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31.
32.
针对旋翼无人机在三维障碍物环境中自主飞行时路径搜索速度慢、轨迹生成通常忽略无人机动力学特性的问题,发展一种基于改进A^*算法并同时考虑无人机动力学特性和运动学性能的快速轨迹规划方法。首先,在三维障碍物环境中运用改进A^*算法通过剔除部分网格节点降低A^*算法的节点计算量,提升算法的路径搜索速度;其次,以最小化飞行轨迹的四阶导数作为目标函数,以路径点处的位置、速度、加速度等各阶导数作为约束条件优化飞行轨迹;最后,在三维障碍物环境中对比A^*算法改进前后的路径搜索结果,并对优化的飞行轨迹进行仿真飞行测试。结果表明:改进A^*算法大幅降低了A^*算法的节点计算量,显著提升了路径搜索速度;且无人机能够始终以较小位置误差沿优化轨迹光滑连续飞行。 相似文献
33.
舰载飞机自动着舰系统的研究 总被引:8,自引:1,他引:8
介绍了舰载飞机的自动着舰系统(包括了飞机的飞行控制系统,推力控制系统及航空母舰的导引系统),并指出只有精确地控制飞机的不滑轨迹,才能使飞机在航空母舰上安全降落,本文着得讨论俯仰指令型的纵向自动着舰系统的原理、结构及设计,并指出导引指令中对舰体运动的补偿。 相似文献
34.
Matteo Ceriotti Gregory May-Wilson 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2021,67(9):2865-2877
The direction and magnitude of a solar sail acceleration are strongly related. For this reason, once the characteristic acceleration has been fixed, it is not possible to modulate the acceleration in a particular direction. In this work, a semi-analytical switching control law is derived, enabling a solar sail to emulate a smaller effective characteristic acceleration (without changes in geometry or optical properties); by periodically changing the pitch (cone) angle of the sail, in average over time, the acceleration produced by the sail matches exactly (in both direction and magnitude) that of a “smaller” sail. The range in which this is possible is determined, and the limitations on this range due to the size difference is computed. The method is validated on optimal Earth-Mars trajectories. 相似文献
35.
《中国航空学报》2020,33(6):1717-1730
To detect highly maneuvering radar targets in low signal-to-noise ratio conditions, a hybrid long-time integration method is proposed, which combines Radon-Fourier Transform (RFT), Dynamic Programming (DP), and Binary Integration (BI), named RFT-DP-BI. A Markov model with unified range-velocity quantification is formulated to describe the maneuvering target’s motion. Based on this model, long-time hybrid integration is performed. Firstly, the whole integration time is divided into multiple time segments and coherent integration is performed in each segment via RFT. Secondly, non-coherent integration is performed in all segments via DP. Thirdly, 2/4 binary integration is performed to further improve the detection performance. Finally, the detection results are exported together with target range and velocity trajectories. The proposed method can perform the long-time integration of highly maneuvering targets with arbitrary forms of motion. Additionally, it has a low computational cost that is linear to the integration time. Both simulated and real radar data demonstrate that it offers good detection and estimation performances. 相似文献
36.
Tommaso Pino Christian Circi Giovanni Vulpetti 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2019,63(11):3675-3690
A good model of solar-radiation pressure induced thrust is one of the key points in sailcraft trajectory design. The sail membrane’s local topographic deformations, i.e. wrinkles and creases, are among the main aspects that such a model should include. We have analyzed the influence of wrinkles/creases, as a whole, by measuring the related deformations on small samples of sail membrane, 2.5?μm thick, consisting of CP1 and physical-vapor-deposition Aluminum. Experimental outcomes from our laboratory facility have been processed, statistically investigated, and inserted into the lightness vector formalism. We have used such formalism for accurate sailcraft trajectory computation via a non-ideal reflection sail thrust model. Finally, we computed the deviations of wrinkled-sail sailcraft final orbital states with respect to the no-wrinkle sail final orbital ones for a circular to circular 2D inward transfer. The radii of the orbits are 1?AU and the semi-major axis of Mercury, respectively. It appears that sail wrinkles and creases are no longer negligible in the sailcraft trajectory design. 相似文献
37.
A cathode mandrel with translational and rotational motion, which was supposed to obtain uniform friction effect on surface, was employed in abrasive-assisted electroforming for revolving parts with complex profile. The effects of current density, translational speed and rotational speed on the deposit properties were studied by orthogonal test. The tensile strength, elongation and micro hardness value were measured to find out how the factors affected the properties. The optimized results show that changes of current density affect the tensile strength of nickel layer most, while translational speed has the most remarkable influences on both elonga-tion and micro hardness. The low rotational speed affects the properties least. In this experiment, a smooth nickel layer with tensile strength 581 MPa, elongation 17%and micro hardness 248HV is obtained by the orthogonal test. 相似文献
38.
在中国空气动力研究与发展中心(CARDC)超高速碰撞中心(HIRC)7.6 mm超高速碰撞设备的基础上,搭建纳秒级脉冲激光数字全息系统。提出滤波片和衰减片组合布置,减弱超高速碰撞等离子体自发光、提高信噪比的方法。实验获得了2.25 mm铝球弹丸以4.0 km/s的速度撞击0.5 mm厚铝板形成碎片云的全息图。采用小波变换算法对碎片云全息图进行重建,得到超高速撞击碎片云的三维结构和碎片大小。碎片云的轮廓呈椭球型,分为碎片云的前端、核心和外壳,碎片主要分布在弹丸破碎形成的碎片云核心,存在大碎片,且分布较集中,对后板的损伤也严重 相似文献
39.
40.
This paper presents the novel use of the particle swarm optimization(PSO)to generate the end-to-end trajectory for hypersonic reentry vehicles in a quite simple formulation.The velocitydependent bank angle profile is developed to reduce the search space of unknown parameters based on the constrained PSO algorithm.The path constraints are enforced by setting the fitness function to be infinite on condition that the particles violate the maximum allowable values.The PSO algorithm also provides a much easier means to satisfy the terminal conditions by adding penalty terms to the fitness function.Furthermore,the approximate reentry landing footprint is fast constructed by incorporating an interpolation model into the standardized bank angle profiles.Numerical simulations demonstrate that the PSO method is a feasible and flexible tool to generate the end-to-end trajectory and landing footprint for hypersonic reentry vehicles. 相似文献