer wall of the first shearing section and the outer diameter of the outer wall of the second shearing section are gradually reduced towards the connecting section. The outer diameter of the connecting section is the smallest outer diameter of the shearing screw. When the shearing platform slides in the straight guide groove into the spiral guide groove, the spiral groove wall of the spiral guide groove can limit the shearing platform and enable the shearing screw to be sheared at the connecting section.

[0010] Further, a first bearing section is included between the first shearing section and the clamping section, and a second bearing section is included inside the second shearing section. Both the first bearing section and the second bearing section are cylindrical structures. The first bearing section is threadedly connected in the inner hole, and the second bearing section is threadedly connected in the connecting hole.

[0011] Further, the inner diameter of the launcher tube is smaller than the outer diameter of the shearing platform, and the outer diameter of the shearing platform is smaller than the inner diameter of the straight guide groove.

[0012] Further, two limiting platforms are symmetrically arranged on the locking hoop, two connecting platforms are symmetrically arranged on the aircraft, the pull rod includes two respectively connected between the two limiting platforms and the two connecting platforms, the shearing screw includes two respectively installed at the two pull rods, and the pull rod is tightly connected with the locking hoop through the limiting platform; 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.

[0013] A pulling-off method for the pulling-off mechanism of the orientation knob of a multi-tube launching device, calculating the outer diameter of the above-mentioned connecting section to enable the shear screw to be sheared at the connecting section. Let the outer diameter of the connecting section be d1, and the outer diameters of the first load-bearing section and the second load-bearing section be d2, then d2 > d1; the tensile force that each pull rod can withstand is F1, the destructive force that the shear platform on each pull rod can withstand is F2, and the thrust generated when the aircraft starts to fly is F3;

[0014] Then F1 should satisfy: F1 > F3 / 2. At this time, under the action of the thrust F3, the pull rod is not broken and the shear screw is broken. The denominator 2 here is the number of pull rods, that is, two pull rods;

[0015] Then d1 should satisfy:

[0016] 、 ;

[0017] where τ is the allowable shear stress of the material used for the shear screw.

[0018] Furthermore, let the maximum destructive force that the actually measured limit shear platform can withstand be F4, and F2 = F4*k; where k is the safety factor, and k ranges from 0.5 to 0.8.

[0019] Furthermore, when the pulling-off is achieved at the first pulling-off checkpoint, it includes the following steps:

[0020] S1: The aircraft starts, and the shear platform slides along the straight guide groove. At this time, the pull rod and the locking hoop both move along the advancing direction of the aircraft;

[0021] S2: When the shear platform approaches the spiral guide groove, the limit platform blocks the end of the launch tube. At this time, the locking hoop and the pull rod no longer advance, and the locking hoop is disengaged from the aircraft;

[0022] S3: As the aircraft continues to operate, the force of the aircraft's advancement is applied to the second shear section and the second load-bearing section of the shear screw through the connecting platform. Since the locking hoop restricts the pull rod from advancing further, the tensile force of the pull rod is applied to the clamping section, the first shear section and the first load-bearing section of the shear screw through the shear platform, and the shear screw is sheared at the connecting section.

[0023] Furthermore, when the pulling-off is not achieved at the first pulling-off checkpoint and the pulling-off is achieved at the second checkpoint, it includes the following steps:

[0024] S1: The aircraft starts, and the shear platform slides along the straight guide groove. At this time, the pull rod and the locking hoop both move along the advancing direction of the aircraft;

[0025] S2: When the limit of the limit platform fails and the shearing table enters the spiral guide groove, the spiral groove wall of the spiral guide groove prevents the shearing table from advancing synchronously with the aircraft. At this time, the locking hoop and the pull rod no longer move forward, and the aircraft is disengaged from the locking hoop.

[0026] S3: As the aircraft continues to operate, the force of the aircraft's advancement is applied to the second shearing section and the second bearing section of the shearing screw through the connecting platform. The pulling force of the pull rod is applied to the clamping section, the first shearing section, and the first bearing section of the shearing screw through the shearing table, and the shearing screw is sheared at the connecting section.

[0027] Compared with the prior art, the present invention can achieve the following beneficial effects:

[0028] It is mainly suitable for the locking of the aircraft in the multi-tube launcher, and can reliably unlock when launching the aircraft. The aircraft is fixed in the aircraft of the multi-tube launcher through the shearing screw, the pull rod, and the locking hoop. While meeting the requirements of bullet blocking and locking, it can effectively solve the problem of the aircraft being used with a traditional aircraft with a spiral guide groove, and can stably achieve the ability to pull off the locking (orientation button) when the aircraft is launched.

