Captive Carry Testing of Remotely Piloted Vehicles

Cross, Alvin

doi:10.1007/978-3-642-84010-4_29

Cited by 3 publications

(1 citation statement)

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“…Although general data for many SUAV are available, the data of airfoils specifically used for SUAV are not. One exception is the LAURA SUAV, which uses Eppler 201 (E201) airfoil (Cross 1989). Furthermore, E201 is a low Reynolds number airfoil that has a maximum thickness equivalent to the base airfoil NACA 0012.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Performance Estimation of Camber Morphing Airfoils for Small Unmanned Aerial Vehicle

Kumar

Venugopal

Ramakrishnananda

et al. 2020

J.Aerosp. Technol. Manag.

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This paper proposes a methodology to harvest the benefits of camber morphing airfoils for small unmanned aerial vehicle (SUAV) applications. Camber morphing using discrete elements was used to morph the base airfoil, which was split into two, three, and four elements, respectively, to achieve new configurations, into the target one. . In total, thirty morphed airfoil configurations were generated and tested for aerodynamic efficiency at the Reynolds numbers of 2.5 × 105 and 4.8 × 105, corresponding to loiter and cruise Reynolds numbers of a typical SUAV. The target airfoil performance could be closely achieved by combinations of 5 to 8 morphed configurations, the best of which were selected from a pool of thirty morphed airfoil configurations for the typical design specifications of SUAV. Interestingly, some morphed airfoil configurations show a reduction in drag coefficient of 1.21 to 15.17% compared to the target airfoil over a range of flight altitudes for cruise and loiter phases. Inspired by the drag reductions observed, a case study is presented for resizing a SUAV accounting for the mass addition due to the morphing system retaining the benefits of drag reduction.

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Section: Introductionmentioning

confidence: 99%

Aerodynamic Performance Estimation of Camber Morphing Airfoils for Small Unmanned Aerial Vehicle

Kumar

Venugopal

Ramakrishnananda

et al. 2020

J.Aerosp. Technol. Manag.

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AERODYNAMICS OFSMALLVEHICLES

Mueller

DeLaurier

2003

Annu. Rev. Fluid Mech.

550

222

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▪ Abstract In this review we describe the aerodynamic problems that must be addressed in order to design a successful small aerial vehicle. The effects of Reynolds number and aspect ratio (AR) on the design and performance of fixed-wing vehicles are described. The boundary-layer behavior on airfoils is especially important in the design of vehicles in this flight regime. The results of a number of experimental boundary-layer studies, including the influence of laminar separation bubbles, are discussed. Several examples of small unmanned aerial vehicles (UAVs) in this regime are described. Also, a brief survey of analytical models for oscillating and flapping-wing propulsion is presented. These range from the earliest examples where quasi-steady, attached flow is assumed, to those that account for the unsteady shed vortex wake as well as flow separation and aeroelastic behavior of a flapping wing. Experiments that complemented the analysis and led to the design of a successful ornithopter are also described.

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Test techniques for small-scale research aircraft

Tigner

Meyer

Holden

et al. 1998

16th AIAA Applied Aerodynamics Conference

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Small-scale aircraft provide a powerful tool for investigating the flying qualities of novel aircraft configurations. Testing procedures have been developed and applied to two small-scale research vehicles, the Blended Wing Body Flight Control Testbed (BWB) and the Oblique All Wing Unstable Demonstrator (OAW). These aircraft carry digital data acquisition and stability augmentation computers that support graphical analysis of flight data, enabling inthe-field evaluation and modification of control laws. The ability to evaluate dynamic behavior in the testing environment supports a creative, hands-on, iterative approach to aerodynamic experimentation and control law design. Methods developed for this research include several bench-top and static tests, an error analysis for measurement of the mass moments of inertia, and characterization of static engine performance. Dynamic car-top testing is used to simulate the dynamics and aerodynamics of flight, early flight-test rehearsals. Data collected in car testing and free flight is used to identify aerodynamic and dynamic characteristics of the configuration for use in future full-scale design and control law development.

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Captive Carry Testing of Remotely Piloted Vehicles

Cited by 3 publications

References 0 publications

Aerodynamic Performance Estimation of Camber Morphing Airfoils for Small Unmanned Aerial Vehicle

Aerodynamic Performance Estimation of Camber Morphing Airfoils for Small Unmanned Aerial Vehicle

AERODYNAMICS OFSMALLVEHICLES

Test techniques for small-scale research aircraft

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