CN111854545B - Boosting gliding small-sized test rocket system - Google Patents

Boosting gliding small-sized test rocket system Download PDF

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CN111854545B
CN111854545B CN202010498011.2A CN202010498011A CN111854545B CN 111854545 B CN111854545 B CN 111854545B CN 202010498011 A CN202010498011 A CN 202010498011A CN 111854545 B CN111854545 B CN 111854545B
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rocket
guide rail
launching
booster
sliding table
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CN111854545A (en
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江振宇
许秋平
杨华波
白锡斌
张士峰
彭科
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National University of Defense Technology
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National University of Defense Technology
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42AMMUNITION; BLASTING
    • F42BEXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B35/00Testing or checking of ammunition
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41WEAPONS
    • F41FAPPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00Rocket or torpedo launchers
    • F41F3/04Rocket or torpedo launchers for rockets
    • F41F3/0406Rail launchers

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Abstract

The invention provides a boosting gliding small-sized test rocket system which comprises an rocket body and a ground boosting launching device, wherein the rocket body comprises a nose cone cabin, an equipment cabin, a strake wing and a tail rudder, the ground boosting launching device comprises a launching rack base, a pitch angle adjusting supporting rod and a guide rail sliding table bracket are arranged at the front end and the rear end of the launching rack base, the guide rail sliding table is erected on the pitch angle adjusting supporting rod and the rocket sliding table bracket, a rocket sliding groove is formed in the guide rail sliding table along a middle axis, a launching booster is arranged at the tail end of the guide rail sliding table, a front sliding block is arranged at the bottom of the rocket body along the front end of a central line, a rear sliding block is arranged at the rear end of the bottom of the rocket body, and the front sliding block and the rear sliding block slide in the rocket sliding groove. According to the invention, the power system engine is not arranged in the rocket body, the launching booster is arranged on the launching frame, and the rocket is launched, so that the launching, storing and transporting processes are safer, the test requirements are met, the recovery system is adopted to recycle the rocket, and the maintenance is simple.

Description

一种助推滑翔小型试验火箭系统A boost-gliding small test rocket system

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 rocket body 2. GPS used to provide navigation function for rockets, and a recovery system used to recover rockets. The ground-assisted launching device includes a launcher base, and the front and rear ends of the launcher base are respectively installed with pitch angle adjustment support rods and the guide rail slide bracket, the guide rail slide table is erected on the pitch angle adjustment support rod and the guide rail slide table bracket, and the guide rail slide table is provided with a rocket sliding slot along the central axis for the rocket to slide forward, and the guide rail slide table is provided with a rocket sliding groove for the rocket to slide forward. The rear end of the rocket is installed with a launch booster that pushes the rocket forward, the bottom of the rocket body is equipped with a front sliding block along the center line at the front end, and a rear sliding block is installed at the rear end. The rocket slides in the sliding groove.

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 rocket body 1, where the rocket body includes a nose cone cabin 11. The equipment cabin 12, the side strips 13 and the tail rudder 14, the equipment cabin is equipped with a satellite antenna, a rudder control box for controlling the tail rudder, a telemetry module for mapping the flight of the rocket, and a The flight control board for solving and correcting the rocket during flight, the battery pack for providing power support for various components in the rocket body, the GPS15 for providing the rocket with the navigation function, the recovery system 16 for recovering the rocket, and the The ground booster launcher 2 includes a launcher base 21, and the front and rear ends of the launcher base are respectively installed with a pitch angle adjustment support rod 211 and a guide rail slide bracket 212, and the guide rail slide 3 is erected On the pitch angle adjustment support rod 211 and the guide rail slide bracket 212, the guide rail slide table is provided with a rocket sliding groove 31 for the rocket to slide forward along the central axis, and a rear end of the guide rail slide table is installed with a rocket to slide the rocket forward. For the launch booster 4 pushed forward, a front slider 17 is installed at the front end of the bottom of the rocket body along the center line, and a rear slider 18 is installed at the rear end. Slide in the sliding groove 31 . In the present invention, various test equipments are installed in the rocket body 1 according to the test requirements. Since the rocket is only used as a test, considering that the small rocket with built-in engine is in the process of storage, transportation, 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. And a recycling system is adopted, which is convenient for the recycling and reuse of the rocket, and the maintenance is simple. The satellite antenna, rudder control box, telemetry module, flight control board, battery pack, GPS, recovery system, etc. installed in the rocket body are all conventional designs in existing rockets. For safety reasons, the engine was eliminated and the launch assist system was installed on the launch pad. The launch angle of the guide rail slide is adjusted through the pitch angle adjustment support rod 211, and the guide rail required for the rocket launch is provided through the guide rail slide 3. Booster 4 replaces the motor on a small rocket by boosting the rocket to the desired launch velocity of the rocket. Compared with the traditional launch pad, the launch pad provides the power required for the flight of the small rocket through the launch booster, which reduces the mass of the small rocket by at least 30%. The cost and difficulty of design meet the needs of low cost and safety.

