The effect of empennage spread on flight attitude was analyzed and validated by flight test data.
针对某型导弹尾翼展开过程对飞行姿态的影响进行了细致地分析,并通过飞行试验数据对分析方法加以验证;最后论证了尾翼展开的不同步性会影响导弹的飞行姿态。
Analyze the impact of empennage on the pose control of FMAVs and develop the moment model.
研究了尾翼对微扑翼飞行器姿态控制的影响,提出了尾翼对机身的力矩模型。
Existing producing condition of complex empennage (aluminum alloy LD10) faces many problems, such as poor precision, weak mechanical properties.
针对复杂尾翼件 ( LD1 0 )生产中存在的精度低、力学性能差的实际问题 ,研究了尾翼等温成型技术 ,并优化了工艺参数。
Based on the results of previous study , through optimization of the superplastic forming process and further tests, the paper puts forward an optimized scheme of superplastic forming process for an armour-piercing fin.
该成形方案使穿甲弹尾翼成形的自动化程度显著提高 ,产品质量更加稳定 ,劳动强度进一步减轻 ,生产率呈多倍提高 ,电能消耗大大减少 ,满足了大批量工业生产的要
There are several types of fins adopted in the modern submarine,including mainly the X-fin and the 十-fin.
现代潜艇尾翼的形式普遍采用十字形和X形两种基本形式,文中通过采用求解RANS方程的数值计算方法,结合RNG-kε、S-kω、SST-kω3种湍流模型,对带有30°、45°,60°3种X形尾翼以及十字形尾翼的潜艇阻力进行数值模拟,通过计算结果发现:对各种方案采用RNG-kε和SST-kω湍流模型进行计算时,阻力比较接近,而采用S-kω湍流模型时,阻力比前两种要大;在所有方案中,45°尾翼具有最小的阻力。
An explosively formed penetrator (EFP) with fins has the advantages of stable flight and deep penetration.
带尾翼的杆状爆炸成形侵彻体 ( explosively formed penetrator,简称 EFP)具有良好的飞行稳定性和侵彻性能 。
The study of aerodynamic characteristics of a notchback car with rear wing at different angles of attack;
尾翼攻角对斜背式轿车气动力特性影响的研究
In order to increase manipulation stability, a rear wing is appended to an automobile.
应用RNGk-ε湍流模型对国产某型号轿车车身进行了外围流场数值模拟,针对高速条件下轿车尾部升力随之增加、操纵稳定性下降的特点,设计了一阶和二阶尾翼。
The heat flux on the rear wing of the rocket,espacially induced by interaction of wing with body,was obtained by correlation of experimental data.
重点研究了尾翼与芯级间的干扰加热,数值求解了自然正交曲线坐标系下尾翼内部二维单层和双层材料热传导方程,给出了典型部位的内外表面温度计算结果,表明表面涂漆对尾翼前缘并不能起到防热隔热效果。
This paper describes the numerical and experimental study on the EFP tail shapes resulting form three-point, four-point and six-point initiation.
文中通过数值模拟和试验,对三点、四点、六点起爆对EFP尾翼形状的影响进行了研究。
This paper discusses the design and the realization of missile wing and rudder electric simulation load test system based on digital signal processor(DSP) TMS320LF2407 and direct torque control(DTC) servo driver ACS600.
实验结果表明,系统能精确地模拟弹翼及尾翼在飞行展开过程中的气流阻力,满足加载测试系统的快速性要求。
fuselage-wing-tail combination configuration
机身－机翼－尾翼组合体
Tail-fin anchor
GB/T10829-1998尾翼锚
APFSDS (Armor Piercing Fin Stabilized Discarding Sabot)
尾翼稳定脱壳穿甲弹
Aerodynamics and Aerodynamic Heating Research for the Wing of Hypersonic Projectile;
高超声速弹箭尾翼（弹翼）的气动力与气动热研究
The conventional tail must be at a negative angle of attack, and the Canard tail at a positive angle.
通常的尾翼必须处于负迎角，而鸭式尾翼则为正迎角。
slow down by moving the tail sideways.
通过摇摆尾翼来减缓行进速度。
a stabilizer that is part of the vertical tail structure of an airplane.
飞机的垂直尾翼部分的稳定器。
The sideslipping airplane gives rise to a side force on the vertical tail.
侧滑的飞机在垂直尾翼上引起侧力。
Analysis for Vertical Target Precision of APFSDS
尾翼稳定脱壳穿甲弹立靶密集度分析
Wind Tunnel Experiments of Symmetric Discarding Sabot Disturbance of APFSDS Projectile
尾翼脱壳穿甲弹对称脱壳的风洞实验
Empennage-Install Stabilizer and Vertical Fin.
尾翼－安装水平安定面、垂直安定面。
A Numerical Wind Tunnel Study on Distance between Tail Wing and Rear Hood and Angle of Attack of Tail Wing of a Car Model Using CFD;
轿车尾翼间隙和攻角的数值风洞研究
The Application Study of Affixed Cover in Forming Process of EFP with Fins
贴隔板法在尾翼EFP成型中的应用研究
Numerical Simulation Study of Performance of Empennage Forming of Liner with Five Concave Arc Margins Cutted
五凹弧切边罩尾翼成形三维模拟研究
Effect of Spinning Rate on Coupling Degree for Wing-deflection Rolling-missile
斜置尾翼导弹的转速对耦合度的影响
Experimental Research on EFP with Fins Formed by Four Detonating Points
四点起爆形成带尾翼EFP的试验研究
The central body of an aircraft, to which the wings and tail assembly are attached and which accommodates the crew, passengers, and cargo.
机身可承载机务人员、乘客和货物的配有机翼和尾翼的飞机的主机
The forces on an isolated tail are represented just like those on an isolated wing.
作用在单独尾翼上的力的表示方法正和单独机翼的情形一样。