Modern Missile Guidance

Yanushevsky, Rafael

doi:10.1201/9781420062281

Cited by 61 publications

(19 citation statements)

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“…Clearly, z > 0 and p > 0 for this system. Therefore, the all-stabilizing controller set is given by 34 Considering the relation 75, the all-stabilizing k p range is given as follows À4:29859 < k p < 5:27732…”

Section: Numerical Examplesmentioning

confidence: 99%

“…The common feature of biproper systems with time delay in the closed loop is that they form a class of delay equations of a neutral type, for which there may be many right half-plane roots under particular circumstances, which require a stronger stability condition to be checked [31]. Even though, from the physical process viewpoint, they are rarer than the strictly proper ones, there are some processes such as seeker dynamics in missiles [32][33][34][35][36], thermal-electrical models of polychromatic and high-power LED luminaires [37,38], and force dynamics in robotics under particular circumstances [39,40], which can be modeled by biproper first-order transfer functions. Additionally, a parallel connection of any static and strictly proper first-order process results in a biproper one, which can particularly be the case in mixed chemical processes [41].…”

Section: Introductionmentioning

confidence: 99%

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All‐Stabilizing Proportional Controllers for First‐Order Bi‐Proper Systems with Time Delay: An Analytical Derivation

Nesimioğlu

Söylemez

2016

Asian Journal of Control

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In this paper, a simple derivation for an all-stabilizing proportional controller set for first-order bi-proper systems with time delay is proposed. In contrast to proper systems, an extremely limited number of studies are available in the literature for such bi-proper systems. To fill this gap in the literature, broader aspects of the stabilizing set are taken into consideration. The effect of zero on the stabilizing set is clearly discussed and we also prove that, when their zeros are placed symmetrically to the origin, the stabilizing set of non-minimum phase plant is always smaller than that of the minimum phase one. Moreover, for an open-loop unstable plant, maximum allowable time delay (MATD) is explicitly expressed as a function of the locations of the pole and zero. From that function, it is shown that for a minimum phase plant, the supremum of the MATD is two times that of the time constant of the plant and the infimum of the MATD is the time constant of the plant. We also prove that the supremum is the time constant and the infimum is zero for a non-minimum phase plant.

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Section: Numerical Examplesmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

All‐Stabilizing Proportional Controllers for First‐Order Bi‐Proper Systems with Time Delay: An Analytical Derivation

Nesimioğlu

Söylemez

2016

Asian Journal of Control

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“…having normal fin and stabilizer) implemented for orthophoto imaging show better stability (especially lateral) compared to the wing type (i.e. flying wing), the later ones are far more advantageous from compositional point of view -it is far easier to incorporate the imaging camera in such frame while keeping small size and good aerodynamics (Yanushevsky, 2009 Despite the mentioned advantages of "flying wing" configuration, its great disadvantage (which is very difficult to overcome) is high stall speed, which makes it very risky to operate at low speeds. The high stall speed comes from the aerodynamics of the "flying wing" airframe itself -to increase the angle of attack of the wing (to get higher lift force at low speeds) the elevons has to be inclined upwards, which in turn decreases the curvature of the wing, decreasing its lift force.…”

Section: Construction Of the Uavmentioning

confidence: 99%

Implementation and Testing of Low Cost Uav Platform for Orthophoto Imaging

Bručas¹,

Sužiedelyte‐Visockiene

Ragauskas

et al. 2013

Int. Arch. Photogramm. Remote Sens. Spatial Inf. Sci.

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ABSTRACT:Implementation of Unmanned Aerial Vehicles for civilian applications is rapidly increasing. Technologies which were expensive and available only for military use have recently spread on civilian market. There is a vast number of low cost open source components and systems for implementation on UAVs available. Using of low cost hobby and open source components ensures considerable decrease of UAV price, though in some cases compromising its reliability. In Space Science and Technology Institute (SSTI) in collaboration with Vilnius Gediminas Technical University (VGTU) researches have been performed in field of constructing and implementation of small UAVs composed of low cost open source components (and own developments). Most obvious and simple implementation of such UAVs -orthophoto imaging with data download and processing after the flight.

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“…This acceleration is acting perpendicular to the instantaneous LOT and is proportional to the LOT angular rate, target closing velocity and navigation constant pr N , which presents effective navigation ratio, and is given by the expression [12],…”

Section: Model Of Impact Kinematics For Simulation Algoritm Based On mentioning

confidence: 99%

“… NLOS missile's guidance effective range is calculated from the trajectory made by the method of proportional navigation by supposed LOT (line between target position and NLOS missile), with a flight navigation angles of mentioned vectors and lines using the method of proportional navigation with coefficient N pr =5 [4,11,12]. This value is used as fixed, depending of maneuver lateral constrained acceleration of the NLOS missile orientated to the mobile target area.…”

Section: Supposition For Analysismentioning

confidence: 99%