Deployment dynamics analysis of CALLISTO’s approach and landing system

Schneider, Anton; Desmariaux, Jean; Klevanski, Josef; Schröder, Silvio; Witte, Lars

doi:10.1007/s12567-021-00411-2

Cited by 2 publications

(1 citation statement)

References 4 publications

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“…Particular attention is paid to the possibility of the stage reusability and study of the aspect under consideration. A more in-depth explanation of how CALLISTO's deployment system operates and how it is affected by the influence of aerodynamics, exhaust plume, and vehicle's attitude is discussed in article [74]. The reference trajectory for CALLISTO, which is similar to the one used by most LVs utilizing the soft-landing method, is provided in Figure 9c.…”

Section: Soft-landing Techniquesmentioning

confidence: 99%

Methods for the Calculation and Control of Launch Vehicle Drop Regions

et al. 2023

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The article aims at reviewing the drop regions (DR) of the launch vehicles (LV) separating parts (SP) and methods of their determination. The DRs include sea and land areas; going beyond them is associated with a number of environmental, economic, and political factors. Their combination dictates the need to ensure the safety of the people, transport, infrastructure, and environment from the negative impact of LV SPs and fuel residues. The Monte Carlo method is mostly used to determine the impact areas. It enables an estimation of the probability of the SPs of LVs falling in certain areas, constituting the DRs. These points are varied according to a set of different initial parameters. The methods of controlling the impact areas are contingently divided into engineering (based on a change in the design appearance of the LV), mathematical (which includes the changes in or optimization of the LV’s trajectory or its SP), and “soft landing” (implying the return of the LV’s to the spaceport or to a certain prepared area). The present analysis can be used as a starting point when choosing a method for determining and controlling the projected LVs and the SPs’ area of impact.

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Section: Soft-landing Techniquesmentioning

confidence: 99%

Methods for the Calculation and Control of Launch Vehicle Drop Regions

et al. 2023

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Physical Modeling and Simulation of Reusable Rockets for GNC Verification and Validation

Farì,

Sagliano,

Macés Hernández

et al. 2024

Aerospace

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Reusable rockets must rely on well-designed Guidance, Navigation and Control (GNC) algorithms. Because they are tested and verified in closed-loop, high-fidelity simulators, emphasizing the strategy to achieve such advanced models is of paramount importance. A wide spectrum of complex dynamic behaviors and their cross-couplings must be captured to achieve sufficiently representative simulations, hence a better assessment of the GNC performance and robustness. This paper focuses on of the main aspects related to the physical (acausal) modeling of reusable rockets, and the integration of these models into a suitable simulation framework oriented towards GNC Validation and Verification (V&V). Firstly, the modeling challenges and the need for physical multibody models are explained. Then, the Vertical Landing Vehicles Library (VLVLib), a Modelica-based library for the physical modeling and simulation of reusable rocket dynamics, is introduced. The VLVLib is built on specific principles that enable quick adaptations to vehicle changes and the introduction of new features during the design process, thereby enhancing project efficiency and reducing costs. Throughout the paper, we explain how these features allow for the rapid development of complex vehicle simulation models by adjusting the selected dynamic effects or changing their fidelity levels. Since the GNC algorithms are normally tested in Simulink®, we show how simulation models with a desired fidelity level can be developed, embedded and simulated within the Simulink® environment. Secondly, this work details the modeling aspects of four relevant vehicle dynamics: propellant sloshing, Thrust Vector Control (TVC), landing legs deployment and touchdown. The CALLISTO reusable rocket is taken as study case: representative simulation results are shown and analyzed to highlight the impact of the higher-fidelity models in comparison with a rigid-body model assumption.

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Deployment dynamics analysis of CALLISTO’s approach and landing system

Cited by 2 publications

References 4 publications

Methods for the Calculation and Control of Launch Vehicle Drop Regions

Methods for the Calculation and Control of Launch Vehicle Drop Regions

Physical Modeling and Simulation of Reusable Rockets for GNC Verification and Validation

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