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 cylindrical body 41 is provided on the upper part of the launch booster 4 , a spring 42 is installed in the hollow cylindrical body 41 , and the front end of the spring is sleeved A hollow spring column 43 with a sealed top end is connected, and the hollow spring column 43 can freely expand and contract from the front end surface of the hollow cylindrical body. The cover plate is encapsulated at the rear end of the hollow cylindrical body, and a polished rod 32 and a screw rod 33 are installed in parallel on both sides of the guide rail groove on the guide rail slide table 3, and the polished rod 32 and the screw rod 33 are fixed by the bearing seat 38. On the guide rail slide table 3 , the bottom of the launch booster 4 is provided with a thread that engages with the thread on the screw rod, and the two sides of the guide rail slide table 3 are respectively provided with booster sliding grooves 34. After the bottom of the launch booster 4 crosses over the polished rod 32 and the screw rod 33, both sides of the bottom of the launch booster 4 are clamped in the booster sliding groove 34, and the screw rod 33 is connected to the motor 5. In this embodiment, the energy is stored mainly by the spring in the air column located at the upper part of the launch booster 4. The front end of the hollow spring column 43 is in contact with the bottom of the rocket, and is squeezed by the hollow spring column 43 when the launch booster 4 slides forward. The pressure spring stores energy. When the motor 5 connected with the screw rod starts, the motor 5 drives the pulley 52 to rotate through the belt 51, and the pulley drives the screw rod to rotate. After the screw rod 33 rotates, because the launch booster 4 relies on the launch booster 4 The thread at the bottom is engaged with the screw rod, which in turn drives the launch booster forward. The booster sliding grooves 34 provided on both sides of the guide rail slide table 3 clamp the bottom of the launch booster in the booster sliding groove, so that the launch booster can move forward stably. The polished rod installed in parallel with the screw rod plays a guiding role, and of course it also plays a role in making the launch pusher straddle the screw rod and the polished rod in a balanced and stable manner.

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 cylindrical body 41 is a conical hollow cylindrical body, the diameter of the cross-sectional circle near the front end of the guide rail slide table is small, and the diameter of the cross-sectional circle at the rear end is large. The small end stretches freely. The hollow cylindrical body 41 opened on the upper part of the launch pusher 4 is opened into a conical hollow cylindrical body, which is convenient for the installation of the spring and the spring column on the one hand, and on the other hand, it is also convenient to encapsulate the spring in the hollow cylindrical body through the cover plate.

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 stop bolt 35 is installed in the rocket sliding groove 34 to prevent the rocket from moving. When the rocket is placed on the guide rail slide 3 , the stop bolt 35 Located in front of the rear slider 18 of the rocket. In this embodiment, when the lead screw 33 rotates to drive the launch booster to move forward, since the rocket is stationary on the guide rail slide 3 by means of the stop bolt 35 before launching, the launch booster 4 is on the thread during launch. Under the action of the rotational force of the rod 33, the hollow spring column 43 and the spring 42 are slid forward to squeeze the hollow spring column 43 and the spring 42. When the thrust of the hollow spring column 43 and the spring 42 to the arrow body 1 is greater than the thrust of the rear slider 18 of the small test rocket to the stop bolt 35 , after pushing down the stop bolt 35, the small rocket slides forward. In this embodiment, the stop bolt 35 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 spring whose top is inclined A hollow cylinder, the inclined surface of the hollow cylinder faces the rear end of the rocket sliding slot. When the spring column and the spring exert thrust on the rocket body, the rear slider of the rocket squeezes the inclined surface of the hollow cylinder of the stop bolt. When the inclined surface is subjected to a thrust of 20kg, the hollow cylinder with the inclined surface at the top presses down, and no longer blocks the launch aid. The pusher slides forward, and when the ramp loses thrust and pressure, the stop bolt 35 rebounds.

