CN204788051U - Formula tray protecgulum is wholly launched to low impact - Google Patents
Formula tray protecgulum is wholly launched to low impact Download PDFInfo
- Publication number
- CN204788051U CN204788051U CN201520528280.3U CN201520528280U CN204788051U CN 204788051 U CN204788051 U CN 204788051U CN 201520528280 U CN201520528280 U CN 201520528280U CN 204788051 U CN204788051 U CN 204788051U
- Authority
- CN
- China
- Prior art keywords
- fixed
- front cover
- cover body
- impact part
- fixed support
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 238000004146 energy storage Methods 0.000 claims abstract description 32
- 230000002093 peripheral effect Effects 0.000 claims description 6
- 230000001154 acute effect Effects 0.000 claims description 4
- 229910000838 Al alloy Inorganic materials 0.000 claims description 3
- 239000007769 metal material Substances 0.000 claims description 3
- 239000000956 alloy Substances 0.000 claims description 2
- 238000007789 sealing Methods 0.000 abstract description 3
- 210000002105 tongue Anatomy 0.000 description 18
- 230000007246 mechanism Effects 0.000 description 12
- 238000000034 method Methods 0.000 description 11
- 230000008569 process Effects 0.000 description 10
- 238000010586 diagram Methods 0.000 description 3
- 230000035939 shock Effects 0.000 description 3
- 235000015842 Hesperis Nutrition 0.000 description 2
- 235000012633 Iberis amara Nutrition 0.000 description 2
- 229910000639 Spring steel Inorganic materials 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 239000002360 explosive Substances 0.000 description 2
- 230000007774 longterm Effects 0.000 description 2
- 230000004044 response Effects 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
Landscapes
- Toys (AREA)
Abstract
本实用新型公开了一种低冲击整体弹射式发射箱前盖，属于火箭和导弹发射技术领域；包括：活动冲击部件、储能弹簧、固定支杆、拉杆、固定锁圈、闭锁舌片、前盖本体及固定支座；固定支座固定在前盖本体的中心；活动冲击部件的空心管与固定支座的导向杆进行孔轴配合，储能弹簧套装在活动冲击部件的空心管及固定支座的导向杆的外表面，固定支杆的一端固定在活动冲击部件的平板上；拉杆的一端分别活动连接在固定支杆的另一端，闭锁舌片分别活动连接在拉杆的另一端；固定锁圈固定在发射箱体的法兰上，前盖本体通过闭锁舌片与固定锁圈的配合安装在发射箱体的开放端；本实用新型能够实现发射箱前盖的有效密封、可靠开启和安全脱落。
The utility model discloses a low-impact integral ejection type launch box front cover, which belongs to the technical field of rocket and missile launch, and comprises: a movable impact part, an energy storage spring, a fixed pole, a pull rod, a fixed lock ring, a locking tongue, a front Cover body and fixed support; the fixed support is fixed at the center of the front cover body; the hollow tube of the movable impact part is matched with the guide rod of the fixed support, and the energy storage spring is set on the hollow tube of the movable impact part and the fixed support The outer surface of the guide rod of the seat, one end of the fixed rod is fixed on the flat plate of the movable impact part; one end of the tie rod is respectively movably connected to the other end of the fixed rod, and the locking tongue is respectively movably connected to the other end of the pull rod; the fixed lock The ring is fixed on the flange of the launch box, and the front cover body is installed on the open end of the launch box through the cooperation of the locking tongue and the fixed lock ring; the utility model can realize effective sealing, reliable opening and safety of the front cover of the launch box. fall off.
Description
技术领域technical field
本实用新型属于火箭和导弹发射技术领域，具体涉及一种低冲击整体弹射式发射箱前盖。The utility model belongs to the technical field of launching rockets and missiles, in particular to a front cover of a low-impact integral ejection launch box.
