Impact point model predictive control of a spin-stabilized projectile with instability protection

Gross, Matthew; Costello, Mark

doi:10.1177/0954410013514743

Cited by 12 publications

(10 citation statements)

References 31 publications

(46 reference statements)

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“…Taking a time derivative of (26), the detector rate is given by, Two assumptions are invoked for model equivalency purposes. First, it is assumed that the airframe flies at low total angle of attack so that , where represents the error components from equation (19). This assumption will be supported in the next section with an observer designed to remove excess angular motion.…”

Section: Control System Gain Selectionmentioning

confidence: 99%

“…For the purposes of this study two motor-wing assemblies are considered to be packaged near the projectile base oriented 180 deg apart in roll angle. Since the focus of this study is on the imager-based guidance and control algorithm, additional details regarding this particular maneuver mechanism are omitted here for brevity but may be found in References [17][18][19][20]. …”

Section: A Projectile Conceptmentioning

confidence: 99%

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Guidance and Control of a Man Portable Precision Munition Concept

Fresconi

Rogers

2015

AIAA Atmospheric Flight Mechanics Conference

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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, 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: Control System Gain Selectionmentioning

confidence: 99%

Section: A Projectile Conceptmentioning

confidence: 99%

Guidance and Control of a Man Portable Precision Munition Concept

Fresconi

Rogers

2015

AIAA Atmospheric Flight Mechanics Conference

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show abstract

“…For the purposes of this study, two motor-wing assemblies are considered to be packaged near the projectile base oriented 180 deg apart in roll angle. Because the focus of this study is on the imager-based guidance and control algorithm, additional details regarding this particular maneuver mechanism are omitted here for brevity but may be found in [17][18][19][20].…”

Section: A Projectile Conceptmentioning

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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“…Repeated expansion and contraction of the nutation at specific states of the precession angle allows us to "walk the precession" and produce a nonzero average of the AOA throughout the precession cycle, which changes the bullet trajectory. Closed-loop trajectory maneuverability can be achieved with active nutation control through trajectory optimization and model predictive controls [10][11][12].…”

Section: B Precession Synchronized Single Actuator Performancementioning

confidence: 99%