WO2021072826A1 - 用于模拟火箭发射的发射装置 - Google Patents

用于模拟火箭发射的发射装置 Download PDF

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Publication number
WO2021072826A1
WO2021072826A1 PCT/CN2019/115461 CN2019115461W WO2021072826A1 WO 2021072826 A1 WO2021072826 A1 WO 2021072826A1 CN 2019115461 W CN2019115461 W CN 2019115461W WO 2021072826 A1 WO2021072826 A1 WO 2021072826A1
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Prior art keywords
tower
rocket
cantilever
assembly
rocket body
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PCT/CN2019/115461
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English (en)
French (fr)
Inventor
陈文强
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唐山维数科技有限公司
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Publication of WO2021072826A1 publication Critical patent/WO2021072826A1/zh

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    • G—PHYSICS
    • G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
    • G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
    • G09B25/00—Models for purposes not provided for in G09B23/00, e.g. full-sized devices for demonstration purposes

Definitions

  • the invention relates to the field of popular science teaching aids, in particular to a launching device for simulating rocket launching.
  • Aerospace technology is very popular among young people.
  • videos and models In order to let young people understand the basic knowledge of aviation technology, they usually use videos and models to introduce the rocket launch process, especially the use of The model introduces this knowledge to young students in a vivid and detailed way.
  • the invention provides a launching device for simulating rocket launching, which can better enhance students' interest in learning aviation knowledge.
  • a launching device for simulating rocket launching includes: a rocket body; a base and a tower, the tower is installed on the base; a lifting assembly, the rocket body is movably installed on the base The lifting assembly; a cantilever assembly, the cantilever assembly is arranged on the tower to clamp or release the rocket body; a control device, the control device controls the cantilever assembly and the lifting assembly to work; wherein After the control device controls the cantilever assembly to switch from the clamped state to the released state, the elevator assembly is controlled to drive the rocket body to make an upward movement.
  • a spray device is provided on the rocket body, and the spray device is configured to spray water mist when the rocket body moves into the air.
  • the base includes a first body and a second body, the first body is disposed above the second body, and an overhead layer is formed between the first body and the second body.
  • the guide rail assembly includes: a rail member disposed on the tower; a slider member disposed on the rail member, the slider member connecting the rail member and the rocket body , To drive the rocket body to move up and down.
  • the cantilever assembly includes two cantilevers, and the two cantilevers are respectively mounted on the tower through a rotating shaft; one end of the cantilever is provided with a through hole for the rotating shaft to pass through, and the other end
  • a clamping part is provided on the upper part, and the clamping part is configured to clamp the rocket body.
  • the rotation angle of the above-mentioned cantilever is 45° to 90°.
  • the launching device further includes a tower crane arranged on the top of the tower, and the tower crane is detachably installed on the tower.
  • the top of the tower crane and the top of the rocket body are at the same level.
  • the movement distance of the rocket body on the rail is three-fifths of the distance from the top of the tower crane to the bottom of the base.
  • control device includes a controller arranged on the tower and a remote controller for remotely controlling the operation of the controller.
  • the launching device used for simulating rocket launching in the present invention is more interesting, making the learning of aviation knowledge more vivid and achieving good learning effects.
  • Figure 1 is a schematic diagram of a launching device used to simulate rocket launch (1)
  • Figure 2 is a schematic diagram of a launching device used to simulate rocket launch (2)
  • FIG. 3 is a schematic diagram of the launch frame in Figure 1;
  • FIG. 4 is a schematic diagram of the structure of area D in FIG. 3;
  • FIG. 5 is a schematic diagram of the structure of area E in FIG. 3;
  • Figure 6 is a schematic diagram of the structure of the base (1)
  • Figure 7 is a schematic diagram of the structure of the base (2)
  • Figure 8 is a schematic diagram of the structure of the lifting assembly
  • Fig. 9 is an enlarged schematic diagram of area F in Fig. 8.
  • Figure 10 is a schematic diagram of the structure of the cantilever assembly
  • Fig. 11 is an enlarged schematic diagram of area G in Fig. 10;
  • 2 is the base, 200 is the round hole, 201 is the first body, 202 is the second body, 203 is the mounting slot, 204 is the slot, and 205 is the plug;
  • 3 is the tower, 31 is the top of the tower, 32 is the clamping piece, and 301 is the mounting foot;
  • 4 is the lifting assembly, 41 is the rail, 411 is the first long rod, 412 is the second long rod, 42 is the slider component, 421 is the slider base, 422 is the bracket, 423 is the fixed part, and 43 is the first synchronization Wheel, 44 is the second synchronous wheel, 45 is the synchronous belt, 46 is the lifting motor;
  • 5 is the cantilever assembly
  • 51 is the cantilever
  • 511 is the shaft
  • 510 is the through hole
  • 512 is the clamping part
  • 52 is the protrusion
  • 53 is the first link
  • 54 is the second link
  • 55 is the motor
  • 56 is the rotation Rod
  • 6 is the control device
  • 7 is the tower crane
  • 100 is the launch device
  • 800 is the launch stand.
