Launching box assembly and target launching method

Abstract

The invention provides a launching box assembly and a target launching method. The launch box assembly comprises a launch box, a restraint system and a buffer system, the restraint system comprises at least one guide rail and an adapter slidably arranged at the guide rail, the at least one guide rail is arranged on the inner wall of a box plate of the launch box, and the end, away from the guide rail, of the adapter is configured to be matched with a target in an inserted mode; the adapter is used for guiding the target and restraining rolling of the target during transportation and launching, is elastically arranged in the radial direction of the target and is used for being separated from the target when the target is separated from the launching box; the buffering system is arranged in the launching box and comprises at least two buffering pieces arranged in the circumferential direction of the target, and the ends, away from the inner wall of the launching box, of the buffering pieces are used for abutting against the side wall of the target during transportation and launching to guide and radially restrain the target. According to the application, the launching of the target can be guided and radially constrained on the basis of not arranging a sliding block, and the flight performance of the target can be improved.

Description

Technical Field

[0001] This application relates to the technical field of aircraft launch devices. Specifically, this application relates to a launch box assembly and a target launch method. Background Art

[0002] Currently, the launch methods of targets include box launch. Targets using box launch usually need to be provided with at least one slider on the surface of the target, and guide rails matching the sliders are arranged inside the launch box. After the engine of the target is ignited, the target leaves the box under the guidance of the sliders and the guide rails. In this solution, the reserved slider, as a protrusion on the target's outer shape, will sacrifice some flight performance of the target. Summary of the Invention

[0003] In view of the disadvantages of the existing method, this application proposes a launch box assembly and a target launch method to solve the technical problem that the sliders on the target in the related art affect the flight performance of the target.

[0004] In a first aspect, an embodiment of this application provides a launch box assembly, including: A launch box; A restraint system, including at least one guide rail extending along the length direction of the launch box and an adapter slidably arranged at the guide rail. At least one of the guide rails is arranged on the inner wall of at least one box panel of the launch box. The end of the adapter away from the guide rail is configured to be plugged and matched with the target, guide the target during transportation and launch, and restrain the roll of the target. And the adapter is elastically arranged along the radial direction of the target for separating from the target when the target leaves the launch box; A buffer system, arranged inside the launch box, including at least two buffer members arranged circumferentially around the target. The end of the buffer member away from the inner wall of the launch box is used to abut against or contact the side wall of the target during transportation and launch, guide the target, and restrain the radial direction of the target.

[0005] Optionally, the launch box includes a detachable upper box body and a lower box body; The number of the guide rails includes at least two. At least one of the guide rails is arranged on the top plate of the upper box body, and at least one of the guide rails is arranged on the bottom plate of the lower box body; The number of the buffer members includes at least four. At least one of the buffer members is arranged on the side plates of the upper box body and the lower box body respectively. The end of each buffer member away from the side plate points to the center line located at the center of the launch box and extending along the length direction of the launch box.

[0006] Optionally, the adapter includes a buffer body provided with a mounting hole, an elastic member disposed in the mounting hole, a top spring seat having a bottom abutting against the elastic member, and a cover fixed to the top of the mounting hole and covering the bottom of the top spring seat, wherein the top spring seat and the cover are slidably arranged; A limiting hole cooperating with the top spring seat is provided at the tail end of the target, and the top spring seat is configured to separate from the target under the action of the elastic member when the target disengages from the launch box.

[0007] Optionally, the buffer member includes a mounting frame, a mounting seat, and a buffer portion sequentially arranged from the side plate of the launch box towards the center line of the launch box. The mounting surface of the mounting seat and the buffer portion are inclined relative to a first plane parallel to the bottom plate. The buffer portion is made of an elastic material, and the end face of the buffer portion is an arc surface that gradually narrows from the end close to the mounting seat to the end far from the mounting seat.

[0008] Optionally, the launch box further includes a rear box cover assembly detachably connected to the upper box body and the lower box body, and the rear box cover assembly is configured to axially and circumferentially constrain the tail end of the target during transportation.

[0009] Optionally, the rear box cover assembly includes an axially limiting stop seat detachably arranged at the tail ends of the upper box body and the lower box body, a rudder surface fixing seat detachably arranged on the axially limiting stop seat, and a rear box cover detachably arranged outside the axially limiting stop seat; The rudder surface fixing seat is provided with a clamping groove for clamping the rudder surface of the target to limit the rudder surface at the tail end of the target during transportation, and the axially limiting stop seat is provided with a target locking interface seat for locking with the tail end of the target during transportation.

[0010] Optionally, the axially limiting stop seat includes a stop seat frame, mounting members arranged at the four corners of the baffle frame for detachably connecting with the upper box body and the lower box body, an annular structure arranged at the center of the stop seat frame and connected to the stop seat frame through a connecting rod, and a rudder surface fixing seat mounting plate arranged around the periphery of the annular structure. The target locking interface seat is arranged on the annular structure and penetrates through the side wall of the annular structure.

[0011] Optionally, the launch box assembly further includes a transportation limiting mechanism partially arranged in the launch box to radially limit the target during transportation, and the transportation limiting mechanism includes: A pressing plate detachably arranged on the top plate of the upper box body; A screw rod passing through and rotatably connected to the pressing plate, and the screw rod passes through the top plate of the upper box body and extends into the launch box; A limit seat is provided at one end of the screw rod away from the pressing plate and is used to abut against the side wall of the target. The limit seat is used to move along a direction perpendicular to the top plate of the upper box body along with the screw rod.

[0012] In a second aspect, an embodiment of the present application provides a target launching method using the launching box assembly as described in the above embodiment, including: Transporting the launching box assembly storing the target to the launching site; Adjusting the launching angle of the launching box assembly; Igniting and launching the target, so that the target drives the adapter of the restraint system to slide along the guide rail, so that the restraint system guides the target and restrains the roll of the target, so that the buffer system guides the target and restrains the radial direction of the target. When the target detaches from the launching box, the adapter is separated.

