Rocket fixture

Abstract

The application relates to the technical field of rockets, and provides a rocket fixing device. The rocket fixing device comprises a vertical lifting arm, a fixing base, a first connecting assembly and a second connecting assembly. The vertical lifting arm is formed with an accommodating cavity for accommodating a rocket, and the fixing base is used for fixing the end of the rocket. The first end of the fixing base is rotatably connected to the end of the vertical lifting arm. The first connecting assembly is arranged on the fixing base, and the first connecting assembly is suitable for connecting the fixing base and the vertical lifting arm. The second connecting assembly is arranged on the fixing base, and the second connecting assembly is suitable for connecting the fixing base and the rocket. According to the rocket fixing device, axial fixing and limiting of the rocket are realized, the fixing and limiting effect of the rocket is guaranteed, and the rocket can be effectively prevented from being displaced during the transfer process or the preparation process before launching.

Description

Technical Field

[0001] This application relates to the field of rocket technology, and in particular to rocket mounting devices. Background Technology

[0002] Before launch, the rocket needs to be transported to the launch site and then tilted and erected. During the transportation and tilting process, the rocket needs to be secured and restrained.

[0003] The rocket fixing devices in related technologies have limited fixing and limiting effects, and there is a risk of rocket displacement. Summary of the Invention

[0004] This application aims to solve at least one of the technical problems existing in the related art. To this end, this application proposes a rocket fixing device that achieves axial fixing and limiting of the rocket, ensuring the fixing and limiting effect of the rocket, and effectively preventing the rocket from shifting during transportation.

[0005] The rocket fixing device according to an embodiment of this application includes:

[0006] The arm is raised to form a receiving cavity for accommodating the rocket;

[0007] A mounting base is used to fix the end of the rocket; wherein, the first end of the mounting base is rotatably connected to the end of the erecting arm;

[0008] A first connecting component is disposed on the fixed base, and the first connecting component is adapted to connect the fixed base and the erecting arm;

[0009] A second connecting assembly is disposed on the mounting base, and the second connecting assembly is adapted to connect the mounting base and the rocket.

[0010] According to the rocket fixing device of this application embodiment, during rocket relocation and transportation, the fixing seat is first rotated relative to the erecting arm, causing the second end of the fixing seat to rotate away from the end of the erecting arm. Then, the rocket is hoisted into the receiving cavity of the erecting arm, at which point the erecting arm can provide a certain limiting effect on the rocket. Next, the fixing seat is rotated so that it abuts against the rocket. Then, the fixing seat and the erecting arm are connected together through a first connecting component, and the fixing seat is connected to the tail or head of the rocket through a second connecting component. At this point, the erecting arm and the rocket are simultaneously connected to the fixing seat, which can provide a limiting and fixing effect on the rocket. Furthermore, since the fixing seat is located at the end of the erecting arm, it can also provide a limiting and fixing effect on the end of the rocket. During the rocket's tilting and erection process, the erecting arm and the fixing seat can provide support and fixation for the rocket. Before launch, because the fixing seat and the rocket are connected, the end of the rocket can be fixed, keeping the rocket stable and preventing it from being affected by wind and waves. This application achieves axial fixation and limitation of the rocket through the cooperation of the erecting arm and the fixed seat, ensuring the fixation and limitation effect of the rocket and effectively preventing the rocket from shifting during transportation or pre-launch preparation.

[0011] According to one embodiment of this application, the mounting base includes a mounting base body and a support lug. A first end of the support lug is rotatably connected to the erecting arm, and a second end of the support lug is connected to the mounting base body, allowing the mounting base body to switch between an unlocked state and a locked state. In the locked state, the mounting base body abuts against the tail of the rocket, a first connecting component is fixedly connected to the mounting base body and the erecting arm, and a second connecting component is fixedly connected to the mounting base body and the rocket. In the unlocked state, the mounting base body is rotatable relative to the erecting arm.

[0012] According to one embodiment of this application, the second end of the support lug and the fixing body are detachably connected.

[0013] According to one embodiment of this application, the fixing seat forms a limiting cavity, which is adapted to limit and fix the end of the rocket.

[0014] According to one embodiment of this application, the first connecting assembly includes a first connecting seat formed on the fixed base, the first connecting seat having a groove, the end of the erecting arm having a first connecting portion, the first connecting portion being adapted to engage with the groove, the first connecting portion having a locking member, the locking member being adapted to connect the first connecting seat and the first connecting portion.