背景技术Background technique
火箭、导弹发射箱前盖是火箭导弹发射箱的重要组成部分。在储运过程中前盖保证发射箱的有效密封，为火箭、导弹提供合适的储运环境；在发射过程中前盖需要可靠开启和安全脱落，保证弹体的安全发射。发射箱前盖设计一直是火箭、导弹发射装置设计的一项重要内容，其关键点包括：1)减少前盖开启的作用时间，提高发射效率；2)减小前盖开启对弹体的冲击作用力，保证弹体安全；3)增加前盖脱落过程的飞行距离，保证弹体和发射装置安全；4)降低结构和工艺复杂程度，提高可靠性。现有火箭、导弹发射箱前盖按开启方式分类通常有机电式、整体脱落式和易碎式等几种。其中机电式前盖在发射前采用电机带动专门机构实现盖体的开启，其结构较为复杂，发射准备时间较长；整体脱落式前盖将燃气冲击波、弹体冲击力或是爆炸索等作为动力在助推发动机点火初期实现盖体的整体脱落，通常需要较大的冲击力或爆炸力，对弹体抗冲击能力有较高要求，而盖体脱落时的飞行距离有限，对弹体以及发射装置的安全有一定影响；易碎式前盖同样以燃气冲击波或弹体冲击力为动力实现盖体的开启和脱落，并碎裂为多片以减小对发射安全的影响，易碎式前盖需要预制碎裂凹槽并保证其储运密封时的强度，工艺实现上较为困难。The front cover of the rocket and missile launch box is an important part of the rocket and missile launch box. During the storage and transportation process, the front cover ensures the effective sealing of the launch box and provides a suitable storage and transportation environment for rockets and missiles; during the launch process, the front cover needs to be reliably opened and safely dropped to ensure the safe launch of the projectile. The design of the front cover of the launch box has always been an important content in the design of rocket and missile launching devices. The key points include: 1) reducing the action time of the front cover opening and improving the launch efficiency; 2) reducing the impact of the front cover opening on the missile body 3) Increase the flight distance of the front cover falling off process to ensure the safety of the projectile and the launching device; 4) Reduce the complexity of the structure and process and improve the reliability. Existing rocket, the front cover of missile launching box are classified by opening mode and usually have several types such as electromechanical type, integral shedding type and fragile type. Among them, the electromechanical front cover uses a motor to drive a special mechanism to realize the opening of the cover before launch. Its structure is more complicated and the preparation time for launch is longer; the integral detachment front cover uses gas shock waves, projectile impact force or explosive cables as power. In the initial stage of ignition of the booster engine, the overall falling off of the cover usually requires a relatively large impact force or explosive force, which has high requirements on the impact resistance of the projectile, and the flight distance when the cover falls off is limited, which is harmful to the projectile and the launch. The safety of the device has a certain impact; the fragile front cover also uses the gas shock wave or projectile impact force as the power to realize the opening and falling of the cover body, and breaks into multiple pieces to reduce the impact on launch safety. The cover needs to prefabricate the broken groove and ensure its strength during storage and transportation, which is difficult to realize in the process.
实用新型内容Utility model content
有鉴于此，本实用新型的目的是提供一种低冲击整体弹射式发射箱前盖，应用于火箭、导弹发射装置中，主要用来实现发射箱前盖的有效密封、可靠开启和安全脱落，以满足发射箱前盖开启脱落过程的快速响应、低弹体冲击力、远飞行距离、结构简单可靠的设计需求。In view of this, the purpose of this utility model is to provide a low-impact integral ejection type launch box front cover, which is used in rocket and missile launching devices, and is mainly used to realize effective sealing, reliable opening and safe falling off of the launch box front cover. To meet the design requirements of fast response, low projectile impact, long flight distance, and simple and reliable structure during the opening and falling off process of the front cover of the launch box.