[0029] 1. Since the orientation button pull-off mechanism of the present invention is installed at the tail of the aircraft, the integrity of the aircraft is ensured; most of the aircraft of the multi-tube launcher are wound with non-metallic materials. After avoiding opening holes in the middle of the aircraft, the processing technology of the aircraft can be greatly improved and the strength of the aircraft can be effectively increased.

[0030] 2. Since the present invention can accurately ensure the locking force of the aircraft by controlling the material or the diameter of the shearing part of the shearing screw, it can stably achieve the ability to pull off the locking (orientation button), and greatly reduces the production cost of the product.

[0031] 3. The structure of the present invention is simple and reliable in action. The locking hoop can also be designed to be lightweight according to actual conditions, providing a new structural mode for the design of the bullet-blocking locking mechanism of the multi-tube launcher.

[0032] Since multi-tube aircraft usually require stable bullet-blocking locking and reliable locking pull-off, in order to better ensure the stable locking of the aircraft, achieve reliable pull-off when the aircraft is launched, reduce production costs, and make the structure lightweight. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 is a schematic structural diagram of the orientation button pull-off mechanism provided by an embodiment of the present invention Figure 1 ;

[0034] Figure 2 is a schematic structural diagram of the orientation button pull-off mechanism provided by an embodiment of the present invention Figure 2 (The launch tube is not shown);

[0035] Figure 3 is Figure 2 the partial enlarged view at position B in

[0036] Figure 4 is the partial structural schematic diagram of the pull rod in the orientation button pull-off mechanism provided by the embodiment of the present invention;

[0037] Figure 5 is Figure 2 the front view of

[0038] Figure 6 is Figure 5 the sectional view in the A-A direction in

[0039] Figure 7 is the structural schematic diagram of the shear screw in the orientation button pull-off mechanism provided by the embodiment of the present invention, where d1 is the outer diameter of the connecting section and d2 is the outer diameter of the first load-bearing section and the second load-bearing section.

[0040] The reference numerals therein include: aircraft 1, large-diameter section 2, small-diameter section 3, launch tube 4, locking hoop 5, spiral guide groove 6, straight guide groove 7, pull rod 8, shear screw 9, shear table 10, shear hole 11, clamping section 12, limiting table 13, connecting table 14, connecting hole 15, clamping step 16, outer hole 17, inner hole 18, first shear section 19, second shear section 20, connecting section 21, first load-bearing section 22, second load-bearing section 23. Specific Embodiments

[0041] In order to make the objectives, technical solutions and advantages of the present invention clearer, the following further describes the present invention in detail with reference to the accompanying Figure 1-7 drawings and specific embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and do not constitute a limitation to the present invention.

[0042] An orientation button pull-off mechanism for a multi-tube launch device, as shown in Figure 1 、 Figure 2 , the launch device includes an aircraft 1, 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 orientation button pull-off mechanism includes a launch tube 4 and a locking hoop 5, the launch tube 4 is sleeved on the aircraft 1, the locking hoop 5 is sleeved on the tail end of the aircraft 1 and is connected with the aircraft 1 in a clearance fit manner, the launch tube 4 is provided with a spiral guide groove 6 and a straight guide groove 7, the straight guide groove 7 is arranged on the tail side of the launch tube 4, and the locking hoop 5 is connected to the tail end of the aircraft 1.

[0043] A pull rod 8 is connected to the locking hoop 5. One 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. One end of the pull rod 8 away from the locking hoop 5 is provided with a shear table 10 that can be accommodated in the straight guide groove 7 and can slide in the straight guide groove 7. A connecting table 14 is provided near the large-diameter section 2 of the small-diameter section 3 of the aircraft 1. A connecting hole 15 for connecting the shear screw 9 is opened on the connecting table 14. The shear table 10 includes a shear hole 11 communicating with the connecting hole 15. The shear hole 11 is a stepped hole structure including Figure 4 the clamping step 16 shown in. Specifically, the shear hole 11 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 that of the inner hole 18. The clamping step 16 is formed by the bottom wall of the outer hole 17. The outer end of the shear screw 9 on the side away from the aircraft 1 includes a clamping section 12. The clamping section 12 is limited within the shear table 10. Specifically, the clamping section 12 of the shear screw 9 is limited on the clamping step 16.