[0015] According to one embodiment of this application, the first connecting portion includes a first connecting plate, a second connecting plate, a third connecting plate, a connecting rod, and the locking member. The second connecting plate connects the first end of the first connecting plate and the first end of the third connecting plate. The first end of the connecting rod is rotatably connected to the second end of the third connecting plate. The locking member is adapted to connect the second end of the connecting rod and the second end of the first connecting plate. At least one of the first connecting plate, the second connecting plate, the third connecting plate, and the connecting rod can be engaged with the groove.

[0016] According to one embodiment of this application, the second connecting assembly includes a first windproof bolt, the fixing seat has a connecting hole, the first windproof bolt passes through the connecting hole and is adapted to be connected to the rocket.

[0017] According to one embodiment of this application, the rocket fixing device includes a connecting strap locking assembly, which is mounted on the fixing base and adapted to be connected to the rocket. The connecting strap locking assembly is configured to melt or break upon being burned.

[0018] According to one embodiment of this application, the connecting belt locking assembly includes a connecting belt and at least two locking seats, wherein the at least two locking seats are evenly distributed along the circumference of the fixed seat;

[0019] At least two of the locking seats are connected by the connecting strap and are connected to the rocket based on the fixing seat; the connecting strap abuts against the end of the rocket.

[0020] According to one embodiment of this application, the locking seat is connected to a rotating block, the rotating block is rotatable relative to the locking seat, the two rotating blocks at the locking seats are connected by the connecting belt, the rotating block is adapted to be connected to the rocket by a locking connector, wherein the rotating block forms a locking groove, the locking connector is inserted into the locking groove and adapted to be connected to the rocket.

[0021] Additional aspects and advantages of this application will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of this application. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments or related technologies of this application, the accompanying drawings used in the description of the embodiments or related technologies will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1This is a schematic diagram of the rocket fixing device provided in the embodiments of this application.

[0024] Figure 2 This is a schematic diagram of the rocket fixing device provided in the embodiment of this application, wherein the erecting arm is in the erected state.

[0025] Figure 3 This is provided by the embodiments of this application. Figure 2 A magnified schematic diagram of the structure at point A in the middle.

[0026] Figure 4 This is one of the partial structural schematic diagrams of the rocket fixing device provided in the embodiments of this application.

[0027] Figure 5 This is the second partial structural schematic diagram of the rocket fixing device provided in the embodiments of this application.

[0028] Figure 6 This is the third partial structural schematic diagram of the rocket fixing device provided in the embodiments of this application.

[0029] Figure 7 This is a schematic diagram of the connecting belt locking assembly provided in an embodiment of this application.

[0030] Figure label:

[0031] 1. Erecting arm; 2. Fixing base; 3. First connecting assembly; 4. Second connecting assembly;

[0032] 5. Connecting and locking assembly; 6. Rocket; 11. Receiving cavity; 12. First connecting part;

[0033] 21. Fixing base body; 22. Support lug; 23. Limiting cavity; 31. First connecting seat; 32. Groove;

[0034] 51. Locking seat; 52. Connecting belt; 53. Rotating block; 54. Locking connector; 55. Locking groove;

[0035] 121. First connecting plate; 122. Second connecting plate; 123. Third connecting plate; 124. Connecting rod;

[0036] 125. Locking components. Detailed Implementation

[0037] The embodiments of this application will be described in further detail below with reference to the accompanying drawings and examples. The following examples are used to illustrate this application, but should not be used to limit the scope of this application.

[0038] In the description of the embodiments of this application, it should be noted that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the embodiments of this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the embodiments of this application. In addition, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0039] In the description of the embodiments of this application, it should be noted that, unless otherwise explicitly specified and limited, the terms "connected" and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in the embodiments of this application based on the specific circumstances.

[0040] In the embodiments of this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0041] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of the embodiments of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0042] The following is combined Figures 1 to 7 Describes the rocket mounting device of this application.

[0043] According to embodiments of this application, such as Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, the rocket fixing device includes an erecting arm 1, a fixing seat 2, a first connecting assembly 3, and a second connecting assembly 4. The erecting arm 1 forms a receiving cavity 11 for accommodating the rocket 6. The fixing seat 2 is used to fix the end of the rocket 6. The first end of the fixing seat 2 is rotatably connected to the end of the erecting arm 1. The first connecting assembly 3 is disposed on the fixing seat 2 and is adapted to connect the fixing seat 2 and the erecting arm 1. The second connecting assembly 4 is disposed on the fixing seat 2 and is adapted to connect the fixing seat 2 and the rocket 6.

