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Relevant bibliographies by topics / Launch Vehicle Model

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Journal articles

Academic literature on the topic 'Launch Vehicle Model'

Author: Grafiati

Published: 6 September 2023

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Journal articles on the topic "Launch Vehicle Model"

1

You, Ming, Qun Zong, Bailing Tian, and Fanlin Zeng. "Nonsingular terminal sliding mode control for reusable launch vehicle with atmospheric disturbances." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 11 (2017): 2019–33. http://dx.doi.org/10.1177/0954410017708211.

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The controller design for reusable launch vehicles is challenging due to enormous amounts of model parameter uncertainties and atmospheric disturbances. This paper first derives six-degree-of-freedom model of a reusable launch vehicle with atmospheric disturbances. Next, four kinds of atmospheric disturbances are introduced and wind models are established respectively. For attitude control of the reusable launch vehicle, a nonsingular terminal sliding mode controller is designed with stability guaranteed. Finally, simulation results show a satisfactory performance for the attitude tracking of

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2

Gibson, Denton, Waldemar Karwowski, Timothy Kotnour, Luis Rabelo, and David Kern. "The Relationships between Organizational Factors and Systems Engineering Process Performance in Launching Space Vehicles." Applied Sciences 12, no. 22 (2022): 11541. http://dx.doi.org/10.3390/app122211541.

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The launch vehicle industry has long been considered a pioneering industry in systems engineering. Launch vehicles are large complex systems that require a methodical multi-disciplinary approach to design, build, and launch. Launch vehicles are used to deliver payloads—such as humans, robotic science missions, or national security payloads—to desired locations in space. Previous research has identified deficient or underperforming systems engineering as a leading contributor to launch vehicle failures. Launch vehicle failures can negatively affect national security, the economy, science, and s

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3

Hladkyi, Ye H., and V. I. Perlyk. "How Yuzhnoye develops models for flight safety index evaluation for the case of a rocket failure during the flight." Kosmičeskaâ tehnika. Raketnoe vooruženie 2023, no. 1 (2023): 14–30. http://dx.doi.org/10.33136/stma2023.01.014.

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Safety of the up-to-date rocket and space complexes remains a topical problem for the developers of rocket and space technology. The integral component of this problem along with the safety of operations during launch vehicle ground pre-launch processing is organization of flight safety. The basic task of this rocket and space complexes safety component is to prevent or minimize serious consequences in case of launch vehicle failure in the flight leg, after all such accidents can cause damage to the population and facilities (including personnel and facilities of the ground complex), located a

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4

Pu, Pengyu, and Yi Jiang. "Assessing Turbulence Models on the Simulation of Launch Vehicle Base Heating." International Journal of Aerospace Engineering 2019 (August 22, 2019): 1–14. http://dx.doi.org/10.1155/2019/4240980.

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Launch vehicles suffer from severe base heating during ascents. To predict launch vehicle base heat flux, the computational fluid dynamics (CFD) tools are widely used. The selection of the turbulence model determines the numerical simulation results of launch vehicle base heating, which may instruct the thermal protection design for the launch vehicle base. To assess performances, several Reynolds-averaged turbulence models have been investigated for the base heating simulation based on a four-nozzle launch vehicle model. The finite-rate chemistry model was used for afterburning. The results s

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5

da Cás, Pedro L. K., Carlos A. G. Veras, Olexiy Shynkarenko, and Rodrigo Leonardi. "A Brazilian Space Launch System for the Small Satellite Market." Aerospace 6, no. 11 (2019): 123. http://dx.doi.org/10.3390/aerospace6110123.

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At present, most small satellites are delivered as hosted payloads on large launch vehicles. Considering the current technological development, constellations of small satellites can provide a broad range of services operating at designated orbits. To achieve that, small satellite customers are seeking cost-effective launch services for dedicated missions. This paper deals with performance and cost assessments of a set of launch vehicle concepts based on a solid propellant rocket engine (S-50) under development by the Institute of Aeronautics and Space (Brazil) with support from the Brazilian

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6

Adelfang, S. I., O. E. Smith, and G. W. Batts. "Ascent wind model for launch vehicle design." Journal of Spacecraft and Rockets 31, no. 3 (1994): 502–8. http://dx.doi.org/10.2514/3.26467.

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7

Wang, J. T., G. Y. Hang, H. M. Shen, et al. "Numerical Simulation of Shock Wave Damage to Medium-Range and Long-Range Targets." Journal of Physics: Conference Series 2478, no. 2 (2023): 022002. http://dx.doi.org/10.1088/1742-6596/2478/2/022002.

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Abstract In order to accurately analyze the effect of a shock wave on a missile launch vehicle as a whole and on its components when the launch vehicle is at a medium or long distance from the detonation center, a simulation method based on the empirical algorithm and numerical analysis was carried out in this study. The method significantly reduced the computational cost while ensuring computational accuracy. Based on the simulation method, a finite element model for a typical missile launch vehicle was established that consisted of 2.5 million elements. Based on the structured arbitrary Lagr

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8

Golubek, A. V., and N. M. Dron'. "Launch Vehicle Rendezvous to Catalogued Orbital Debris while Injecting into Highly-Inclined Orbits." Nauka ta innovacii 16, no. 6 (2020): 46–55. http://dx.doi.org/10.15407/scin16.06.046.

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Introduction. A constant increase in the amount of space debris already constitutes a significant threat to satellites in nearEarth orbits, starting with the trajectory of their launch vehicle injection. Problem Statement. Design and development of various modern methods of protection against space debris requires knowledge of the statistical characteristics of the distribution of the kinematic parameters of the simultaneous motion of a launch vehicle injecting satellite and a group of space debris objects in the area of its trajectory. Purpose. Development of a mathematical model of a launch

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9

Golubek, A. V., and N. M. Dron'. "Launch Vehicle Rendezvous to Catalogued Orbital Debris while Injecting into Highly-Inclined Orbits." Science and innovation 16, no. 6 (2020): 46–55. http://dx.doi.org/10.15407/scine16.06.046.

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Introduction. A constant increase in the amount of space debris already constitutes a significant threat to satellites in nearEarth orbits, starting with the trajectory of their launch vehicle injection. Problem Statement. Design and development of various modern methods of protection against space debris requires knowledge of the statistical characteristics of the distribution of the kinematic parameters of the simultaneous motion of a launch vehicle injecting satellite and a group of space debris objects in the area of its trajectory. Purpose. Development of a mathematical model of a launch

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10

Peng, Bo, Cheng Ma, Guodong Wang, Fengyan Hu, Ke Mei, and Jian Yang. "An aerodynamic surrogate model of launch vehicle based on relevance vector machine." Journal of Physics: Conference Series 2181, no. 1 (2022): 012021. http://dx.doi.org/10.1088/1742-6596/2181/1/012021.

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Abstract In the process of launch vehicle multidisciplinary design optimization, aerodynamic calculation takes a long time, which affects the overall design cycle. In order to solve the above problems, based on the idea of machine learning, this paper constructs the surrogate model of relevance vector machine and calculates the aerodynamic coefficients of launch vehicles quickly. Firstly, the aerodynamic model of launch vehicle is established, and the orthogonal design method is used to generate test sample points. Then, the aerodynamic coefficients of the sample points are calculated by using

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