机场热点时空分布特征及运行风险评价

为研究大型机场航空器地面滑行冲突风险,提出一种基于机场热点时空分布特征的机场机动区运行风险评价方法。首先,以中南地区某机场为例,将场监雷达数据按每3 h分段,分别识别各时间段的机场热点,分析其时空分布特征;然后,基于热点发生的可能性和后果的严重性,构建考虑航空器冲突架次比、冲突可能性、冲突持续时间、冲突级别的机场热点风险评价模型,依据现有机场热点风险等级评价标准,评价该机场的热点风险等级。结果表明：该机场02号跑道运行风险高于20号跑道;02号跑道起降时,12：00—15：00点的机场热点风险最高;20号跑道起降时,9：00—12：00点机场热点的风险较高,与该机场实际运行情况基本相符。

基于利用率和跑道占用时间的军用机场快速出口滑行道位置优化模型

现行快速出口滑行道位置确定模型常以最小跑道占用时间为唯一目标,主要应用对象为民用机场,未能有效解决多机种、多运行模式下的军用机场快速出口滑行道位置确定问题。针对这个缺陷,基于综合利用率和综合跑道占用时间这2个指标,建立了综合考虑双指标的军用机场快速出口滑行道位置优化模型。以某军用机场飞行区构型为背景,以4种飞机为对象,结合该机场2种年架次比,在不同飞机着陆滑跑距离分布概率密度函数基础上,计算了不同位置快速滑行道出口对应的利用率,在此基础上得到了快速出口滑行道综合利用率。针对利用率大于90%的快速出口滑行道,应用贪心算法迭代不同快速出口滑行道的跑道占用时间,并通过加权计算得到综合跑道占用时间。基于综合利用率和综合跑道占用时间,确定出了快速出口滑行道数量和位置,给出了建议的方案,并进一步分析了年架次比改变对快速出口滑行道位置的影响。结果表明:与仅以利用率或最小跑道占用时间为优化目标的2种传统模型相比,应用优化模型提出的快速出口滑行道设计方案,在2种年架次比下使跑道占用时间分别缩短18.42,34.82 s,效率分别提高34.2%,40.6%。

Application of the Latching Control System on the Power Performance of a Wave Energy Converter Characterized by Gearbox,Flywheel,and Electrical GeneratorGustavor

The latching control represents an attractive alternative to increase the power absorption of wave energy converters(WECs)by tuning the phase of oscillator velocity to the wave excitation phase.However,increasing the amplitude of motion of the floating body is not the only challenge to obtain a good performance of the WEC.It also depends on the efficiency of the power take-off system(PTO).This study aims to address the actual power performance and operation of a heaving point absorber with a direct mechanical drive PTO system controlled by latching.The PTO characteristics,such as the gear ratio,the flywheel inertia,and the electric generator,are analyzed in the WEC performance.Three cylindrical point absorbers are also considered in the present study.A wave-to-wire model is developed to simulate the coupled hydro-electro-mechanical system in regular waves.The wave energy converter(WEC)performance is analyzed using the potential linear theory but considering the viscous damping effect according to the Morison equation to avoid the overestimated responses of the linear theory near resonance when the latching control system is applied.The latching control system increases the mean power.However,the increase is not significant if the parameters that characterize the WEC provide a considerable mean power.The performance of the proposed mechanical power take-off depends on the gear ratio and flywheel.However,the gear ratio shows a more significant influence than the flywheel inertia.The operating range of the generator and the diameter/draft ratio of the buoy also influence the PTO performance.

Liftoff of a New Hovering Oscillating-wing Micro Aerial Vehicle

Hovering ability forms the basis for space operations of Micro Aerial Vehicles(MAVs).The problem of uneven load puts high demands on the wing design.In this paper,a new hovering-mode for MAVs,inspired by flapping flight in bees and hummingbirds but using high-aspect-ratio and low-stress wings,is proposed.Different from the flapping actuations that occur at the wing roots,the two wings are driven back and forth in a straight line.To simplify the design and control the angle of attack,passive wing rotation is employed.The numerical results and analysis show that the maximum stress of the oscillating wing is approximately 1/6 of that of the flapping wing when the lift of the oscillating wing is twice that of the flapping wing.A theoretical aerodynamic model of the kinematics of the vehicle's driving mechanism was developed to fulfill its design.Force measurements indicate that the vehicle generates a sufficiently high cycle-averaged vertical thrust(71 g)for liftoff at a maximum frequency of 5.56 Hz,thereby validating the proposed aerodynamic model.Moreover,liftoff performance is presented to visually demonstrate the vertical take-off capabilities and hovering potential of the aeromechanical solution.