An Improvement in Three-Dimensional Pure Proportional Navigation Guidance

2021 ◽  
pp. 1-1
Author(s):  
Hyo-Sang Shin ◽  
Ke-Bo Li
Keyword(s):  
Three Dimensional ◽  
Proportional Navigation ◽  
Proportional Navigation Guidance

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.

A Singular Perturbation Based Midcourse Guidance Law for Realistic Air-to-Air Engagement

2016 ◽  
Vol 67 (1) ◽  
pp. 108 ◽  
Author(s):  
M Manickavasagam ◽  
A.K. Sarkar ◽  
V Vaithiyanathan
Keyword(s):  
Singular Perturbation ◽  
Degrees Of Freedom ◽  
Three Dimensional ◽  
Terminal Phase ◽  
Proportional Navigation ◽  
Guidance Law ◽  
Kinetic Information ◽  
Monte Carlo Studies ◽  
Midcourse Guidance ◽  
Proportional Navigation Guidance

In this study, a singular perturbation based technique is used for synthesis and analysis of a near optimal midcourse guidance law for realistic air-to-air engagement. After designing the proposed midcourse guidance law using three dimensional point mass formulation it has been validated through detailed realistic six degrees of freedom simulation. During terminal phase only proportional navigation guidance have been used. The calculation of optimal altitude in present guidance law has been carried out using Newton’s method, which needs generally one iteration for convergence and suitable for real-time implementation. Extended Kalman filter based estimator has been used for obtaining evader kinetic information from both radar and seeker noisy measurements available during midcourse and terminal guidance. The data link look angle constraint due to hardware limitation which affects the performance of midcourse guidance has also been incorporated in guidance law design. Robustness of complete simulation has been carried out through Monte Carlo studies. Extension of launch boundary due to singular perturbation over proportional navigation guidance at a given altitude for a typical engagement has also been reported.<br />

Co-operative 3D salvo attack of multiple missiles under switching topologies subject to time-varying communication delays

2019 ◽  
Vol 123 (1262) ◽  
pp. 464-483
Author(s):  
X.L. Ai ◽  
L.L. Wang ◽  
Y.C. Shen
Keyword(s):  
Initial Conditions ◽  
Sufficient Conditions ◽  
Time Varying ◽  
Communication Delays ◽  
Proportional Navigation ◽  
Stationary Target ◽  
Switching Topologies ◽  
Guidance Law ◽  
Multiple Missiles ◽  
Proportional Navigation Guidance

ABSTRACTThis study focuses on the co-operative salvo attack problem of multiple missiles against a stationary target under jointly connected switching topologies subject to time-varying communication delays. By carefully exploring certain features of the typical pure proportional navigation guidance law, a two-stage distributed guidance scheme is proposed without any information on time-to-go in this study to realise the simultaneous attack of multiple missiles. In the first guidance stage, a co-operative guidance law is proposed using local neighbouring communications only to achieve consensus on range-to-go and heading error to provide favourable initial conditions for the latter phase, in which switching topologies and time-varying communication delays are taken into account when obtaining sufficient conditions of consensus in terms of linear matrix inequalities. Then, missiles disconnect from each other and are guided individually by the typical pure proportional navigation guidance law with the same navigation gain to realise salvo attack in the second guidance phase. Finally, numerical simulations are carried out to clearly validate the theoretical results.

scholarly journals Nonsingular PNG-Based Impact Time Control Guidance with Lower Dependence on Time-to-Go Estimate

2019 ◽  
Vol 2019 ◽  
pp. 1-14
Author(s):  
Sijiang Chang ◽  
Shengfu Chen
Keyword(s):  
Numerical Simulation ◽  
Theoretical Analysis ◽  
Research Literature ◽  
Proportional Navigation ◽  
Impact Time ◽  
Time Control ◽  
Practical Engineering ◽  
Adjustable Range ◽  
Natural Characteristics ◽  
Proportional Navigation Guidance

In a bid to take advantage of natural characteristics of the proportional navigation guidance (PNG) in practical engineering, the PNG-based impact time control guidance (ITCG) continues to be a popular alternative for achieving the desired impact time of a missile. For most such ITCG, the performance is dependent on the accuracy of the time-to-go estimation. Along the lines of the development of PNG-based ITCG in earlier studies, a nonsingular ITCG is proposed on the basis of nonlinear formulations. It is demonstrated that, by theoretical analysis and numerical simulation, this proposed ITCG is shown to be advantageous in certain circumstances. By deriving a novel additional acceleration command, the proposed law is of lower dependence on time-to-go estimate and is capable of eliminating some singularities, leading to wider adjustable range of the desired impact time and better adaptability to more conditions. This research is expected to be supplementary to those presented in the current research literature.

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