An Experimental Investigation of the Transient Effects Associated with Wing Deployment During Ballistic Flight

Browning, Patrick; Cain, R; Labarbara, Kirk; Huebsch, Wade W.; Wilhelm, Jay

doi:10.4271/2011-01-2647

Cited by 8 publications

(2 citation statements)

References 5 publications

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“…Before determining which deployment condition was more effective, the model calculated if the wings were deployed using a body angle condition. Wind tunnel test data was collected for both conditions of deployed and non-deployed flight (Browning 2011), and the coefficients can be seen in Figure 14. However, the data was reference to the nose in this experiment, not the traditional chord and span of airplane aerodynamic data.…”

Section: Force Calculation Blockmentioning

confidence: 99%

Hybrid Projectile Body Angle Estimation for Selectable Range Increase

Gioia¹

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A Hybrid Projectile (HP) is a tube launched munition that transforms into a gliding UAV, and is currently being researched at West Virginia University. A simple launch timer was first envisioned to control the transformation point in order to achieve maximum distance. However, this timer would need to be reprogrammed for any distance less than maximum range due to the nominal time to deployment varying with launch angle. A method was sought for automatic wing deployment that would not require reprogramming the round. A body angle estimation system was used to estimate the pitch of the HP relative to the Earth to determine when the HP is properly oriented for the designed glide slope angle. It was also necessary to filter out noise from a simulated inertial measurement unit (IMU), GPS receiver, and magnetometer. An Extended Kalman Filter (EKF) was chosen to estimate the Euler angles, position and velocity of the HP while an algorithm determined when to deploy the wings. A parametric study was done to verify the optimum deployment condition using a Simulink aerodynamic model. Because range is directly related to launch angle, various launch angles were simulated in the model. By fixing the glide slope angle to-10° as a deployment condition for all launch angles, the range differed only by a maximum of 6.1% from the maximum possible range. Based on these findings, the body angle deployment condition provides the most flexible option to maintain maximum distance without the need of reprogramming. Position and velocity estimates were also determined from the EKF using the GPS measurements. Simulations showed that the EKF estimates exhibited low root mean squared error values, corresponding to less than 3% of the total position values. Because the HP was in flight for less than a minute in this experiment, the drift encountered was acceptable. I would also like to thank the other members of my thesis committee Dr. Wade Huebsch and Dr. Mridul Gautam for providing suggestions and edits on my thesis. Last but certainly not least, I would like to thank my mother, father and sister who gave me the confidence and encouragement to continue my education. I would not be where I am today without your love and support. Sincerely, Christopher J. Gioia Euler angle-roll rad or deg θ Euler angle-pitch rad or deg ψ Euler angle-yaw rad or deg ω Body angular velocity rad/s Body angular acceleration rad/s 2

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Section: Force Calculation Blockmentioning

confidence: 99%

Hybrid Projectile Body Angle Estimation for Selectable Range Increase

Gioia¹

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“…While work to date on Hybrid Projectiles has been somewhat limited, there has been some previous work on the design of stowable vehicles and of wing deployment mechanisms [2] [3]. The following discussion examines the deliberations made in pursuance of the development of an HP, in particular, as such development relates to deriving an effective wing planform.…”

Section: Motivationmentioning

confidence: 99%

Aerodynamics Investigation of Faceted Airfoils at Low Reynolds Number

Napolillo¹

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The desire and demand to fly farther and faster has progressively integrated the concept of optimization with airfoil design, resulting in increasingly complex numerical tools pursuing efficiency often at diminishing returns; while the costs and difficulty associated with fabrication increases with design complexity. Such efficiencies may often be necessary due to the power density limitations of certain aircraft such as small unmanned aerial vehicles (UAVs) and micro air vehicles (MAVs). This research, however, focuses on reducing the complexity of airfoils for applications where aerodynamic performance is less important than the efficiency of manufacturing; in this case a Hybrid Projectile. By employing faceted sections to approximate traditional contoured wing sections it may be possible to expedite manufacturing and reduce costs. We applied this method to the development of a low Reynolds number, disposable Hybrid Projectile requiring a 4.5:1 glide ratio, resulting in a series of airfoils which are geometric approximations to highly contoured cross-sections called ShopFoils. This series of airfoils both numerically and experimentally perform within a 10% margin of the SD6060 airfoil at low Re. Additionally, flow visualization has been conducted to qualitatively determine what mechanisms, if any, are responsible for the similarity in performance between the faceted ShopFoil sections and the SD6060. The data obtained by these experiments did not conclusively reveal how the faceted surfaces may influence low Re flow but did indicate that the ShopFoils did not maintain flow attachment at higher angles of attack than the SD6060. Two reasons are provided for the unexpected performance of the ShopFoil: one is related to downwash effects, which are suspected of placing the outer portion of the span at an effective angle of attack where the ShopFoils outperform the SD6060; the other is the influence of the tip vortex on separation near the wing tips, which possibly provides a 'comparative advantage' to the ShopFoil because it has more to gain from a reduction in its pressure drag component. Additionally, I appreciative of Dr. Loth for cultivating my conceptual understanding of fluid dynamics and thermodynamics as well as providing academic advice. Further, my thanks to Shanti Hamburg and Chris Menchini for offering guidance in developing my skills and understanding of Meshing and CFD. I appreciate the assistance from Dr. Xingbo Liu and Dr. Koorosh Mirfakhraie for recommending me to the WVU graduate engineering program. Thanks to Brian Parker for helping with my wind tunnel test preparations. To all of the influences throughout my life which gave rise to my interest in aeronautics, spaceflight, and the sciences.

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A Study of a Mobile Launch Platform Effect on Bi-folded Wing Deployment

Lee

Kim

et al. 2021

Int. J. Aeronaut. Space Sci.

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An Experimental Investigation of the Transient Effects Associated with Wing Deployment During Ballistic Flight

Cited by 8 publications

References 5 publications

Hybrid Projectile Body Angle Estimation for Selectable Range Increase

Hybrid Projectile Body Angle Estimation for Selectable Range Increase

Aerodynamics Investigation of Faceted Airfoils at Low Reynolds Number

A Study of a Mobile Launch Platform Effect on Bi-folded Wing Deployment

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