CN111854545B - Boosting gliding small-sized test rocket system - Google Patents
Boosting gliding small-sized test rocket system Download PDFInfo
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
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Abstract
Description
技术领域technical field
本发明属于火箭试验领域,尤其涉及一种助推滑翔小型试验火箭系统。The invention belongs to the field of rocket testing, in particular to a small-scale test rocket system for boosting and gliding.
背景技术Background technique
现有的小型示范火箭只能通过展示模型,使学生观察其内部的大概结构,说明其包含的模块及功能,无法进行设计、组装、测试分析等实践环节,更不能进行试飞或作为创新技术的应用载体。The existing small demonstration rockets can only be displayed by the model, so that students can observe the general structure of its interior, explain the modules and functions it contains, and cannot carry out practical links such as design, assembly, test analysis, etc., let alone test flight or as an innovative technology. application vector.
现有的火箭中都带有发动机作为动力,火箭在发射架上安置好后点火发射,在火箭内置发动机的工作推力下向前飞行。但是对于火箭发射流程来说,内置发动机的小型火箭在存储、转运、保存及发射过程,尤其是安装过程有较大的危险性。而且发动机成本大,通常占据整个教学火箭30%以上;质量大,约占据整个火箭质量的30%以上,因此发动机占据了教学火箭尾部大量的空间。现有的带有发动机的动力火箭系统对于教学试验来说存在较大的安全隐患,而且火箭发动机不能通过回收重复使用,导致使用成本高。Existing rockets are powered by engines. After the rocket is installed on the launch pad, it is ignited and launched, and it flies forward under the working thrust of the built-in engine of the rocket. However, for the rocket launch process, small rockets with built-in engines are more dangerous in the process of storage, transfer, preservation and launch, especially the installation process. Moreover, the cost of the engine is large, usually occupying more than 30% of the entire teaching rocket; the mass is large, accounting for more than 30% of the mass of the entire rocket, so the engine occupies a large amount of space at the rear of the teaching rocket. The existing powered rocket system with an engine has great potential safety hazards for teaching experiments, and the rocket engine cannot be reused through recycling, resulting in high use costs.
发明内容SUMMARY OF THE INVENTION
本发明要解决的技术问题是怎样解决现有小型示范火箭只能观察不能试飞且因带有发动机使得危险性增大的问题,提供了一种不带发动机且可试飞的助推滑翔小型试验火箭系统。The technical problem to be solved by the present invention is how to solve the problem that the existing small demonstration rockets can only be observed and cannot be tested, and the danger is increased due to the engine, so as to provide a small test rocket for boost gliding without an engine and capable of test flight system.
为解决该问题,本发明所采用的技术方案是:In order to solve this problem, the technical scheme adopted in the present invention is:
一种助推滑翔小型试验火箭系统,包括箭体及地面助力发射装置,在所述箭体包括头锥舱、设备舱、边条翼和尾舵,所述设备舱内装设有卫星天线、用于控制尾舵的舵控盒、用于对火箭的飞行进行测绘的遥测模块、用于对火箭飞行时提供解算和修正的飞控板、用于为箭体内各部件提供电源支持的电池组、用于为火箭提供导航功能的GPS,用于对火箭进行回收的回收系统,所述地面助力发射装置包括发射架基座,所述发射架基座前后两端分别安装有俯仰角调节支撑杆和导轨滑台托架,导轨滑台架设在所述俯仰角调节支撑杆和导轨滑台托架上,导轨滑台沿中间轴线上开设有供火箭向前滑行的火箭滑动槽,在导轨滑台的尾端安装有将火箭向前推行的发射助推器,所述箭体底部沿中心线前端装设有前滑行块,后端装有后滑行块,所述前滑行块和后滑行块在所述火箭滑动槽内滑行。A boost gliding small test rocket system includes an arrow body and a ground booster launching device, wherein the arrow body includes a nose cone cabin, an equipment cabin, a side strip wing and a tail rudder, and a satellite antenna is installed in the equipment cabin. The rudder control box used to control the tail rudder, the telemetry module used to map the flight of the rocket, the flight control board used to provide solutions and corrections when the rocket is flying, and the battery pack used to provide power support for various components in the
