面对称运载火箭优势面滚转迎风技术
2024,46(3):88-97
赵永志
中国运载火箭技术研究院 北京宇航系统工程研究所, 北京 100076;
余梦伦智能火箭创新实验室, 北京 100076，zhaoyzh_01@139.com
张普卓
中国运载火箭技术研究院 北京宇航系统工程研究所, 北京 100076;
余梦伦智能火箭创新实验室, 北京 100076
杜昊昱
中国运载火箭技术研究院 北京宇航系统工程研究所, 北京 100076;
余梦伦智能火箭创新实验室, 北京 100076
唐攀
中国运载火箭技术研究院 北京宇航系统工程研究所, 北京 100076;
余梦伦智能火箭创新实验室, 北京 100076
王紫扬
中国运载火箭技术研究院 北京宇航系统工程研究所, 北京 100076;
余梦伦智能火箭创新实验室, 北京 100076
中国运载火箭技术研究院 北京宇航系统工程研究所, 北京 100076;
余梦伦智能火箭创新实验室, 北京 100076，zhaoyzh_01@139.com
张普卓
中国运载火箭技术研究院 北京宇航系统工程研究所, 北京 100076;
余梦伦智能火箭创新实验室, 北京 100076
杜昊昱
中国运载火箭技术研究院 北京宇航系统工程研究所, 北京 100076;
余梦伦智能火箭创新实验室, 北京 100076
唐攀
中国运载火箭技术研究院 北京宇航系统工程研究所, 北京 100076;
余梦伦智能火箭创新实验室, 北京 100076
王紫扬
中国运载火箭技术研究院 北京宇航系统工程研究所, 北京 100076;
余梦伦智能火箭创新实验室, 北京 100076
摘要：
针对面对称运载火箭飞行中俯仰、偏航通道控制力不匹配问题,提出通过姿态滚转控制调整迎风面以减小最大飞行摆角的控制技术,称为滚转迎风(bank-to-wind, BTW)技术。重点研究了BTW控制的离线法,推导了BTW控制滚动程序角理论值的解析解,证明了该理论值的偏差与飞行姿态偏差是同阶小量。提出带权重的傅里叶级数拟合算法,对滚动程序角进行修正,以符合工程应用的可行性。开展六自由度飞行动力学仿真,分析BTW控制对控制力、飞行气动载荷和滚动程序角跟踪品质的影响,验证BTW控制的有效性。比对不同拟合基频的仿真结果得出结论:拟合频率过高将影响控制品质,从工程应用角度看滚动程序角的“光滑性”比“拟合性”更重要。
针对面对称运载火箭飞行中俯仰、偏航通道控制力不匹配问题,提出通过姿态滚转控制调整迎风面以减小最大飞行摆角的控制技术,称为滚转迎风(bank-to-wind, BTW)技术。重点研究了BTW控制的离线法,推导了BTW控制滚动程序角理论值的解析解,证明了该理论值的偏差与飞行姿态偏差是同阶小量。提出带权重的傅里叶级数拟合算法,对滚动程序角进行修正,以符合工程应用的可行性。开展六自由度飞行动力学仿真,分析BTW控制对控制力、飞行气动载荷和滚动程序角跟踪品质的影响,验证BTW控制的有效性。比对不同拟合基频的仿真结果得出结论:拟合频率过高将影响控制品质,从工程应用角度看滚动程序角的“光滑性”比“拟合性”更重要。
基金项目：
国家自然科学基金资助项目(61903350)
国家自然科学基金资助项目(61903350)
Preferred plane bank-to-wind technology for plane-symmetric launch vehicle
ZHAO Yongzhi
Beijing Institute of Astronautical Systems Engineering, China Academy of Launch Vehicle Technology, Beijing 100076, China;
YU Menglun Intelligent Rocket Innovation Laboratory, Beijing 100076, China,zhaoyzh_01@139.com
ZHANG Puzhuo
Beijing Institute of Astronautical Systems Engineering, China Academy of Launch Vehicle Technology, Beijing 100076, China;
YU Menglun Intelligent Rocket Innovation Laboratory, Beijing 100076, China
DU Haoyu
Beijing Institute of Astronautical Systems Engineering, China Academy of Launch Vehicle Technology, Beijing 100076, China;
YU Menglun Intelligent Rocket Innovation Laboratory, Beijing 100076, China
TANG Pan
Beijing Institute of Astronautical Systems Engineering, China Academy of Launch Vehicle Technology, Beijing 100076, China;
YU Menglun Intelligent Rocket Innovation Laboratory, Beijing 100076, China
WANG Ziyang
Beijing Institute of Astronautical Systems Engineering, China Academy of Launch Vehicle Technology, Beijing 100076, China;
YU Menglun Intelligent Rocket Innovation Laboratory, Beijing 100076, China
Beijing Institute of Astronautical Systems Engineering, China Academy of Launch Vehicle Technology, Beijing 100076, China;
YU Menglun Intelligent Rocket Innovation Laboratory, Beijing 100076, China,zhaoyzh_01@139.com
ZHANG Puzhuo
Beijing Institute of Astronautical Systems Engineering, China Academy of Launch Vehicle Technology, Beijing 100076, China;
YU Menglun Intelligent Rocket Innovation Laboratory, Beijing 100076, China
DU Haoyu
Beijing Institute of Astronautical Systems Engineering, China Academy of Launch Vehicle Technology, Beijing 100076, China;
