Nonlinear Three Dimensional Composite Guidance Law Based on Feedback Linearization

Srivastava, Rituraj; Sarkar, Achintya Kumar; Ghose, Debasish; Gollakota, S

doi:10.2514/6.2004-4903

Cited by 6 publications

(4 citation statements)

References 7 publications

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“…Sliding mode control theory has been used in the nonlinear control system for decades, so here we deduce the guidance laws based on SMC, not based on nonlinear dynamic inversion like in reference [4] and [5], because when the nonlinear dynamic inversion was used, the system is more sensitive to uncertainties than SMC.…”

Section: Three Dimensional Guidance Lawmentioning

confidence: 99%

Derivation and simulation of three dimensional guidance law

Liu

Chen

2011

2011 Chinese Control and Decision Conference (CCDC)

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in this paper, three dimensional guidance law was proposed. It differs from previous guidance laws in three aspects, considering the random maneuverability of target, considering the relative acceleration along the line of sight, considering the difference between the commanded acceleration and realistic acceleration of missile. The derivation of three dimensional guidance law was derived based on sliding mode control theory, the effectiveness of the derived guidance laws was validated through the three dimensional simulation, the future research work was also recommended finally. P 3803 978-1-4244-8738-7/11/$26.00 c 2011 IEEE

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Section: Three Dimensional Guidance Lawmentioning

confidence: 99%

Derivation and simulation of three dimensional guidance law

Liu

Chen

2011

2011 Chinese Control and Decision Conference (CCDC)

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“…In [9], the control of the projections of the RHE angle in yaw and pitch planes is suggested. In [10], the errors between the missile's flight angles and LOS angles are controlled. In [11], the control of the LOS angles rate has been proposed.…”

Section: A Control Problemmentioning

confidence: 99%

“…The controlled parameters are the projections of the relative heading error (RHE) in yaw and pitch planes. In [10], the FL method is applied to derive a 3-D pure pursuit guidance law, where the system outputs are the missile's flight-path angles, and the controlled parameters are the errors between the missile's flight angles and line-of-sight (LOS) angles. In [11], the application of FL is proposed to derive a 3-D guidance law where the system outputs are the LOS angles and the controlled parameters are the LOS angles rates.…”

Section: Introductionmentioning

confidence: 99%

All-Aspect Three-Dimensional Guidance Law Based on Feedback Linearization

Weiss

Rusnak

2015

Journal of Guidance, Control, and Dynamics

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“…Many guidance and control techniques have been investigated by researchers: vector field approach [4][5][6][7][8][9][10], line of sight algorithms [11], Serret-Frenet representation based methods [6,12], feedback linearization [13][14][15] and thebackstepping approach [16][17][18]. This paper explores the implementation of a nonlinear guidance and control design technique for a UAV to track a target in 3D environment.…”

Section: Introductionmentioning

confidence: 99%

Target Tracking in 3-D Using Estimation Based Nonlinear Control Laws for UAVs

Ahmed

Subbarao

2016

Aerospace

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This paper presents an estimation based backstepping like control law design for an Unmanned Aerial Vehicle (UAV) to track a moving target in 3-D space. A ground-based sensor or an onboard seeker antenna provides range, azimuth angle, and elevation angle measurements to a chaser UAV that implements an extended Kalman filter (EKF) to estimate the full state of the target. A nonlinear controller then utilizes this estimated target state and the chaser's state to provide speed, flight path, and course/heading angle commands to the chaser UAV. Tracking performance with respect to measurement uncertainty is evaluated for three cases: (1) stationary white noise; (2) stationary colored noise and (3) non-stationary (range correlated) white noise. Furthermore, in an effort to improve tracking performance, the measurement model is made more realistic by taking into consideration range-dependent uncertainties in the measurements, i.e., as the chaser closes in on the target, measurement uncertainties are reduced in the EKF, thus providing the UAV with more accurate control commands. Simulation results for these cases are shown to illustrate target state estimation and trajectory tracking performance.

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Nonlinear Three Dimensional Composite Guidance Law Based on Feedback Linearization

Cited by 6 publications

References 7 publications

Derivation and simulation of three dimensional guidance law

Derivation and simulation of three dimensional guidance law

All-Aspect Three-Dimensional Guidance Law Based on Feedback Linearization

Target Tracking in 3-D Using Estimation Based Nonlinear Control Laws for UAVs

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