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You searched for subject:(Salvo Attack). Showing records 1 – 3 of 3 total matches.

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Indian Institute of Science

1. Ghosh, Satadal. Analysis of Proportional Navigation Class of Guidance Law against Agile Targets.

Degree: 2014, Indian Institute of Science

Guidance is defined as the determination of a strategy for following a nominal path in the presence of o-nominal conditions, disturbances and uncertainties, and the strategy employed is called a guidance law. Variants of Proportional Navigation (PN), such as True Proportional Navigation (TPN) and Pure Proportional Navigation (PPN), have been studied extensively in the literature on tactical missile guidance. In the absence of target maneuvers, in a linear interceptor guidance problem, TPN was shown to be optimal. However, the standard PN class of guidance laws per se does not show good performance against maneuvering targets, and was found to be eective in intercepting a maneuvering target only from a restrictive set of initial geometries. Also, since these guidance laws were eectively designed for lower speed targets, they show a degraded performance when applied against higher speed targets. However, in the current defense scenario, two classes of agile targets, which are capable of continuous maneuver, and/or of much higher speed than the interceptor, are a reality. This thesis presents analysis of several variants of PN class of guidance laws against these two classes of agile targets. In the literature, an augmentation of the TPN guidance law, termed as Augmented Proportional Navigation (APN), was shown to be optimal in linearized engagement framework. The present work proposes an augmentation of the PPN guidance law, which is more realistic than TPN for an aerodynamically controlled interceptor, and an-alyzes its capturability in fully nonlinear framework, and develops sauciest conditions on speed ratio, navigation gain and augmentation parameter to ensure that all possible initial engagement geometries are included in the capture zone when applied against a target executing piecewise continuous maneuver. The thesis also obtains the capture zone in the relative velocity space for augmented PPN guidance law. In the literature, a novel guidance law was proposed for the interception of higher speed targets in planar engagement by using a negative navigation gain instead of the standard positive one, and was termed as Retro-PN. It was shown that even though the Retro-PN guided interceptor takes more time than PN guided one in achieving successful interception, Retro-PN performs significantly better than the classical PN law, in terms of capturability, lateral acceleration demand, and closing velocity, when used against higher speed targets. The thesis analyzes Retro-PN guidance law in 3-D engagement geometries to yield the complete capture zone of interceptors guided by Retro-PN guidance philosophy, and derives necessary and sucient conditions for the capture of higher speed non-maneuvering targets with and without a constraint on finiteness of lateral acceleration. Terminal impact angle control is crucial for enhancement of warhead eectiveness. In the literature, this problem has been addressed mostly in the context of targets with lower speeds than the interceptor. The thesis analyzes the performance of a… Advisors/Committee Members: Ghose, Debasish, Raha, Soumyendu.

Subjects/Keywords: Proportional Navigation; Maneuvering Target; Guidance; Augumented Pure Portional Navigation (APPN) Guidance Laws; Retro-PN Guidance Law; Guidance Laws; Higher-Speed Target; Agile Targets; Impact Angle Control; Composite Proportional Navigation (CPN); Impact Angle Analysis; Impact Time Control; Salvo Attack; Higher Speed Nonmaneuvering Targets; Time-varying Target; Mathematics

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Ghosh, S. (2014). Analysis of Proportional Navigation Class of Guidance Law against Agile Targets. (Thesis). Indian Institute of Science. Retrieved from http://hdl.handle.net/2005/2903

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16th Edition):

Ghosh, Satadal. “Analysis of Proportional Navigation Class of Guidance Law against Agile Targets.” 2014. Thesis, Indian Institute of Science. Accessed December 06, 2019. http://hdl.handle.net/2005/2903.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7th Edition):

Ghosh, Satadal. “Analysis of Proportional Navigation Class of Guidance Law against Agile Targets.” 2014. Web. 06 Dec 2019.

