Integration Analysis of Conceptual Design and Stealth-Aerodynamic Characteristics of Combat Aircraft

Cheng, Long; Yue, Kuizhi; Guo, Wei; Yu, Dingwen

doi:10.5028/jatm.v8i1.514

Cited by 7 publications

(3 citation statements)

References 5 publications

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“…From Ansys flow simulation, it is obtained that this designed RC Aircraft have a lift force of 34.055757 N and Drag force of 10.117772N [1] and the simulation results is represented in Figure 9. Hand Launch: With the power off, the airplane was hand-launched from shoulder height.…”

Section: Resultsmentioning

confidence: 99%

Design, Analysis and making of RC Controlled Stealth Aircraft Working Model

A. K. Arun

2024

acsjse

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The project focused on the design, construction, and testing of a working model of an RC controlled stealth aircraft. A multidisciplinary approach was adopted, incorporating aerodynamics, electronics, materials, and control systems to achieve the desired performance. The aerodynamic design of the model involved careful consideration of the shape, contours, andsurfaces. The goal was to minimize radar reflections and reduce the infrared signature, leading to the incorporation of smooth and streamlined surfaces, blended wing profiles, and carefully shaped edges.RC channel mixing was implemented to coordinate the movements of control surfaces. This allowed for synchronized actions of ailerons, elevators, rudder, and flaps, facilitating precise maneuvering and stability during flight. By combining input signals from multiple control channels, the model's control surfaces operated seamlessly, emulating the behavior of larger stealth aircraft. The construction process focused on assembling a lightweight yet sturdy airframe using appropriate materials. Structural integrity was ensured to withstand the aerodynamic forces encountered during flight. Extensive testing and fine-tuning were conducted to optimize the model's performance, including stability, responsiveness, and stealth characteristics. The completion of the project resulted in a fully functional RC controlled stealth aircraft model.

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Section: Resultsmentioning

confidence: 99%

Design, Analysis and making of RC Controlled Stealth Aircraft Working Model

A. K. Arun

2024

acsjse

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“…Hoy en día existen investigaciones centradas en el diseño de aeronaves de quinta generación con el propósito de cumplir las necesidades de defensa en el futuro, estas proponen aviones polivalentes y aeronaves tripuladas (Liangliang et al, 2016), en este último caso, los diseños están enfocados en la superioridad aérea (Atique et al, 2016). También se ha combinado la quinta generación con aeronaves no tripuladas ucav, estas investigaciones incluyen conceptos como el de la inteligencia artificial para así eliminar cualquier dependencia de un piloto (Kong et al, 2020).…”

Section: Requerimientos De Diseñounclassified

Diseño de aeronave de combate no tripulada de quinta generación para el apoyo aéreo cercano

Aguirre

García

et al. 2021

Ciencia y Poder Aéreo

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La evolución en el diseño de aeronaves de combate se ha visto modificada por la inclusión de nuevos parámetros de alta exigencia, dentro de los cuales se incluyen las áreas de investigación relacionadas con la aerodinámica, la furtividad y la optimización en los procesos de operación. El presente artículo contempla el diseño de un Vehículo de Combate Aéreo no Tripulado (UCAV) para la ejecución de misiones de Apoyo Aéreo Cercano (CAS por sus siglas en inglés) en las próximas décadas. Los resultados obtenidos demuestran las habilidades de los UCAV como aeronaves de quinta generación para el reemplazo de flotas reconocidas a nivel mundial (A-10 Thunderbolt II y Sukhoi Su-25) y, además, garantiza su utilidad y viabilidad en los futuros entornos de combate. Así mismo, la investigación se enfoca en una de las variables de mayor discusión respecto a la supervivencia en el combate aéreo, se trata de la furtividad por fenómenos electromagnéticos, con la cual se obtuvieron valores de Sección Equivalente de Radar (RCS) iguales a -24,18 dBsm o representables en un área de detectabilidad de 0,0038 m2 en configuración limpia, de modo que este valor es inferior al de aeronaves furtivas como lo es el Northrop Grumman B-2 Spirit. Finalmente, el diseño permite la operación con un máximo peso de despegue de 61,900 lb y una carga paga de 11,240 lb que se acondicionan a una configuración alar y de estabilizadores para rangos transónicos.

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“…The development of science technology and optimization theory make it possible to achieve autonomous combat for armed helicopters in military warfare. 1,2 The integrated control technology is the inevitable trend in the development of modern aviation technology, especially for the use of integrated fire/flight control (IFFC) systems. The IFFC integrates the fire control system and flight control system into a closed-loop automatic weapon delivery system by using a fire/flight coupling controller.…”

Section: Introductionmentioning

confidence: 99%

Integrated fire/flight control coupler design for armed helicopters based on improved non-monotone adaptive trust region algorithm with distributionally robust optimization

Zhou

Wang

2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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Aiming at enhancing the extent of military automatization and the effectiveness of armed helicopters in complex battlefield environment, integrated fire/flight control (IFFC) coupler connects the fire control system and the flight control system which is used to generate the optimal flight command signals. However, it is difficult to obtain satisfactory flight command signals within a certain firing accuracy due to the unavoidable uncertain information in battlefield environment. In this paper, a new IFFC scheme is proposed for armed helicopters against complex combat by using the idea of distributionally robust optimization combined with the framework of trust region. Initially, a vector equation and coordinate transformation are employed to acquire the relative motion model of the IFFC coupler problem in complex battlefield environment. Moreover, an improved performance index is designed according to the constraints, and the original non-convex problem is handled by the Taylor formula combined with an improved BFGS (Broyden–Fletcher–Goldfard–Shanno) algorithm. Considering the uncertain parameters during optimization, the non-linear distributionally robust optimization is transformed into a linear matrix inequality optimization problem based on the worst-case conditional value-at-risk (WC-CVaR) approximation. Then, an algorithmic framework with a non-monotone adaptive trust region algorithm is given to obtain the optimal flight command signals. Finally, a simulation example is given to illustrate the effectiveness of the proposed approach.

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Integration Analysis of Conceptual Design and Stealth-Aerodynamic Characteristics of Combat Aircraft

Cited by 7 publications

References 5 publications

Design, Analysis and making of RC Controlled Stealth Aircraft Working Model

Design, Analysis and making of RC Controlled Stealth Aircraft Working Model

Diseño de aeronave de combate no tripulada de quinta generación para el apoyo aéreo cercano

Integrated fire/flight control coupler design for armed helicopters based on improved non-monotone adaptive trust region algorithm with distributionally robust optimization

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