Engineering Analysis for Rocket Sled Aerodynamics

Hegedus, Martin C.; Mendenhall, Michael R.; Perkins, S. C.; Stremel, Paul M.; Faltz, Judy A.

doi:10.2514/6.2006-664

Cited by 7 publications

(3 citation statements)

References 3 publications

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“…An engineering aerodynamic analysis tool called RSX (Rocket Sled eXpert) has been designed to achieve fast and accurate calculations of the aerodynamic characteristics of multistage rocket sled vehicles (8) . This integrated engineering-level aerodynamic analysis tool, sponsored by the US Air Force, is applicable to rocket sled vehicles at subsonic, transonic, supersonic, and hypersonic Mach numbers.…”

Section: Rsxmentioning

confidence: 99%

Corporate memory contribution to integrated design and analysis systems

Mendenhall

2006

Aeronaut. j.

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The recent decline in the USA aerospace industry has resulted in fewer programs, fewer engineers, and a potential loss of capability for future technology development. As engineers retire or leave the industry, their corporate memory or retained knowledge must be preserved for future use. A process to capture their expert knowledge is described, and a framework which provides a means to retrieve and use this valuable technical information is shown. Four examples of integrated design and analysis systems for four diverse technologies and applications are discussed.

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Section: Rsxmentioning

confidence: 99%

Corporate memory contribution to integrated design and analysis systems

Mendenhall

2006

Aeronaut. j.

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“…Lofthouse 12,13 designed and installed the deflector in front of the connecting device between the sled and the slipper and studied the pressure and temperature distribution of the flow field on the surface of the deflector under Ma = 2, 3, 4, and 5 using CFD methods. Hegedus 14 used CFD methods to compare the pressure distribution of the rocket sled flow field with and without a deflector, and the structured grid used improved the calculation accuracy. Zou 15 used the CFD methods to study the deflector behind the rocket sled and investigated the aerodynamic characteristics of the deflector when the incoming flow was Ma = 0.6-2.0.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic design optimization of a hypersonic rocket sled deflector using the free-form deformation technique

Dang

Hu³

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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An aerodynamic design optimization of a hypersonic rocket sled deflector is presented using the free-form deformation (FFD) technique. The objective is to optimize the aerodynamic shape of the hypersonic rocket sled deflector to increase its negative lift and enhance the motion stability of the rocket sled. The FFD technique is selected as the aerodynamic shape parameterization method, and the continuous adjoint method based on the gradient method is used to search the optimization in the geometric shape parameter space; the computational fluid dynamics method for a hypersonic rocket sled is employed. An automatic design optimization method for the deflector is carried out based on the aerodynamic requirements of the rocket sled. The optimization results show that the optimized deflector meets the design requirement of increasing the negative lift under the constraint of drag. By improving the pressure distribution on the surface of the deflector, the negative lift is increased by 7.39%, which confirms the effectiveness of the proposed method.

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“…A group of researcher developed an integrated aerodynamic analysis tool, a CBM-based tool, to analyze rocket systems [63]. In the conventional-aircraft design process, Roskam [6] uses CBM to predict the aerodynamic properties of conventional aircraft.…”

Section: The Simulation Results Show Thatmentioning

confidence: 99%

Computational investigation on aerodynamic and stability characteristics of a vertical take-off and landing micro air vehicle

Tobing¹

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This research focuses on the numerical investigation of the aerodynamic and stability characteristics of a Vertical Takeoff and Landing (VTOL) Micro Air Vehicle (MAV). The numerical investigation is divided into two parts: statics and dynamics. In the static analysis, the full configuration of the VTOL MAV as well as various design and operating parameters are investigated. The dynamic analysis is conducted to obtain the dynamic stability derivatives due to angular rate variations. Time and computational costs have always been the issue in the numerical investigation. As a solution, an innovative method termed the Improved-Component Buildup Method (I-CBM) is developed. The results obtained indicate that the VTOL MAV has favorable aerodynamic performances and static stability quality in the longitudinal and directional modes, although it tends to be unstable in the lateral mode. The results also show that the I-CBM provides fast and reasonably accurate prediction of the aerodynamic and stability properties of the MAV.

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Engineering Analysis for Rocket Sled Aerodynamics

Cited by 7 publications

References 3 publications

Corporate memory contribution to integrated design and analysis systems

Corporate memory contribution to integrated design and analysis systems

Aerodynamic design optimization of a hypersonic rocket sled deflector using the free-form deformation technique

Computational investigation on aerodynamic and stability characteristics of a vertical take-off and landing micro air vehicle

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