[0044] According to the rocket fixing device of this application embodiment, during the transfer and transportation of rocket 6, the fixing seat 2 is first rotated relative to the erecting arm 1, so that the second end of the fixing seat 2 rotates away from the end of the erecting arm 1. Then, rocket 6 is hoisted into the receiving cavity 11 of the erecting arm 1. At this time, the erecting arm 1 can play a certain limiting role for rocket 6. Then, the fixing seat 2 is rotated so that the fixing seat 2 abuts against rocket 6. Then, the fixing seat 2 and the erecting arm 1 are connected together by the first connecting component 3, and the fixing seat 2 and the tail or head of rocket 6 are connected together by the second connecting component 4. At this time, the erecting arm 1 and rocket 6 are simultaneously connected to the fixing seat 2. The fixing seat 2 can play a limiting and fixing role for rocket 6. And since the fixing seat 2 is located at the end of the erecting arm 1, the fixing seat 2 can play a limiting and fixing role for the end of rocket 6. During the tilting and erection of rocket 6, the erecting arm 1 and the fixing seat 2 provide support and fixation for rocket 6. Before launch, because the fixing seat 2 is connected to rocket 6, it can fix the end of rocket 6, keeping rocket 6 stable and preventing it from being affected by wind and waves. In other words, this application achieves axial fixation and limitation of rocket 6 through the cooperation of the erecting arm 1 and the fixing seat 2, ensuring the fixation and limitation effect of rocket 6 and effectively preventing rocket 6 from shifting during transportation or pre-launch preparation.

[0045] Understandably, the lifting arm 1 is equipped with components for fixing the rocket 6, such as a clamping mechanism or any other suitable structure. When the rocket 6 is hoisted into the receiving cavity 11, the clamping mechanism can hold the rocket 6 tightly, which plays a certain role in limiting and fixing the rocket 6.

[0046] Understandably, the erecting arm 1 is provided with an elongated hole that communicates with the receiving cavity 11, so that the rocket 6 can be hoisted into the receiving cavity 11 through the elongated hole.

[0047] In one embodiment of this application, such as Figure 2 , Figure 3 and Figure 5As shown, the fixed base 2 includes a fixed base body 21 and a support ear 22. The first end of the support ear 22 is rotatably connected to the erecting arm 1, and the second end of the support ear 22 is connected to the fixed base body 21, so that the fixed base body 21 can switch between an unlocked state and a locked state. In the locked state, the fixed base body 21 abuts against the tail of the rocket 6. The first connecting component 3 is fixedly connected to the fixed base body 21 and the erecting arm 1, and the second connecting component 4 is fixedly connected to the fixed base body 21 and the rocket 6. In the unlocked state, the fixed base body 21 can rotate relative to the erecting arm 1.

[0048] Understandably, before transferring rocket 6, the mounting base 21 can be rotated to the unlocked state. At this time, the mounting base 21 can rotate relative to the lifting arm 1, moving the mounting base 21 away from the lifting arm 1 so that rocket 6 can be smoothly hoisted into the receiving cavity 11. After rocket 6 is hoisted into the receiving cavity 11, the mounting base 21 can be rotated to the locked state, so that both the lifting arm 1 and rocket 6 are connected to the mounting base 21, thus securing rocket 6.

[0049] It is understandable that in the unlocked state, the mounting base 21 is horizontal; in the locked state, the mounting base 21 is vertical. During the transport of rocket 6, rocket 6 is generally placed horizontally, so the mounting base 21 in the locked state can provide axial fixation and limitation for rocket 6.

[0050] Understandably, the end of the erecting arm 1 has an opening communicating with the receiving cavity 11. In the locked state, the fixing base body 21 is at the opening, and the rocket 6 cannot move at the opening, thus limiting the movement of the rocket 6. In the unlocked state, the fixing base body 21 is not at the opening, so when the rocket 6 is hoisted into the receiving cavity 11, the rocket 6 can be hoisted from the opening into the receiving cavity 11, and then the rocket 6 can be fully adjusted into the receiving cavity 11.

[0051] In one embodiment of this application, the second end of the lug 22 is detachably connected to the mounting body 21.

[0052] Understandably, designing the mounting base body 21 and the lug 22 as a separate structure allows the lug 22 to be detached from the mounting base body 21 before rocket launch. This enables the lug 22 and the erecting arm 1 to be transported to a location away from rocket launch, preventing the exhaust gas flow during rocket launch from affecting the lug 22 and the erecting arm 1. Furthermore, the mounting base body 21 is rotatably connected to the erecting arm 1 via the lug 22. Removing the lug 22 prevents the exhaust gas flow from damaging the rotational shaft between the erecting arm 1 and the mounting base 2, reducing post-launch maintenance costs.

