nozzle的例句大全

The thrust characteristics of axis symmetry nozzle were mainly measured in test. For the nozzle having a vectoring angle, the deflection efficiency was measured too.

对于轴对称喷管模型主要进行了喷管的推力特性测量，对于实施矢量偏转后的喷管模型除了给出了喷管推力特性外，还给出了喷管的偏转效率。

Calculations of Thrust Coefficient and Thrust Deviation Angle of the Nozzle with Obligue Exit Section

斜切口喷管的推力系数、推力偏角的计算

The thrust coefficient has direct relationship with the area ratio of nozzle and is independent of the area of nozzle throat.

矢量状态下，推力系数与面积比呈正比关系，而对喉道面积的变化不敏感。

The characteristic velocity, area of nozzle throat and other parameters are calculated by using the static test results of solid rocket motor ( SRM) and introducing generalized pressure coefficient and thrust coefficient.

利用发动机地面试验结果，引入广义的压强系数和推力系数，计算了发动机的特征速度、喷管喉部面积等参数。

The internal portion of nozzle afterbody is designed using the theory of expansion wave. The upper wall is designed for better thrust coefficient. The propulsion performance of nozzle afterbody is improved.

介绍了后体喷管的参数化设计方法，应用膨胀波理论设计后体内部喷管，以推力系数为目标设计上壁型面，提高了后体喷管的推进性能。

The effect of operation pressure on the specific impulse of tactical missile solid motors is analyzed from several factors, such as characteristic velocity, thrust coefficient, impulse coefficients of the chamber and nozzle.

从固体发动机的特征速度、推力系数、燃烧室冲量系数和喷管冲量系数等因素出发，分析了发动机工作压强对战术固体火箭发动机比冲的影响。

The particularity of the altitude simulated test of an engine with Laval nozzle was analyzed in brief. The engine thrust determination and correction in altitude test with large deviation of simulated ambient pressure was put forward.

简析了拉瓦尔喷管发动机高空模拟试验的特殊性，提出了大模拟偏差条件下确定和修正拉瓦尔喷管发动机推力的方法。

An Experimental Study on Theory for Minimized Thrust Misalignment Nozzle

小推偏喷管理论实验研究

The effects of entrance half angle on the thrust misalignment of parabolic nozzle

抛物型喷管入口扩张半角对推力偏心的影响

Thrust misalignment in double-circular nozzle s

双圆弧超音速喷管的推力偏心特性

Experimental tests and applications on rockets show that the mini thrust misalignment nozzle exists and the new method of design is feasible.

试验和应用表明，微推偏喷管是存在的，新设计方法是可行的。

The internal flow in the mini thrust misalignment nozzle where the inlet flow is not parallel with the axis of its supersonic section is studied.

研究了入流倾斜于喷管超音速段轴线的微推偏喷管内流场。

Thrust misalignment in parabolic nozzle is investigated for the situation where the gas flow is misaligned with respect to the axis of the supersonic region of the nozzle.

研究了当气流偏离抛物型喷管超音速段对称轴时所引起的喷管推力偏心。

Thrust misalignment caused by gas flow is one of the main reasons for uncontroled-rocket dispersion. This dissertation researches the rule of side thrust and misalignment moment according to Laval nozzle of different type inner profiles.

气动偏心是影响无控火箭密集度的主要原因之一，本文研究不同型面拉瓦尔喷管产生侧向力、推力偏心力矩的规律，结合实验研究，丰富和完善了微推偏喷管的设计方法。

A calculation method for the rocket engine's optimum thrust nozzle contour design

火箭发动机最佳推力喷管型线的计算方法

The condition of the existence of solution of functional extreme value problem applied to maximum thrust nozzle is also presented.

同时，还导出了最大推力喷管这个泛函极值问题解存在的条件。

A study of the maximum solid rocket engine thrust nozzle surface for one-dimensional two-phase flows

固体火箭发动机一元两相流动最大推力喷管型面研究

Design of Optimum Thrust Nozzle Contour

最佳推力喷管型面设计

Transonic vibration induced by mismatching between engine and thrust nozzle

发动机和尾喷管匹配引起的跨音振动

Unsteady internal performance study of counterflow vectoring thrust nozzle

逆流推力矢量喷管的非定常内流性能研究