1) Aerodynamic Parameters Calculation
气动参数解算
2) calculating parameters
参数解算
1.
It points out that the traditional method used for calculating parameters of 3D coordinates transformation is the Least Squares(LS) method,this method only takes coordinates are erroneous of one coordinate system into account,but it is not agree with the reality apparently.
指出传统最小二乘三维坐标转换参数解算方法仅考虑其中之一坐标系下坐标存在误差,显然与实际情况存在偏差,为了解决该问题,介绍了一种基于总体最小二乘法的三维坐标转换参数解算方法,并对该方法进行了程序实现和仿真实验验证,结果表明,总体最小二乘方法能够有效用于三维坐标转换参数的解算。
3) aerodynamic numerical solution
气动计算数值解
4) aerodynamic parameters
气动参数
1.
The problem of aerodynamic parameters estimate was focused on.
设计了防空导弹气动参数估计步骤,并提出气动参数估计合理的判别准则,研究了气动参数估计所需要的必要参数;结合工程设计方法,提出了一种基于反设计的防空导弹气动参数估计方法。
2.
On the basis of the simulation results, aerodynamic parameters are analyzed, and the optimal design of the aerodynamic shape can be obtained.
文中应用数值仿真软件对某弹头部的三种设计方案进行了外流场数值仿真,在仿真结果的基础上对弹头部气动参数进行对比分析,得出了较优气动外形。
3.
From the aspects of stability margin and aerodynamic parameters, this paper states that aerodynamic coupling is the dominant reason why missile s control system on the condition of large angle of attack is unstable.
现分别从稳定裕度和气动参数两个方面 ,论述了气动交连耦合是造成大迎角飞行导弹控制系统不稳定的重要原因 ,并由此得出结论 :对于大迎角下气动耦合强烈的导弹 ,其控制系统需考虑采用解耦控制 ,以便行之有效地变不稳定系统为稳定系统。
5) aerodynamic parameter
气动参数
1.
The effects on the forces between two stages of some aerodynamic parameters were analyzed,and through reasonable designation of the aerodynamic figure of the missile,the forces between two stages could be reduced effectively.
通过定量分析多个气动参数对级间作用力的影响程度,可知合理设计两级弹体气动外形可以有效减小弹体的级间作用力。
2.
The change rules of aerodynamic parameters including lift coefficient,drag coefficient and pitch moment coefficient have been analyzed when angle of attack and fuel flow rate is changed.
考虑了不同飞行攻角、不同燃料流率下气动参数,包括升力系数、阻力系数和俯仰力矩系数的变化规律。
3.
According to the rigid body trajectory model of finless-aerial-bomb under the ideal conditions,the influences of aerodynamic parameters on the motion of centroid and angle of finless-aerial-bomb were analyzed by theoretical simulation.
依据理想条件下的无安定器航弹刚体弹道模型,通过计算机仿真系统分析了无安定器航弹各气动参数对航弹质心运动和绕质心运动的影响。
6) aerodynamic coefficients
气动参数
1.
The aerodynamic coefficients were estimated by using STF.
首先用强跟踪滤波器对气动参数进行估计,然后根据估计值与标称值的偏差对攻角和倾斜角进行修正,最后对原始非线性方程沿着标称轨道线性化得到线性偏差方程,并利用线性二次型最优调节器原理设计控制律。
2.
The results show that this technique is useful for quick determination of aerodynamic coefficients, and particularly applicable to nonlinear flight regimes, such as high angle of attack regime.
给出了一种利用飞行器飞行试验实测数据估算飞行器气动参数的建模前估计算法，完成了某轴对称无控飞行器的非线性气动参数辨识。
补充资料：参数
分子式：
CAS号：
性质：对指定应用而言，它可以是赋予的常数值；在泛指时，它可以是一种变量，用来控制随其变化而变化的其他的量。
CAS号：
性质：对指定应用而言，它可以是赋予的常数值；在泛指时，它可以是一种变量，用来控制随其变化而变化的其他的量。
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