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Design of an aircraft pitch control experimental test bench

机译:飞机俯仰控制实验台架设计

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Aircraft pitch control is fundamental to improve the performance of unmanned aerial vehicles. This paper presents the instrumentation and modeling process of an experimental platform for aircraft pitch control. A complementary filter is designed to improve the angular position estimation based on inertial measurements. The platform was used for the implementation of different controllers in a wind tunnel facility: a Ziegler-Nichols PID and a loop shaping compensator. The test bench allows the implementation of typical continuous-time linear and non-linear controllers. The plant identification process is designed to compute the parameters that meet the open loop time domain characteristics and the closed loop frequency characteristics. The time delay in the control loop is computed through an experiment and used for the loop shaping design process. The controllers are implemented and compared according to its time domain performance. The best suited control is then analyzed in terms of perturbation rejection and more demanding tests. The article shows that the resulting test bench is suitable for the experimental evaluation of typical pitch angle control strategies. Due to the integration with a wind tunnel, the test bench is able to simulate a wide range of flight conditions. Including extreme conditions that would not be safe in real flight experiments.
机译:飞机俯仰控制是提高无人机性能的基础。本文介绍了用于飞机俯仰控制的实验平台的仪器和建模过程。互补滤波器被设计为基于惯性测量来改善角位置估计。该平台用于在风洞设施中实施不同的控制器:Ziegler-Nichols PID和环路整形补偿器。该测试台允许实施典型的连续时间线性和非线性控制器。工厂识别过程旨在计算满足开环时域特性和闭环频率特性的参数。通过实验计算出控制回路中的时间延迟,并将其用于回路整形设计过程。根据其时域性能来实现和比较控制器。然后根据扰动抑制和更苛刻的测试来分析最合适的控制。该文章表明,所得的测试台适用于典型俯仰角控制策略的实验评估。由于与风洞集成在一起,因此测试台能够模拟各种飞行条件。包括在实际飞行实验中不安全的极端条件。

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