检索结果-南通市图书馆

Chinese Journal of Aeronautics 2023年第8期36卷 331-350页

作者： Tao CHAO Xintao wang songyan wang Ming YANG Control and Simulation Center Harbin Institute of TechnologyHarbin 150080China

A new type of guidance strategy, combining linear quadratic and norm-bounded game theory, is proposed for the scenario of an attacker against active defense aircraft in three-player engagement. The problem involves three players, an attacker, a defender and a target. The differential game theory and the solution of Hamiltonian equation are utilized to obtain the combined guidance strategy for each player with arbitrary-order dynamics. The game process is divided into4 phases, C1-C4, according to the switching time. The linear quadratic differential game guidance scheme is employed to reduce the fuel cost in the game parts of C1 and C3. The norm-bounded game guidance strategy is adopted to satisfy the constraint of control input in the game stages C2 and C4. Furthermore, zero-effort miss distance is introduced to meet the constraints of game space and defender’s killing radius in the guidance strategy, which guarantees that the attacker is able to avoid the interception of the defender and hit the target with lower fuel cost and maximum acceleration. And it is proved that the proposed guidance strategy satisfies the Nash equilibrium condition. Finally, the feasibility and superiority of combined guidance strategy are respectively illustrated by nonlinear numerical simulation and verified by comparing with linear quadratic and norm-bounded differential game guidance strategies.

关键词： Activedefense aircraft Acceleration Energy optimization Game theory Three-player engagement

Linear-quadratic and norm-bounded combined differential game guidance scheme with obstacle avoidance for attacking defended aircraft in three-player engagement

在线全文

学校读者我要写书评

暂无评论

Defence Technology（防务技术） 2024年第12期42卷 136-155页

作者： Xintao wang Ming Yang songyan wang Mingzhe Hou Tao Chao Control and Simulation Center Harbin Institute of TechnologyHarbin 150001China National Key Laboratory of Complex System Control and Intelligent Agent Cooperation Harbin 150001China Center for Control Theory and Guidance Technology Harbin Institute of TechnologyHarbin 150001China

A differential game guidance scheme with obstacle avoidance,based on the formulation of a combined linear quadratic and norm-bounded differential game,is designed for a three-player engagement scenario,which includes a pursuer,an interceptor,and an *** confrontation between the players is divided into four phases(P1-P4)by introducing the switching time,and proposing different guidance strategies according to the phase where the static obstacle is located:the linear quadratic game method is employed to devise the guidance scheme for the energy optimization when the obstacle is located in the P1 and P3 stages;the norm-bounded differential game guidance strategy is presented to satisfy the acceleration constraint under the circumstance that the obstacle is located in the P2 and P4 ***,the radii of the static obstacle and the interceptor are taken as the design parameters to derive the combined guidance strategy through the dead-zone function,which guarantees that the pursuer avoids the static obstacle,and the interceptor,and attacks the ***,the nonlinear numerical simulations verify the performance of the game guidance strategy.

关键词： Active defense aircraft Differential game theory Three-player confrontation Energy optimization Acceleration constraint Obstacle avoidance

Robust spline-line energy management guidance algorithm with multiple constraints and uncertainties for solid rocket ascending

在线全文

学校读者我要写书评

暂无评论

Chinese Journal of Aeronautics 2022年第2期35卷 214-234页

作者： songyan wang Fei LIU Tao CHAO Ming YANG Control and Simulation Center Harbin Institute of TechnologyHarbin 150001China

For the solid rocket with depletion shutdown system,effective energy management is significant to meet terminal constraints by exhausting excess *** traditional energy management algorithms cannot satisfy the altitude constraint and path constraints are not sufficiently *** velocity adjustment capability of these algorithms is limited and the uncertainties are not *** on the on-line programming of velocity capability curve,Spline-Line Energy Management(SLEM)guidance algorithm is *** introduces lateral maneuvers to further consume the available velocity on the basis of longitudinal energy *** expressing the constraints as several algebraic equations,the closed-loop guidance problem is converted to solving a system of nonlinear equations about the curve parameters in real *** advantage is that the altitude constraint can be satisfied *** overload and control variable change rate and amplitude constraints are also considered during the flight by constructing the feasible boundary of velocity capability *** improve the robustness,it is further extended by estimating the actual *** effectiveness and advantages of SLEM are demonstrated by simulations and comparisons with other energy management *** results show that the proposed approach can satisfy multiple constraints with high precision under the condition of uncertainties.

