Multidisciplinary design optimization of sounding rocket fins shape using a tool called MDO-SONDA

Barbosa, Alexandre Nogueira; Guimarães, Lamartine Nogueira Frutuoso

doi:10.5028/jatm.2012.04044412

Cited by 8 publications

(3 citation statements)

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“…It includes studies on issues such as aviation design problems, aerodynamics, structural components, propulsion, flight mechanics, control, manufacturing and maintenance [1][2][3]. Another rocket component to be considered in rocket designs is nose cones.…”

Section: Introductionmentioning

confidence: 99%

Investigation of Flight Performance of Notched Delta Wing Rockets on Different Types of Nose Cones

ÖZEL,

MACİT,

ÖZEL

2023

Turkish Journal of Science and Technology

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In this study, four solid fuel model rockets with conical, parabolic, power and haack series nose cones that can carry 4 kg payload at an average altitude of 3 km were designed in the OpenRocket program. Later, the notched delta fin model was mounted on these designed model rockets. The effects of this fin model on the changes in the speed, stability, acceleration, weight and altitude of the rockets were analyzed numerically in the OpenRocket program. As a result of the analysis, it was determined that the conical nose rocket showed the worst flight performance and the Haack series nose cone rocket model showed the best performance. When used with the notched delta fin of the Haack series model, it was determined that the rocket's altitude increased by 7.67%, and its speed increased by 1.83%, but decreased by 1.2% in mach number, 0.6% in weight, 0.3% in acceleration, and 4.5% in stability. As a result, it was seen that it would be beneficial to consider the nose cone and fin together when evaluating the flight performance of the rocket. The results obtained in the study have shown that the notched delta fin model can be used experimentally in defense industry and model rocket applications and the studies can be advanced.

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Section: Introductionmentioning

confidence: 99%

Investigation of Flight Performance of Notched Delta Wing Rockets on Different Types of Nose Cones

ÖZEL,

MACİT,

ÖZEL

2023

Turkish Journal of Science and Technology

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“…In the field of aerodynamics and aircraft design, maximizing the lift-to-drag ratio is a critical objective for achieving optimal performance and efficiency. It was discovered that, utilizing the proposed technique, the drag caused by the rocket fins may be reduced by up to 29% without increasing the probability of undesirable effects leading to unstable behavior (Barbosa and Guimãraes, 2012). To achieve an optimal lift-to-drag ratio, engineers and researchers employ various optimization techniques.…”

Section: Introductionmentioning

confidence: 99%

Design Optimization of Fins of a Sounding Rocket for Maximum Lift-to-Drag Ratio and Minimum Radar Cross- Section Area Using ANSYS

Shah,

Sah

2023

Int. J. Engin. Technol.

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The optimization of a sounding rocket's fins is a crucial part of improving its performance. The geometric optimization of a sounding rocket's fins is presented in this paper. The main goal is to optimize the geometry for the minimum radar cross-section area and maximum lift-to-drag ratio. In CATIA, a 3D model was created. The L/D ratio was maximized using the ANSYS adjoint solver, and the radar cross-section area was minimized using ANSYS optimetrics. To determine the total RCS, the RCS of each fin was determined individually and then added together. Root, leading edge, tip, and trailing edge were the four parameters that were defined for the RCS optimization. The L/D ratio was increased by 8.3 times, and the RCS was decreased by 12% after optimization. Additionally, the body surface can be optimized further. The missile industry can benefit from the paper's findings.

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“…The VS-40 is a Brazilian solid fuel sounding rocket developed by IAE distributed between the first stage S40TM (4200 kg) engine and the second stage S44M (810 kg) engine. It is a non-controlled, unmanned and high performance space vehicle [6].The first stage includes the engine, rear gables and a front skirt, and the second stage, a second propellant, a base instrumentation and a hood, to store payloads. This configuration corresponds to the upper stages of the Brazilian Satellite Launch Vehicle (VLS-1) rocket (https://en.wikipedia.org/wiki/VS-40).…”

Section: Introductionmentioning

confidence: 99%

Analysis of the flow patterns on the fore-body section of a sounding vehicle in the transonic regime

Avelar

Basso

Filho

et al. 2018

J Braz. Soc. Mech. Sci. Eng.

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The present study has the purpose of presenting a numerical and experimental analysis of the flow patterns on the fore-body section of a sounding rocket model in the transonic regime. The measurements were carried out in the Pilot Transonic Wind Tunnel, known as TTP, at the Instituto de Aeronáutica e Espaço (IAE), in São José dos Campos, Brazil, for Mach numbers ranging from 0.6 to 1.06 and zero angle of attack. The experimental techniques of pressure taps, pressure-sensitive paint (PSP) and schlieren visualization method were performed on a 1:34 scaled model of a sounding rocket. Complex phenomena as shock waves, boundary layer detachment, and expansion waves were clearly identified from the PSP pressure field and from the schlieren images. Good agreements between the PSP, pressure taps and numerical simulation results were observed, except around the tip of the model because of the curvature and also in details that were not captured by the camera.

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Multidisciplinary design optimization of sounding rocket fins shape using a tool called MDO-SONDA

Cited by 8 publications

References 0 publications

Investigation of Flight Performance of Notched Delta Wing Rockets on Different Types of Nose Cones

Investigation of Flight Performance of Notched Delta Wing Rockets on Different Types of Nose Cones

Design Optimization of Fins of a Sounding Rocket for Maximum Lift-to-Drag Ratio and Minimum Radar Cross- Section Area Using ANSYS

Analysis of the flow patterns on the fore-body section of a sounding vehicle in the transonic regime

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