  • Figure 1 is a schematic diagram of a launching device used to simulate rocket launches (1)
  • Figure 2 is a schematic diagram of a launching device used to simulate rocket launches (2)
  • Figure 3 is a schematic diagram of the launcher in Figure 1.
  • 4 is a schematic diagram of the structure of area D in Figure 3
  • Figure 5 is a schematic diagram of the structure of area E in Figure 3
  • Figure 6 is a schematic diagram of the structure of the base (1)
  • Figure 7 is a schematic diagram of the structure of the base (2)
  • Figure 8 is a lifting assembly
  • Figure 9 is an enlarged schematic diagram of the F area in Figure 8
  • Figure 10 is a schematic structural diagram of the cantilever assembly
  • Figure 11 is an enlarged schematic diagram of the G area in Figure 10, as shown in Figure 1, Figure 2, Figure 3, Figure 4, As shown in Figure 5, Figure 6, Figure 7, Figure 8, Figure 9, Figure 10 and Figure 11:
  • a launching device 100 for simulating rocket launch which includes a rocket body 1, a base 2, a tower 3, a lifting assembly 4, a cantilever assembly 5 and a control device 6.
  • the rocket body 1 imitates the design of the Long March 2F manned carrier rocket, imitating the rocket's auxiliary 101, core stage first stage, core stage second stage, fairing, escape tower, etc.
  • the structure forms the outer shell of the rocket.
  • the rocket body 1 is equipped with a spray device 110 (not shown in the figure), including a storage chamber 102 (not shown in the figure), which can store liquid or liquid carbon dioxide.
  • the tail of the booster 101 generates an airflow that simulates propulsion, that is, it can directly spray water mist, or the water mist generated by the contact of liquid carbon dioxide with air, which highly simulates the propulsion scene during the rocket lift-off process.
  • the control device 6 can control a valve body (not shown in the figure) to open or close the storage chamber 102 to realize the above-mentioned spraying process.
  • the base 2 and the tower 3, and the tower 3 is installed on the base 2.
  • the base 2 includes a first body 201 and a second body 202, the first body 201 is disposed above the second body 202, and an overhead layer A is formed between the first body 201 and the second body 202.
  • At least one round hole 200 is provided on the first body 201.
  • the lifting assembly 4 is used to simulate the propulsion of the rocket when it is lifted into the air, and the rocket body 1 is movably installed on the lifting assembly 4.
  • the lifting assembly 4 includes: a rail 41 provided on the tower 3; a slider member 42 provided on the rail 41.
  • the slider member 42 is set to drive the rocket body 1 to move up and down on the rail 41. .
  • the cantilever assembly 5 is arranged on the tower 3 to clamp or release the rocket body 1.
  • the cantilever assembly 5 includes two cantilever arms 51, the two cantilever arms 51 are respectively mounted on the tower 3 via a rotating shaft 511, and the two cantilever arms 51 are pivoted to clamp or release the rocket body 1.
  • one end 511 of the cantilever 51 is provided with a through hole 510 through which the rotating shaft 511 passes, and the other end is provided with a clamping portion 512 configured to clamp the rocket body 1.
  • the rotation angle of the cantilever 51 is 45° to 90°, which can better clamp and release the rocket body 1.
  • control device 6 controls the cantilever assembly 5 and the lifting assembly 4 to work; the control device 6 controls the cantilever assembly 5 to turn from the clamped state to the released state, and then controls the lifting assembly 4 to drive the rocket body 1 to move upward. This movement imitates the effect of the rocket when it lifts up. After the lift-off is completed, the control device 6 controls the lifting assembly 4 to drive the rocket body 1 down to the initial position.
  • the control device 6 includes a controller 61 arranged on the tower 3 and a remote controller 62 (not shown in the figure) for remotely controlling the operation of the controller 61.
  • the remote controller 62 can simulate the control panel in the operating room, and by remotely controlling the launch of the rocket, the students can feel the fun of the rocket launching process more.
  • the launching device 100 further includes: a tower crane 7 arranged on the top 31 of the tower 3, and the tower crane 7 is detachably installed on the tower 3.
  • the top 71 of the tower crane 7 is at the same level as the top 11 of the rocket body 1, and the height is set at about 1.2 meters, which is convenient for packaging and transportation.
  • the movement distance of the rocket body 1 on the rail 41 is three-fifths of the distance from the top 71 of the tower crane 7 to the bottom of the base 2.
  • a launch stand 800 for simulating rocket launch is also provided.
  • the launch model it can be used separately from the rocket body 1, and the rocket body 1 can be installed on the launch stand 800.
