Titlebook: Lighter Than Air Systems; Proceedings of the I Dhwanil Shukla Conference proceedings 2023 The Editor(s) (if applicable) and The Author(s),

GLUE

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Designing Helium-Filled Aerostats Applying Scaling Procedure, Mini-Models CANDY and Fly-Tests on SKats dedicated to perform determined mission (between the altitudes . and .) will be discussed with preliminary experimental verification process, based on scaling procedure of aerostat mini-model, so-called CANDY, and fly-tests on SKYLAB will be proposed.

血统

Effect of Reynolds Number on the Aerodynamic Characteristics of Leading-Edge Protuberanced Airship ranced models at different Re are analysed in detail. Assessment of aerodynamic characteristics of modified leading-edge protuberanced fins under different Reynolds number is one of the immediate issues which needs to be addressed to bring such novel design in to airships and different kinds of LTA platform.

Lime石灰

滔滔不绝的人

Directed

V洗浴

Airship Sling-Load Operations: A Model Flight-Test Approach, controller and suitable airship configuration is the first step performed. Operational challenges during the flight missions result in learnings and observations of importance for performing such flight tests. Observations regarding maneuverability of the model help in improving the propulsion and controller configuration of heavy load airships.

dermatomyositis

A Multidisciplinary Design Optimisation (MDO) Algorithm for the Automatic Sizing of an Unmanned Ligof the mission affects the distribution of the masses in the airship, and therefore, how the optimal design and sizing change. Finally, further studies on the energy systems are presented, to verify the convenience of one option above the other one as a function of the distance from the mission location and the survey area.

fringe

Numerical Investigation of Laminar to Turbulent Boundary Layer Transition Over Airship Envelopes,urbulence model. The results obtained in numerical analysis are validated with the data available in the literature. It is seen that the two-equation k-ω SST turbulence model is not able to capture the laminar to turbulent transition, whereas the four-equation k-ω SST-LM transition turbulence model can capture it quite well.

CRUDE

Numerical Approach to Maneuver Design and Feasibility Evaluation for the Autonomy of Airship, pertaining to the imposed limitations on the lateral excursion, control, and state constraints. The effectiveness of the proposed maneuvers is then evaluated using numerical simulations with computed control schedules in an open-loop.