关键词： Ascent guidance Energy management Multiple constraints Solid rockets Uncertainty Velocity capability curve

Modified rolling guidance law for single moving mass controlled reentry vehicle against maneuvering target with impact angle constraints

在线全文

学校读者我要写书评

暂无评论

Chinese Journal of Aeronautics 2022年第6期35卷 226-239页

作者： Guanlin LI Ming YANG songyan wang Tao CHAO Control and Simulation Center Harbin Institute of TechnologyHarbin 150001China

This paper deals with the problem of guidance law design for the single moving mass controlled reentry vehicle when impact angle constraints and maneuvering target are taken into *** specifically,a modified rolling guidance law is proposed with the interactive virtual target and the landing point prediction ***,considering the fact that the roll channel can be controlled directly,the relative motion between the single moving mass controlled reentry vehicle and the target is described by the error angle between the relative velocity and the ***,a nonlinear error angle command is given to reduce the rotation *** satisfy impact angle constraints,an interactive virtual target is presented and the‘‘S”formed velocity of the virtual target is given to abate the error angle tracking difficulty at the final stage of the reentry ***,the landing point prediction strategy is employed and the motion variation trend is also taken into *** the maneuvering target is replaced with the predicted landing point,the error angle tracking difficulty caused by the target velocity decreases,which is helpful to meet impact angle constraints and improve guidance accuracy at the same ***,the finite-time rolling guidance law is proposed and proved via Lyapunov stability *** with the existing method,lower-speed rotation,smaller missing distance and less impact angle errors are obtained,which can be demonstrated by numerical simulations.

关键词： Reentry vehicles Guidance law Impact angle Maneuvering target Finite-time convergence

Integrated guidance and control design method based on finite-time state observer

在线全文

学校读者我要写书评

暂无评论

Journal of Systems Engineering and Electronics 2018年第6期29卷 1251-1262页

作者： MA Ping ZHANG Denghui wang songyan CHAO Tao Control and Simulation Center Harbin Institute of Technology

A composited integrated guidance and control(IGC) algorithm is presented to tackle the problem of the IGC design in the dive phase for the bank-to-turn(BTT) vehicle with the inaccuracy information of the line-of-sight(LOS) rate. For the sake of theoretical derivation, an IGC model in the pitch plane is established. The high-order finite-time state observer(FTSO), with the LOS angle as the single input, is employed to reconstruct the states of the system online. Besides, a composited IGC algorithm is presented via the fusion of back-stepping and dynamic inverse. Compared with the traditional IGC algorithm, the proposed composited IGC method can attenuate effectively the design conservation of the flight control system, while the LOS rate is mixed with noise. Extensive experiments have been performed to demonstrate that the proposed approach is globally finite-time stable and strongly robust against parameter uncertainty.

关键词： integrated guidance and control(IGC) finite-time state observer(FTSO) back-to-turn(BTT) vehicle composited control

High-precision shape approximation low-thrust trajectory optimization method satisfying bi-objective index

在线全文

学校读者我要写书评

暂无评论

Chinese Journal of Aeronautics 2022年第1期35卷 436-457页

作者： Ruiye JIANG Ming YANG songyan wang Tao CHAO Rajan SHANKARAN Control and Simulation Center Harbin Institute of TechnologyHarbin 150080China Department of Computing Macquarie UniversitySydneyNSW 2109Australia

The shape approximation method has been proven to be rapid and practicable in resolving low-thrust trajectory;however,it still faces the challenges of large deviation from the optimal solution and inability to satisfy the specific flight time and fuel mass *** this paper,a modified shape approximation low-thrust model is presented,and a novel constrained optimization algorithm is developed to solve this *** proposed method aims at settling the bi-objective optimization orbit involving the twin objectives of minimum flight time and low fuel consumption and enhancing the accuracy of optimized *** particular,a transformed high-order polynomial model based on finite Fourier series is proposed,which can be characterized as a multi-constraint optimization ***,a novel optimization algorithm is specifically developed to optimize the large-scale multi-constraint dynamical equations of shape *** key performance indicators of the index include minimum flight time,low fuel consumption and bi-objective optimization of the *** results prove that this approach possesses both the high precision achievable by numerical methods and low computational complexity offered by shape approximation ***,the Pareto front of the fuel-time bi-objective optimization orbit is firstly introduced to analyze an intact optimal solution ***,we have demonstrated that our proposed approach is appropriate to generate the preliminary orbit for pseudo-spectral method.