进一步地,所述发射助推器上部为空心柱状体,在所述空心柱状体中装设有弹簧,弹簧的前端套接有顶端密封的空心弹簧柱,所述空心弹簧柱可从空心柱状体的前端面自由伸缩,所述空心弹簧柱的密封端抵接在火箭的底部,所述弹簧的后端被封装在空心柱状体的尾端,在所述导轨滑台上沿导轨槽的两边分别装设一根光杆和一根丝杆,光杆和丝杆通过轴承座固定在所述导轨滑台上,所述发射助推器的底部开设有与所述丝杆上的螺纹啮合的螺纹,在所述导轨滑台的两侧分别开设有助推器滑行槽,所述发射助推器的底部横跨过光杆和丝杆后其底部两侧卡接在所述助推器滑行槽中,所述丝杆与电机相连接。Further, the upper part of the launch booster is a hollow cylindrical body, a spring is installed in the hollow cylindrical body, the front end of the spring is sleeved with a hollow spring column with a sealed top end, and the hollow spring column can be removed from the hollow cylindrical body. The front end of the spring is free to expand and contract, the sealing end of the hollow spring column abuts against the bottom of the rocket, and the rear end of the spring is encapsulated at the rear end of the hollow cylindrical body. A polished rod and a screw rod are installed, and the polished rod and the screw rod are fixed on the guide rail sliding table through the bearing seat, and the bottom of the launch booster is provided with a thread that engages with the thread on the screw rod. Both sides of the guide rail slide table are respectively provided with booster sliding grooves, and the bottom of the launch booster is clamped in the booster sliding groove after the bottom of the launch booster crosses the polished rod and the screw rod. The screw rod is connected with the motor.
进一步地,所述空心柱状体为锥形空心柱状体,靠近导轨滑台前端的截面圆直径小,后端截面圆直径大,所述弹簧柱从截面圆直径小的一端自由伸缩。Further, the hollow cylindrical body is a conical hollow cylindrical body, the cross-sectional circle near the front end of the guide rail slide table has a small diameter, and the rear cross-sectional circle has a large diameter.
进一步地,在所述火箭滑动槽内装设有防止火箭移动的止动螺栓,当火箭放置在导轨滑台上时,所述止动螺栓位于火箭的后滑行块之前。Further, a stop bolt for preventing the rocket from moving is installed in the rocket sliding groove, and when the rocket is placed on the guide rail sliding platform, the stop bolt is located in front of the rear sliding block of the rocket.
进一步地,所述止动螺栓包括一个螺钉,所述螺钉螺接在所述火箭滑动槽的底部,在所述螺钉顶部套设有一个弹簧,在所述弹簧外套设有一顶端为斜面的空心圆柱,所述空心圆柱的斜面朝向火箭滑动槽的后端。Further, the stop bolt includes a screw, the screw is screwed on the bottom of the rocket sliding groove, a spring is sleeved on the top of the screw, and a hollow cylinder with a sloped top is arranged on the spring jacket. , the inclined surface of the hollow cylinder faces the rear end of the rocket sliding slot.
进一步地,所述丝杆前端未刻有螺纹,在所述导轨滑台的侧边靠近丝杆螺纹的末端处装设有电机拨动开关,当所述发射助推器到达丝杆螺纹末端时,发射助推器触发电机拨动开关关闭电机。Further, the front end of the lead screw is not engraved with a thread, and a motor toggle switch is installed on the side of the guide rail slide near the end of the lead screw thread. When the launch booster reaches the end of the lead screw thread , the launch booster triggers the motor toggle switch to turn off the motor.
进一步地,在所述丝杆和导向杆的顶端装设有抗压弹簧。Further, compression springs are installed at the top ends of the screw rod and the guide rod.