[0013] Optionally, before transporting the launching box assembly storing the target to the launching site, it further includes: Horizontally placing the lower box body of the launching box and installing an adapter in the guide rail of the lower box body; Hoisting the target into the lower box body and making the top spring seat of the adapter be inserted and matched with the limit hole of the target; Locking the axial limit stop seat with the upper box body, the lower box body and the tail end of the target, and installing the rudder surface fixing seat so that the rudder surface of the target is clamped into the clamping groove of the rudder surface fixing seat; Inserting and matching the adapter corresponding to the upper box body with the limit hole on the top surface of the target; Hoisting and placing the upper box body so that the guide rail of the upper box body is matched with the adapter on the top surface of the target, so that the plurality of buffer members of the buffer system are arranged around the circumference of the target; Installing the rear box cover so that the rear box cover is locked with the axial limit stop seat; Installing the transportation limit mechanism so that the transportation limit mechanism passes through the limit seat of the upper box body and abuts against the target.

[0014] The beneficial technical effects brought by the technical solution provided by the embodiment of the present application include: In the embodiment of the present application, by providing an adapter that slides in cooperation with the guide rail and the adapter is inserted and matched with the target, during the launching process of the target, the target drives the adapter to slide along the guide rail, and the sliding process is the take-off process of the target in the launching box assembly. During the take-off process of the target, the adapter guides the target; since the adapter is inserted and matched with the target, the roll of the target can be restrained. When the tail end of the target detaches from the launching box instantaneously, the adapter is separated from the target under the elastic force, completing the launching of the target.

[0015] By providing a buffer system that abuts or contacts the side wall of the target and is arranged circumferentially around the target, during the launching process of the target, the buffer system can guide and radially constrain the target, ensuring that the buffer system is launched along the center line of the launching box, avoiding radial deviation during the launching process, and ensuring that the target is launched along a predetermined route. As a result, there is no need to provide a slider on the target, improving the aerodynamic performance of the outer surface of the target, facilitating weight reduction of the target, and further enhancing the flight performance of the target.

[0016] Moreover, during the transportation of the launching box assembly storing the target, the buffer system can buffer the radial shaking of the target to avoid the target from being knocked, and can also ensure that the axis of the target coincides with the center line of the launching box, avoiding radial deviation of the target during transportation.

[0017] Additional aspects and advantages of the present application will be partially presented in the following description, which will become apparent from the following description or be understood through the practice of the present application. Description of the Drawings

[0018] The above-mentioned and / or additional aspects and advantages of the present application will become apparent and easy to understand from the following description of the embodiments in conjunction with the drawings, where: Figure 1 is a schematic structural diagram of a launching box assembly provided by an embodiment of the present application; Figure 2 is a schematic side view of a launching box assembly provided by an embodiment of the present application; Figure 3 is a schematic diagram of the cooperation between the lower box body, the rear box cover assembly and the adapter and the target in an embodiment of the present application; Figure 4 is a schematic overall structural diagram and a schematic sectional structural diagram of the adapter in an embodiment of the present application; Figure 5 is a schematic side view of the lower box body in an embodiment of the present application; Figure 6 is a schematic specific structural diagram of the lower box body in an embodiment of the present application; Figure 7 is a schematic side view of the upper box body in an embodiment of the present application; Figure 8 is a schematic specific structural diagram of the upper box body in an embodiment of the present application; Figure 9 is an exploded schematic diagram of the rear box cover assembly in an embodiment of the present application; Figure 10 is a schematic structural diagram of the axial limit seat in an embodiment of the present application; Figure 11 is a schematic structural diagram of the transportation limit mechanism in an embodiment of the present application; Figure 12 A schematic flow chart of a target launching method provided in an embodiment of the present application.

[0019] Description of reference numerals: 1-launch box; 11-lower box; 12-upper box; 13-first connecting seat; 14-second connecting seat; 15-hanging seat; 16-guide pin seat; 17-installation interface; 2-restraint system; 21-guide rail; 22-adapter; 221-buffer body; 222-elastic seat; 223-cover; 224-embedded part; 225-elastic part; 226-mounting hole; 3-buffer system; 31-buffer member; 311-mounting frame; 312-mounting seat; 313-buffer part; 4-rear box cover assembly; 41-rear box cover; 42-axial limit stopper; 421-stopper frame; 422-annular structure; 423-connecting rod; 424-mounting piece; 425-target locking interface seat; 426-rudder surface fixing seat mounting plate; 43-rudder surface fixing seat; 431-clamping groove; 5-transport limit mechanism; 51-screw; 52-pressing plate; 53-limiting seat; 54-blocking plate; 55-rotating wheel; 56-rubber pad; 57-ball head plug cover; 6-front box cover; 7-switching antenna; 8-target. DETAILED DESCRIPTION

[0020] The embodiments of the present application are described below in conjunction with the drawings in the present application. It should be understood that the implementation methods described below in conjunction with the drawings are exemplary descriptions for explaining the technical solutions of the embodiments of the present application and do not constitute a limitation on the technical solutions of the embodiments of the present application.

[0021] Those skilled in the art will appreciate that, unless otherwise stated, "said" and "the" used herein may also include plural forms. The term "and / or" used herein refers to at least one of the items defined by the term, for example, "A and / or B" may be implemented as "A", or as "B", or as "A and B".

[0022] In order to make the objectives, technical solutions and advantages of the present application clearer, the implementation methods of the present application will be further described in detail below in conjunction with the accompanying drawings.

