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Introduction
Published in Pylyp Volodin, Blade Element Rotor Theory, 2023
An essential part of the simulator software is a flight dynamics application, which performs computations of an aircraft motion in the airspace. The flight dynamics generally solves the equations of motion of the aircraft as a rigid body under the actions of forces and moments, which appear at the interaction of the aircraft with the air. These forces and moments are supported by power of an engine or engines of an aircraft. The flight dynamics of an aircraft can be realized as a set of elements, each of which represents a separate source of forces and moments affecting the simulated aircraft. For example, the flight dynamics of a helicopter with a single-rotor configuration can be simplistically decomposed into the following separate force source elements: a main rotor, a tail rotor, a fuselage, gears as interaction with the ground, and the gravity. Each element is described by a correspondent model, which computes element forces and moments acting on the aircraft and is based on the nature of this element. Each element model is a part of the aircraft flight dynamics software. All element models compose the superposition of forces and moments, based on which the aircraft motion is computed.
Real-Time Vision-Based Aircraft Vertical Tail Damage Detection and Parameter Estimation
Published in IETE Journal of Research, 2022
Kishan S. Chowhan, Hemendra Arya, Vijay V. Patel, Girish S. Deodhare
In this paper, we will discuss the vision techniques for reliable, fast, and accurate detection of fault for damage specific to the vertical tail [3–6] of a fighter aircraft. The fault in an aircraft is mainly attributed to three types, i.e. actuator fault, sensor fault, or physical damage to the aircraft structure. Of the three, structural damage is the least researched topic due to the non-availability of the test data. It is known that the damage to aircraft’s geometric shape greatly modifies the aerodynamic characteristics, often represented by stability and control derivatives. It also results in abrupt deterioration of flight performance and handling quality, which impairs safety. Flight dynamics for a general aircraft are developed to account for changes in aerodynamics, mass properties, and the center of gravity that can compromise the stability of the damaged aircraft.
High downforce race car vertical dynamics: aerodynamic index
Published in Vehicle System Dynamics, 2018
Felipe Pereira Marchesin, Roberto Spinola Barbosa, Marco Gadola, Daniel Chindamo
In general, the pitch moment coefficient is not used by the motorsport industry. The race car manufacturers supply a parameter called aerobalance [16,17–20], it represents the percentage of the total downforce acting on the vehicle front axle. It is very useful for quasi-static analysis as it is compared to the vehicle static weight distribution in order to have an idea of how much understeer/oversteer tendency (i.e. car balance) is expected at high speeds. For the purpose of this work it is not the main parameter to be analysed. Aerobalance is not directly a function of speed, it changes because of sprung mass movements. The pitch moment is the pitch moment coefficient multiplied by the dynamic pressure, which makes the moment increase with the square of speed. Also the pitch moment coefficient is a combination of both downforce coefficient and aerobalance, as showed in Equation (11). This means that it combines the variation of both. As an example, increases of aerobalance with decrease of downforce do not change aerodynamic pitch moment and aren’t important from the pitch performance/stability point of view. The pitch moment coefficient is also used by the aerospace industry to analyse flight dynamics [21].
Industry 4.0: state of the art and future trends
Published in International Journal of Production Research, 2018
In Industry 4.0, complex engineering problems have to be jointly solved by multi-disciplinary teams with multitudinous computational software and physical systems. The efficiency and effectiveness of solving complex engineering problems largely depend on strategic collaboration (Schuh et al. 2014), seamless integration of disparate CPS, and integration of heterogeneous data. Wang (2016) presents a multidisciplinary design and analysis (MDA) environment in conjunction with its application to aircraft flight dynamics analyses. The MDA infrastructure has built a cybernetic platform that integrates structure analysis and flow computation systems with wind tunnel experiment systems; moreover, this reconciles and interoperates diverse data sources generated by the CPS.