Missile guidance with constrained intercept body angle

Rusnak, Ilan; Weiss, Haim; Eliav, Rei; Shima, Tal

doi:10.1109/taes.2014.120100

Cited by 25 publications

(4 citation statements)

References 21 publications

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“…A different scheme for integrated missile guidance [18] also utilizes adaptive dynamic surface control but with input saturation. Furthermore, it has also been proposed that for a maneuvering missile, the body angle at which the target is intercepted is the sum of the flight path angle and the angle of attack [19] and therefore it should not be disregarded because it is significant in several cases.…”

Section: Incas Bulletin Volume 9 Issue 2/ 2017mentioning

confidence: 99%

Integrated CLOS and PN Guidance for Increased Effectiveness of Surface to Air Missiles

Tuz¹,

Islam²,

Ali³

2017

INCAS BULLETIN

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Section: Incas Bulletin Volume 9 Issue 2/ 2017mentioning

confidence: 99%

Integrated CLOS and PN Guidance for Increased Effectiveness of Surface to Air Missiles

Tuz¹,

Islam²,

Ali³

2017

INCAS BULLETIN

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“…For maneuvering targets, Idan et al 4 proposed an optimal planar interception law to achieve a given interception angle with constraints on the initial and the final flight-path angles of the interceptor. Optimal guidance laws with terminal impact angle constraints in the form of the state feedback for the lag-free and the first order lag systems were proposed by Ryoo et al 5 Considering the dynamics of the angle of attack, a guidance law for achieving the required terminal body angle was discussed by Rusnak et al 6 Optimal impact angle constraint guidance laws were also addressed in Refs. [7] and [8].…”

Section: Introductionmentioning

confidence: 99%

Time-optimal moving target interception with impact angle constraint

Singh

Hota

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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The time-optimal guidance law with impact angle constraint to intercept a nonstationary nonmaneuvering target in three-dimensional (3D) space by Unmanned Aerial Vehicles (UAVs) is discussed in this paper. To achieve less computational complexity, the guidance law proposed here is based on the proportional navigation (PN) law existing in the literature. Three stages are used with different values of the Navigation gains of PN law to intercept the target moving in any given direction. To calculate the final position of each phase, a geometric based optimal path calculation technique has been adopted. Another important factor of this guidance law is that the lateral acceleration bound has also been taken into account in designing the guidance law. The simulation results show that the presented scheme performs better than the existing work in literature based on the Sliding Mode Control (SMC).

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“…Several studies on the IR signatures of rocket exhaust plumes have been conducted at a zero AOA (α, angle between thrust and vehicle velocity vector) [10][11][12][13]. However, the launch vehicle or missile travels with a varying AOA according to the attitude adjustment and tactical conditions [14,15]. Generally, a moderate AOA is less than 30°, however, higher values can be employed under extreme conditions [16].…”

Section: Introductionmentioning

confidence: 99%

Investigation on Infrared Radiation Signatures of Under-Expanded Rocket Exhaust Plumes Due to Angle of Attack

et al. 2021

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A real flight trajectory varying from 5-60 km altitude was adopted for analyzing the effects of the angle of attack (AOA) on the IR signatures of rocket exhaust plumes. Three representative underexpanded states based on nozzle pressure ratio (NPR), including moderately under-expanded (NPR = 1.27), highly under-expanded (NPR = 12.5), and over-highly under-expanded (NPR = 120) states, were discussed. The results show that the appearance of the AOA shortens the plume scale size and afterburning region, but the peak temperature cannot significantly change. As an increase in the AOA, the high-temperature region and Mach cells are compressed to a small domain. The spectral radiant intensity is reduced and the decreasing rate is gradual for a large AOA. The peak radiance in the 2.7 μm band decreases, but that in the 4.3 μm band increases. The peak radiance curve shifted toward the increasing NPR as the AOA increases, and then the curve decreases monotonically from an initial "arched" shape. In addition, a group of band pairs can be observed by two intersecting in-band profiles as a function of altitude. The characteristic altitude of band pairs became more concentrated and moved toward low altitude with the increase in AOA.

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Missile guidance with constrained intercept body angle

Cited by 25 publications

References 21 publications

Integrated CLOS and PN Guidance for Increased Effectiveness of Surface to Air Missiles

Integrated CLOS and PN Guidance for Increased Effectiveness of Surface to Air Missiles

Time-optimal moving target interception with impact angle constraint

Investigation on Infrared Radiation Signatures of Under-Expanded Rocket Exhaust Plumes Due to Angle of Attack

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