[0023] In the related art, in order to reduce the transportation cost of the target and improve the launching efficiency of the target, the target is usually launched in a box when launched. For the target launched in a box, most of them choose to set sliders on both sides of the "I" or "III" quadrant of the target to form a "squatting type" or "hanging type" configuration, and there are also sliders set at the positions of the "II" and "IV" quadrants of the target. In this case, a guide rail matching with the slider is arranged inside the launch box, and after the engine of the target is ignited, the target leaves the box under the guidance of the slider and the guide rail. In this solution, the reserved slider, as a protrusion, will sacrifice part of the flight performance of the target.

[0024] To solve the above technical problems, referring to Figures 1-11 , an embodiment of the present application provides a launch box assembly, including a launch box 1, and a constraint system 2 and a buffer system 3 arranged inside the launch box 1.

[0025] The constraint system 2 includes at least one guide rail 21 extending along the length direction of the launch box 1 and an adapter 22 slidably arranged at the guide rail 21. At least one guide rail 21 is arranged on the inner wall of at least one box panel of the launch box 1. One end of the adapter 22 away from the guide rail 21 is configured to be plugged and matched with the target 8, guide the target 8 during transportation and launching, and constrain the roll of the target 8, and the adapter 22 is elastically arranged along the radial direction of the target 8 for separating from the target 8 when the target 8 leaves the launch box 1.

[0026] The buffer system 3 includes at least two buffer members 31 arranged circumferentially around the target 8. One end of the buffer member 31 away from the inner wall of the launch box 1 is used to abut against the side wall of the target 8 during transportation and launching, guide the target 8, and constrain the radial direction of the target 8.

[0027] In the embodiment of the present application, by setting the adapter 22 slidably matched with the guide rail 21 and the adapter 22 being plugged and matched with the target 8, during the launching process of the target 8, the target 8 drives the adapter 22 to slide along the guide rail 21, and the sliding process is the take-off process of the target in the launch box assembly. During the take-off process of the target, the adapter 22 guides the target 8; since the adapter 22 is plugged and matched with the target 8, the roll of the target 8 can be constrained. When the tail end of the target 8 leaves the launch box 1 instantaneously, the adapter 22 separates from the target 8 under the elastic force, and the launching of the target 8 is completed.

[0028] By setting the buffer system 3 that abuts against or contacts the side wall of the target 8 and is arranged circumferentially around the target 8, during the launching process of the target 8, the buffer system 3 can guide and radially constrain the target 8, ensure that the buffer system 3 is launched along the center line of the launch box 1, avoid radial deviation during the launching process, ensure that the target 8 is launched along a predetermined route, so that there is no need to set sliders on the target 8, which can improve the aerodynamic performance of the outer surface of the target 8, is beneficial to reducing the weight of the target 8, and further improves the flight performance of the target 8.

[0029] Moreover, during the transportation of the launch box assembly storing the target 8, the buffer system 3 can buffer the radial shaking of the target 8 to avoid the target 8 from being knocked, and can also ensure that the axis of the target 8 coincides with the center line of the launch box 1 to avoid radial deviation of the target 8 during transportation.

[0030] Optionally, referring to Figures 1-2 , the launch box 1 includes an upper box body 12 and a lower box body 11 that are detachably connected. The number of guide rails 21 includes at least two. At least one guide rail 21 is provided on the top plate of the upper box body 12, and at least one guide rail 21 is provided on the bottom plate of the lower box body 11.

[0031] The number of buffer members 31 includes at least four. At least one buffer member 31 is arranged on the side plates of the upper box body 12 and the lower box body 11 respectively. One end of each buffer member 31 away from the side plate points to the center line located at the center of the launch box 1 and extending along the length direction of the launch box 1.

[0032] Referring to Figures 1-3 , the launch box 1 includes an upper box body 12 and a lower box body 11 that are detachably connected. During loading, the target 8 is directly hoisted into the lower box body 11 by a hoisting device, and then the upper box body 12 is hoisted and positioned and locked with the lower box body 11 to complete the loading. There is no need to use a special loading device to load from the port of the launch box 1, which is convenient for loading the target 8 and saves the loading cost.

[0033] Optionally, referring to the partial enlarged view at A in Figure 6 , a plurality of first connection seats 13 are provided at one end of the upper box body 12 and the lower box body 11 close to the opening. The first connection seats 13 are arranged at intervals along the length direction of the upper box body 12 and the lower box body 11. The first connection seats 13 are used to realize the docking and locking of the upper and lower box bodies 11.

[0034] Optionally, referring to Figure 5 , a guide pin seat 16 is further provided at one end of the lower box body 11 close to the bottom plate. The guide pin seat 16 is used for guiding during the hoisting and docking process of the overall structure of the launch box 1 and the erection frame of the launch system.

[0035] Optionally, referring to the partial enlarged view at B in Figure 6 , a plurality of second connection seats 14 are provided at one end of the lower box body 11 close to the bottom plate. The second connection seats 14 are used to realize the connection and fixation after the hoisting and docking with the erection frame of the launch system. The second connection seats 14 are arranged at intervals along the length direction of the lower box body 11.

[0036] Optionally, referring to Figure 7 and Figure 8Partial enlarged view at position C in the figure. At one end of the upper box body 12 close to the top plate, there are at least four lifting seats 15 for detachably connecting with lifting equipment, which are used for two working conditions: individual lifting of the upper box body 12 and overall lifting of the launch box 1. At least four lifting seats 15 are symmetrically arranged to ensure that the upper box body 12 is horizontally lifted above the lower box body 11.

[0037] Optionally, referring to Figure 6 and Figure 8 , the upper box body 12 and the lower box body 11 adopt a skin-skeleton structure. The skeleton is welded by rectangular tubes, and the skin is made of steel plates.

[0038] Referring to Figures 2-4 , two guide rails 21 are provided and are respectively arranged on the top plate of the upper box body 12 and the bottom plate of the lower box body 11. During the loading process of the target 8, it is convenient to arrange the mating relationship between the adapter 22 and the target 8, which can simplify the installation layout and improve the loading efficiency. The rolling motion of the target 8 is restricted by the adapter 22 and the guide rail 21 to ensure that the target 8 is launched along the launch box 1.

