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Research Papers

Actuator Design and Flight Testing of an Active Microspoiler-Equipped Projectile

[+] Author and Article Information
Dooroo Kim, Laura Strickland

Woodruff School of Mechanical Engineering,
Georgia Institute of Technology,
Atlanta, GA 30332

Matthew Gross, Mark Costello

Guggenheim School of Aerospace Engineering,
Georgia Institute of Technology,
Atlanta, GA 30332

Jonathan Rogers

Woodruff School of Mechanical Engineering,
Georgia Institute of Technology,
Atlanta, GA 30332
e-mail: jonathan.rogers@me.gatech.edu

Frank Fresconi

Guided Weapons, Weapons and
Materials Research Directorate,
U.S. Army Research Laboratory,
Aberdeen Proving Ground,
Aberdeen, MD 21005

Ilmars Celmins

Weapons and Materials Research Directorate,
U.S. Army Research Laboratory,
Aberdeen Proving Ground,
Aberdeen, MD 21005

Contributed by the Dynamic Systems Division of ASME for publication in the JOURNAL OF DYNAMIC SYSTEMS, MEASUREMENT, AND CONTROL. Manuscript received October 27, 2016; final manuscript received April 28, 2017; published online July 10, 2017. Assoc. Editor: Soo Jeon. The United States Government retains, and by accepting the article for publication, the publisher acknowledges that the United States Government retains, a nonexclusive, paid-up, irrevocable, worldwide license to publish or reproduce the published form of this work, or allow others to do so, for United States Government purposes.

J. Dyn. Sys., Meas., Control 139(11), 111002 (Jul 10, 2017) (15 pages) Paper No: DS-16-1519; doi: 10.1115/1.4036808 History: Received October 27, 2016; Revised April 28, 2017

Actively controlled gun-launched projectiles require a means of modifying the projectile flight trajectory. While numerous potential mechanisms exist, microspoiler devices have been shown to be a promising control actuator for fin-stabilized projectiles in supersonic flight. These devices induce a trim force and moment generated by the boundary layer–shock interaction between the projectile body, rear stabilizing fins, and microspoilers. Previous investigations of microspoiler mechanisms have established estimates of baseline control authority, but experimental results have been restricted to cases in which the mechanism was statically deployed. This paper details the design and flight testing of a projectile equipped with a set of active microspoilers. A mechanical actuator is proposed that exhibits unique advantages in terms of robustness, simplicity, gun-launch survivability, and bandwidth compared to other projectile actuator mechanisms considered to date. A set of integrated test projectiles is constructed using this actuator design, and flight experiments are performed in which the microspoilers are oscillated near the projectile roll frequency. Data obtained from these flight tests are used in parameter estimation studies to experimentally characterize the aerodynamic effects of actively oscillating microspoilers. These predictions compare favorably with estimates obtained from computational fluid dynamics (CFD). Overall, the results presented here demonstrate that actively controlled microspoilers can generate reasonably high levels of lateral acceleration suitable for trajectory modification in many smart-weapons applications.

Copyright © 2017 by ASME
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References

Figures

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Fig. 1

Microspoiler mechanism on-board a fin-stabilized projectile

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Fig. 2

Army-Navy Finner projectile. All dimensions in calibers.

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Fig. 3

Optimized microspoiler geometry identified in CFD studies [15]

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Fig. 4

Microspoiler forces and moments versus angle of attack, Mach 2.5 [15]

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Fig. 5

Cross-range versus range for example trajectory simulation

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Fig. 6

Candidate rotary actuator mechanism designs: (a) scotch yoke design, (b) modified scotch yoke design, (c) positive return mechanism design, and (d) cam-follower design

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Fig. 7

Microspoiler extension versus cam angle for candidate actuator designs

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Fig. 8

Motor assembly (left) and latch circuit schematic (right) for microspoiler projectile

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Fig. 9

Lab-characterized actuator step response

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Fig. 10

Exploded view of active microspoiler assembly

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Fig. 11

Active microspoiler projectile integrated design

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Fig. 12

Fully assembled active microspoiler assembly in aft section of projectile

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Fig. 13

Fully integrated active projectile and sabot assembly

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Fig. 14

Example spark range shadowgraph from active microspoiler flight experiment

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Fig. 15

Cross-range measurements from spark range experiments

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Fig. 16

Altitude measurements from spark range experiments

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Fig. 17

Yaw angle measurements from spark range experiments

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Fig. 18

Pitch angle measurements from spark range experiments

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Fig. 19

Example baseline no-microspoiler trajectory fit

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Fig. 20

Example controlled projectile trajectory fit

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Fig. 21

Microspoiler perturbation forces versus Mach number

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Fig. 22

Microspoiler perturbation moments versus Mach number

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Fig. 23

Cross-range versus range for control authority simulations

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Fig. 24

Angle of attack versus time for control authority simulations

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