摘要：【中文】本发明属于固体火箭发动机技术领域，具体涉及一种固体火箭发动机喷堵测试工装及测试方法，本发明技术方案以高压气体代替点火药盒作为破堵气源的破堵压力测试方法，并设计了相关工装。该方法与原有测试方法相比，不涉及火工品，安全性较高；气源压力稳定，测试结果波动较小；可以测试不同形状、尺寸的喷堵，通用性强；测试速度高，成本低。 【EN】The invention belongs to the technical field of solid rocket engines, and particularly relates to a solid rocket engine spray plugging test tool and a test method. Compared with the original test method, the method does not relate to initiating explosive devices and has higher safety; the air source pressure is stable, and the fluctuation of the test result is small; the spray plugs with different shapes and sizes can be tested, and the universality is strong; the test speed is high, and the cost is low.

摘要：【中文】本发明公开了一种模块化力矩转接器，用于在狭小的结构空间中实现力矩的转向和传动功能，适用于当在狭小空间安装紧固件的过程对预紧力有一定要求时力矩的转向和传动，主要用于提高安装紧固件的装配精度和效率。该模块化力矩转接器由力矩转接器、转接套筒、传动柱和批头组成。在不同安装工况下，通过转接套筒和传动柱组合不同的力矩转接器模块，可实现狭小空间的转接功能。本发明的突出优点是，采用模块化设计，可适用于不同的安装工况，具有较强的适用性；结构尺寸小，能够伸入较小的结构空间，具有很大的实用价值；成本低廉，操作简单，便于使用，具有较大的推广应用空间。 【EN】The invention discloses a modular torque adapter which is used for realizing the functions of steering and transmission of torque in a narrow structural space, is suitable for steering and transmission of torque when a fastening piece has a certain requirement on pretightening force in the process of mounting the fastening piece in the narrow space, and is mainly used for improving the assembly precision and efficiency of mounting the fastening piece. The modular torque adapter consists of a torque adapter, an adapter sleeve, a transmission column and a batch head. Under different installation conditions, different torque adapter modules are combined through the adapter sleeve and the transmission column, and the adapter function in a narrow space can be realized. The invention has the outstanding advantages that the modular design is adopted, the invention is suitable for different installation working conditions, and the applicability is stronger; the structure has small size, can extend into a smaller structure space, and has great practical value; low cost, simple operation, convenient use and larger popularization and application space.

摘要：【中文】本发明属于固体火箭发动机技术领域，具体涉及一种宽温发动机喷堵的制备方法，所制备的喷堵可以满足发动机宽温试验(‑50℃～70℃)的要求。在70℃条件下，对喷堵进行长时间保温，很容易造成产品二次发泡。通过对原料进行合适的前处理工艺和对产品进行合适的后处理工艺，制备出质量可靠、稳定性高的宽温喷堵，有效解决了喷堵产品二次发泡的问题。 【EN】The invention belongs to the technical field of solid rocket engines, and particularly relates to a preparation method of a wide-temperature engine spray plug, wherein the prepared spray plug can meet the requirements of wide-temperature tests of engines (minus 50-70 ℃). The spray plug is insulated for a long time at 70 ℃, and secondary foaming of the product is easily caused. By carrying out a proper pretreatment process on the raw materials and a proper post-treatment process on the product, the wide-temperature spray plug with reliable quality and high stability is prepared, and the problem of secondary foaming of the spray plug product is effectively solved.

摘要：【中文】本发明公开了一种姿态角大范围变化条件下的半实物仿真试验方法，在制导火箭姿态角大范围变化，超过三轴转台的工作角度范围时，进行标志位的切换，由三分量注入切换至六分量注入，本发明能够完成制导火箭姿态角大范围变化时的仿真试验。 【EN】The invention discloses a semi-physical simulation test method under the condition of wide-range change of an attitude angle, which is characterized in that when the attitude angle of a guided rocket is changed in a wide range and exceeds the working angle range of a three-axis turntable, the switching of a mark position is carried out, and the switching is carried out from three-component injection to six-component injection.

摘要：【中文】本发明公开了一种拖曳式二次起爆云爆弹引战配合精确控制方法，实现引战配合精确控制；根据拖曳式二次起爆云爆弹飞行条件、云团形态和二次起爆装置起爆延时等设计值及偏差范围，给出引战配合缆长，确保在最佳云团形成时，二次起爆装置在云团内部起爆，以实现引战配合精确控制，最大化发挥二次起爆云爆战斗部威力。 【EN】The invention discloses a method for accurately controlling towing war cooperation of a towing type secondary detonation cloud explosion bomb, which realizes accurate control of towing war cooperation; according to design values and deviation ranges of flight conditions of the towed secondary detonation cloud detonation bomb, cloud cluster shapes, detonation delay of the secondary detonation device and the like, the length of the priming fight coordination cable is given, and the secondary detonation device is ensured to detonate inside the cloud cluster when the optimal cloud cluster is formed, so that the priming fight coordination accurate control is realized, and the power of the secondary detonation cloud detonation warhead is exerted to the maximum extent.

摘要：【中文】本发明提供了一种具有中心通道的抛射结构，能够满足抛射带子弹线缆子弹的需要，可实现子弹抛出后(爆炸前)与母弹的信息传递。本发明通过抛射筒、底座、推板与推力筒形成一个具有环形药室和中心通道的抛射结构，实现了可以中心走线的抛射功能，能够满足抛射带子弹线缆子弹的需要，在子弹爆炸前，可实现子弹抛出后与母弹的信息传递。本发明推力筒为轴向伸缩筒，增加子弹在抛射筒中的运动空间，并且可适用于不同的抛射要求。 【EN】The invention provides a projecting structure with a central channel, which can meet the requirement of projecting a cable bullet with a bullet and can realize information transmission between the bullet and a mother bullet after the bullet is projected (before explosion). The invention forms a projecting structure with an annular medicine chamber and a central channel by the projecting cylinder, the base, the push plate and the thrust cylinder, realizes the projecting function of central routing, can meet the requirement of projecting the cable bullet with the bullet, and can realize the information transmission between the thrown bullet and the mother bullet before the bullet explodes. The thrust cylinder is an axial telescopic cylinder, increases the movement space of a bullet in the projectile cylinder, and is suitable for different projectile requirements.