YU Menglun Intelligent Rocket Innovation Laboratory, Beijing 100076, China
TANG Pan
Beijing Institute of Astronautical Systems Engineering, China Academy of Launch Vehicle Technology, Beijing 100076, China;
YU Menglun Intelligent Rocket Innovation Laboratory, Beijing 100076, China
WANG Ziyang
Beijing Institute of Astronautical Systems Engineering, China Academy of Launch Vehicle Technology, Beijing 100076, China;
YU Menglun Intelligent Rocket Innovation Laboratory, Beijing 100076, China
Abstract：
The control force can be mismatched on pitch and yaw plane for plane-symmetric launch vehicle, a control method named BTW(bank-to-wind) was proposed to solve the problem, which adjusts the windward side according to rolling program angle to decrease the maximum engine deflection. The off-line method of BTW control was studied, the analytical solution of the theoretical value of BTW control rolling program angle was derived, and it was proved that the deviation of the theoretical value is the same order as the flight attitude deviation. A fitting algorithm based on Fourier series with weights was proposed to modify the rolling program angle, ensuring engineering feasibility. Six-degree-of-freedom flight dynamics simulations were conducted to analyze the impact of BTW control on control forces, aerodynamic loads, and the tracking quality of the program angle, thereby verifying the effectiveness of BTW control. By comparing the simulation results of different fitting base frequencies, it is concluded that excessively high fitting frequencies can affect control quality. From an engineering perspective, the "smoothness" of the rolling program angle is more important than its "fitting accuracy".
The control force can be mismatched on pitch and yaw plane for plane-symmetric launch vehicle, a control method named BTW(bank-to-wind) was proposed to solve the problem, which adjusts the windward side according to rolling program angle to decrease the maximum engine deflection. The off-line method of BTW control was studied, the analytical solution of the theoretical value of BTW control rolling program angle was derived, and it was proved that the deviation of the theoretical value is the same order as the flight attitude deviation. A fitting algorithm based on Fourier series with weights was proposed to modify the rolling program angle, ensuring engineering feasibility. Six-degree-of-freedom flight dynamics simulations were conducted to analyze the impact of BTW control on control forces, aerodynamic loads, and the tracking quality of the program angle, thereby verifying the effectiveness of BTW control. By comparing the simulation results of different fitting base frequencies, it is concluded that excessively high fitting frequencies can affect control quality. From an engineering perspective, the "smoothness" of the rolling program angle is more important than its "fitting accuracy".
收稿日期：
2022-03-02
2022-03-02