本实用新型是通过下述技术方案实现的：The utility model is achieved through the following technical solutions:
一种低冲击整体弹射式发射箱前盖，包括：蓄能弹射机构、锁紧/解锁机构及前盖本体结构；A low-impact integral ejection launch box front cover, including: an energy storage ejection mechanism, a locking/unlocking mechanism and a front cover body structure;
外围设备包括：发射箱体和弹体；Peripheral equipment includes: launch box and projectile;
所述蓄能弹射机构包括：活动冲击部件、储能弹簧和固定支杆；The energy-storage ejection mechanism includes: a movable impact part, an energy-storage spring and a fixed strut;
锁紧/解锁机构包括：拉杆、固定锁圈和闭锁舌片；The locking/unlocking mechanism includes: a pull rod, a fixed lock ring and a locking tongue;
所述前盖本体结构包括：前盖本体、固定支座和配重；The front cover body structure includes: a front cover body, a fixed support and a counterweight;
所述活动冲击部件由平板、斜板及空心管组成，平板和斜板呈锐角固定连接，空心管垂直固定在平板的中心；The movable impact part is composed of a flat plate, an inclined plate and a hollow tube, the flat plate and the inclined plate are fixedly connected at an acute angle, and the hollow tube is vertically fixed at the center of the flat plate;
所述固定支杆为L型杆；The fixed pole is an L-shaped pole;
所述固定锁圈的内圆周面设有与闭锁舌片相配合的凹槽；The inner peripheral surface of the fixed locking ring is provided with a groove matching with the locking tongue;
所述前盖本体为圆弧状壳体；The front cover body is an arc-shaped shell;
所述固定支座由支撑板和导向杆组成，导向杆垂直固定在支撑板上；The fixed support is composed of a support plate and a guide rod, and the guide rod is vertically fixed on the support plate;
其连接关系如下：配重固定在前盖本体的边缘处，使前盖本体的质心靠近前盖本体的边缘，固定支座固定在前盖本体的中心；活动冲击部件的空心管与固定支座的导向杆进行孔轴配合，储能弹簧套装在活动冲击部件的空心管及固定支座的导向杆的外表面，且储能弹簧的一端固定在活动冲击部件上，另一端固定在固定支座上；固定支杆的一端固定在活动冲击部件的平板上，且两个以上固定支杆以活动冲击部件的空心管为对称轴呈中心对称分布；拉杆的一端分别活动连接在固定支杆的另一端，闭锁舌片分别活动连接在拉杆的另一端；The connection relationship is as follows: the counterweight is fixed at the edge of the front cover body, so that the center of mass of the front cover body is close to the edge of the front cover body, and the fixed support is fixed at the center of the front cover body; the hollow tube of the movable impact part and the fixed support The guide rod is matched with the hole shaft, the energy storage spring is set on the hollow tube of the movable impact part and the outer surface of the guide rod of the fixed support, and one end of the energy storage spring is fixed on the movable impact part, and the other end is fixed on the fixed support Above; one end of the fixed strut is fixed on the flat plate of the movable impact part, and more than two fixed struts are center-symmetrically distributed with the hollow tube of the movable impact part as the axis of symmetry; one end of the tie rod is respectively movably connected to the other end of the fixed strut At one end, the locking tongues are respectively movably connected to the other end of the pull rod;
固定锁圈固定在发射箱体的法兰上，闭锁舌片伸入到固定锁圈的凹槽内，前盖本体通过闭锁舌片与固定锁圈的配合安装在发射箱体的开放端，且前盖本体的质心位于活动冲击部件斜板的法线下方。The fixed lock ring is fixed on the flange of the launch box, the locking tongue extends into the groove of the fixed lock ring, and the front cover body is installed on the open end of the launch box through the cooperation of the lock tongue and the fixed lock ring, and The center of mass of the front cover body is located below the normal line of the sloping plate of the movable impact part.
进一步的，所述活动冲击部件的平板和斜板的夹角为15～25度。Further, the angle between the flat plate and the inclined plate of the movable impact part is 15-25 degrees.
进一步的，所述储能弹簧的刚度为50～100N/mm，自由长度为100～150mm，采用高强度弹簧钢。Further, the stiffness of the energy storage spring is 50-100 N/mm, the free length is 100-150 mm, and high-strength spring steel is used.