[0039] Optionally, referring to Figure 4 , the adapter 22 includes a buffer body 221 with an installation hole 226, an elastic member 225 arranged in the installation hole 226, a top spring seat 222 with its bottom abutting against the elastic member 225, and a cover 223 fixed at the top of the installation hole 226 and covering the bottom of the top spring seat 222. The top spring seat 222 and the cover 223 are slidably arranged.

[0040] The tail end of the target 8 is provided with a limit hole for mating with the top spring seat 222. The top spring seat 222 is used to separate from the target 8 under the action of the elastic member 225 when the target 8 detaches from the launch box 1.

[0041] The top spring seat 222 is coaxial with the installation hole 226. The top spring seat 222 can slide along the axis of the installation hole 226 under the action of the elastic member 225. In the normal state of the elastic member 225, the top end of the top spring seat 222 protrudes from the installation hole 226. When the target 8 is loaded, the top end of the top spring seat 222 is inserted into the limit hole of the target 8, so as to combine with the target 8 and provide guidance and rolling restraint for the target 8.

[0042] Optionally, both ends of the guide rail 21 are in a closed state. When the tail end of the target 8 is about to disengage from the launch box 1, at this time, the adapter 22 has moved from the end of the guide rail 21 to the front end of the guide rail 21. At the moment when the target 8 disengages from the launch box 1, the top spring seat 222 inserted in the limit hole stretches the elastic member 225 under the action of inertia. The elastic member 225 has a tendency to contract and recover, so that the elastic member 225 obtains a restoring force. The top spring seat 222 gradually disengages from the limit hole under the action of the restoring force of the elastic member 225 and gradually resets, causing the adapter 22 to separate from the target 8. Since the target 8 of the present application is not provided with a slider, better flight performance can be obtained during flight.

[0043] Optionally, the buffer main body 221 of the adapter 22 is made of a lightweight material with buffer performance. In this application, the foam main body formed by using polyurethane foam as the material of the buffer main body 221 is taken as an example for illustration, so that the adapter 22 has certain impact resistance and shock absorption, reducing the hard impact between the target 8 and the guide rail 21 and the adapter 22 during long-distance transportation, and protecting the mechanical structures of the target 8 and the adapter 22.

[0044] Optionally, the elastic member 225 of the present application is illustrated by taking a spring as an example.

[0045] Optionally, a columnar embedded member 224 is also coaxially arranged in the mounting hole 226, and the spring is sleeved outside the embedded member 224. There is a distance between the top of the embedded member 224 and the bottom of the top spring seat 222, which can ensure that the top spring seat 222 has enough sliding space. The embedded member 224 provides support and limitation for the spring, avoiding or reducing axial deflection or displacement of the spring. Optionally, the embedded member 224 is pre-embedded into the mold before foaming, so that the embedded member 224 is coaxially arranged in the mounting hole 226.

[0046] Optionally, referring to Figure 2 , at least four buffer members 31 are provided, and at least four buffer members 31 all point to the center line of the launch box 1. In the embodiment of the present application, at least four buffer members 31 are respectively arranged on the left side plate of the upper box body 12, the right side plate of the upper box body 12, the left side plate of the lower box body 11, and the right side plate of the lower box body 11. After the target 8 is loaded, a left upper buffer area, a left lower buffer area, a right upper buffer area, and a right upper buffer area can be formed in the circumferential direction of the target 8 to ensure uniform restraint of the target 8.

[0047] In an alternative solution, referring to Figure 6 , one buffer member 31 is arranged on the left side plate of the upper box body 12, the right side plate of the upper box body 12, the left side plate of the lower box body 11, and the right side plate of the lower box body 11 respectively, and each buffer member 31 extends along the length direction of the launch box 1.

[0048] In another optional embodiment, multiple buffer members 31 are arranged at intervals on the left side plate of the upper box body 12, the right side plate of the upper box body 12, the left side plate of the lower box body 11, and the right side plate of the lower box body 11, so that four buffer members 31 form a group, and the four buffer members 31 in each group are coplanar.

[0049] The present application only takes the example that four buffer members 31 are provided and each buffer member 31 extends along the length direction of the launch box 1 for explanation.

[0050] When the target 8 is loaded into the launch box 1, the buffers 31 can be evenly arranged around the target 8. The end of each buffer 31 abuts against the target 8, which can clamp the target 8 during transportation and limit the radial shaking of the target 8. During the launch of the target 8, the target 8 and the buffer 31 move relative to each other. Since the end of each buffer 31 points to the center line of the launch box 1, the buffer 31 can guide the movement of the target 8 and ensure that the target 8 is launched smoothly along the center line of the launch box 1.

[0051] Optionally, refer to Figure 2 , Figure 4 and Figure 6 The structure of each buffer 31 is consistent, and the only difference is the installation position. This application only takes any one of the buffers 31 as an example for description.

[0052] Reference Figure 7 The buffer component 31 includes a mounting frame 311, a mounting seat 312 and a buffer portion 313 which are arranged in sequence from the side panel of the launch box 1 to the center line of the launch box 1. The mounting surface of the mounting seat 312 and the buffer portion 313 are inclined relative to a first plane parallel to the bottom plate of the lower box body 11. The buffer portion 313 is made of elastic material, and the end face of the buffer portion 313 is an arc surface that gradually decreases from one end close to the mounting seat 312 to the end away from the mounting seat 312.

[0053] The elastic material of the buffer part 313 can buffer the shaking of the target 8 during transportation, avoid the hard collision between the target 8 and the side plate of the launch box 1, and ensure the integrity of the mechanical structure of the target 8. In the present application, the material of the buffer part 313 includes but is not limited to polyurethane, so that the target 8 can be effectively buffered from collision during transportation.

