Preliminary Design Estimation of the V/STOL Airplane Performance

Bronz, Murat; Drouin, Antoine

doi:10.1260/1756-8293.7.4.449

Cited by 11 publications

(5 citation statements)

References 5 publications

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“…9 Additional viscous drag, moment, and equilibrium case calculations are added by Bronz and Drouin. 10 The method has been already explained completely with detail in those references, 9, 10 however in order to keep the consistency of this paper, the main points will be repeated in the following subsections.…”

Section: Aerodynamic Model For Propeller Wing Combinationmentioning

confidence: 99%

Development of A Fixed-Wing mini UAV with Transitioning Flight Capability

Bronz

Smeur

Marina

et al. 2017

35th AIAA Applied Aerodynamics Conference

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This study presents the development of the transitioning vehicle Cyclone, which has been specifically designed for meteorological and agricultural applications. The mission requirements demand takeoff and landing from a small area and the ability to cope with high wind speeds. In contrast with recent suggestions, our proposed design aims to be closer to a fixed-wing airplane rather than a rotary wing. In particular, the design focuses on a tiltbody style transitioning vehicle with blown-wing concept. The propeller wing interaction is calculated using a semi-empirical method. The total wing span and wing surface area are decided according to the mission performance requirements. For the control of the vehicle, incremental nonlinear dynamic inversion is used. This control method does not need the modeling of external forces or moments and is able to counteract the strong aerodynamic forces and moments acting on the vehicle through the feedback of its angular acceleration. Together with the design phases and manufacturing process, several test flights are presented. Particular difficulties of the proposed design are discussed, including lack of providing sufficient pitch-up moment and control reversal during descent. The test flights demonstrate the vertical takeoff and landing capabilities of the vehicle, as well as its transitioning into forward flight from hovering, and vice versa, for an efficient mission performance.

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Section: Aerodynamic Model For Propeller Wing Combinationmentioning

confidence: 99%

Development of A Fixed-Wing mini UAV with Transitioning Flight Capability

Bronz

Smeur

Marina

et al. 2017

35th AIAA Applied Aerodynamics Conference

Self Cite

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“…Эти аспекты рассматриваются в авиа-и вертолетостроении при моделировании и осуществлении вертикальных взлетов (Vertical Takeoff and Landing, VTOL) и взлетов с коротким разбегом (Short Takeoff and Landing, STOL) [10,11,20,168,219,233,234]. Используем имеющийся опыт, накопленный в этих отраслях, привнеся при этом авторский графоаналитический подход.…”

Section: компоненты вектора трастаunclassified

Fundamentals of the quantum mobile theory

Kotikov¹

2021

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Рассмотрены достижения физики в области извлечения энергии физического вакуума квантовыми двигателями (КвД), перспективы внедрения КвД в объекты транспорта – квантомобили. Актуализировано формирование Теории квантомобиля. Проведены общие структурные построения Теории квантомобиля. Далее поочередно рассмотрены отдельные аспекты Теории. • Освещены понятия физического вакуума, концепции КвД, вопросы формирования и использования квантовой тяги (траста) КвД (трастера). • Рассмотрены вопросы продольного движения наземного квантомобиля. • Подключено рассмотрение движения квантомобиля в плоскости тангажа. • Сформированы 3D-модели пространственного использования траста. • Сформировано понятие Всесредного мультимодального квантомобиля (ВМК), рассмотрено наследование им свойств традиционных транспортных средств, затронуты аспекты математического моделирования ВМК. • Осуществлено расширение использования квантовой тяги КвД на класс подъемно-транспортных машин (портовых, карьерных), а также на железнодорожный транспорт. • Рассмотрено размещение трастеров на опытных концептах квантомобилей. Обобщены результаты, дан прогноз дальнейших исследований.

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“…The influence of each angle to the magnitude of generated thrust L z , drag force D F , and lift force L F can be calculated using blade element theory. 15,16 The vibrometer is in a static position and the propeller is in a dynamic state. Because the scanning process from laser vibrometer is faster than the propeller angular velocity, there is a “spacing” in which the laser does not read the value of propeller, as shown in Figure 3(a).…”

Section: Non-contact Vibration Analysis Techniquesmentioning

confidence: 99%

Analysis of quadcopter propeller vibration based on laser vibrometer

Kuantama

Moldovan

Ţarcă

et al. 2019

Journal of Low Frequency Noise, Vibration and Active Control

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An unbalanced propeller can affect a quadcopter's performance due to vibration, also decreasing its thrust's yield. Analyses were conducted to determine the correlation between vibration in the dynamic movement of a balanced and an imbalanced propeller using a laser vibrometer (portable digital vibrometer) PDV-100, to determine the correlation between propeller rotational speed and its vibration, as well as to determine the propeller's maximum rotational speed to avoid over-vibration. The vibration analysis was conducted on a carbon fiber 2-blade propeller by comparing the results of vibration tests with the propeller blade contour. The vibration response of the propeller has been analyzed at three points, respectively the hub, the center, and the tip of the blade, to determine the point having the largest value of the vibration on the propeller running at a maximum rotation speed of 7000 rpm. The same analysis was made on two propellers: the first one of type 1340 with a diameter of 13 inches and the second one of type 1447 with a diameter of 14 inches. The vibration was reduced by propeller's static balancing, thus increasing the propeller stability. The result showed that an imbalanced propeller generated a decrease in the rotational speed and higher vibration values compared to the balanced propeller. The vibration values showed a linear dependency to the rotor speed; the higher the speed, the bigger the vibration. The limit of rotational speed for the balanced model of the 1340 type propeller was 5000 rpm whilst the corresponding value for the 1447 type propeller was 4500 rpm. Finally, the result was used to optimize the propeller's overall performance.

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Preliminary Design Estimation of the V/STOL Airplane Performance

Cited by 11 publications

References 5 publications

Development of A Fixed-Wing mini UAV with Transitioning Flight Capability

Development of A Fixed-Wing mini UAV with Transitioning Flight Capability

Fundamentals of the quantum mobile theory

Analysis of quadcopter propeller vibration based on laser vibrometer

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