Testing the Maneuvering Performance of a Mach 4 Projectile

Massey, Kevin; Silton, Sidra I.

doi:10.2514/6.2006-3649

Cited by 15 publications

(20 citation statements)

References 2 publications

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“…(1) . Six positions were selected to be tested under the same conditions using a hexadedral grid, consisting of approximately 5 .…”

Section: Methodsmentioning

confidence: 99%

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Numerical investigation of optimal pin location on a supersonic projectile

Bell¹,

Robinson²,

Robinson³

2012

Aeronaut. j. (1968)

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The flowfield around a supersonic projectile using a pin actuator control method has been predicted using computational fluid dynamics. It has been predicted using both viscous and inviscid methods for a number of positions. Both methods showed that an optimal longitudinal position exists. However, the inviscid model over-predicted the lateral acceleration due to the difference in shock formation around the pin between the two approaches. The optimal location was predicted independent of solver, however the higher-fidelity solver predicted lower achievable lateral accelerations. This is due to the viscous interactions caused by the pin. The effect of projectile orientation has shown that shielding the pin leads to reduced effectiveness due to the wake of the fin enveloping the pin. When the pin is exposed to onset flow, the forces achieved are increased. There is also an increase in the achievable forces and moments with increasing Mach number.

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“…(1) . Six positions were selected to be tested under the same conditions using a hexadedral grid, consisting of approximately 5 .…”

Section: Methodsmentioning

confidence: 99%

“…Pin based actuators have been shown to be a viable method of providing directional control of supersonic projectiles (1) . Massey and Silton have demonstrated that a pin actuator generated a lateral acceleration of 14g for a gun-launched, spin-stabilised projectile (2) .…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of optimal pin location on a supersonic projectile

Bell¹,

Robinson²,

Robinson³

2012

Aeronaut. j. (1968)

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show abstract

“…Most recently, Leonard et al [15] investigated possible geometric arrangements of microspoilers on the projectile surface and obtained an optimal configuration that maximizes control authority. In a separate set of investigations, Massey et al [16][17][18] considered a control mechanism called "pin fins," which are similar to microspoilers except they are larger (on the order of onethird the fin height) and protrude beyond the boundary layer. Both computational and experimental analysis showed that significant force multiplication can be generated by modifying the boundary layer-shock interaction of the projectile fin and body, leading to large and controllable aerodynamic load perturbations.…”

Section: Introductionmentioning

confidence: 99%

“…Another novel concept proposed by Celmins et al [22] for man-portable munitions uses a set of motors at the rear of the projectile to move a static airfoil into and out of the oncoming airflow. A final control actuator particularly relevant to this paper was proposed by Massey and Silton [18] for pin-fin mechanisms. This device is purely passive and involves a springmass system which yields oscillatory motion of the fins into and out of the projectile body.…”

Section: Introductionmentioning

confidence: 99%

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

Kim

Strickland

Gross

et al. 2017

Journal of Dynamic Systems, Measurement, and Control

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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.

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“…Massey et al [4], Massey and Guthrie [5], Massey and Silton [6], and Bell et al [7] considered protuberance effects on fin-body interactions of high-speed projectiles. Both computational and experimental analysis showed that significant force multiplication can exist by modifying the boundary-layer shock interaction of the projectile fin and body.…”

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confidence: 99%

Use of Microspoilers for Control of Finned Projectiles

Dykes

Montalvo

Costello

et al. 2012

Journal of Spacecraft and Rockets

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Due to space limitations, cost restrictions, and performance challenges, the physical control mechanism on a smart projectile plays a central role in the overall system design. Many different smart projectile control mechanisms have been created including aerodynamic-based mechanisms such as movable canards, propellant-based mechanisms such as squibs, and inertia-based mechanisms such as internal moving masses. The work reported here considers small microspoilers located between rear fins of a finned projectile to create aerodynamic load changes to enable projectile control. In particular, boundary-layer shock interaction between the projectile body, fins, and microspoilers provides a multiplicative effect on controllable forces and moments induced by microspoiler activation. A parametric study varying the microspoiler configuration is conducted to examine the level of control authority possible for this control mechanism concept. Results indicate that relatively small microspoilers located between fins generate substantial control authority that is capable of eliminating impact errors caused by muzzle jump, aerodynamic uncertainty, and atmospheric winds. These conclusions are based on computational fluid dynamic predictions of the effect of microspoilers on air loads coupled to a rigid six-degree-of-freedom projectile trajectory simulation.

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Testing the Maneuvering Performance of a Mach 4 Projectile

Cited by 15 publications

References 2 publications

Numerical investigation of optimal pin location on a supersonic projectile

Numerical investigation of optimal pin location on a supersonic projectile

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

Use of Microspoilers for Control of Finned Projectiles

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