Online Four-Dimensional Flight Trajectory Search and its Flight Testing

AIAA Guidance, Navigation, and Control Conference and Exhibit ◽

10.2514/6.2005-6475 ◽

2005 ◽

Cited By ~ 9

Author(s):

Shinji Suzuki ◽

Yutaka Komatsu ◽

Satoshi Yonezawa ◽

Kazuya Masui ◽

Hiroshi Tomita

Keyword(s):

Flight Trajectory ◽

Flight Testing ◽

Trajectory Search

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A Study on Online Flight Trajectory Search and its Flight Simulator Testing

AIAA Infotech@Aerospace 2007 Conference and Exhibit ◽

10.2514/6.2007-2830 ◽

2007 ◽

Cited By ~ 1

Author(s):

Satoshi Yonezawa ◽

Masahiro Miwa ◽

Takeshi Tsuchiya ◽

Shinji Suzuki ◽

Nobuhiro Yokoyama

Keyword(s):

Flight Simulator ◽

Flight Trajectory ◽

Trajectory Search

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

Journal of Dynamic Systems Measurement and Control ◽

10.1115/1.4036808 ◽

2017 ◽

Vol 139 (11) ◽

Author(s):

Dooroo Kim ◽

Laura Strickland ◽

Matthew Gross ◽

Jonathan Rogers ◽

Mark Costello ◽

...

Keyword(s):

Lateral Acceleration ◽

Shock Interaction ◽

Frequency Data ◽

Flight Trajectory ◽

Flight Testing ◽

Flight Tests ◽

Smart Weapons ◽

Control Authority ◽

Computational Fluid Dynamics Cfd ◽

Actuator Design

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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