[0053] It is understandable that the mounting body 21 has a snap-fit ​​groove, and the second end of the lug 22 is inserted into the snap-fit ​​groove. The snap-fit ​​groove can limit the position of the lug 22, and then the connecting component is used to connect the second end of the lug 22 to the mounting body 21.

[0054] For example, the connecting components are bolts or screws or any other suitable structure.

[0055] For example, the fixed base body 21 is fixedly connected to the lug 22 via a connecting component. The connecting component includes a first connecting block, a second connecting block, a third connecting block, a connecting shaft, and a locking part. The second connecting block connects the first end of the first connecting block and the first end of the third connecting block. The first end of the connecting shaft is rotatably connected to the second end of the third connecting block. The locking part is adapted to connect the second end of the connecting shaft and the second end of the first connecting block. (Specific structure and...) Figure 6 The structure shown is the same and can be used as a reference. Figure 6 (To understand)

[0056] Specifically, the first end of the first connecting block is rotatably connected to the second connecting block, and the first end of the third connecting block is rotatably connected to the second connecting block. The first connecting block, the second connecting block, and the third connecting block form a clamping space. The connecting component is sleeved on the outer wall of the snap-fit ​​groove. The connecting shaft and the first connecting block are locked together by the locking part, so that the first connecting block, the second connecting block, the third connecting block, and the connecting shaft clamp the snap-fit ​​groove. The snap-fit ​​groove deforms to clamp the lug 22, so that the lug 22 and the fixed base body 21 are fixedly connected.

[0057] In one embodiment of this application, such as Figure 4 and Figure 5 As shown, the fixing seat 2 forms a limiting cavity 23, which is suitable for limiting and fixing the end of the rocket 6.

[0058] It is understandable that inserting the end (e.g., tail) of rocket 6 into the limiting cavity 23 allows the limiting cavity 23 to limit and fix rocket 6, thereby improving the stability of rocket 6 during transportation and tilting.

[0059] In one embodiment of this application, such as Figure 2 , Figure 3 and Figure 5 As shown, the first connecting component 3 includes a first connecting seat 31 formed on the fixed base 2. The first connecting seat 31 has a groove 32. The end of the erecting arm 1 is provided with a first connecting part 12. The first connecting part 12 is adapted to be engaged with the groove 32. The first connecting part 12 is provided with a locking member 125. The locking member 125 is adapted to connect the first connecting seat 31 and the first connecting part 12.

[0060] Understandably, by engaging the first connecting part 12 with the groove 32 of the first connecting seat 31, the groove 32 can limit the movement of the first connecting part 12. Simultaneously, the locking member 125 connects the first connecting seat 31 and the first connecting part 12 together, thus achieving a stable connection between the fixed seat 2 and the erecting arm 1. After the rocket 6 is flipped and erected, the locking member 125 is opened, and the first connecting part 12 is pulled out from the groove 32, allowing the fixed seat 2 and the erecting arm 1 to separate.

[0061] In the embodiments of this application, such as Figure 6 As shown, the first connecting part 12 includes a first connecting plate 121, a second connecting plate 122, a third connecting plate 123, a connecting rod 124, and a locking member 125. The second connecting plate 122 connects the first end of the first connecting plate 121 and the first end of the third connecting plate 123. The first end of the connecting rod 124 is rotatably connected to the second end of the third connecting plate 123. The locking member 125 is adapted to connect the second end of the connecting rod 124 and the second end of the first connecting plate 121. At least one of the first connecting plate 121, the second connecting plate 122, the third connecting plate 123, and the connecting rod 124 can be engaged in the groove 32.

[0062] Understandably, one or at least two of the first connecting plate 121, the second connecting plate 122, the third connecting plate 123, and the connecting rod 124 are engaged in the groove 32, and then the connecting rod 124 and the first connecting plate 121 are locked together by the locking member 125, so that one or at least two of the first connecting plate 121, the second connecting plate 122, the third connecting plate 123, and the connecting rod 124 are stably engaged in the groove 32, thus achieving a stable connection between the fixed seat 2 and the erecting arm 1. After the rocket 6 is flipped and erected, the locking member 125 is opened, and the connecting rod 124 is rotated so that the second end of the connecting rod 124 moves away from the first connecting plate 121, thereby allowing the first connecting part 12 to be pulled out from the groove 32, thus separating the fixed seat 2 and the erecting arm 1.

