Show/Hide Menu
Hide/Show Apps
Logout
Türkçe
Türkçe
Search
Search
Login
Login
OpenMETU
OpenMETU
About
About
Open Science Policy
Open Science Policy
Open Access Guideline
Open Access Guideline
Postgraduate Thesis Guideline
Postgraduate Thesis Guideline
Communities & Collections
Communities & Collections
Help
Help
Frequently Asked Questions
Frequently Asked Questions
Guides
Guides
Thesis submission
Thesis submission
MS without thesis term project submission
MS without thesis term project submission
Publication submission with DOI
Publication submission with DOI
Publication submission
Publication submission
Supporting Information
Supporting Information
General Information
General Information
Copyright, Embargo and License
Copyright, Embargo and License
Contact us
Contact us
SDRE Based Guidance and Flight Control of Aircraft Formations
Date
2015-01-05
Author
Tekinalp, Ozan
Metadata
Show full item record
Item Usage Stats
185
views
0
downloads
Cite This
In this paper, a nonlinear guidance algorithm to control unmanned aircraft formationsis presented. This algorithm is based on State Dependent Riccati Equation (SDRE) ap-proach. Guidance equations are developed for leader-follower formation configurations.Flight control algorithms use SDRE based controllers as well, in the longitudinal and lat-eral dynamic channels of the aircraft. Leader aircraft follows the given speed, heading andaltitude commands and follower aircraft follows the leader using the commands generatedby SDRE based guidance algorithm. The effectiveness of the algorithms are demonstratedthrough simulations
URI
www.aiaa.org
https://hdl.handle.net/11511/80699
https://www.researchgate.net/publication/306260201_SDRE_Based_Guidance_and_Flight_Control_of_Aircraft_Formations
DOI
https://doi.org/10.2514/6.2015-0601
Conference Name
AIAA ScitTech 2015 Konferansı, 5 - 09 Ocak 2015
Collections
Department of Aerospace Engineering, Conference / Seminar
Suggestions
OpenMETU
Core
Numerical simulation of lateral jets in supersonic crossflow of missiles using computational fluid dynamics
Dağlı, Efe Can; Aksel, M. Haluk.; Department of Mechanical Engineering (2019)
In this thesis, numerical simulation method for modelling lateral jet in supersonic crossflow is presented. Lateral jet control provides high maneuverability to the missile at difficult flow conditions. Besides, jet in a crossflow case has a highly complicated flow domain which should be examined using numerical or experimental methods. In this study, numerical methods are used. The thesis consists of two main sections. In the first section, a validation study is conducted for numerical simulation method us...
Nonlinear Dynamic Inversion Autopilot Design for an Air Defense System with Aerodynamic and Thrust Vector Control
Bıyıklı, Rabiya; Yavrucuk, İlkay; Tekin, Raziye; Department of Aerospace Engineering (2022-2)
The study proposes complete attitude and acceleration autopilots in all three channels of a highly agile air defense missile by utilizing a subcategory of nonlinear feedback linearization methods Nonlinear Dynamic Inversion (NDI). The autopilot design includes cross-coupling effects enabling bank-to-turn (BTT) maneuvers and a rarely touched topic of control in the boost phase with hybrid control which consists of both aerodynamic fin control and thrust vector control. This piece of work suggests solut...
Feedback motion planning of a novel fully actuated unmanned surface vehicle via sequential composition of random elliptical funnels
Özdemir, Oğuz; Ankaralı, Mustafa Mert; Department of Electrical and Electronics Engineering (2022-12-27)
This thesis proposes and analyzes a motion planning and control schema for unmanned surface vehicles that fuses sampling-based approaches’ probabilistic completeness with closed-loop approaches’ robustness. The Proposed schema is based on the sequential composition of elliptical funnels, and it consists of two stages: tree generation and motion control. For validation of the approach, we carried out experiments using both simulation and physical setup besides the mathematical analysis. In order to have a co...
Slew Maneuver Control of Flexible Spacecraft
ALTINIŞIK, SÜLEYMAN; Tekinalp, Ozan (2019-07-04)
Nonlinear slew maneuver algorithms for flexible spacecraft are developed. Theattitude trackingalgorithm that uses quaternion parametrizationand follows the prescribed time dependent attitude trajectory incorporating the derivative of the desired attitudeis employed. Nonlinear tracking feedback control algorithms that includes piezoelectric actuators and modal sensors are also developed. Through simulations, the effectiveness of the tracking attitude control algorithm is demonstra...
Nonlinear aeroservoelastic modelling and analysis of aircraft with control surface freeplay
Yurtsever, Utku; Şahin, Melin; Kayran, Altan; Department of Aerospace Engineering (2022-11-24)
In this study, nonlinear aeroservoelastic analysis of aircraft with control surface freeplay is performed using the fictitious mass approach. For the demonstration of the nonlinear aeroservoelastic analysis methodology, an available very light aircraft (VLA) design configuration is selected. The aeroelastic model of the aircraft is obtained by combining the structural and aerodynamic models of the aircraft, which are prepared by the finite element modelling and analysis tool MSC.Patran/MSC.Nastran and the a...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
O. Tekinalp, “SDRE Based Guidance and Flight Control of Aircraft Formations,” Orlando, Florida, Amerika Birleşik Devletleri, 2015, p. 1, Accessed: 00, 2021. [Online]. Available: www.aiaa.org.