[0054] The mounting frame 311 is made of metal, so that the buffer 31 as a whole has better mechanical stability. The mounting seat 312 is mounted on the mounting frame 311 by bolts. The buffer portion 313 and the mounting seat 312 are detachably connected. Considering the material of the buffer portion 313, this application takes the bonding of the buffer portion 313 and the mounting seat 312 as an example for explanation, so as to facilitate replacement of the buffer portion 313 after wear occurs.

[0055] The end face of the buffer part 313 is an arc surface, and it gradually narrows from the end close to the mounting base 312 to the end far from the mounting base 312, which can reduce the frictional resistance between the buffer part 313 and the target 8. On the basis of being able to guide and radially constrain the target 8, it can avoid affecting the launching performance of the target 8.

[0056] Optionally, referring to Figure 1 and Figure 3 , the launch box 1 further includes a rear box cover assembly 4 detachably connected to the upper box body 12 and the lower box body 11. The rear box cover assembly 4 is used to axially and circumferentially constrain the tail end of the target 8 during transportation.

[0057] The rear box cover assembly 4 is used to be detachably connected to the tail end of the target 8, as well as the tail ends of the upper box body 12 and the lower box body 11 after the target 8 is loaded, so as to restrict the circumferential rotation and axial sliding of the target 8.

[0058] Optionally, referring to Figure 9 , the rear box cover assembly 4 includes an axial limit retaining seat 42 detachably arranged at the tail ends of the upper box body 12 and the lower box body 11, a rudder surface fixing seat 43 detachably arranged on the axial limit retaining seat 42, and a rear box cover 41 detachably arranged outside the axial limit retaining seat 42.

[0059] Referring to Figure 9 , the rudder surface fixing seat 43 is provided with a clamping groove 431 for clamping the rudder surface of the target 8, which is used to limit the rudder surface at the tail end of the target 8 during transportation. The axial limit retaining seat 42 is provided with a target locking interface seat 425 for locking with the tail end of the target 8 during transportation.

[0060] Optionally, the rudder surface fixing seat 43 and the axial limit retaining seat 42 are coplanar.

[0061] The axial limit retaining seat 42 has sufficient mechanical strength and can serve as the load-bearing main body for axial overload during the transportation of the target 8 and the load-bearing main body after the target 8 and the launch box 1 are erected.

[0062] By providing the target locking interface seat 425 on the axial limit retaining seat 42, during the transportation of the target 8, a locking member can be used to lock the target locking interface seat 425 and the tail end of the target 8 to avoid axial movement of the target 8.

[0063] Optionally, the target locking interface seat 425 includes a locking hole, and the locking hole is a clearance hole that can be adapted to a high-strength bolt (for example, a bolt with a strength not lower than M16). Thus, a high-strength bolt can be used to lock the axial limit retaining seat 42 and the tail end of the target 8, avoiding the separation of the target 8 from the axial limit retaining seat 42 during long-distance transportation, and being able to achieve stable axial limit for the target 8 and avoid structural damage caused by axial movement of the target 8.

[0064] By providing a rudder surface fixing seat 43 on the axial limiting baffle, after the target 8 is loaded, the rudder surface of the target 8 is snapped into the clamping groove 431 of the rudder surface fixing seat 43, so that the rudder surface fixing seat 43 can limit the circumferential rotation of the target 8 and provide protection for the rudder surface during long-distance transportation, avoiding structural collision damage caused by the rotation of the rudder surface.

[0065] The rear box cover 41 is detachably connected to the axial limiting seat 42, so as to achieve the sealing protection of the rear end face of the launch box 1, prevent foreign objects from entering the inside of the launch box 1, and avoid affecting the launch of the target 8.

[0066] Optionally, referring to Figure 10 , the axial limiting seat 42 includes a seat frame 421, mounting members 424 provided at the four corners of the baffle frame for detachably connecting to the upper box body 12 and the lower box body 11, a ring structure 422 arranged at the center of the seat frame 421 and connected to the seat frame 421 through a connecting rod 423, and a rudder surface fixing seat mounting plate 426 arranged around the periphery of the ring structure 422. The target locking interface seat 425 is provided on the ring structure 422 and axially penetrates the side wall of the ring structure 422.

[0067] Optionally, a plurality of rudder surface fixing seats 43 are arranged around the periphery of the ring structure 422. In the plane where the rudder surface fixing seat 43 and the ring structure 422 are located, the opening of the clamping groove 431 faces outward.

[0068] Optionally, referring to Figure 10 , the seat frame 421 is a square frame matching the port of the launch box 1. The ring structure 422 is arranged at the center of the seat frame 421, and the end face shape of the ring structure 422 matches the end face of the tail end of the target 8, which is convenient for connecting the target locking interface seat 425 and the tail end of the target 8 with high-strength bolts.

[0069] A plurality of connecting rods 423 are provided, and each connecting rod 423 is perpendicularly arranged with respect to the seat frame 421 and one end is connected to the periphery of the ring structure 422. Optionally, the plurality of connecting rods 423 are symmetrically arranged with respect to the horizontal center line or the vertical center line of the seat frame 421. In an example of the present application, eight connecting rods 423 are provided, and every two of them form a group. The two connecting rods 423 in the same group are connected to one of the side frames of the baffle frame, and the distance between the two connecting rods 423 in each group is the same.

[0070] Optionally, referring to Figure 10, the rudder surface fixing seat mounting plate 426 is used to mount the rudder surface fixing seat 43. By arranging the rudder surface fixing seat mounting plate 426 on the periphery of the annular structure 422 and arranging it circumferentially around the annular structure 422, the rudder surface fixing seats 43 can be evenly arranged circumferentially around the annular structure 422, making the force on the rudder surface of the target 8 more uniform and avoiding knocking on the rudder surface of the target 8.