[0063] It is understood that the first end of the first connecting plate 121 and the second connecting plate 122 can be rotatably connected, and the first end of the third connecting plate 123 and the second connecting plate 122 can be rotatably connected.

[0064] For example, the locking member 125 is a locking nut, and the second end of the connecting rod 124 is threaded, so that the locking member 125 can connect the second end of the connecting rod 124 and the second end of the first connecting plate 121 together.

[0065] In one embodiment of this application, the second connecting component 4 includes a first windproof bolt, the fixing base 2 has a connecting hole, the first windproof bolt passes through the connecting hole and is adapted to be connected to the rocket 6.

[0066] It is understandable that connecting the mounting base 2 and the rocket 6 together with the first windproof bolt will ensure a stable connection between them. The first windproof bolt can be removed before the rocket 6 is launched.

[0067] It is understandable that there can be at least two first windproof bolts. Different first windproof bolts connect different positions of the fixing seat 2 and the rocket 6, thereby improving the stability of the connection between the fixing seat 2 and the rocket 6.

[0068] In one embodiment of this application, such as Figure 1 , Figure 3 , Figure 4 and Figure 5 As shown, the rocket fixing device includes a connecting belt locking assembly 5, which is installed on the fixing base 2. The connecting belt locking assembly 5 is adapted to be connected to the rocket 6, and the connecting belt locking assembly 5 is configured to melt or break upon being burned.

[0069] It is understandable that when the fixed base 2 is connected to the rocket 6, the connecting belt locking component 5 will also be connected to the rocket 6 at the same time, thereby increasing the limiting and fixing of the rocket 6 and improving the limiting and fixing effect of the rocket 6.

[0070] Understandably, during the launch of Rocket 6, the flames from Rocket 6 could cause the connecting belt locking assembly 5 to be burned, melting or breaking, thus ensuring that the connecting belt locking assembly 5 would not affect the launch of Rocket 6.

[0071] In one embodiment of this application, such as Figure 7 As shown, the connecting strap locking assembly 5 includes a connecting strap 52 and at least two locking seats 51. The at least two locking seats 51 are evenly distributed along the circumference of the fixing seat 2 and are connected by the connecting strap 52. The connecting strap 52 abuts against the end of the rocket 6, based on the connection between the fixing seat 2 and the rocket 6. Specifically, the connecting strap 52 in the connecting strap locking assembly 5 can be configured to melt or break upon being burned, thus securing the rocket before ignition and preventing any impact on the rocket's launch after ignition.

[0072] Understandably, during the transfer of rocket 6, the connecting strap 52 comes into contact with rocket 6, so that the connecting strap locking component 5, like the fixing seat 2, plays a limiting role in rocket 6. Furthermore, during the process of rocket 6 being flipped and erected, the connecting strap 52 can also provide support for rocket 6.

[0073] It is understandable that by evenly distributing the locking seats 51 along the circumference of the fixed seat, and then connecting multiple locking seats 51 together using the connecting straps 52, the distribution of the connecting straps 52 will also be more even, and the connecting straps 52 can provide better support for the rocket 6.

[0074] For example, the connecting strap locking assembly 5 includes at least two connecting straps 52, which are evenly distributed at the end of the rocket to provide uniform support and restraint for the rocket.

[0075] For example, a connecting strap 52 can connect to three or more locking seats 51 at the same time. For instance, the connecting strap 52 can connect to three locking seats 51 at the same time, so that the connecting strap 52 is distributed in a triangular shape. The connecting strap 52 can better support and limit the rocket 6.

[0076] In one embodiment of this application, such as Figure 7 As shown, a rotating block 53 is connected to the locking seat 51. The rotating block 53 can rotate relative to the locking seat 51. The two rotating blocks 53 at the locking seats 51 are connected by a connecting belt 52. The rotating block 53 is adapted to be connected to the rocket 6 by a locking connector 54. The rotating block 53 forms a locking groove 55. The locking connector 54 is inserted into the locking groove 55 and is adapted to be connected to the rocket 6.

[0077] It is understandable that during the launch and takeoff of Rocket 6, the exhaust gas from Rocket 6 will burn off the connecting belt 52 to prevent the connecting belt 52 from affecting the takeoff of Rocket 6.

[0078] Understandably, the locking connector 54 can be removed before the rocket 6 launches to avoid affecting the rocket 6's takeoff.