进一步的，所述前盖本体采用非金属材料；所述活动冲击部件、固定支杆、拉杆、闭锁舌片及固定支座均采用铝合金材料。Further, the front cover body is made of non-metallic materials; the movable impact parts, fixed rods, pull rods, locking tongues and fixed supports are all made of aluminum alloy.
工作原理：在锁紧(或密封)工作状态下，闭锁舌片伸入固定锁圈的凹槽内以保证前盖本体的有效固定，此时，储能弹簧处于自由状态，以保证长期储运过程不会发生应力松弛失效；Working principle: In the locked (or sealed) working state, the locking tongue extends into the groove of the fixed lock ring to ensure the effective fixing of the front cover body. At this time, the energy storage spring is in a free state to ensure long-term storage and transportation No stress relaxation failure will occur during the process;
在开启工作状态下，随着火箭、导弹点火发射，弹体向靠近前盖本体的方向运动并与活动冲击部件的斜板接触，活动冲击部件与弹体同步向靠近前盖本体的方向运动并压缩储能弹簧；同时，与活动冲击部件相连的固定支杆带动拉杆运动，使闭锁舌片从固定锁圈的凹槽中逐渐拔出，实现盖体的开启；在开启过程中，储能弹簧的压缩变形，能够有效降低弹体头部受到的冲击作用力；当斜板与弹体接触时，斜板的法线与弹体轴线倾斜一定角度，使前盖本体受到向前FX、向下Fy的作用力，以保证前盖本体与弹体的快速分离；In the open working state, as the rocket and missile are ignited and launched, the projectile moves towards the direction close to the front cover body and contacts the inclined plate of the movable impact part, and the movable impact part moves synchronously with the projectile towards the direction close to the front cover body. Compress the energy storage spring; at the same time, the fixed rod connected to the movable impact part drives the pull rod to move, so that the locking tongue is gradually pulled out from the groove of the fixed lock ring to realize the opening of the cover; during the opening process, the energy storage spring The compression deformation of the projectile can effectively reduce the impact force on the projectile head; when the swash plate contacts the projectile, the normal line of the swash plate and the projectile axis are inclined at a certain angle, so that the front cover body is subjected to forward F X , Lower the force of F y to ensure the rapid separation of the front cover body and the elastic body;
在脱落工作状态下，前盖本体与固定锁圈的约束解除，被压缩的储能弹簧能量释放，前盖本体及固定在前盖本体上的部件向前、向下弹出；且前盖本体上的配重，使前盖本体脱落时受到一个翻转力矩，使其向下翻转与弹体快速分离。In the falling off working state, the restraint of the front cover body and the fixed lock ring is released, the energy of the compressed energy storage spring is released, and the front cover body and the parts fixed on the front cover body pop up forward and downward; and the front cover body When the front cover body falls off, it is subject to a turning moment, so that it can be turned down and separated from the elastic body quickly.
有益效果：(1)本实用新型综合火箭、导弹发射箱前盖设计的需求，提出一种低冲击整体弹射式发射箱前盖，在储运过程中通过锁紧机构实现发射箱的有效密封；在发射初期以弹体接触力作为开启动力，通过解锁和蓄能弹射机构有效降低弹体承受的冲击力并实现前盖本体的可靠开启；前盖本体开启后，由蓄能弹射机构释放能量将前盖整体弹射抛出并远离弹体和发射装置，保障安全、可靠发射。Beneficial effects: (1) The utility model integrates the design requirements of the front cover of the rocket and missile launch box, and proposes a low-impact integral ejection type launch box front cover, which can effectively seal the launch box through the locking mechanism during storage and transportation; In the early stage of launch, the contact force of the projectile is used as the opening power, and the impact force on the projectile is effectively reduced through the unlocking and energy storage ejection mechanism, and the reliable opening of the front cover body is realized; after the front cover body is opened, the energy released by the energy storage ejection mechanism will The front cover is ejected as a whole and is thrown away from the projectile body and the launching device to ensure safe and reliable launching.