  • the features of the launch frame 800 and other solutions of this embodiment can be combined with each other, as shown in FIG. 3, FIG. 4, FIG. 5, FIG. 6 and FIG. 7:
  • the launching frame 800 includes a base 2, a tower 3 and a lifting assembly 4, the tower 3 is installed on the base 2; wherein the lifting assembly 4 is used to simulate rocket lift-off, and the rocket body 1 is movably installed on the lifting assembly 4.
  • the launch frame 800 further includes: a tower crane 7 arranged on the top 31 of the tower 3, and the tower crane 7 is detachably installed on the tower 3.
  • the base 2 includes a first body 201 and a second body 202.
  • the first body 201 is disposed above the second body 202.
  • the first body 201 is detachably mounted on the second body 202 to form the base 2.
  • An overhead layer A is formed between the one body 201 and the second body 202.
  • At least one circular hole 200 is provided on the first body 201.
  • the water mist can pass through the circular hole 200 and emit from the aerial layer A, which further increases the propulsion during the rocket lift-off process. The realism of the scene.
  • the first body 201 is provided with a first circular portion 201a and a first square portion 201b
  • the second body 202 is provided with a second circular portion 202a and a second square portion 202b; wherein the first circular portion 201a and the second round portion 202a are set as the launch area B of the rocket body 1, and the first square portion 201b and the second square portion 202b are set as the installation area C where the tower 3 is installed.
  • the above-mentioned circular hole 200 is mounted on the circular portion 201a.
  • the area of the first circular portion 201a is smaller than the area of the second circular portion 202a, and this design can make the base more stable and reliable.
  • Most of the components of the launch frame 800 are connected and installed in a detachable installation manner, which is convenient for young people to install the launch model through hands-on operation, and can increase the interest of learning.
  • the launch frame 800 includes a plug 205 and a slot 204 provided on the first circular portion 201a and the second circular portion 202a; the plugs 205 are respectively inserted into the slots 204 to fixedly connect the first body 201 and the second body 202.
  • the six slots 204 and six pins 205 are arranged in a ring arrangement on the first circular portion 201a and the second circular portion 202a.
  • the launching frame 800 is installed on the above-mentioned installation area C in a plug-in manner.
  • the tower 3 is provided with mounting feet 301.
  • the mounting feet 301 are inserted into the mounting slots 203 provided on the first square portion 201b and the second square portion 202b.
  • the first body 201 and the second body 202 are fixedly connected.
  • four mounting feet 301 are provided, and four corresponding mounting grooves 203 are respectively provided on the first square portion 201b and the second square portion 202b.
  • another launch stand 800 for simulating rocket launch is also provided.
  • it can be used separately from the rocket body 1, and the rocket body 1 can be installed on the launch stand 800.
  • the launch stand 800 can be combined with the features in other solutions of this embodiment, as shown in FIGS. 3, 4, 5, 8 and 9:
  • the launching frame 800 includes a base 2, a tower 3 and a lifting assembly 4, the tower 3 is installed on the base 2; wherein the lifting assembly 4 is used to simulate rocket lift-off, and the rocket body 1 is movably installed on the lifting assembly 4.
  • the launch frame 800 further includes: a tower crane 7 arranged on the top 31 of the tower 3, and the tower crane 7 is detachably installed on the tower 3.
  • the lifting assembly 4 includes: a rail 41 provided on the tower 3; a slider member 42 provided on the rail 41.
  • the slider member 42 is set to drive the rocket body 1 to move up and down on the rail 41.
  • a clamping member 32 is provided on the tower 3, and the clamping member 32 is configured to fix the rail 41 in the vertical direction.
  • the movement distance of the rocket body 1 on the rail 41 is three-fifths of the distance from the top 71 of the tower crane 7 to the bottom of the base 2.
  • the track member 41 includes: a first long rod 411 and a second long rod 412, a guide groove 410 is formed between the first long rod 411 and the second long rod 412;
  • the timing belt 45 is installed in the guide groove 410 through the first timing wheel 43 and the second timing wheel 44, and the timing belt 45 drives the slider member 42 to make the rocket body 1 move up and down on the track member 41.
  • a lifting motor 46 is provided at the lower end of the first long rod 411, and the lifting motor 46 drives the first synchronous wheel 43 to rotate.
  • the lifting motor 46 can drive the first synchronization wheel 43 to rotate clockwise or counterclockwise through forward and reverse rotation. Under this action, the synchronization belt 45 can drive the slider member 42 to rise or fall, thereby driving the rocket body 1 to work on the rail 41. Lifting movement.
  • the slider component 42 includes a slider base 421, a bracket 422 arranged on the slider base 421, and a fixing member 423 installed on the bracket 422; wherein the fixing member 423 is fixedly connected to the rocket body 1 to make The rocket body 1 moves with the slider member 42.
  • brackets 422 are provided in two, which are respectively installed at two ends of the slider base 421; the fixing member 423 is provided with a fixing hole 424 for fixing the rocket body 1.
  • the base 2 described above includes a first body 201 and a second body 202.