[0079] Understandably, when rocket 6 takes off, locking connector 54 remains connected to rocket 6. As rocket 6 rises, it will drive locking connector 54 to rise, which in turn will pull rotating block 53 to rotate, allowing locking connector 54 to disengage from locking groove 55, thus enabling rocket 6 to take off smoothly.

[0080] Understandably, the locking connector 54 is the second windproof bolt. This second windproof bolt is first inserted into the locking groove 55 and then connected to the rocket 6. Before the rocket 6 is launched, the bolt head is limited by the locking block 53 and cannot rise further. After the rocket 6 is launched, it applies an upward force to the second windproof bolt, causing the second windproof bolt to rotate and the locking groove 55 to open upwards. This removes the limitation imposed by the rotating block 53 on the head of the second windproof bolt, allowing it to rise along with the rocket 6, thus ensuring a smooth launch.

[0081] For example, the connecting strip 52 is a magnesium strip or any other suitable combustible strip.

[0082] For example, the connecting strip 52 is located within the limiting cavity 23.

[0083] Finally, it should be noted that the above embodiments are only used to illustrate this application and are not intended to limit this application. Although this application has been described in detail with reference to the embodiments, those skilled in the art should understand that various combinations, modifications, or equivalent substitutions of the technical solutions of this application do not depart from the spirit and scope of the technical solutions of this application and should be covered within the scope of the claims of this application.

Claims

1. A rocket securing device, characterised in that, The rocket fixing device comprises: an erecting arm, which is formed with a containing cavity for containing a rocket; a fixing base, which is used for fixing an end of the rocket; wherein a first end of the fixing base is rotatably connected to an end of the erecting arm; a first connecting assembly, which is arranged on the fixing base and is adapted to connect the fixing base and the erecting arm; a second connecting assembly, which is arranged on the fixing base and is adapted to connect the fixing base and the rocket; the fixing base comprises a fixing base body and a lug, a first end of the lug is rotatably connected to the erecting arm, and a second end of the lug is connected to the fixing base body, so that the fixing base body can be switched between an unlocked state and a locked state; in the locked state, the fixing base body abuts against a tail of the rocket, the first connecting assembly fixedly connects the fixing base body and the erecting arm, and the second connecting assembly fixedly connects the fixing base body and the rocket; in the unlocked state, the fixing base body can rotate relative to the erecting arm; the second end of the lug and the fixing base body are detachably connected; the first connecting assembly comprises a first connecting seat formed on the fixing base, the first connecting seat is formed with a groove, an end of the erecting arm is provided with a first connecting part, the first connecting part is adapted to be clamped in the groove, and the first connecting part is provided with a locking piece, which is adapted to connect the first connecting seat and the first connecting part; the first connecting part comprises a first connecting plate, a second connecting plate, a third connecting plate, a connecting rod and the locking piece, the second connecting plate connects a first end of the first connecting plate and a first end of the third connecting plate, a first end of the connecting rod is rotatably connected to a second end of the third connecting plate, the locking piece is adapted to connect a second end of the connecting rod and a second end of the first connecting plate, and at least one of the first connecting plate, the second connecting plate, the third connecting plate and the connecting rod can be clamped in the groove.

2. The rocket fixture of claim 1, wherein, the fixing base is formed with a limiting cavity, which is adapted to limit and fix the end of the rocket.

3. The rocket anchor of any one of claims 1 to 2, wherein, the second connecting assembly comprises a first windproof bolt, the fixing base is formed with a connecting hole, and the first windproof bolt is arranged in the connecting hole and is adapted to be connected with the rocket.

4. The rocket anchor of any one of claims 1 to 2, wherein, the rocket fixing device comprises a connecting belt locking assembly, which is arranged on the fixing base, is adapted to be connected with the rocket, and is arranged to be melted or broken after being burned.

5. The rocket anchor of claim 4, wherein, the connecting belt locking assembly comprises a connecting belt and at least two locking seats, and the at least two locking seats are uniformly distributed along the circumference of the fixing base; wherein the at least two locking seats are connected through the connecting belt and are connected with the rocket based on the fixing base; and the connecting belt abuts against the end of the rocket.

6. The rocket attachment of claim 5, wherein, The locking seat is connected with a rotating block, the rotating block can rotate relative to the locking seat, the rotating blocks at two locking seats are connected through the connecting belt, the rotating block is suitable for being connected with the rocket through a locking connector, wherein the rotating block is formed with a locking groove, the locking connector is inserted in the locking groove and is suitable for being connected with the rocket.

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