An Ideal Proportional Navigation Guidance system for moving object interception-robotic experiments

2002 ◽  
Author(s):  
J.M. Borg ◽  
M. Mehrandezh ◽  
R.G. Fenton ◽  
B. Benhabib
Keyword(s):  
Moving Object ◽  
Guidance System ◽  
Proportional Navigation ◽  
Proportional Navigation Guidance

scholarly journals Influence of Seeker Disturbance Rejection and Radome Error on the Lyapunov Stability of Guidance Systems

2018 ◽  
Vol 2018 ◽  
pp. 1-9
Author(s):  
Kaiwei Chen ◽  
Qunli Xia ◽  
Xiao Du ◽  
Yuemin Yao
Keyword(s):  
Lyapunov Stability ◽  
Disturbance Rejection ◽  
Rejection Rate ◽  
Guidance System ◽  
Time Varying ◽  
Proportional Navigation ◽  
Mathematical Simulations ◽  
Guidance Systems ◽  
The Stability ◽  
Proportional Navigation Guidance

This study analyzes the effects of disturbance rejection and radome error on the stability of guidance systems. First, disturbance rejection rate transfer function (DRRTF) models are established. Second, the Lyapunov stability of a proportional navigation guidance system is proposed. The passivity theorems are introduced for the analysis of the Lyapunov stability of the nonlinear time-varying system. Finally, the influence of the different DRRTF models on the stability of the guidance system is analyzed by mathematical simulations. The simulation results indicate that the stable boundary of the guidance system varies and its tolerance to disturbance differs significantly for various disturbance torque types and radome slope.

scholarly journals Observability-enhanced proportional navigation guidance with bearings-only measurements

1999 ◽  
Vol 40 (4) ◽  
pp. 497-512 ◽  
Author(s):  
Mingyan Li ◽  
Cheng-Chew Lim
Keyword(s):  
Closed Form ◽  
Navigation System ◽  
Low Cost ◽  
Guidance System ◽  
Control Law ◽  
Proportional Navigation ◽  
Closed Form Solutions ◽  
Homing Missiles ◽  
Proportional Navigation Guidance

AbstractWe analyse the performance of the additive observable proportional navigation guidance system, which is well-suited for low-cost homing missiles with bearings-only measurements. Closed-form solutions are derived for both manoeuvring and non-manoeuvring targets. Guidelines on how to select the navigation constants of the control law are presented. We show that the additive observable proportional navigation guidance system can cover a larger capture area than can a conventional proportional navigation system.

scholarly journals Analysis of the Influence of Trace Point Step-Jump Behavior

2020 ◽  
Vol 2020 ◽  
pp. 1-14
Author(s):  
Yao Yang ◽  
Yang Xu ◽  
Pei Wang
Keyword(s):  
Recovery Time ◽  
Sliding Mode ◽  
Initial Step ◽  
Guidance System ◽  
Adjoint Model ◽  
Proportional Navigation ◽  
Guidance Law ◽  
Optimal Guidance ◽  
Fundamental Reason ◽  
Terminal Guidance

To explore the influence of the trace point step-jump behavior on a terminal guidance system, an analysis is performed from the line-of-sight rate (LOS rate) and guidance accuracy views for designing an anti-step-jump guidance law. First, the linear terminal guidance model under the trace point jump circumstance is constructed, and then the fundamental reason for the miss distance is investigated by deriving the upper bound of the LOS rate at the initial step-jump moment. Following this, the novel proposed analytical differential adjoint model is established with the adjoint method, and its validity is demonstrated comparing with the numeric derivative model. Based on the adjoint model, the effects of the ratio coefficient, the time constant, and the jump amplitude on the guidance accuracy are explored. Finally, a novel anti-step-jump guidance law is designed to shorten the recovery time of the overload. The simulations have shown that the faster recovery time and higher accuracy are achieved in comparison with the proportional navigation guidance, optimal guidance, and adaptive sliding mode guidance.

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.

Investigation into Air Interception Guidance Algorithms for Autonomous Aerial Hard Docking of Dissimilar Platforms

2014 ◽  
Vol 629 ◽  
pp. 214-218
Author(s):  
Omar Kassim Ariff ◽  
E. Salami ◽  
M.T. Ahmad ◽  
T.H. Go
Keyword(s):  
Guidance System ◽  
Missile Guidance ◽  
Proportional Navigation ◽  
Terminal Constraints ◽  
Rigid Connection ◽  
The Moment ◽  
Further Development ◽  
Rotary Wing ◽  
Guidance Laws ◽  
Specific Scenario

Autonomous aerial hard docking is the process where an aircraft approaches and forms a rigid connection with another aircraft. After the docking process is complete, it is not necessary for the lift and propulsion system of the docked aircraft to be operating. Docking allows the larger aircraft to carry the small aircraft outside its airframe, thereby extending the range of endurance of the smaller aircraft. In this paper, we investigate specific scenario where docking occurs between a rotary wing aircraft and a fixed wing aircraft. To perform the above procedure, a guidance system on each platform has to ensure interception while satisfying the primary interception condition of velocity vector co-linearity at the moment of intercept of the two trajectories or flight paths. Pursuit guidance and proportional navigation were assessed as candidates for further development for the terminal docking phase. Since the platforms are in quasi-perfect knowledge of each other, the pursuer evader scenario is replaced by the pursuer-pursuer scenario. The novelty of this work lies in the formulation of terminal constraints, as well as the findings obtained. This paper concludes that contrary to the missile guidance scenario, pursuit based guidance laws provide superior baseline laws from which AAHD guidance and navigation laws can be developed.

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