[0071] Optionally, referring to Figure 10 , a space for mounting the rudder surface fixing seat mounting plate 426 is formed between two adjacent connecting rods 423 arranged perpendicular to each other. In this application, the rudder surface fixing seat mounting plate 426 is inclined and arranged between two adjacent connecting rods 423 arranged perpendicular to each other. The rudder surface fixing seat 43 is vertically arranged on the rudder surface fixing seat mounting plate 426 through bolts, ensuring that the clamping groove 431 of the rudder surface fixing seat 43 is parallel to the axis of the annular structure 422.

[0072] Optionally, referring to Figure 9 , both ends of the rudder surface fixing seat 43 do not protrude beyond the two sides of the axial limit retaining seat 42, so as to avoid occupying the space on both sides of the axial limit retaining seat 42. By integrating the rudder surface fixing seat 43 on the axial limit retaining seat 42, on the basis of realizing the axial limit, rolling ring limit and rudder surface protection of the target 8, the volume of the rear box cover assembly 4 can be reduced, and the overall volume of the launch box assembly can be lightened.

[0073] Optionally, referring to Figure 10 , the mounting part 424 is selected as the limit retaining seat mounting flange and is locked with the upper box body 12 and the lower box body 11 through bolts, which is convenient for fixing the axial limit retaining seat 42 with the upper box body 12 and the lower box body 11.

[0074] Optionally, referring to Figure 1 , the launch box 1 further includes a front box cover 6 detachably arranged at the front ends of the upper box body 12 and the lower box body 11, which is used to seal and protect the front end face of the launch box 1.

[0075] Optionally, both the front box cover 6 and the rear box cover 41 are processed from aluminum plates, which can reduce the weight while ensuring sufficient stiffness and can reduce the overall weight of the launch box 1.

[0076] Optionally, referring to Figure 1 、 Figure 2 and Figure 11 , the launch box assembly further includes a transportation limit mechanism 5 partially arranged in the launch box 1 to radially limit the target 8 during transportation. The transportation limit mechanism 5 includes a pressing plate 52, a screw rod 51 and a limit seat 53.

[0077] The pressing plate 52 is detachably arranged above the top plate of the upper box body 12. The screw rod 51 passes through and is rotatably connected with the pressing plate 52. The screw rod 51 passes through the top plate of the upper box body 12 and extends into the launching box 1. The limiting seat 53 is arranged at one end of the screw rod 51 far from the pressing plate 52 and is used to abut against the side wall of the target 8. The limiting seat 53 is used to move along the direction perpendicular to the top plate of the upper box body 12 along with the screw rod 51.

[0078] Referring to Figure 2 、 Figure 8 and Figure 11 , a part of the screw rod 51 is located outside the upper box body 12, and a part is located inside the upper box body 12. An installation interface 17 for the transportation limiting mechanism 5 is reserved on the upper side of the top plate of the upper box body 12. The limiting seat 53 is arranged inside the upper box body 12 and can move along the direction perpendicular to the top plate of the upper box body 12 along with the screw rod 51. When the upper box body 12 is covered above the lower box body 11 and locked with the lower box body 11, by driving the part of the screw rod 51 located outside the upper box body 12, the limiting seat 53 is driven to move downward until the limiting seat 53 abuts against the outer side wall of the target 8, so as to utilize the radial pressure of the limiting seat 53 on the target 8 to limit the radial displacement and circumferential rotation of the target 8.

[0079] Optionally, a through hole for the screw rod 51 to pass through is formed on the pressing plate 52. The transportation limiting mechanism 5 further includes a plug plate 54 detachably arranged on the pressing plate 52. The plug plate 54 includes a cylindrical part for embedding into the through hole. The inner wall of the cylindrical part is provided with internal threads matching the screw rod 51. By arranging the plug plate 54, the threaded connection area between the pressing plate 52 and the screw rod 51 can be increased, ensuring the radial movement of the screw rod 51 along the target 8.

[0080] In order to facilitate the operator to hold, a rotating wheel 55 is installed at one end of the screw rod 51 located outside the upper box body 12. The outer shape of the rotating wheel 55 can be designed into shapes such as square, round or irregular, which is not limited herein. In this application, the rotating wheel 55 is taken as an example of a disc shape for illustration.

[0081] Optionally, a ball head plug 57 is threadedly connected to one end of the screw rod 51 far from the rotating wheel 55. The screw rod 51 is detachably connected with the limiting seat 53 through the ball head plug 57. In this application, the ball head plug 57 is taken as an example of being bolted to the limiting seat 53 for illustration.

[0082] Optionally, the contact surface of the limiting seat 53 can be designed as an arc surface according to the radian of the outer side wall of the target 8.

[0083] Optionally, a rubber pad 56 can also be arranged on the contact surface of the limiting seat 53 for contacting the target 8 to buffer the hard contact between the pressing plate 52 and the target 8 and avoid hard indentations or abrasions on the outer side wall of the target 8. The rubber pad 56 and the limiting seat 53 can be fixedly connected or detachably connected, which is not limited herein.

[0084] Optionally, refer to Figure 8 In the partial enlarged view at D in the middle, the transmitting box assembly of the present application also includes a switching antenna 7. The switching antenna 7 is installed on the side of the main body of the upper box 12, and the data reception between this type of metal box and the ground measurement and control equipment can be realized through the switching antenna 7.

[0085] Based on the same inventive concept, Figure 12 The present application embodiment provides a target launching method using the launching box assembly in the above embodiment, including: S1: Transporting the launch box assembly storing the target 8 to the launch site.

[0086] S2: Adjust the launch angle of the launch box assembly.