进一步地,所述俯仰角调节支撑杆为双液压撑杆,所述双液压撑杆的上端与导轨滑台铰接,下端与所述发射架基座铰接,所述导轨滑台托架包括固接在发射架基座上的支撑架,在所述支撑架上装设有可随导轨滑台角度调整而转动的转动托架,所述火箭发射底座为铝板,通过膨胀螺栓固接在硬质地面上。Further, the pitch angle adjustment support rod is a double hydraulic support rod, the upper end of the double hydraulic support rod is hinged with the guide rail slide, and the lower end is hinged with the launcher base, and the guide rail slide bracket includes a fixed connection. The support frame on the base of the launch frame is provided with a rotating bracket that can be rotated with the angle adjustment of the guide rail slide, and the base of the rocket launcher is an aluminum plate, which is fixed on the hard surface through expansion bolts .
进一步地,所述回收系统包括回收伞包,爆炸螺栓,伞绳吊挂器、回收伞绳、牵引绳、回收伞盖板,所述回收伞包通过回收伞绳与伞绳吊挂器连接,所述伞绳吊挂器固接在箭体内,所述爆炸螺栓与回收伞盖板连接,所述牵引绳与回收伞盖板连接。Further, the recovery system includes a recovery umbrella bag, an explosion bolt, an umbrella rope hanger, a recovery umbrella rope, a traction rope, and a recovery umbrella cover plate, and the recovery umbrella bag is connected with the umbrella rope hanger through the recovery umbrella rope, The umbrella rope hanger is fixed in the arrow body, the explosion bolt is connected with the recovery umbrella cover plate, and the traction rope is connected with the recovery umbrella cover plate.
与现有技术相比,本发明所取得的有益效果是:Compared with the prior art, the beneficial effects achieved by the present invention are:
本发明一种助推滑翔小型试验火箭系统,箭体内根据试验需要装设各种试验设备,考虑到内置发动机的小型火箭在存储、转运、保存及发射过程,尤其是安装过程有较大的危险性,本发明在火箭体内没有安装动力系统发动机,而是在发射架上安装了发射助推器,将火箭发射出去,使得发射、存储及运输的过程也更加的安全,满足了试验的需要,并且采用了回收系统,便于火箭的回收再利用,维护简单,而且由于没有发动机,箭体的体积可以更小,或者箭体内可以安装更多的仪器进行试验,满足了低成本和安全的需要。The invention is a small test rocket system for boosting and gliding. Various test equipments are installed in the rocket body according to the test requirements. Considering that the small rocket with built-in engine is in the process of storage, transport, preservation and launch, especially the installation process has greater danger The present invention does not install a power system engine in the rocket body, but installs a launch booster on the launch frame to launch the rocket, which makes the process of launch, storage and transportation safer, and meets the needs of the test. Moreover, the recovery system is adopted, which is convenient for the recovery and reuse of the rocket, and the maintenance is simple. Moreover, because there is no engine, the volume of the rocket body can be smaller, or more instruments can be installed in the rocket body for testing, which meets the needs of low cost and safety.
附图说明Description of drawings
图1为本发明火箭系统的示意图;Fig. 1 is the schematic diagram of the rocket system of the present invention;
图2为俯仰角调节支撑杆和导轨滑台托架示意图;Figure 2 is a schematic diagram of the pitch angle adjustment support rod and the guide rail slide bracket;
图3为发射助推器与导轨滑台的连接示意图;Fig. 3 is the connection schematic diagram of the launch booster and the guide rail slide;
图4为导轨滑台上各部件放大示意图;Fig. 4 is the enlarged schematic diagram of each component on the guide rail slide;
图5为止动螺栓与火箭上后滑块的位置示意图;Figure 5 is a schematic diagram of the position of the stop bolt and the rear slider on the rocket;
图6为助推器滑动槽与火箭滑动槽示意图;Figure 6 is a schematic diagram of the booster sliding groove and the rocket sliding groove;
图7为火箭外形示意图;Figure 7 is a schematic diagram of the shape of the rocket;
图8为火箭前滑块和后滑块示意图;Figure 8 is a schematic diagram of the front slider and the rear slider of the rocket;
图9为火箭回收系统示意图。Figure 9 is a schematic diagram of the rocket recovery system.