摘要：【中文】本发明提供了一种单平面双通道六分量气动数据的双平面三通道扩展方法，能够基于单平面双通道轴对称气动数据，获取双平面三通道气动数据。本发明将纵向平面阻力系数与滚转力矩系数进行拆分，获取零升系数部分与诱导系数部分，进而综合零升系数、纵向平面诱导系数、侧向平面诱导系数得到弹身部分与滚转舵部分对应阻力系数与滚转力矩系数；在已有纵向平面内获取纵向力与力矩系数的同时利用轴对称特性以侧滑角代替攻角、偏航通道舵偏代替俯仰通道舵偏得到对应侧向力与力矩系数。可通用于各类只有单平面双通道六分量气动数据但要求双平面三通道六自由度弹道计算的轴对称外形制导弹药中。 【EN】The invention provides a biplane three-channel expansion method for uniplanar two-channel six-component pneumatic data, which can be used for acquiring biplane three-channel pneumatic data based on uniplanar two-channel axisymmetric pneumatic data. The method comprises the steps of splitting a longitudinal plane resistance coefficient and a roll torque coefficient to obtain a zero-lift coefficient part and an induction coefficient part, and further integrating the zero-lift coefficient, the longitudinal plane induction coefficient and a lateral plane induction coefficient to obtain a resistance coefficient and a roll torque coefficient corresponding to a body part and a roll rudder part; the method is characterized in that a longitudinal force coefficient and a moment coefficient are obtained in the existing longitudinal plane, and meanwhile, a sideslip angle replaces an attack angle, a yaw channel rudder deflection replaces a pitch channel rudder deflection by utilizing the axial symmetry characteristic, so that a corresponding lateral force coefficient and a corresponding moment coefficient are obtained. The method can be universally used in various axisymmetric shape guided munitions which only have single-plane two-channel six-component pneumatic data but require double-plane three-channel six-degree-of-freedom ballistic calculation.

摘要：【中文】本发明属于固体火箭发动机技术领域，具体涉及一种固体火箭发动机用聚苯乙烯喷堵及其发泡方法。该方法利用蒸汽发生器产生的高温蒸汽加热发泡模具，使可发性聚苯乙烯受热发泡成产品形状。通过控制蒸汽温度、压力和流量实现快速发泡，实现了低密度喷堵的发泡。与水煮工艺相比，该工艺发泡率高，发泡时间短，生产效率高。 【EN】The invention belongs to the technical field of solid rocket engines, and particularly relates to a polystyrene spray plug for a solid rocket engine and a foaming method thereof. The method utilizes high-temperature steam generated by a steam generator to heat a foaming mould, so that the expandable polystyrene is heated and foamed into a product shape. The rapid foaming is realized by controlling the temperature, pressure and flow of the steam, and the foaming of the low-density spray plug is realized. Compared with the water boiling process, the process has the advantages of high foaming rate, short foaming time and high production efficiency.

摘要：【中文】本发明公开了一种用于超声速弹箭快速减速的阻力板及其气动设计方法。使用本发明能够在有效增加阻力的同时，对全弹的其他气动参数以及操纵性能影响较小。本发明将多块阻力板沿周向安装在弹体头部的末端，收拢状态时，阻力板贴合在弹体头部外表面，展开时，沿弹体法向展开，呈花瓣状。本发明提出的阻力板方案一方面可以满足大幅度提高阻力的要求，另一方面不破坏弹上控制部件，由于张开后的阻力板对全弹气动性能的影响主要在于增大阻力，对其他气动参数影响较小，可以满足精确制导的要求，有效地克服了现有技术方案的缺陷。 【EN】The invention discloses a resistance plate for quickly decelerating a supersonic rocket and a pneumatic design method thereof. The invention can effectively increase the resistance and has small influence on other pneumatic parameters and the manipulation performance of the full projectile. The invention installs a plurality of resistance plates at the tail end of the head of the projectile body along the circumferential direction, when the projectile body is in a furled state, the resistance plates are attached to the outer surface of the head of the projectile body, and when the projectile body is unfolded, the resistance plates are unfolded along the normal direction of the projectile body to form a petal shape. The resistance plate scheme provided by the invention can meet the requirement of greatly improving the resistance on one hand, and does not damage the control component on the bullet on the other hand.

摘要：【中文】本发明公开了一种拖曳式二次起爆云爆弹二次起爆装置抛射初速计算方法，综合考虑拖曳式二次起爆云爆弹不确定条件，给出了拖缆最大受力正相关的最大速度差计算表达式，据此可确定出二次起爆装置最佳抛射初速范围，确保拖缆强度余量有尽可能大，以实现二次起爆，该方法为拖曳式二次起爆云爆弹引战配合中抛射初速的设计奠定了理论基础，该方法具有广阔的军事应用前景。 【EN】The invention discloses a method for calculating the casting primary speed of a towed secondary detonation cloud detonation bomb secondary detonation device, which comprehensively considers the uncertain conditions of the towed secondary detonation cloud detonation bomb, provides a maximum speed difference calculation expression of the maximum stress positive correlation of a towing cable, determines the optimal casting primary speed range of the secondary detonation device according to the maximum speed difference calculation expression, ensures that the strength margin of the towing cable is available, and realizes secondary detonation.