[0087] S3: Ignite and launch the target 8, so that the target 8 drives the adapter 22 of the constraint system 2 to slide along the guide rail 21, so that the constraint system 2 guides the target 8 and constrains the rolling of the target 8, and the buffer system 3 guides the target 8 and constrains the radial direction of the target 8. When the target 8 leaves the launch box 1, the adapter 22 is separated.

[0088] In the embodiment of the present application, during the launch of the target 8, the target 8 drives the adapter 22 to slide along the guide rail 21, and the adapter 22 guides the target 8 and constrains the rolling of the target 8. When the tail end of the target 8 leaves the launch box 1, the adapter 22 separates from the target 8 under the elastic force, completing the launch of the target 8. By providing the adapter 22 that cooperates with the target 8, the guidance and rolling constraint of the target 8 are achieved, so that there is no need to provide a slider on the target 8, and the flight performance of the target 8 can be improved.

[0089] Moreover, during the launch of the target 8, the buffer system 3 can have a certain buffering effect on the radial shaking of the target 8 to prevent the target 8 from bumping, and can also ensure that the axis of the target 8 coincides with the center line of the launch box 1 to prevent the target 8 from radial deviation during transportation. During the launch of the target 8, the buffer system 3 can guide and radially constrain the target 8 to ensure that the buffer system 3 is launched along the center line of the launch box 1 to avoid radial deviation during the launch process, and can ensure that the target 8 is launched along the predetermined route, thereby improving the flight performance of the target 8.

[0090] Optionally, before transporting the launch box assembly storing the target 8 to the launch site, the target 8 needs to be loaded, including: S01: Place the lower box body 11 of the launch box 1 horizontally, and install the adapter 22 in the guide rail 21 of the lower box body 11.

[0091] S02: Hang the target 8 into the lower box 11 and make the top spring seat 222 of the adapter 22 engage with the limiting hole of the target 8.

[0092] S03: Lock the axial limit stopper 42 with the upper box body 12 , the lower box body 11 and the tail end of the target 8 , and install the rudder surface fixing seat 43 so that the rudder surface of the target 8 is clamped into the clamping groove 431 of the rudder surface fixing seat 43 .

[0093] S04: Insert and match the adapter 22 corresponding to the upper box body 12 with the limiting hole on the top surface of the target 8.

[0094] S05 : Hanging the upper box 12 , so that the guide rail 21 of the upper box 12 cooperates with the adapter 22 on the top surface of the target 8 , so that the multiple buffer members 31 of the buffer system 3 are arranged around the circumference of the target 8 .

[0095] S06: Install the rear box cover 41 so that the rear box cover 41 and the axial limit stopper 42 are locked.

[0096] S07: Install the transport limiting mechanism 5 so that the transport limiting mechanism 5 passes through the limiting seat 53 of the upper box body 12 and abuts against the target 8.

[0097] The beneficial technical effects brought about by the technical solution provided by the embodiment of the present application include: By providing an adapter 22 that slides with the guide rail 21, and the adapter 22 is plugged into the target 8, during the launch of the target 8, the target 8 drives the adapter 22 to slide along the guide rail 21. The sliding process is the take-off process of the target in the launch box assembly. During the take-off process of the target, the adapter 22 guides the target 8. Since the adapter 22 is plugged into the target 8, the rolling of the target 8 can be constrained. At the moment when the tail end of the target 8 leaves the launch box 1, the adapter 22 is separated from the target 8 under the elastic force, and the launch of the target 8 is completed.

[0098] By providing a buffer system 3 that abuts or contacts the side wall of the target 8 and is circumferentially arranged around the target 8, during the launch process of the target 8, the buffer system 3 can guide and radially constrain the target 8, ensuring that the buffer system 3 is launched along the center line of the launch box 1, avoiding radial deviation during the launch process, and ensuring that the target 8 is launched along a predetermined route. There is no need to provide a slider on the target 8, which can improve the aerodynamic performance of the outer surface of the target 8, help reduce the weight of the target 8, and further improve the flight performance of the target 8.

[0099] Moreover, during the transportation of the launch box assembly storing the target 8, the buffer system 3 can produce a certain buffering effect on the radial shaking of the target 8 to prevent the target 8 from being bumped, and can also ensure that the axis of the target 8 coincides with the center line of the launch box 1 to prevent the target 8 from being radially deflected during transportation.

[0100] The launch box 1 includes an upper box body 12 and a lower box body 11 that are detachably connected. During loading, the target 8 is directly lifted into the lower box body 11 using a lifting device, and then the upper box body 12 is lifted and positioned and locked with the lower box body 11 to complete the loading. There is no need to use a special loading device to load from the port of the launch box 1, which facilitates the loading of the target 8 and saves the loading cost.

[0101] By providing a target locking interface seat 425 on the axial limit seat 42, when the target 8 is being transported, a locking member can be used to lock the target locking interface seat 425 and the tail end of the target 8 to prevent axial movement of the target 8. By providing a rudder surface fixing seat 43 on the axial limit baffle, when the loading of the target 8 is completed, the rudder surface of the target 8 is snapped into the clamping groove 431 of the rudder surface fixing seat 43, enabling the rudder surface fixing seat 43 to restrict the circumferential rotation of the target 8 and for the protection of the rudder surface during long-distance transportation to avoid structural collision damage caused by the rotation of the rudder surface.

[0102] By providing a transportation limit mechanism 5, the target 8 can be radially limited during transportation, ensuring the smooth transportation of the target 8 and avoiding structural damage to the target 8.

[0103] In the description of the present application, the directions or positional relationships indicated by the words "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. are exemplary directions or positional relationships based on the figures shown, which are for the convenience of describing or simplifying the embodiments of the present application, rather than indicating or implying that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present application.

[0104] The terms "first" and "second" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present application, unless otherwise stated, the meaning of "plurality" is two or more.

[0105] In the description of the present application, it should be noted that unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be directly connected, or indirectly connected through an intermediate medium, and it may be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances.