(2)本实用新型利用弹体运动过程中与活动冲击部件的接触力作为动力实现前盖开启，响应时间快；利用活动冲击部件的运动和储能弹簧的变形，降低弹体冲击作用力；利用储能弹簧的能量转换、作用力方向和质心位置偏转实现前盖本体向前向下弹射脱落，前盖本体脱落飞行距离远，保证弹体和发射装置安全；此外通过机械结构实现前盖的锁紧、开启和脱落，结构简单可靠。(2) The utility model uses the contact force between the projectile body and the movable impact part as power to realize the opening of the front cover, and the response time is fast; the movement of the movable shock part and the deformation of the energy storage spring are used to reduce the impact force of the projectile; The energy conversion of the energy storage spring, the direction of the force and the deflection of the center of mass position are used to realize the ejection of the front cover body forward and downward. Locking, opening and falling off, the structure is simple and reliable.
(3)本实用新型的活动冲击部件上的斜板在与弹体接触时，产生的作用力不再沿着弹体轴线方向，而可分解为沿轴向的作用力和沿切向作用力，切向作用力能够使得盖体向远离轴线的方向运动，避免盖体脱落过程中对弹体的影响。(3) When the swash plate on the movable impact part of the utility model is in contact with the projectile, the force generated is no longer along the axis of the projectile, but can be decomposed into the force along the axial direction and the force along the tangential direction. , the tangential force can make the cover move away from the axis, avoiding the impact on the elastic body during the process of the cover falling off.
附图说明Description of drawings
图1为本实用新型的结构图。Fig. 1 is a structural diagram of the utility model.
图2为本实用新型锁紧时的结构图。Fig. 2 is a structural diagram of the utility model when it is locked.
图3为本实用新型脱落时的结构图。Fig. 3 is a structural diagram when the utility model falls off.
其中，1-活动冲击部件，2-储能弹簧，3-固定支杆，4-拉杆，5-固定锁圈，6-闭锁舌片，7-配重，8-质心，9-法线，10-固定支座，11-前盖本体，12-发射箱体，13-弹体。Among them, 1-movable impact part, 2-energy storage spring, 3-fixed strut, 4-tie rod, 5-fixed lock ring, 6-locking tongue, 7-counterweight, 8-center of mass, 9-normal line, 10-fixed support, 11-front cover body, 12-launch box, 13-elastic body.
具体实施方式Detailed ways
下面结合附图并举实施例，对本实用新型进行详细描述。The utility model will be described in detail below in conjunction with the accompanying drawings and examples.
本实用新型提供了一种低冲击整体弹射式发射箱前盖，参见附图1，包括：蓄能弹射机构、锁紧/解锁机构及前盖本体结构；The utility model provides a low-impact integral ejection type launch box front cover, referring to the accompanying drawing 1, comprising: an energy storage ejection mechanism, a locking/unlocking mechanism and a front cover body structure;
其外围设备包括：发射箱体12和弹体13；Its peripheral equipment includes: launching box body 12 and projectile body 13;
所述蓄能弹射机构包括：活动冲击部件1、储能弹簧2和固定支杆3；The energy storage and ejection mechanism includes: a movable impact part 1, an energy storage spring 2 and a fixed support rod 3;
锁紧/解锁机构包括：拉杆4、固定锁圈5和闭锁舌片6；The locking/unlocking mechanism includes: a pull rod 4, a fixed locking ring 5 and a locking tongue 6;
所述前盖本体结构包括：前盖本体11、固定支座10和配重7；The front cover body structure includes: a front cover body 11, a fixed support 10 and a counterweight 7;
所述活动冲击部件1由平板、斜板及空心管组成，平板和斜板呈锐角固定连接，空心管垂直固定在平板的中心；所述锐角为15～25度，即斜板与弹体13接触时，斜板的法线9与弹体13轴线的夹角为15～25度；The movable impact part 1 is composed of a flat plate, an inclined plate and a hollow tube, the flat plate and the inclined plate are fixedly connected at an acute angle, and the hollow tube is vertically fixed at the center of the flat plate; the acute angle is 15-25 degrees, that is, the inclined plate and the elastic body 13 When in contact, the angle between the normal line 9 of the inclined plate and the axis of the body 13 is 15 to 25 degrees;
