| 引用本文: | 程杨,吕忠,孙志鸿,董梁,余莉.翼伞系统两体模型雀降操纵高度的优化[J].哈尔滨工业大学学报,2024,56(8):34.DOI:10.11918/202308068 |
| CHENG Yang,LV Zhong,SUN Zhihong,DONG Liang,YU Li.Optimization of flare landing maneuver altitude for two-body model of parafoil system[J].Journal of Harbin Institute of Technology,2024,56(8):34.DOI:10.11918/202308068 |
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| 翼伞系统两体模型雀降操纵高度的优化 |
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程杨1,吕忠3,孙志鸿1,董梁1,余莉1,2
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(1.飞行器环境控制与生命保障工业和信息化部重点实验室(南京航空航天大学),南京 210016;2. 南京航空航天大学 航空学院,南京 210016; 3. 航空工业宏光空降装备有限公司,南京 210022)
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| 摘要: |
| 为减小翼伞系统的着陆速度,提高载荷的着陆安全性,提出了最优雀降高度确定方法,并完成相对雀降高度和着陆速度影响因素及计算模型研究。首先建立了翼伞-载荷系统两体九自由度动力学模型和雀降操纵耦合气动特性模型,更真实地模拟了翼伞-载荷两体之间操纵情况下的运动性能,研究了雀降操纵下翼伞系统的速度、姿态变化,数值结果和文献规律一致,滑翔比最大误差为8.20%。其次,基于该两体模型,以最小垂直着陆速度为优化目标,采用时间二分法确定最优雀降高度,分析了雀降操纵时机对着陆速度的影响。然后,开展了不同初始工况、翼载荷、着陆海拔高度、安装角下翼伞系统最优雀降实施的仿真计算,并采用最小二乘法完成了相对雀降高度、着陆速度的公式拟合。结果表明:初始参数对相对雀降高度几乎没有影响；随着翼载荷及着陆海拔高度的升高,着陆速度及相对雀降实施高度增加；安装角对着陆速度影响不大,但安装角的增大会引起雀降实施高度增加；所提出的相对雀降高度和着陆速度计算模型与仿真结果较为符合,最大误差小于4.00%,表明该计算模型有良好的适用性。 |
| 关键词: 翼伞 9自由度模型 雀降操纵 雀降高度 着陆速度 |
| DOI：10.11918/202308068 |
| 分类号:V211 |
| 文献标识码:A |
| 基金项目:国家自然科学基金(11972192) |
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| Optimization of flare landing maneuver altitude for two-body model of parafoil system |
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CHENG Yang1,LV Zhong3,SUN Zhihong1,DONG Liang1,YU Li1,2
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(1.Key Laboratory of Aircraft Environment Control and Life Support,MIIT (Nanjing University of Aeronautics and Astronautics),Nanjing 210016,China; 2. College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics, Nanjing 210016,China; 3. AVIC Hongguang Airborne Equipment Co., Ltd., Nanjing 210022,China)
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| Abstract: |
| To decrease landing velocity of parafoil system and improve landing safety of payload, a method for determining the optimal flare landing altitude was proposed, and a study on the influencing factors and calculation models of relative flare landing altitude and landing velocity was completed. Firstly, a two-body nine-degree-of-freedom(DOF) dynamic model of the parafoil system and a coupled aerodynamic characteristic model of flare landing control were established, providing a more realistic simulation of the motion performance of the parafoil system under control between two bodies. The velocity and attitude changes of the parafoil system under flare landing control were studied, and the numerical results were consistent with the results in the literature, with a maximum error of 8.20% in glide ratio. Secondly, based on this model, with the minimum vertical landing velocity as the optimization objective, the optimal landing altitude was determined using the time dichotomy method, and the impact of flare maneuver timing on the landing velocity was analyzed. Then, simulation calculations were conducted on the optimal landing altitude under different initial conditions, wing load, landing altitude, and attack angle. The formula fitting of relative flare altitude and landing velocity was completed by the least squares method. It was found that the initial parameters have a minimal effect on the optimal landing altitude. As the wing load and landing altitude increase, the landing velocity and relative landing altitude also increase. The attack angle has a minor impact on the landing velocity, but an increase in the attack angle leads to an increase in the height of flare landing. The relative flare altitude and landing velocity calculation model proposed in this paper is in goof agreement with the numerical calculation results, with a maximum error less than 4.00%, indicating that the calculation model has good applicability. |
| Key words: parafoil 9DOF model flare maneuver flare altitude landing velocity |
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