图例说明:illustration:
1、箭体,11、头锥舱,12、设备舱,13、边条翼,14、尾舵,15、GPS,16、回收系统, 17、前滑块,18、后滑块;161、回收伞包,162、爆炸螺栓,163、伞绳吊挂器、164、回收伞绳,165、牵引绳,166、回收伞盖板;1. Arrow body, 11, nose cone cabin, 12, equipment cabin, 13, side strip, 14, tail rudder, 15, GPS, 16, recovery system, 17, front slider, 18, rear slider; 161, Recover umbrella bag, 162, Explosion bolt, 163, Umbrella rope hanger, 164, Recover umbrella rope, 165, Traction rope, 166, Recover umbrella cover;
2、地面助力发射装置,21、发射架基座,211、俯仰角调节支撑杆,212、导轨滑台托架, 2121、支撑架,2122、转动托架;2. Ground booster launcher, 21, Launcher base, 211, Pitch angle adjustment support rod, 212, Rail slide bracket, 2121, Support frame, 2122, Rotation bracket;
3、导轨滑台,31、火箭滑动槽,32、光杆,33、丝杆,34、助推器滑行槽,35、止动螺栓,36、电机拨动开关,37、抗压弹簧,38、轴承座;3. Guide rail sliding table, 31, Rocket sliding groove, 32, Polished rod, 33, Screw rod, 34, Booster sliding groove, 35, Stop bolt, 36, Motor toggle switch, 37, Compression spring, 38, bearing seat;
4、发射助推器,41、空心柱状体,42、弹簧,43、空心弹簧柱;4. Launch booster, 41, hollow cylindrical body, 42, spring, 43, hollow spring column;
5、电机,51、皮带,52、皮带轮。5. Motor, 51, belt, 52, pulley.
具体实施方式Detailed ways
图1至图9示出了本发明一种助推滑翔小型试验火箭系统的具体实施例,如图1、图2、图7所示,包括箭体1,在所述箭体包括头锥舱11、设备舱12、边条翼13和尾舵14,所述设备舱内装设有卫星天线、用于控制尾舵的舵控盒、用于对火箭的飞行进行测绘的遥测模块、用于对火箭飞行时提供解算和修正的飞控板、用于为箭体内各部件提供电源支持的电池组、用于为火箭提供导航功能的GPS15,用于对火箭进行回收的回收系统16,还包括地面助力发射装置 2,所述地面助力发射装置包括发射架基座21,所述发射架基座前后两端分别安装有俯仰角调节支撑杆211和导轨滑台托架212,导轨滑台3架设在所述俯仰角调节支撑杆211和导轨滑台托架上212,导轨滑台沿中间轴线上开设有供火箭向前滑行的火箭滑动槽31,在导轨滑台的尾端安装有将火箭向前推行的发射助推器4,所述箭体底部沿中心线前端装设有前滑块17,后端装有后滑块18,所述前滑块17和后滑块18在所述火箭滑动槽31内滑行。本发明通过在箭体 1内根据试验需要装设各种试验设备,由于火箭只是作为试验,考虑到内置发动机的小型火箭在存储、转运、保存及发射过程,尤其是安装过程有较大的危险性,本发明在火箭体内没有安装动力系统发动机,而是在发射架上安装了发射助推器,将火箭发射出去,使得发射、存储及运输的过程也更加的安全,满足了试验的需要,并且采用了回收系统,便于火箭的回收再利用,维护简单。箭体内装设的卫星天线、舵控盒、遥测模块、飞控板、电池组、GPS、回收系统等都是采用现有火箭中的常规设计,根据试验需要增减需要的模块,主要是从安全考虑取消了发动机,将发射助力系统安装在发射架上。通过俯仰角调节支撑杆211调节导轨滑台的发射角,通过导轨滑台3提供了火箭发射所需导轨,通过丝杆与发射助推器的啮合在电机的作用下加速发射助推器,发射助推器4将火箭助推到火箭所需的发射速度从而代替小型火箭上的发动机。与传统的发射架相比,该发射架通过发射助推器提供了小型火箭飞行所需的动力,使得小型火箭的质量降低至少30%,其可内置的更多的仪器设备进行试验,降低火箭的设计成本和难度,满足了低成本和安全的需要。Figures 1 to 9 show specific embodiments of a boost-gliding small test rocket system of the present invention, as shown in Figures 1, 2, and 7, including an
