Aerodynamic Characterization of a Microspoiler System for Supersonic Finned Projectiles

Scheuermann, Edward; Costello, Mark; Silton, Sidra I.; Sahu, Jubaraj

doi:10.2514/1.a33005

Cited by 14 publications

(6 citation statements)

References 20 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Note that, in comparison to the fourspoiler designs used previously in Refs. [13,14], the optimized geometry obtained in Ref. [15] exhibits an impressive 80% increase in control moment with only a 39% increase in drag.…”

Section: Microspoiler Actuationmentioning

confidence: 80%

“…[16], this represents the first experimental work to date verifying the control efficacy of microspoilers as they undergo active oscillation (the work in Ref. [14] studied statically deployed spoilers only). This is particularly important since active control mechanisms on spinning projectiles must provide actuation in a constant maneuver direction and thus must be activated in an oscillatory fashion at the projectile spin rate.…”

Section: Introductionmentioning

confidence: 93%

“…However, the estimated C X0 value at Mach 2.5 in Table 2 shows very good agreement with the CFD predictions reported in Refs. [30] (C X0 % 0.47) and [14] (C X0 % 0.45). Given this close agreement with the results of two independent prior studies, it is likely that the semi-empirical PRODAS prediction of C X0 is in error by about 10% and the estimated value in Table 3 is very close to the true value.…”

Section: Flight Experimentsmentioning

confidence: 99%

“…This paper considers one type of aerodynamic mechanism, termed microspoilers, which have been shown to be a promising control mechanism in previous investigations [13][14][15]. Microspoilers are small flow-effector mechanisms that extend orthogonally to the projectile body and are typically located between the rear stabilizing fin sets of a finned projectile.…”

Section: Introductionmentioning

confidence: 99%

“…Microspoilers were originally introduced as a candidate control mechanism by Dykes et al [13], who predicted the control authority induced by the mechanism using aerodynamic coefficients obtained through computational fluid dynamics (CFD). In a subsequent experimental study, Scheuermann et al [14] constructed a small-scale finned projectile with statically deployed microspoilers and obtained spark range measurements that were used to estimate aerodynamic coefficients. 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.…”

Section: Introductionmentioning

confidence: 99%

See 4 more Smart Citations

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

Kim

Strickland

Gross

et al. 2017

Journal of Dynamic Systems, Measurement, and Control

Self Cite

View full text Add to dashboard Cite

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.

show abstract

Section: Microspoiler Actuationmentioning

confidence: 80%

Section: Introductionmentioning

confidence: 93%

Section: Flight Experimentsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

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

Kim

Strickland

Gross

et al. 2017

Journal of Dynamic Systems, Measurement, and Control

Self Cite

View full text Add to dashboard Cite

show abstract

Study on performance degradation and failure analysis of machine gun barrel

Zang

et al. 2020

Defence Technology

View full text Add to dashboard Cite

Aerodynamic Layout Designs Using of Microflaps for Flow Control of a Supersonic Finned Projectile

Kang

Wang

et al. 2019

西北工业大学学报

View full text Add to dashboard Cite

In this paper, the flow control system consists of some small microflaps located between the rear fins of the projectile. These microflaps can alter the flow field in the finned region of the projectile resulting in asymmetric pressure distribution and thus producing control forces and moments, furthermore to provide directional control for a supersonic projectile. Due to the small size and high speed characteristics of projectile, which is with fast and valid response characteristics, this flow control system has initially shown excellent potential in terms of supersonic flow control. The CFD simulation used here solves steady-state Reynolds-averaged Navier-Stokes equation with two-equation turbulence model k-ε. Firstly, we investigate the flow mechanism around microflap in supersonic flow, the flow fields around the microflap are complex, involving three-dimensional shock-shock, shock-boundary layer interactions. Secondly, for the microflap and the fin of Basic Finner configuration, the influence of microflap geometric parameters, microflap locations on aerodynamics is obtained and the interference mechanism is explored. Finally, several typical roll and pitch control layouts are described. According to the simulation results and their analysis, some preliminary conclusions can be drawn: by analyzing the flow interference mechanism between microflap and the fin, we find that the separated shocks ahead of the microflap, the bow shocks around microflap, and the trailing-edge wake, have influences on fin's surface pressure; among these factors, the bow shocks are stronger than separated shocks, furthermore it can generate larger high pressure region. Then we find out the aerodynamic characteristics of several typical control layouts at a supersonic speed, Ma=2.5, furthermore, hence nearly 4.8% drag is increase compared with the condition without microflap. As the number of microflaps increasing, the control aerodynamic forces and moments increases almost linearly. With a proper layout of the microflap's location, quick change in the surface pressure distribution can be achieved for rear fins of the projectile, the microflap should be mounted that can increase the high pressure zone, meanwhile, reduce the low pressure zone on the surface of fins, thus modulating the projectile's attitude can be realized.

show abstract

Aerodynamic Characterization of a Microspoiler System for Supersonic Finned Projectiles

Cited by 14 publications

References 20 publications

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

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

Study on performance degradation and failure analysis of machine gun barrel

Aerodynamic Layout Designs Using of Microflaps for Flow Control of a Supersonic Finned Projectile

Contact Info

Product

Resources

About