  • the first body 201 is disposed above the second body 202.
  • the first body 201 is detachably mounted on the second body 202 to form the base 2.
  • An overhead layer A is formed between the one body 201 and the second body 202.
  • the first body 201 is provided with an installation opening 206 for accommodating the lifting motor 46, and the wires of the lifting motor 46 are arranged in the overhead layer A through the installation opening 206.
  • another launch stand 800 for simulating rocket launch is also provided.
  • the launch model it can be used separately from the rocket body 1, and the rocket body 1 can be installed on the launch stand 800.
  • the launch stand 800 can be combined with the features in other solutions of this embodiment, as shown in FIG. 3, FIG. 4, FIG. 5, FIG. 10, and FIG. 11:
  • the launch frame 800 includes a base 2, a tower 3, a lifting assembly 4 and a cantilever assembly 5, and the tower 3 is installed on the base 2.
  • the lift assembly 4 is used for simulating the lift-off of a rocket, and the rocket body 1 is movably installed on the lift assembly 4. After the rocket body 1 is turned from the clamped state to the released state by the cantilever assembly 5, the lifting assembly 4 can drive the rocket body 1 to move up and down.
  • the launch frame 800 further includes: a tower crane 7 arranged on the top 31 of the tower 3, and the tower crane 7 is detachably installed on the tower 3.
  • the base 2 and the tower 3, and the tower 3 is installed on the base 2.
  • the base 2 includes a first body 201 and a second body 202, the first body 201 is disposed above the second body 202, and an overhead layer A is formed between the first body 201 and the second body 202.
  • At least one round hole 200 is provided on the first body 201.
  • the lift assembly 4 is used to simulate the propulsion of the rocket when it is lifted into the air.
  • the rocket body 1 is movably installed on the lift assembly 4.
  • the lifting assembly 4 includes: a rail 41 provided on the tower 3; a slider member 42 provided on the rail 42.
  • the slider member 42 is set to drive the rocket body 1 to make a lifting movement on the rail 41. .
  • the cantilever assembly 5 is arranged on the tower 3.
  • the cantilever assembly 5 includes two cantilever arms 51.
  • the two cantilever arms 51 are respectively mounted on the tower 3 via a rotating shaft 511.
  • the two cantilever arms 51 can pivot to clamp or release the rocket body 1.
  • one end of the cantilever 51 is provided with a through hole 510 through which the rotating shaft 511 passes, and the other end is provided with a clamping portion 512 configured to clamp the rocket body 1.
  • the rotation angle of the cantilever 51 is 0° to 90°, which can better realize the clamping and release of the rocket body 1.
  • the cantilever 51 includes a first arm 51a and a second arm 51b, the first arm 51a is disposed above the second arm 51b, and the first arm 51a and the second arm 51b are connected to each other.
  • One end of the first arm 51a and the second arm 51b are respectively provided with through holes 510a, 510b for the shaft 511 to pass through, and the other end is provided with clamping portions 512a, 512b, respectively, the clamping portion is configured to clamp the rocket Body 1.
  • the clamping portions 512a, 512b are provided with depressions, and the depressions are triangular in shape, which can clamp the rocket body 1 more firmly.
  • a first link 53 is provided on the end of the second arm 51b close to the rotating shaft 511, and the first link 53 is set to drive the second arm 51b and the first arm 51a to rotate during movement, that is, to drive the cantilever 51 to rotate To achieve opening and closing.
  • first connecting rods 53 are provided to connect the protrusions 52 on the second arms 51b of the two cantilevers 51 respectively.
  • the cantilever assembly 5 further includes a second connecting rod 54 connecting the two first connecting rods 53.
  • the second connecting rod 54 drives the two first connecting rods 53 to move when reciprocating to drive the rotation of the two cantilever arms 51.
  • the cantilever assembly 5 further includes a motor 55, a rotating rod 56 connected to the motor 55, the rotating rod 56 passes through the second connecting rod 54, and the motor 55 drives the rotating rod 56 to rotate to make the second connecting rod 54 reciprocate
  • the two first connecting rods 53 are driven by the second connecting rod 54 to control the rotation of the two cantilevers 51, that is, to open and close, so as to realize the clamping and releasing of the rocket body 1.