[0044] The shear screw 9 further includes a first shear section 19 located in the inner hole 18 and a second shear section 20 located in the connecting hole 15. The outer walls of the first shear section 19 and the second shear section 20 are both conical wall structures. The connection between the first shear section 19 and the second shear section 20 is a connecting section 21. The outer diameters of the outer walls of the first shear section 19 and the second shear section 20 gradually decrease towards the connecting section 21. The outer diameter of the connecting section 21 is the smallest outer diameter of the shear screw 9. Between the first shear section 19 and the clamping section 12 includes a first bearing section 22. The inner side of the second shear section 20, that is, the side of the second shear section 20 away from the first shear section 22, includes a second bearing section 23. Both the first bearing section 22 and the second bearing section 23 are cylindrical structures. The first bearing section 22 is threadedly connected in the inner hole 18. The second bearing section 23 is threadedly connected in the connecting hole 15. The structural design of the shear screw 9 can ensure the connection stability and can also achieve the smooth shearing of the shear screw 9 when needed. The specific structure of the shear screw 9 is as Figure 7 shown. The connection position of the shear screw 9 is as Figure 6 shown.

[0045] The inner diameter of the launch 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 table 13 is provided at the inner end of the locking hoop 5. The outer diameter of the limiting table 13 is larger than the inner diameter of the launch tube 4. The inner diameter of the launch tube 4 is smaller than the outer diameter of the shear table 10. The outer diameter of the shear table 10 is smaller than the inner diameter of the straight guide groove 7. The shear table 10 can limit the shaking of the aircraft 1 during transportation and storage.

[0046] There are two symmetrically arranged limiting platforms 13 on the locking hoop 5, and two symmetrically arranged connecting platforms 14 on the aircraft 1. The pull rod 8 includes two that are respectively connected between the two limiting platforms 13 and the two connecting platforms 14. The shear screw 9 includes two that are respectively installed at the two pull rods 8. The pull rod 8 is firmly connected to the locking hoop 5 through the limiting platform 13. The two pull rods 8 are respectively arranged corresponding to the two straight guide grooves 7. The axial cross-section of the pull rod 8 and the straight guide groove 7 is coplanar. The axial direction is as Figure 5 shown by the direction M in the figure. The axial cross-sections of the two pull rods 8 and the two straight guide grooves 7 are all coplanar, which can ensure the stability of the connection of the pull rod 8, so that the shear platform 10 slides stably in the straight guide groove 7, providing guarantee for the subsequent torsional pull-off of the aircraft, and when the shear platform 10 slides into the spiral guide groove 6 in the straight guide groove 7, the spiral groove wall of the spiral guide groove 6 can limit the shear platform 10 and cause the shear screw 9 to be sheared at the connecting section 21.

[0047] During the storage and transportation of the aircraft 1, the aircraft 1 is restricted in the straight guide groove 7 through the shear platform 10 and the shear screw 9 on the pull rod 8. The internal force generated between the aircraft 1 and the launch tube 4 is less than the bullet-blocking locking force of the shear screw 9, ensuring that the shear screw 9 is not damaged. Therefore, there will be no axial relative movement between the aircraft 1 and the launch tube 4. At this time, the locking requirement when the aircraft 1 breaks away from the locking hoop 5 can be met.

[0048] During launch, the first pull-off checkpoint: The forward movement of the aircraft 1 drives the locking hoop 5 to move forward. When the shear platform 10 slides to near the spiral guide groove 6 in the straight guide groove 7, the limiting platform 13 is limited on the end of the launch tube 4. The locking hoop 5 touches the end of the launch tube and stops moving forward. The thrust generated by the nozzle acts on the locking hoop 5, pulling the pull rod 8 and acting the force on the shear screw 9, which can stably achieve locking pull-off, causing the aircraft 1 to lose the locking force, and the aircraft 1 loses the axial constraint and flies forward, thus forming the first pull-off checkpoint to make the aircraft 1 break away from the locking hoop 5 and be launched. At this time, the shear screw 9 is sheared under the force applied by the pull rod 8 and the aircraft 1.

[0049] The second pull-off checkpoint: When the shear platform 10 slides into the spiral guide groove 6 in the straight guide groove 7, the spiral groove wall of the spiral guide groove 6 can limit the shear platform 10 and cause the shear screw 9 to be sheared and unlocked, forming the second pull-off checkpoint to make the aircraft 1 break away from the locking hoop 5 and be launched. That is, when the limiting platform 13 is successfully limited on the launch tube 4 and the aircraft 1 is successfully pulled off, the shear platform 10 does not need to cooperate with the spiral guide groove 6 to shear the shear screw 9. At this time, the shear screw 9 is sheared by the force applied by the pull rod 8 and the aircraft. Only when the first pull-off checkpoint fails, the shear platform 10 cooperates with the spiral guide groove 6 to realize the shearing of the shear screw 9. The second pull-off checkpoint can further ensure that the aircraft 1 can achieve reliable pull-off.

