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To improve the development efficiency, RF guided HILS system is adopted to examine the missile system. To ensure the effectiveness of the simulation result, it is necessary to evaluate the reliability of the RF guided HILS system. Because of some factors such as measurement error and method error, evaluation index values tend to have uncertainty. In this context, the reliability evaluation index system...
A cooperative guidance law with time constraint for multiple missiles is designed for cooperative engagement. Missiles with various functions work together in combination, they play different roles in attack. A leader is selected to lead the others to complete the guidance task. The main idea of this scheme is to convert a guidance problem with time constraints to a nonlinear tracking problem via...
Three-dimensional terminal guidance law design problem of flight vehicle with terminal impact angle constraints is investigated in the paper. In order to improve the control performance of precision guided weapon in dive phase, a nonlinear guidance law with finite time convergence and terminal impact angle constrains is derived with non smooth control approach. Based on three-dimensional design model,...
A new algorithm based on iteration of the semi-major axis and graphic analysis, which is called Graphic Semi-major Axis Iteration Algorithm (GSAIM), is presented for Lambert problem. The key concept of the proposed algorithm is using numerical iterative or graphic analysis to obtain the intersection of the curves of the given transfer time and the Lambert equation, so that the required semi-major...
Focusing on the problem that the guidance system exists model uncertainty and the disturbance caused by target maneuver in the terminal guidance program, a finite time converge guidance law with taking account of disturbance and terminal impact angle constraint is designed in this paper based on the extended state observer(ESO). Firstly, a finite time converge guidance law with taking no account of...
This paper mainly focuses on the terminal guidance problem for reentry vehicles with terminal angle constraints. An optimal finite time convergent guidance law is proposed which includes guidance equations in both dive plane and turn plane. Finite time control is introduced into the designing process along with optimal guidance law to make the line-of-sight (LOS) angular rate deviation converge to...
A new guidance law with terminal trajectory angle constraint is designed for bank to turn flight vehicle, which aims at the fixed position ground target. The general form of guidance law with sight angle and sight angle velocity as feedback variables is presented, and the stability of it is proved via finite time convergent stability theory, which makes traditional optimal guidance as a specific example...
This paper presents a methodology of performance assessment for precision guided system. Hierarchical performance index system is established with a tree-like structure. Scheme of performance evaluation platform design is presented with four main parts, such as process management system, vehicle guidance simulation system, data processing system, and evaluation system. Based on the scheme, performance...
A new aerodynamic parameter fitting approach is proposed to avoid online aerodynamic parameter interpolation for advanced flight vehicle trajectory generation, guidance and control. Due to its ability to fit any nonlinear function and simple structure, BP neural network was chosen as the tool to fit the aerodynamic parameters which are the function of Mach number, angle of attack and other variables...
In the entry phase, aero-environment is extremely complex for Reusable Launch Vehicles (RLVs). This brings a huge challenge to design the entry guidance law for RLVs. In this paper, an entry trajectory planning method for RLVs is researched and the algorithm is improved to ensure the continuity and smoothness of the longitudinal reference trajectory. Meanwhile, the skipping of trajectory control is...
Maximum crossrange guidance with heat flux, overload factor and dynamic pressure constraints is required when lifting body reentry vehicle (LBRV) needs to travel long crossrange to reach the target point. A new maximum corssrange guidance method is presented for LBRV. The proposed guidance method converts maximum crossrange guidance into two subproblems, i.e. trajectory design subproblem and trajectory...
This paper proposed a novel layered VAR control strategy to solve VAR and voltage stability caused by wind farm integration. The strategy first calculated reactive power demand of the wind farm by deviation of reference voltage and measured voltage of control point. Then the calculated reactive power demand was distributed by equal power factor algorithm to single wind generator in the wind farm....
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