本实施例中,如图3、图4、图6所示,所述发射助推器4上部开设有空心柱状体41,在所述空心柱状体41中装设有弹簧42,弹簧的前端套接有顶端密封的空心弹簧柱43,所述空心弹簧柱43可从空心柱状体的前端面自由伸缩,所述空心弹簧柱43的密封端抵接在火箭的底部,所述弹簧42的后端被盖板封装在空心柱状体的尾端,在所述导轨滑台3上沿导轨槽的两边平行装设有一根光杆32和一根丝杆33,光杆32和丝杆33通过轴承座38固定在所述导轨滑台3 上,所述发射助推器4的底部开设有与所述丝杆上的螺纹啮合的螺纹,在所述导轨滑台3的两侧分别开设有助推器滑行槽34,所述发射助推器4的底部横跨过光杆32和丝杆33后其底部两侧卡接在所述助推器滑行槽34中,所述丝杆33与电机5相连接。本实施例主要通过位于发射助推器4上部的空气柱状体中的弹簧进行储能,空心弹簧柱43的前端与火箭底部接触,在发射助推器4向前滑行时依靠空心弹簧柱43挤压弹簧储能,当与丝杆连接的电机5启动后,电机5通过皮带51带动皮带轮52旋转,皮带轮带动丝杆旋转,丝杆33旋转后,由于发射助推器4依靠发射助推器4底部与丝杆啮合的螺纹,进而带动发射助推器前行。在导轨滑台3 两侧开设的助推器滑行槽34,将发射助推器的底部卡接在助推器滑行槽中,使发射助推器可以平稳的向前行进。与丝杆平行装设的光杆起导向的作用,当然也起到使发射推行器平衡稳固的横跨在丝杆与光杆上。In this embodiment, as shown in FIGS. 3 , 4 and 6 , a hollow
本实施例中,如图4所示,所述空心柱状体41为锥形空心柱状体,靠近导轨滑台前端的截面圆直径小,后端截面圆直径大,所述弹簧柱从截面圆直径小的一端自由伸缩。发射推行器 4上部所开设的空心柱状体41开设成锥形空心柱状体,一方面是便于弹簧与弹簧柱的安装,另一方面也便于通过盖板将弹簧封装在空心柱状体中。In this embodiment, as shown in FIG. 4 , the hollow
本实施例中,如图4、图5所示,在所述火箭滑动槽34内装设有防止火箭移动的止动螺栓35,当火箭放置在导轨滑台3上时,所述止动螺栓35位于火箭的后滑块18之前。本实施例中在丝杆33转动时驱动发射助推器向前行进时,由于火箭待发射前是借助于止动螺栓35静止在导轨滑台3上,发射时,发射助推器4在丝杆33旋转力的作用下向前滑行挤压空心弹簧柱43和弹簧42,待空心弹簧柱43和弹簧42对箭体1的推力大于小型试验火箭后滑块18 对止动螺栓35的推力时,将止动螺栓35向下推压后,小型火箭向前滑行。本实施例中所述止动螺栓35包括一个螺钉,所述螺钉螺接在所述火箭滑动槽的底部,在所述螺钉顶部套设有一个弹簧,在所述弹簧外套设有一顶端为斜面的空心圆柱,所述空心圆柱的斜面朝向火箭滑动槽的后端。当弹簧柱和弹簧对箭体施加推力时,火箭后滑块挤压止动螺栓空心圆柱的斜面,当该斜面受到20kg的推力时,顶端为斜面的空心圆柱往下压,不再阻挡发射助推器向前滑行,当斜面失去推力和压力时,止动螺栓35反弹。In this embodiment, as shown in FIGS. 4 and 5 , a
本实施例中,如图4所示,所述丝杆33前端未刻有螺纹,在所述导轨滑台3的侧边靠近丝杆螺纹的末端处装设有电机拨动开关36,当所述发射助推器4到达丝杆螺纹末端时,发射助推器触发电机拨动开关36关闭电机。本实施例中,丝杆33前端500mm没有螺纹,当发射助推器到达丝杆螺纹末端时,发射助推器4触发电机拨动开关36关闭电机5。电机5关闭后,发射助推器4以约35m/s的速度向前运动,此时,电机5不再给发射助推器4传递动能,发射助推器4与小型火箭之间的被压缩弹簧相互作用,弹簧42释放压缩势能,对小型火箭产生一个向前的推力,相互的也给发射助推器一个向后的推力,降低发射助推器向前的冲击速度。之后,小型火箭速度大于助推滑块,沿着火箭滑行槽向前滑出导轨滑台。而发射助推器借助惯性继续向前滑行,由于在丝杆与导向杆的前端装设有抗压弹簧37,被减速的发射助推器撞击在抗压弹簧上37,降低了发射助推器的冲击力,发射助推器与抗压弹簧数次作用直到减速停下。抗压弹簧37的作用一方面是起到减速的作用,另一方面则是避免助推器直接撞击到丝杆顶端的轴承座上,对发射架造成损伤。本实施例中,丝杆长约5m,丝杆的螺纹占有丝杆长度的9/10,受力大约300kg,材料为30CrMnSiA。In this embodiment, as shown in FIG. 4 , the front end of the
