Optimal control and analysis for helicopter after releasing slung load

被引：0
|
作者：
Wang L. [1 ]
Chen R. [1 ]
Yan X. [1 ]
机构：
[1] National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2021年 / 36卷 / 03期
关键词：
Helicopter slung load systems; Nonlinear equations; Optimal control; Pilot inputs; Slung load release; Trajectory optimization;
D O I：
10.13224/j.cnki.jasp.2021.03.010
中图分类号：
V211 [空气动力学]; V411 [空气动力学];
学科分类号：
0801 ; 080103 ; 080104 ;
摘要：
The proper manipulations after releasing a slung load for safety and for control law design assistance were studied. A helicopter slung load model was developed and validated at first. Trajectory optimization methodology was adopted to obtain the optimal time histories of controls and states after the release to stabilize the helicopter. Optimization results of different objectives were compared, and the configuration of the objective function was determined by analyzing the results. The optimal control required after the release was summarized and the effects of slung load mass variations on results were investigated. According to the results of releasing the slung load at hover, the pilot should focus on the collective stick control and longitudinal stick control, while the lateral stick control and pedal displacement could be neglected. The heavier the slung load, the larger control amplitude was required for stabilization. © 2021, Editorial Department of Journal of Aerospace Power. All right reserved.
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页码：543 / 552
页数：9
相关论文
共 20 条
  • [11] CHEN J, SHI Z., Flight controller design of transport airdrop, Chinese Journal of Aeronautics, 24, 5, pp. 600-606, (2011)
  • [12] GASSAWAY B, STROPE K, CICOLANI L, Et al., Predictive capabilities of a UH-60 FLIGHTLAB<sup>Ⓡ</sup> model with an external sling load, American Helicopter Society 62nd Annual Forum, (2006)
  • [13] HOWLETT J J., UH-60A black hawk engineering simulation program: Volume Ⅰ mathematical model, (1981)
  • [14] CHEN R T N., A simplified rotor system mathematical model for piloted flight dynamics simulation, (1979)
  • [15] PITT D M, PETERS D A., Theoretical prediction of dynamic-inflow derivatives, Vertica, 5, 1, pp. 21-34, (1981)
  • [16] CICOLANI L S, SAHAI R, TUCKER G.E, Et al., Flight test identification and simulation of a UH-60A helicopter and slung load, (2001)
  • [17] BALLIN M G., Validation of a real-time engineering simulation of the UH-60A helicopter, (1987)
  • [18] MENG W, CHEN R., Study of helicopter autorotation landing following engine failure based on a six-degree-of-freedom rigid-body dynamic model, Chinese Journal of Aeronautics, 26, 6, pp. 1380-1388, (2013)
  • [19] YAN X, CHEN R., Augmented flight dynamics model for pilot workload evaluation in tilt-rotor aircraft optimal landing procedure after one engine failure, Chinese Journal of Aeronautics, 32, 1, pp. 92-103, (2019)
  • [20] BETTS J T., A survey of numerical methods for trajectory optimization, Journal of Guidance, Control, and Dynamics, 21, 2, pp. 193-207, (1998)
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