盈余从美国s。空军固体火箭马达。
附加的固体火箭助推器重量210千克。
本文介绍一种设计固体火箭喷管的新方法。
A new method of the solid propellant rocket nozzle design is presented.
研究了整体式固体火箭冲压发动机的应用性能。
Applications of integral solid propellant rocket ramjets arc researched.
据说，这种东西最早是由NASA作为固体火箭燃料而研发的。
Supposedly, it was developed by NASA as a solid rocket fuel.
探讨和分析了固体火箭助推器内弹道的同步性问题。
The interior ballistics synchronism of solid boosting rockets is discussed and analyzed.
对固体火箭助推器进行了较详细的分析，证明方案是可行的。
On the basis of more detailed analysis, verified is that the idea is very feasible.
但在发射点，轨道器一面是15层楼高的外挂燃料箱，两侧是两个固体火箭助推器。
But in launch position, the orbiter is perched on the side of its 15-story external fuel tank and flanked by two solid rocket boosters.
介绍了主发动机加助推器和简易控制方法实现固体火箭等高飞行的设计方案。
The tentative design of constant altitude flight solid rocket composed of the sustainer, the booster and its simple control method is presented.
介绍了主发动机加助推器和简易控制方法实现固体火箭等高飞行的设计方案。
The tentative design of constant altitude flight solid rocket composed of the sustainer the booster and its simple control method is presented.
火箭有一个巨大的核心，两侧是两个固体火箭助推器，每个比战神i的第一级稍微大一些。
The rocket consists of a giant core stage flanked by two solid rocket boosters, each slightly larger than the first stage of Ares I.
国家航空航天署正在检查奋进号航天飞机及其固体火箭助推器是否被闪电损坏。
NASA is now checking on the damage of lightning on Endeavor and its solid rocket booster.
首先建立研究静止增程固体火箭冲压发动机补燃室燃烧特性的物理和数学模型。
Physical and mathematic model of investigating combustion characteristics of secondary combustion chamber for static extended solid rocket ramjet was established.
从外部燃料箱的顶端至船尾固体火箭助推器的裙摆，发射台上的航天飞机高184英尺(56米)。
A shuttle on the launch pad measures 184 feet (56 meters) tall from the tip of the external tank down to the aft skirts of its twin solid rocket boosters.
固体火箭推进剂是一种粘弹性高聚物，同时又是颗粒基复合材料。其断裂实验难度较大。
Solid rocket propellant is a kind of high filled granular composite with viscoelastic behavior so that the experimental researches on its fracture are very difficult.
采用传统设计优化方法和多学科设计优化(MDO)方法进行了固体火箭助推器设计优化。
Design optimization of solid rocket booster was carried out by using traditional and multi-disciplinary design optimization (MDO) method.
由无控固体探空火箭和地面发射设备组成的运载系统是固体火箭探空系统的一个组成部分。
The carrier system that consists of an unguided solid sounding rocket and a set of launching facilities is a part of solid rocket sounding system.
应用概率密度函数非预混模型，对固体火箭冲压发动机补燃室内的湍流燃烧进行了数值模拟。
The numerical simulation of turbulent combustion in the afterburner of solid rocket ramjet was performed by applying the probability density function non -premixed mode.
密闭燃烧器法是一种能测定很宽压强范围内固体火箭推进剂燃速特性及变化情况的快速测量方法。
Burning rate measurement with closed burner is a rapid method for measuring burning rate character and its change of solid rocket propellants in a wide pressure range.
介绍了固体火箭冲压发动机地面实验装置及测控系统组成、功能、技术指标和可以开展的研究工作。
The paper presents the composition, functions, technical performance and research of the solid rocket ramjet engine ground test equipment and measurement control system in detail.
航天飞机的初始设计即没有预料到泡沫脱落问题也没有预料到固体火箭助推器连接密封性能这么差。
The initial Shuttle design predicted neither foam debris problems nor poor sealing action of the Solid Rocket Booster joints.
采用MDO方法，可提高固体火箭助推器的设计质量，大大减少设计迭代次数，从而缩短设计周期。
MDO method can improve design quality for solid rocket booster, and greatly reduce iterative times and shorten design period.
应用二阶隐式TVD格式对固体火箭冲压发动机增程弹丸超音速进气道内部湍流流场进行了数值仿真。
The numerical simulation of supersonic inlet internal turbulent flow of solid rocket ramjet assisted range projectiles was performed by 2-order implicit TVD.
文中对航天飞机固体火箭助推器回收系统所用的降落伞及即将使用的新式轻型降落伞的研制情况作了简要介绍。
This paper describes the parachutes that have been developed for the space shuttle solid booster recovery system. A status report on a new lightweight parachute system being developed is presented.
硼颗粒在通过固体火箭冲压发动机的燃气发生器喷管进入补燃室的过程中，颗粒通常都会受到高速气流的作用。
The effects of various parameters on boron particle ignition of ducted rocket secondary chamber were studied with the model developed by the King.
推导了一种自旋固体火箭的流体动力学模型，并通过实例对模型进行了验证计算，计算结果与实际情况基本吻合。
The paper deduced the Fluid dynamics model of Spinning solid propellant rockets, and validated the Fluid dynamics model by analyzing the examples, the result accord with the actual status.
贫氧推进剂燃速是固体火箭冲压发动机设计和性能分析的重要参数，也是对推进剂配方进行检验验收的主要指标。
The burning rate of the fuel-rich propellants is the parameter which is important for Ducted Rocket design and performance analysis and is main inspection criterions of propellant prescriptions.
小型固体火箭脉冲发动机具有体积小、反应时间短、结构简单、成本低廉等优点，是一种比较理想的修正执行机构。
The small solid rocket impulse engines have the advantages of small volume, short reaction time, and simple configuration, low cost, so it is a right choice.
采用块结构网格与二阶精度流场分区求解技术，对固体火箭冲压发动机增程弹丸超声速进气道特性进行了深入研究。
By means of block structure grid and second-order zonal solver method, the research on supersonic inlet performance of solid rocket ramjet assisted range projectiles was carried out.
采用块结构网格与二阶精度流场分区求解技术，对固体火箭冲压发动机增程弹丸超声速进气道特性进行了深入研究。
By means of block structure grid and second-order zonal solver method, the research on supersonic inlet performance of solid rocket ramjet assisted range projectiles was carried out.
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