本实施例中,如图2所示,所述俯仰角调节支撑杆211为双液压撑杆,所述双液压撑杆的上端与导轨滑台铰接,下端与所述发射架基座铰接。所述导轨滑台托架212包括固接在发射架基座上的支撑架213,在所述支撑架上装设有可随导轨滑台角度调整而转动的转动托架214。转动托架主要起到承托导轨滑台的作用,并能够在俯仰角调节支撑杆调节导轨滑台的发射角度时,转动托架也能随导轨滑台的角度调整而调整,使转动托架更好地承托导轨滑台。本实施例中火箭发射底座为铝板,通过膨胀螺栓固接在硬质地面上,通过发射底座可以调节火箭发射的方位角。In this embodiment, as shown in FIG. 2 , the pitch angle
本实施例中,如图9所示,所述回收系统16包括回收伞包161,爆炸螺栓162,伞绳吊挂器163、回收伞绳164、牵引绳165、回收伞盖板166,所述回收伞包161通过回收伞绳164 与伞绳吊挂器163连接,所述伞绳吊挂器163固接在箭体1内,所述爆炸螺栓162与回收伞盖板166连接,所述牵引绳165与回收伞盖板连接。在助推滑翔教学试验火箭飞行至预定弹道的最高点向下倾斜时,控制系统发出指令信号爆炸螺栓爆炸,将回收伞盖板弹开。回收伞盖板166通过拉扯牵引绳165将回收伞包161从舱内拉出。回收伞包161另一侧连接着伞绳吊挂器163。待牵引绳165的拉力到达预定阈值时,牵引绳165断裂回收伞盖板166与回收伞包161自动分离,之后回收伞包打开,吊挂着助推滑翔小型试验火箭箭体结构落地回收。In this embodiment, as shown in FIG. 9 , the
本发明的动力发射架主要应用训练及试验发射使用。在平时训练和进行某些新技术验证发射时,保证了没有带火药发动机所带来的安全性问题,也显著的降低了发射成本。能满足绝大多数的学习训练及研究的要求,也为研究带来便利性。The power launcher of the present invention is mainly used for training and test launching. During normal training and some new technology verification launches, it is guaranteed that there are no safety problems brought about by the gunpowder engine, and the launch cost is also significantly reduced. It can meet most of the requirements of learning, training and research, and it also brings convenience to research.
以上仅是本发明的优选实施方式,本发明的保护范围并不仅局限于上述实施例,凡属于本发明思路下的技术方案均属于本发明的保护范围。应当指出,对于本技术领域的普通技术人员来说,在不脱离本发明原理前提下的若干改进和润饰,应视为本发明的保护范围。The above are only preferred embodiments of the present invention, and the protection scope of the present invention is not limited to the above-mentioned embodiments, and all technical solutions that belong to the idea of the present invention belong to the protection scope of the present invention. It should be pointed out that for those skilled in the art, some improvements and modifications without departing from the principle of the present invention should be regarded as the protection scope of the present invention.
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