Capture region of a 3D PPN guidance law for intercepting high-speed targets

2011 ◽  
Vol 14 (5) ◽  
pp. 1215-1226 ◽  
Author(s):  
Feng Tyan
Keyword(s):  
High Speed ◽  
Guidance Law ◽  
Capture Region

Performance analysis of differential geometric guidance law against high-speed target with arbitrarily maneuvering acceleration

2018 ◽  
Vol 233 (10) ◽  
pp. 3547-3563 ◽  
Author(s):  
Ke-Bo Li ◽  
Wen-Shan Su ◽  
Lei Chen
Keyword(s):  
High Speed ◽  
Control System Design ◽  
Proportional Navigation ◽  
Full Account ◽  
Guidance And Control ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Classical Differential Geometry ◽  
Relative Dynamics ◽  
And Control

The interception of high-speed target with an arbitrary maneuvering acceleration causes serious troubles to the guidance and control system design of airborne missile. A novel guidance law based on the classical differential geometry curve theory was proposed not long ago. Although it is believed and numerically demonstrated that this differential geometric guidance law (DGGL) is superior to the classical pure proportional navigation (PPN) in intercepting high-speed targets, its performance has not been thoroughly analyzed. In this paper, using the Lyapunov-like approach, the performance of DGGL against the high-speed target with an arbitrary but upper-bounded maneuvering acceleration is well studied. The upper bounds of the LOS rate and commanded acceleration of DGGL are obtained, and conditions that guarantee the capture of this type of maneuvering target are also presented. The nonlinear relative dynamics between the missile and target is taken into full account. Finally, the proposed theoretical findings are demonstrated by numerical simulation examples.

scholarly journals Bubble density gradient with laser detection: A wake-homing scheme for supercavitating vehicles

2018 ◽  
Vol 10 (6) ◽  
pp. 168781401878234 ◽  
Author(s):  
Jia Song ◽  
Likun Bian ◽  
Erfu Yang ◽  
Dongjing Su
Keyword(s):  
Density Gradient ◽  
High Speed ◽  
Wake Flow ◽  
Three Dimensional Model ◽  
Ship Wake ◽  
Laser Detection ◽  
Supercavitating Vehicles ◽  
Guidance Law ◽  
Bubble Density ◽  
Simulation Results

The poor mobility and complex target motion estimation are the two main challenges in the anti-ship attack missions of high-speed guided missiles. In this study, a new wake-homing scheme of supercavitating vehicles is proposed using the gradient wake flow phenomenon. The basic principle of the wake-homing with laser detection and the information which can be obtained are studied. According to the idiosyncrasy of laser detection, the geometrical characteristics of the vessel wake, and the bubble distribution characteristics, the three-dimensional model of bubble density gradient in horizontal plane of the maneuvering target ship wake flow is first built; the guidance law based on the gradient wake flow is designed and tested. Then, simulation results show the validity of the model wake, the guidance law based on the wake gradient information can accurately track the target. From the simulation results, we also can see that the new wake-homing scheme effectively improve the hit probability, reduce the range of loss, reduce power consumption and gentle guidance trajectory, greatly reduce the mobility requirements of the supercavitating vehicles.

scholarly journals Attack behaviour in naïve Gyrfalcons is modelled by the same guidance law as in Peregrines, but at a lower guidance gain

2021 ◽  
pp. jeb.238493
Author(s):  
Caroline H. Brighton ◽  
Katherine E. Chapman ◽  
Nicholas C. Fox ◽  
Graham K. Taylor
Keyword(s):  
High Speed ◽  
Angular Rate ◽  
Species Level ◽  
Line Of Sight ◽  
Proportional Navigation ◽  
Evolutionary Origins ◽  
Guidance Law ◽  
Flight Morphology ◽  
Aerial Hunting ◽  
The Individual

The aerial hunting behaviours of birds are strongly influenced by flight morphology and ecology, but little is known of how this relates to the behavioural algorithms guiding flight. Here we use GPS loggers to record the attack trajectories of captive-bred Gyrfalcons (Falco rusticolus) during their maiden flights against robotic aerial targets, which we compare to existing flight data from Peregrines (Falco peregrinus). The attack trajectories of both species are well modelled by a proportional navigation (PN) guidance law, which commands turning in proportion to the angular rate of the line-of-sight to target, at a guidance gain. However, naïve Gyrfalcons operate at significantly lower values of N than Peregrines, producing slower turning and a longer path to intercept. Gyrfalcons are less manoeuvrable than Peregrines, but physical constraint is insufficient to explain the lower values of N we found, which may reflect either the inexperience of the individual birds or ecological adaptation at the species level. For example, low values of N promote the tail-chasing behaviour that is typical of wild Gyrfalcons and which apparently serves to tire their prey in a prolonged high-speed pursuit. Likewise, during close pursuit of typical fast evasive prey, PN will be less prone to being thrown off by erratic target manoeuvres at low guidance gain. The fact that low-gain PN successfully models the maiden attack flights of Gyrfalcons suggests that this behavioural algorithm is embedded in a guidance pathway ancestral to the clade containing Gyrfalcons and Peregrines, though perhaps with much deeper evolutionary origins.

scholarly journals Capture region for a realistic TPN guidance law

1993 ◽  
Vol 29 (3) ◽  
pp. 995-1003 ◽  
Author(s):  
A. Dhar ◽  
D. Ghose
Keyword(s):  
Guidance Law ◽  
Capture Region

Biased optimal guidance law with specified velocity rendezvous angle constraint

2015 ◽  
Vol 119 (1220) ◽  
pp. 1287-1299 ◽  
Author(s):  
X. Xu ◽  
Y. Liang
Keyword(s):  
High Speed ◽  
Terminal Phase ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Terminal Time ◽  
Optimal Guidance ◽  
Simulation Results ◽  
Miss Distance ◽  
Simplified Mathematical Model ◽  
Distance Setting

Abstract In order to increase the effectiveness of interceptor missile, velocity rendezvous angle control is required in the terminal phase. The purpose of this paper is to obtain an optimal guidance law which can achieve specified velocity rendezvous angle as well as zero terminal miss distance. A biased optimal guidance law based on a simplified mathematical model is deduced for interceptors engaging against invasion aircraft. Different from previous literatures on this issue, the presented guidance law suitable for intercepting high-speed maneuvering target. Another advantage is, under centimeter level miss distance setting, the guidance law needs smaller guidance command near the terminal time, which can successfully avoid command saturation. Simulation results demonstrate the effectiveness of the presented guidance law.

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