所述储能弹簧2的刚度为50～100N/mm，自由长度为100～150mm，采用高强度弹簧钢，以获得足够的弹射动力并具有较小的布置空间；The energy storage spring 2 has a stiffness of 50-100N/mm, a free length of 100-150mm, and uses high-strength spring steel to obtain sufficient ejection power and a small layout space;
所述固定支杆3为L型杆；The fixed pole 3 is an L-shaped pole;
所述拉杆4的长度由固定支杆3调节，以保证闭锁舌片6具有足够的运动距离；The length of the pull rod 4 is adjusted by the fixed pole 3 to ensure that the locking tongue 6 has a sufficient movement distance;
所述固定锁圈5的内圆周面设有与闭锁舌片6相配合的凹槽；The inner peripheral surface of the fixed locking ring 5 is provided with a groove matching with the locking tongue 6;
所述前盖本体11为圆弧状壳体，采用非金属材料；The front cover body 11 is an arc-shaped shell made of non-metallic material;
所述固定支座10由支撑板和导向杆组成，导向杆垂直固定在支撑板上；The fixed support 10 is made up of a support plate and a guide rod, and the guide rod is vertically fixed on the support plate;
所述活动冲击部件1、固定支杆3、拉杆4、闭锁舌片6及固定支座10均采用铝合金材料，具有较轻的质量；The movable impact part 1, the fixed support rod 3, the pull rod 4, the locking tongue 6 and the fixed support 10 are all made of aluminum alloy material, which has a relatively light weight;
其连接关系如下：配重7固定在前盖本体11的边缘处，使前盖本体11的质心8靠近前盖本体11的边缘，固定支座10固定在前盖本体11的中心；活动冲击部件1的空心管与固定支座10的导向杆进行孔轴配合，储能弹簧2套装在活动冲击部件1的空心管及固定支座10的导向杆的外表面，且储能弹簧2的一端固定在活动冲击部件1上，另一端固定在固定支座10上；四个固定支杆3的一端固定在活动冲击部件1的平板上，且四个固定支杆3以活动冲击部件1的空心管为对称轴呈中心对称分布；四个拉杆4的一端分别活动连接在固定支杆3的另一端，闭锁舌片6分别活动连接在拉杆4的另一端；Its connection relationship is as follows: the counterweight 7 is fixed on the edge of the front cover body 11, so that the center of mass 8 of the front cover body 11 is close to the edge of the front cover body 11, and the fixed support 10 is fixed at the center of the front cover body 11; the movable impact part The hollow tube of 1 is matched with the guide rod of the fixed support 10, the energy storage spring 2 is set on the hollow tube of the movable impact part 1 and the outer surface of the guide rod of the fixed support 10, and one end of the energy storage spring 2 is fixed On the movable impact component 1, the other end is fixed on the fixed support 10; one end of the four fixed struts 3 is fixed on the flat plate of the movable impact component 1, and the four fixed struts 3 are connected with the hollow tube of the movable impact component 1. The axis of symmetry is centrally symmetrical; one end of the four pull rods 4 is respectively movably connected to the other end of the fixed pole 3, and the locking tongue 6 is movably connected to the other end of the pull rod 4;
固定锁圈5通过螺栓固定在发射箱体12的法兰上，闭锁舌片6伸入到固定锁圈5的凹槽内，前盖本体11通过闭锁舌片6与固定锁圈5的配合安装在发射箱体12的开放端，且前盖本体11的质心8位于活动冲击部件1斜板的法线9下方，储能弹簧2处于自由状态。The fixed lock ring 5 is fixed on the flange of the launching box 12 by bolts, the locking tongue 6 extends into the groove of the fixed lock ring 5, and the front cover body 11 is installed through the cooperation of the locking tongue 6 and the fixed lock ring 5 At the open end of the launching box 12, and the center of mass 8 of the front cover body 11 is located below the normal 9 of the sloping plate of the movable impact part 1, the energy storage spring 2 is in a free state.
