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Response and Control of an Aircraft in the Presence of Wind Shear

存在风切变时飞机的响应和控制

基本信息

批准号：
61460080
负责人：
KIMURA Haruo
金额：
$ 3.39万
依托单位：
Kyushu University
依托单位国家：
日本
项目类别：
Grant-in-Aid for General Scientific Research (B)
财政年份：
1986
资助国家：
日本
起止时间：
1986 至 1987
项目状态：
已结题

项目摘要

1. Expressions for aerodynamic forces and stability derivatves in wind shear have been given considering effects of spatial wind distribution over the aircraft. It has been found by a numerical example that the eigenvalues of longitudinal motion are influenced by the potitional relation between the wing and the horizontal tail.2. Effects of temporal wind variation in wind shear have beeen investigated and formulation of acceleration derivatives has been made. It has been shown that the acceleration influences the phugoid-mode motion and the aerodynamic disturbance forces due to the acceleration cannot be neglected.3. Measurement of aerodynamic forces on a two-dimensional wing-tail combination model has been performed in various wind shear conditions generated in a wind tunnel. The results show the validity of the theoretical expressions for the aerodynamic effects of wind distribution. The existence of forces depending on the wind acceleration has also been verified qualitatively.4. A method of experimental prediction of the stability derivatives has been tested by giving forced oscillation to the afore-mentioned model, and it has been confermed that the effects of wind shear can be detected.5. A method of real-time onboard estimation of wind variation has been developed as follows: Optimal estimation of the ground speed is made by using the data of onboard navigational instruments, the inertial navigation system and others, and the difference between the estimated ground speed and the measured airspeed is considered as the wind speed. The results of simulation has shown the availability of the method.6. Utility of an automatic flight control system. operating as an optimal regulator, in preventing deviation of the flight course due to wind shear has been examined by a simulation applying the system for the alleviation of gust response of the aircraft and extent of the effectiveness has been found.

1. 考虑飞机空间风分布的影响，给出了风切变的气动力和稳定性导数的表达式。通过数值算例发现，纵向运动特征值受机翼与水平尾翼位置关系的影响。 2．研究了风切变中风的时间变化的影响，并制定了加速度导数的公式。研究表明，加速度对长周期运动有影响，且加速度产生的气动扰动力不可忽略。 3．二维翼尾组合模型的气动力测量已在风洞中产生的各种风切变条件下进行。结果表明风分布气动效应理论表达式的有效性。依赖于风加速度的力的存在也得到了定性的验证。4．通过对上述模型施加受迫振荡，对稳定性导数的实验预测方法进行了验证，证实可以检测出风切变的影响。 5．提出了一种实时风速变化机载估计方法，利用机载导航仪器、惯导系统等数据对地速进行优化估计，将估计地速与实测空速之差作为风速。仿真结果表明了该方法的有效性。 6．自动飞行控制系统的实用性。通过模拟应用该系统来减轻飞机的阵风响应，检查了作为最佳调节器的操作，防止由于风切变导致的飞行路线偏差，并发现了有效性的程度。