Projectile Roll Dynamics and Control with a Low-Cost Maneuver System

Fresconi, Frank; Celmins, Ilmars; Ilg, Mark; Maley, James M.

doi:10.2514/1.a32553

Cited by 32 publications

(7 citation statements)

References 10 publications

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“…1,21 The aerodynamic model for most of the high-performance missiles defines the dependence of rolling moment coefficient on various variables such as aerodynamic roll angle, total angle of attack, Mach number, angle of attack, side-slip angle, and control surface deflection. To this end, the generic model for roll dynamics can be written as 3,22,23 …”

Section: Roll Autopilot Design Problem Mathematical Modelmentioning

confidence: 99%

Performance investigation of extended-state-observer-based roll autopilot design

Sirisha

Das

Talole

2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this work, performance analysis of the recently appeared extended-state-observer (ESO)-based roll autopilot design is carried out. Firstly, considering a more realistic roll dynamics, performance comparison of the ESO-based design with several classical roll autopilot structures is carried out and the related results are presented. Next, the better performing designs are implemented and validated through a high fidelity nonlinear 6-DOF environment for a typical tactical missile in a realistic engagement scenario. Lastly, performance of the ESO-based design is investigated using Monte Carlo simulations under several subsystem parameter uncertainties. The results show that the ESO-based design offers satisfactory performance in controlling roll angle and its rate in the presence of significant disturbances, parameter uncertainties and crosscoupling effects and thus offers a viable approach towards design of roll autopilot for high performance tactical missiles.

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Section: Roll Autopilot Design Problem Mathematical Modelmentioning

confidence: 99%

Performance investigation of extended-state-observer-based roll autopilot design

Sirisha

Das

Talole

2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Collision-avoidance and formation-flight algorithms for airdrop of supplies from multiple units deployed in the same airspace have been derived and verified in simulation and experiment. 8 Guided projectile technologies have demonstrated [10][11][12] substantial progress recently. The emergence and subsequent gun hardening of Global Positioning System (GPS) technology has enabled precision artillery weapons.…”

Section: Introductionmentioning

confidence: 99%

“…Enhanced maneuverability while maintaining low-cost actuation components has been established more recently. 12 These efforts have largely focused on a single flight for larger caliber and indirect-fire applications.…”

Section: Introductionmentioning

confidence: 99%

Delivery of Modular Lethality via a Parent-Child Concept

Fresconi¹,

Fermen-Coker²

2015

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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.

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“…However, the maneuverability of such configurations is limited by the body being rolled in the proper orientation to move the center of gravity in the desired direction. Research shows [5][6][7] that a nonrolling airframe using four independent canards in a skid-to-turn ‡ arrangement can be the most effective method by which to guide a munition with movable lifting surfaces. As the desire of the military to engage moving targets as well as stationary targets increases, the need for understanding the aerodynamics associated with highly maneuverable airframes also increases.…”

mentioning

confidence: 99%

Effect of Canard Interactions on Aerodynamic Performance of a Fin-Stabilized Projectile

Silton

Fresconi

2015

Journal of Spacecraft and Rockets

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This study was undertaken to better understand the impact of the canard trailing vortex flow interactions on the aerodynamic design and flight performance of short length-to-diameter, fin-stabilized munitions. Advanced computational aerodynamic and parameter sensitivity analysis techniques were applied. Results indicated that airframe designs that did not consider canard trailing vortex interactions on tail fins suffered from drastically underpredicted stability. Analyses were performed with the canard trailing-edge vortex-tail-fin interactions included to design a new airframe, and the suitability of this design was verified. The aerodynamics of the resulting configuration, as determined from advanced computational techniques, compared within 25% of the predictions (stability underpredicted) using scaled aerodynamic coefficients, suggesting that inclusion of scaled interference effects is a reasonable assumption during the design process. Nomenclature C l = roll moment coefficient C m = pitching moment coefficient referenced to configuration center of gravityof body coordinates D = reference diameter, m f c = canard scaling factor f F = fin scaling factor L∕D = lift-to-drag ratio M = Mach number x c = axial location of canard hinge location, caliber from X cg x c ref = axial location of canard hinge location at which the canard aerodynamic coefficients are determined. X cg = center of gravity location, mm y = nondimensional turbulent boundary-layer coordinate α = angle of attack, deg α trim = trim angle of attack, deg Δy = first cell spacing off wall, mm δ = canard deflection angle, deg Superscripts B = body C = canards F = tail fins

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Projectile Roll Dynamics and Control with a Low-Cost Maneuver System

Cited by 32 publications

References 10 publications

Performance investigation of extended-state-observer-based roll autopilot design

Performance investigation of extended-state-observer-based roll autopilot design

Delivery of Modular Lethality via a Parent-Child Concept

Effect of Canard Interactions on Aerodynamic Performance of a Fin-Stabilized Projectile

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