TIME-TO-GO

作品数：8被引量：28H指数：3
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相关期刊：《Journal of Systems Engineering and Electronics》《Journal of Beijing Institute of Technology》《Journal of Harbin Institute of Technology(New Series)》《Chinese Journal of Aeronautics》更多>>
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Multiple-stage spatial-temporal cooperative guidance without time-to-go estimation被引量：1
《Chinese Journal of Aeronautics》2024年第9期399-416,共18页Chunyan WANG Weilin WANG Wei DONG Jianan WANG Fang DENG 
the National Science Fund for Distinguished Young Scholars of China (No.62025301);the National Natural Science Foundation of China (Nos.62273043 and 62373055);the China National Postdoctoral Program for Innovative Talents (No.BX20230461);the China Postdoctoral Science Foundation (No.2023M740249)。
This paper investigates the spatial-temporal cooperative guidance problem for multiple flight vehicles without relying on time-to-go information.First,a two-stage cooperative guidance strategy,namely the cooperative g...
关键词：Cooperative guidance Guided missiles Impact time consensus Impact angle constraint Spatial-temporal cooperative guidance 
Efficient and accurate online estimation algorithm for zero-effort-miss and time-to-go based on data driven method被引量：1
《Chinese Journal of Aeronautics》2019年第10期2311-2323,共13页Hongxia LI Huijie LI Yuanli CAI 
supported by the National Natural Science Foundation of China(No.71571190)
This paper introduces a novel and efficient algorithm for online estimation of zero-effortmiss and time-to-go based on data driven method.Only missile-target separations are utilized to construct the estimation models...
关键词：Data driven Missile-target SEPARATIONS Online estimation TIME-TO-GO Zero-effort-miss 
Satellite proximate interception vector guidance based on differential games被引量：10
《Chinese Journal of Aeronautics》2018年第6期1352-1361,共10页Dong YE Mingming SHI Zhaowei SUN 
co-supported by the National Natural Science Foundation of China (Nos.61603115,91438202 and91638301);China Postdoctoral Science Foundation (No.2015M81455);the Open Fund of National Defense Key Discipline Laboratory of Micro-Spacecraft Technology of China (No.HIT.KLOF.MST.201601);the Heilongjiang Postdoctoral Fund of China (No.LBH-Z15085)
This paper studies the proximate satellite interception guidance strategies where both the interceptor and target can perform orbital maneuvers with magnitude limited thrusts. This problem is regarded as a pursuit-eva...
关键词：Differential games Saddle solution Satellite interception Time-to-go estimation Zero effort miss trajectory 
Sliding mode control and Lyapunov based guidance law with impact time constraints被引量：5
《Journal of Systems Engineering and Electronics》2017年第6期1186-1192,共7页Xiaojian Zhang Mingyong Liu Yang Li 
supported by the National Natural Science Foundation of China(51379176;51679201)
This paper analyses the issue of impact time control of super-cavitation weapons impact fixed targets which mainly refer to the ships or submarines who lost power, but still have combat capability. Control over impact...
关键词：Lyapunov stability sliding mode control impact time salvo attack TIME-TO-GO guidance law 
Extended trajectory shaping guidance law considering a first-order autopilot lag
《Journal of Beijing Institute of Technology》2015年第3期291-297,共7页王辉 王江 程振轩 
Supported by the National Natural Science Foundation of China(61172182)
To satisfy the terminal position and impact angel constraints,an optimal guidance problem was discussed for homing missiles. For a stationary or a slowly moving target on the ground,an extended trajectory shaping guid...
关键词：extended trajectory shaping guidance law time-to-go first-order autopilot guidance performance 
Homing Guidance Law with Falling Angle and Flying Time Control被引量：3
《Journal of Harbin Institute of Technology(New Series)》2014年第1期55-61,共7页Peng-Yun Liu Rui-Sheng Sun Wei-Ming Li 
In this paper,a new homing guidance method is used to control the flying time and falling angle for guided missiles. Through this approach,it finds the approximate solution to the quadratic equation of time-togo,which...
关键词：homing guidance law falling angle flying time rocket-propelled torpedo TIME-TO-GO 
Time-to-go weighted optimal trajectory shaping guidance law被引量：7
《Journal of Beijing Institute of Technology》2011年第3期317-323,共7页王辉 林德福 程振轩 
For maneuvering target, the optimal trajectory shaping guidance law which can simultaneously achieve the designed specifications on miss distance and final impact angle was deduced using optimal control theory based o...
关键词：trajectory shaping guidance optimal control TIME-TO-GO close-form solution 
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