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The problem of generating optimal paths for curvature-constrained unmanned aerial vehicles (UAVs) performing surveillance of multiple ground targets is addressed in this paper. UAVs are modeled as Dubins vehicles so that the constraints of UAVs' minimal turning radius can be taken into account. In view of the effective surveillance range of the sensors equipped on UAVs, the problem is formulated as a Dubins traveling salesman problem with neighborhood (DTSPN). Considering its prohibitively high computational complexity, the Dubins paths in the sense of terminal heading relaxation are introduced to simplify the calculation of the Dubins distance, and a boundary-based encoding scheme is proposed to determine the visiting point of every target neighborhood. Then, an evolutionary algorithm is used to derive the optimal Dubins tour. To further enhance the quality of the solutions, a local search strategy based on approximate gradient is employed to improve the visiting points of target neighborhoods. Finally, by a minor modification to the individual encoding, the algorithm is easily extended to deal with other two more sophisticated DTSPN variants (multi-UAV scenario and multiple groups of targets scenario). The performance of the algorithm is demonstrated through comparative experiments with other two state-of-the-art DTSPN algorithms identified in literature. Numerical simulations exhibit that the algorithm proposed in this paper can find high-quality solutions to the DTSPN with lower computational cost and produce significantly improved performance over the other algorithms. 相似文献
444.
采用LES(large eddy simulation)+FW-H(Ffowcs Williams-Hawkings)方程,研究了圆柱表面使用不同PPI(pore number per inch)和厚度的多孔介质对圆柱尾迹及圆柱-翼型干涉噪声的影响,探索了多孔介质的降噪规律和机理。结果表明:多孔介质能稳定圆柱表面的剪切层,抑制旋涡脱落,从而削弱尾迹对下游翼型的影响,圆柱单音噪声最大可降79 dB,翼型单音峰值降低13.22 dB,宽频噪声降低20 dB;多孔材料PPI的变化对降噪效果影响较小,而厚度是影响流场模态、降噪效果及气动性能的一个关键参数;多孔材料厚度合适时,圆柱-翼型流场形态为“剪切层模态”,可有效降低湍流干涉噪声;多孔材料厚度较小时,发现了一种流场形态,即“剪切层-尾迹模态”,导致翼型噪声增大;合适的多孔介质厚度不仅降噪效果显著,对圆柱-翼型的气动性能也有改善作用。 相似文献
445.
《中国航空学报》2022,35(8):132-142
Solar power satellite receives great attention because it can release the energy crisis and environmental problems in the future. However, the launch and maintenance costs are tremendous due to the large system mass and large fuel consumption to counteract space perturbations. To reduce mass and fuel, a novel quasi-Sun-pointing attitude in Sun-frozen orbit is proposed. The Sun-frozen orbit has a nonzero eccentricity vector that always points towards the Sun. The quasi-Sun-pointing attitude is a periodic solution of the Sun-pointing attitude angle. Although about 3 % electricity must be given up because of the variation of Sun-pointing attitude angle, little control action is required to deal with the solar radiation pressure and gravity-gradient torque. The algorithm to obtain initial conditions is proposed. The influences of system parameters and structural flexibilities are studied. Simulation results reveal that the quasi-Sun-pointing attitude in Sun-frozen orbit dramatically reduce fuel consumption, the dry mass, and complexity of the control system. In addition, structural vibration is hardly induced by the gravity-gradient torque. Thus, the bending stiffness as well as the mass of the supporting structure can be reduced. 相似文献
446.
当航天器执行高动态敏捷机动或者姿态动态跟踪控制等任务时,常使用控制力矩陀螺(control moment gyroscope,简称CMG)和飞轮(reaction wheel,简称RW)构成的混合执行机构来提供大力矩。提出了基于力矩输出能力最优化的混合执行机构操纵律,从几何角度出发,给出了力矩输出能力最优的CMG框架角速度和RW角加速度,通过引入参数,并讨论参数的设置的最优,使得框架转速误差和输出力矩误差的混合二次型达到最小,保证了混合执行机构在输出力矩误差最小的情况下,力矩输出能力最优。以金字塔构型的CMG集群和正交的RW集群构成的混合执行机构为例,对基于力矩输出能力最优化的混合执行机构操纵律进行合理化分析,证明了引入参数的作用,并且证明了混合执行机构不存在CMG奇异情况。仿真结果表明,基于力矩输出能力最优化的混合执行机构操纵律解决了CMG奇异的问题并使得RW不陷入饱和,输出力矩误差较小,输出力矩能力强,能够应用于航天器大角度机动任务。 相似文献
447.
《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2023,71(3):1769-1783
Lunar final approach navigation is critical for pin-point lunar landing in future missions. This study investigates the use of lunar gravity gradient measurements for autonomous navigation of a lunar probe during the final approach phase. As the spacecraft approaches the Moon, the strength of gravity gradient signals improves. A spaceborne gravity gradiometer can precisely measure local gravity gradients, and the latest lunar gravity model GL1500E is used to provide reference values. The employed truncation degree and order of the gravity model are increased stepwise considering the decreasing altitude of the spacecraft in order to reach a compromise between computational costs and model accuracy. An iterative Kalman filter is developed for coupled orbit and attitude estimation using gravity gradient measurements and attitude quaternions obtained from star sensors. A simulated spacecraft with a gradiometer noise level of 0.01 E is considered. Simulation results show that the spacecraft’s position converges rapidly and achieves an accuracy of less than 100 m at the last epoch. 相似文献