工作原理：参见附图2、3，在锁紧(或密封)工作状态下，闭锁舌片6伸入固定锁圈5的凹槽内以保证前盖本体11的有效固定，此时，储能弹簧2处于自由状态，以保证长期储运过程不会发生应力松弛失效；Working principle: see attached drawings 2 and 3. In the locked (or sealed) working state, the locking tongue 6 extends into the groove of the fixed lock ring 5 to ensure the effective fixing of the front cover body 11. At this time, the energy storage Spring 2 is in a free state to ensure that stress relaxation failure does not occur during long-term storage and transportation;
在开启工作状态下，随着火箭、导弹点火发射，弹体13向靠近前盖本体11的方向运动并与活动冲击部件1的斜板接触，活动冲击部件1与弹体13同步向靠近前盖本体11的方向运动并压缩储能弹簧2；同时，与活动冲击部件1相连的固定支杆3带动拉杆4运动，使闭锁舌片6从固定锁圈5的凹槽中逐渐拔出，实现盖体的开启；在开启过程中，储能弹簧2的压缩变形，能够有效降低弹体13头部受到的冲击作用力；当斜板与弹体13接触时，斜板的法线9与弹体13轴线倾斜一定角度，使前盖本体11受到向前FX、向下Fy的作用力，以保证前盖本体11与弹体13的快速分离；In the open working state, as the rocket and missile are ignited and launched, the projectile body 13 moves towards the direction close to the front cover body 11 and contacts the slant plate of the movable impact part 1, and the movable impact part 1 and the projectile body 13 move towards the front cover synchronously. The main body 11 moves in the direction and compresses the energy storage spring 2; at the same time, the fixed strut 3 connected to the movable impact part 1 drives the pull rod 4 to move, so that the locking tongue 6 is gradually pulled out from the groove of the fixed lock ring 5, and the cover is realized. The opening of the body; in the opening process, the compression deformation of the energy storage spring 2 can effectively reduce the impact force on the head of the projectile 13; 13 The axis is inclined at a certain angle, so that the front cover body 11 is subjected to the forward F X and downward F y forces, so as to ensure the rapid separation of the front cover body 11 and the elastic body 13;
在脱落工作状态下，前盖本体11与固定锁圈5的约束解除，被压缩的储能弹簧2能量释放，前盖本体11及固定在前盖本体11上的部件向前、向下弹出；且前盖本体11上的配重7，使前盖本体11脱落时受到一个翻转力矩，使其向下翻转与弹体13快速分离。In the falling off working state, the constraint of the front cover body 11 and the fixed lock ring 5 is released, the energy of the compressed energy storage spring 2 is released, and the front cover body 11 and the components fixed on the front cover body 11 are ejected forward and downward; And the counterweight 7 on the front cover body 11 is subjected to an overturning moment when the front cover body 11 falls off, so that it turns downward and separates quickly from the elastic body 13 .
综上所述，以上仅为本实用新型的较佳实施例而已，并非用于限定本实用新型的保护范围。凡在本实用新型的精神和原则之内，所作的任何修改、等同替换、改进等，均应包含在本实用新型的保护范围之内。To sum up, the above are only preferred embodiments of the present utility model, and are not intended to limit the protection scope of the present utility model. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present utility model shall be included in the protection scope of the present utility model.