Vancouver:

Ghosh S. Analysis of Proportional Navigation Class of Guidance Law against Agile Targets. [Internet] [Thesis]. Indian Institute of Science; 2014. [cited 2019 Dec 06]. Available from: http://hdl.handle.net/2005/2903.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Ghosh S. Analysis of Proportional Navigation Class of Guidance Law against Agile Targets. [Thesis]. Indian Institute of Science; 2014. Available from: http://hdl.handle.net/2005/2903

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation


Indian Institute of Science

2. Abdul Saleem, P K. Guidance Laws for Engagement Time Control.

Degree: 2016, Indian Institute of Science

Autonomous aerial vehicles like missiles and unmanned aerial vehicles (UAVs) have attracted various military and civilian applications. The primary guidance objective of any autonomous vehicle is to reach the desired destination point (target or waypoint). However, many practical engagements impose additional constraints like minimum control effort, a desired final velocity direction or a predefined engagement time. This thesis addresses engagement time constrained guidance problems pertaining to missiles and UAVs. The first part of the thesis discusses a nonlinear guidance law for impact time control of missiles against stationary target. The guidance law is designed with a particular choice of missile heading error variation as a function of ran to-target. The proposed heading error variation leads to an exact closed-form expression for the impact time. controlling the impact time, a closed-form relation is derived relating the control parameter to the desired impact time. A new Lyapunov based guidance law with a monotonically decreasing lateral acceleration is proposed in the next part of the thesis. An exact expression for impact time with minimum and maximum achievable impact times is derived. A control parameter is proposed with a closed-form relationship to the desired impact time. Using the concept of predicted interception point, the two guidance laws are extended for impact time control against non-maneuvering and moving targets. The proposed guidance models are extended to three-dimensional engagements by deducing yaw and pitch lateral accelerations satisfying the desired heading error profile. Extensive simulation studies are carried out for single missile and salvo attack scenarios. The last part of the thesis presents a guidance methodology governing the arrival time of a UAV at a waypoint. A specific arrival angle is considered as an additional constraint. The arrival constraints are satisfied by varying the navigation gain of the proportional navigation guidance law. The methodology is applied for simultaneous and sequential arrival of UAVs at a waypoint. Advisors/Committee Members: Ratnoo, Ashwini.

Subjects/Keywords: Unmanned Aerial Vehicles; Missile Impact Time Control; Guidance Laws; Missile Guidance; Impact Time Control Guidance Law; Unmanned Aerial Vehcile Arrival Time Control; Lyapunov Guidance Law; Unmanned Aerial Vehicle Guidance; Nonlinear Guidance Laws; Autonomous Aerial Vehicles; Missiles; Salvo Attack; Impact Time Control; UAVs; Aerospace Engineering

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Abdul Saleem, P. K. (2016). Guidance Laws for Engagement Time Control. (Thesis). Indian Institute of Science. Retrieved from http://hdl.handle.net/2005/2926

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16th Edition):

Abdul Saleem, P K. “Guidance Laws for Engagement Time Control.” 2016. Thesis, Indian Institute of Science. Accessed December 06, 2019. http://hdl.handle.net/2005/2926.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7th Edition):

Abdul Saleem, P K. “Guidance Laws for Engagement Time Control.” 2016. Web. 06 Dec 2019.

Vancouver:

Abdul Saleem PK. Guidance Laws for Engagement Time Control. [Internet] [Thesis]. Indian Institute of Science; 2016. [cited 2019 Dec 06]. Available from: http://hdl.handle.net/2005/2926.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Abdul Saleem PK. Guidance Laws for Engagement Time Control. [Thesis]. Indian Institute of Science; 2016. Available from: http://hdl.handle.net/2005/2926

