Optimized Guidance of a Supersonic Projectile Using Pin Based Actuators

Massey, Kevin; Guthrie, Kevin; Silton, Sidra I.

doi:10.2514/6.2005-4966

Cited by 23 publications

(15 citation statements)

References 2 publications

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“…Using the results from the CFD, it was possible to conclude that the use of pins could conceptually produce enough force and moment to implement a bank to turn type control scheme. 6DOF simulations based on the results described in this paper implementing such a concept are described by Massey, et al (19) . Several hurdles still remained.…”

Section: Cfd Of Pinsmentioning

confidence: 99%

Development of mechanical guidance actuators for a supersonic projectile

et al. 2008

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There has been a recent interest in both missiles and guided projectiles that operate in the high supersonic to hypersonic range for various missions. The Office of Naval Research in the US has been pursuing HyFly (1) which is a proposed Mach 6 missile that would be used to strike targets of opportunity in a timely fashion before they could reposition. Marx et al (2) . discuss small guided projectiles that are under consideration for the future Objective force. They discuss how the increased lethality of guided projectiles will improve the survivability of the future soldier. Another area of interest revolves around cruise missile defense such as DARPA's low cost cruise missile defense (LCCMD) program and the Army's enhanced area air defense system (EAADS). One possible scheme for missile defense assumes that medium caliber guns with high rates of fire could fire multiple supersonic projectiles that could be guided into an incoming missile that may be undergoing evasive action. Warnash and Killen (3) describe several military programs where high speed guided munitions are in development or are under consideration. In all cases, it is found that the high closure rates between the projectile and the target may necessitate large turning forces.It was the goal of this effort to provide an initial feasibility study into the use of strategically located actuators to provide the turning force needed to terminally steer a missile or ABSTRACT In this paper, the results of a series of experiments funded by DARPA to determine the feasibility of using small actuators to provide directional control for a supersonic projectile are presented. Controlling the flight of the projectile was accomplished by taking advantage of complex shock-boundary-layer interactions produced by mechanical devices. Experimental tests were conducted at GTRI to screen several control concepts and actuator locations. Further experiments were conducted on a scale projectile in a supersonic stream to investigate the rise time of the forces. Several different mechanical actuators were tested which served to provide guidance for future actuator designs. CFD results were also used to predict the results in flight as well as gain insights into the fluid mechanics involved. Flight tests of a Mach 4 round proved the viability of the guidance actuator. NOMENCLATURE AOAangle-of-attack M Mach number P pressure ∆X lateral offset of pin from fin ∆Y stream wise distance of pin from fin trailing edge THE AERONAUTICAL JOURNAL

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Section: Cfd Of Pinsmentioning

confidence: 99%

Development of mechanical guidance actuators for a supersonic projectile

et al. 2008

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“…This is lower than the single pin on the flat plate which produced 8.4 lbs as shown in Table 1. The two configurations have similar total cross-section area with the micro flaps having 60 mm 2 and the single pin having 64.5 mm 2 . The microflaps themselves produced a similar level of axial force with 3.77 lbs vs 4.00 lbs for the single pin.…”

Section: Micro Flap Studymentioning

confidence: 99%

Flow Manipulation of a Fin on a Flat Plate Interaction in High-Speed Flow by Means of Micro Flaps

Cler¹,

Carson²,

Dillon³

et al. 2009

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. 1. REPORT DATE (DD-MM-YYYY)AUGUST 200 ARWSB-TR-09011 SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES)U.S. Army ARDEC REPORT NUMBER Benet Laboratories, RDAR-WSB Watervliet, NY 12189-4000 SPONSOR/MONITOR'S ACRONYM(S) SPONSORING/MONITORING AGENCY REPORT NUMBER DISTRIBUTION AVAILABILITY STATEMENTApproved for public release; distribution is unlimited. SUPPLEMENTARY NOTES ABSTRACTPrevious work has been done by Massey and Bell of protuberances on fin-body interactions of high speed projectiles. Both computational and experimental analysis has shown that significant force multiplication can exist by modifying the boundary layer shock interaction of the fin and body. The devices used in these previous studies were relatively large (on the order of one third the fin height) and protruded beyond the boundary layer. The purpose of this study is to show the effects of multiple micro flap devices on the fin and flat-plate interaction problem. The aerodynamic mechanisms could then be incorporated into micro adaptive flow control schemes to control a projectile. Computational fluid dynamics will be used to analyze various configurations, including a validation against experimental data from Massey. Study of the various configurations will help to determine critical features and flow qualities necessary for favorable interactions. SUBJECT TERMS

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“…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%

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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Optimized Guidance of a Supersonic Projectile Using Pin Based Actuators

Cited by 23 publications

References 2 publications

Development of mechanical guidance actuators for a supersonic projectile

Development of mechanical guidance actuators for a supersonic projectile

Flow Manipulation of a Fin on a Flat Plate Interaction in High-Speed Flow by Means of Micro Flaps

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

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