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Abstract

一种用于模拟火箭发射的发射装置（100），包括：火箭本体（1）；底座（2）和塔架（3），塔架（3）安装在底座（2）上；升降组件（4），火箭本体（1）可移动地安装在升降组件（4）上；悬臂组件（5），悬臂组件（5）设置在塔架（3）上用以夹持或释放火箭本体（1）；控制装置（6），控制装置（6）控制悬臂组件（5）和升降组件（4）工作；其中控制装置（6）控制悬臂组件（5）从夹持状态转为释放状态后，控制升降组件（4）带动火箭本体（1）作上升运动。

Description

用于模拟火箭发射的发射装置 【技术领域】
本发明涉及科普教具领域，具体涉及一种用于模拟火箭发射的发射装置。
【背景技术】
近年来，中小学校对于学生的课外扩展教育日益重视，其中航空航天科技深受青少年的喜爱，为了让青少年了解航空科技的基础知识，通常用视频和模型介绍火箭发射升空的过程，尤其是利用模型以生动细致的方式把这些知识介绍给青少年学生。
目前，市面上的火箭发射多为固定模型，学生无法演练火箭的升空过程，如仅仅通过图文和视频资料，学生的学习兴趣不高，从而无法达到寓教于乐的效果，学生对知识的接收不强。
【发明内容】
本发明提供一种用于模拟火箭发射的发射装置，能更好地提升学生学习航空知识的兴趣。
根据本发明提供的一种用于模拟火箭发射的发射装置，包括：火箭本体；底座和塔架，所述塔架安装在所述底座上；升降组件，所述火箭本体可移动地安装在所述升降组件上；悬臂组件，所述悬臂组件设置在所述塔架上用以夹持或释放所述火箭本体；控制装置，所述控制装置控制所述悬臂组件和所述升降 组件工作；其中所述控制装置控制所述悬臂组件从夹持状态转为释放状态后，控制所述升降组件带动所述火箭本体作上升运动。
在一个实施方案中，所述火箭本体上设有喷雾装置，所述喷雾装置被设置为在所述火箭本体作升空运动时喷出水雾。
在一个实施方案中，所述底座包括第一本体和第二本体，所述第一本体设置在所述第二本体上方，所述第一本体和所述第二本体之间形成架空层。
在一个实施方案中，所述导轨组件包括：设置在所述塔架上的轨道件；设置在所述轨道件上的滑块部件，所述滑块部件连接所述轨道件和所述火箭本体，以带动使得所述火箭本体作升降运动。
在一个实施方案中，所述悬臂组件包括两个悬臂，两个所述悬臂分别通过转轴安装在所述塔架上；所述悬臂的一端设有供所述转轴穿过的通孔，另一端上设有夹持部，所述夹持部被设置为用于夹持火箭本体。
在一个实施方案中，上述悬臂的旋转角度为45°至90°。
在一个实施方案中，发射装置还包括：设置在所述塔架顶部的塔吊，所述塔吊以可拆卸的方式安装在所述塔架上。
在一个实施方案中，所述塔吊的顶部与所述火箭本体的顶部在同一水平高度。
在一个实施方案中，所述火箭本体在所述轨道件上的运动距离为所述塔吊的顶部到所述底座底部距离的五分之三。
在一个实施方案中，所述控制装置包括设置在所述塔架上的控制器和远程控制所述控制器工作的遥控器。
通过本发明中的用于模拟火箭发射的发射装置，相比传统的视频教学，更具有趣味性，使得学习航空知识变得更加生动，达到良好的学习效果。
【附图说明】
此处所说明的附图用来提供对本发明的进一步理解，构成本申请的一部分，本发明的示意性实施例及其说明用于解释本发明，并不构成对本发明的不当限定。在附图中：
图1是一种用于模拟火箭发射的发射装置的示意图(一)；
图2是一种用于模拟火箭发射的发射装置的示意图(二)；
图3是图1中发射架的示意图；
图4是图3中D区域的结构示意图；
图5是图3中E区域的结构示意图；
图6是底座的结构示意图(一)；
图7是底座的结构示意图(二)；
图8是升降组件的结构示意图；
图9是图8中F区域的放大示意图；
图10是悬臂组件的结构示意图；
图11是图10中G区域的放大示意图；
附图中：
1为火箭本体，101为助推器，102为存储室；
2为底座，200为圆孔，201为第一本体，202为第二本体，203为安装槽，204为插槽，205为插销；
3为塔架，31为塔顶，32为卡接件，301为安装脚；
4为升降组件，41为轨道件，411为第一长杆，412为第二长杆，42为滑块部件，421为滑块底座，422为支架，423为固定件，43为第一同步轮，44为第二同步轮，45为同步带，46为升降电机；
5为悬臂组件，51为悬臂，511为转轴，510为通孔，512为夹持部，52为突起部，53为第一连杆，54为第二连杆，55为电机，56为转动杆；
6为控制装置，7为塔吊，100为发射装置，800为发射架。
【具体实施方式】
下文中将参考附图并结合实施例来详细说明本发明。需要说明的是，在不冲突的情况下，本申请中的实施例及实施例中的特征可以相互组合。实施例中多数部件通过可拆卸的方式安装，便于青少年通过自己安装来学习火箭发射模型的结构和工作原理。
