Effects of the rotational vehicle dynamics on the ascent flight trajectory of the SpaceLiner concept

Krummen, Sven; Sippel, Martin

doi:10.1007/s12567-018-0223-7

Cited by 6 publications

(3 citation statements)

References 11 publications

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“…These correlations have been developed in the past from an extensive range of experiments, in order to estimate aerodynamic coefficients of a vehicle from a simple parametrization of its geometry. Since these correlations require very little computational resources but commonly imply high uncertainty, these results are usually considered during the conceptual design phase only [23]. For CALLISTO these results have therefore only be used for cross-validation, particularly in flight conditions where the other datasets are very sparse.…”

Section: Semi-empirical Correlationsmentioning

confidence: 99%

Applying Bayesian Inference to Estimate Uncertainties in the Aerodynamic Database of CALLISTO

Krummen,

Tummala,

Wilken

et al. 2023

2023 IEEE Aerospace Conference

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The three national space centers DLR, CNES & JAXA have joined their efforts in the project CALLISTO to develop and mature key technologies for future operational Reusable Launch Vehicles (RLVs). The goal of this project is to develop, manufacture and test a reusable Vertical-Takeoff Vertical-Landing (VTVL) first stage demonstrator, which will be operated at the European Spaceport in French Guiana from late 2024.

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Section: Semi-empirical Correlationsmentioning

confidence: 99%

Applying Bayesian Inference to Estimate Uncertainties in the Aerodynamic Database of CALLISTO

Krummen,

Tummala,

Wilken

et al. 2023

2023 IEEE Aerospace Conference

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“…Aeroelastic instabilities are some of the critical issues affecting the reliability and safety of military and commercial aircraft [1][2][3]. The tri-wing configuration is usually adopted for large swept-back hypersonic flight vehicles [4,5], such as the American X-37B, the Soviet Union's Buran, the British Hotol, and the German Sanger [6][7][8]. The aileron structure of such flight vehicles is thin, which may lead to the flutter behavior.…”

Section: Introductionmentioning

confidence: 99%

Flutter Optimization of Large Swept-Back Tri-Wing Flight Vehicles

Wang,

Qian,

et al. 2023

Aerospace

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The aerodynamic configuration of large swept-back tri-wings is generally adopted for hypersonic vehicles, but the structural stiffness of the ailerons is weak, which may lead to damage due to the flutter behavior. In the initial stage of structural design, studying the flutter characteristics of tri-wing flight vehicles is necessary and can provide the stiffness index of the tri-wing structural design. To assess the flutter characteristics of tri-wing flight vehicles efficiently, a rapid modeling technique of the finite element method was used in this paper. For the structural scheme of large swept-back tri-wing flight vehicles, a structural dynamic model was modeled using the rapid modeling technique, the unsteady aerodynamic was computed using the double-lattice method, and the flutter characteristics were analyzed using the P-K method. Variable parametric studies were conducted to evaluate the effects of the stiffness of the aileron skin, the stiffness of the control mechanism, and the mass distribution of the aileron on the flutter characteristics of large swept-back tri-wing flight vehicles. The results showed that the key flutter coupling modes of such vehicles are symmetric and anti-symmetric combinations of aileron rotation and torsion. Additionally, optimizing the control mechanism stiffness and mass distribution of the aileron could improve the flutter boundary, which can be helpful in the structural design of such vehicles. The flutter optimization technique effectively improved the flutter boundary, significantly enlarged the flight envelope, and accurately provided the stiffness index for the structural design of large swept-back tri-wing flight vehicles.

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“…An alternative application of the suborbital flights is a point to point transportation. Studies on both spaceport and vehicles can be found in [3][4][5] and [6] The researchers from the Warsaw University of Technology were inspired by the Ansary X-Prize competition and begun to work on their own concept of vehicle for manned suborbital tourism flights [7,8]. The MAS (Modular Airplane System) project consists of two airplanes-a mother plane and a rocket plane (see Fig.…”

Section: Introductionmentioning

confidence: 99%

An investigation into directional characteristics of the rocket plane in a tailless configuration

Kwiek

Figat

2022

CEAS Space J

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This paper embraces result of wind tunnel tests of a rocket plane designed to space tourism application. The rocket plane is designed in a tailless configuration with a leading edge extension (LEX) and side plates on the wing’s tip which work as all moving tail. Usually for such a concept of control, movable surfaces are position in a horizontal direction while in the considered concept there is no classical rudder, and the movable surfaces are mounted with a significant dihedral angle. The research was carried out in the subsonic closed circuit wind tunnel with an open test section. Moreover, MGAERO and PANUKL package were used for numerical computations. The first research question is to investigate how the configuration of the side plate affects the directional stability of the rocket plane. The second aim is to study the efficiency of the side plates deflected like an all moving tail for both low and high angles of attack. As a result of this investigation, the directional stability derivatives and the control derivatives were obtained. Finally, the experimental results were compared with numerical outcomes to establish does software with no full flow model can be applicable for design an aircraft with all moving tail in case of low of angles of attack.

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Effects of the rotational vehicle dynamics on the ascent flight trajectory of the SpaceLiner concept

Cited by 6 publications

References 11 publications

Applying Bayesian Inference to Estimate Uncertainties in the Aerodynamic Database of CALLISTO

Applying Bayesian Inference to Estimate Uncertainties in the Aerodynamic Database of CALLISTO

Flutter Optimization of Large Swept-Back Tri-Wing Flight Vehicles

An investigation into directional characteristics of the rocket plane in a tailless configuration

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