Roll-pitch-yaw integrated μ-synthesis for high angle-of-attack missiles

Choi, Byungjoo; Kang, Seonhyeok; Kim, H. Jin; Jun, Byung-Eul; Lee, Jin-Ik; Tahk, Min-Jea; Park, Changhan

doi:10.1016/j.ast.2011.08.002

Cited by 13 publications

(9 citation statements)

References 9 publications

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Section: Transformation Of 2-dof Mimo Pid Into Sof Controlmentioning

confidence: 99%

“…Augmenting the states , with the plant (1), the statex of the augmented system is obtained as in (29). Further, augmenting z e along with z, the regulated outputz of the augmented system can be represented as in (29). Substituting y = C y x in (27) and rearranging, the control law u can be written as (28), where output matrix of the augmented system becomesC y in (30) (which does not contain 1∕ term and is of full row rank, provided rank(C y ) = r).…”

Section: Transformation Of 2-dof Mimo Pid Into Sof Controlmentioning

confidence: 99%

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A hybrid search based synthesis of static output feedback controllers for uncertain systems with application to multivariable PID control

Gopmandal

Garg

2021

Intl J Robust & Nonlinear

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This article proposes a hybrid search (involving the  ∞ performance level and a positive scalar variable in sequence) based method for  ∞ synthesis of linear time-invariant (LTI) static output feedback (SOF) controllers for a class of linear systems with norm-bounded time-varying parametric uncertainties. Using an available extended linear matrix inequality (LMI) formulation of bounded real lemma, a new sufficient condition in terms of LMIs is obtained for existence of SOF controllers, where a triangular structure in the variable part of the Lyapunov matrix is introduced, unlike the diagonal structure existing in direct synthesis methods in literature. To obtain as less as possible, the part of the Lyapunov matrix which is kept fixed while computing the variable part is first obtained using a -search based method. Then with this fixed part, the final variable triangular part of the Lyapunov matrix is obtained using a single positive scalar search based LMI method to further reduce .The efficacy of the proposed method is studied on a number of benchmark examples. The method is also extended for structured SOF design. Finally, the proposed method is applied to design two-degree-of-freedom (2-DOF) multivariable proportional-integral-derivative (PID) controllers for  ∞ compensation of norm-bounded uncertain plants. A case study on designing roll-pitch-yaw integrated missile autopilots is also considered to show the efficacy of the proposed multivariable PID compensation. K E Y W O R D Shybrid search based  ∞ method, MIMO PID, norm-bounded uncertainty, skid-to-turn missiles, static output feedback

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Section: Transformation Of 2-dof Mimo Pid Into Sof Controlmentioning

confidence: 99%

Section: Transformation Of 2-dof Mimo Pid Into Sof Controlmentioning

confidence: 99%

A hybrid search based synthesis of static output feedback controllers for uncertain systems with application to multivariable PID control

Gopmandal

Garg

2021

Intl J Robust & Nonlinear

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“…Aerodynamic control surfaces, even though they can prove to be mechanically fragile, offer the advantage of continuous time control as well as a close resemblance to well-mastered traditional missile control systems [2,6,17,21,[25][26][27]. The main means of ensuring a projectile's airframe stability are either tail-located fins or a high body roll-axis spin rate, whereas nose-located canards are additionally employed for trajectory correction.…”

Section: Introductionmentioning

confidence: 99%

Robust gain-scheduled autopilot design for spin-stabilized projectiles with a course-correction fuze

Theodoulis

Sève

Wernert

2015

Aerospace Science and Technology

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“…Classical autopilot designs typically approximated the flight channels as independent and focused on single-input single-output (SISO) controllers (Blakelock, 1991; Nelson, 1998). Recently, interest in multi-input multi-output (MIMO) controller methods has increased for missiles (Bruyere et al, 2003; Choi et al, 2012; Kang et al, 2009; Tsay, 2007), helicopters (Basri et al, 2014; Sheng et al, 2014; Yang and Liu, 2003) and multirotor vehicles (Ahmad et al, 2001; Efe, 2010; Liu et al, 2014; Özbek et al, 2015), where dynamical couplings are prominent. For fixed-wing aircraft, however, these effects are less pronounced, so approximate SISO techniques still dominate the process.…”

Section: Introductionmentioning

confidence: 99%

Scheduled smooth MIMO robust control of aircraft verified through blade element SIL testing

Kasnakoğlu

2016

Transactions of the Institute of Measurement and Control

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This paper demonstrates a multi-input multi-output (MIMO) robust control approach where multiple scheduled designs are merged to produce a smooth control law. The design is verified using software-in-the-loop (SIL) testing based on blade element theory (BET) for highly realistic flight simulations. An inner-loop attitude controller balances performance and robustness, achieving a fast response time, low overshoot, good noise rejection and minimal lateral–longitudinal coupling. The controllers are formed at several predetermined grid points so the design covers a wide flight envelope. Blade element SIL testing shows that the flight control system preserves stable flight and follows the references well, even under tough weather conditions. The proposed strategy is also compared with a classical autopilot design procedure and is seen to be superior.

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Roll-pitch-yaw integrated μ-synthesis for high angle-of-attack missiles

Cited by 13 publications

References 9 publications

A hybrid search based synthesis of static output feedback controllers for uncertain systems with application to multivariable PID control

A hybrid search based synthesis of static output feedback controllers for uncertain systems with application to multivariable PID control

Robust gain-scheduled autopilot design for spin-stabilized projectiles with a course-correction fuze

Scheduled smooth MIMO robust control of aircraft verified through blade element SIL testing

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