[0106] In the description of this specification, specific features, structures, materials, or characteristics may be combined in a suitable manner in any one or more embodiments or examples.

[0107] The above are only partial embodiments of this application. It should be noted that for those of ordinary skill in the art, without departing from the technical concept of the solution of this application, other similar implementation means based on the technical idea of this application also fall within the scope of protection of the embodiments of this application.

Claims

1. A launcher box assembly, characterized in that, For the storage, transportation and launch of a target, including: A launch box; A restraint system, including at least one guide rail extending along the length direction of the launch box and an adapter slidably arranged at the guide rail. At least one of the guide rails is arranged on the inner wall of at least one box panel of the launch box. The end of the adapter away from the guide rail is configured to be plugged and matched with the target, guiding the target and restraining the roll of the target during transportation and launch, and the adapter is elastically arranged along the radial direction of the target for separating from the target when the target disengages from the launch box; A buffer system, arranged inside the launch box, including at least two buffer members arranged circumferentially around the target. The end of the buffer member away from the inner wall of the launch box is used to abut against or contact the side wall of the target during transportation and launch, guiding the target and restraining the radial direction of the target.

2. The launch box assembly according to claim 1, characterized in that, The launch box includes an upper box body and a lower box body that are detachably connected; The number of the guide rails includes at least two. At least one of the guide rails is arranged on the top plate of the upper box body, and at least one of the guide rails is arranged on the bottom plate of the lower box body; The number of the buffer members includes at least four. At least one of the buffer members is arranged on the side plates of the upper box body and the lower box body respectively. The end of each buffer member away from the side plate points to the center line located at the center of the launch box and extending along the length direction of the launch box.

3. The launch box assembly according to claim 1, characterized in that, The adapter includes a buffer main body provided with a mounting hole, an elastic member arranged in the mounting hole, a top elastic seat whose bottom abuts against the elastic member, and a cover fixed at the top of the mounting hole and covering the bottom of the top elastic seat. The top elastic seat and the cover are slidably arranged; A limit hole matched with the top elastic seat is provided at the tail end of the target. The top elastic seat is used for separating from the target under the action of the elastic member when the target disengages from the launch box.

4. The launch box assembly according to claim 2, characterized in that, The buffer member includes a mounting type frame, a mounting seat and a buffer part arranged in sequence from the side plate of the launch box to the center line of the launch box. The mounting surface of the mounting seat is inclined relative to a first plane parallel to the bottom plate with the buffer part. The buffer part is made of an elastic material, and the end face of the buffer part is an arc surface that gradually shrinks from the end close to the mounting seat to the end away from the mounting seat.

5. The launch box assembly according to claim 2, characterized in that, The launch box further includes a rear box cover assembly detachably connected to the upper box body and the lower box body, and the rear box cover assembly is used for axially and circumferentially restraining the tail end of the target during transportation.

6. The launch box assembly according to claim 5, wherein The rear box cover assembly includes an axial limit stop seat detachably arranged at the tail ends of the upper box body and the lower box body, a rudder surface fixing seat detachably arranged on the axial limit stop seat, and a rear box cover detachably arranged outside the axial limit stop seat; The rudder surface fixing seat is provided with a clamping groove for clamping the rudder surface of the target, used for limiting the rudder surface at the tail end of the target during transportation, and the axial limit stop seat is provided with a target locking interface seat for locking with the tail end of the target during transportation.

7. The launch box assembly according to claim 6, characterized in that, The axial limiting seat includes a seat frame, mounting members disposed at four corners of the baffle frame for detachably connecting to the upper box body and the lower box body, an annular structure arranged at the center of the seat frame and connected to the seat frame through a connecting rod, and a rudder surface fixing seat mounting plate arranged around the periphery of the annular structure. The target locking interface seat is disposed on the annular structure and penetrates through the side wall of the annular structure.

8. The launch box assembly according to claim 2, wherein, It further includes a transportation limiting mechanism partially disposed inside the launch box for radially limiting the target during transportation. The transportation limiting mechanism includes: A pressing plate detachably disposed above the top plate of the upper box body; A screw rod passing through and rotatably connected to the pressing plate. The screw rod passes through the top plate of the upper box body and extends into the launch box; A limiting seat disposed at one end of the screw rod away from the pressing plate for abutting against the side wall of the target; The limiting seat is adapted to move along a direction perpendicular to the top plate of the upper box body with the screw rod.

9. A target launching method using the launching box assembly according to any one of claims 1-8, characterized in that, It includes: Transporting the launch box assembly storing the target to the launch site; Adjusting the launch angle of the launch box assembly; Igniting and launching the target, such that the target drives the adapter of the restraint system to slide along the guide rail, such that the restraint system guides the target and restrains the roll of the target, such that the buffer system guides the target and radially restrains the target. When the target detaches from the launch box, the adapter is separated.

10. The target emission method according to claim 9, wherein Before transporting the launch box assembly storing the target to the launch site, it further includes: Horizontally placing the lower box body of the launch box and installing an adapter in the guide rail of the lower box body; Lifting and placing the target into the lower box body and making the top spring seat of the adapter inserted and mated with the limiting hole of the target; Locking the axial limiting seat to the upper box body, the lower box body and the tail end of the target, and installing the rudder surface fixing seat such that the rudder surface of the target is snapped into the clamping groove of the rudder surface fixing seat; Inserting and mating the corresponding adapter of the upper box body with the limiting hole on the top surface of the target; Lifting and placing the upper box body such that the guide rail of the upper box body is mated with the adapter on the top surface of the target, such that multiple buffer members of the buffer system are arranged circumferentially around the target; Installing the rear box cover such that the rear box cover is locked to the axial limiting seat; Installing the transportation limiting mechanism such that the transportation limiting mechanism passes through the limiting seat of the upper box body and abuts against the target.

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