Modified three‐dimensional true proportional navigation and its inverse optimal form

2021 ◽  
Author(s):  
Fei Liao ◽  
Sheng Zhang
Keyword(s):  
Three Dimensional ◽  
Proportional Navigation ◽  
Optimal Form

A generalized design method for three-dimensional guidance laws

2016 ◽  
Vol 231 (1) ◽  
pp. 47-60 ◽  
Author(s):  
Sheng Sun ◽  
Di Zhou ◽  
Jingyang Zhou ◽  
Kok Lay Teo
Keyword(s):  
Lyapunov Function ◽  
Sliding Mode ◽  
Three Dimensional ◽  
Line Of Sight ◽  
Generalized Function ◽  
Proportional Navigation ◽  
Guidance Law ◽  
Target Acceleration ◽  
Guidance Laws ◽  
Proportional Navigation Guidance

The true proportional navigation guidance law, the augmented proportional navigation guidance law, or the adaptive sliding-mode guidance law, is designed based on the planar target-to-missile relative motion dynamics. By a proper construction of a nonlinear Lyapunov function for the line-of-sight angular rates in the three-dimensional guidance dynamics, it is shown that the three guidance laws mentioned above are able to ensure the asymptotic convergence of the angular rates as they are directly applied to the three-dimensional guidance environment. Furthermore, considering the missile autopilot dynamics as a first-order lag, we design three-dimensional nonlinear guidance laws by using the backstepping technique for three cases: (1) the target does not maneuver; (2) the information of target acceleration can be acquired; and (3) the target acceleration is not available but its bound is known a priori. In the first step of the backstepping design of the control law, there is no need to cancel the nonlinear coupling terms in the three-dimensional guidance dynamics in such way that the final expressions of the proposed guidance laws are significantly simplified. Thus, the proposed nonlinear Lyapunov function for the line-of-sight angular rates is a generalized function for designing three-dimensional guidance laws. Simulation results of a missile interception mission show that the proposed guidance laws are highly effective.

Non-linear missile guidance synthesis using control Lyapunov functions

2005 ◽  
Vol 219 (2) ◽  
pp. 77-87 ◽  
Author(s):  
P Gurfil
Keyword(s):  
Lyapunov Functions ◽  
Three Dimensional ◽  
Performance Measure ◽  
Line Of Sight ◽  
Missile Guidance ◽  
Proportional Navigation ◽  
Guidance Law ◽  
Non Linear ◽  
Non Linear Systems ◽  
Fixed Line

This paper derives a new non-linear guidance law aimed at interception of highly manoeuvring targets. The guidance law is developed based on the theory of control Lyapunov functions (CLFs), a methodology for universal stabilization of non-linear systems which is also inverse optimal with respect to some performance measure. The three-dimensional guidance dynamics are formulated in a fixed-line-of-sight coordinate system, yielding matching between the target and missile accelerations. Closed-form expressions for the CLF guidance commands are given. Simulation shows that the new guidance scheme significantly outperforms augmented proportional navigation in short-range engagements.

scholarly journals Impact Time Control Cooperative Guidance Law Design Based on Modified Proportional Navigation

Aerospace ◽  
2021 ◽  
Vol 8 (8) ◽  
pp. 231
Author(s):  
Zhanyuan Jiang ◽  
Jianquan Ge ◽  
Qiangqiang Xu ◽  
Tao Yang
Keyword(s):  
Constant Velocity ◽  
Three Dimensional ◽  
Estimation Method ◽  
Time Varying ◽  
Two Dimensional ◽  
Proportional Navigation ◽  
Impact Time ◽  
Time Control ◽  
Guidance Law ◽  
Cooperative Guidance

The paper proposes a two-dimensional impact time control cooperative guidance law under constant velocity and a three-dimensional impact time control cooperative guidance law under time-varying velocity, which can both improve the penetration ability and combat effectiveness of multi-missile systems and adapt to the complex and variable future warfare. First, a more accurate time-to-go estimation method is proposed, and based on which a modified proportional navigational guidance (MPNG) law with impact time constraint is designed in this paper, which is also effective when the initial leading angle is zero. Second, adopting cooperative guidance architecture with centralized coordination, using the MPNG law as the local guidance, and the desired impact time as the coordination variables, a two-dimensional impact time control cooperative guidance law under constant velocity is designed. Finally, a method of solving the expression of velocity is derived, and the analytic function of velocity with respect to time is given, a three-dimensional impact time control cooperative guidance law under time-varying velocity based on desired impact time is designed. Numerical simulation results verify the feasibility and applicability of the methods.

Active homing performance enhancement with multiple model radome slope estimation

2005 ◽  
Vol 219 (3) ◽  
pp. 217-224 ◽  
Author(s):  
T L Song ◽  
D G Lee ◽  
S J Shin
Keyword(s):  
Performance Enhancement ◽  
Three Dimensional ◽  
Interacting Multiple Model ◽  
Multiple Model ◽  
Proportional Navigation ◽  
Filter Structure ◽  
Homing Performance ◽  
Scenarios Simulation ◽  
Slope Estimation ◽  
Miss Distance

In this paper, a new filter structure with the interacting multiple model (IMM) algorithm for estimating both the radome slope and target states is suggested to reduce the radome induced miss distance effectively in active homing engagements of a surface-to-air missile. The proposed filter in conjunction with proportional navigation guidance is tested by a series of simulation runs in three-dimensional engagement scenarios. Simulation results show that the proposed filter structure stabilizes the missile system and gives allowable miss distance in case of large incident lag that may cause system instability in the presence of the radome slope.

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