The Role of Terrestrial and Space Environments in Launch Vehicle Development

Johnson, Dale L.; Vaughan, William W.

doi:10.5028/jatm.v11.1088

Cited by 4 publications

(2 citation statements)

References 11 publications

(17 reference statements)

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“…This is the third historical paper which concludes what the previous two papers Vaughan, 2019 andVaughan, 2020) presented, dealing with the subject of the role of the Earth's terrestrial and space natural environment involvement in launch vehicle design and development.…”

Section: Introductionmentioning

confidence: 59%

The Wind Environment Interactions Relative to Launch Vehicle Design

Johnson

Vaughan

2020

J.Aerosp. Technol. Manag.

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Section: Introductionmentioning

confidence: 59%

The Wind Environment Interactions Relative to Launch Vehicle Design

Johnson

Vaughan

2020

J.Aerosp. Technol. Manag.

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“…Речь идет о продольных и перерезывающих силах, изгибающих и крутящих моментах. Данные об указанных силовых факторах задействуют для прочностного анализа при проектировании новых изделий, экспериментальной отработке конструкции [1] и адаптации средств выведения под конкретный пуск [2]. Нагрузки подразделяются на квазистатические и динамические.…”

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Analytical solution to approximate equations of the launch vehicle motion under the gust action for the dynamic loading calculation

Malykhina

2022

Vestnik Donskogo gosudarstvennogo tehničeskogo universiteta

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Introduction. The launch vehicle (LV) in flight and the dynamic components of loads from the impact of a trapezoidal wind gust are considered. It is proposed to determine the dynamic components of the force factors using analytical solutions for the structure points accelerations. The work objective is to create a technique for selecting the duration of the standard gust, under the influence of which maximum loads are provided in the sections of the LV structure.Materials and Methods. The launch vehicle is presented as an uneven beam. The description of its vibrations is reduced to a system of independent ordinary differential equations that determine the motion of an equivalent system of oscillators. The equation of oscillator vibrations under the action of a trapezoidal pulse load is solved by the overlay method, and it is reduced to the calculation of the Duhamel integral. It is proposed to get the parameters of an equivalent system of oscillators based on the results of the calculation of dynamic characteristics for a finite element LV model in the Nastran program.Results. Analytical relations for the LV structure point accelerations under the action of a trapezoidal wind gust are given. For the beam model, test calculations of accelerations were carried out according to the technique proposed in this paper. These data are compared to the results of finite element modeling. With the help of analytical solutions, dependences are constructed that determine the nature of the change in the magnitude of the bending moment for different sections of the launch vehicle when the duration of the wind gust varies.Discussion and Conclusions. The presented technique provides building an equivalent dynamic model of systems with a large number of degrees of freedom on the example of a LV and obtaining analytical solutions for accelerations of points of a mechanical system under trapezoidal external action. These solutions are applicable for the study of dynamic loads. The analysis results enable to select the duration of the wind gust, at which maximum loads are reached in the sections of the LV structure. Calculations based on the analytical solutions are very economical in terms of time spent. They can be used in design calculations for preliminary assessment of loading.

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High-Fidelity Dynamics Modelling for the Design of a High-Altitude Supersonic Sounding Rocket

Milne

Samson

Carrese

et al. 2023

Designs

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The accurate modelling and simulation of vehicle dynamics is a fundamental prerequisite for the design and experimental flight testing of aerospace vehicles. In the case of high-altitude supersonic sounding rockets, it is critically important to produce realistic trajectory predictions in a representative range of operational and environmental conditions as well as to produce reliable probability distributions of terminal locations. This article proposes a methodology to develop high-fidelity flight dynamics models that accurately capture aeroelastic, turbulence, atmospheric and other effects relevant to sounding rockets. The significance of establishing a high-fidelity model and of addressing such a problem in the context of developing a digital twin are sed upfront, together with the key tools utilised in the analysis. In addition to state-of-the-art computational methods to determine the aerodynamic forces, moments and mass changes in various flight regimes (including parachute release), a detailed methodology for incorporating the dynamic aeroelastic response of the rocket is presented. The validity of the proposed method is demonstrated through a simulation case study, which utilises data from an existing rocket prototype. Results corroborate the correct implementation of the proposed algorithms and provide foundations for future research on virtual sensing and digital twin for autonomous navigation and guidance.

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The Role of Terrestrial and Space Environments in Launch Vehicle Development

Cited by 4 publications

References 11 publications

The Wind Environment Interactions Relative to Launch Vehicle Design

The Wind Environment Interactions Relative to Launch Vehicle Design

Analytical solution to approximate equations of the launch vehicle motion under the gust action for the dynamic loading calculation

High-Fidelity Dynamics Modelling for the Design of a High-Altitude Supersonic Sounding Rocket

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