图1是一种用于模拟火箭发射的发射装置的示意图(一),图2是一种用于模拟火箭发射的发射装置的示意图(二),图3是图1中发射架的示意图,图4是图3中D区域的结构示意图,图5是图3中E区域的结构示意图,图6是底座的结构示意图(一),图7是底座的结构示意图(二),图8是升降组件的结构示意图,图9是图8中F区域的放大示意图,图10是悬臂组件的结构示意图,图11是图10中G区域的放大示意图，如图1、图2、图3、图4、图5、图6、图7、图8、图9、图10和图11所示：
在本实施例中，提供了一种用于模拟火箭发射的发射装置100，包括：火箭本体1，底座2，塔架3，升降组件4，悬臂组件5和控制装置6。
如图1所示，火箭本体1，模仿了长征2F载人运载火箭的设计，模仿了运载火箭的助器101、芯级第一级、芯级第二级、整流罩、逃逸塔等箭体结构组成了火箭的外壳体。为了演示火箭升空的效果，火箭本体1设有喷雾装置110(图中未显示)，包括存储室102(图中未显示)，可存储液体或液态二氧化碳，在火箭演练发射的时候，能够在助推器101的尾部产生模拟推进的气流，即能够直接喷 射出水雾，或者液体二氧化碳与空气接触生成的水雾，高度的模拟了火箭升空过程中的推进场景。具体地，可由控制装置6控制阀体(图中未示出)打开或关闭存储室102来实现上述喷雾过程。
底座2和塔架3，塔架3安装在底座2上。作为优选，底座2包括第一本体201和第二本体202，第一本体201设置在第二本体202上方，第一本体201和第二本体202之间形成架空层A。第一本体201上至少设置一个圆孔200，在上述助推器101喷雾时，水雾能够穿过上述圆孔200从架空层A散发出来，进一步增加了火箭升空过程中的推进场景的真实度。
升降组件4，用于模拟火箭升空时的推进，火箭本体1可移动地安装在升降组件4上。具体地，升降组件4包括：设置在塔架3上的轨道件41；设置在轨道件41上的滑块部件42，滑块部件42被设置为带动火箭本体1在轨道件41上作升降运动。
悬臂组件5，悬臂组件5设置在塔架3上用以夹持或释放火箭本体1。悬臂组件5包括两个悬臂51，两个悬臂51分别通过转轴511安装在塔架3上，两个悬臂51通过作枢转运动以夹持或释放火箭本体1。具体地，悬臂51的一端511设有供转轴511穿过的通孔510，另一端上设有夹持部512，夹持部512被设置为用于夹持火箭本体1。悬臂51的旋转角度为45°至90°，这样能够较好地实现对火箭本体1的夹持和释放。
控制装置6，控制装置6控制悬臂组件5和升降组件4工作；其中控制装置6控制悬臂组件5从夹持状态转为释放状态后，控制升降组件4带动火箭本体1作上升运动。该运动模仿了火箭升空时的效果，在完成升空后，控制装置6控制升降组件4带动火箭本体1下降至初始位置。
作为优选，控制装置6包括设置在塔架3上的控制器61和远程控制控制器61工作的遥控器62(图中未显示)。遥控器62可模拟操作室内的控制面板，通过远程控制火箭的发射，使得学生们更能感受到火箭发射过程中趣味性。
作为优选方案，发射装置100还包括：设置在塔架3顶部31的塔吊7，塔吊7以可拆卸的方式安装在塔架3上。塔吊7的顶部71与火箭本体1的顶部11在同一水平高度，高度设置在1.2米左右，这样便于包装运输。
在模拟的火箭发射运动过程中，火箭本体1在轨道件41上的运动距离为塔吊7的顶部71到底座2底部距离的五分之三。
在本实施中，还提供用于模拟火箭发射的发射架800，作为上述发射模型的一部分，可与上述火箭本体1分开使用，上述火箭本体1可安装在发射架800上。在不冲突的情况下，发射架800与本实施例其它方案中的特征可以相互组合，如图3、图4、图5、图6和图7所示:
发射架800包括：底座2、塔架3和升降组件4，塔架3安装在底座2上；其中升降组件4用于模拟火箭升空，火箭本体1可移动地安装在升降组件4上。可选的，发射架800还包括：设置在塔架3顶部31的塔吊7，塔吊7以可拆卸的方式安装在塔架3上。
底座2包括第一本体201和第二本体202，第一本体201设置在第二本体202上方，作为优选，第一本体201通过可拆卸的方式安装在第二本体202上以形成底座2，第一本体201和第二本体202之间形成架空层A。
作为优选，第一本体201上至少设置一个圆孔200，在上述助推器101喷雾时，水雾能够穿过上述圆孔200从架空层A散发出来，进一步增加了火箭升空过程中的推进场景的真实度。
作为优选，第一本体201上设有第一圆形部201a和第一方形部201b，第二本体202上设有第二圆形部202a和第二方形部202b；其中第一圆形部201a与第二圆形部202a被设置成火箭本体1的发射区B，第一方形部201b与第二方形部202b被设置成安装塔架3的安装区C。具体地，上述圆孔200安装在圆形部201a上。
