Pitch/Yaw Channels Control Design for a 155mm Projectile with Rotating Canards, using a H∞ Loop-Shaping Design Procedure

Small diameter, gun-launched projectiles pose a challenging platform on which to implement closed-loop guidance and control. This paper presents a novel imager-based guidance and control algorithm for small diameter, spin-stabilized projectiles. The control law is specifically formulated to rely on feedback only from a strap-down detector and roll angle sensors.Following introduction of the projectile nonlinear dynamic model, an integrated guidance and control algorithm is presented in which control commands are computed directly from detector feedback using a gain-scheduled proportional control. Time-varying controller gains are derived through a surrogate modeling approach, and controller performance is further enhanced through use of an observer that filters unwanted angular motion components from detector feedback.Example closed-loop flight simulations demonstrate performance of the proposed control system, and Monte Carlo analysis shows a factor of two accuracy improvement for the closed-loop system over ballistic flight. Results indicate that delivery system improvements are achievable in small, gyroscopically-stabilized projectiles containing low cost guidance elements using the proposed integrated guidance and control approach. mass [kg]This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States. AIAA SciTech I moment of inertia matrix [kg-m 2 ] , ⁄ total velocity of projectile with respect to the wind, velocity of center of gravity with respect to inertial frame in body-fixed coordinates [m/s] atmospheric density [kg/m 3 ] dynamic pressure at projectile mass center [N/m 2 ] q M dynamic pressure at wing actuator center of pressure [N/m 2 ] Mach number √ pitch angle-of-attack [rad] √ yaw angle-of-attack [rad] √ √ total angle-of-attack [rad] aerodynamic roll angle [rad] , , aerodynamic forces acting on projectile [N] , , gravity forces acting on projectile [N] , , aerodynamic moments acting on projectile [Nm] , , total, zero-yaw, and yaw-dependent axial force coefficient , , , total, trim, linear and nonlinear normal force coefficient roll damping moment coefficient , , , total, trim, linear and nonlinear pitching moment coefficient pitch damping moment coefficient Magnus force coefficient Magnus moment coefficient , , , Wind actuator aerodynamic coefficients , axial center-of-pressure, radial CP [m] → vector from center-of-gravity to i th moveable Downloaded by NANYANG TECHNICAL UNIVERSITY on October 1, 2015 | http://arc.aiaa.org | aerodynamic surface center-of-pressure [m] , , , Φ, Earth-fixed commanded, Earth-fixed control, body-fixed control, relative, and stowed roll angles [rad] 1 0 0 0 Φ Φ 0 Φ Φ transformation matrix from body-fixed to moveable aerodynamic surface coordinates transformation matrix from body-fixed to Earthfixed coordinates transformation matrix from body-fixed to wing surface coordinates transformation matrix from velocity vector coordinates to Earth-fixed coordinates , , inertial position [m] , , inertial translational veloc...

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Section: Introductionmentioning

confidence: 99%

“…Over the past several decades, numerous solutions have been proposed primarily for large artillery projectiles [1,2] or for slowly-rolling airframes [3][4][5]. The general methodology employed by most of these studies has been to use GPS [1,6], inertial measurements [7], and seekers [8] to provide feedback to a flight control system.…”

Section: Introductionmentioning

confidence: 99%

Guidance and Control of a Man Portable Precision Munition Concept

Fresconi

Rogers

2015

AIAA Atmospheric Flight Mechanics Conference

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“…Since the H∞ loop shaping design procedure based on robust stabilization combined with classical loop-shaping was proposed by McFarlane and Glover [4], it has been applied in fields of aerospace, mechanical control [5,6]. The design method of fixed-structure H∞ control was first proposed by Apkarian and Gahinet in 2012 [7], and the algorithmic approach is a non-smooth technique which gets the locally optimal solution of the practical problem.…”

Section: Introductionmentioning

confidence: 99%

Comparisons of H∞ Loop Shaping Method and Fixed-structure H∞ Method for Attitude Controllers of a Quadrotor

Kan¹,

Zhao²,

Belmiloud³

2017

dtetr

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Abstract. The H∞ loop shaping method and fixed-structure H∞ method are employed to design controllers of a quadrotor. The validity of these two controllers is verified by numerical simulations, and it is observed that both the methods can achieve the design requirements and have a well tracking performance and restraining noise performance. Compared to H∞ loop shaping controller, the fixed-structure H∞ controller has not only the general nature based on h-infinity theory, but also takes into account easy realization.

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“…Introduction D EVELOPMENT of viable guidance and control technologies for gun-launched projectiles is a unique engineering challenge. Over the past several decades, numerous solutions have been proposed, primarily for large artillery projectiles [1,2] or for slowly rolling airframes [3][4][5]. The general methodology employed by most of these studies has been to use GPS [1,6], inertial measurements [7], and seekers [8] to provide feedback to a flight control system.…”

mentioning

confidence: 99%

“…The general methodology employed by most of these studies has been to use GPS [1,6], inertial measurements [7], and seekers [8] to provide feedback to a flight control system. Course correction maneuvers are then initiated through aerodynamic mechanisms [2,4,9] or jet control [10]. The numerous engineering challenges associated with fielding viable smart weapons systems have been repeatedly noted in the literature, including lack of payload volume for electronics, harsh accelerations at gun launch, highly nonlinear dynamics, and low-cost requirements.…”

mentioning

confidence: 99%

Flight Control of a Small-Diameter Spin-Stabilized Projectile Using Imager Feedback

Fresconi

Rogers

2015

Journal of Guidance, Control, and Dynamics

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Small-diameter gun-launched projectiles pose a challenging platform on which to implement closed-loop guidance and control. This paper presents a novel imager-based guidance and control algorithm for small-diameter spinstabilized projectiles. The control law is specifically formulated to rely on feedback only from a strapdown detector and roll angle sensors. Following introduction of the projectile nonlinear dynamic model, an integrated guidance and control algorithm is presented in which control commands are computed directly from detector feedback using a gainscheduled proportional control. Time-varying controller gains are derived through a surrogate modeling approach, and controller performance is further enhanced through use of an observer that filters unwanted angular motion components from detector feedback. Example closed-loop flight simulations demonstrate performance of the proposed control system, and Monte Carlo analysis shows a factor of 2 accuracy improvement for the closed-loop system over ballistic flight. Results indicate that delivery system improvements are achievable in small, gyroscopically stabilized projectiles containing low-cost guidance elements using the proposed integrated guidance and control approach.

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Pitch/Yaw Channels Control Design for a 155mm Projectile with Rotating Canards, using a H∞ Loop-Shaping Design Procedure

Cited by 15 publications

References 21 publications

Guidance and Control of a Man Portable Precision Munition Concept

Guidance and Control of a Man Portable Precision Munition Concept

Comparisons of H∞ Loop Shaping Method and Fixed-structure H∞ Method for Attitude Controllers of a Quadrotor

Flight Control of a Small-Diameter Spin-Stabilized Projectile Using Imager Feedback

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