UC知道帮忙翻译一下啊 飞控方向的 后天就要交了 十万火急
来源：百度知道 编辑：UC知道 时间：2024/06/01 16:36:25
IV. Identification of the UAV Model Parameters
The UAV model has several parameters for which values need to be estimated. Parameter values of the model have to be chosen carefully to adequately represent the behavior of the UAV. Easily measurable parameters are determined by measures. This is the case for the mass of the UAV, its inertia moments and some of its physical dimensions such the wingspan, the mean aerodynamic chord, and the wing area.
Other parameters are determined with the output-error approach algorithm, using data obtained from
flight tests.7–9 The parameters estimated with this method are the stability and control derivatives from
which each aerodynamic coefficient is evaluated, that is drag force, lift force, side force, pitch moment, roll
moment and yaw moment coefficients. Also, the output-error approach is used to find the x position of the
aerodynamic center and the Jxz inertia product.
A. The Output-Error Approach
The
The UAV model has several parameters for which values need to be estimated. Parameter values of the model have to be chosen carefully to adequately represent the behavior of the UAV. Easily measurable parameters are determined by measures. This is the case for the mass of the UAV, its inertia moments and some of its physical dimensions such the wingspan, the mean aerodynamic chord, and the wing area.
Other parameters are determined with the output-error approach algorithm, using data obtained from
flight tests.7–9 The parameters estimated with this method are the stability and control derivatives from
which each aerodynamic coefficient is evaluated, that is drag force, lift force, side force, pitch moment, roll
moment and yaw moment coefficients. Also, the output-error approach is used to find the x position of the
aerodynamic center and the Jxz inertia product.
A. The Output-Error Approach
The
四.无人飞行器模型参数的确定
无人飞行器模型有几个参数的值需要被估计。模型的参数值应当被仔细地选择以恰当地描述飞行器的工作状态。大多数飞行器都有一些容易测量的参数，它们可以直接通过测量而得到，例如惯性力矩和飞行器的自身尺寸包括翼展、空气动力弦和两翼面积。
其它参数可以通过“输出误差算法”来求得。这种方法使用7-9次的航空测试获得的数据。使用这种方法可以估计出的参数包括稳定性和控制导数，其中后者可以把每一个空气动力系数估计出来，例如阻力、举力、侧力、倾斜力矩、转动力矩和偏航力矩等参数。另外，“输出误差算法”可以找出空气动力中心的x方位和Jxz平面的惯量乘积。
A.“输出误差算法”
这种方法是在记录输入的同时被激活从而对其进行操作算出输出并进行记录。接下来，通过使下面的目标函数取得最小值估计出模型参数：
G =
N Xi=1
[yM(i) − y(i)]T B[yM(i) − y(i)] （9）
其中N是记录下来的采样点数，B是加权矩阵，y(i)是即将被记录的经过处理的输出向量，而 yM(i)是对于给定输入的预测出的模型输出向量。为了得到更好的结果，输入应当有丰富的频谱范围从而使精度得到保证。如果存在非线性因素，那么还要求有各种各样的输入幅度。