Claims (4)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520528280.3U CN204788051U (en) | 2015-07-20 | 2015-07-20 | Formula tray protecgulum is wholly launched to low impact |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520528280.3U CN204788051U (en) | 2015-07-20 | 2015-07-20 | Formula tray protecgulum is wholly launched to low impact |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204788051U true CN204788051U (en) | 2015-11-18 |
Family
ID=54528075
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520528280.3U Expired - Fee Related CN204788051U (en) | 2015-07-20 | 2015-07-20 | Formula tray protecgulum is wholly launched to low impact |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204788051U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105043166A (en) * | 2015-07-20 | 2015-11-11 | 北京理工大学 | Low-impact overall ejection type launching canister front cover |
| CN109211007A (en) * | 2018-10-11 | 2019-01-15 | 上海航天精密机械研究所 | A kind of protective cover of the launch canister with burn-out proof and rain and snow function |
| CN110045609A (en) * | 2019-04-17 | 2019-07-23 | 北京理工大学 | It is a kind of that perpendicular apparatus control system is played based on PID- sliding-mode variable structure algorithm |
| CN114184228A (en) * | 2021-11-30 | 2022-03-15 | 中煤科工集团沈阳研究院有限公司 | Detector for controllable distance emission type disaster relief |
-
2015
- 2015-07-20 CN CN201520528280.3U patent/CN204788051U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105043166A (en) * | 2015-07-20 | 2015-11-11 | 北京理工大学 | Low-impact overall ejection type launching canister front cover |
| CN109211007A (en) * | 2018-10-11 | 2019-01-15 | 上海航天精密机械研究所 | A kind of protective cover of the launch canister with burn-out proof and rain and snow function |
| CN110045609A (en) * | 2019-04-17 | 2019-07-23 | 北京理工大学 | It is a kind of that perpendicular apparatus control system is played based on PID- sliding-mode variable structure algorithm |
| CN114184228A (en) * | 2021-11-30 | 2022-03-15 | 中煤科工集团沈阳研究院有限公司 | Detector for controllable distance emission type disaster relief |
| CN114184228B (en) * | 2021-11-30 | 2023-05-02 | 中煤科工集团沈阳研究院有限公司 | Detector for controllable-distance emission type disaster relief |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105043166B (en) | Low-impact integral ejection type launch box front cover | |
| CN106481633B (en) | A low-impact, high-load-bearing pyrotechnic unlocking bolt | |
| CN204788051U (en) | Formula tray protecgulum is wholly launched to low impact | |
| CN102494565B (en) | Separation mechanism of oriented rocket nose body | |
| US7762194B2 (en) | Apparatus comprising a payload ejection mechanism | |
| CN111256544B (en) | Liquid rocket | |
| CN102991731A (en) | Flying mesh catapulting device for acquiring discarded spacecraft | |
| CN105758442A (en) | Emission and recovery integrated air cannon experiment apparatus | |
| CN104864774A (en) | Self-catapulting launching device for guided missile | |
| CN113883972A (en) | Interstage separation device suitable for small-diameter missile aircraft | |
| CN107953999A (en) | It is a kind of to penetrate umbrella rocket means for the quick parachute-opening of parachute | |
| CN108284970A (en) | One kind can carry the curved load firer separating mechanism of high intensity tension and compression and separation method | |
| CN110631433B (en) | Shear screw type hood separating mechanism | |
| CN111521073A (en) | Rocket recovery method | |
| CN203298658U (en) | Bolt capturing apparatus for explosive release and explosive-release capture system | |
| CN111017213B (en) | Unmanned aerial vehicle recovery system guide umbrella penetrates umbrella mechanism | |
| KR101441284B1 (en) | Shear breaking explosive separation device that bear 2 way forces | |
| KR101200745B1 (en) | Separation device for propulsion system of missile and missile launching system having the same | |
| CN112693639B (en) | Energy storage type ejection sealing protection device and aircraft launching method | |
| CN112896561B (en) | A space flying net launching device and launching method | |
| CN210853001U (en) | A collect box for spacecraft separator | |
| CN217814424U (en) | Large-load low-impact explosive bolt | |
| CN111306996A (en) | Ammunition flight resistance device | |
| CN207274995U (en) | A kind of aircraft sliding block separating mechanism | |
| CN112319866A (en) | Piston type recovery device of civil rocket |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151118 Termination date: 20160720 |