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation


Indian Institute of Science

3. Kumar, Shashi Ranjan. Sliding Mode Control Based Guidance Strategies with Terminal Constraints.

Degree: 2015, Indian Institute of Science

In the guidance literature, minimizing miss distance along with optimizing the energy usage had been an objective for several decades. In current day applications, additional terminal performance such as impact angle and impact time are of paramount importance. These terminal constraints increase warhead effectiveness and survivability of the interceptor. This thesis contributes to the design of guidance laws addressing terminal constraints such as impact angle, impact time, and both impact time as well as impact angle, in addition to interception of targets. In the first part of the thesis, the guidance laws which ensure the alignment of the interceptor at a desired impact angle within a finite time is proposed using different variants of sliding mode control(SMC).The impact angle is first redefined in terms of line-of-sight angle and then the impact angle problem is converted to a simpler problem of controlling line-of-sight angle and their rates. The sliding mode capturability and interpretation of the guidance laws are presented. In order to cater to very large heading angle errors, which give rise to negative closing speed initially, modifications to the guidance laws are also suggested. The modifications to the guidance laws for avoiding singularities, which may be encountered during implementation, due to the inherent nature of terminal SMC, are suggested. However, the guidance laws, which alleviates the possibility of such singularities completely, are also designed by using non singular terminal SMC. The two loop guidance and control, for a skid-to-turn cruciform interceptor in the pitch plane, is also proposed with an autopilot designed using the concept of dynamic SMC. The guidance laws addressing impact angle constraint for three dimensional scenarios are also presented. Unlike the usual approach of decoupling the three dimensional engagement in to two mutually orthogonal planar engagements, the guidance laws are derived using coupled engagement dynamics. These guidance laws are designed using conventional and non singular terminal SMC and provide asymptotic and finite time alignment of the intercept or to the desired impact angles, respectively. Next, the SMC based guidance laws which ensure the interception of targets at pre-speciļ¬ed impact times is proposed in this thesis. The guidance law is first designed for stationary targets and then extended to constant velocity targets using the notion of predicted interception point. A switching surface is designed using the concepts of collision course and time-to-go with non-linear engagement dynamics and its role in achieving the objectives is also discussed. In order to account for large heading angle errors and even for negative initial closing speeds, different methods of estimation of time-to-go, resulting in two different guidance laws, are used. Unlike the existing guidance laws, the proposed guidance laws achieve an impact time even less than its initially estimated value. The flexibility in selecting a desired impact time is also exploited using… Advisors/Committee Members: Ghose, Debasish.

Subjects/Keywords: Sliding Mode Control; Guidance and Control Theory; Sliding Mode Guidance Laws; Impact Angle Guidance; Impact Time Guidance; Guidance Laws; Sliding Mode Guidance; Salvo Attack Guidance; Nonlinear Engagement Dynamics; Missile Guidance; Flight Control; Finite Time Convergence; Sliding-Mode Guidance; Impact Time Guidance; Aerospace Engineering

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6th Edition):

Kumar, S. R. (2015). Sliding Mode Control Based Guidance Strategies with Terminal Constraints. (Thesis). Indian Institute of Science. Retrieved from http://etd.iisc.ernet.in/2005/3876 ; http://etd.iisc.ernet.in/abstracts/4748/G26895-Abs.pdf

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16th Edition):

Kumar, Shashi Ranjan. “Sliding Mode Control Based Guidance Strategies with Terminal Constraints.” 2015. Thesis, Indian Institute of Science. Accessed December 06, 2019. http://etd.iisc.ernet.in/2005/3876 ; http://etd.iisc.ernet.in/abstracts/4748/G26895-Abs.pdf.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7th Edition):

Kumar, Shashi Ranjan. “Sliding Mode Control Based Guidance Strategies with Terminal Constraints.” 2015. Web. 06 Dec 2019.

Vancouver:

Kumar SR. Sliding Mode Control Based Guidance Strategies with Terminal Constraints. [Internet] [Thesis]. Indian Institute of Science; 2015. [cited 2019 Dec 06]. Available from: http://etd.iisc.ernet.in/2005/3876 ; http://etd.iisc.ernet.in/abstracts/4748/G26895-Abs.pdf.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Kumar SR. Sliding Mode Control Based Guidance Strategies with Terminal Constraints. [Thesis]. Indian Institute of Science; 2015. Available from: http://etd.iisc.ernet.in/2005/3876 ; http://etd.iisc.ernet.in/abstracts/4748/G26895-Abs.pdf

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

.