作为优选，第一圆形部201a的面积小于第二圆形部202a的面积，该设计能使得底座更加稳定牢靠。
发射架800的部件多数采用可拆卸的安装方式连接安装，便于青少年通过动手操作安装发射模型，能够增加学习的趣味性。
发射架800包括插销205，以及设置在第一圆形部201a和所述第二圆形部202a上的插槽204；插销205分别插入插槽204中以固定连接第一本体201和第二本体202。
具体地，插槽204和插销205分别设置六个，六个插槽204在第一圆形部201a与第二圆形部202a上设置成环状排布。
发射架800以插接的方式安装在上述安装区C上，塔架3上设有安装脚301，安装脚301通过插入第一方形部201b与第二方形部202b上设置的安装槽203以固定连接第一本体201和第二本体202。具体地，安装脚301设有四个，第一方形部201b与第二方形部202b上分别设有对应的四个安装槽203。
在本实施中,还提供另一种用于模拟火箭发射的发射架800，作为上述发射模型的一部分，可与上述火箭本体1分开使用，上述火箭本体1可安装在发射架800上。在不冲突的情况下，该发射架800与本实施例其它方案中的特征可以相互组合，如图3、图4、图5、图8和图9所示:
发射架800包括：底座2、塔架3和升降组件4，塔架3安装在底座2上；其中升降组件4用于模拟火箭升空，火箭本体1可移动地安装在升降组件4上。可选的，发射架800还包括：设置在塔架3顶部31的塔吊7，塔吊7以可拆卸的方式安装在塔架3上。
具体地，升降组件4包括：设置在塔架3上的轨道件41；设置在轨道件41上的滑块部件42，滑块部件42被设置为带动火箭本体1在轨道件41上作升降运动。作为优选，塔架3上设有卡接件32，卡接件32被设置为在竖直方向上固定轨道件41。作为优选，火箭本体1在轨道件41上的运动距离为塔吊7的顶部71到底座2底部距离的五分之三。
作为优选，所述轨道件41包括：第一长杆411和第二长杆412，第一长杆411和第二长杆412之间形成一个导向槽410；分别设置在第一长杆411和第二长杆412两端的第一同步轮43和第二同步轮44；
以及同步带45，同步带45通过第一同步轮43和第二同步轮44安装在导向槽410内，同步带45通过带动滑块部件42以使得火箭本体1在轨道件41上作升降运动。
作为优选，第一长杆411的下端设有升降电机46，升降电机46驱动所述第一同步轮43转动。升降电机46能够通过正反转带动第一同步轮43顺时针或逆时针转动，同步带45在此作用下能够带动滑块部件42作上升或下降，从而带动火箭本体1在轨道件41上作升降运动。
作为优选，所述滑块部件42包括滑块底座421，设置在滑块底座421上的支架422，以及安装在支架422上的固定件423；其中固定件423与火箭本体1固定连接，以使得火箭本体1随滑块部件42运动。
具体地，上述支架422设置为两个，分别安装在滑块底座421的两端；固定件423上设有固定火箭本体1的固定孔424。
上述底座2包括第一本体201和第二本体202，第一本体201设置在第二本体202上方，作为优选，第一本体201通过可拆卸方式安装在第二本体202上以形成底座2，第一本体201和第二本体202之间形成架空层A。
作为优选，第一本体201上设有容纳升降电机46的安装开口206，升降电机46的导线通过安装开口206设置在架空层A内。
在本实施中，还提供了又一种用于模拟火箭发射的发射架800，作为上述发射模型的一部分，可与上述火箭本体1分开使用，上述火箭本体1可安装在发射架800上。在不冲突的情况下，该发射架800与本实施例其它方案中的特征可以相互组合，如图3、图4、图5、图10和图11所示:
发射架800包括：底座2、塔架3、升降组件4和悬臂组件5，塔架3安装在底座2上。升降组件4用于模拟火箭升空，火箭本体1可移动地安装在升降组件4上。火箭本体1在被悬臂组件5从夹持状态转为释放状态后，升降组件4可带动火箭本体1作升降运动。
可选的，发射架800还包括：设置在塔架3顶部31的塔吊7，塔吊7以可拆卸的方式安装在塔架3上。
底座2和塔架3，塔架3安装在底座2上。作为优选，底座2包括第一本体201和第二本体202，第一本体201设置在第二本体202上方，第一本体201和第二本体202之间形成架空层A。第一本体201上至少设置一个圆孔200，在上述助推器101喷雾时，水雾能够穿过上述圆孔200从架空层A散发出来，进一步增加了火箭升空过程中的推进场景的真实度。
升降组件4，用于模拟火箭升空时的推进，火箭本体1可移动地安装在升 降组件4上。具体地，升降组件4包括：设置在塔架3上的轨道件41；设置在轨道件42上的滑块部件42，滑块部件42被设置为带动火箭本体1在轨道件41上作升降运动。