[0050] A pulling-off method for the pulling-off mechanism of the orientation knob of a multi-tube launching device, calculates the outer diameter of the above-mentioned connecting section 21 to achieve the shearing of the shear screw 9 at the connecting section 21. Let the outer diameter of the connecting section 21 be d1, and the outer diameters of the first load-bearing section 22 and the second load-bearing section 23 be d2, then d2 > d1; the tensile force that each pull rod 8 can withstand is F1, and the destructive force that the shear table 10 on each pull rod 8 can withstand is F2, and the thrust generated when the aircraft starts to fly is F3;

[0051] Then F1 should satisfy: F1 > F3 / 2. At this time, under the action of the thrust F3, the pull rod 8 is not broken and the shear screw 9 is broken. The denominator 2 here is the number of pull rods, that is, two pull rods;

[0052] Then d1 should satisfy:

[0053] 、 ;

[0054] where τ is the allowable shear stress of the material used for the shear screw 9, ensuring that the connecting section 21 is not easily damaged and is cut off under the action of the corresponding force.

[0055] Here, F2 is proposed for the shear table 9 on the pull rod 8 and is related to the materials of the pull rod 8 and the shear 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 magnitude of the thrust. The value of F2 may be greater than F3, or the value of F2 may be less than F3.

[0056] Let the actually measured maximum destructive force that the limit shear table 10 can withstand be F4, and F2 = F4 * k; where k is the safety factor, and k takes values from 0.5 to 0.8 to ensure that the limit shear table 10 does not reach the maximum destructive force F4 and will not be damaged, and at the same time leaves a value range for d1 of the shear screw 9.

[0057] When the pulling-off is achieved at the first pulling-off checkpoint, it includes the following steps:

[0058] S1: The aircraft 1 starts, and the shear table 10 slides along the straight guide groove 7. At this time, the pull rod 8 and the locking hoop 5 both move along the traveling direction of the aircraft 1; the traveling direction of the aircraft 1 is as Figure 2 shown by the F direction in

[0059] S2: When the shear table 10 approaches the spiral guide groove 6, the limit table 13 blocks the end of the launch tube 4. At this time, the locking hoop 5 and the pull rod 8 no longer move forward, and the locking hoop 5 is disengaged from the aircraft 1.

[0060] S3: As the aircraft 1 continues to operate, the force of the aircraft 1's advancement is applied to the second shear section 20 and the second bearing section 23 of the shear screw 9 through the connecting platform 14. Since the locking hoop 5 restricts the pull rod 8 from advancing further, the pulling force of the pull rod 8 is applied to the clamping section 12, the first shear section 19, and the first bearing section 22 of the shear screw 9 through the shear platform 10, and the shear screw 9 is sheared at the connecting section 21.

[0061] When the pull-off is not achieved at the first pull-off check point and is achieved at the second check point, the following steps are included:

[0062] S1: The aircraft 1 starts, and the shear platform 10 slides along the straight guide groove 7. At this time, both the pull rod 8 and the locking hoop 5 move along with the advancing direction of the aircraft 1.

[0063] S2: When the limit of the limit platform 13 fails, when the shear platform 10 enters the spiral guide groove 6, the spiral groove wall of the spiral guide groove 6 prevents the shear platform 10 from continuing to advance synchronously with the aircraft 1. At this time, both the locking hoop 5 and the pull rod 8 no longer continue to move forward, and the aircraft 1 is disengaged from the locking hoop 5.

[0064] S3: As the aircraft 1 continues to operate, the force of the aircraft 1's advancement is applied to the second shear section 20 and the second bearing section 23 of the shear screw 9 through the connecting platform 14. The pulling force of the pull rod 8 is applied to the clamping section 12, the first shear section 19, and the first bearing section 22 of the shear screw 9 through the shear platform 10, and the shear screw 9 is sheared at the connecting section 21.

[0065] Although the embodiments of the present invention have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as limitations on the present invention. Those of ordinary skill in the art can make changes, modifications, substitutions, and variations to 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: 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.

6. A method for pulling off a directional button pulling-off mechanism of a multi-tube launcher, applied to the directional button pulling-off mechanism of a multi-tube launcher as claimed in claim 5, wherein the outer diameter of the connecting section in claim 5 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.

7. The method for pulling off the directional button pulling off mechanism of the multi-tube launching device according to claim 6, 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 ranges from 0.5 to 0.

8.

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: 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.

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 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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