Investigative design of missile longitudinal dynamics using LQR-LQG controller in presence of measurement noise and inaccurate model

Arikapalli, V.S.N. Murthy; Bhowmick, Shiladitya; Rao, P V R R Bhogendra; Ayyagari, Ramakalyan

doi:10.1007/s12046-021-01784-0

Sādhanā

2022

DOI: 10.1007/s12046-021-01784-0

|View full text |Cite

Investigative design of missile longitudinal dynamics using LQR-LQG controller in presence of measurement noise and inaccurate model

V.S.N. Murthy Arikapalli

Shiladitya Bhowmick

P V R R Bhogendra Rao

et al.

Help me understand this report

Search citation statements

Order By: Relevance

Paper Sections

Select...

Citation Types

Supporting

Mentioning

Contrasting

Year Published

2024

Publication Types

Select...

Article1

Relationship

Self Cite0

Independent1

Authors

Journals

Cited by 1 publication

References 21 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

An investigation on LQR based optimal terminal states control for exo-atmospheric flight of super heavy hypersonic intercontinental ballistic missiles using Gauss pseudospectral method

Mamandi

2024

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

Using 3-DOF model for the launch vehicle, the governing dynamic differential equations for the flight of intercontinental ballistic missiles (ICBMs) in a rotating Earth model has been employed to form the optimal control problem (OCP). Based on the Gauss pseudospectral method (GPM) for the OCP, the state and control variables are discretized using the Legendre-Gauss (LG) points in which the system dynamics is approximated on these LG points. Based on GPM, the linear quadratic regulator (LQR) controller for objective function of the OCP has been used for the state and control variables when the vacuum flight of the missile is constrained by a fixed terminal state-fixed terminal time condition. Then the objective function of OCP has been discretized in terms of state variables employing the Gauss differential approximation matrix. Using LQR based optimal control in conjunction with the GPM, input control variables are comprised to meet the terminal conditions of the system accordingly. In order to evaluate the performance and applicability of the present LQR based GPM optimal terminal states control in the exo-atmospheric flight of super heavy hypersonic ICBMs, the Titan II and RS-28 Sarmat are used as the launch vehicles. Numerical simulations for terminal errors are examined for the perturbed thrust and control problems. Numerical simulations reveal that the nonzero terminal errors are quite small in which the terminal accuracy of the solution can be regarded as acceptable. Moreover, it is concluded that the applied method effectively able to keep ICBM on to the desired terminal coordinates.

show abstract

An investigation on LQR based optimal terminal states control for exo-atmospheric flight of super heavy hypersonic intercontinental ballistic missiles using Gauss pseudospectral method

Mamandi

2024

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

show abstract

scite is a Brooklyn-based organization that helps researchers better discover and understand research articles through Smart Citations–citations that display the context of the citation and describe whether the article provides supporting or contrasting evidence. scite is used by students and researchers from around the world and is funded in part by the National Science Foundation and the National Institute on Drug Abuse of the National Institutes of Health.

Contact Info

customersupport@researchsolutions.com

10624 S. Eastern Ave., Ste. A-614

Henderson, NV 89052, USA

This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.

Blog Terms and Conditions API Terms Privacy Policy Contact Cookie Preferences Do Not Sell or Share My Personal Information

Made with 💙 for researchers

Part of the Research Solutions Family.

Investigative design of missile longitudinal dynamics using LQR-LQG controller in presence of measurement noise and inaccurate model

Cited by 1 publication

References 21 publications

An investigation on LQR based optimal terminal states control for exo-atmospheric flight of super heavy hypersonic intercontinental ballistic missiles using Gauss pseudospectral method

An investigation on LQR based optimal terminal states control for exo-atmospheric flight of super heavy hypersonic intercontinental ballistic missiles using Gauss pseudospectral method

Contact Info

Product

Resources

About