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Euler angle error model,rotation vector error model(RVE)and quaternion error model(QE)were qualitatively and quantitatively compared and an in-flight alignment filter algorithm was designed.This algorithm used extended Kalman filter(EKF)based on RVE and QE separately avoiding the accuracy problem of the Euler angle model and used Rauch-Tung-Striebel(RTS)smoothing method to refine the accuracy recuperating the coning error for simplified RVE.Simulation results show that RVE and QE are more adapt for nonlinear filter estimation than the Euler angle model.The filter algorithm designed has more advantages in convergence speed,accuracy and stability comparing with the algorithm based on the three models separately. 相似文献
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为解决空中来袭诱骗目标难于被导引头发现的问题,提出了用谐波雷达导引头进行目标识别的方法。根据目标的运动轨迹推导了目标谐波弹道系数模型,就不同的目标进行谐波弹道系数仿真,仿真结果表明通过比较谐波弹道系数的数值能够区分空中真实目标和虚假目标,由此验证了谐波雷达导引头在目标识别领域的实用性,为谐波散射理论在雷达导引头设计中的应用打下基础。 相似文献
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航空布撒器动力学具有非线性、强耦合、大参变的特点.针对动力学模型耦合和气动系数不确定性,给出了倾斜转弯自动驾驶仪的三通道独立设计方法.首先,采用混合灵敏度理论设计俯仰和滚转通道自动驾驶仪,以保证弹体在大空域范围内有较好的指令响应特性和稳定性.针对快速滚转引起的耦合,在偏航通道中引入攻角和滚转角速率信息,实现滚转/偏航运动解耦,抑制侧滑角.全弹道仿真表明,该方法设计的驾驶仪能适应大范围的气动参数变化,具有很好的鲁棒性,并能有效地实现倾斜转弯控制的好r forl coordinated law for yaw channel is givenaft Using . 相似文献
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In this dissertation, un-powered gliding aircraft's optimal extended rangeproblem is discussed. The aircraft movement model was built. According to the degree of coupling, the model can be classified into a simple model or a complicated model. Using an optimal control method, two different movement models gave out the aircraft's attitude angle optimal flight path. Complicated model's optimal solution can be found by the genetic algorithm. This method can transfer the analytic solution of complicated model to a numerical value solution. Comparing the simulation results of different methods, it showed that the genetic algorithm combined with the complicated model's numerical value solution had the best performance in control strategy. This method solved the problem in which the highly coupling complicated model's analytic solution was hard to obtain. It verified that the genetic algorithm has validity in the field of extended range solution searching. 相似文献
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The alignment accuracy of the strap-down inertial navigation system (SINS) of airborne weapon is greatly degraded by the dynamic wing flexure of the aircraft. An adaptive Kalman filter uses innovation sequences based on the maximum likelihood estimated criterion to adapt the system noise covariance matrix and the measurement noise covariance matrix on line, which is used to estimate the misalignment if the model of wing flexure of the aircraft is unknown. From a number of simulations, it is shown that the accuracy of the adaptive Kalman filter is better than the conventional Kalman filter, and the erroneous misalignment models of the wing flexure of aircraft will cause bad estimation results of Kalman filter using attitude match method. 相似文献
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