Guidance and Control of a Cannon-Launched Guided Projectile

Morrison, P.; S.Amberntson, David

doi:10.2514/3.57205

Cited by 45 publications

(16 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…Guidance and flight control techniques for large, slowly rolling projectiles (1,(7)(8)(9) exist in the literature, but there is no published work for small, fast-spinning airframes. These flight bodies exhibit unique characteristics that increase the difficulty of the guidance problem.…”

Section: Introductionmentioning

confidence: 99%

Guidance and Control of a Man-Portable Precision Munition Concept

Fresconi¹,

Rogers²

2014

View full text Add to dashboard Cite

Approved for public release; distribution is unlimited.ii REPORT DOCUMENTATION PAGE Form Approved OMB No. 0704-0188Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing the burden, to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY)June 2014 ARL-TR-6966 SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSOR/MONITOR'S ACRONYM(S) SPONSOR/MONITOR'S REPORT NUMBER(S) DISTRIBUTION/AVAILABILITY STATEMENTApproved for public release; distribution is unlimited. SUPPLEMENTARY NOTES ABSTRACTThe hypothesis of this report is that delivery accuracy of small-diameter spin-stabilized projectiles can be improved through novel guidance and control techniques using low-cost components. A gyroscopically stable projectile equipped with a strap-down detector and rotary actuation assembly is introduced. Flight models are formulated to enable nonlinear simulation. The unique guidance challenges posed by characteristics of spin-stabilized flight dynamics such as limit cycles, center-ofgravity swerve, instability, and practical feedback are illustrated. New guidance and control techniques to circumvent these difficulties are proposed. Modeling, parameter estimation, and stability analysis results underpin control design. Representative feedback, control commands, and flight behaviors from nonlinear simulations demonstrate the efficacy of this guidance approach. Monte Carlo analysis shows more than a factor of two in accuracy improvement of the guided over the ballistic flight. These results indicate that delivery system improvements are achievable in small, gyroscopically stable projectiles containing low-cost guidance elements using integrated control formulations. iii SUBJECT TERMS

show abstract

Section: Introductionmentioning

confidence: 99%

Guidance and Control of a Man-Portable Precision Munition Concept

Fresconi¹,

Rogers²

2014

View full text Add to dashboard Cite

show abstract

“…Guidance and flight control of projectiles 8,[23][24][25][26][27][28][29][30][31][32][33][34][35][36][37][38] and missiles [39][40][41][42][43][44] has been explored in depth in the literature. Of particular interest for this study are investigations into roll control.…”

mentioning

confidence: 99%

Control Performance, Aerodynamic Modeling and Validation of Coupled Simulation Techniques for Guided Projectile Roll Dynamics

Sahu

Fresconi

Heavey

2014

AIAA Atmospheric Flight Mechanics Conference

View full text Add to dashboard Cite

This paper describes a computational study to understand the roll behavior of a canardcontrolled projectile. Numerical computations were performed for this projectile with roll control maneuvers using advanced computational fluid dynamics and coupled aerodynamics/rigid body dynamics techniques. Roll control algorithms were formulated based on aerodynamic model assessment and parameter estimation. Coupled techniques were validated against wind tunnel experiments for roll control maneuvers. Overall, computed roll control results matched well with the wind tunnel test data; this indicated that the coupled calculations seem to capture the relevant physics observed in the experiment. Nomenclature , ,= roll, roll rate, roll acceleration, rad, rad/s, rad/s 2 = axial moment-of-inertia, kg m 2 = mass, kg = diameter, m 4 = reference area, m 2 = velocity, m/s = Mach number , , , = pitch angle of attack, yaw angle of attack, total angle of attack, aerodynamic roll angle, rad = atmospheric density, kg/m 3 1 2 = dynamic pressure, Pa , , = body-fixed coordinate system = roll damping moment coefficient = radial center-of-pressure, calibers = axial center-of-pressure, calibers = center-of-gravity, calibers = roll moment coefficient = number = deflection, rad 2 ⁄ = velocity of projectile center-of-gravity, m/s ⁄ = angular velocity of projectile, rad/s = transformation matrix from body frame to i th lifting surface frame = time constant, s , , , = state, controls, measurement, error vector , , , = system dynamics, controls, forcing function, measurement matrices = cost function = gain matrix , = control error and control effort matrices = Riccati equation matrix = time, s , = aerodynamic roll moment, friction moment, N m = parameter matrix = likelihood function = covariance = error between measurement and calculation , , , = conservative variables, inviscid flux vector, viscous flux vector, source term , = cell volume, cell area Θ = observability map f = factor = Levenberg-Marquardt parameter subscripts= canard, calculated, command = fin = aerodynamic = i th lifting surface 0, 1, 3, 5 = zeroeth, first, third, fifth order terms = delay = bias = maneuver surface, measurement = friction

show abstract

“…Murphy's coefficients, [-], E = (ρSd)/(2m) reduction mass expression, [-], Sg gyroscopic stability factor, [-], Sd dynamic stability factor, [-], λ 1,2 damping stability coefficients, [-].…”

Section: P T M Gmentioning

confidence: 99%