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 lead screw 33 is not threaded, and a motor toggle switch 36 is installed on the side of the guide rail slide 3 near the end of the lead screw thread. When the launch booster 4 reaches the end of the screw thread, the launch booster triggers the motor toggle switch 36 to turn off the motor. In this embodiment, the front end of the lead screw 33 has no thread at 500 mm. When the launch booster reaches the end of the screw thread, the launch booster 4 triggers the motor toggle switch 36 to turn off the motor 5 . After the motor 5 is turned off, the launch booster 4 moves forward at a speed of about 35m/s. At this time, the motor 5 no longer transmits kinetic energy to the launch booster 4, and the space between the launch booster 4 and the small rocket is compressed. The springs interact, and the spring 42 releases the compression potential energy, which generates a forward thrust on the small rocket, and also gives the launch booster a backward thrust, reducing the forward impact velocity of the launch booster. After that, the speed of the small rocket is greater than that of the booster slider, and it slides forward along the rocket sliding slot and out of the rail slide. The launch booster continues to slide forward by virtue of inertia. Since a compression spring 37 is installed at the front end of the screw rod and the guide rod, the decelerated launch booster hits the compression spring 37, lowering the launch booster. The impact force, the launch booster and the compression spring act several times until the deceleration stops. On the one hand, the function of the anti-compression spring 37 is to decelerate, and on the other hand, it is to prevent the booster from directly hitting the bearing seat at the top of the screw rod, causing damage to the launcher. In this embodiment, the length of the screw is about 5m, the thread of the screw occupies 9/10 of the length of the screw, the force is about 300kg, and the material is 30CrMnSiA.

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 adjustment support rod 211 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. The guide rail slide bracket 212 includes a support frame 213 fixed on the base of the launch frame, and a rotating bracket 214 that can rotate with the angle adjustment of the guide rail slide table is installed on the support frame. The rotating bracket mainly plays the role of supporting the guide rail slide, and can adjust the launch angle of the guide rail slide when the support rod is adjusted in the pitch angle. Better support for rail slides. In this embodiment, the rocket launch base is an aluminum plate, which is fixed on the hard surface through expansion bolts, and the azimuth angle of the rocket launch can be adjusted through the launch base.

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 recovery system 16 includes a recovery umbrella bag 161 , an explosion bolt 162 , an umbrella rope hanger 163 , a recovery umbrella rope 164 , a traction rope 165 , and a recovery umbrella cover plate 166 . The recovery umbrella bag 161 is connected with the umbrella rope hanger 163 through the recovery umbrella rope 164, the umbrella rope hanger 163 is fixed in the arrow body 1, the explosion bolt 162 is connected with the recovery umbrella cover plate 166, and the traction The rope 165 is connected to the recovery umbrella cover. When the boost-gliding teaching test rocket flies to the highest point of the predetermined trajectory and tilts downward, the control system sends out a command signal to explode the bolts, which will pop open the recovery umbrella cover. The recovery umbrella cover plate 166 pulls the recovery umbrella bag 161 out of the cabin by pulling the traction rope 165 . The other side of the recovery umbrella bag 161 is connected with a paracord hanger 163 . When the pulling force of the traction rope 165 reaches a predetermined threshold, the traction rope 165 breaks and the recovery umbrella cover 166 is automatically separated from the recovery umbrella bag 161. After that, the recovery umbrella bag is opened, and the rocket body structure of the boost gliding small test rocket is suspended and recovered.

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.

Claims (9)