悬臂组件5，悬臂组件5设置在塔架3上。悬臂组件5包括两个悬臂51，两个悬臂51分别通过转轴511安装在塔架3上，两个悬臂51能作枢转以夹持或释放火箭本体1。具体地，悬臂51的一端设有供转轴511穿过的通孔510，另一端上设有夹持部512，夹持部512被设置为用于夹持火箭本体1。悬臂51的旋转角度为0°至90°，这样能够较好地实现对火箭本体1的夹持和释放。
具体地，悬臂51包括第一臂51a和第二臂51b，第一臂51a设置在第二臂51b的上方，第一臂51a和第二臂51b互相连接。第一臂51a和第二臂51b上的一端分别设有供转轴511穿过的通孔510a，510b，另一端分别设有夹持部512a，512b，夹持部被设置为用于夹持火箭本体1。优选地，夹持部512a，512b上设有凹陷，该凹陷设置呈三角形，能够更牢靠地夹持火箭本体1。
作为优选方案，第二臂51b靠近转轴511的一端上设有第一连杆53，第一连杆53被设置成在运动时带动第二臂51b和第一臂51a转动，即带动悬臂51转动以实现张开和闭合。
对应地，第一连杆53设置两个，分别连接两个悬臂51的第二臂51b上的突起部52。
作为优选，悬臂组件5还包括连接两个第一连杆53的第二连杆54，第二连杆54作往复运动时带动两个第一连杆53运动从而带动两个悬臂51的转动。
作为优选，悬臂组件5还包括电机55，与电机55连接的转动杆56，转动杆56穿设在第二连杆54上，电机55通过驱动转动杆56转动以使第二连杆54 作往复运动，两个第一连杆53在第二连杆54的带动下控制两个悬臂51的转动，即张开和闭合，以实现对火箭本体1的夹持和释放。
上文所描述以及附图所示的各种具体实施方式仅用于说明本发明，并非本发明的全部。在本发明的基本技术思想的范畴内，相关技术领域的普通技术人员针对本发明所进行的任何形式的变更均在本发明的保护范围之内。

Claims (10)

  1. 一种用于模拟火箭发射的发射装置，其特征在于，包括：
    火箭本体(1)；
    底座(2)和塔架(3)，所述塔架(3)安装在所述底座(2)上；
    升降组件(4)，所述火箭本体(1)可移动地安装在所述升降组件(4)上；
    悬臂组件(5)，所述悬臂组件(5)设置在所述塔架(3)上用以夹持或释放所述火箭本体(1)；
    控制装置(6)，所述控制装置(6)控制所述悬臂组件(5)和所述升降组件(4)工作；
    其中所述控制装置(6)控制所述悬臂组件(5)从夹持状态转为释放状态后，控制所述升降组件(4)带动所述火箭本体(1)作上升运动。
  2. 如权利要求1所述的发射装置，其特征在于：
    所述火箭本体(1)上设有喷雾装置(110)，所述喷雾装置(110)被设置为在所述火箭本体(1)作升空运动时喷出水雾。
  3. 如权利要求1所述的发射装置，其特征在于：
    所述底座(2)包括第一本体(201)和第二本体(202)，所述第一本体(201)设置在所述第二本体(202)上方；
    其中所述第一本体(201)和所述第二本体(202)之间形成架空层A.
  4. 如权利要求1所述的发射装置，其特征在于，所述升降组件(4)包括：
    设置在所述塔架(3)上的轨道件(41)；
    设置在所述轨道件(41)上的滑块部件(42)，所述滑块部件(42)被设置为带动所述火箭本体(1)在所述轨道件(41)上作升降运动。
  5. 如权利要求1所述的发射装置，其特征在于：
    所述悬臂组件(5)包括两个悬臂(51)，两个所述悬臂(51)分别通过转轴(511)安装在所述塔架(3)上；
    所述悬臂(51)的一端设有供所述转轴(511)穿过的通孔(510)，另一端上设有夹持部(512)，所述夹持部(512)被设置为用于夹持所述火箭本体(1)。
  6. 如权利要求5所述的发射装置，其特征在于：
    所述悬臂(51)的旋转角度为45°至90°。
  7. 如权利要求4所述的发射装置，其特征在于，包括：
    设置在所述塔架(3)顶部的塔吊(7)，所述塔吊(7)以可拆卸的方式安装在所述塔架(3)上。
  8. 如权利要求7所述的发射装置，其特征在于：
    所述塔吊(7)的顶部(71)与所述火箭本体(1)的顶部(11)在同一水平高度。
  9. 如权利要求8所述的发射装置，其特征在于：
    所述火箭本体(1)在所述轨道件(41)上的运动距离为所述塔吊(7)的顶部(71)到所述底座(2)底部距离的五分之三。
  10. 如权利要求1所述的发射装置，其特征在于：
    所述控制装置(6)包括设置在所述塔架(3)上的控制器(61)和远程控制所述控制器(61)工作的遥控器(62)。
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