关键词： Constrained optimization Intelligent optimization Low-thrust trajectory Multi-objective optimization Shape approximation method

Research on Credibility Evaluation for Radio Frequency Guided Hardware-In-the-Loop Simulation System 36

在线全文

学校读者我要写书评

暂无评论

Research on Credibility Evaluation for Radio Frequency Guide...

含大规模风电系统的非AGC与AGC机组高峰协调控制策略

第36届中国控制会议

作者： Yuxiao wang Tao Chao Chaolei wang songyan wang Harbin Institute of Technology Science and Technology on Special System Simulation Laboratory Beijing Simulation Center

ISBN: (纸本)9781538629185

To ensure the effectiveness of the RF（Radio Frequency） guided HILS（Hardware-In-the-Loop Simulation） system,the credibility evaluation was *** present,most of the methods were applied in the case of the simulation system input being consistent with the real system input,which is difficult to achieve in some subsystem of the RF guided HILS *** this paper,the relative complete system reliability evaluation index system was *** were classified,for different categories of subsystem,corresponding reliability assessment methods were *** particular,reliability evaluation methods based on performance level were put forward,when certain subsystems cannot be evaluated by consistency analysis methods.A simple example was given to show the evaluation process.

关键词： Radio Frequency Guided Hardware-In-the-Loop Simulation Credibility Evaluation Index System Performance Index

来源： cnki会议评论

在线全文

cnki会议

学校读者我要写书评

暂无评论

中国电机工程学报 2013年第7期33卷 156-163,6页

作者：王松岩于继来哈尔滨工业大学电气工程及自动化学院黑龙江省哈尔滨市150001

大规模风电接入使得电网在高峰运行时段可能面临较大的调峰与调频压力。提出了一种高峰运行时段非自动发电控制(automatic generation control,AGC)机组、按期望运行点调整(base load off-regulated,BLO)型AGC和按区域控制偏差(area con... 详细信息

大规模风电接入使得电网在高峰运行时段可能面临较大的调峰与调频压力。提出了一种高峰运行时段非自动发电控制(automatic generation control,AGC)机组、按期望运行点调整(base load off-regulated,BLO)型AGC和按区域控制偏差(area control error,ACE)自动调节(base load regulated,BLR)型AGC三类机组的协调控制策略。首先根据BLO和BLR型AGC机组在每个预调度时段末期机组总体调节容量情况,判断是否启动控制策略;若策略启动后,BLR型AGC机组根据负荷与风电功率预报偏差概率分布信息,整定其在下一个在线调度时段的基点功率值,使其具有合理概率意义上的正负调节能力;非AGC机组一般按经济计划点运行,在BLO型AGC机组正备用匮乏,或系统频率出现较大偏差时适度调整非AGC机组的出力,以增补BLO型AGC机组的正备用;BLO型AGC机组在每个在线调度时段及时恢复BLR型AGC机组的调节能力,在整个控制策略中起承上启下的作用。算例结果表明,该协调控制策略正确可行。

关键词：风电自动发电控制高峰调频协调控制

在线全文

学校读者我要写书评

暂无评论

短时风速概率分布的混合威布尔逼近方法

电力系统自动化 2010年第6期34卷 89-93页

作者：王松岩于继来哈尔滨工业大学电气工程及自动化学院黑龙江省哈尔滨市150001

风速概率分布特性是决定风电场功率输出的重要因素。常用的两参数威布尔函数在拟合较长周期风速时效果很好,然而在研究短周期或特殊时段风速概率分布后发现,其分布规律常为双峰或多峰分布,很难用传统方法准确逼近。对此,提出一种混合威... 详细信息

风速概率分布特性是决定风电场功率输出的重要因素。常用的两参数威布尔函数在拟合较长周期风速时效果很好,然而在研究短周期或特殊时段风速概率分布后发现,其分布规律常为双峰或多峰分布,很难用传统方法准确逼近。对此,提出一种混合威布尔函数逼近特殊时段风速分布的方法,构造极大似然函数逼近风速实际分布并采用数论布点方法获得待求参数。结果显示,七参数混合威布尔函数显著提高了双峰型风速概率密度分布逼近的精度,而极大似然估计的加权处理,提高了关注风速段的拟合优度,达到了降低逼近误差的目的。

关键词：风速概率统计混合威布尔分布加权极大似然估计数论布点方法

Optimization method of multi-stages launch vehicle trajectory based on segmental Chebyshev pseudo spectral method

在线全文

学校读者我要写书评

暂无评论

Optimization method of multi-stages launch vehicle trajector...