1. A small-size experimental rocket system of boosting gliding, including the rocket body, including nose cone cabin, equipment cabin, strake wing and tail vane at the rocket body, install satellite antenna, the rudder control box that is used for controlling the tail vane in the equipment cabin, a telemetry module that is used for surveying and mapping the flight of rocket, be used for providing the flight control board of resolving and revising when flying the rocket, be used for providing the group battery of power support for each part in the rocket body, a GPS for providing navigation function for the rocket, a recovery system for retrieving the rocket, its characterized in that: the ground power-assisted launching device comprises a launching frame base, a pitch angle adjusting support rod and a guide rail sliding table bracket are respectively arranged at the front end and the rear end of the launching frame base, the guide rail sliding table is erected on the pitch angle adjusting support rod and the guide rail sliding table bracket, a rocket sliding groove for the rocket to slide forwards is formed in the guide rail sliding table along an intermediate axis, a launching booster for pushing the rocket forwards is arranged at the tail end of the guide rail sliding table, a front sliding block is arranged at the bottom of the rocket body along the front end of the central line, a rear sliding block is arranged at the rear end of the rocket body, and the front sliding block and the rear sliding block slide in the rocket sliding groove;
the upper part of the launching booster is provided with a hollow cylindrical body, a spring is arranged in the hollow cylindrical body, the front end of the spring is sleeved with a hollow spring column with a sealed top end, the hollow spring column can freely stretch out and draw back from the front end surface of the hollow cylindrical body, the sealing end of the hollow spring column is abutted against the bottom of the rocket, the rear end of the spring is packaged at the tail end of the hollow cylindrical body, a polished rod and a lead screw are arranged on the guide rail sliding table in parallel along two sides of the guide rail groove, the polished rod and the lead screw are fixed on the guide rail sliding table through a bearing seat, the bottom of the launching booster is provided with a thread engaged with the thread on the lead screw, two sides of the guide rail sliding table are respectively provided with a booster sliding groove, the bottom of the launching booster stretches across a polished rod and a screw rod, and then two sides of the bottom of the launching booster are clamped in the booster sliding grooves, and the screw rod is connected with a motor;
after a motor connected with the screw rod is started, the motor drives the belt pulley to rotate through a belt, the belt pulley drives the screw rod to rotate, and after the screw rod rotates, the launching booster drives the launching booster to move forwards by means of threads meshed with the screw rod at the bottom of the launching booster.
2. A thrust glide bench-scale rocket system according to claim 1, wherein: the hollow cylindrical body is a conical hollow cylindrical body, the diameter of a section circle close to the front end of the guide rail sliding table is small, the diameter of a section circle at the rear end is large, and the hollow spring column can freely stretch out and draw back from the end with the small diameter of the section circle.
3. A thrust glide bench-scale rocket system according to claim 1, wherein: and a stop bolt for preventing the rocket from moving is arranged in the rocket sliding groove, and when the rocket is placed on the guide rail sliding table, the stop bolt is positioned in front of the rear sliding block of the rocket.
4. A thrust glide bench-scale rocket system according to claim 3, wherein: the stop bolt comprises a screw, the screw is screwed at the bottom of the rocket sliding groove, a spring is sleeved at the top of the screw, a hollow cylinder with an inclined surface at the top end is sleeved outside the spring, and the inclined surface of the hollow cylinder faces the rear end of the rocket sliding groove.
5. A thrust glide bench-scale rocket system according to claim 1, wherein: the lead screw front end is not carved with the screw thread the terminal department that the side of guide rail slip table is close to the lead screw thread has installed motor toggle switch, works as when the transmission boost arrives lead screw thread end, transmission boost trigger motor toggle switch closes the motor.
6. A thrust glide bench-scale rocket system according to claim 1, wherein: and the top ends of the screw rod and the guide rod are provided with anti-collision compression springs.
7. A thrust gliding mini-test rocket system according to any one of claims 1 to 6, wherein: the angle of pitch regulation bracing piece is two hydraulic support rods, the upper end and the guide rail slip table of two hydraulic support rods are articulated, the lower extreme with the launching cradle base is articulated, guide rail slip table bracket includes the support frame of rigid coupling on the launching cradle base the support frame facial make-up is equipped with can be along with guide rail slip table angular adjustment and pivoted rotation bracket.
8. A thrust gliding mini-test rocket system according to any one of claims 1 to 6, wherein: the base of the rocket launching cradle is made of aluminum plate and is fixedly connected to the hard ground through expansion bolts.
9. A thrust gliding mini-test rocket system according to any one of claims 1 to 6, wherein: the recovery system comprises a recovery umbrella bag, an explosion bolt, an umbrella rope hanger, a recovery umbrella rope, a traction rope and a recovery umbrella cover plate, wherein the recovery umbrella bag is connected with the umbrella rope hanger through the recovery umbrella rope, the umbrella rope hanger is fixedly connected in a cylinder body, the explosion bolt is connected with the recovery umbrella cover plate, and the traction rope is connected with the recovery umbrella cover plate.
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CN113008515B (en) * 2021-02-26 2023-04-18 中国船舶科学研究中心 Multi-angle water-entering simulation auxiliary device for winged cone model
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