1) solid-propellant missile
固体推进剂导弹
2) Liquid propellant missile
液体推进剂导弹
1.
On the basis of the analysis for the transient characteristic, failure characteristics, and the introducing method of fault factor for whole power system, especially for the spontaneous pressurization system, the non-linear dynamic fault model of a liquid propellant missile power system is set up according to its actual structure to simulate the dynamic fault.
为了仿真液体推进剂导弹动力系统动态故障,通过对动力系统,特别是自生增压系统动态工作过程的过渡特性分析、故障特性分析和故障因素的引入方法研究,依据某导弹动力系统的实际结构,完整地建立了该导弹动力系统的全系统动态故障模型方程。
2.
In order to analyze, simulate, detect, diagnose steady-state fault and develop onboard monitoring system, the steady-state fault model of the whole power system of liquid propellant missile mast be established.
为了对液体推进剂导弹动力系统进行稳态故障分析、仿真、检测、诊断以及研制箭载监控系统,必须建立其全系统稳态故障模型。
3) solid propellant
固体推进剂
1.
Hygrothermal aging life model of a composite solid propellant;
某固体推进剂湿热老化模型
2.
Fuzzy evaluation method for synthesis sensitivity of solid propellant;
固体推进剂综合感度模糊评价法
3.
Progress in the application of nano aluminum powder in solid propellants;
纳米铝粉在固体推进剂中的应用
4) solid propellants
固体推进剂
1.
Application and prospects of microencapsulation in solid propellants;
微胶囊化在固体推进剂中的应用及展望
2.
The application prospects of IPN technique to improve the mechanical properties, technological properties and creep resistance of the solid propellants in solid pro-pellant binder curing system were summarised .
分析了互穿聚合物网络(IPN)技术的特点,综述了IPN技术在固体推进剂粘合剂固化体系中提高固体推进剂力学性能、改善加工工艺性能和增强抗蠕变性能等方面的应用前景,并概述了IPN技术在固体推进剂衬层和包覆层中的应用。
3.
This paper presents calculating formula to diagnose stress relaxation modulus on the basis of the experiments, theoretical analysis reasoning and revisal of dynamic-static viscoelastic properties for solid propellants.
在动态与静态粘弹性力学性能实验的基础上，通过动－静态力学特性理论转换计算公式的推导、分析和修正，提出适用于固体推进剂转换计算诊断应力松弛模量的公式。
5) Composite solid propellant
复合固体推进剂
1.
Advances on burning rate catalyzer of composite solid propellant at home and abroad;
国内外复合固体推进剂燃速催化剂研究进展
2.
Modulus tailoring of composite solid propellant;
复合固体推进剂的模量调节
3.
The Vague Sub cluster theory is presented for investigating the constitutive relation of the stress strain curves and the factors which affect the mechanical properties of composite solid propellant.
运用模糊群子理论对影响复合固体推进剂力学性能的因素及其单向拉伸曲线进行了分析 ,结果发现 ,推进剂的力学性能可由控制阻碍形变因素和屈服因素的主次对比来调节 ;不同的拉伸曲线对应于不同的主导控制因素。
6) solid rocket propellant
固体火箭推进剂
1.
By studying and summing up the failure physical models in common use,this paper advanced a cumulative damage-reaction theory life model to the storage and usage of solid rocket propellant,and,by calculating examples,demonstrated this model clearly.
通过对常用失效物理模型的分析和总结,提出了固体火箭推进剂贮存使用寿命的累积损伤-反应论模型,并通过算例阐释了这一模型。
2.
By using real time holographic interferometry,the solid rocket propellant combustion process were investigated and recorded by a video camera with a shooting speed of 25 frames per second and the maximum electronic shutter speed of 1/2000 second.
本文采用实时全息法与摄像机相结合的方法来研究固体火箭推进剂的燃烧过程，记录速度为２５帧／秒，曝光快门速度最高可达１／２０００秒。
3.
Anti-stick coatings for stripping of solid rocket propellant, which could be cured at room temperature had been successfully developed.
开发一种用于固体火箭推进剂脱模的可常温固化溶剂型防粘涂料,该涂料是以常温固化型氟树脂为基体,加入改性微粉及其他各种助剂,配制而成的悬浮液。
补充资料：固体推进剂导弹
| 固体推进剂导弹 solid-propellant missile 以固体推进剂火箭发动机为动力装置的导弹。简称固体导弹。这种导弹有战术导弹，也有战略导弹。固体战略导弹都携带核弹头。固体战术导弹多数携带常规弹头，少数携带核弹头；有的既可携带常规弹头，又可携带核弹头。固体导弹的火箭发动机结构简单，推进剂贮存在燃烧室常备待用，能适应自旋状态下工作，失重状态下点火容易，地面设备较少。因此，维护使用方便，发射准备时间较短，便于携载和机动，被各国广泛采用。 |
说明：补充资料仅用于学习参考，请勿用于其它任何用途。
参考词条