Low cost development of a nonlinear simulation for a flexible uninhabited air vehicle

Kotikalpudi, Aditya; Moreno, Claudia P.; Taylor, Brian; Pfifer, Harald; Balas, Gary J.

doi:10.1109/acc.2014.6859455

Cited by 8 publications

(9 citation statements)

References 25 publications

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“…The mass properties of the aircraft were obtained from experiments reported by Ref. 7. The estimates of inertia and center of gravity are summarized in the Table 1.…”

Section: Body Freedom Flutter Aircraftmentioning

confidence: 99%

“…The length of each wing (nodes 4-8 and 9-13) is taken as 1.27 m with a sweep angle of 22 deg. The wing is discretized in 4 elements to take into account the point masses of the actuators corresponding to inboard flaps (5,10), mid-board flaps (6,11) and outboard flaps (7,12). The winglets are located at nodes 8 and 13.…”

Section: Finite Element Modelmentioning

confidence: 99%

“…Actuators for the body and outboard flaps weigh approximately 65 g, actuators for the inboard and middle flaps weigh 50 g, winglets are 50 g, batteries 2.25 kg, propulsion motor 200 g and electronics 150 g. Lastly, additional inertia is located at the center of gravity to account for the use of lumped masses and match the total aircraft inertia which has been obtained from swing tests in Ref. 7. Table 3 shows the natural frequencies computed using the assembled mass and stiffness matrices of the structure and compares these results with the identified frequencies from the GVT.…”

Section: Wing Dynamic Testsmentioning

confidence: 99%

“…Similarly the distributed mass in the wings µ wing is allowed to vary in a large interval. Lastly, additional local masses and inertias are added to the wing nodes (4)(5)(6)(7)(8)(9)(10)(11)(12)(13) . As mentioned previously, the aircraft roll inertia value obtained from experiments has poor accuracy, hence, variations in the roll inertia of each node are allowed in both wings and center of gravity.…”

Section: Va Parameter Selection: Allowable Variation and Constraintsmentioning

confidence: 99%

“…Flutter analysis of aircraft has been widely studied in the literature [1][2][3][4] and numerous researchers have addressed aeroelastic modeling for highly flexible aircraft. [5][6][7] Currently, modeling aeroelastic behavior of flexible aircraft requires the development of a structural model coupled with an aerodynamic model. The nonlinear aeroelastic models are derived based on structural finite elements (FE) and lifting surface theory, both of which are available in general purpose commercial code.…”

Section: Introductionmentioning

confidence: 99%

See 4 more Smart Citations

Updating a finite element based structural model of a small flexible aircraft

Gupta

Moreno

Pfifer

et al. 2015

AIAA Modeling and Simulation Technologies Conference

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“…The mass properties of the aircraft were obtained from experiments reported by Ref. 7. The estimates of inertia and center of gravity are summarized in the Table 1.…”

Section: Body Freedom Flutter Aircraftmentioning

confidence: 99%

Section: Finite Element Modelmentioning

confidence: 99%

Section: Wing Dynamic Testsmentioning

confidence: 99%

Section: Va Parameter Selection: Allowable Variation and Constraintsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Updating a finite element based structural model of a small flexible aircraft

Gupta

Moreno

Pfifer

et al. 2015

AIAA Modeling and Simulation Technologies Conference

Self Cite

View full text Add to dashboard Cite

Methods for accurate measurements of small fixed wing UAV inertial properties

2016

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Two methods have been compared for the determination of the inertial properties of a small, fixed-wing un-manned aerial vehicle. The first method uses the standard single degree of freedom pendulum method and the second method implements a novel, potentially easier, 3 degrees of freedom pendulum method, which yields the entire inertia tensor from a single swing test. Both methods are using system identification of the pendulum motion to estimate the inertial properties. Substantial corrections (up to 25%) have to be applied to the experimental results. These corrections are caused by the acceleration of the pendulum being immersed in the surrounding air, also called the added mass effect. It has been found that the methods presented in literature to determine the corrections for full-scale aircraft do not give the correct results for the small-scale un-manned aerial vehicle under consideration. The only feasible, cost-effective method to generate these corrections utilise swing tests with a geometrically similar object of known inertial properties. It has also been found that the corrections are unique with respect to the experimental methods. Several benchmarking methods, including the innovative use of static and dynamic wind-tunnel test data, give high confidence in the results.

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Wilberforce pendulum: modelling linearly damped coupled oscillations of a spring-mass system

Uy¹,

Yuan²,

Chai³

et al. 2021

Eur. J. Phys.

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The Wilberforce pendulum is a coupled spring-mass system, where a mass with adjustable moment of inertia is suspended from a helical spring. Energy is converted between the translational and torsional modes, and this energy conversion is most clearly observed at resonance, which occurs when the damped natural frequencies of the two oscillation modes are equal. A theoretical model—with energy losses due to viscous damping accounted for—was formulated using the Lagrangian formalism to predict the pendulum mass’ trajectory. Theoretical predictions were compared with experimental data, showing good agreement. Fourier analysis of both theoretical predictions and experimental data further corroborate the validity of our quantitative model. The dependence of oscillation features like beat frequency and maximum conversion amplitude on relevant parameters such as the initial vertical displacement, initial angular displacement and moment of inertia was also investigated and experimentally verified.

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Low cost development of a nonlinear simulation for a flexible uninhabited air vehicle

Cited by 8 publications

References 25 publications

Updating a finite element based structural model of a small flexible aircraft

Updating a finite element based structural model of a small flexible aircraft

Methods for accurate measurements of small fixed wing UAV inertial properties

Wilberforce pendulum: modelling linearly damped coupled oscillations of a spring-mass system

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